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{{#Wiki_filter:1) A     i   ,      t I ti       .                                                          COPY 2300 N Street, N.W.                 Tel 202.663.8000 Washington, D.C. 20037-1 128         F~ax 202.663.8007 www.pillsburylaw.coni MATIAS F. TRAVwEso-DIAZ 202-663-8142                                   DOCKETED Matias.travieso-diaz@pillsburylaw.comn           USNRC March 10, 2009 (3:02pm)
{{#Wiki_filter:1) A i
March 10, 2009                                       OFFICE OF SECRETARY RULEMAKINGS AND ADJUDICATIONS STAFF Alex S. Karlin, Esq., Chairman                   Administrative Judge                 .  '
t I
Atomic Safety and Licensing Board               Dr. William H. Reed Mail Stop T-3 F23                               Atomic Safety and Licensing Board U.S. Nuclear Regulatory Commission               Mail Stop T-3 F23 Washington, D.C. 20555-0001               '    U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 Administrative Judge Dr. Richard E. Wardwell Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, D.C. 20555-0001 In the Matter of Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc.
ti COPY 2300 N Street, N.W.
Tel 202.663.8000 Washington, D.C. 20037-1 128 F~ax 202.663.8007 www.pillsburylaw.coni MATIAS F. TRAVwEso-DIAZ 202-663-8142 DOCKETED Matias.travieso-diaz@pillsburylaw.comn USNRC March 10, 2009 (3:02pm)
March 10, 2009 OFFICE OF SECRETARY RULEMAKINGS AND ADJUDICATIONS STAFF Alex S. Karlin, Esq., Chairman Administrative Judge Atomic Safety and Licensing Board Dr. William H. Reed Mail Stop T-3 F23 Atomic Safety and Licensing Board U.S. Nuclear Regulatory Commission Mail Stop T-3 F23 Washington, D.C. 20555-0001 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 Administrative Judge Dr. Richard E. Wardwell Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, D.C. 20555-0001 In the Matter of Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc.
(Vermont Yankee Nuclear Power Station)
(Vermont Yankee Nuclear Power Station)
Docket No. 50-271-LR; ASLBP No. 06-849-03-LR Gentlemen:
Docket No. 50-271-LR; ASLBP No. 06-849-03-LR Gentlemen:
In accordance with the provisions of the Board's Partial Initial Decision (Ruling on Contentions 2A, 2B, 3, and 4), LBP-08-25, 68 N.R.C.             (Nov. 24, 2008), slip op. at 67, and the Board's Order (Clarifying Deadline for Filing New or Amended Contentions) (Mar. 9, 2009),
In accordance with the provisions of the Board's Partial Initial Decision (Ruling on Contentions 2A, 2B, 3, and 4), LBP-08-25, 68 N.R.C.
(Nov. 24, 2008), slip op. at 67, and the Board's Order (Clarifying Deadline for Filing New or Amended Contentions) (Mar. 9, 2009),
Entergy has revised and issued its final calculations of record for the confirmatory environmentally assisted fatigue (CUFen) analyses on the reactor pressure vessel core spray (CS) and recirculation outlet (RO) nozzles at the Vermont Yankee Nuclear Power Station. These revised analyses are presented in the following Structural Integrity Associates, Inc. (SIA) calculations: Calculation No. 0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.303, Revision 1, "Fatigue Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle;" Calculation No.
Entergy has revised and issued its final calculations of record for the confirmatory environmentally assisted fatigue (CUFen) analyses on the reactor pressure vessel core spray (CS) and recirculation outlet (RO) nozzles at the Vermont Yankee Nuclear Power Station. These revised analyses are presented in the following Structural Integrity Associates, Inc. (SIA) calculations: Calculation No. 0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.303, Revision 1, "Fatigue Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle;" Calculation No.
0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle;" and Calculation No. 0801038.306, Revision 1, "Fatigue Analysis of Reactor Recirculation Outlet Nozzle." Calculation 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle" has not been revised so that the version sent to the parties on January 8, 2009 remains the final calculation of record.
0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle;" and Calculation No. 0801038.306, Revision 1, "Fatigue Analysis of Reactor Recirculation Outlet Nozzle." Calculation 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle" has not been revised so that the version sent to the parties on January 8, 2009 remains the final calculation of record.
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March 10, 2009 Page 2 Entergy is serving at this time electronic copies of those analyses on the parties to the above captioned proceeding. Hard copies are also being sent today by overnight mail to the NRC Staff, the New England Coalition and the Vermont Department of Public Service.
March 10, 2009 Page 2 Entergy is serving at this time electronic copies of those analyses on the parties to the above captioned proceeding. Hard copies are also being sent today by overnight mail to the NRC Staff, the New England Coalition and the Vermont Department of Public Service.
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CERTIFICATE OF SERVICE I hereby certify that copies of the foregoing letter were served on the persons listed below by deposit in the U.S. Mail, first class, postage prepaid; where indicated by an asterisk, by electronic mail; and where indicated by a double asterisk, by both overnight and electronic mail, this 1 0 th day of March, 2009.
CERTIFICATE OF SERVICE I hereby certify that copies of the foregoing letter were served on the persons listed below by deposit in the U.S. Mail, first class, postage prepaid; where indicated by an asterisk, by electronic mail; and where indicated by a double asterisk, by both overnight and electronic mail, this 1 0 th day of March, 2009.
*Administrative Judge                                    *Administrative Judge Alex S. Karlin, Esq., Chairman                           Dr. Richard E. Wardwell Atomic Safety and Licensing Board                       Atomic Safety and Licensing Board Mail Stop T-3 F23                                        Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission                      U.S. Nuclear Regulatory Commission Washington, DC 20555-0001                                Washington, DC 20555-0001 ask2(@nrc.gov                                            rew(anrc.gov
*Administrative Judge Alex S. Karlin, Esq., Chairman Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 ask2(@nrc.gov
*Administrative Judge
*Administrative Judge Dr. William H. Reed 1819 Edgewood Lane Charlottesville, VA 22902 whrcville(ieinbarqmail.com
* Secretary Dr. William H. Reed                                     Att'n: Rulemakings and Adjudications Staff 1819 Edgewood Lane                                       Mail Stop 0-16 CI Charlottesville, VA 22902                               U.S. Nuclear Regulatory Commission whrcville(ieinbarqmail.com                               Washington, DC 20555-0001 secy(anrc.gov, hearingdocket(Dnrc. gov
*Office of Commission Appellate Adjudication Mail Stop 0-16 C1 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 OCAAmaila~nrc.gov
*Office of Commission Appellate Adjudication             Atomic Safety and Licensing.Board Mail Stop 0-16 C1                                       Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission                      U.S. Nuclear Regulatory Commission Washington, DC 20555-0001                                Washington, DC 20555-0001 OCAAmaila~nrc.gov
*Lloyd Subin, Esq.
*Lloyd Subin, Esq.                                      **Sarah Hofmann, Esq.
*Susan L. Uttal, Esq.
*Susan L. Uttal, Esq.                                   Director of Public Advocacy
*Maxwell C. Smith, Esq.
*Maxwell C. Smith, Esq.                                 Department of Public Service Office of the General Counsel                             112 State Street - Drawer 20 Mail Stop O-15-D21                                       Montpelier, VT 05620-2601 U.S. Nuclear Regulatory Commission                       Sarah.hofinann(state.vt.us Washington, D.C. 20555-0001 LBS3@(cnrc.gov; susan.uttal(ynrc.gov; maxwell.smith(ai)nrc. gov Pillsbury Winthrop Shaw Pittman LLP
Office of the General Counsel Mail Stop O-15-D21 U.S. Nuclear Regulatory Commission Washington, D.C. 20555-0001 LBS3@(cnrc.gov; susan.uttal(ynrc.gov; maxwell.smith(ai)nrc. gov
*Administrative Judge Dr. Richard E. Wardwell Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 rew(anrc.gov
* Secretary Att'n: Rulemakings and Adjudications Staff Mail Stop 0-16 CI U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 secy(anrc.gov, hearingdocket(Dnrc. gov Atomic Safety and Licensing.Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001
**Sarah Hofmann, Esq.
Director of Public Advocacy Department of Public Service 112 State Street - Drawer 20 Montpelier, VT 05620-2601 Sarah.hofinann(state.vt.us Pillsbury Winthrop Shaw Pittman LLP


**Anthony Z. Roisman, Esq.                       **Raymond Shadis National Legal Scholars Law Firm                 37 Shadis Road 84 East Thetford Road                             PO Box 98 Lyme, NH 03768                                   Edgecomb, ME 04556 aroisman(-,nationalleaalscholars.com             shadis(lprexar.comr
**Anthony Z. Roisman, Esq.
*Peter L. Roth, Esq.                              *Zachary Kahn, Esq.
National Legal Scholars Law Firm 84 East Thetford Road Lyme, NH 03768 aroisman(-,nationalleaalscholars.com
Office of the New Hampshire Attorney General     Atomic Safety and Licensing Board Panel 33 Capitol Street                                 Mail Stop T-3 F23 Concord, NH 03301                                 U.S. Nuclear Regulatory Commission Peter.roth(adoi.nh.gov                            Washington, DC 20555-0001 zachary.kalmn(arc. gov
**Raymond Shadis 37 Shadis Road PO Box 98 Edgecomb, ME 04556 shadis(lprexar.comr
*Peter L. Roth, Esq.
Office of the New Hampshire Attorney General 33 Capitol Street Concord, NH 03301 Peter.roth(adoi.nh.gov
*Matthew Brock, Esq.
*Matthew Brock, Esq.
Assistant Attorney General Environmental Protection Division Office of the Attorney General One Ashburton Place, 18th Floor Boston, MA 02108 Matthew.Brocke,state.ma.us Matias F. Tr*avieso-Diaz Pillsbury Winthrop Shaw Pittman LLP
Assistant Attorney General Environmental Protection Division Office of the Attorney General One Ashburton Place, 18th Floor Boston, MA 02108 Matthew.Brocke,state.ma.us
*Zachary Kahn, Esq.
Atomic Safety and Licensing Board Panel Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 zachary.kalmn(arc. gov Matias F. Tr*avieso-Diaz Pillsbury Winthrop Shaw Pittman LLP


V StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
CALCULATION PACKAGE File No.: 0801038.302 Project No.: 0801038 Quality Program E Nuclear   E- Commercial PROJECT NAME:
File No.: 0801038.302 CALCULATION PACKAGE Project No.: 0801038 Quality Program E Nuclear E-Commercial PROJECT NAME:
VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:
VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:
10163217 Amendment 5 CLIENT:                                             PLANT:
10163217 Amendment 5 CLIENT:
Entergy Nuclear Operations, Inc                     Vermont Yankee Nuclear Power Station CALCULATION TITLE:
PLANT:
Stress Analysis of Reactor Core Spray Nozzle Document       Affected                                         Project Manager             Preparer(s) &
Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:
DocumentsAfted                 Revision Description                 Approval                 Checker(s)
Stress Analysis of Reactor Core Spray Nozzle Document Affected Project Manager Preparer(s) &
Revision         Pages                                           Signature & Date         Signatures & Date 01             - 15             Initial issue.
DocumentsAfted Revision Description Approval Checker(s)
Gary L. Stevens         Tyler D. Novotny Computer Files                                           01/06/09                 01/06/09 Jennifer D. Correa
Revision Pages Signature & Date Signatures & Date 01  
                                                                                              .01/06/09 1       1-3,7-8,11       Revised per summary           /                       Preparer:
- 15 Initial issue.
contained in Section 1.1.                 /     &1t@                           /
Gary L. Stevens Tyler D. Novotny Computer Files 01/06/09 01/06/09 Jennifer D. Correa
Computer Files   Changes are marked with revision handbars"   in right-Stevens margin.                   03/09/09             Tyler D. Novotny 03/09/09 Checker:
.01/06/09 1
1-3,7-8,11 Revised per summary  
/
Preparer:
contained in Section 1.1.  
/  
&1t@  
/
Computer Files Changes are marked with revision bars" in right-Stevens hand margin.
03/09/09 Tyler D. Novotny 03/09/09 Checker:
Tim D. Gilman 03/09/09 Page 1 of 15 F0306-O1RO
Tim D. Gilman 03/09/09 Page 1 of 15 F0306-O1RO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
Table of Contents 1.0   O B JECTIV E ......... .......................................................................................................................         3 1.1       Changes Made in Revision 1 of this Calculation ...........................................................                                       3 2.0 METHODOLOGY ..............................................................................................................                                 3 3.0 ASSUMPTIONS / DESIGN INPUTS .....................................................................................                                           3 4.0 C A LCU L A T IO N S ........................................................................................................................               3 4.1       Finite Element Unit Pressure Stress Analysis...............................                                                                     3 4.2       Thenr al Transient Stress Analysis ................................................................................                             4 4.3       Determining Critical Stress Paths .................................................................................                             .5 4.4       Stress C alculation ..........................................................................................................                   5 4 .5     P ip in g L o ad s .............................. ............................................................................................ 7 5.0    RESULTS OF ANALYSIS .....................................................................................................                              8 6.0    RE FEREN C E S ............................................................................................................................            8 List of Tables Table    1:  Pressure Results (1,000 psi) .............................................................................................                         6 Table   2: Stresses Under Unit Pressure Load, psi ...................................                                                                        9 Table    3:  Membrane Plus Bending Stresses Due to Piping Loads ................................................                                              10 Table    4:  Example Thermal Stress Result Output, psi .....................................................................                                  11 List of Figures Figure    1. Core Spray Nozzle Internal Pressure Distribution ....................... ................................                                        12 Figure    2. Core Spray Nozzle Pressure Cap Load & Boundary Condition ..................                                                                      13 Figure    3. Core Spray Nozzle Vessel Wall Boundary Condition                                                        ........................                14 Figure    4. Limiting Stress Paths ................................. .....................................................................                    15 FileNo.: 0801038.302                                                                                                                                     Page 2 of 15 Revision: 1 F0306-01RO
Table of Contents 1.0 O B JE C T IV E................................................................................................................................
3 1.1 Changes Made in Revision 1 of this Calculation...........................................................
3 2.0 METHODOLOGY..............................................................................................................
3 3.0 ASSUMPTIONS / DESIGN INPUTS.....................................................................................
3 4.0 C A L C U L A T IO N S........................................................................................................................
3 4.1 Finite Element Unit Pressure Stress Analysis...............................
3 4.2 Thenr al Transient Stress Analysis................................................................................
4 4.3 Determining Critical Stress Paths.................................................................................  
.5 4.4 Stress C alculation..........................................................................................................
5 4.5 P ip in g L o ad s..............................
7 5.0 RESULTS OF ANALYSIS.....................................................................................................
8 6.0 R E FE R E N C E S............................................................................................................................
8 List of Tables Table 1: Pressure Results (1,000 psi).............................................................................................
6 Table 2: Stresses Under Unit Pressure Load, psi...................................
9 Table 3: Membrane Plus Bending Stresses Due to Piping Loads................................................
10 Table 4: Example Thermal Stress Result Output, psi.....................................................................
11 List of Figures Figure 1. Core Spray Nozzle Internal Pressure Distribution.......................
12 Figure 2. Core Spray Nozzle Pressure Cap Load & Boundary Condition..................
13 Figure 3. Core Spray Nozzle Vessel Wall Boundary Condition 14 Figure 4. Lim iting Stress Paths.................................
15 FileNo.: 0801038.302 Page 2 of 15 Revision: 1 F0306-01RO


VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
1.0     OBJECTIVE The objective of this calculation package is to obtain stress distributions for the reactor pressure vessel (RPV) core spray (CS) nozzle at the Vermont Yankee Nuclear Power Station. ANSYS [1]
1.0 OBJECTIVE The objective of this calculation package is to obtain stress distributions for the reactor pressure vessel (RPV) core spray (CS) nozzle at the Vermont Yankee Nuclear Power Station. ANSYS [1]
thernal transient and pressure stress analyses are performed, along with calculation of stresses due to attached piping loads. The stress results will be used for a subsequent ASME Code, Section III NB-3200 [2] fatigue usage calculation.
thernal transient and pressure stress analyses are performed, along with calculation of stresses due to attached piping loads. The stress results will be used for a subsequent ASME Code, Section III NB-3200 [2] fatigue usage calculation.
1.1   Changes Made in Revision 1 of this Calculation Description of changes made in Revision 1 of this calculation:
1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision 1 of this calculation:
: a. All changes marked throughout this calculation are editorial changes made to the text of the calculation package.
: a. All changes marked throughout this calculation are editorial changes made to the text of the calculation package.
2.0     METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
[3]. A previously developed finite element model (FEM) [3] of the CS nozzle is used to perform thermal and pressure stress analyses using ANSYS [1]. A thermal transient analysis is performed for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads. For these loads, unit load analyses (based on finite element analysis for pressure and manual calculations for attached piping loads) are performed. All six components of the stress tensor are determined in the stress calculations.
[3]. A previously developed finite element model (FEM) [3] of the CS nozzle is used to perform thermal and pressure stress analyses using ANSYS [1]. A thermal transient analysis is performed for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads. For these loads, unit load analyses (based on finite element analysis for pressure and manual calculations for attached piping loads) are performed. All six components of the stress tensor are determined in the stress calculations.
The fatigue usage calculation and environmental fatigue usage analysis will be performed in a separate calculation package. That subsequent calculation will utilize the thermal and pressure stresses determined in this calculation, along with stresses due to attached piping loads provided in Table 3. The stresses due to pressure and the attached piping loads will be scaled based on the temperature and pressure magnitudes during each individual transient, and the location being analyzed. From the Reference [3] calculation, the FEM includes a factor of two on the modeled RPV radius to account for the 3-D effects of two intersecting cylinders at the nozzle blend radius location.
The fatigue usage calculation and environmental fatigue usage analysis will be performed in a separate calculation package. That subsequent calculation will utilize the thermal and pressure stresses determined in this calculation, along with stresses due to attached piping loads provided in Table 3. The stresses due to pressure and the attached piping loads will be scaled based on the temperature and pressure magnitudes during each individual transient, and the location being analyzed. From the Reference [3] calculation, the FEM includes a factor of two on the modeled RPV radius to account for the 3-D effects of two intersecting cylinders at the nozzle blend radius location.
3.0     ASSUMPTIONS / DESIGN INPUTS Assumptions and design inputs were previously established in Section 3.1 of the Reference [3]
3.0 ASSUMPTIONS / DESIGN INPUTS Assumptions and design inputs were previously established in Section 3.1 of the Reference [3]
calculation.
calculation.
4.0     CALCULATIONS 4.1 Finite Element Unit Pressure Stress Analysis A uniform pressure of 1,000 psi was applied to the FEM along the inside surface of the CS nozzle and the RPV wall (Figure 1). A pressure load of 1,000 psi was used because it is easily scaled up or FileNo.: 0801038.302                                                                                 Page 3 of 15 Revision: 1 F0306-O1RO
4.0 CALCULATIONS 4.1 Finite Element Unit Pressure Stress Analysis A uniform pressure of 1,000 psi was applied to the FEM along the inside surface of the CS nozzle and the RPV wall (Figure 1). A pressure load of 1,000 psi was used because it is easily scaled up or FileNo.: 0801038.302 Page 3 of 15 Revision: 1 F0306-O1RO


StructuralIntegrityAssociates, Inc.
Structural Integrity Associates, Inc.
down to account for different pressures that occur during transients. In addition, a membrane stress "cap load" was applied to the modeled end of the piping attached to the core spray nozzle safe end.
down to account for different pressures that occur during transients. In addition, a membrane stress "cap load" was applied to the modeled end of the piping attached to the core spray nozzle safe end.
This membrane stress was calculated as follows:
This membrane stress was calculated as follows:
p* Di2 cap - Do 2 - Di 2 where:
p* Di2 cap 2
2 Do - Di where:
P = Pressure = 1,000 psi unit load Di= Inner Diameter at end of model = 9.834 in Do = Outer Diameter at end of model = 10.815 in Therefore, the membrane stress is 4,774 psi. The calculated value is given a negative sign in order for it to exert tension on the piping end of the model. The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, input file VYCSNGEOMINP].
P = Pressure = 1,000 psi unit load Di= Inner Diameter at end of model = 9.834 in Do = Outer Diameter at end of model = 10.815 in Therefore, the membrane stress is 4,774 psi. The calculated value is given a negative sign in order for it to exert tension on the piping end of the model. The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, input file VYCSNGEOMINP].
The ANSYS input file VY 16Q_P.INP, as obtained from Appendix A of Reference [5], contains the pressure loading. Figure 1 shows the applied 1,000 psi internal pressure distribution. At the vessel wall, a symmetric boundary condition is applied. At the piping end of the model, axial displacement is coupled to simulate the effect of the attached piping that is not modeled. Figure 2 and Figure 3 show the boundary conditions.
The ANSYS input file VY 16Q_P.INP, as obtained from Appendix A of Reference [5], contains the pressure loading. Figure 1 shows the applied 1,000 psi internal pressure distribution. At the vessel wall, a symmetric boundary condition is applied. At the piping end of the model, axial displacement is coupled to simulate the effect of the attached piping that is not modeled. Figure 2 and Figure 3 show the boundary conditions.
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The thermal results are used as input for the stress analysis for each transient. The boundary conditions used for the pressure load case were also applied to the thermal stress cases. Figure 2 and Figure 3 show the application of these boundary conditions.
The thermal results are used as input for the stress analysis for each transient. The boundary conditions used for the pressure load case were also applied to the thermal stress cases. Figure 2 and Figure 3 show the application of these boundary conditions.
All ANSYS input files for the thennal analyses, as listed below, are saved in the project computer files:
All ANSYS input files for the thennal analyses, as listed below, are saved in the project computer files:
VY_CSNGEOM.INP: Geometry and material properties VY_16QTRAAN2-T.INP, VY 16QTRAN2-S.INP: Transient 2, thermal and stress analyses VY_16QTRAN3-T.INP, VY 16QTRAN3-S.INP: Transient 3, thermal and stress analyses VTY_ 6QTRAN11-T.INP, VYI 16QTRAN11-S.INP: Transient 11, thermal and stress analyses FileNo.: 0801038.302                                                                             Page 4 of 15 Revision: I F0306-O1RO
VY_CSNGEOM.INP: Geometry and material properties VY_16QTRAAN2-T.INP, VY 16QTRAN2-S.INP: Transient 2, thermal and stress analyses VY_16QTRAN3-T.INP, VY 16QTRAN3-S.INP: Transient 3, thermal and stress analyses VTY_ 6QTRAN11-T.INP, VYI 16QTRAN11-S.INP: Transient 11, thermal and stress analyses FileNo.: 0801038.302 Page 4 of 15 Revision: I F0306-O1RO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
VY_16QTRAN14-T.JNP, VY         16QTRAN14-S.INP: Transient 14, thermal and stress analyses VYý_]6QTRAN21-23-T.INP,       VY_ 6Q_TRAN21-23-S.INP: Transient 21-23, thermal and stress analyses VY_16QTRAN24-T.INP, VY         16QTRAN24-S.JNP: Transient 24, thermal and stress analyses VY_16QTRAN30-T.INP, VY         16QTRAN30-S.INP: Transient 30, thermal and stress analyses 4.3 Determining Critical Stress Paths From Section 4.0 of Reference [5], the critical location in the safe end was determined to be at Node 3719. This location was selected since it possessed the highest stress intensity during the worst case thermal transient.
VY_16QTRAN14-T.JNP, VY 16QTRAN14-S.INP: Transient 14, thermal and stress analyses VYý_]6QTRAN21-23-T.INP, VY_ 6Q_TRAN21-23-S.INP: Transient 21-23, thermal and stress analyses VY_16QTRAN24-T.INP, VY 16QTRAN24-S.JNP: Transient 24, thermal and stress analyses VY_16QTRAN30-T.INP, VY 16QTRAN30-S.INP: Transient 30, thermal and stress analyses 4.3 Determining Critical Stress Paths From Section 4.0 of Reference [5], the critical location in the safe end was determined to be at Node 3719. This location was selected since it possessed the highest stress intensity during the worst case thermal transient.
Also from Section 4.0 of Reference [5], the critical stress location in the nozzle blend radius was chosen based upon the highest pressure stress (which is controlling in the nozzle blend radius). The pressure stress results showed the critical location in the nozzle blend radius to be at Node 2166.
Also from Section 4.0 of Reference [5], the critical stress location in the nozzle blend radius was chosen based upon the highest pressure stress (which is controlling in the nozzle blend radius). The pressure stress results showed the critical location in the nozzle blend radius to be at Node 2166.
Figure 4 shows the two critical stress paths that will be used to find the linearized stresses at the safe end and nozzle blend radius.
Figure 4 shows the two critical stress paths that will be used to find the linearized stresses at the safe end and nozzle blend radius.
4.4 Stress Calculation Linearized stresses from Node 3719 (safe end inside surface) and Node 2166 (nozzle blend radius inside surface of base metal) are used for the fatigue usage analysis, as shown in Figure 4. For the nozzle blend radius location, the stresses used are for the base metal only; the cladding material is unselected prior to stress extraction.
4.4 Stress Calculation Linearized stresses from Node 3719 (safe end inside surface) and Node 2166 (nozzle blend radius inside surface of base metal) are used for the fatigue usage analysis, as shown in Figure 4. For the nozzle blend radius location, the stresses used are for the base metal only; the cladding material is unselected prior to stress extraction.
The pressure stress intensities for the safe end and blend radius paths were extracted using the ANSYS file VY_]6QP.INP. This produced one file, PRESSURE.lin, which contains results of the critical stress paths.
The pressure stress intensities for the safe end and blend radius paths were extracted using the ANSYS file VY_]6QP.INP. This produced one file, PRESSURE. lin, which contains results of the critical stress paths.
Table 1 shows the final pressure results for the safe end and blend radius. These results are slightly different from those reported in Table 14 of Reference [5] as a result of the revised material properties (i.e., temperature dependent material properties were used in the current evaluation vs. constant material properties in Reference [5]).
Table 1 shows the final pressure results for the safe end and blend radius. These results are slightly different from those reported in Table 14 of Reference [5] as a result of the revised material properties (i.e., temperature dependent material properties were used in the current evaluation vs. constant material properties in Reference [5]).
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Table 1: Pressure Results (1,000 psi)
Table 1: Pressure Results (1,000 psi)
Membrane plus                   Total Stress Location                 Bending Stress                   Intensit Intensity                         (psi)
Membrane plus Total Stress Location Bending Stress Intensit Intensity (psi)
(psi)
(psi)
Safe End                       12,030                         12,070 Blend Radius                     30,720                       36,150 Results were also extracted from the vessel portion of the model to verify the accuracy of the results obtained from the ANSYS model, and to check the results due to the use of the 2.0 multiplier on the vessel radius. These results are contained in the file PRESSURE.lin. The radius of the finite element model (FEM) was multiplied by a factor of 2.0 [3] to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is the intersection of two cylinders.
Safe End 12,030 12,070 Blend Radius 30,720 36,150 Results were also extracted from the vessel portion of the model to verify the accuracy of the results obtained from the ANSYS model, and to check the results due to the use of the 2.0 multiplier on the vessel radius. These results are contained in the file PRESSURE. lin. The radius of the finite element model (FEM) was multiplied by a factor of 2.0 [3] to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is the intersection of two cylinders.
The equation for the membrane hoop stress in a sphere is:
The equation for the membrane hoop stress in a sphere is:
(pressure)x (radius) 2 x thickness Considering a vessel base metal radius, R, of 105.906 inches increased by a factor of 2.0, a vessel base metal thickness, t, of 5.4375 inches, and an applied pressure, P, of 1,000 psi, the calculated stress for a sphere is PR/(2t) = 19,477 psi. This compares very well with the remote vessel wall membrane hoop stress from the ANSYS result file, PRESSURE.lin, of 18,960 psi. Thus, considering the peak total pressure stress of 36,150 psi reported above, the stress concentrating effect of the nozzle comer is 36,150/19,477 = 1.86. In other words, the peak nozzle comer stress is 1.86 times higher than nominal vessel wall stress for the axisymmetric model.
(pressure) x (radius) 2 x thickness Considering a vessel base metal radius, R, of 105.906 inches increased by a factor of 2.0, a vessel base metal thickness, t, of 5.4375 inches, and an applied pressure, P, of 1,000 psi, the calculated stress for a sphere is PR/(2t) = 19,477 psi. This compares very well with the remote vessel wall membrane hoop stress from the ANSYS result file, PRESSURE.lin, of 18,960 psi. Thus, considering the peak total pressure stress of 36,150 psi reported above, the stress concentrating effect of the nozzle comer is 36,150/19,477 = 1.86. In other words, the peak nozzle comer stress is 1.86 times higher than nominal vessel wall stress for the axisymmetric model.
The equation for the membrane hoop stress in a cylinder is:
The equation for the membrane hoop stress in a cylinder is:
I
((pressure) x (radius))
((pressure) x (radius))
thickness Based on the previous dimensions, the calculated stress for a cylinder without the 2.0 factor is 19,477 psi. Increasing this by a factor of 1.86 yields an expected peak nozzle comer stress of 36,227 psi, which would be expected from a cylindrical geometry that is representative of the nozzle configuration. Therefore, the result from the ANSYS file for the peak nozzle comer stress (36,150 psi) is close to the peak nozzle comer stress for a cylindrical geometry because of the use of the 2.0 File No.: 0801038.302                                                                             Page 6 of 15 Revision: 1 F0306-OIRO
thickness I Based on the previous dimensions, the calculated stress for a cylinder without the 2.0 factor is 19,477 psi. Increasing this by a factor of 1.86 yields an expected peak nozzle comer stress of 36,227 psi, which would be expected from a cylindrical geometry that is representative of the nozzle configuration. Therefore, the result from the ANSYS file for the peak nozzle comer stress (36,150 psi) is close to the peak nozzle comer stress for a cylindrical geometry because of the use of the 2.0 File No.: 0801038.302 Page 6 of 15 Revision: 1 F0306-OIRO


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multiplier. This is consistent with SI's experience where a factor of two increase in radius is typical for representing the 3-D effect in an axisymmetric model.
multiplier. This is consistent with SI's experience where a factor of two increase in radius is typical for representing the 3-D effect in an axisymmetric model.
4.5 Piping Loads The piping loads per Reference [4] are as follows:
4.5 Piping Loads The piping loads per Reference [4] are as follows:
F, = 2,500 lbs                   Mx= 264,000 in-lb Fy = 4,600 lbs                   My= 85,200 in-lb F, = 1,700 lbs                   Mz= 105,600 in-lb The point of loads application is at the intersection between the safe end-to-pipe weld [4, 61]
F, = 2,500 lbs Mx= 264,000 in-lb Fy = 4,600 lbs My= 85,200 in-lb F, = 1,700 lbs Mz= 105,600 in-lb The point of loads application is at the intersection between the safe end-to-pipe weld [4, 61]
Therefore, the safe end critical location is 0.303 inches and the nozzle blend radius is 30.817 inches from the load application point. (The nozzle blend radius location was measured from approximately the middle of the critical stress path for the blend radius and applied to the inside blend radius location along the critical stress path.) From general structural mechanics, the membrane plus bending stresses at the inside surface of a thick-walled cylinder are:
Therefore, the safe end critical location is 0.303 inches and the nozzle blend radius is 30.817 inches from the load application point. (The nozzle blend radius location was measured from approximately the middle of the critical stress path for the blend radius and applied to the inside blend radius location along the critical stress path.) From general structural mechanics, the membrane plus bending stresses at the inside surface of a thick-walled cylinder are:
cyzl = axial stress due to axial force = Fz/A cy, = axial stress due to bending moment = Mxy(ID/2)/I (z =     Tzl 5"z2
cyzl = axial stress due to axial force = Fz/A cy, = axial stress due to bending moment = Mxy(ID/2)/I (z =
                    ,re = shear stress due to torsion     = Mz(ID/2)/J z = shear stress due to shear force = 2Fxy/A, where Fx, Fy, Fz, M,, My, and Mz are forces and moments at the pipe-to-safe end weld M* = moment about x axis translated by length z = -L = M, - Fy L MyL = moment about y axis translated by length z = -L = My + Fx L 2
Tzl 5"z2
Mxy = resultant bending moment = (MxL + MyL2)0.5 2
,re = shear stress due to torsion = Mz(ID/2)/J z = shear stress due to shear force = 2Fxy/A, where Fx, Fy, Fz, M,, My, and Mz are forces and moments at the pipe-to-safe end weld M* = moment about x axis translated by length z = -L = M, - Fy L MyL = moment about y axis translated by length z = -L = My + Fx L Mxy = resultant bending moment = (MxL 2 + MyL2)0.5 Fxy = resultant shear force = (Fx2 + Fy2)0.5 ID, OD = inside and outside diameters A = area of cross section = (it/4)(OD 2 - ID2)
Fxy = resultant shear force = (Fx + Fy2)0.5 ID, OD = inside and outside diameters             2 2
A = area of cross section = (it/4)(OD - ID )
I = moment of inertia = (7/64)(OD 4 - ID 4)
I = moment of inertia = (7/64)(OD 4 - ID 4)
J = polar moment of inertia = (7/32)(0D 4 - ID4)
J = polar moment of inertia = (7/32)(0D4 - ID4)
The piping load stress calculations for these locations are shown in Table 3.
The piping load stress calculations for these locations are shown in Table 3.
The piping loads tabulated in and pictorially shown in Reference [4] were applied by CB&I at the safe end-to-pipe weld. Refer to Reference [6], page 9 of 13; CB&I RPV Stress Report, Section S7.
The piping loads tabulated in and pictorially shown in Reference [4] were applied by CB&I at the safe end-to-pipe weld. Refer to Reference [6], page 9 of 13; CB&I RPV Stress Report, Section S7.
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5.0     RESULTS OF ANALYSIS A thermal transient analysis for each defined transient, as well as unit pressure stress and piping interface load analyses were performed for the CS nozzle at Vermont Yankee. All six components of the stress tensor were extracted from the ANSYS model at the two limiting path locations. Table 2 provides the unit pressure stress analysis results. The unit pressure load results are used to choose the location to analyze at the nozzle blend radius and will be scaled up or down based on applied pressures for the final fatigue analysis. Table 3 provides the piping stresses at the two critical locations. Table 4 shows an example of thermal stress results. The remaining thermal stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:
5.0 RESULTS OF ANALYSIS A thermal transient analysis for each defined transient, as well as unit pressure stress and piping interface load analyses were performed for the CS nozzle at Vermont Yankee. All six components of the stress tensor were extracted from the ANSYS model at the two limiting path locations. Table 2 provides the unit pressure stress analysis results. The unit pressure load results are used to choose the location to analyze at the nozzle blend radius and will be scaled up or down based on applied pressures for the final fatigue analysis. Table 3 provides the piping stresses at the two critical locations. Table 4 shows an example of thermal stress results. The remaining thermal stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:
PRESSURE.lin: Unit pressure stress analysis results VY_16QTRAN2-S. lin: Transient 2, thermal stress analysis results VY_ 6QTRAN3-S. lin: Transient 3, thermal stress analysis results VY_16QTRANll-S.lin: Transient 11, thermal stress analysis results VY_16QTRAN14-S.lin: Transient 14, thernal stress analysis results VY_16QTRAN21-23-S. lih: Transient 21-23, thermal stress analysis results VY_16QTRAN24-S. lin: Transient 24, thermal stress analysis results VY_]6Q TRAN3 0-S. lin: Transient 30, thermal stress analysis results A fatigue calculation using the methodology of Subarticle NB-3200 of Section III of the ASME Code [2] and an environmental fatigue usage analysis will be performed in a separate calculation package using the stress results from this calculation.
PRESSURE. lin: Unit pressure stress analysis results VY_16QTRAN2-S. lin: Transient 2, thermal stress analysis results VY_ 6QTRAN3-S. lin: Transient 3, thermal stress analysis results VY_16QTRANll-S.lin: Transient 11, thermal stress analysis results VY_16QTRAN14-S.lin: Transient 14, thernal stress analysis results VY_16QTRAN21-23-S. lih: Transient 21-23, thermal stress analysis results VY_16QTRAN24-S. lin: Transient 24, thermal stress analysis results VY_]6Q TRAN3 0-S. lin: Transient 30, thermal stress analysis results A fatigue calculation using the methodology of Subarticle NB-3200 of Section III of the ASME Code [2] and an environmental fatigue usage analysis will be performed in a separate calculation package using the stress results from this calculation.
The results of this calculation are used in a subsequent SIA Calculation No. 0801038.303, "Fatigue Analysis of Core Spray Nozzle."
The results of this calculation are used in a subsequent SIA Calculation No. 0801038.303, "Fatigue Analysis of Core Spray Nozzle."


==6.0     REFERENCES==
==6.0 REFERENCES==
: 1. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
: 1. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
: 2. ASME Boiler and Pressure Vessel Code, Section III, Subsection-NB, 1998 Edition with 2000 Addenda.
: 2. ASME Boiler and Pressure Vessel Code, Section III, Subsection-NB, 1998 Edition with 2000 Addenda.
Line 137: Line 176:
919D294), SI File No. VY-05Q-241.
919D294), SI File No. VY-05Q-241.
: 5. SI Calculation No. VY-16Q-309, Revision 1, "Core Spray Nozzle Green's Functions."
: 5. SI Calculation No. VY-16Q-309, Revision 1, "Core Spray Nozzle Green's Functions."
: 6. Entergy Design Input Record (DIR), Rev. 1, EC No. 1773, Rev. 0, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY- 16Q-209.
: 6. Entergy Design Input Record (DIR), Rev. 1, EC No. 1773, Rev. 0, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-16Q-209.
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Table 2: Stresses Under Unit Pressure Load, psi Membrane plus Bending                         Total Node   S     SY     Sz     Sxy Syz Sxz   SX   S       Sz     Sxy     Syz Sxz SafeEnd   3719 -1011   4829   11010   -104.8 0   0 -1011 4912   11050   -85.31     0   0 Blend Radius 2166 -1052   1657 25960     4886   0   0 -1052 1720   35050   348.9     0   0 FileNo.: 0801038.302                                                                   Page 9 of 15 Revision: 1 F0306-01RO
Table 2: Stresses Under Unit Pressure Load, psi Membrane plus Bending Total Node S
SY Sz Sxy Syz Sxz SX S
Sz Sxy Syz Sxz SafeEnd 3719  
-1011 4829 11010  
-104.8 0
0  
-1011 4912 11050  
-85.31 0
0 Blend Radius 2166  
-1052 1657 25960 4886 0
0  
-1052 1720 35050 348.9 0
0 FileNo.: 0801038.302 Revision: 1 Page 9 of 15 F0306-01RO


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Table 3: Membrane Plus Bending Stresses Due to Piping Loads Safe End         Blend Radius Fx, kip         2.5           2.5 Fy, kip         4.6           4.6 F,, kip           1.7           1.7 Mx, kip-in         264           264 My, kip-in         85.2         85.2 M,, kip-in         105.6         105.6 L, in         0.30         30.82 MxL, kip-in       262.61       122.24 MyL, kip-in       85.96       162.24 MxY, kip-in       276.32       203.14 Fy,, kip-in       5.24         5.24 OD, in         10.82         24.25 ID,in         9.834       12.125 A, in2         15.91       346.40 I, in4       212.46       15914.32 J, in4       424.93       31828.64 a.,, ksi         0.107         0.005 az2, ksi         6.395         0.077 oz, ksi       6.502         0.082 "ro, ksi         1.222         0.020 cz, ksi         0.658         0.030 Note: The axial and shear stresses are expressed in a local coordinate system with r radial (X in ANSYS coordinates), 0 circumferential (Z in ANSYS coordinates), and Z axial (Y in ANSYS coordinates) components with respect to the nozzle centerline.
Table 3: Membrane Plus Bending Stresses Due to Piping Loads Safe End Blend Radius Fx, kip 2.5 2.5 Fy, kip 4.6 4.6 F,, kip 1.7 1.7 Mx, kip-in 264 264 My, kip-in 85.2 85.2 M,, kip-in 105.6 105.6 L, in 0.30 30.82 MxL, kip-in 262.61 122.24 MyL, kip-in 85.96 162.24 MxY, kip-in 276.32 203.14 Fy,, kip-in 5.24 5.24 OD, in 10.82 24.25 ID, in 9.834 12.125 A, in2 15.91 346.40 I, in4 212.46 15914.32 J, in4 424.93 31828.64 a.,, ksi 0.107 0.005 az2, ksi 6.395 0.077 oz, ksi 6.502 0.082 "ro, ksi 1.222 0.020 cz, ksi 0.658 0.030 Note: The axial and shear stresses are expressed in a local coordinate system with r radial (X in ANSYS coordinates), 0 circumferential (Z in ANSYS coordinates), and Z axial (Y in ANSYS coordinates) components with respect to the nozzle centerline.
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Table 4: Example Thermal Stress Result Output, psi Membrane Plus Bending                         Total Transient NodeI I Time (s) I.Sx           Sy         Sz   Sxy   Syz Sxz'   Sx     Sy     Sz     Sxy   Syz Sxz 0       48      288        696    -50    0  0    48          641      -86        0 10.002     49      280        689    -50    0  0    49    -11    630      -86        0 123.23     52      197        644    -53    0  0    52  -131    561      -89        0 1716.1     124      467        1587  -123    0  0    124  -293  1413    -212        0 6984.8     380      1918      5199  -385    0  0  380    -358  4733    -663        0 7946.2     430     2206       5907   -436    0  0  430    -365  5384    -752        0 8919      482      2506      6638  -489    0  0  482    -371  6056    -843        0 16055      845      4684      11830  -857   0  0    845  -352  10830    -1487        0 16164    -849      4707      11880  -861    0  0    849  -352  10880    -1494        0 3719 16304      850      4831      12000  -864    0  0    850  -219  11020    -1500        0 19448      851      5001      12110  -870   0   0   851   -45 11140    -1506        0 20622      851      5002      12110  -870    0  0    851    -44 11140    -1506        0 29155      851      5002      12110  -870    0  0    851    -44 11140   -1506         0 32155      851      5002      12110  -870    0  0    851    -44  11140   -1506         0 40155      851      5002      12110  -870    0  0    851    -44  11140   -1506         0 50155      851      5002      12110  -870    0   0   851    -44  11140    -1506        0 65155      851      5002      12110  -870    0   0   851    -44  11140    -1506        0 66165      851      5002      12110  -870    0   0   851    -44  11140    -1506        0 3
Table 4: Example Thermal Stress Result Output, psi Transient Node Time Membrane Plus Bending Total I I (s)
0       86      -140        1025    44        0     87  -1084  -628      -68        0 10.002     87     -141       1030    44        0    109 -1242  -955      -70        0 123.23      109    -210        1224    60        0    310  -3331  -4776    -184        0 1716.1    310    -1469      2676    359        0    794  -9114  -9547    -537        0 6984.8    794    -2777      8114    775        0    882 -10220 -10520    -607        0 7946.2    882    -3032      8912   812       0   973 -11350 -11470    -678        0 8919      973    -3298      9762    859        0  1553 -18930 -18300    -1177        0 16055    1553    -5119      14660  1049        0  1562 -19040 -18390    -1184        0 16164    1562    -5143      14730  1051        0  1545 -18980 -18070    -1190        0 2166 16304    1545    -5079      14620  1032        0  1433 -18220 -14130    -1169        0
I.Sx Sy Sz Sxy Syz Sxz' Sx Sy Sz Sxy Syz Sxz 3719 0
                          .19448    1433    -3608      14270  632        0  1422 -18180 -13900    -1169        0 20622      1422    -3508      14050  566        0  1409 -18140 -13810,  -1173        0 29155      1409    -3451      13540  461        0  1409 -18140 -13810    -1173        0 32155      1409    -3452      13520  459        0  1409 -18140 -13810    -1173        0 40155      1409    -3452      13510  458        0  1409 -18140 -13810   -1173         0 50155      1409    -3452      13510  458        0  1409 -18140 -13810   -1173         0 65155      1409    -3452      13510  458        0  1409 -18140 -13810   -1173         0 66165      1409    -3452      13510  458        0  1409 -18140 -13810   -1173         0 Note: Not all time steps are listed in this table.
10.002 123.23 1716.1 6984.8 7946.2 8919 16055 16164 16304 19448 20622 29155 32155 40155 50155 65155 66165 48 49 52 124 380 430 482 845
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-849 850 851 851 851 851 851 851 851 851 288 280 197 467 1918 2206 2506 4684 4707 4831 5001 5002 5002 5002 5002 5002 5002 5002 696 689 644 1587 5199 5907 6638 11830 11880 12000 12110 12110 12110 12110 12110 12110 12110 12110
-50
-50
-53
-123
-385
-436
-489
-857
-861
-864
-870
-870
-870
-870
-870
-870
-870
-870 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 48 49 52 124 380 430 482 845 849 850 851 851 851 851 851 851 851 851
-11
-131
-293
-358
-365
-371
-352
-352
-219
-45
-44
-44
-44
-44
-44
-44
-44 641
-86 630
-86 561
-89 1413
-212 4733
-663 5384
-752 6056
-843 10830
-1487 10880
-1494 11020
-1500 11140
-1506 11140  
-1506 11140
-1506 11140
-1506 11140  
-1506 11140
-1506 11140
-1506 11140  
-1506 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 3
2166 0
10.002 123.23 1716.1 6984.8 7946.2 8919 16055 16164 16304
.19448 20622 29155 32155 40155 50155 65155 66165 86
-140 87  
-141 109  
-210 310
-1469 794
-2777 882
-3032 973
-3298 1553
-5119 1562
-5143 1545
-5079 1433
-3608 1422
-3508 1409
-3451 1409
-3452 1409
-3452 1409
-3452 1409
-3452 1409
-3452 1025 1030 1224 2676 8114 8912 9762 14660 14730 14620 14270 14050 13540 13520 13510 13510 13510 13510 44 44 60 359 775 812 859 1049 1051 1032 632 566 461 459 458 458 458 458 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 87 109 310 794 882 973 1553
-18930 1562
-19040 1545
-18980 1433
-18220 1422
-18180 1409
-18140 1409
-18140 1409
-18140 1409
-18140 1409
-18140 1409
-18140 1409
-18140
-1084
-1242
-3331
-9114
-10220
-11350
-628
-68
-955
-70
-4776
-184
-9547
-537
-10520
-607
-11470
-678
-18300
-1177
-18390
-1184
-18070
-1190
-14130
-1169
-13900
-1169
-13810,
-1173
-13810
-1173
-13810  
-1173
-13810
-1173
-13810  
-1173
-13810
-1173
-13810  
-1173 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 0
0 Note: Not all time steps are listed in this table.
File No.: 0801038.302 Revision: 1 Page 11 of 15 F0306-01RO


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Figure 1. Core Spray Nozzle Internal Pressure Distribution File No.: 0801038.302                                                           Page 12 of 15 Revision: 1 F0306-O1RO
Figure 1. Core Spray Nozzle Internal Pressure Distribution File No.: 0801038.302 Revision: 1 Page 12 of 15 F0306-O1RO


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Core Spray Nozzle Finite Element Model Figure 2. Core Spray Nozzle Pressure Cap Load & Boundary Condition File No.: 0801038.302 Revision: 1 Page 13 of 15 F0306-01RO
    *Structurai Core Spray Nozzle Finite Element Model Figure 2. Core Spray Nozzle Pressure Cap Load & Boundary Condition File No.: 0801038.302                                                             Page 13 of 15 Revision: 1 F0306-01RO


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Core Spray Nozzle Finite Element Model Figure 3. Core Spray Nozzle Vessel Wall Boundary Condition FileNo.: 0801038.302                                                           Page 14 of 15 Revision: 1 F0306-O1RO
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V~~~~rd~N pi3t l~~l dpa
V~~~~rd~N dpa  
                              -0:1 NodE2166 C-r $pray :hzerirnre zl--es -o1q, Figure 4. Limiting Stress Paths FileNo.: 0801038.302                                                                 Page 15 of 15 Revision: 1 F0306-01RO
-0:1 pi3t l~~l NodE 2166 C-r  
$pray :hzerirnre zl--es  
-o1q, Figure 4. Limiting Stress Paths FileNo.: 0801038.302 Revision: 1 Page 15 of 15 F0306-01RO


J V StructuralIntegrityAssociates, Inc.                     File No.: 0801038.303 Project No.: 0801038, CALCULATION PACKAGE                               ,Quality Program Z Nuclear L! Commercial PROJECT NAME:
J V Structural Integrity Associates, Inc. File No.: 0801038.303 Project No.: 0801038, CALCULATION PACKAGE  
,Quality Program Z Nuclear L! Commercial PROJECT NAME:
VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:
VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:
10163217 Amendment 5 CLIENT:                                             PLANT:
10163217 Amendment 5 CLIENT:
Entergy Nuclear Operations, Inc                   Vermont Yankee Nuclear Power Station CALCULATION TITLE:
PLANT:
Fatigue Analysis of Reactor Core Spray Nozzle, Document       Affected                                     Project Manager           Preparer(s) &
Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:
Revision         Pages         Revision Description             Approval               Checker(s)
Fatigue Analysis of Reactor Core Spray Nozzle, Document Affected Project Manager Preparer(s) &
Signature & Date         Signatures & Date 0           1 - 18             Initial issue.
Revision Pages Revision Description Approval Checker(s)
Gary L. Stevens         Tyler Novotny Computer Files.                                     01/06/09                 01/06/09 W. F. Weitze 01/06/09 1       1-3, 5-8, 11-12,   Revised per summary                           .. Preparer:
Signature & Date Signatures & Date 0
17-18       contained in Section 1.1.             /           -
1 - 18 Initial issue.
Changes are marked with         Gary L. Stevens Computer Files.   "revision bars" in right-hand margin.               03/09/09             Tyler D. Novotny 03/09/09 Checker:
Gary L. Stevens Tyler Novotny Computer Files.
01/06/09 01/06/09 W. F. Weitze 01/06/09 1
1-3, 5-8, 11-12, Revised per summary Preparer:
17-18 contained in Section 1.1.  
/
Changes are marked with Gary L. Stevens Computer Files.  
"revision bars" in right-hand margin.
03/09/09 Tyler D. Novotny 03/09/09 Checker:
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Table of Contents 1.0   O B JEC T IVE .................................................................................................................................               3 1.1     Changes Made in Revision 1 of this Calculation ...........................                                                                               3 2.0 M E TH O D O L O G Y ...........................................................................................                 ...        ................... 3 3.0 D E SIG N IN P U TS .........................................................................................................................                   3 3.1     Stress C alculation ..........................................................................................................                           3 3.2     Fatigue Usage Analysis, General ..................................................................................                                       4 3.3     Event Cycles, V ESLFA T ...............................................................................................                                 4 3.4     M aterial Properties, VESLFA T .....................................................................................                                     5 3.5     Stress Indices .............................................................................................................                             5 4.0 C A L C U L A TION S .........................................................................................................................                   6 5.0   RESULTS OF ANALYSIS .............................................                                                                                             7
Table of Contents 1.0 O B JE C T IV E.................................................................................................................................
3 1.1 Changes Made in Revision 1 of this Calculation...........................
3 2.0 M E TH O D O L O G Y...........................................................................................  
................... 3 3.0 D E SIG N IN P U T S.........................................................................................................................
3 3.1 Stress C alculation..........................................................................................................
3 3.2 Fatigue U sage A nalysis, General..................................................................................
4 3.3 Event Cycles, V ESLFA T...............................................................................................
4 3.4 M aterial Properties, VESLFA T.....................................................................................
5 3.5 Stress Indices.............................................................................................................
5 4.0 C A L C U L A T IO N S.........................................................................................................................
6 5.0 RESULTS OF ANALYSIS.............................................
7


==6.0   CONCLUSION==
==6.0 CONCLUSION==
S AND DISCUSSIONS ...............................................................................                                                   7 7.0   RE FEREN CE S .............................................................             ...............................................................      8 List of Tables Table   1: Safe End Load Sets as Input to VESLFAT .......................................................................                                           9 Table   2: Nozzle Blend Radius Load Sets as Input to VESLFAT .......................................................                                                 10 Table 3: Temperature-Dependent Material Properties for VESLFAT ....................                                                                               11 Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves ....................                                                                           12 Table 5: Pressure and Attached Piping Unit LoadCase Stress Components .................................                                                           13 Table 6: Fatigue Usage Calculation for the Safe End (Inconel) .......                                                   .................                          13 Table 7: Fatigue Usage Calculation for the Safe End (Stainless Steel) ..........................................                                                   14 Table   8: Fatigue Usage Calculation for the Nozzle Blend Radius                                                       .......................                    15 Table 9: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location ........................                                                               16 Table   10: Linearized Stress Files Compiled for VY-StressResults.xls ......................                                                                       18 File No.: 0801038.303                                                                                                                                           Page 2 of 18 Revision: 1 F0306-01RO
S AND DISCUSSIONS...............................................................................
7 7.0 R E FE R E N C E S.............................................................
8 List of Tables Table 1: Safe End Load Sets as Input to VESLFAT.......................................................................
9 Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT.......................................................
10 Table 3: Temperature-Dependent Material Properties for VESLFAT....................
11 Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves....................
12 Table 5: Pressure and Attached Piping Unit LoadCase Stress Components.................................
13 Table 6: Fatigue Usage Calculation for the Safe End (Inconel).......
13 Table 7: Fatigue Usage Calculation for the Safe End (Stainless Steel)..........................................
14 Table 8: Fatigue Usage Calculation for the Nozzle Blend Radius 15 Table 9: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location........................
16 Table 10: Linearized Stress Files Compiled for VY-StressResults.xls......................
18 File No.: 0801038.303 Page 2 of 18 Revision: 1 F0306-01RO


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1.0       OBJECTIVE The objective of this calculation package is to perform an ASME Code, Section III fatigue usage evaluation and a plant-specific evaluation of reactor water environmental effects for the reactor pressure vessel (RPV) core spray (CS) nozzle at the Vermont Yankee Nuclear Power Station.
1.0 OBJECTIVE The objective of this calculation package is to perform an ASME Code, Section III fatigue usage evaluation and a plant-specific evaluation of reactor water environmental effects for the reactor pressure vessel (RPV) core spray (CS) nozzle at the Vermont Yankee Nuclear Power Station.
1.1     Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:
1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:
: a. Changed Reference [1] to reflect revision of that document.
: a. Changed Reference [1] to reflect revision of that document.
: b. All other changes marked throughout this calculation are editorial changes made to the text of the calculation package.
: b. All other changes marked throughout this calculation are editorial changes made to the text of the calculation package.
2.0       METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
[2]. Based on that methodology, thermal stresses, pressure stresses, and attached piping load stresses were developed in the Reference [1] calculation for use in a fatigue calculation. The thermal stresses are added to pressure stresses and attached piping load stresses 1 . Both the pressure and piping' load stresses are scaled based on the magnitudes of the pressure and nozzle temperature during each transient. All six components of the stress tensor from the stress results are used in the fatigue calculation.
[2]. Based on that methodology, thermal stresses, pressure stresses, and attached piping load stresses were developed in the Reference [1] calculation for use in a fatigue calculation. The thermal stresses are added to pressure stresses and attached piping load stresses1. Both the pressure and piping' load stresses are scaled based on the magnitudes of the pressure and nozzle temperature during each transient. All six components of the stress tensor from the stress results are used in the fatigue calculation.
The fatigue calculation is performed for both of the limiting safe end and nozzle blend radius locations, as determined in the Reference [1] calculation, and uses the methodology of Subarticle NB-3200 of Section III of the ASME Code [3]. An environmental fatigue usage analysis is also performed in this calculation applying the methodology described in Reference [6].
The fatigue calculation is performed for both of the limiting safe end and nozzle blend radius locations, as determined in the Reference [1] calculation, and uses the methodology of Subarticle NB-3200 of Section III of the ASME Code [3]. An environmental fatigue usage analysis is also performed in this calculation applying the methodology described in Reference [6].
3.0       DESIGN INPUTS 3.1 Stress Calculation Linearized stress components at Node 3719 (limiting safe end path at inside surface) and Node 2166 (limiting nozzle blend radius path at inside surface) are used for the fatigue usage calculation, as shown in Figure 4 of Reference [1]. For the nozzle blend radius location, the stresses used in the evaluation are for the base metal only; that is, the cladding material is unselected prior to stress extraction. The stress components from the thermal stress analyses are combined with stress components due to pressure and piping loads. The linearized thermal stress components for each Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 70'F and the full values are reached at a reactor design temperature of 575F [2, Assumption 3.1.7]. In addition, design seismic and deadweight loads are also included and scaled in combination with the thermal loads for each transient. This combination, coupled with assigning the stress due to these loads the same sign as the thermal stress, is considered to be a very conservative treatment of the loads overall in that deadweight and design seismic loads are considered and scaled for every transient.
3.0 DESIGN INPUTS 3.1 Stress Calculation Linearized stress components at Node 3719 (limiting safe end path at inside surface) and Node 2166 (limiting nozzle blend radius path at inside surface) are used for the fatigue usage calculation, as shown in Figure 4 of Reference [1]. For the nozzle blend radius location, the stresses used in the evaluation are for the base metal only; that is, the cladding material is unselected prior to stress extraction. The stress components from the thermal stress analyses are combined with stress components due to pressure and piping loads. The linearized thermal stress components for each Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 70'F and the full values are reached at a reactor design temperature of 575F [2, Assumption 3.1.7]. In addition, design seismic and deadweight loads are also included and scaled in combination with the thermal loads for each transient. This combination, coupled with assigning the stress due to these loads the same sign as the thermal stress, is considered to be a very conservative treatment of the loads overall in that deadweight and design seismic loads are considered and scaled for every transient.
File No.: 0801038.303                                                                                                   Page 3 of 18 Revision: 1 F0306-OIRO
File No.: 0801038.303 Page 3 of 18 Revision: 1 F0306-OIRO


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transient are taken from the relevant output files associated with the Reference [1] calculation (a sample of which was provided in Table 4 of Reference [1]). The unit pressure stress component results are taken from Table 2 of Reference [1]. Piping load stress components are taken from Table 3 of the Reference [I] calculation.
transient are taken from the relevant output files associated with the Reference [1] calculation (a sample of which was provided in Table 4 of Reference [1]). The unit pressure stress component results are taken from Table 2 of Reference [1]. Piping load stress components are taken from Table 3 of the Reference [I] calculation.
3.2 Fatigue Usage Analysis, General Structural Integrity's VESLFAT program [4] is used to perform the fatigue usage calculation in accordance with the fatigue usage portion of ASME Code Subarticle NB-3200 [3]. VESLFAT performs the analysis required by NB-3222.4(e) [3] for Service Levels A and B conditions defined by the user. The VESLFAT program computes the primary-plus-secondary and total stress ranges for all events and performs a correction for elastic-plastic analysis, if necessary.
3.2 Fatigue Usage Analysis, General Structural Integrity's VESLFAT program [4] is used to perform the fatigue usage calculation in accordance with the fatigue usage portion of ASME Code Subarticle NB-3200 [3]. VESLFAT performs the analysis required by NB-3222.4(e) [3] for Service Levels A and B conditions defined by the user. The VESLFAT program computes the primary-plus-secondary and total stress ranges for all events and performs a correction for elastic-plastic analysis, if necessary.
The program computes the stress intensity range based on the stress component ranges for all event pairs [3, NB-3216.2]. The program evaluates the stress ranges for primary-plus-secondary and primary-plus-secondary-plus-peak stresses based on all six components of stress (3 normal and 3 shear stresses). If the primary-plus-secondary stress intensity range is greater than 3 Sm, the total stress range must be increased by the simplified elastic-plastic strain correction factor Ke, as described in NB-3228.5 [3]. The design stress intensity, Sm, is specified as a function of temperature. The input maximum temperature for both states of a load set pair is used to determine the temperature that Sm is determined from the user-defined values.
The program computes the stress intensity range based on the stress component ranges for all event pairs [3, NB-3216.2]. The program evaluates the stress ranges for primary-plus-secondary and primary-plus-secondary-plus-peak stresses based on all six components of stress (3 normal and 3 shear stresses). If the primary-plus-secondary stress intensity range is greater than 3 Sm, the total stress range must be increased by the simplified elastic-plastic strain correction factor Ke, as described in NB-3228.5 [3]. The design stress intensity, Sm, is specified as a function of temperature. The input maximum temperature for both states of a load set pair is used to determine the temperature that Sm is determined from the user-defined values.
When more than one stress set is defined for either of the event pair loadings, the stress differences are determined for all of the potential stress pairs, saving the maximum for the event pair, based on the pair producing the largest alternating total stress intensity (Salt), including any effects of Ke. The principal stresses for the stress ranges are determined by solving for the roots of the following cubic equation2:
When more than one stress set is defined for either of the event pair loadings, the stress differences are determined for all of the potential stress pairs, saving the maximum for the event pair, based on the pair producing the largest alternating total stress intensity (Salt), including any effects of Ke. The principal stresses for the stress ranges are determined by solving for the roots of the following cubic equation2:
S3 _ (aix "+ aiy +k (iz)S2 -+- ((x (yy + a(y (iz + (iz U, - Sxyz -x2_    2_-X yz2 )S
S3 _ (aix "+ aiy +k (iz)S2 -+- ((x (y y + a (y (iz + (iz U, - Sxyz -x2
                        - ((Fxa (y Uz + 2rxy Txz T"yz -   Uz Cxy   -2 (y Txz -_ax Tyz   )   0 The stress intensities for the event pairs are reordered in decreasing order of Salt, including a correction for the ratio of modulus of elasticity (E) from the fatigue curve divided by E from the material evaluated at the maximum event temperature. This allows a fatigue table to be created to eliminate the number of cycles available for each of the transient events. This fatigue table is based on a worst-case progressive pairing of events in order of the most severe alternating stress to the least severe, allowing determination of a bounding fatigue usage per NB-3222.4(e) [3]. For each load set pair in the fatigue table, the allowable number of cycles is determined based on Salt.
-X 2 _ yz2 )S
3.3       Event Cycles, VESLFAT For the Vermont Yankee CS nozzle analysis, transients that consist of combined stress ramps are split so that each successive ramp is treated separately. Therefore, there are 25 load sets based on the combined stress changes for the safe end, and 27 load sets based on the combined stress changes 2 Note that a., a,, a,, etc. are used synonymously with S,, S,,, S., etc., in this calculation.
- ((Fxa (y Uz + 2 rxy Txz T"yz - Uz Cxy  
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-2 (y Txz -_ax Tyz )
0 The stress intensities for the event pairs are reordered in decreasing order of Salt, including a correction for the ratio of modulus of elasticity (E) from the fatigue curve divided by E from the material evaluated at the maximum event temperature. This allows a fatigue table to be created to eliminate the number of cycles available for each of the transient events. This fatigue table is based on a worst-case progressive pairing of events in order of the most severe alternating stress to the least severe, allowing determination of a bounding fatigue usage per NB-3222.4(e) [3]. For each load set pair in the fatigue table, the allowable number of cycles is determined based on Salt.
3.3 Event Cycles, VESLFAT For the Vermont Yankee CS nozzle analysis, transients that consist of combined stress ramps are split so that each successive ramp is treated separately. Therefore, there are 25 load sets based on the combined stress changes for the safe end, and 27 load sets based on the combined stress changes 2 Note that a., a,, a,, etc. are used synonymously with S,, S,,, S., etc., in this calculation.
File No.: 0801038.303 Page 4 of 18 Revision: 1 F0306-OIRO


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for the nozzle blend radius location. The reason the number of load sets are not equal for each path is because the time history stress results of those paths differ. Tables 1 and 2 show the load sets applicable to plant operation, with cycle counts per Table 2 of Reference [2], used as input to VESLFAT for the safe end and nozzle blend radius locations, respectively. The cycle counts of Reference [2] consider 60 years of operation; see Reference [8] for the numbers of cycles. The data from Table I is entered into the VESLFAT input files VY-VFA T-1I. CYC (safe end-Inconel) and VY-VFAT2-1I.CYC (safe end-Stainless Steel), and the data from Table 2 is entered into the. file VY-VFA T-21.CYC (nozzle blend radius).
for the nozzle blend radius location. The reason the number of load sets are not equal for each path is because the time history stress results of those paths differ. Tables 1 and 2 show the load sets applicable to plant operation, with cycle counts per Table 2 of Reference [2], used as input to VESLFAT for the safe end and nozzle blend radius locations, respectively. The cycle counts of Reference [2] consider 60 years of operation; see Reference [8] for the numbers of cycles. The data from Table I is entered into the VESLFAT input files VY-VFA T-1I. CYC (safe end-Inconel) and VY-VFAT2-1I. CYC (safe end-Stainless Steel), and the data from Table 2 is entered into the. file VY-VFA T-21. CYC (nozzle blend radius).
3.4     Material Properties, VESLFAT Material properties are entered in VESLFAT input files VY-VFAT-]1.FDT (safe end-Inconel), VY-VY-VFAT2-1LFDT (safe end-Stainless Steel) and VY-VFAT-2I.FDT (nozzle blend radius). Table 3 lists the temperature-dependent material properties used in the analysis [5]. Table 4 lists the fatigue curve for the nozzle and safe end materials [3, Appendix I, Table 1-9.1 and Figure 1-9.1 (UTS < 80.0 ksi) for the nozzle blend radius, and Tables 1-9.1 and 1-9.2.2 (Curve C) and Figures 1-9.2.1 and 1-9.2.2 for both safe end locations]. Curve C is selected because it is the most conservative curve among the three extended curves for austenitic steel. VESLFAT automatically scales the stresses by the ratio of E on the fatigue curve to E in the analysis, for purposes of determining allowable numbers of cycles, as required by the ASME Code.
3.4 Material Properties, VESLFAT Material properties are entered in VESLFAT input files VY-VFAT-]1.FDT (safe end-Inconel), VY-VY-VFAT2-1LFDT (safe end-Stainless Steel) and VY-VFAT-2I.FDT (nozzle blend radius). Table 3 lists the temperature-dependent material properties used in the analysis [5]. Table 4 lists the fatigue curve for the nozzle and safe end materials [3, Appendix I, Table 1-9.1 and Figure 1-9.1 (UTS < 80.0 ksi) for the nozzle blend radius, and Tables 1-9.1 and 1-9.2.2 (Curve C) and Figures 1-9.2.1 and 1-9.2.2 for both safe end locations]. Curve C is selected because it is the most conservative curve among the three extended curves for austenitic steel. VESLFAT automatically scales the stresses by the ratio of E on the fatigue curve to E in the analysis, for purposes of determining allowable numbers of cycles, as required by the ASME Code.
Other material properties are input as follows:
Other material properties are input as follows:
m 1.7, n = 0.3, parameters used to calculate Ke for the safe end location (both materials) [3, Table NB-3228.5(b)-1]
m 1.7, n = 0.3, parameters used to calculate Ke for the safe end location (both materials) [3, Table NB-3228.5(b)-1]
Line 215: Line 474:
E from fatigue curve = 28,300 ksi [3, Appendix I, Figure 1-9.2] for the safe end locations.
E from fatigue curve = 28,300 ksi [3, Appendix I, Figure 1-9.2] for the safe end locations.
E from fatigue curve = 30,000 ksi [3, Appendix I, Figure 1-9.1 ] for the nozzle blend radius location.
E from fatigue curve = 30,000 ksi [3, Appendix I, Figure 1-9.1 ] for the nozzle blend radius location.
3.5     Stress Indices Stress indices are calculated per Reference [2, Section 3.8]. For the safe end location and using the ANSYS thermal stress results, the membrane plus bending stress results are multiplied by K3 and then are added to the peak thermal stress results to yield total thermal stress, taking guidance from Equation 11 of NB-3600 [3]. The total thermal stresses are then added to the total piping and total pressure stresses.
3.5 Stress Indices Stress indices are calculated per Reference [2, Section 3.8]. For the safe end location and using the ANSYS thermal stress results, the membrane plus bending stress results are multiplied by K3 and then are added to the peak thermal stress results to yield total thermal stress, taking guidance from Equation 11 of NB-3600 [3]. The total thermal stresses are then added to the total piping and total pressure stresses.
C1 = C2 = C3 = 1, because the ANSYS model is sufficient to account for the effects of gross structural discontinuity. The path for Node 2166 does not contain a weld and, therefore, does not take the same guidance from NB-3600. However, the path for Node 3719 uses guidance and the following values from NB-3600 for an "as welded girth butt weld":
C1 = C2 = C3 = 1, because the ANSYS model is sufficient to account for the effects of gross structural discontinuity. The path for Node 2166 does not contain a weld and, therefore, does not take the same guidance from NB-3600. However, the path for Node 3719 uses guidance and the following values from NB-3600 for an "as welded girth butt weld":
K1 = 1.2, From Table 3681(a)-I of NB-3600 [3]
K1 = 1.2, From Table 3681(a)-I of NB-3600 [3]
K 2 = 1.8, From Table 3681(a)-I of NB-3600 [3]
K 2 = 1.8, From Table 3681(a)-I of NB-3600 [3]
K 3 = 1.7, From Table 3681(a)-I of NB-3600 [3]
K3 = 1.7, From Table 3681(a)-I of NB-3600 [3]
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V     StructuralIntegrity Associates, Inc.
V Structural Integrity Associates, Inc.
The K values listed above are used to multiply the Membrane plus Bending stress results of the pressure load and piping load to yield Total Stress. So, Ki * (Memb+Bend)pressure = Total Stresspressure and K2 * (Memb+Bend)piping = Total StressPiping.
The K values listed above are used to multiply the Membrane plus Bending stress results of the pressure load and piping load to yield Total Stress. So, Ki * (Memb+Bend)pressure = Total Stresspressure and K2 * (Memb+Bend)piping = Total StressPiping.
4.0     CALCULATIONS Table 5 contains the stress components at the locations of interest for the 1,000 psi unit pressure stress case [1, Table 2]. Table 5 also contains the stress components for the attached piping load unit stress case [1, Table 3], which correspond to a reactor design temperature of 575'F [2, Section 3.1.7].
4.0 CALCULATIONS Table 5 contains the stress components at the locations of interest for the 1,000 psi unit pressure stress case [1, Table 2]. Table 5 also contains the stress components for the attached piping load unit stress case [1, Table 3], which correspond to a reactor design temperature of 575'F [2, Section 3.1.7].
The attached piping load stress components were applied assuming the same signs as the thermal stress, which yields the largest stress component ranges.
The attached piping load stress components were applied assuming the same signs as the thermal stress, which yields the largest stress component ranges.
The stress indices for each location and loading scenario are calculated in the previous section. These stress indices are used in the Excel workbooks described below.
The stress indices for each location and loading scenario are calculated in the previous section. These stress indices are used in the Excel workbooks described below.
The calculations of all of the VESLFAT stress inputs are automated in Excel workbooks VY-VFAT-]i.xls (safe end-both materials) and VY-VFAT-2i.xls (nozzle blend radius). These files are organized with sheets labeled as follows:
The calculations of all of the VESLFAT stress inputs are automated in Excel workbooks VY-VFAT-]i.xls (safe end-both materials) and VY-VFAT-2i.xls (nozzle blend radius). These files are organized with sheets labeled as follows:
* Overview: Contains general information.
Overview: Contains general information.
* Other Stresses: Contains pressure and attached piping load stresses. As shown in Table 5, the pressure and thermal stresses use the membrane-plus-bending and total stress from the finite element analysis [1], and include stress indices where appropriate.
* Other Stresses: Contains pressure and attached piping load stresses. As shown in Table 5, the pressure and thermal stresses use the membrane-plus-bending and total stress from the finite element analysis [1], and include stress indices where appropriate.
Rearranger: There are 7 Rearranger sheets, one for each thermal transient as analyzed by ANSYS. In these sheets, thermal stresses are copied from Excel workbook VY-StressResults.xls, and rearranged to conform to VESLFAT input format (including switching the shear stress components Sxz and Syz as required by VESLFAT). VY-StressResults.xls contains the results of the ANSYS stress linearization for each transient. The files contained within this workbook are shown in Table 10. Time-varying scale factors for the attached piping loads (based on path metal temperature) and pressure are determined, and used to scale the unit load case stresses, which are then added to the thermal stresses. Since the attached piping loads can act in any direction, the stresses due to the attached piping loads are assigned the same sign as the thermal stresses to maximize the component stresses.
Rearranger: There are 7 Rearranger sheets, one for each thermal transient as analyzed by ANSYS. In these sheets, thermal stresses are copied from Excel workbook VY-StressResults.xls, and rearranged to conform to VESLFAT input format (including switching the shear stress components Sxz and Syz as required by VESLFAT). VY-StressResults.xls contains the results of the ANSYS stress linearization for each transient. The files contained within this workbook are shown in Table 10. Time-varying scale factors for the attached piping loads (based on path metal temperature) and pressure are determined, and used to scale the unit load case stresses, which are then added to the thermal stresses. Since the attached piping loads can act in any direction, the stresses due to the attached piping loads are assigned the same sign as the thermal stresses to maximize the component stresses.
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VESLFAT: Contains the VESLFAT stress input, as obtained from the Rearranger sheets.
VESLFAT: Contains the VESLFAT stress input, as obtained from the Rearranger sheets.
Load set numbers are entered on this sheet, as defined in Table I and Table 2. These sheets are saved to VESLFAT input files VY-VFAT-]i.STR (safe end-Inconel), VY-VFAT2-1i.STR (safe end-Stainless Steel), and VY-VFAT-2i.STR (nozzle blend radius).
Load set numbers are entered on this sheet, as defined in Table I and Table 2. These sheets are saved to VESLFAT input files VY-VFAT-]i.STR (safe end-Inconel), VY-VFAT2-1i.STR (safe end-Stainless Steel), and VY-VFAT-2i.STR (nozzle blend radius).
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W StructuralIntegrityAssociates, Inc.
W Structural Integrity Associates, Inc.
5.0     RESULTS OF ANALYSIS Table 6, Table 7 and Table 8 provide the detailed calculated 60-year fatigue usage, as obtained from VESLFAT output files VY-VFAT-11.FAT (safe end-Inconel), VY-VFAT2-1LFAT (safe end-Stainless Steel), and VY-VFAT-2L.FAT (nozzle blend radius). All VESLFAT input and output files are saved in the project computer files associated with this calculation.
5.0 RESULTS OF ANALYSIS Table 6, Table 7 and Table 8 provide the detailed calculated 60-year fatigue usage, as obtained from VESLFAT output files VY-VFAT-11.FAT (safe end-Inconel), VY-VFAT2-1LFAT (safe end-Stainless Steel), and VY-VFAT-2L.FAT (nozzle blend radius). All VESLFAT input and output files are saved in the project computer files associated with this calculation.
From Table 6, the safe end (Inconel) cumulative usage factor (CUF) is 0.000174 for 60 years. From Table 7, the safe end (Stainless Steel) cumulative usage factor (CUF) is 0.000742 for 60 years.
From Table 6, the safe end (Inconel) cumulative usage factor (CUF) is 0.000174 for 60 years. From Table 7, the safe end (Stainless Steel) cumulative usage factor (CUF) is 0.000742 for 60 years.
From Table 8, the nozzle blend radius CUF is 0.0171 for 60 years.
From Table 8, the nozzle blend radius CUF is 0.0171 for 60 years.
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The resulting EAF adjusted CUF value is 0.0171 x 8.20 = 0.140, which is less than the allowable value of 1.0 and is therefore acceptable.
The resulting EAF adjusted CUF value is 0.0171 x 8.20 = 0.140, which is less than the allowable value of 1.0 and is therefore acceptable.


==6.0     CONCLUSION==
==6.0 CONCLUSION==
S AND DISCUSSIONS Detailed fatigue calculations for the Vermont Yankee CS nozzle were performed based on the results of stress analyses previously performed [1]. The thermal stresses were combined with stresses due to pressure and attached piping loads, both of which were scaled based on the magnitudes of the pressure and metal temperature during each thermal transient. All six components of the stress tensor were used for the fatigue calculations. The fatigue calculations were performed at previously-determined limiting locations in the safe end and nozzle blend radius, and used the methodology of Subarticle NB-3200 of Section III of the ASME Code [3].
S AND DISCUSSIONS Detailed fatigue calculations for the Vermont Yankee CS nozzle were performed based on the results of stress analyses previously performed [1]. The thermal stresses were combined with stresses due to pressure and attached piping loads, both of which were scaled based on the magnitudes of the pressure and metal temperature during each thermal transient. All six components of the stress tensor were used for the fatigue calculations. The fatigue calculations were performed at previously-determined limiting locations in the safe end and nozzle blend radius, and used the methodology of Subarticle NB-3200 of Section III of the ASME Code [3].
The 60-year CUF for the safe end location (Inconel) was determined to be 0.000 174, the safe end location (Stainless Steel) was determined to be 0.000742, and the CUF for the nozzle blend radius File No.: 0801038.303                                                                                   Page 7 of 18 Revision: 1 F0306-O1RO
The 60-year CUF for the safe end location (Inconel) was determined to be 0.000 174, the safe end location (Stainless Steel) was determined to be 0.000742, and the CUF for the nozzle blend radius File No.: 0801038.303 Page 7 of 18 Revision: 1 F0306-O1RO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
location was determined to be 0.0171. All three values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.
location was determined to be 0.0171. All three values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.
Detailed EAF assessments were also performed for the two CS nozzle locations. The 60-year EAF CUF for the safe end location was determined to be 0.000259 using standard Alloy 600 methodology
Detailed EAF assessments were also performed for the two CS nozzle locations. The 60-year EAF CUF for the safe end location was determined to be 0.000259 using standard Alloy 600 methodology
Line 256: Line 515:
The 60-year EAF CUF for the nozzle blend radius location was determined to be 0.140 using temperature-dependent Fen multipliers for each load pair. All EAF CUF values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.
The 60-year EAF CUF for the nozzle blend radius location was determined to be 0.140 using temperature-dependent Fen multipliers for each load pair. All EAF CUF values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.


==7.0     REFERENCES==
==7.0 REFERENCES==
: 1. Structural Integrity Associates Calculation No. 0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle."
: 1. Structural Integrity Associates Calculation No. 0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle."
: 2. Structural Integrity Associates Calculation No. 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle."
: 2. Structural Integrity Associates Calculation No. 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle."
Line 265: Line 524:
: 7. EPRI Report No. TR-105759, "An Environmental Factor Approach to Account for Reactor Water Effects in Light Water Reactor Pressure Vessel and Piping Fatigue Evaluations,"
: 7. EPRI Report No. TR-105759, "An Environmental Factor Approach to Account for Reactor Water Effects in Light Water Reactor Pressure Vessel and Piping Fatigue Evaluations,"
December 1995.
December 1995.
: 8. Entergy Design Input Record (DIR) EC No. 1773, DIR. Revision 1, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY- 16Q-209.
: 8. Entergy Design Input Record (DIR) EC No. 1773, DIR. Revision 1, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-16Q-209.
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VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
Table 1: Safe End Load Sets as Input to VESLFAT VESLFAT                 Start Temp Change Pressure Change Transient   tiee                               Cycles Load Set            Time, sec Tm2 T1_         0       None        None        120 2      Trn2T2_       0       None          Up        120 3      Trn2T3_       0       None        Down        120 4        1Tm3r       0         Up            Up        300 5        2Trn3       56.6       Up            Up        300 6      I1Tml 1-     0       None      Up & Down      10 7      2Trnl 1       5     Down          Down        10 8      3Tml 1     26.962     Down          None        10 9      4Trn I 1   207.34   Down & Up      None        10 10      5TrnIl 1   1734.9   Up & Down      Down        10 11      6Trnl 1   2332.6   Down & Up    Down & UP      10 12      7Trnl 1   5625.1   Up & Down    Up & Down      10 13      8Trnl 1   7125.4   Down & Up    Down & Up      10 14      9Trnl 1   14315   Up & Down        Up        10 15      1OTrnl 1   16749     Down          None        10 16      lTrnl4       0       Down          Down        1 17      2Tm14       270     Down          Down        1 18      lTrn21       0       Down          Down        300 19      2Trn2l     17.00     Down          Down        300 20      Tn24_TI_       0       None        None        1 21      Tn24 T2       0       None          Up        1 22      Tn24_T3_       0       None        Down        1 23        1Trn3O       0       Down          Down        1 24        2Trn3O       12.2     Down         Down         1 25        3Trn3O      631      None         Down         1 File No.: 0801038.303                                                                   Page 9 of 18 Revision: I F0306-0IRO
Table 1: Safe End Load Sets as Input to VESLFAT VESLFAT Load Set 2
3 4
5 6
7 8
9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 Start Transient tiee Time, sec Tm2 T1_
0 Trn2T2_
0 Trn2T3_
0 1Tm3r 0
2Trn3 56.6 I1Tml 1-0 2Trnl 1 5
3Tml 1 26.962 4Trn I 1 207.34 5TrnIl 1 1734.9 6Trnl 1 2332.6 7Trnl 1 5625.1 8Trnl 1 7125.4 9Trnl 1 14315 1OTrnl 1 16749 lTrnl4 0
2Tm14 270 lTrn21 0
2Trn2l 17.00 Tn24_TI_
0 Tn24 T2 0
Tn24_T3_
0 1Trn3O 0
2Trn3O 12.2 3Trn3O 631 Temp Change Pressure Change None None None Up Up None Down Down Down & Up Up & Down Down & Up Up & Down Down & Up Up & Down Down Down Down Down Down None None None Down Down None None Up Down Up Up Up & Down Down None None Down Down & UP Up & Down Down & Up Up None Down Down Down Down None Up Down Down Down Down Cycles 120 120 120 300 300 10 10 10 10 10 10 10 10 10 10 1
1 300 300 1
1 1
1 1
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StructuralIntearity Associates, Inc.
Structural Intearity Associates, Inc.
Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT Start VESLFAT Transient   Time, Temp Change Pressure Change Cycles Load Set sec Inc.
Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT VESLFAT Load Set Transient Structurai Integrity Associates, Inc.
Trn2_TI       0       None          None      120 Associates, Structurai Integrity Trn2_T2_      0       None          Up        120 Trn2_T3_      0       None        Down        120 1Trn3_    .0         Up            Up        300 2Trn3      56.6       Up            Up        300 ITrnll1      0       None      Up & Down      10 2Trn I1_      5     Down          Down        10 3Trnl 1  142.64   Down & Up      None        10 4Trnl 1  1655.2   Up & Down      Down        10 5Trnl I  2302.7   Down & Up   Down & Up       10 6Trn 11  3193.7  Up & Down   Up & Down       10 7Trnl I  7255.1  Down & Up       Down         10 8Trnl I    9913        Up       Down & Up       10 9Trnll1    12514  Up and Down       Up         10 1Trnl4_      0      Down         Down 2Tm14 2Trnl4_      40      Down         Down 3Tm14      1200    Down         Down 1Tmn21I      0      Down         Down       300 2Tin21I    32.15    Down         Down       300 3Tm2l1    6462.7    Down          None        300 Tn24_Ti1      0      None        None        1 Tn24 T2        0      None          Up        1 Tn24_T3_      0      None        Down        1 1Tm30_        0      None        Down        1 2Tmn3O      1.2    Down          Down        1 3Tmn30      25      Down          Down        1 4Tmn30_    3331      Down          Down        1 File No.: 0801038.303                                                                     Page 10 of 18 Revision: 1 F0306-O1RO
Trn2_TI Trn2_T2_
Trn2_T3_
1Trn3_
2Trn3 ITrnll1 2Trn I1_
3Trnl 1 4Trnl 1 5Trnl I 6Trn 11 7Trnl I 8Trnl I 9Trnll1 1Trnl4_
2 Tm14 2Trnl4_
3Tm14 1Tmn21I 2Tin21I 3Tm2l1 Tn24_Ti1 Tn24 T2 Tn24_T3_
1Tm30_
2Tmn3O 3Tmn30 4Tmn30_
Start
: Time, sec 0
0 0
.0 56.6 0
5 142.64 1655.2 2302.7 3193.7 7255.1 9913 12514 0
40 1200 0
32.15 6462.7 0
0 0
0 1.2 25 3331 Temp Change Pressure Change Cycles None None None Up Up None Down Down & Up Up & Down Down & Up Up & Down Down & Up Up Up and Down Down Down Down Down Down Down None None None None Down Down Down None Up Down Up Up Up & Down Down None Down Down & Up Up & Down Down Down & Up Up Down Down Down Down Down None None Up Down Down Down Down Down 120 120 120 300 300 10 10 10 10 10 10 10 10 10 300 300 300 1
1 1
1 1
1 1
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StructuralIntegrityAssociates, Inc.
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Table 3: Temperature-Dependent Material Properties for VESLFAT                                   (4)
Table 3: Temperature-Dependent Material Properties for VESLFAT (4)
Material             T, OF   E x 106 , psi     S., ksi     Sy, ksi SB-166 Inconel             70        31.0          23.3        35.0
Material T, OF E x 106, psi S., ksi Sy, ksi SB-166 Inconel
                                    .(safe end(')           200       30.2           23.3        32.0 300      29.8           23.3        31.2 400        29.5            23.3       30.7 500      29.0           23.3       30.3 600        28.7            23.3       29.9
.(safe end(')
* SA-508  Class 2 (5)        70      27.8            26.7       50.0 (Nozzle blend radius    (2)) 200        27.1            26.7       47.0 300        26.7           26.7       45.5 400        26.1            26.7        44.2 500      25.7           26.7        43.2 600        25.2            26.7       42.1 SA-312 TP 304               70      28.3            20          30 (Core Spray Piping                     27.6 200                        20          25 8 x 10 Reducer (3))
* SA-508 Class 2(5)
300        27.0            20        22.4 400        26.5            18.7        20.7 500        25.8            17.5        19.4 600        25.3            16.4        18.4 Notes:
(Nozzle blend radius (2))
: 1. For the safe end material, SB-166 Inconel properties are used (72Ni-15Cr-8Fe), per Reference [2]. Annealed heat treatment is conservatively assumed for Sm and Sy values.
70 200 300 400 500 600 70 200 300 400 500 600 70 200 300 400 500 600 31.0 30.2 29.8 29.5 29.0 28.7 27.8 27.1 26.7 26.1 25.7 25.2 28.3 27.6 27.0 26.5 25.8 25.3 23.3 23.3 23.3 23.3 23.3 23.3 26.7 26.7 26.7 26.7 26.7 26.7 20 20 20 18.7 17.5 16.4 35.0 32.0 31.2 30.7 30.3 29.9 50.0 47.0 45.5 44.2 43.2 42.1 30 25 22.4 20.7 19.4 18.4 SA-312 TP 304 (Core Spray Piping 8 x 10 Reducer (3))
: 2. For the nozzle blend radius material, SA508 Class 2 material properties are used (3/4Ni-1/2Mo-1/3Cr-V), per Reference [2].
Notes:
: 3. For the nozzle safe end extension material, SA-312 TP304 material properties are used (18Cr-8Ni), per Reference [2].
: 1.
: 4. All values are taken from Reference [5].
For the safe end material, SB-166 Inconel properties are used (72Ni-15Cr-8Fe), per Reference [2]. Annealed heat treatment is conservatively assumed for Sm and Sy values.
: 5. SA-508 Class 2 in the Code of Construction is the same as SA-508 Gr. 2 Class 2 in the 1998 ASME Code [5]
: 2.
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For the nozzle blend radius material, SA508 Class 2 material properties are used (3/4Ni-1/2Mo-1/3Cr-V), per Reference [2].
: 3.
For the nozzle safe end extension material, SA-312 TP304 material properties are used (18Cr-8Ni), per Reference [2].
: 4.
All values are taken from Reference [5].
: 5.
SA-508 Class 2 in the Code of Construction is the same as SA-508 Gr. 2 Class 2 in the 1998 ASME Code [5]
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6     StructuralIntegrityAssociates, Inc.
6 Structural Integrity Associates, Inc.
Table 4: Carbon/Low Alloy Steel and Stainless Steel/Nickel Alloy Fatigue Curves Sa, ksi                       S,, ksi Number of Cycles      Carbon/Low Alloy (1)       Austenitic/Nickel Alloy 10                 580                           708 20                410                            512 50                275                            345 100                205                            261 200                155                          201 500                105                          148 1000                  83                          119 2000                  64                            97 5000                  48                            76 10000                38                            64 20000                  31                          55.5 50000                  23                          46.3 100000                  20                          40.8 200000                16.5                          35.9 500000                13.5                            31 1000000              12.5                          28.2 2.E+06                N/A                          22.8(2) 5.E+06                N/A                          18.4(2) 1.E+07              N/A                          16.4(2) 2.E+07                N/A                          15.2(2) 5.E+07              N/A                          14.3(2) 1.E+08              N/A                          14.1(2) 1.E+09              N/A                          13.9(2) 1.E+10              N/A                          13.7(2) 1.E+311              N/A                          13.6(2)
Table 4: Carbon/Low Alloy Steel and Stainless Steel/Nickel Alloy Fatigue Curves Number of Cycles Sa, ksi Carbon/Low Alloy (1)
S,, ksi Austenitic/Nickel Alloy 10 20 50 100 200 500 1000 2000 5000 10000 20000 50000 100000 200000 500000 1000000 2.E+06 5.E+06 1.E+07 2.E+07 5.E+07 1.E+08 1.E+09 1.E+10 1.E+311 580 410 275 205 155 105 83 64 48 38 31 23 20 16.5 13.5 12.5 N/A N/A N/A N/A N/A N/A N/A N/A N/A 708 512 345 261 201 148 119 97 76 64 55.5 46.3 40.8 35.9 31 28.2 22.8(2) 18.4(2) 16.4(2) 15.2(2) 14.3(2) 14.1(2) 13.9(2) 13.7(2) 13.6(2)
Note:
Note:
: 1. Using UTS _ 80 ksi curve.
: 1. Using UTS _ 80 ksi curve.
: 2. Using Curve C for austenitic steel/nickel alloy.
: 2.
File No.: 0801038.303                                                                         Page 12 of 18 Revision: I F0306-OIRO
Using Curve C for austenitic steel/nickel alloy.
File No.: 0801038.303 Revision: I Page 12 of 18 F0306-OIRO


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Table 5: Pressure and Attached Piping Unit Load Case Stress Components Membrane plus Bending (1)                                                 Total   )
Table 5: Pressure and Attached Piping Unit Load Case Stress Components Membrane plus Bending (1)
Node                                                         S   y"(
Total )
s)                   Sy    (5)   S         Sx             Sz(s5)
Node S
Load           (2)         Sx           SY           Sz       Sy       Sxz               S           S           S               Sxz       yZ Pressure(3)     3719     -1011           4829       11010     -104.8       0     0       -1011         4912         11050     -85.31   0       0 2166     -1052           1657     25960       4886       0     0       -1052         1720       35050       348.9   0       0 Piping(4)       3719         0           6502         0       658     1222   0         0         11704         0         1184   2200       0 2166         0           82           0       30       20     0         0           82           0         30     20       0
y"(
        'MnM,     1   All otr*-oc ,an m or* , nnitc nfendf
s)
: 2. The safe end location is represented by Node 3719, and the nozzle blend radius location is represented by Node 2166.
(5)
: 3. The stresses for both nodes represent the stress due to an applied pressure of 1,000 psig.
Sy S
: 4. Piping stresses for both locations represent the stress due to full attached piping loads at an RPV temperature of 575'F.
Sx Sz(s5)
: 5. Sy. and S. components have been rearranged from the ANSYS output in order to be in correct order for VESLFAT.
Load (2)
Sx SY Sz Sy Sxz S
S S
Sxz yZ Pressure(3) 3719  
-1011 4829 11010  
-104.8 0
0  
-1011 4912 11050  
-85.31 0
0 2166  
-1052 1657 25960 4886 0
0  
-1052 1720 35050 348.9 0
0 Piping(4) 3719 0
6502 0
658 1222 0
0 11704 0
1184 2200 0
2166 0
82 0
30 20 0
0 82 0
30 20 0
'MnM, 1
All otr*-oc,an or*
m
, nnitc nfendf 2.
3.
4.
5.
The safe end location is represented by Node 3719, and the nozzle blend radius location is represented by Node 2166.
The stresses for both nodes represent the stress due to an applied pressure of 1,000 psig.
Piping stresses for both locations represent the stress due to full attached piping loads at an RPV temperature of 575'F.
Sy. and S. components have been rearranged from the ANSYS output in order to be in correct order for VESLFAT.
Table 6: Fatigue Usage Calculation for the Safe End (Inconel)
Table 6: Fatigue Usage Calculation for the Safe End (Inconel)
Load                             Load                                                                    Salt
Load
        #1       Desc. #1             #2       Desc. #2         n (cvcles)     Sn (psi)         Ke         (psi)         Nallow           U 24       2Trn3O               25       3Trn3O_               1         67883                     63663           10260       0.000098 17        2Trn 14              23        1Trn30                1        44360                    48903          37919        0.000026 5          2Trn3_            .8        3Trn 1_              10        26107                      18347        5088300      0.000002 5          2Trn3              9        4Trn 11_              10        25551                      17850        6002500      0.000002 5          2Trn3              6        1Trn 11              10        24728                      16797        8657500      0.000001 5          2Tm3_              7        2Tn I I_              10        24429                      16784        8698300      0.000001 5          2Trn3              10        5Trnl 1_              10        23571                      16559        9436700      0.000001 5          2Trn3_            14        9Trn 1I-              10        23593                      16507        9615800      0.000001 5          2Trn3_            11        6Trnl 1_              10        23214                      16399        10007000      0.000001 5          2Trn3_            15        1OTrnl 11            10        23358                      16262        10800000      0.000001 5          2Trn3_            .12        7Trnl 1              10        23247                      15968        12760000      0.000001 4          1Trn3_              5          2Trn3_            210        23000                      15922        13097000      0.000016 4          1Trn3_              19        2Trn21l              90        22979                      15914        13155000      0.000007 1      Trn2_Ti1              19        2Trn2l_              120        22979                      15899      .13273000      0.000009 19        2Trn2l_            20      Tn24_TI1                1        22383                      15552        16233000      0.000000 19        2Trn2l1            22      Tn24_T3_                1        22383                      15552        16233000      0.000000 3      Trn2_T3_              19      2Tm2l_                88        22383                      15552        16233000      0.000005 3      Trn2_T3_              18        1Trn21              32        22389                      15549        16263000      0.000002 Total Usage        0.000174 Note:     All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
#1 Load Desc. #1  
File No.: 0801038.303                                                                                                                   Page 13 of 18 Revision: 1 F0306-0IRO
#2 Salt Desc. #2 n (cvcles)
Sn (psi)
Ke (psi)
Nallow U
24 17 5
5 5
5 5
5 5
5 5
4 4
1 19 19 3
3 2Trn3O 2Trn 14 2Trn3_
2Trn3 2Trn3 2Tm3_
2Trn3 2Trn3_
2Trn3_
2Trn3_
2Trn3_
1Trn3_
1Trn3_
Trn2_Ti1 2Trn2l_
2Trn2l1 Trn2_T3_
Trn2_T3_
25 23
.8 9
6 7
10 14 11 15
.12 5
19 19 20 22 19 18 3Trn3O_
1Trn30 3Trn 1_
4Trn 11_
1 Trn 11 2Tn I I_
5Trnl 1_
9Trn 1I-6Trnl 1_
1OTrnl 11 7Trnl 1 2Trn3_
2Trn21l 2Trn2l_
Tn24_TI1 Tn24_T3_
2Tm2l_
1Trn21 1
1 10 10 10 10 10 10 10 10 10 210 90 120 1
1 88 32 67883 44360 26107 25551 24728 24429 23571 23593 23214 23358 23247 23000 22979 22979 22383 22383 22383 22389 63663 48903 18347 17850 16797 16784 16559 16507 16399 16262 15968 15922 15914 15899 15552 15552 15552 15549 10260 37919 5088300 6002500 8657500 8698300 9436700 9615800 10007000 10800000 12760000 13097000 13155000
.13273000 16233000 16233000 16233000 16263000 Total Usage 0.000098 0.000026 0.000002 0.000002 0.000001 0.000001 0.000001 0.000001 0.000001 0.000001 0.000001 0.000016 0.000007 0.000009 0.000000 0.000000 0.000005 0.000002 0.000174 Note:
All other load pairs have an alternating stress, they do not contribute to fatigue usage.
Salt, that is below the endurance limit of the fatigue curve. Therefore, File No.: 0801038.303 Page 13 of 18 Revision: 1 F0306-0IRO


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Table 7: Fatigue Usage Calculation for the Safe End (Stainless Steel)
Table 7: Fatigue Usage Calculation for the Safe End (Stainless Steel)
Load                     Load                                                              Salt Desc. #1                   Desc. #2     n (cycles)       Sn (psi)     Ke                       Nallow          U
Load
        #1                       #2                                                              (psi) 24      2Trn3O          25        3Trn3O_            1            68465      1.47      101779         1699.05     0.000589 17      2Trn 14          23        1Trn30              1            44360        1      54103          22751      0.000044 5      2Trn3            8        3Trn 11_          10            26107        1      20551          3117000    0.000003 5      2Trn3            9        4Trn 11_          10            25551        1      19856          3611400    0.000003 5      2Trn3            6        1Trn 11            10            24728        1      18923          4435200    0.000002 5      2Trn3_          7        2Trnl 1_          10            24429        1      18905        4453400      0.000002 5      2Trn3_          14        9Trnl 1_          10            23593        1      18620        4752000      0.000002 5      2Trn3_          10        5Trnl 11          10            23626        1      18525        4857700      0.000002 5      2Trn3_          15        1OTrnl 11          10            23358        1      18336          5106400    0.000002 5      2Trn3_          11        6Trn 1I-          10            23214        1      18295        5175200      0.000002 4        1Trn3_          5        2Trn3_                          23000        1      17975          5755400    0.000038 4        1Trn3_        19        2Trn2l_                          22979        1      17967          5772000    0.000014 1    Trn2 T1          19        2Trn2l_                          22979        1      17949          5806200    0.000021 19      2Trn21          20      Tn24 Ti                          22383        1      17557        6632000      0.000000 19      2Trn2l          22      Tn24_T3_                          22383        1      17557        6632000      0.000000 3    Trn2 T3          19        2Trn2l                          22383        1      17557        6632000      0.000015 3    Trn2_T3_          18        1Trn21_            22            22389        1      17554        6640000      0.000003 Total 0.000742 Usage =
#1 24 17 5
Note:   All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
5 5
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5 5
5 5
5 4
4 1
19 19 3
3 Desc. #1 2Trn3O 2Trn 14 2Trn3 2Trn3 2Trn3 2Trn3_
2Trn3_
2Trn3_
2Trn3_
2Trn3_
1 Trn3_
1Trn3_
Trn2 T1 2Trn21 2Trn2l Trn2 T3 Trn2_T3_
Load
#2 25 23 8
9 6
7 14 10 15 11 5
19 19 20 22 19 18 Desc. #2 3Trn3O_
1 Trn30 3Trn 11_
4Trn 11_
1 Trn 11 2Trnl 1_
9Trnl 1_
5Trnl 11 1OTrnl 11 6Trn 1I-2Trn3_
2Trn2l_
2Trn2l_
Tn24 Ti Tn24_T3_
2Trn2l 1Trn21_
n (cycles) 1 1
10 10 10 10 10 10 10 10 22 Sn (psi) 68465 44360 26107 25551 24728 24429 23593 23626 23358 23214 23000 22979 22979 22383 22383 22383 22389 Ke 1.47 1
1 1
1 1
1 1
1 1
1 1
1 1
1 1
1 Salt (psi) 101779 54103 20551 19856 18923 18905 18620 18525 18336 18295 17975 17967 17949 17557 17557 17557 17554 Nallow 1699.05 22751 3117000 3611400 4435200 4453400 4752000 4857700 5106400 5175200 5755400 5772000 5806200 6632000 6632000 6632000 6640000 Total Usage =
U 0.000589 0.000044 0.000003 0.000003 0.000002 0.000002 0.000002 0.000002 0.000002 0.000002 0.000038 0.000014 0.000021 0.000000 0.000000 0.000015 0.000003 0.000742 Note:
All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
File No.: 0801038.303 Revision: 1 Page 14 of 18 F0306-01RO


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Table 8: Fatigue Usage Calculation for the Nozzle Blend Radius Load
Table 8: Fatigue Usage Calculation for the Nozzle Blend Radius Load Load n
            #1     Desc. #1       Load L#2       Desc. #2             n (cycles)       Sn (psi)   Ke       Salt (psi)         Nallow       U 25       2Trn3O0       26       3Trn3O0               1         51402     1.00     44455           6278       0.0002 8      3Trnl 1_        13      8Trnl 1_            10         15961     1.00     39383           8994       0.0011 19      2Trn21        22      Tn24_T2_              1         39644     1.00     34138         14404       0.0001 7      2Trnl 1       27        4Trn3O0              1        38618     1.00     27466         28999       0.0000 4        1Trn3_        7        2Trnl 1_            9         36665     1.00     27150         30048       0.0003 10       5Trn11 _      19        2Trn21l            10          15935     1.00     26332         33005       0.0003 1      Trn2 TI          6        1Trn 11            10         49693     1.00     25486         36486       0.0003 2      Trn2_T2_        19        2Trn21,            120         25423     1.00     24010         43822       0.0027 12      7Trnl 1        19        2Trn21              10         13983     1.00     23200         48691       0.0002 1      Trn2_Ti1        9        4Trnl 1            10         47005     1.00     22776         52484       0.0002 4        1Trn3_        11        6Trn 11_            10         35885     1.00     22731         53008       0.0002 1      Trn2 T1          5        2Trn3            100         44974     1.00     22190         59737       0.0017 4        1Trn3_        5        2Trn3_          200           44974     1.00     22190         59737       0.0033 4        1Trn3_        24        lTrn30-              1         44912     1.00     22187         59767       0.0000 4        1Trn3_        18        1Trn21_            80         44912     1.00     22187         59767       0.0013 17      3Trn14_        18        1Trn21_              1         44598     1.00     21478         70216       0.0000 18      1Trn21_        20        3Trn21_          219           43608     1.00     21218         74590       0.0029 19      2Trn21_        20        3Trn21_            81         43426     1.00     21130         76147       0.0011 3      Trn2_T3_        19        2Trn21l            78         43219     1.00     21117         76367       0.0010 3      Trn2 T3        14        9Trn 11_            10         43408     1.00     21016         78221       0.0001 3      Trn2_T3_        15        1Trn14_              1         42722     1.00     20993         78639       0.0000 3      Trn2_T3_        16        2Trn14_              1         41044     1.00     20341         91957       0.0000 Total     0.0171 Usage =
Salt
Note:   All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
#1 L
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Desc. #1  
#2 Desc. #2 (cycles)
Sn (psi)
Ke (psi)
Nallow U
25 2Trn3O0 26 3Trn3O0 8
3Trnl 1_
13 8Trnl 1_
19 2Trn21 22 Tn24_T2_
7 2Trnl 1 27 4Trn3O0 4
1Trn3_
7 2Trnl 1_
10 5Trn11 _
19 2Trn21l 1
Trn2 TI 6
1Trn 11 2
Trn2_T2_
19
: 2Trn21, 12 7Trnl 1 19 2Trn21 1
Trn2_Ti1 9
4Trnl 1 4
1Trn3_
11 6Trn 11_
1 Trn2 T1 5
2Trn3 4
1Trn3_
5 2Trn3_
4 1Trn3_
24 lTrn30-4 1Trn3_
18 1Trn21_
17 3Trn14_
18 1Trn21_
18 1Trn21_
20 3Trn21_
19 2Trn21_
20 3Trn21_
3 Trn2_T3_
19 2Trn21l 3
Trn2 T3 14 9Trn 11_
3 Trn2_T3_
15 1Trn14_
3 Trn2_T3_
16 2Trn14_
1 51402 1.00 44455 6278 0.0002 10 15961 1.00 39383 8994 0.0011 1
39644 1.00 34138 14404 0.0001 1
38618 1.00 27466 28999 0.0000 9
36665 1.00 27150 30048 0.0003 10 15935 1.00 26332 33005 0.0003 10 49693 1.00 25486 36486 0.0003 120 25423 1.00 24010 43822 0.0027 10 13983 1.00 23200 48691 0.0002 10 47005 1.00 22776 52484 0.0002 10 35885 1.00 22731 53008 0.0002 100 44974 1.00 22190 59737 0.0017 200 44974 1.00 22190 59737 0.0033 1
44912 1.00 22187 59767 0.0000 80 44912 1.00 22187 59767 0.0013 1
44598 1.00 21478 70216 0.0000 219 43608 1.00 21218 74590 0.0029 81 43426 1.00 21130 76147 0.0011 78 43219 1.00 21117 76367 0.0010 10 43408 1.00 21016 78221 0.0001 1
42722 1.00 20993 78639 0.0000 1
41044 1.00 20341 91957 0.0000 Total 0.0171 Usage =
Note:
All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
File No.: 0801038.303 Revision: 1 Page 15 of 18 F0306-OIRO


C     StructuralIntegrity Associates, Inc.
C Structural Integrity Associates, Inc.
Table 9: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location VY CS Nozzle Corner Environmental Fatigue Calculation CUF Calculation from file VY-VFAT-2i.fat:
Table 9: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location VY CS Nozzle Corner Environmental Fatigue Calculation CUF Calculation from file VY-VFAT-2i.fat:
Index   Load #1: Description #1: n1 (cycles) t5) Load #2&Description #2i n 2 (cycles) t5 ycles} 's SK psi t   lt (psi} Nallmy         U 1       25         2Trn30_           1       26   i   3Trn3O_             1         1       51402 1.00 44455       6278       0.0002 2         8   i     3Trnl_           10       13   i   8Trn11_     i       10         10       15961 1-00 39383       8994       0.0011 3       19   i   2Trn21           300       22     Tn24 T2     '        1         1     39644 1.00 34138     14404       0-0001 4         7         2Trnl1           10       27       4Trn30               1         1       38618 1-00 27466     28999       0.0000 5         4           1Trn3         300         7       2Trn11-             9         9       36665 1.00 27150     30048       0.0003 6       10         5Trn11           10       19       2Trn21             299         10       15935 1.00 26332     33005       0.0003 7         1   1 Trn2 TI             120         6     iTrnl 1               10         10     49693 1.00 25486. 36486       0.0003 8         2         Trn2 T2         120       19       2Trn2l             289       120     25423 1.00 24010     43822       0.0027 9       12         7Tlr 11   i     10       19 i     2Trn21-           169         10       13983 1.00 23200     48691       0.0002 10         1     ITrn2 Ti           110         9       4Trn11             10         10     47005 1.00 22776     52484       0.0002 11         4           1Trn3         291       11       6Trn11-             10         10       35885 1.00 22731     53008       0.0002 12         1         Trn2 T1         100         5       2Trn3             300       100     44974 1.00 22190     59737       0.0017 13         4           1Tr,3         281                 2Trn3             200       200       44974 1.00 22190     59737       0.0033 14         4           1Trn3           81       24             OTrn3_         1         1     44912 1.00 22187     59767       0.0000 15         4           lTrn3           80       18     1 Trn21             300         80       44912 1.00 22187     59767       0.0013 16       17         3Trn14           1       18       1Trn21_           220         1     44598 1.00 21478     70216       0.0000 17       18         1Trn21     i   219       20 i     3Trn21     i     300       219       43608 1.00 21218     74590       0.0029 18       19         2Trn21           159       20   i   3Trn21             81         81     43426 1.00 21130     76147       0.0011 19         3         Trn2 T3         120       19       2Trn21             78         78       43219 1.00 21117     76367       0.0010 20         3         Trn2 T3           42       14       9Trn11-             10         10     43408 1.00 21016     78221       0.0001 21         3         Trn2 T3           32       15       1Tm14-               1         1     42722 1.00 20993     78639       0.0000 22         3         Trn2 T3-         31       16   1 2Trn14                 1         1     41044 1.00 20341     91957       0.1000 Total, U =   0.0171 File No.: 0801038.303                                                                                                               Page 16 of 18 Revision: I F0306-0IRO
Index Load #1: Description #1: n1 (cycles) t5) Load #2& Description #2i n2 (cycles) t5 ycles} 's SK psi t
lt (psi}
Nallmy U
1 25 2Trn30_
1 26 i
3Trn3O_
1 1
51402 1.00 44455 6278 0.0002 2
8 i
3Trnl_
10 13 i
8Trn11_
i 10 10 15961 1-00 39383 8994 0.0011 3
19 i
2Trn21 300 22 Tn24 T2 1
1 39644 1.00 34138 14404 0-0001 4
7 2Trnl1 10 27 4Trn30 1
1 38618 1-00 27466 28999 0.0000 5
4 1Trn3 300 7
2Trn11-9 9
36665 1.00 27150 30048 0.0003 6
10 5Trn11 10 19 2Trn21 299 10 15935 1.00 26332 33005 0.0003 7
1 1
Trn2 TI 120 6
iTrnl 1 10 10 49693 1.00 25486.
36486 0.0003 8
2 Trn2 T2 120 19 2Trn2l 289 120 25423 1.00 24010 43822 0.0027 9
12 7Tlr 11 i
10 19 i
2Trn21-169 10 13983 1.00 23200 48691 0.0002 10 1
ITrn2 Ti 110 9
4Trn11 10 10 47005 1.00 22776 52484 0.0002 11 4
1Trn3 291 11 6Trn11-10 10 35885 1.00 22731 53008 0.0002 12 1
Trn2 T1 100 5
2Trn3 300 100 44974 1.00 22190 59737 0.0017 13 4
1Tr,3 281 2Trn3 200 200 44974 1.00 22190 59737 0.0033 14 4
1Trn3 81 24 OTrn3_
1 1
44912 1.00 22187 59767 0.0000 15 4
lTrn3 80 18 1 Trn21 300 80 44912 1.00 22187 59767 0.0013 16 17 3Trn14 1
18 1Trn21_
220 1
44598 1.00 21478 70216 0.0000 17 18 1Trn21 i
219 20 i
3Trn21 i
300 219 43608 1.00 21218 74590 0.0029 18 19 2Trn21 159 20 i
3Trn21 81 81 43426 1.00 21130 76147 0.0011 19 3
Trn2 T3 120 19 2Trn21 78 78 43219 1.00 21117 76367 0.0010 20 3
Trn2 T3 42 14 9Trn11-10 10 43408 1.00 21016 78221 0.0001 21 3
Trn2 T3 32 15 1 Tm14-1 1
42722 1.00 20993 78639 0.0000 22 3
Trn2 T3-31 16 1
2Trn14 1
1 41044 1.00 20341 91957 0.1000 Total, U =
0.0171 File No.: 0801038.303 Revision: I Page 16 of 18 F0306-0IRO


Structural Integrity Associates, -Inc.
Structural Integrity Associates, -Inc.
Table 9 (Continued): EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location EAF Calculations:               HWC DO      HWC D0O (00 and HWCINWC inputs fromTable 1 of Reference [6})         97          114          ppb Transient Maximum Temperatures:                                                                                                                    %, HWC =       0.47         0.53         =%NWC Frnm "V'Y-VtFAT-2i AlII '
Table 9 (Continued): EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location EAF Calculations:
Index   Load #1     Desc. #1 Load #21 Desc.#2         Line #     Ti (4) si(4) T2(4) s2(4] Sn (psi) T (IF) (1)                  TMAX -F) (1)    TMAX ('C)    HWC Fen (2)NWC Fen (2)  Uenv (3) 1         25       2Trn30-     26       3Trn3O   591851       25     15     26     30   51402       543                     543          2.54        6.49        10.65        0.002 2          B       3Trnhl _     13       UTrnh1 - 127122       8     30     13     14   15961       3D1                     391          199        3.68        4.22        0.005 3        19       2Trn21       22     Tn24 T.2   574137       19   20       22           39644       359                     389            1 5'8      3.54        4.17        01.000 4          7       2Trnl 1     27       4Trn30   107543       7     32     27     17   3561t       465                         145      241    I    5.65        6.62        0.000 5          4       lTrn3_       7       2Trnill     3921         4     1       7     32   36f665       465                     465          241        5.63        6.62        0.002 6        10       5Trn 1-     19       2Trn2l     24a,706     10     67     19     20   15935       389                     359          198        3.84        4.17        0.001 7         1     Trn2 Tl       6       lTrn 1.     70         1     1       6       4   49693       526                     526          274        7.78        9.60        D.002 5         2     Trn2 T2_     19       2Trn21_     2028         2     1     19     20   25423       389                     389          198        3.64        4.17        0.011 9         12       Tfrn 1I-     19       2Trn2i_   391806       12     30     .19     20   13983       3&9                     359          198        3.84        4.17        0.001 10         .1     Trn2_Ti1       9       4Trnll     161         1     1       9       1   47005       434                      434           223        4.34        5.48        01.001 11         4       1Trn3_     11       6Trnl 11   5546         4     1     11       1   35655       348                     345          176        3.11        3.25        01.001 12         1     Trn2_TI_       5       2Trn3_       56         1     1       5     42   44974       549                      549           267        8.76        11.05        0.017 13         4       lTrn3       5         2Trn3_   3475         4     t1     5     42   44974       549                     549          287        6.76        11.05        0.033 14         4       iTrn3_     24       1Trn30_   10815       4     1     24       1   44912       549                     549          287        8.76        11.05        01.000 15         4       ITrn3_     i 15        Trn21_   1016         4     1     18       1   44912       549                     549          257        6.76        11.05        U..013 16r        17       3Trn14_     18       1Trn21_   53601 3     17   111     16       1   44596       549                     549          287        8.76        11.05        .0.000 17         15     lTrn2i_     20       3Trn21   571713       18     1     20     39   43605       549                      549           287        8.76        11.05        0.029 15         19       2Trn21       20       3Trn21   573512       19     1     20     39   43426       549                     549          297        6.76        11.05        0c.011 19         3     Trn2 T3       19       2Trn21_     3151         3     1     1,9     1   43219       549                      549           287        8.76a      11.05        01.010 524          273        7.70          49        0.001 20         3     Trn2 T3       14       9Trnll_     296-5       3     1     14     155   43405       524 21         3     Trn2 T3       15     lTrn14     2979         3     1     15       1   42722       526                     526          274        7.75        9.60        0.000 22         3     Trnm2T3       16     , 2Trn 14_   2953         3     1     16       1   41044       524,                     524           273         7.70         9.89         01.000 Total. U =     0.140 Notes:   1.Tv,,., is the maximum temperature of the two paired load states, and represents the metal (nodal) temperature at the location                                 Overall Fen      8.20 being analzed. This, which is include-d as 'T in the'Transient Maximum Temperatures7' table above. determined from the VESLFAT
(00 and HWCINWC inputs fromTable 1 of Reference [6})
%, HWC =
HWC DO 97 0.47 HWC D0O 114 0.53 ppb
=% NWC Transient Maximum Temperatures:
Frnm "V'Y-VtFAT-2i AlII '
Index Load #1 Desc. #1 Load #21 Desc.#2 Line #
Ti (4) si(4) T2(4) s2(4] Sn (psi) T (IF) (1) 1 25 2Trn30-26 3Trn3O 591851 25 15 26 30 51402 543 2
B 3Trnhl _
13 UTrnh 1 -
127122 8
30 13 14 15961 3D1 3
19 2Trn21 22 Tn24 T.2 574137 19 20 22 39644 359 4
7 2Trnl 1 27 4Trn30 107543 7
32 27 17 3561t 465 5
4 lTrn3_
7 2Trnill 3921 4
1 7
32 36f665 465 6
10 5Trn 1-19 2Trn2l 24a,706 10 67 19 20 15935 389 7
1 Trn2 Tl 6
lTrn 1.
70 1
1 6
4 49693 526 5
2 Trn2 T2_
19 2Trn21_
2028 2
1 19 20 25423 389 9
12 Tfrn 1I-19 2Trn2i_
391806 12 30  
.19 20 13983 3&9 10  
.1 Trn2_Ti1 9
4Trnll 161 1
1 9
1 47005 434 11 4
1Trn3_
11 6Trnl 11 5546 4
1 11 1
35655 348 12 1
Trn2_TI_
5 2Trn3_
56 1
1 5
42 44974 549 13 4
lTrn3 5
2Trn3_
3475 4
t1 5
42 44974 549 14 4
iTrn3_
24 1Trn30_
10815 4
1 24 1
44912 549 15 4
ITrn3_
15 i
Trn21_
1016 4
1 18 1
44912 549 16 r 17 3Trn14_
18 1Trn21_
53601 3 17 111 16 1
44596 549 17 15 lTrn2i_
20 3Trn21 571713 18 1
20 39 43605 549 15 19 2Trn21 20 3Trn21 573512 19 1
20 39 43426 549 19 3
Trn2 T3 19 2Trn21_
3151 3
1 1,9 1
43219 549 20 3
Trn2 T3 14 9Trnll_
296-5 3
1 14 155 43405 524 21 3
Trn2 T3 15 lTrn14 2979 3
1 15 1
42722 526 22 3
Trnm2T3 16  
, 2Trn 14_
2953 3
1 16 1
41044
: 524, TMAX -F) (1)
TMAX ('C)
HWC Fen (2) NWC Fen (2) Uenv (3) 543 2.54 6.49 10.65 0.002 391 199 3.68 4.22 0.005 389 1 5'8 3.54 4.17 01.000 145 241 I
5.65 6.62 0.000 465 241 5.63 6.62 0.002 359 198 3.84 4.17 0.001 526 274 7.78 9.60 D.002 389 198 3.64 4.17 0.011 359 198 3.84 4.17 0.001 434 223 4.34 5.48 01.001 345 176 3.11 3.25 01.001 549 267 8.76 11.05 0.017 549 287 6.76 11.05 0.033 549 287 8.76 11.05 01.000 549 257 6.76 11.05 U..013 549 287 8.76 11.05
.0.000 549 287 8.76 11.05 0.029 549 297 6.76 11.05 0c.011 549 287 8.76a 11.05 01.010 524 273 7.70 49 0.001 526 274 7.75 9.60 0.000 524 273 7.70 9.89 01.000 Total. U =
Overall Fen Notes:
: 1. Tv,,., is the maximum temperature of the two paired load states, and represents the metal (nodal) temperature at the location being analzed. This, which is include-d as 'T in the'Transient Maximum Temperatures7' table above. determined from the VESLFAT
: 2. F, values computed using the low alloy steel equation from Section 3.0 of Reference [61 with S' conservatively set to a maximum value of 0.0 15. and the transtformed strain rate conservat~rely set to a minimum value of In (0.00t1) = 508 for all load
: 2. F, values computed using the low alloy steel equation from Section 3.0 of Reference [61 with S' conservatively set to a maximum value of 0.0 15. and the transtformed strain rate conservat~rely set to a minimum value of In (0.00t1) = 508 for all load
: 3. U*, = [U x HWC F, x % HWCI [U x NWC F_. x % NWC1.
: 3. U*, = [U x HWC F, x % HWCI
[U x NWC F_. x % NWC1.
: 4. T1 and 72 represent the load number for Load #1 and Load #2, respectively, and sl and s2 represent the state number for each
: 4. T1 and 72 represent the load number for Load #1 and Load #2, respectively, and sl and s2 represent the state number for each
: 5. For each load pair, nj is the number of available cycles for Load #1, n- is the number of available cycles for Load #2, and n is the available number of cycles for the load pair (i.e., the minimum of nj and n.).
: 5. For each load pair, nj is the number of available cycles for Load #1, n-is the number of available cycles for Load #2, and n is the available number of cycles for the load pair (i.e., the minimum of nj and n.).
File No.: 0801038.303                                                                                                                                                                 Page 17 of 18 Revision: 1 F0306-OI RO
0.140 8.20 File No.: 0801038.303 Revision: 1 Page 17 of 18 F0306-OI RO


SStructuralIntegrity Associates, Inc.
SStructural Integrity Associates, Inc.
Table 10: Linearized Stress Files Compiled for VY-StressResults.xls Filename                       Description vyl 6qtran2-s.csv           Transient 2 linearized stress vyl 6q_tran3-s.csv           Transient 3 linearized stress vy_l 6q_tranl 1-s.csv       Transient 11 linearized stress vyl 6q_tran 14-s.csv         Transient 14 linearized stress vyl 6q_tran21-23-s.csv       Transients 21-23 linearized stress vyl 6q_tran24-s.csv         Transient 24 linearized stress vyl 6q_tran30-s.csv         Transient 30 linearized stress Note: All files are from the supporting computer files associated with Reference [1].
Table 10: Linearized Stress Files Compiled for VY-StressResults.xls Filename Description vyl 6qtran2-s.csv vyl 6q_tran3-s.csv vy_l 6q_tranl 1-s.csv vyl 6q_tran 1 4-s.csv vyl 6q_tran21-23-s.csv vyl 6q_tran24-s.csv vyl 6q_tran30-s.csv Transient 2 linearized stress Transient 3 linearized stress Transient 11 linearized stress Transient 14 linearized stress Transients 21-23 linearized stress Transient 24 linearized stress Transient 30 linearized stress Note: All files are from the supporting computer files associated with Reference [1].
File No.: 0801038.303                                                                           Page 18 of 18 Revision: I F0306-OIRO
File No.: 0801038.303 Revision: I Page 18 of 18 F0306-OIRO


StructuralIntegrity Associates, Inc.                 File No.: 0801038.304 CALCULATION PACKAGE                               Project No.: 0801038 Quality Program: Z Nuclear [ Commercial PROJECT NAME:
Structural Integrity Associates, Inc.
File No.: 0801038.304 CALCULATION PACKAGE Project No.: 0801038 Quality Program: Z Nuclear
[ Commercial PROJECT NAME:
VY Confirmatory Analysis for CS and RO Nozzles CONTRACT NO.:
VY Confirmatory Analysis for CS and RO Nozzles CONTRACT NO.:
10163217 Amendment 5 CLIENT:                                             PLANT:
10163217 Amendment 5 CLIENT:
Entergy Nuclear Operations, Inc                 Vermont Yankee Nuclear Power Station CALCULATION TITLE:
PLANT:
Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle Document         Affected                                   Project Manager           Preparer(s) &
Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:
Documen           afe           Revision Description           Approval                 Checker(s)
Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle Document Affected Project Manager Preparer(s) &
Revision         Pages                                     Signature & Date       Signatures & Date 01             - 20,           Initial issue.                               Preparers:
Documen afe Revision Description Approval Checker(s)
Appendix:                                   Gary L. Stevens         Michael J. Minard A- I - A-23                                       01/07/09                 01/07/09 Computer files.                                                         Tyler D. Novotny 01/07/09 Checker:
Revision Pages Signature & Date Signatures & Date 01  
Terry J. Herrmann 01/07/09 1         1-8,10,11,       Revised per summary.     /                     Preparer:
- 20, Initial issue.
13-20,       contained in Section 1.1.           0(,. 11Z64-A-2         Changes are marked with "revision bars" in     Gary L. Stevens right-hand margin.             03/09/09             Tyler D. Novotny 03/09/09 Checker:
Preparers:
Appendix:
Gary L. Stevens Michael J. Minard A-I - A-23 01/07/09 01/07/09 Computer files.
Tyler D. Novotny 01/07/09 Checker:
Terry J. Herrmann 01/07/09 1
1-8,10,11, Revised per summary.  
/
Preparer:
13-20, contained in Section 1.1.
0( 11Z64-A-2 Changes are marked with "revision bars" in Gary L. Stevens right-hand margin.
03/09/09 Tyler D. Novotny 03/09/09 Checker:
William Weitze 03/09/09 Page 1 of 20 F0306-01 RO
William Weitze 03/09/09 Page 1 of 20 F0306-01 RO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
Table of Contents 1.0     OBJECTIVE ............................................................................................................             4 1.1     Changes M ade in Revision 1 of this Calculation ..........................................                                   4 2.0     M ETHODOLOGY ...................................................................................................                   4 3.0     ASSUM PTIONS / DESIGN INPUTS .......................................................................                               5 3.1     Assumptions ...............................................................................................               .. 5 3.2     ASM E Code Edition .....................................................................................                     5 3.3     Transients ......................................................................................................             6 3.4     Heat Transfer Coefficients .............................................................                         ...... 6 3.5     Finite Element M odel ..................................................................................                     8 3.6     Nozzle Blend Radius Pressure Stress ..........................................................                               8 3.7     Piping Interface Loads...............................................................................             ......... 8 3.8     SCFs, Safe End ............................................................................................                   9 3.9     Environmental Fatigue M ultipliers ................................................................                           9 4.0     CALCULATIONS ............... ..................................................................................                 13 4.1     Piping Interface Loads ....................................                                                               13 5.0     RESULTS OF ANALYSIS .....................................................................................                       18
Table of Contents 1.0 OBJECTIVE............................................................................................................
4 1.1 Changes M ade in Revision 1 of this Calculation..........................................
4 2.0 M ETHODOLOGY...................................................................................................
4 3.0 ASSUM PTIONS / DESIGN INPUTS.......................................................................
5 3.1 Assumptions...............................................................................................  
.. 5 3.2 ASM E Code Edition.....................................................................................
5 3.3 Transients......................................................................................................
6 3.4 Heat Transfer Coefficients.............................................................  
...... 6 3.5 Finite Element M odel..................................................................................
8 3.6 Nozzle Blend Radius Pressure Stress..........................................................
8 3.7 Piping Interface Loads...............................................................................  
......... 8 3.8 SCFs, Safe End............................................................................................
9 3.9 Environmental Fatigue M ultipliers................................................................
9 4.0 CALCULATIONS.................................................................................................
13 4.1 Piping Interface Loads....................................
13 5.0 RESULTS OF ANALYSIS.....................................................................................
18


==6.0     REFERENCES==
==6.0 REFERENCES==
........................................................................................................            19 APPENDIX A: ANSYS INPUT FILE: RON VY.INP .................................................                                           A-1 FileNo.: 0801038.304                                                                                                                       Page 2 of 20 Revision: 1 F0306-01!
19 APPENDIX A: ANSYS INPUT FILE: RON VY.INP.................................................
A-1 FileNo.: 0801038.304 Page 2 of 20 Revision: 1 F0306-01!


VStructural integrity Associates, Inc.
VStructural integrity Associates, Inc.
List of Tables Table 1: Vessel and Nozzle/Safe End Transients .............................................................                   10 Table 2: H eat Transfer Coefficients ....................................................................................... 11 Table 3: Temperature-Dependent Material Properties ...........................................................                 11 Table 4: Recirculation Outlet Nozzle Attached Piping Loads and Dimensions [9, 11] ......... 14 Table 5: Membrane Plus Bending Stresses Due to Piping Loads ....................................                               14 Table 6: 0% Flow Regions I and 3 Heat Transfer Coefficients .......................................                             15 Table 7: 0% Flow Region 5 Heat Transfer Coefficient ...................................................                         16 List of Figures Figure 1: Nozzle and Vessel Wall Thermal Boundaries ...................................................                         12 Figure 2: Coordinate System for Forces and Moments .....................................................                       17 Figure 3: RO Nozzle and Safe End Geometry [20] ..........................................................                       17 File No.: 0801038.304                                                                                                                 Page 3 of 20 Revision: 1 F0306-01I
List of Tables Table 1: Vessel and Nozzle/Safe End Transients.............................................................
10 Table 2: H eat Transfer Coefficients.......................................................................................
11 Table 3: Temperature-Dependent Material Properties...........................................................
11 Table 4: Recirculation Outlet Nozzle Attached Piping Loads and Dimensions [9, 11]......... 14 Table 5: Membrane Plus Bending Stresses Due to Piping Loads....................................
14 Table 6: 0% Flow Regions I and 3 Heat Transfer Coefficients.......................................
15 Table 7: 0% Flow Region 5 Heat Transfer Coefficient...................................................
16 List of Figures Figure 1: Nozzle and Vessel Wall Thermal Boundaries...................................................
12 Figure 2: Coordinate System for Forces and Moments.....................................................
17 Figure 3: RO Nozzle and Safe End Geometry [20]..........................................................
17 File No.: 0801038.304 Revision: 1 Page 3 of 20 F0306-01I


VStructural Integrity Associates, Inc.
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1.0 OBJECTIVE The objective of this calculation package is to establish the design inputs and methodology to be used for an ASME Code, Section III fatigue usage calculation of the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at Vermont Yankee Nuclear Power Station (VYNPS) 1 .
1.0 OBJECTIVE The objective of this calculation package is to establish the design inputs and methodology to be used for an ASME Code, Section III fatigue usage calculation of the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at Vermont Yankee Nuclear Power Station (VYNPS)1.
This calculation, along with subsequent calculations for stress and fatigue, are being performed to assess the impact of using finite element analysis using all six components of stress in lieu of the Green's Function approach used in SI project VY-16Q [4, 7, and 11]. Therefore, to the extent possible, inputs from that project will be maintained and used.
This calculation, along with subsequent calculations for stress and fatigue, are being performed to assess the impact of using finite element analysis using all six components of stress in lieu of the Green's Function approach used in SI project VY-16Q [4, 7, and 11]. Therefore, to the extent possible, inputs from that project will be maintained and used.
1.1     Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:
1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:
: a. Transient 9 described in Table 1 was changed to more precisely match the Green's Function analysis.
: a. Transient 9 described in Table 1 was changed to more precisely match the Green's Function analysis.
: b. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.
: b. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.
Line 371: Line 1,026:
All six components of the stress tensor will be used for stress calculations. The stress components for the non-axisymmetric loads (shear and moment piping loads) can have opposite signs depending upon which side of the nozzle is being. examined. Therefore, when combining stress components from these loads with stress components from thermal transients and other loads, the signs of the stress components will be adjusted to maximize the magnitude of the stress component ranges. The fatigue analysis will be performed at locations that were determined in a previous calculation [4]. Stresses will be linearized at these locations.
All six components of the stress tensor will be used for stress calculations. The stress components for the non-axisymmetric loads (shear and moment piping loads) can have opposite signs depending upon which side of the nozzle is being. examined. Therefore, when combining stress components from these loads with stress components from thermal transients and other loads, the signs of the stress components will be adjusted to maximize the magnitude of the stress component ranges. The fatigue analysis will be performed at locations that were determined in a previous calculation [4]. Stresses will be linearized at these locations.
The methodology described and applied herein and in the two additional recirculation outlet nozzle fatigue calculations is in accordance with the approach used in the SIA calculations for the feedwater nozzle [16, 17, 18] and contains no significantly different scientific or technical judgments used in those calculations.
The methodology described and applied herein and in the two additional recirculation outlet nozzle fatigue calculations is in accordance with the approach used in the SIA calculations for the feedwater nozzle [16, 17, 18] and contains no significantly different scientific or technical judgments used in those calculations.
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StructuralIntegrityAssociates, Inc.
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The linearized primary plus secondary membrane plus bending stress will be used to determine the value of Ke to be used in the simplified elastic-plastic analysis in accordance with ASME Code NB-3200 methodology. Environmental fatigue multipliers will be applied in accordance with NUREG/CR-6583 [2]
The linearized primary plus secondary membrane plus bending stress will be used to determine the value of Ke to be used in the simplified elastic-plastic analysis in accordance with ASME Code NB-3200 methodology. Environmental fatigue multipliers will be applied in accordance with NUREG/CR-6583 [2]
for the low alloy steel forging and NUREG/CR-5704 [15.] for the stainless steel safe end.
for the low alloy steel forging and NUREG/CR-5704 [15.] for the stainless steel safe end.
3.0 ASSUMPTIONS / DESIGN INPUTS 3.1     Assumptions
3.0 ASSUMPTIONS / DESIGN INPUTS 3.1 Assumptions
: 1. Extended power uprate (EPU) effects are considered as being applied to the entire 60-year period of operation. The higher pressures, flows, and temperatures at uprate conditions are used in determining and applying heat transfer coefficients [4, Section 3.2] [11, Section 4.1].
: 1. Extended power uprate (EPU) effects are considered as being applied to the entire 60-year period of operation. The higher pressures, flows, and temperatures at uprate conditions are used in determining and applying heat transfer coefficients [4, Section 3.2] [11, Section 4.1].
: 2. The Boltup transientdoes not affect the RO nozzle because there is no pressure or temperature change, and the nozzle is sufficiently removed from the vicinity of the flange such that stresses due to head stud tensioning are insignificant at the nozzle location [8]. The Boltup transient is therefore excluded from the transients analyzed.
: 2. The Boltup transientdoes not affect the RO nozzle because there is no pressure or temperature change, and the nozzle is sufficiently removed from the vicinity of the flange such that stresses due to head stud tensioning are insignificant at the nozzle location [8]. The Boltup transient is therefore excluded from the transients analyzed.
Line 386: Line 1,041:
: 8. Consistent with Reference [4], 12% of the available temperature difference (AT) between the fluid and surface was assumed for all natural convection thermal heat transfer coefficients.
: 8. Consistent with Reference [4], 12% of the available temperature difference (AT) between the fluid and surface was assumed for all natural convection thermal heat transfer coefficients.
: 9. The instant temperature change for transients is assumed as a 1-second time step.
: 9. The instant temperature change for transients is assumed as a 1-second time step.
3.2     ASME Code Edition The analysis will be performed in a manner consistent with the fatigue usage rules in NB-3200 of Section III of the ASME Code; the 1998 Edition with Addenda through 2000 [1] will be used, for consistency with the previous analysis [11].
3.2 ASME Code Edition The analysis will be performed in a manner consistent with the fatigue usage rules in NB-3200 of Section III of the ASME Code; the 1998 Edition with Addenda through 2000 [1] will be used, for consistency with the previous analysis [11].
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VStructural integrity Associates, Inc.
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3.3     Transients Previously developed thermal and pressure transients [11 Tables 2 and 3] are used for this analysis. The transients to be evaluated are shown in Table 1. For each transient, the time, nozzle fluid temperature, RPV pressure, percent reactor recirculation flow rate, and number of cycles are included. In some cases, flow rates and nozzle temperature values from the nozzle thermal cycle diagram [8, Attachment 1, p. 4] are used' to reduce excess conservatism. Note that the only difference between the vessel and the safe end/nozzle transients is the temperature difference between the two regions for Transient 9.
3.3 Transients Previously developed thermal and pressure transients [11 Tables 2 and 3] are used for this analysis. The transients to be evaluated are shown in Table 1. For each transient, the time, nozzle fluid temperature, RPV pressure, percent reactor recirculation flow rate, and number of cycles are included. In some cases, flow rates and nozzle temperature values from the nozzle thermal cycle diagram [8, Attachment 1, p. 4] are used' to reduce excess conservatism. Note that the only difference between the vessel and the safe end/nozzle transients is the temperature difference between the two regions for Transient 9.
At the inside surface of the RPV, the Region B or BI bulk fluid temperature from the reactor thermal cycle diagram [8, Attachment 1, p. 2] shall be applied.
At the inside surface of the RPV, the Region B or BI bulk fluid temperature from the reactor thermal cycle diagram [8, Attachment 1, p. 2] shall be applied.
3.4     Heat Transfer Coefficients Heat transfer coefficients are calculated at 300' F, as in the previous analysis [4]. The heat transfer coefficients for the 100% flow and 50% flow cases were calculated from Reference [5] as follows:
3.4 Heat Transfer Coefficients Heat transfer coefficients are calculated at 300' F, as in the previous analysis [4]. The heat transfer coefficients for the 100% flow and 50% flow cases were calculated from Reference [5] as follows:
K =0.8   (     0.2 S3 h&deg;-25       DDf Where:
K =0.8
hDf= the heat transfer coefficient at a Diameter and flow rate h 300 = the heat transfer coefficient from Reference [5] at 300&deg;F,f= 25 ft/sec, and D= 26" =,4,789 BTU/hr-ft2_OF fif= the flow velocity corresponding to hDf (ft/sec)
(
0.2 S3 h&deg;-25 DDf Where:
hDf= the heat transfer coefficient at a Diameter and flow rate h300 = the heat transfer coefficient from Reference [5] at 300&deg;F,f= 25 ft/sec, and D= 26" =,4,789 BTU/hr-ft2_OF fif= the flow velocity corresponding to hDf (ft/sec)
DDf= the diameter corresponding to hDf(in)
DDf= the diameter corresponding to hDf(in)
The heat transfer coefficients for 0% flow were calculated in spreadsheet HTCOEF.xls for natural convection and are shown in Tables 6 and 7.
The heat transfer coefficients for 0% flow were calculated in spreadsheet HTCOEF.xls for natural convection and are shown in Tables 6 and 7.
As shown in Figure 1, the following heat transfer coefficients were applied:
As shown in Figure 1, the following heat transfer coefficients were applied:
Region 1 The heat transfer coefficient, h, for 100% flow is 4789     17-36)     "82-0.82   =3583 BTU/hr-ft2-&deg;F at 300TF, where 17.364 ft/sec is converted from 28,294 GPM and 25.8 in ID [20].
Region 1 The heat transfer coefficient, h, for 100% flow is 4789 17-36)  
The heat transfer coefficient, h, for 50% flow is 4789 -
"82-0.82  
(8.6821~0(
=3583 BTU/hr-ft2-&deg;F at 300TF, where 17.364 ft/sec is converted from 28,294 GPM and 25.8 in ID [20].
                                                                                      -
(8.6821~ 0(
26 J
26 >0.2 The heat transfer coefficient, h, for 50% flow is 4789 -
                                                                                            >0.2
J = 2058 BTU/hr-ft2 -
                                                                                                  = 2058 BTU/hr-ft2 -
'F at 300TF, where 8.682 ft/sec is converted from 14,147 GPM and 25.8 in ID [20].
                  'F at 300TF, where 8.682 ft/sec is converted from 14,147 GPM and 25.8 in ID [20].
The heat transfer coefficient, h, for 12% flow is 4789 (-2.084) 08 26 0.82 =657 BTU/hr-ft2-&deg;F at 300'F, where 2.084 ft/sec is converted from 3,395 GPM and 25.8 in ID [20].
The heat transfer coefficient, h, for 12% flow is 4789 (-2.084)   08   26   0.82 =657 BTU/hr-ft2-&deg;F at 300'F, where 2.084 ft/sec is converted from 3,395 GPM and 25.8 in ID [20].
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VStructural Integrity Associates, Inc.
VStructural Integrity Associates, Inc.
The heat transfer coefficient, h, for 0% flow is 112 BTU/hr-ft 2-&deg;F at 300'F. (Table 6, for natural convection)
The heat transfer coefficient, h, for 0% flow is 112 BTU/hr-ft2-&deg;F at 300'F. (Table 6, for natural convection)
Region 2 The heat transfer coefficient for Region 2 is linearly transitioned from the value of the heat transfer coefficient used in Region I to the value used for Region 3.
Region 2 The heat transfer coefficient for Region 2 is linearly transitioned from the value of the heat transfer coefficient used in Region I to the value used for Region 3.
Region 3 (the point between Region 2 and Region 4)
Region 3 (the point between Region 2 and Region 4)
The inside diameter of Region 3, as measured on the ANSYS model, is 35.49 inches.
The inside diameter of Region 3, as measured on the ANSYS model, is 35.49 inches.
The heat transfer coefficient, h, for 100% flow is 4789 (9.176_0.g     (26     )       2018 BTU/hr-ft2-25__       35.49 OF at 300'F, where 9.176 ft/sec is converted from 28,294 GPM and 35.49 in. ID.
The heat transfer coefficient, h, for 100% flow is 4789 (9.176_0.g (26  
The heat transfer coefficient, h, for 50% flow is 4789 4.5)       08     26     0.2 = 1159 BTU/hr-ft2-
)
___25        35.49)I OF at 300TF, where 4.588 ft/sec is converted from 14,147 GPM and 35.49. in. ID.
2018 BTU/hr-ft2-25__
                                            . for 12% flow is 4789 \ ~~~~25 The heat transfer coefficient, h,                                )     35-.49       =7BU/-f2&deg;
35.49 OF at 300'F, where 9.176 ft/sec is converted from 28,294 GPM and 35.49 in. ID.
                                                                                                  - 370 BTU/hr2ft -.F at 300&deg;F, where 1.101 ft/sec is converted from 3,395 GPM and 35.49 in. ID.
The heat transfer coefficient, h, for 50% flow is 4789 4.5) 08 26 0.2 = 1159 BTU/hr-ft2-
___ 25 35.49)I OF at 300TF, where 4.588 ft/sec is converted from 14,147 GPM and 35.49. in. ID.
The heat transfer coefficient, h, for 12% flow is 4789  
- 370 BTU/hr2ft -.F
\\ ~~~~25  
)
35-.49  
=7BU/-f2&deg; at 300&deg;F, where 1.101 ft/sec is converted from 3,395 GPM and 35.49 in. ID.
The heat transfer coefficient, h, for 0% flow is 112 BTU/hr-ft2-&deg;F at 300'F. using the same HTC as Region 1 (Table 6, for natural convection)
The heat transfer coefficient, h, for 0% flow is 112 BTU/hr-ft2-&deg;F at 300'F. using the same HTC as Region 1 (Table 6, for natural convection)
Region 4 The heat transfer coefficient for Region 4 (Nozzle Blend Radius).is linearly transitioned from the value of the heat transfer coefficient used in Region 3 to the value used in Region 5.
Region 4 The heat transfer coefficient for Region 4 (Nozzle Blend Radius).is linearly transitioned from the value of the heat transfer coefficient used in Region 3 to the value used in Region 5.
Region 5 A value of 0.5 x Region 1 HTC from Reference [5, page I-T9-4, 6] is used to simulate the interior of the RPV shell for all conditions.
Region 5 A value of 0.5 x Region 1 HTC from Reference [5, page I-T9-4, 6] is used to simulate the interior of the RPV shell for all conditions.
The heat transfer coefficient, h, for 100% flow is 0.5 x 3583.3 = 1,792 BTU/hr-ft 2-OF at 300 0 F.
The heat transfer coefficient, h, for 100% flow is 0.5 x 3583.3 = 1,792 BTU/hr-ft2-OF at 3000F.
The heat transfer coefficient, h, for 50%flow is 0.5 x 2058.1       1029 BTU/hr-ft2-OF at 300 0 F.
The heat transfer coefficient, h, for 50%flow is 0.5 x 2058.1 1029 BTU/hr-ft2-OF at 3000F.
The heat transfer coefficient, h, for 12% flow is 0.5 x 657.2= 329 BTU/hr-ft 2-OF at 300 0F.
The heat transfer coefficient, h, for 12% flow is 0.5 x 657.2= 329 BTU/hr-ft2-OF at 3000F.
The heat transfer coefficient, h, for 0% flow is 101 BTU/hr-ft 2 -OF at 300&deg;F. (Table 7, for natural convection) by using 40 in. hydraulic diameter [5].
The heat transfer coefficient, h, for 0% flow is 101 BTU/hr-ft2-OF at 300&deg;F. (Table 7, for natural convection) by using 40 in. hydraulic diameter [5].
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StructuralIntegrity Associates, Inc.
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Region 6 The heat transfer coefficient, h, is 0.4 BTU/hr-ft2 -OF [5].
Region 6 The heat transfer coefficient, h, is 0.4 BTU/hr-ft2-OF [5].
A summary of the heat transfer coefficients (HTC) to be used is shown in Table 2.
A summary of the heat transfer coefficients (HTC) to be used is shown in Table 2.
3.5   Finite Element Model The ANSYS program [6] will be used to perform the finite element analysis. A previously developed axisymmetric model will be used [7, file RONVYINP], except that temperature-dependent material properties will be used. Table 3 shows the applicable material properties [10].
3.5 Finite Element Model The ANSYS program [6] will be used to perform the finite element analysis. A previously developed axisymmetric model will be used [7, file RONVYINP], except that temperature-dependent material properties will be used. Table 3 shows the applicable material properties [10].
Stresses will be extracted and linearized at two locations, both on the inside surface of the model, one at the safe end, and one at the blend radius, as was done previously [4].
Stresses will be extracted and linearized at two locations, both on the inside surface of the model, one at the safe end, and one at the blend radius, as was done previously [4].
3.6   Nozzle Blend Radius Pressure Stress The axisymmetric model has the effect of modeling the cylindrical RPV as spherical. The following paragraphs describe the details of the modeling used to account for the differences in this approximation and the actual geometry of two intersecting cylinders.
3.6 Nozzle Blend Radius Pressure Stress The axisymmetric model has the effect of modeling the cylindrical RPV as spherical. The following paragraphs describe the details of the modeling used to account for the differences in this approximation and the actual geometry of two intersecting cylinders.
The radius of the vessel in the finite element model was multiplied by a factor of 2 to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is a cylinder. The equation for the membrane hoop stress for a sphere is:
The radius of the vessel in the finite element model was multiplied by a factor of 2 to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is a cylinder. The equation for the membrane hoop stress for a sphere is:
(pressure) x (radius) 2 x thickness The equation for the membrane hoop stress in a cylinder is:
(pressure) x (radius) 2 x thickness The equation for the membrane hoop stress in a cylinder is:
(pressure)x (radius) thickness The factor of two was verified in Reference [4], where actual stress results were compared to the results of this analytical form.
(pressure) x (radius) thickness The factor of two was verified in Reference [4], where actual stress results were compared to the results of this analytical form.
The pressure stress components for the safe end and blend radius paths will be extracted using ANSYS [6].
The pressure stress components for the safe end and blend radius paths will be extracted using ANSYS [6].
3.7   Piping Interface Loads Per Reference [9, 11], the RO nozzle piping loads, which conservatively use the design loads for the seismic, thermal and deadweight load combination, are stated in Table 4 along with relevant dimensions.
3.7 Piping Interface Loads Per Reference [9, 11], the RO nozzle piping loads, which conservatively use the design loads for the seismic, thermal and deadweight load combination, are stated in Table 4 along with relevant dimensions.
The coordinate system used for these are shown in Figure 2 and is consistent with Reference [9]. The finite element model coordinate system is shown in Figure 1.
The coordinate system used for these are shown in Figure 2 and is consistent with Reference [9]. The finite element model coordinate system is shown in Figure 1.
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3.8   SCFs, Safe End At the safe end inside surface, guidance is taken from the piping analysis rules in Subarticle NB-3600 of Section III of the ASME Code [1]. The stresses caused by the piping will be hand calculated and require a stress concentration factor, if appropriate. The stress concentration factor for the safe end location is 1.53 [5, page I-S9-4E, Table 5]. This value is conservatively used for both the C 2 and K2 values required by the ASME code [1, NB-3600]. The piping loads are relatively minor in comparison to the other loads this nozzle experiences so the conservative C2 and K 2 values will have a small impact on the analysis.
3.8 SCFs, Safe End At the safe end inside surface, guidance is taken from the piping analysis rules in Subarticle NB-3600 of Section III of the ASME Code [1]. The stresses caused by the piping will be hand calculated and require a stress concentration factor, if appropriate. The stress concentration factor for the safe end location is 1.53 [5, page I-S9-4E, Table 5]. This value is conservatively used for both the C2 and K2 values required by the ASME code [1, NB-3600]. The piping loads are relatively minor in comparison to the other loads this nozzle experiences so the conservative C2 and K2 values will have a small impact on the analysis.
These factors are conservatively applied to all six components of the stress tensor.
These factors are conservatively applied to all six components of the stress tensor.
3.9   Environmental Fatigue Multipliers The environmental fatigue multipliers for the safe end will be calculated in accordance with NUREG/CR-5704 methodology [15], and the environmental fatigue multipliers for the nozzle blend radius will be calculated in accordance with NUREG/CR-6583 methodology [2].
3.9 Environmental Fatigue Multipliers The environmental fatigue multipliers for the safe end will be calculated in accordance with NUREG/CR-5704 methodology [15], and the environmental fatigue multipliers for the nozzle blend radius will be calculated in accordance with NUREG/CR-6583 methodology [2].
File No.: 0801038.304                                                                                 Page 9 of 20 Revision: 1 F0306-01.
File No.: 0801038.304 Revision: 1 Page 9 of 20 F0306-01.


Structural IntegrityAssociates, Inc.
Structural Integrity Associates, Inc.
Table 1: Vessel and Nozzle/Safe End Transients Transient       Time Temp   Time Step Pressure   Flow Rate           Transient               Time     Temp   Time Step Pressure Flow Rate Number           LS     L       U     *psg)
Table 1: Vessel and Nozzle/Safe End Transients Transient Time Temp Time Step Pressure Flow Rate Transient Time Temp Time Step Pressure Flow Rate Number LS L
La}        (GPMI               Number                         JLM
U  
("F         L"s Lpsi       (GPM)
*psg)
: 1. Normal Startup with       0   100                 0       14147.0 6. Reactor Overpressure               0     526               1010       28294 0
(GPMI Number La}
Heatup at 10 *F/hr     16164 549     16164     1010         (50%)         1 Cycle (1,2)                 2     526         2     1375     (100%)
JLM
300 Cycles (2)   56164   549     40000     1010                                                   32       526       30       940
("F L"s Lpsi (GPM)
: 2. Turbine Roll and     0   549               1010       28294                                   1832       526     1800       940 Increase to Rated Power     1   542       1       1010       (100%)                                   2252       549       420     1010 300 Cycles (1, 2)     601   542     600       1010                                                 2312       549       60     1010 602   526       1       1010                                                 2313       542         1     1010 40602   526     40000     1010   1                                             2913       542       600     1010
: 1. Normal Startup with 0
: 3. Loss of Feedwater     0   526               1010       28294                                   2914       526         1     1010 Heaters         1800   542     1800     1010       (100%)                                   7914       526     5000     1010 Turbine Trip 25% Power     2100   542     300       1010                   7. SRV Blowdown                 0       526               1010       28294 10 Cycles (2)     2460   526     360       1010                         1 Cycle (2)             600       375       600       170     (100%)
100 0
3060   526     600       1010                                               11580       70     10980       50 3960   542     900       1010                                               51580       70     40000       50 4260   542     300       1010                   8. SCRAM Other                 0       526               1010     28294 6060   526     1800     1010                   228 Cycles (1, 2)             15       526       15       940     (100%)
14147.0
11060   526     5000     1010                                                 1815       526     1800       940
: 6. Reactor Overpressure 0
: 4. Loss of Feedwater     0   526               1010           0                                     2235       549       420     1010 Pumps             3   526       3       1190         (0%)                                   2295       549       60     1010 10 Cycles (1,2)       13   526       10       1135                                                 2296       542         1     1010 233   300     220       1135                                                 2356       542       60     1010 2213   500     1980     1135                                                 2357       526         1     1010 2393   300     180       885                                                 7357       526     5000     1010 6773   500     4380       1135                 9. Improper Startup               0       526               1010       3395 7193   300     420       675         14147         1 Cycle (1, 2)               1     130O         1     1010       (12%)
526 1010 28294 Heatup at 10 0*F/hr 16164 549 16164 1010 (50%)
7493   300     300       675         (50%)                                     27       130       26       1010 11093   400     3600       240                                                   28       526         1     1010 16457   549     5364     1010                                                 5028       526     5000     1010 16517   549       60       1010                     10. Shutdown                 0       549               1010       14147 16518   542       1       1010       28294         300 Cycles (2)             6264       375     6264       170       (50%)
1 Cycle (1,2) 2 526 2
17118   542     600       1010     (100%)                                     6864       330       600       88 17119   526       1       1010                                               16224       70     9360       50 57119   526     40000     1010                                               56224       70     40000       50
1375 (100%)
: 5. Turbine Generator Trip   0    526                1010      28294  11. Design Hydrostatic                  --  100                  0        1981 60 Cycles (1, 2)       10   526       10       1135     (100%)               Test                                               1100         (7%)
300 Cycles (2) 56164 549 40000 1010 32 526 30 940
15  526      5        1135                      120 Cvcles (2)                                            50 30    526      15      940                  12. Hydrostatic Test             -        100       -        50         1981 1830  526      1800      940                        1 Cycle (2)                             I ______ j    15633 50  ____
: 2. Turbine Roll and 0
(7%)
549 1010 28294 1832 526 1800 940 Increase to Rated Power 1
549      420      1010                                  _________________      _____
542 1
2250 2310  549      60      1010 2311  542        1      1010 2911  542      600      1010 2912  526        1      1010 7912  526    5000      1010
1010 (100%)
2252 549 420 1010 300 Cycles (1, 2) 601 542 600 1010 2312 549 60 1010 602 526 1
1010 2313 542 1
1010 40602 526 40000 1010 1
2913 542 600 1010
: 3. Loss of Feedwater 0
526 1010 28294 2914 526 1
1010 Heaters 1800 542 1800 1010 (100%)
7914 526 5000 1010 Turbine Trip 25% Power 2100 542 300 1010
: 7. SRV Blowdown 0
526 1010 28294 10 Cycles (2) 2460 526 360 1010 1 Cycle (2) 600 375 600 170 (100%)
3060 526 600 1010 11580 70 10980 50 3960 542 900 1010 51580 70 40000 50 4260 542 300 1010
: 8. SCRAM Other 0
526 1010 28294 6060 526 1800 1010 228 Cycles (1, 2) 15 526 15 940 (100%)
11060 526 5000 1010 1815 526 1800 940
: 4. Loss of Feedwater 0
526 1010 0
2235 549 420 1010 Pumps 3
526 3
1190 (0%)
2295 549 60 1010 10 Cycles (1,2) 13 526 10 1135 2296 542 1
1010 233 300 220 1135 2356 542 60 1010 2213 500 1980 1135 2357 526 1
1010 2393 300 180 885 7357 526 5000 1010 6773 500 4380 1135
: 9. Improper Startup 0
526 1010 3395 7193 300 420 675 14147 1 Cycle (1, 2) 1 130O 1
1010 (12%)
7493 300 300 675 (50%)
27 130 26 1010 11093 400 3600 240 28 526 1
1010 16457 549 5364 1010 5028 526 5000 1010 16517 549 60 1010
: 10. Shutdown 0
549 1010 14147 16518 542 1
1010 28294 300 Cycles (2) 6264 375 6264 170 (50%)
17118 542 600 1010 (100%)
6864 330 600 88 17119 526 1
1010 16224 70 9360 50 57119 526 40000 1010 56224 70 40000 50
: 5. Turbine Generator Trip 60 Cycles (1, 2) 0 10 15 30 1830 2250 2310 2311 2911 2912 7912 526 526 526 526 526 549 549 542 542 526 526 10 5
15 1800 420 60 1
600 1
5000 1010 1135 1135 940 940 1010 1010 1010 1010 1010 1010 28294 (100%)
: 11. Design Hydrostatic Test 120 Cvcles (2) 100 0
1100 50 1981 (7%)
: 12. Hydrostatic Test 100 50 1981 1 Cycle (2)
I 1563 3 (7%)
_____ ______ j 50
: 1. The instant temperature change is assumed as 1-second time step.
: 1. The instant temperature change is assumed as 1-second time step.
: 2. The number of cycles is for 60 years [8].
: 2. The number of cycles is for 60 years [8].
: 3. 130'F is the Region I temperature for Transient 9, whereas the blend radius is at 268&deg;F and the vessel is at 2687F, as was modeled previously [ 11].
: 3. 130'F is the Region I temperature for Transient 9, whereas the blend radius is at 268&deg;F and the vessel is at 2687F, as was modeled previously [ 11].
File No.: 0801038.304                                                                                                                     Page 10 of 20 Revision: 1 F0306-01
File No.: 0801038.304 Revision: 1 Page 10 of 20 F0306-01


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Table 2: Heat Transfer Coefficients Flow Rate Thermal Region                           100%                       50%                   12%             0% (Natural 1 Convection)
Table 2: Heat Transfer Coefficients Flow Rate Thermal Region 100%
Region 1                         3583                       2058                   657                   112 Region 2                                               Linear transition from Region 1 and Region 3 values Region 3                         2018                       1159                   370                   112 Region 4                                               Linear transition from Region 3 and Region 5 values Region 5                           1792                       1029                   329                   101 Region 6                                                                 0.4 for all flow rates Note: All Heat transfer coefficients are in units of BTU/hr-ft2 -&deg;F and are evaluated at 300'F.
50%
Table 3: Temperature-Dependent Material Properties Mean Young's       Coefficient of  Conductivity,                  Specific Heat, Diffusivity, Material                        Tempera-       Modulus,         Thermal              k                              cp Description       ture, *F       E x 106                                               d No.                                                          Expansion,   (BTU/hr-ft-&deg;F)                   (BTU/ibm-*F)
12%
0% (Natural 1
Convection)
Region 1 3583 2058 657 112 Region 2 Linear transition from Region 1 and Region 3 values Region 3 2018 1159 370 112 Region 4 Linear transition from Region 3 and Region 5 values Region 5 1792 1029 329 101 Region 6 0.4 for all flow rates Note: All Heat transfer coefficients are in units of BTU/hr-ft2 -&deg;F and are evaluated at 300'F.
Table 3: Temperature-Dependent Material Properties Material No.
Young's Tempera-
: Modulus, Description ture, *F E x 106 (psi)
Mean Coefficient of Thermal Expansion, ax 10,6 (in/in- 0F)
Conductivity, k
(BTU/hr-ft-&deg;F)
(see Note 1)
Diffusivity, d
(ft2/hr)
(ft2/hr)
(psi)            ax 10,6      (see Note 1)                   (see Note 4)
Specific Heat, cp (BTU/ibm-*F)
(in/in- 0 F) 4     SA533 Grade B,           70         29.2               7.0           23.5           0.458           0.105
(see Note 4) 4 SA533 Grade B, 70 29.2 7.0 23.5 0.458 0.105
[Vessel Wall]         .200         28.5               7.3           23.6           0.425           0.114 (Mn-1/2AMo-1/2/2Ni)         300         28.0               7.4           23.4           0.401           0.119 400         27.4               7.6           23.1           0.378           0.125 500         27.0               7.7           22.7           0.356           0.130 600         26.4               7.8           22.2           0.336           0.135 2       SA-508 Class 2           70         27.8               6.4           23.5           0.458           0.105
[Vessel Wall]  
[Nozzle Forging]         200         27.1               6.7           23.6           0.425           0.114 300         26.7               6.9           23.4           0.401           0.119 400         26.1               7.1           23.1           0.378           0.125 500         25.7               7.3           22.7           0.356           0.130 (See Note 2)         600         25.2               7.4           22.2           0.336           0.135 1,3       SA 240 Type             70         28.3               8.5             8.6           0:151           0.116 304, SS Clad,           200         27.6               8.9             9.3           0.156           0.122 SA 182 Type           300         27.0               9.2             9.8           0.160           0.125 F316             400         26.5               9.5             10.4           0.165           0.129
.200 28.5 7.3 23.6 0.425 0.114 (Mn-1/2AMo-1/2/2Ni) 300 28.0 7.4 23.4 0.401 0.119 400 27.4 7.6 23.1 0.378 0.125 500 27.0 7.7 22.7 0.356 0.130 600 26.4 7.8 22.2 0.336 0.135 2
[Clad, Safe End]         500         25.8             9.7             10.9           0.170           0.131 (see Note 3)           600         25.3               9.8             11.3           0.174           0.133 Notes:     1. Convert to BTU/see-in-&deg;F for input to ANSYS.
SA-508 Class 2 70 27.8 6.4 23.5 0.458 0.105
: 2. Properties of A508 Class II are used (3/4Ni-I/2Mo-1/3Cr-V).
[Nozzle Forging]
: 3. Properties of 18Cr - 8Ni austenitic stainless steel are used.
200 27.1 6.7 23.6 0.425 0.114 300 26.7 6.9 23.4 0.401 0.119 400 26.1 7.1 23.1 0.378 0.125 500 25.7 7.3 22.7 0.356 0.130 (See Note 2) 600 25.2 7.4 22.2 0.336 0.135 1,3 SA 240 Type 70 28.3 8.5 8.6 0:151 0.116 304, SS Clad, 200 27.6 8.9 9.3 0.156 0.122 SA 182 Type 300 27.0 9.2 9.8 0.160 0.125 F316 400 26.5 9.5 10.4 0.165 0.129
: 4. Calculated as [k/(pd)]/122.
[Clad, Safe End]
FileNo.: 0801038.304                                                                                                   Page 11 of 20 Revision: I F0306-01I
500 25.8 9.7 10.9 0.170 0.131 (see Note 3) 600 25.3 9.8 11.3 0.174 0.133 Notes:
1.
2.
3.
4.
Convert to BTU/see-in-&deg;F for input to ANSYS.
Properties of A508 Class II are used (3/4Ni-I/2Mo-1/3Cr-V).
Properties of 18Cr - 8Ni austenitic stainless steel are used.
Calculated as [k/(pd)]/122.
FileNo.: 0801038.304 Revision: I Page 11 of 20 F0306-01I


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AFLEAS 10*.T NULN APP, 19 2007 13:35:14 Region 5 Region 6 Region 4 RegRion 2 Region 1 Region 3 x
AFLEAS 10*.T NULN Region 5 Region 6 Region 4 RegRion 2 Region 3 Recirc Outlet Nozzle Finite Element Model APP, 19 2007 13:35:14 Region 1 x
Recirc   Outlet Nozzle   Finite   Element Model Figure 1: Nozzle and'Vessel Wall Thermal Boundaries File No.: 0801038.304                                                             Page 12 of 20 Revision: 1 F0306-01
Figure 1: Nozzle and'Vessel Wall Thermal Boundaries File No.: 0801038.304 Revision: 1 Page 12 of 20 F0306-01


VStructural IntegrityAssociates, Inc.
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4.0 CALCULATIONS 4.1   Piping Interface Loads From general structural mechanics [14], the membrane plus bending stresses at the inside surface of a thick-walled cylinder are:
4.0 CALCULATIONS 4.1 Piping Interface Loads From general structural mechanics [14], the membrane plus bending stresses at the inside surface of a thick-walled cylinder are:
az, = axial stress due to axial force = Fz/A cz, = axial stress due to bending moment = Mxy(ID/2)/I cz = czI + cyz2 TrO =.shear stress due to torsion = Mz(ID/2)/J Trz = shear stress due to shear force = 2Fxy/A, where F,, Fy, Fz, Mx, My, and M, are forces and moments at the pipe-to-safe end weld MxL = moment about x axis translated by length z = -L = M, - Fy L MyL = moment about y axis translated by length2 z0 =5 -L = My + Fx L Mxy = resultant bending moment2 = (MxL2     + MyL )
az, = axial stress due to axial force = Fz/A cz, = axial stress due to bending moment = Mxy(ID/2)/I cz = czI + cyz2 TrO =.shear stress due to torsion = Mz(ID/2)/J Trz = shear stress due to shear force = 2Fxy/A, where F,, Fy, Fz, Mx, My, and M, are forces and moments at the pipe-to-safe end weld MxL = moment about x axis translated by length z = -L = M, - Fy L MyL = moment about y axis translated by length z = -L = My + Fx L Mxy = resultant bending moment = (MxL2 + MyL2 )0 5 Fxy = resultant shear force = (Fx2 F y2)0'5 ID, OD = inside and outside diameters A = area of cross section = (n/4)(OD 2 - ID 2)
Fxy = resultant shear force = (Fx F y2)0'5 ID, OD = inside and outside diameters A = area of cross section = (n/4)(OD 2 - ID 2)
I = moment of inertia = (ir/64)(OD4 - ID4)
I = moment of inertia = (ir/64)(OD4 - ID 4)
J = polar moment of inertia = (70/32)(0D 4 - ID4)
J = polar moment of inertia = (70/32)(0D 4 - ID4)
The shear stresses are expressed in a local coordinate system with r radial (X in ANSYS coordinates), 0 circumferential (Z in ANSYS coordinates), and Z axial (Y in ANSYS coordinates). Tables 4 and 5 show the calculation of stresses; ID, OD, and L are taken from the previous piping load stress calculations [11, Section 3.4]. Forces and moments are taken from Reference 11, Table 1. Note that the IDs shown in Table 4 for the safe end and nozzle blend radius (25.938" and 37.368", respectively) represent the two most limiting locations for the nozzle (See Figure 3), and therefore do not represent the ID values where the HTCs were calculated.
The shear stresses are expressed in a local coordinate system with r radial (X in ANSYS coordinates), 0 circumferential (Z in ANSYS coordinates), and Z axial (Y in ANSYS coordinates). Tables 4 and 5 show the calculation of stresses; ID, OD, and L are taken from the previous piping load stress calculations [11, Section 3.4]. Forces and moments are taken from Reference 11, Table 1. Note that the IDs shown in Table 4 for the safe end and nozzle blend radius (25.938" and 37.368", respectively) represent the two most limiting locations for the nozzle (See Figure 3), and therefore do not represent the ID values where the HTCs were calculated.
File No.: 0801038.304                                                                             Page 13 of 20 Revision: 1 F0306-01:
File No.: 0801038.304 Page 13 of 20 Revision: 1 F0306-01:


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Table 4: Recirculation Outlet Nozzle Attached Piping Loads and Dimensions [9, 11]
Table 4: Recirculation Outlet Nozzle Attached Piping Loads and Dimensions [9, 11]
Safe End     Nozzle Blend Radius Fx, kip             20.0               20.0 Fy, kip             20.0               20.0 F,, kip             30.0               30.0 Mx, kip-in         2004.0             2004.0 My, kip-in         3000.0             3000.0 Mz, kip-in         2004.0             2004.0 L, in             4.25             42.77 OD, in             28.38             55.88 ID, in           25.938             37.368 Table 5: Membrane Plus Bending Stresses Due to Piping Loads Safe End    Blend Radius MxL, kip-in         1919.00      1148.60 MyL,     kip-in     3085.00        3855.40 Mxy, kip-in         3633.15        4022.86 F,,, kip-in           28.28        28.28 A, in2 4 104.18       1355.76 I, in 4      9624.85     382912.48 J, in        19249.69     765824.95 UYzi,  ksi        0.288         0.022 az, ksi            4.895         0.196 cz, ksi          5.183          0.218
Safe End Nozzle Blend Radius Fx, kip 20.0 20.0 Fy, kip 20.0 20.0 F,, kip 30.0 30.0 Mx, kip-in 2004.0 2004.0 My, kip-in 3000.0 3000.0 Mz, kip-in 2004.0 2004.0 L, in 4.25 42.77 OD, in 28.38 55.88 ID, in 25.938 37.368 Table 5: Membrane Plus Bending Stresses Due to Piping Loads MxL, kip-in MyL, kip-in Mxy, kip-in F,,, kip-in A, in2 I, in4 J, in4 UYzi, ksi az, ksi cz, ksi
                                    'rrO, ksi          1.350          0.049 Tz, ksi            0.543          0.042 FileNo.: 0801038.304                                                                   Page 14 of 20 Revision: 1 F0306-01.
'rrO, ksi Tz, ksi Safe End 1919.00 3085.00 3633.15 28.28 104.18 9624.85 19249.69 0.288 4.895 5.183 1.350 0.543 Blend Radius 1148.60 3855.40 4022.86 28.28 1355.76 382912.48 765824.95 0.022 0.196 0.218 0.049 0.042 FileNo.: 0801038.304 Revision: 1 Page 14 of 20 F0306-01.


V           StructuralIntegrity Associates, Inc.
V Structural Integrity Associates, Inc.
Table 6: 0% Flow Regions 1 and 3 Heat Transfer Coefficients Pipe Inside Diameter, D =:                     L.. inche- =               2.150         ft
Table 6: 0% Flow Regions 1 and 3 Heat Transfer Coefficients Pipe Inside Diameter, D =:
                                                                                                                                                \   '     0.655         mn Outer Pipe, Inside radius, r.=,                     12.9       inches =           1.075         ft 0.328         m Inner Pipe Outside Diameter, D                                   inches                 0.000         ft
L..
                                                                                                                                                  -"      0.000         mi Inner Pipe, Outside radius, r, =                         0   inches               0.000         ft 0.000         m Fluid Velocity, V =             0.000         Itsec
inche- =
* eOoo*' gpm=                                   0 .       rlb/br Characteristic Length, L = D = r                 2.150             ft =             0.655         m T..     --..       AT : assumed to be 12% of fluid temperature =                                   0.40 8                12.00 r         24.00             36.00               40.00             60.00                     72.00             "F
2.150 ft
                                                                                        =                 4.67             6.67             13.33           20.00               26.67             33.33                     40.00           TC Value at Fluid Temperature. T [121                                                                         Units Conversion                         70                 100             200               300               400                 500                   600                     F Water Property                               Factor [19]                     21.11               37.78           93.33             148.89             204.44           260.00                 315.56                   2C k                                     1.7307                     0.5997             0.6300           0.67B4             0.63,-             0.6611           0.6040                 0.5071               W/rr-C
\\ '
      ......         ........................................................................
0.655 mn Outer Pipe, Inside radius, r.=,
                    ....
12.9 inches =
(Termal    .................
1.075 ft 0.328 m
Conductivity)                  ......                                 k*......... 0.3640 0.3465                                  *..........o:
Inner Pipe Outside Diameter, D inches 0.000 ft 0.000 mi Inner Pipe, Outside radius, r, =
                                                                                                                                          ...................
0 inches 0.000 ft 0.000 m
0.30920            0.3950s ".........:*0.382D.*............*.o.
Fluid Velocity, V =
0.3490              .........
0.000 Itsec eOoo *' gpm=
2 o .........
0.
02930              f .L.r.:.-.'...
rlb/br Characteristic Length, L = D = r 2.150 ft =
Btulhr-ft-'F c;                                    4.109                        4.165              4,179            4.229              4.313              4.522              4.902                  6.322              kJlkg-=C
0.655 m
                                            ~ ~~~ ~
T.. --..
                                      ~ (Seii~a)1.000
AT : assumed to be 12% of fluid temperature =
                                  .............                                   ~~~~~~~~-09
8 0.40 12.00 r 24.00 36.00 40.00 60.00 72.00 "F
                                                                  ~ ~ ~s!!.e.t...........................o...........         ........   ...
=
oo.........1.030 1.010                o.3.o......... 1,080 .........1.190
4.67 6.67 13.33 20.00 26.67 33.33 40.00 TC Value at Fluid Temperature. T [121 Units Conversion 70 100 200 300 400 500 600 F
                                                                                                                                                                              ........               =.9o....           !.=o. ..............
Water Property Factor [19]
                                                                                                                                                                                                                  .......1.510                  u..........
21.11 37.78 93.33 148.89 204.44 260.00 315.56 2C k
Btu/Ibnn.F 97.1              004.7
1.7307 0.5997 0.6300 0.67B4 0.63,-
                                                                                                                      .916.01          982.7              917.6              650.6              784.9                  679.2                  t'gIm3
0.6611 0.6040 0.5071 W/rr-C (Termal Conductivity) 0.3465 0.3640 0.30920 0.3950 0.382D 0.3490 02930 Btulhr-ft-'F k*.........  
                          .o*. *.......................... ...........................
*..........o:
      ................. (Density)                                                                  *62.3
s ".........:*.*............*.o.
                                                                                                    ..............
2 o......... f.L.r.:.-.'...
                                                                                                      .                   .. 60.1,:................ 57.3
c; 4.109 4.165 4,179 4.229 4.313 4.522 4.902 6.322 kJlkg-=C (Seii~a)1.000 09 1.010 1.030 1,080 1.190 1.510 Btu/Ibnn.F
                                                                                                                  . 662.1:............                     ........... . 5............
.............~ ~
53.6              f49.0.o..................
~ ~ ~ ~ ~ ~ ~ ~~~~~~~~-
                                                                                                                                                                                                                  . .... 42.4............     *.. ..........
s !!.e.t...........................o......................oo......... o.3.o.........  
lbrnift 1.8                  1.896E-04            3.24E-04        6.66E-04            1.016-03            1.40E-03          1.90E-03              3.15E-03              n*i:'_C
......... =.9o....  
      .....f(Volumetric:
.......!.=o...............
              .o........     * .o.t
u..........
                          ....
.916.01 97.1 004.7 982.7 917.6 650.6 784.9 679.2 t'gIm3 (Density) 62.3 62.1 60.1, 57.3 53.6 49.0 42.4 lbrnift
Rate  Iof Expansion).
..................o*. *.....................................................  
                                        ..
............... 6 :............
* n....
............................ 5 f.o..................
                                            ....      ..... ...........................     ....1:05E-04
1.8 1.896E-04 3.24E-04 6.66E-04 1.016-03 1.40E-03 1.90E-03 3.15E-03 n*i:'_C (Volumetric: Rate of Expansion).
                                                                                                  ,.o o.f......       ......................................................
1:05E-04 1.80E-04 3.70E-04 15.60E-04 7.800E-04 1.10E-03 1.756E-03 felft-F
1.80E-04        3.70E-04          15.60E-04              * .. .........
..... f.o.....  
7.800E-04              o*..
*.o.t I..
1.10E-03  ?*........ !.*........
* n....  
1.756E-03                  . ..F*...
....,.o o.f......
                                                                                                                                                                                                                                ........ .*.felft-  ---..
o* ?*........ !.*........
1                                    0.3046                      9.006              9.80f            9.,06              9.806              9.306            9.606                  ME.606                Ms (Gravitational Constant)                                                          32.17              32.17            32.17              32.17              :32.17            32.17                  32.17                  *s; M                                      1.4681                  9.86E-04            6.926-04        3.07E-04            1.93E-04          1.38-04          1.04E-04              8.62E-015                lgm-s
1 0.3046 9.006 9.80f 9.,06 9.806 9.306 9.606 ME.606 Ms (Gravitational Constant) 32.17 32.17 32.17 32.17
      ...................*t V...o...................
:32.17 32.17 32.17
(Dy~namic    Viscosity)                  ........................... ....**EO.    ....................
*s; M
6.869-04            4.58E-04            0..-...
1.4681 9.86E-04 6.926-04 3.07E-04 1.93E-04 1.38-04 1.04E-04 8.62E-015 lgm-s (Dy~namic Viscosity) 6.869-04 4.58E-04 2.06E-04 1.306-04 9.306-05 7.006-05 5.796-05 lbnrdft-s
                                                                                                                                          ...............
*t V...o..................................................**EO.
2.06E-04              .*O................O-.
0..-....*O................O-.
1.306-04          9.306-05          7.O.................
7.O................. SZ*.5..........
                                                                                                                                                                                              .......
0.......
7.006-05                SZ*.5.
Pr 6.980 4.510 1.910 1.220 0.950 0.859 1.070 (Prandtl Number)
5.796-05......... lbnrdft-s 0.......
Calculated Parameter Formula 70 100 200 300 4S0 500 T00 ReynoldMs Number, Re pVO/ft 0
                                                                                                                                                                                                                                                      .....
0 0
Pr                                                                  6.980              4.510            1.910              1.220              0.950            0.859                  1.070                    -
0 0
(Prandtl Number)
0 0
Calculated Parameter                                Formula                        70                100              200                300                4S0                500                                            T00 ReynoldMs Number, Re                                pVO/ft                        0                  0                0                0                  0                  0                    0                    -
GrasheofNumber. Gr gATL-/(Ip}
GrasheofNumber. Gr                            gATL-/(Ip}                2441754517            1.2,97E+10      2.417E&#xf7;11            1.252E+12 3.9768E+12                1.034-+13          2.16049E+13                    -
2441754517 1.2,97E+10 2.417E&#xf7;11 1.252E+12 3.9768E+12 1.034-+13 2.16049E+13 Grashof Number, Gr, gAAT(r.-rj)-'/(u~p-3.05E+08 1.506+D9 3.026+10 1.576+11 4.97E+11 1.29E612 2.70E+12 Rayleigh Number. Ru GrPr 170434-46531 5.7265E&#xf7;10 4.616.+11 1.528ME12 3.77770+12 8.8836+12 2.311726+13 Rayleigh Number, Ru GrPr 2.1356-09 7.16E+09 5.77E+10 1.91E611 4.72E+11 1.116+12 2.696.12 From [19):
Grashof Number, Gr,                        gAAT(r.-rj)-'/(u~p-            3.05E+08            1.506+D9        3.026+10            1.576+11            4.97E+11          1.29E612              2.70E+12                    -
Inside Surface Natural Convection Heat Transfer Coefficient:
Rayleigh Number. Ru                                GrPr                170434-46531          5.7265E&#xf7;10 4.616.+11                1.528ME12          3.77770+12        8.8836+12          2.311726+13                    -
Case:
Rayleigh Number, Ru                                GrPr                  2.1356-09            7.16E+09        5.77E+10            1.91E611            4.72E+11          1.116+12              2.696.12                    -
Enclosed cylinder C
From [19):
n'0.55l n= =fl H*,
Inside Surface NaturalConvection Heat TransferCoefficient:
C(OrPr)7'IL 181.85 258.65 46934 637.80 7"/'73.57 875.17 933.22 Wnr-'C 32.03 45.55 82.66
Case:                            Enclosed cylinder                                        C                                  n==fl n'0.55l H*,                                  C(OrPr)7'IL                  181.85              258.65          46934              637.80              7"/'73.57        875.17                933.22              Wnr-'C 32.03              45.55            82.66          ,i-,112.34U,.          136.24            154.13                164.35            Btufhr-ft:-*F FileNo.: 0801038.304                                                                                                                                                                                                                Page 15 of 20 Revision: I F0306-01.
,i-,112.34U,.
136.24 154.13 164.35 Btufhr-ft:-*F FileNo.: 0801038.304 Revision: I Page 15 of 20 F0306-01.


VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
Table 7: 0% Flow Region 5 Heat Transfer Coefficient Pipe Inside Diameter, D =             .40..O0OW?&#x17d;       inches =           3.333         ft
Table 7: 0% Flow Region 5 Heat Transfer Coefficient Pipe Inside Diameter, D =  
                                                                                                                                                  =       1.016         m Outer Pipe, Inside radius, r, =                         20       inches =         1.667         ft 0.508         m Inner Pipe Outside Diameter, D =                                   inches =           0.000         ft
.40..O0OW?&#x17d; inches =
                                                                                                                                                    =   0.600         m Inner Pipe, Outside radius, r, =                           0     inches =         0.000         ft 0.000         m Fluid Velocity, V =             00,00           fusec             0     D       pm=                               0 Mitlhr Characteristic Length, L = D =                   3.333               ft =           1.016         m T_       T           Lt = assumed to be 12% of fluid temperature =                                 0.40             12,00             24.00             3M.00,             46.00,           60.00                       72.00                  'F 4.67               6.67             13.33             20.00             25.67             33.33                     40.00                   =C Value at Fluid Temperature, T [121                                                                             Units Conversion                       70                 100                 200             300               400                 000                   600                           'F Water Property                               Factor [19]                   21.11               37.78             93.33           140.89             204.44           260,00                   3105.6                         'C k                                     1.7307                     0.5997             0.6300             0.6784           0.6636             0.6M11           0.6040                   0.5071                   W/M-lC
3.333 ft
        ......................     *. . ).
=
                        . .. cConductivity)
1.016 m
                .(Thermal                      ............................................. o0.a4605              :** o..........:*.*.........z*
Outer Pipe, Inside radius, r, =
                                                                                                    ... ..................
20 inches =
0.36.40  ...........0.3020          0.39500.          ........
1.667 ft 0.508 m
0.3E20Lo          0.3.* . ..............
Inner Pipe Outside Diameter, D =
                                                                                                                                                                                          ........
inches =
                                                                                                                                                                                              ....
0.000 ft
0.3490                    0.29300 .    *      ........
= 0.600 m
                                                                                                                                                                                                                                              *~,
Inner Pipe, Outside radius, r, =
                                                                                                                                                                                                                                              .........     :. .:
0 inches =
tu/tir-ft-'F
0.000 ft 0.000 m
: c.                                     4.1069                      4.185              4.179              4229            4.313              4.522            4.002                    6.322                  Ij/Vg-'C
Fluid Velocity, V =
        ......................     Heat)
00,00 fusec 0
(Specific................................                                 1.000              0.990              1.010          1.030
D pm=
                                                                      ...................................................................................................... 1.050            1.190
0 Mitlhr Characteristic Length, L = D =
                                                                                                                                                                                          *...........................                          Btu'lbm-'F 1.510 ........................
3.333 ft =
O                                    16.018                      997.1              994.7              S62.7            917.8              056.6            784.0                    679.2                      kgin&#xfd; (Density)                                                              62.3                62.1                60.1            57.3                5316              49.0                    42.4                    lbn~fe
1.016 m
                                                          ,--          1.0 -:24-          1.0E-04                              6..66-04        1.01E-03            1.400-03          1.9-SE3.                  3.15E-03                  m r/m,C (Volumetric Rate of E*pansion)                                                      1.05E-04            1.00E-04          3.730-34        5.605-04            7.80E-04          1.1OE-03                  1.7zE-03                    '/f-=F 9                                    0.3042                      9.5,06              9.006                .9.006        9.006              9.806            9.805                    9.606                      tV':
T_
(Graygaittinal
T Lt = assumed to be 12% of fluid temperature =
      .......................      Constant)
0.40 12,00 24.00 3M.00, 46.00, 60.00 4.67 6.67 13.33 20.00 25.67 33.33 72.00
                              /4"...........1.
'F 40.00  
                                  .....................              14...........
=C Value at Fluid Temperature, T [121 Units Conversion 70 100 200 300 400 000 600  
S                    32.17 E0              32.17 2 -4          30 32.17 6 0        .32.17 3 -4
'F Water Property Factor [19]
                                                                                      ..... .......................................................................
21.11 37.78 93.33 140.89 204.44 260,00 3105.6  
99                                                                        1.32.17              32.17E-E-4"..................................1.
'C k
                                                                                                                                                                                                                        ,.....":"                    is.
1.7307 0.5997 0.6300 0.6784 0.6636 0.6M11 0.6040 0.5071 W/M-lC (Thermal Conductivity) 0.a4605 0.36.40 0.3020 0.3950 0.3E20 0.3490 0.2930 tu/tir-ft-'F
32.17 ..... ..................
... c *.  
A1.4081                                                9.96E-114          6.82f-04          3.07E0-4        1.93E-04            1.38E-04          1.0,4E-D4 8.62E-05                                  kg~nm-s 1.30E-04            9.300-05                                    1.19E-01                  infft-s
)........................................... o.....................
                  . .P....
:** o..........:*.*.........z*
                  ...      ..Viscosity) namic  r              .......................................... 6.69E-04 6............. 4.56E0-4
: 0.
                                                                                                                    "...1"..........
Lo 0.3.*.
                                                                                                                ..........            2.06E--04
0
                                                                                                                                  ....... *b              Y* *
*~,
                                                                                                                                                        .........            6* "........7.00--05
: c.
                                                                                                                                                                      ..........              "7*.......... ....            ;*..............    .............
4.1069 4.185 4.179 4229 4.313 4.522 4.002 6.322 Ij/Vg-'C (Specific Heat) 1.000 0.990 1.010 1.030 1.050 1.190 1.510 Btu'lbm-'F O
Pr6.900                                                              4.5110              1.910          1.220              0.9150            0.659                    1.00 (Prandtl Number)
16.018 997.1 994.7 S62.7 917.8 056.6 784.0 679.2 kgin&#xfd; (Density) 62.3 62.1 60.1 57.3 5316 49.0 42.4 lbn~fe 1.0 1.0E-04
Calculated Parameter                                Formula                        70                100                200            300                400                500                    600                        'F Reynold's Number, Re                                pVDat                        0                    0                  0                0                  0                  0                      0 GrashofNumb*er, Or                            g*ATL=/r4p}u              90S'9,61160-        4.73190410 9.006E011                4.667E.&#xfd;12        1,.461S9E'13      3.854E+13            6.05143E+13                          --
-:24-6..66-04 1.01E-03 1.400-03 1.9-SE3.
Grashof Number, Gr,                        gALT(rr,-?/(ta)a                1.14E49            5.915049          1.13E011        5.083011            1.85,+12        4.825-12                  1.01E-13                        -
3.15E-03 m
Rayleigh Number, Ra                                GrPr                63515209008          2.134t1611          1.72E-12      5.69305&#xf7;12          1,40755413        3.315013              8.61503E+13                          -
r/m, C (Volumetric Rate of E*pansion) 1.05E-04 1.00E-04 3.730-34 5.605-04 7.80E-04 1.1OE-03 1.7zE-03
Rayleigh Number, Ra                                Gr5 Pr                  7.94E01-            2.67E+10          2.15E-11          7.12E011            1.76E+12        4.145-12                  1.08E+13                         -
'/f-=F 9
From f191:
0.3042 9.5,06 9.006
.9.006 9.006 9.806 9.805 9.606 tV':
(Graygaittinal Constant) 32.17 32.17 32.17 32.17 32.17 32.17 32.17 is.
/4"...........1.
14 S 99 E 0 2 -4 30 6 0
. 3 -4
: 1.
E-4"..................................1.
E-A1.4081 9.96E-114 6.82f-04 3.07E0-4 1.93E-04 1.38E-04 1.0,4E-D4 8.62E-05 kg~nm-s namic Viscosity) 6.69E-04 4.56E0-4 2.06E--04 1.30E-04 9.300-05 7.00--05 1.19E-01 infft-s
.P....  
..r 6.............  
"...1".......... *b Y*
* 6* "........ "7*.............. ;*..............
Pr6.900 4.5110 1.910 1.220 0.9150 0.659 1.00 (Prandtl Number)
Calculated Parameter Formula 70 100 200 300 400 500 600
'F Reynold's Number, Re pVDat 0
0 0
0 0
0 0
GrashofNumb*er, Or g*ATL=/r4p}u 90S'9,61160-4.73190410 9.006E011 4.667E.&#xfd;12 1,.461S9E'13 3.854E+13 6.05143E+13 Grashof Number, Gr, gALT(rr,-?/(ta)a 1.14E49 5.915049 1.13E011 5.083011 1.85,+12 4.825-12 1.01E-13 Rayleigh Number, Ra GrPr 63515209008 2.134t1611 1.72E-12 5.69305&#xf7;12 1,40755413 3.315013 8.61503E+13 Rayleigh Number, Ra Gr5Pr 7.94E01-2.67E+10 2.15E-11 7.12E011 1.76E+12 4.145-12 1.08E+13 Fro m f191:
Inside Surface Natural Convection Hleat Transfer Coefficient:,
Inside Surface Natural Convection Hleat Transfer Coefficient:,
Case:                           Enclosed cylinder                                       C=                                   n (1                                       -.      ,.-3-&deg;'           .*)-." .
Case:
H. .                                 C(GrPrY65WL                 162*97             231.79             420.60           571.E6       '      693.25           704.30                   836.32                   W .r.--C 2&.70               40.82             74.07         .103.6.O .           122.09           138.13                   147.29               Btu/hr-ft:_F File No.: 0801038.304                                                                                                                                                                                                                   Page 16 of 20 Revision: 1 F0306-01
Enclosed cylinder C =
(1 n
,.-3-&deg;'  
.*)-.".
H..
C(GrPrY65WL 162*97 231.79 420.60 571.E6 693.25 704.30 836.32 W  
.r.--C 2&.70 40.82 74.07  
.103.6.O.
122.09 138.13 147.29 Btu/hr-ft:_F File No.: 0801038.304 Revision: 1 Page 16 of 20 F0306-01


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I+
+
                                                  , "*   I       .- "-,- - _
I
tMz                               Y, S7Z Z
"* I tMz Y,
Figure 2: Coordinate System for Forces and Moments SST CLAD 103.00 R MIN LOW ALLOY
S7Z Z
                                                                                        -  STEEL NOZZLE REPLACEMENT PIPE                                                                      SA 508 CL IIt SUPPLIED BY OTHERS                                                                2.50 R ,
Figure 2: Coordinate System for Forces and Moments SST CLAD 103.00 R MIN LOW ALLOY STEEL NOZZLE SA 508 CL IIt 2.50 R,
I25.40 MIN 0 25.93 '_:'0, NOTE: NOZZLE DIMENSIONS ARE REFERENCE DIMENSIONS IN INCHES 14                         -EXISTING SST (308 LI OVERLAY Figure 3: RO Nozzle and Safe End Geometry [201 File No.: 0801038.304                                                                           Page 17 of 20 Revision: I F0306-01
REPLACEMENT PIPE SUPPLIED BY OTHERS I25.40 MIN 0 25.93 '_:'0, NOTE: NOZZLE DIMENSIONS ARE REFERENCE DIMENSIONS IN INCHES 14
-EXISTING SST (308 LI OVERLAY Figure 3: RO Nozzle and Safe End Geometry [201 File No.: 0801038.304 Revision: I Page 17 of 20 F0306-01


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5.0 RESULTS OF ANALYSIS This calculation package specifies the ASME Code Edition, finite element model, thermal and pressure transients (Table 1), and HTCs (Table 2) to be used in a fatigue usage calculation of the RO nozzle at Vermont Yankee. Thermal transient and pressure stress components will be calculated using ANSYS [6]
5.0 RESULTS OF ANALYSIS This calculation package specifies the ASME Code Edition, finite element model, thermal and pressure transients (Table 1), and HTCs (Table 2) to be used in a fatigue usage calculation of the RO nozzle at Vermont Yankee. Thermal transient and pressure stress components will be calculated using ANSYS [6]
and will be combined with piping loads in subsequent calculations.
and will be combined with piping loads in subsequent calculations.
Linearized stress components will be used for the fatigue usage calculation. For the nozzle blend radius location, the stresses used in the evaluation will be for the base metal only; that is, the cladding material will be unselected prior to stress extraction consistent with ASME Code rules and Reference [13].
Linearized stress components will be used for the fatigue usage calculation. For the nozzle blend radius location, the stresses used in the evaluation will be for the base metal only; that is, the cladding material will be unselected prior to stress extraction consistent with ASME Code rules and Reference [13].
The fatigue usage calculation will consider all six stress components, and will be performed using the rules of Subarticle NB-3200 of Section III of the ASME Code [1]. Calculated fatigue usage factors will be multiplied by the appropriate environmental fatigue multipliers computed for each location.
The fatigue usage calculation will consider all six stress components, and will be performed using the rules of Subarticle NB-3200 of Section III of the ASME Code [1]. Calculated fatigue usage factors will be multiplied by the appropriate environmental fatigue multipliers computed for each location.
The results of this calculation are to be used in SIA calculations: No. 081038.305, Stress Analysis of Reactor Recirculation Outlet Nozzle and No. 081038.306, Fatigue Analysis of Recirculation Outlet Nozzle File No.: 0801038.304                                                                                 Page 18 of 20 Revision: 1 F0306-01I
The results of this calculation are to be used in SIA calculations: No. 081038.305, Stress Analysis of Reactor Recirculation Outlet Nozzle and No. 081038.306, Fatigue Analysis of Recirculation Outlet Nozzle File No.: 0801038.304 Revision: 1 Page 18 of 20 F0306-01I


V     StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.


==6.0 REFERENCES==
==6.0 REFERENCES==
Line 654: Line 1,408:
: 12. N. P. Cheremisinoff, "Heat Transfer Pocket Handbook," Gulf Publishing Co., 1984.
: 12. N. P. Cheremisinoff, "Heat Transfer Pocket Handbook," Gulf Publishing Co., 1984.
: 13. NUREG/CR-6260 (INEL-95/0045), "Application of NUREG/CR-5999 Interim Fatigue Curves to Selected Nuclear Power Plant Components," March 1995.
: 13. NUREG/CR-6260 (INEL-95/0045), "Application of NUREG/CR-5999 Interim Fatigue Curves to Selected Nuclear Power Plant Components," March 1995.
: 14. Warren C. Young, "Roark's Formulas for Stress & Strain," Sixth Edition, McGraw- Hill Book Company, 1989.
: 14. Warren C. Young, "Roark's Formulas for Stress & Strain," Sixth Edition, McGraw-Hill Book Company, 1989.
: 15. NUREG/CR-5704, "Effects of LWR Coolant Environments on Fatigue Design Curves of Austenitic Stainless Steels," April, 1999.
: 15. NUREG/CR-5704, "Effects of LWR Coolant Environments on Fatigue Design Curves of Austenitic Stainless Steels," April, 1999.
FileNo.: 0801038.304                                                                           Page 19 of 20 Revision: 1 f0306-01i
FileNo.: 0801038.304 Page 19 of 20 Revision: 1 f0306-01i


V     StructuralIntegrity Associates, Inc.
V Structural Integrity Associates, Inc.
: 16. SI Calculation No. VY-19Q-301, Revision 0, "Design Inputs and Methodology for ASME Code Confirmatory Fatigue Usage Analysis of Reactor Feedwater Nozzle."
: 16. SI Calculation No. VY-19Q-301, Revision 0, "Design Inputs and Methodology for ASME Code Confirmatory Fatigue Usage Analysis of Reactor Feedwater Nozzle."
: 17. SI Calculation No. VY-19Q-302, Revision 0, "ASME Code Confirmatory Fatigue Evaluation of Reactor Feedwater Nozzle."
: 17. SI Calculation No. VY-19Q-302, Revision 0, "ASME Code Confirmatory Fatigue Evaluation of Reactor Feedwater Nozzle."
Line 664: Line 1,418:
: 19. J. P. Holman, "Heat Transfer," 4th Edition, McGraw Hill Inc., 1976.
: 19. J. P. Holman, "Heat Transfer," 4th Edition, McGraw Hill Inc., 1976.
: 20. GE Stress Report 23A4316, Revision 0, "Stress Report-Reactor Vessel Recirculation Outlet Safe End," SI File No. VY-16-204.
: 20. GE Stress Report 23A4316, Revision 0, "Stress Report-Reactor Vessel Recirculation Outlet Safe End," SI File No. VY-16-204.
File No.: 0801038.304                                                                       Page 20 of 20 Revision: 1 F0306-01
File No.: 0801038.304 Revision: 1 Page 20 of 20 F0306-01


V     StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
APPENDIX A:
APPENDIX A:
ANSYS Input File: RONVY.INP FileNo.: 0801038.304                                     Page A-I of A-23 Revision: 1 F0306-O1F
ANSYS Input File: RONVY.INP FileNo.: 0801038.304 Revision: 1 Page A-I of A-23 F0306-O1F


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
ANSYS Input File: RONVY.INP finish
ANSYS Input File: RONVY.INP finish
  /clear, start
/clear, start
  /prep7
/prep7
  /title,     Recirc Outlet Nozzle Finite Element Model
/title, Recirc Outlet Nozzle Finite Element Model
  /com, PLANE42, 2-D Solid et,1,PLANE42,,,1           !Axisymmetric
/com,
  /com,     ****************************
: PLANE42, 2-D Solid et,1,PLANE42,,,1  
  /com,     Material Properties
!Axisymmetric
  /corn,   ****************************
/com,  
MPTEMP, , 70,200,300,400,500,600 tmp = 3600*12             ! hr-ft to sec-in
/com, Material Properties
  /COM, Material #1 Safe-End and Portion of Piping (SA-182 F316)                   (18Cr-8Ni)
/corn,
MPDATA,EX       ,1, , 28.3e6,     27.6e6,     27.0e6,   26.5e6,   25.8e6,     25.3e6 MPDATA,ALPX,I, , 8.5e-6,           8.9e-6,       9.2e-6,   9.5e-6,   9.7e-6,       9.8e-6 MPDATA, KXX,1I,,       8.6/tmp,   9.3/tmp,   9.8/tmp,   10.4/tmp, 10.9/tmp,   11.3/tmp MPDATA,       C,1, , 0.116,       0.122,       0.125,     0.129,     0.131,       0.133 mp, nuxy, 1, 0. 3 mp, dens, 1,0.283
: MPTEMP,  
  /COM, Material #2 (Nozzle Forging) SA-508 Class 2 (3/4Ni-I/2Mo-I/3Cr-V)
, 70,200,300,400,500,600 tmp = 3600*12  
MPDATA,EX       ,2, , 27.8e6,   27.1e6,     26.7e6,   26.1e6,   25.7e6,     25.2e6 MPDATA,ALPX,2, , 6.4e-6,           6.7e-6,       6.9e-6,   7.le-6,   7.3e-6,       7.4e-6 MPDATA, KXX,2, , 23.5/tmp, 23.6/tmp, 23.4/tmp, 23.1/tmp, 22.7/tmp, 22.2/tmp MPDATA,       C,2, , 0.105,       0.114,       0.119,     0.125,     0.130,       0.135 mp, nuxy, 2, 0. 3 mp, dens, 2,0.283
! hr-ft to sec-in
    /COM, Material #3 (Cladding) SA-240 Type 304 (18Cr-8Ni)
/COM, Material #1 Safe-End and Portion of Piping (SA-182 F316) 8Ni)
MPDATA,EX       ,3, , 28.3e6,   27.6e6,     27.0e6,   26.5e6,   25.8e6,     25.3e6 MPDATA,ALPX,3, , 8.5e-6,           8.9e-6,       9.2e-6,   9.5e-6,     9.7e-6,     9. 8e-6 MPDATA, KXX,3, , 8.6/tmp, 9.3/tmp, 9.8/tmp, 10.4/tmp, 10.9/tmp, 11.3/tmp MPDATA,       C,3, , 0.116,       0.122,       0.125,     0.129,     0.131,       0.133 mp, nuxy, 3, 0.3 File No.: 0801038.304                                                         Page A-2 of A-23 Revision: 1 F0306-01I
MPDATA,EX  
,1,, 28.3e6, 27.6e6, 27.0e6, 26.5e6, 25.8e6, MPDATA,ALPX,I,  
, 8.5e-6, 8.9e-6, 9.2e-6, 9.5e-6, 9.7e-6, 6
(18Cr-25.3e6 9.8e-
: MPDATA, KXX,1I,,
8.6/tmp, 9.3/tmp, 9.8/tmp, 10.4/tmp, 10.9/tmp, 11.3/tmp
: MPDATA, C,1,  
, 0.116, 0.122, 0.125, 0.129, 0.131, 0.133 mp, nuxy, 1, 0. 3 mp, dens, 1,0.283
/COM, Material #2 (Nozzle Forging) SA-508 Class 2 (3/4Ni-I/2Mo-I/3Cr-V)
MPDATA,EX  
,2,  
, 27.8e6, 27.1e6, 26.7e6, 26.1e6, 25.7e6, 25.2e6 MPDATA,ALPX,2,  
, 6.4e-6, 6.7e-6, 6.9e-6, 7.le-6, 7.3e-6, 7.4e-6
: MPDATA, KXX,2,  
, 23.5/tmp, 23.6/tmp, 23.4/tmp, 23.1/tmp, 22.7/tmp, 22.2/tmp
: MPDATA, C,2,  
, 0.105, 0.114, 0.119, 0.125, 0.130, mp, nuxy, 2, 0. 3 mp, dens, 2,0.283 0.135
/COM, Material #3 (Cladding) SA-240 Type 304 (18Cr-8Ni)
MPDATA,EX  
,3,  
, 28.3e6, 27.6e6, 27.0e6, 26.5e6, 25.8e6, MPDATA,ALPX,3,  
, 8.5e-6, 8.9e-6, 9.2e-6, 9.5e-6, 9.7e-6, 6
25.3e6
: 9. 8e-
: MPDATA, KXX,3,  
, 8.6/tmp, 9.3/tmp, 9.8/tmp, 10.4/tmp, 10.9/tmp, 11.3/tmp
: MPDATA, C,3,  
, 0.116, 0.122, 0.125, 0.129, 0.131, 0.133 mp, nuxy, 3, 0.3 File No.: 0801038.304 Revision: 1 Page A-2 of A-23 F0306-01I


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
mp, dens, 3,0.283
mp, dens, 3,0.283
    /COM,   Material #4   (Vessel) SA-533,     GR. B (Mn-1/2Mo-1/2Ni)-
/COM, Material #4 (Vessel) SA-533, GR.
MPDATA,EX       14, , 29.2e6,   28.5e6,     28.0e6,     27.4e6,   27.0e6,     26.4e6 MPDATA,ALPX,4,       , 7.0e-6,     7.3e-6,       7.4e-6,   7.6e-6,     7.7e-6,     7.8e-6 MPDATA, KXX,4,       , 23.5/tmp,   23.6/tmp,     23.4/tmp, 23.1/tmp,   22.7/tmp, 22.2/tmp MPDATA,       C,4, ,   0.105,     0.114,         0.119,     0.125,     0.130,       0.135 mp, nuxy, 4, 0. 3 mp,dens,4, 0.283
B (Mn-1/2Mo-1/2Ni)-
    *AFUN, DEG
MPDATA,EX 14,  
    /com, *** Geometric Parameters *
, 29.2e6, 28.5e6, 28.0e6, 27.4e6, 27.0e6, 26.4e6 MPDATA,ALPX,4,  
    *set,vira, (103+3/16)               !Actual Vessel Inner Radius to base metal used for model
, 7.0e-6, 7.3e-6, 7.4e-6, 7.6e-6, 7.7e-6, 7.8e-6
    *set,vir,2.0*vira                                               !2.0 time of Vessel Inner Radius to base metal used for model
: MPDATA, KXX,4,  
  *settvw,5+5/8-3/16                   !Vessel Wall Thickness
, 23.5/tmp, 23.6/tmp, 23.4/tmp, 23.1/tmp, 22.7/tmp, 22.2/tmp
  *set, ril, 25.75/2
: MPDATA, C,4,  
  *setrol     28.375/2
, 0.105, 0.114, 0.119, 0.125, 0.130, 0.135 mp, nuxy, 4, 0. 3 mp,dens,4, 0.283
  *set,L1,5
*AFUN, DEG
  *set, ro2,28.375/2
/com,  
  *set, L2,4.25
*** Geometric Parameters *
  *set, ro3,28.875/2
*set,vira, (103+3/16)  
  *set, ro4,48.75/2
!Actual Vessel Inner Radius to base metal used for model
  *set, L3, 1.5
*set,vir,2.0*vira  
  *set, L4, 5.25
!2.0 time of Vessel Inner Radius to base metal used for model
  *set, L5,7+1/16
*settvw,5+5/8-3/16  
  *set, L6, 12+13/16
!Vessel Wall Thickness
  *setL7,9+7/8
*set, ril, 25.75/2
  *set,L8, 9+3/8
*setrol 28.375/2
  *set,L9, 31+15/16
*set,L1,5
  *set, L0, L9-12-13/16-tvw
*set, ro2,28.375/2
    *set, ra, 7
*set, L2,4.25
  *set, rb, 1
*set, ro3,28.875/2
    *set, rc, 5.25
*set, ro4,48.75/2
  *set, rd, 2.5
*set, L3, 1.5
    *set, tv, 3/16
*set, L4, 5.25
    *set,dimA,vir-(tv*2.0)+L9+11+Ll           !Vessel Centerline to End of Safe End used for model
*set, L5,7+1/16
    *set,L21,1
*set, L6, 12+13/16
    *set, L22,4.25
*setL7,9+7/8
    *set,ri21, (25+15/16)/2
*set,L8, 9+3/8
    /com,   Geometry File No.: 0801038.304                                                         Page A-3 of A-23 Revision: 1 F0306-01,
*set,L9, 31+15/16
*set, L0, L9-12-13/16-tvw
*set, ra, 7
*set, rb, 1
*set, rc, 5.25
*set, rd, 2.5
*set, tv, 3/16
*set,dimA,vir-(tv*2.0)+L9+11+Ll  
!Vessel Centerline to End of Safe End used for model
*set,L21,1
*set, L22,4.25
*set,ri21, (25+15/16)/2
/com, Geometry File No.: 0801038.304 Page A-3 of A-23 Revision: 1 F0306-01,


VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
local, 13,0, , dimA,       , .
local, 13,0,, dimA,,.
csys, 13
csys, 13
  /com,     Begin at end of Safe-End           - Carbon Section k,   9, ril,     -1*(dimA) k,   2,f ril+tv, -l*(dimA) k,   3, rol, -!*(dimA) k,   4, ril,     -l*(dimA-Ll) k,   5, ril+tv, -l*(dimA-Ll) k,   6, rol, -l*(dimA-Ll) k,   7, ril,     -T*(dimA-Ly-L2) k,   8, ril+tv, -1*(dimA-L5-L2) k,   9f ro2, -r*(dimA-Li-L2) k,   10, ril,     -I*(dimA-LI-L2-,L3) k,22,     ril+tv, -I*(dimA-LI-L2-L3) k, 12,     1o3, -r*(dimA-Lb-L2-L3) k, 13,     ril,     -1*(dimA.Ll-L2-L3-L4) k, 24,     ril+tv, -I*(dimA-LI-L2-L3-L4) k, 15,     ro3, -1*(dimA-Lt-L2-L3-L4) k, 16,     ril,     -1*(dimA-Lt-L2-L3-L4-L5) k, 17,     ril+tv, -         t*(dimA-Ln-L2-L3-L4-L5) k, 18,     ro3, -1*(dirtA-LP-L2-L3-L4-L5) k,19,           ro4,   -0*(dimA-LI-L2-L3-L4-L5-L7)!Temporary Point 1, 19, 18 1,18,15 fillc, 29,i3,2,ira k,22,           ro4+(LS+6)*tan(15),         -I*(dimA-LI-L2-L3-L4-L5-L7-(L8+6) 1, 19, 22 LFILLT, 1i, 4, rb k,   25, ril,     -I*(dimA-LI-L2-L3-L4-L6) k,   26, ril+tv, -I*(dimA-Ll-L2-L3-L4-L6) k,   27, ril+(Ll0+tvw+ltv+4)*tan(15),           -l*(vir-tv-4) k,   28, ril+tv+(L10+tvw+t~v+4)*tan(15),           -l*(vir-tv-4) k,29,           (vir+tvw+tv) tsin (45) . -l* (vir+tvw+tv) *cos (45) k,30,           0, -l*(vir+tvw+tv)           !Temporary   Point k,31.,         0, 0 ! Temporary Point larc, 29, 30, 31, vir+tvw+tv k,32,           (.vir+tv)*sin(45),     -1*(vir+tv)*cos(45)
/com, Begin at end of Safe-End Carbon Section k,
File No.: 0801038.304                                                         Page A-4 of A-23 Revision: I F0306-01I
9, ril,  
-1*(dimA) k, 2,f ril+tv, -l*(dimA) k, 3,
rol, -!*(dimA) k, 4,
: ril,  
-l*(dimA-Ll) k, 5,
ril+tv, -l*(dimA-Ll) k, 6,
rol, -l*(dimA-Ll) k, 7,
: ril,  
-T*(dimA-Ly-L2) k, 8, ril+tv, -1*(dimA-L5-L2) k, 9f ro2, -r*(dimA-Li-L2) k, 10, ril,  
-I*(dimA-LI-L2-,L3) k,22, ril+tv, -I*(dimA-LI-L2-L3) k, 12,
: 1o3,  
-r*(dimA-Lb-L2-L3) k, 13,
: ril,  
-1*(dimA.Ll-L2-L3-L4) k, 24, ril+tv, -I*(dimA-LI-L2-L3-L4) k, 15,
: ro3,  
-1*(dimA-Lt-L2-L3-L4) k, 16,
: ril,  
-1*(dimA-Lt-L2-L3-L4-L5) k, 17, ril+tv, -
t*(dimA-Ln-L2-L3-L4-L5) k, 18,
: ro3,  
-1*(dirtA-LP-L2-L3-L4-L5) k,19, ro4, -0*(dimA-LI-L2-L3-L4-L5-L7)! Temporary Point 1, 19, 18 1,18,15 fillc, 29,i3, 2,ira k,22, ro4+(LS+6)*tan(15),  
-I*(dimA-LI-L2-L3-L4-L5-L7-(L8+6) 1, 19, 22 LFILLT, 1i, 4, rb k,
25,
: ril,  
-I*(dimA-LI-L2-L3-L4-L6) k, 26, ril+tv, -I*(dimA-Ll-L2-L3-L4-L6) k, 27, ril+(Ll0+tvw+ltv+4)*tan(15),  
-l*(vir-tv-4) k, 28, ril+tv+(L10+tvw+t~v+4)*tan(15),  
-l*(vir-tv-4) k,29, (vir+tvw+tv) tsin (45). -l* (vir+tvw+tv) *cos (45) k,30, 0,  
-l*(vir+tvw+tv)  
!Temporary Point k,31.,
0, 0 ! Temporary Point larc, 29, 30, 31, vir+tvw+tv k,32,
(.vir+tv)*sin(45), -1*(vir+tv)*cos(45)
File No.: 0801038.304 Page A-4 of A-23 Revision: I F0306-01I


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
k,33,       0, -1*(vir+tv)         Temporary Point larc, 32, 33, 31,vir+tv k,34,       vir*sin(45),   -1*vir*cos(45) k,35,       0, -l*vir       Temporary Point larc, 34,35,31,vir LSTR,           4,       5 LSTR,           5,       6 LSTR,           6,       9 LSTR,           9,     12 LSTR,         12,       15 LSTR,           5,       8 LSTR,           4,       7 LSTR,           7,     10 LSTR,           8,     11 LSTR,         11,       14 LSTR,         i0,       13 LSTR,         13,       16 LSTR,         14,       17 LSTR,         16,       25 LSTR,         17,       26 LSTR,         26,       28 LSTR,         25,       27 LSTR,           4,       1 LSTR,           1,       2 LSTR,           2,       3 LSTR,           3,       6 LSTR,           5,       2 LSTR,           7,       8 LSTR,           8,       9 LSTR,         12,       11 LSTR,         11,       10 LSTR,         13,       14 LSTR,         14,       15 FLST, 2,2,4, ORDE, 2 FITEM, 2,4 FITEM, 2, 6 LPTN, P51X FLST, 2,2, 4, ORDE, 2 FITEM, 2,8 FITEM, 2,25 LPTN, P51X FLST, 2,2,4,ORDE, 2 FileNo.: 0801038.304                                   Page A-5 of A-23 Revision: 1 F0306-01
k,33, 0,  
-1*(vir+tv)
Temporary Point larc, 32, 33, 31,vir+tv k,34, vir*sin(45),  
-1*vir*cos(45) k,35, 0,  
-l*vir Temporary Point larc, 34,35,31,vir
: LSTR, 4,
5
: LSTR, 5,
6
: LSTR, 6,
9
: LSTR, 9,
12
: LSTR, 12, 15
: LSTR, 5,
8
: LSTR, 4,
7
: LSTR, 7,
10
: LSTR, 8,
11
: LSTR, 11, 14
: LSTR, i0, 13
: LSTR, 13, 16
: LSTR, 14, 17
: LSTR, 16, 25
: LSTR, 17, 26
: LSTR, 26, 28
: LSTR, 25, 27
: LSTR, 4,
1
: LSTR, 1,
2
: LSTR, 2,
3
: LSTR, 3,
6
: LSTR, 5,
2
: LSTR, 7,
8
: LSTR, 8,
9
: LSTR, 12, 11
: LSTR, 11, 10
: LSTR, 13, 14
: LSTR, 14, 15 FLST, 2,2,4, ORDE, 2 FITEM, 2,4 FITEM, 2, 6 LPTN, P51X FLST, 2,2, 4, ORDE, 2 FITEM, 2,8 FITEM, 2,25 LPTN, P51X FLST, 2,2,4,ORDE, 2 FileNo.: 0801038.304 Revision: 1 Page A-5 of A-23 F0306-01


V     StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
FITEM, 2, 7 FITEM, 2,24 LPTN, P51X FLST, 2, 6, 4, ORDE, 6 FITEM, 2, 6 FITEM, 2,25 FITEM, 2,37 FITEM, 2,40 FITEM, 2,42 FITEM, 2,44 LDELE,P51X, , .1 LFILLT,4,41,rd,       ,
FITEM, 2, 7 FITEM, 2,24 LPTN, P51X FLST, 2, 6, 4, ORDE, 6 FITEM, 2, 6 FITEM, 2,25 FITEM, 2,37 FITEM, 2,40 FITEM, 2,42 FITEM, 2,44 LDELE,P51X,  
1*
.1 LFILLT,4,41,rd, 1*
LFILLT, 43, 8, rd,     .
LFILLT, 43, 8, rd,.
LFILLT, 39, 38, rc, FLST, 2,3, 4,ORDE, 3 FITEM, 2,1 FITEM, 2,3 FITEM, 2,5 LCOMB,P51X, ,0 LSTR,           16,         17 LSTR,           17,         21 LSTR,           25,         26 LSTR,           26,         24 LSTR,           22,         30 LSTR,           30,         35 LSTR,           27,         28 LSTR,           28,         33 LSTR,           29,         32 LSTR,           32,         34 k,39,         0,   -1*(vir+tvw+tv)
LFILLT, 39, 38, rc, FLST, 2,3, 4,ORDE, 3 FITEM, 2,1 FITEM, 2,3 FITEM, 2,5 LCOMB,P51X,  
    !Create Areas FLST, 2,4,4 FITEM, 2,27 FITEM, 2,30 FITEM, 2,26 FITEM, 2, 9 AL, P51X, FLST, 2,4,4 FITEM, 2,28 File No.: 0801038.304                       Page A-6 of A-23 Revision: 1 F0306-011
,0
: LSTR, 16, 17
: LSTR, 17, 21
: LSTR, 25, 26
: LSTR, 26, 24
: LSTR, 22, 30
: LSTR, 30, 35
: LSTR, 27, 28
: LSTR, 28, 33
: LSTR, 29, 32
: LSTR, 32, 34 k,39, 0,  
-1*(vir+tvw+tv)
!Create Areas FLST, 2,4,4 FITEM, 2,27 FITEM, 2,30 FITEM, 2,26 FITEM, 2, 9 AL, P51X, FLST, 2,4,4 FITEM, 2,28 File No.: 0801038.304 Page A-6 of A-23 Revision: 1 F0306-011


V     StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
FITEM, 2,29 FITEM, 2, 10 FITEM, 2,30 AL, P51X FLST, 2,4,4 FITEM, 2, 11 FITEM, 2,32 FITEM, 2, 10 FITEM, 2, 14 AL, P51X FLST, 2,4,4 FITEM, 2, 15 FITEM, 2, 14 FITEM, 2, 9 FITEM, 2, 31 AL, P51X FLST, 2,4,4 FITEM,2,32 FITEM, 2,33 FITEM, 2, 12 FITEM, 2, 17 AL, P51X FLST, 2,4,4 FITEM, 2, 16 FITEM, 2, 17 FITEM, 2,31 FITEM, 2,34 AL, P51X FLST, 2,4,4 FITEM, 2,36 FITEM, 2, 13 FITEM, 2,33 FITEM, 2, 18 AL, P51X FLST, 2, 4, 4 FITEM, 2, 19 FITEM, 2, 18 FITEM, 2,35 FITEM, 2,34 AL, P51X FLST, 2,4,4 FITEM, 2,2 FITEM, 2, 5 FITEM, 2,36 FITEM, 2,21 AL, P51X FLST, 2,4,4 File No.: 0801038.304                         Page A-7 of A-23 Revision: 1 F0306-01
FITEM, 2,29 FITEM, 2, 10 FITEM, 2,30 AL, P51X FLST, 2,4,4 FITEM, 2, 11 FITEM, 2,32 FITEM, 2, 10 FITEM, 2, 14 AL, P51X FLST, 2,4,4 FITEM, 2, 15 FITEM, 2, 14 FITEM, 2, 9 FITEM, 2, 31 AL, P51X FLST, 2,4,4 FITEM,2,32 FITEM, 2,33 FITEM, 2, 12 FITEM, 2, 17 AL, P51X FLST, 2,4,4 FITEM, 2, 16 FITEM, 2, 17 FITEM, 2,31 FITEM, 2,34 AL, P51X FLST, 2,4,4 FITEM, 2,36 FITEM, 2, 13 FITEM, 2,33 FITEM, 2, 18 AL, P51X FLST, 2, 4, 4 FITEM, 2, 19 FITEM, 2, 18 FITEM, 2,35 FITEM, 2,34 AL, P51X FLST, 2,4,4 FITEM, 2,2 FITEM, 2, 5 FITEM, 2,36 FITEM, 2,21 AL, P51X FLST, 2,4,4 File No.: 0801038.304 Page A-7 of A-23 Revision: 1 F0306-01


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
FITEM, 2,20 FITEM, 2, 21 FITEM, 2, 3 FITEM, 2,35 AL, P51X FLST, 2,4,4 FITEM, 2, 1 FITEM, 2,37 FITEM, 2,23 FITEM, 2,5 AL, P51X FLST, 2,4,4 FITEM, 2,22 FITEM, 2,23 FITEM, 2,25 FITEM, 2,3 AL, P51X FLST, 2,4,4 FITEM, 2,38 FITEM, 2,42 FITEM, 2,37 FITEM, 2, 8 AL, P51X FLST, 2,4,4 FITEM, 2, 4 FITEM, 2,8 FITEM, 2,25 FITEM, 2,40 AL, PSIX FLST, 2,4,,4 FITEM, 2,24 FITEM, 2,45 FITEM, 2,7 FITEM, 2,42 AL, P51X FLST, 2,4,4 FITEM, 2, 6 FITEM, 2, 7 FITEM, 2,44 FITEM, 2,40 AL, P51X FLST, 2,4,4 FITEM, 2, 41 FITEM, 2,43 FITEM, 2, 47 FITEM, 2,44 AL, P51X File No.: 0801038.304                         Page A-8 of A-23 Revision: 1 F0306-01.
FITEM, 2,20 FITEM, 2, 21 FITEM, 2, 3 FITEM, 2,35 AL, P51X FLST, 2,4,4 FITEM, 2, 1 FITEM, 2,37 FITEM, 2,23 FITEM, 2,5 AL, P51X FLST, 2,4,4 FITEM, 2,22 FITEM, 2,23 FITEM, 2,25 FITEM, 2,3 AL, P51X FLST, 2,4,4 FITEM, 2,38 FITEM, 2,42 FITEM, 2,37 FITEM, 2, 8 AL, P51X FLST, 2,4,4 FITEM, 2, 4 FITEM, 2,8 FITEM, 2,25 FITEM, 2,40 AL, PSIX FLST, 2,4,,4 FITEM, 2,24 FITEM, 2,45 FITEM, 2,7 FITEM, 2,42 AL, P51X FLST, 2,4,4 FITEM, 2, 6 FITEM, 2, 7 FITEM, 2,44 FITEM, 2,40 AL, P51X FLST, 2,4,4 FITEM, 2, 41 FITEM, 2,43 FITEM, 2, 47 FITEM, 2,44 AL, P51X File No.: 0801038.304 Page A-8 of A-23 Revision: 1 F0306-01.


VStructural Integrity Associates, Inc.
VStructural Integrity Associates, Inc.
FLST, 2, 4,4 FITEM, 2,39 FITEM, 2, 46 FITEM, 2, 45 FITEM, 2,43 AL, P51X define materials FLST, 5,8,5, ORDE, 2 FITEM, 5,1 FITEM, 5, -8 CM, Y,AREA ASEL, , , ,P51X CM, Y1,AREA CMSEL,S,_Y 1*
FLST, 2, 4,4 FITEM, 2,39 FITEM, 2, 46 FITEM, 2, 45 FITEM, 2,43 AL, P51X define materials FLST, 5,8,5, ORDE, 2 FITEM, 5,1 FITEM, 5, -8 CM, Y,AREA
CMSEL,S, _YI AATT,           1, , 1,       0, CMSEL,S, Y CMDELE, Y CMDELE, Y1 1*
: ASEL,  
FLST, 5,5,5, ORDE, 5 FITEM, 5,9 FITEM, 5,11 FITEM, 5,13 FITEM, 5,15 FITEM, 5,18 CM, _Y,AREA ASEL, , , ,P51X CM, _Y1,AREA CMSEL,S, Y I*
,P51X CM, Y1,AREA CMSEL,S,_Y 1*
CMSEL,S, Y1 AATT,           2, , 1,       0, CMSEL,S, Y CMDELE, _Y CMDELE, Y1 FLST, 5,5,5, ORDE, 5 FITEM, 5,10 FITEM, 5,12 FITEM, 5,14 FITEM, 5,16 FITEM, 5, -17 CM, _Y,AREA ASEL, , , ,P51X File No.: 0801038.304                     Page A-9 of A-23 Revision: I F0306-01:
CMSEL,S, _YI
: AATT, 1,,
1, 0,
CMSEL,S, Y
: CMDELE, Y
: CMDELE, Y1 1*
FLST, 5,5,5, ORDE, 5 FITEM, 5,9 FITEM, 5,11 FITEM, 5,13 FITEM, 5,15 FITEM, 5,18 CM, _Y,AREA
: ASEL,  
,P51X CM, _Y1,AREA CMSEL,S, Y
I*
CMSEL,S, Y1
: AATT, 2,
1, 0,
CMSEL,S, Y
CMDELE, _Y
: CMDELE, Y1 FLST, 5,5,5, ORDE, 5 FITEM, 5,10 FITEM, 5,12 FITEM, 5,14 FITEM, 5,16 FITEM, 5, -17 CM, _Y,AREA
: ASEL,  
,P51X File No.: 0801038.304 Page A-9 of A-23 Revision: I F0306-01:


V     StructuralIntegrityAssociates,   Inc.
V Structural Integrity Associates, Inc.
CM, _Y, AREA CMSEL, S, _Y CMSEL,S,_YI AATT,           3,   ,  1,       0, CMSEL, S, _Y CMDELE, Y CMDELE, Y1 I*
CM, _Y, AREA CMSEL, S, _Y CMSEL,S,_YI
  !/com, Map mesh areas FLST, 5,10,4,ORDE, 10 FITEM, 5,5 FITEM, 5, 10 FITEM, 5,28 FITEM, 5,32 FITEM, 5,-33 FITEM, 5,36 FITEM, 5,-37 FITEM, 5,42 FITEM, 5,45 FITEM, 5, -46 CM, _Y,LINE LSEL, , , ,P51X CM, Y1,LINE CMSEL,, _Y LESIZE,   Y1,   , ,15,   ,  ,  ,i 1*
: AATT, 3,
FLST, 5,10,4, ORDE, 10 FITEM, 5,3 FITEM, 5,9 FITEM, 5,25 FITEM, 5,27 FITEM, 5,31 FITEM, 5,34 FITEM, 5,-35 FITEM, 5,40 FITEM, 5, 44 FITEM, 5,47 CM, Y,LINE LSEL,   , ,  ,P51X CM, YI,LINE CMSEL,, _Y I*
1, 0,
LESIZE,       .Y1,
CMSEL, S, _Y
                    ,  ,2, ,      ,
: CMDELE, Y
1*
: CMDELE, Y1 I*
File No.: 0801038.304                           Page A-10 of A-23 Revision: I F0306-011
!/com, Map mesh areas FLST, 5,10,4,ORDE, 10 FITEM, 5,5 FITEM, 5, 10 FITEM, 5,28 FITEM, 5,32 FITEM, 5,-33 FITEM, 5,36 FITEM, 5,-37 FITEM, 5,42 FITEM, 5,45 FITEM, 5, -46 CM, _Y,LINE
: LSEL,  
,P51X CM, Y1,LINE CMSEL,, _Y
: LESIZE, Y1,,  
,15,  
,i 1*
FLST, 5,10,4, ORDE, 10 FITEM, 5,3 FITEM, 5,9 FITEM, 5,25 FITEM, 5,27 FITEM, 5,31 FITEM, 5,34 FITEM, 5,-35 FITEM, 5,40 FITEM, 5, 44 FITEM, 5,47 CM, Y,LINE
: LSEL,  
,P51X CM, YI,LINE CMSEL,, _Y I*
: LESIZE,  
.Y1,  
,2, 1*
File No.: 0801038.304 Page A-10 of A-23 Revision: I F0306-011


VFLST, Structural   IntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
5,3,4, ORDE, 3 FITEM., 5, 39 FITEM, 5, 41 FITEM, 5,43 CM, _Y, LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y LESIZE,     YI,       ,80,     ,    ,  ,  l 1*
FLST, 5,3,4, ORDE, 3 FITEM., 5, 39 FITEM, 5, 41 FITEM, 5,43 CM, _Y, LINE
FLST,5,3,4,ORDE,3 FITEM, 5,6 FITEM, 5, -7 FITEM,5,24 CM, _Y,LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y LESIZE,    Y1,    ,  ,20,    ,    ,    ,
: LSEL,  
,P51X CM, _Y1,LINE CMSEL,, _Y
: LESIZE, YI,  
,80, l
1*
1*
FLST, 5,3,4, ORDE, 3 FITEM, 5,4 FITEM, 5,8 FITEM, 5,38 CM, _Y,LINE LSEL, , , ,P51X CM, Y1,LINE CMSEL,,__Y 1*
FLST,5,3,4,ORDE,3 FITEM, 5,6 FITEM, 5, -7 FITEM,5,24 CM, _Y,LINE
LESIZE,_Y1,       ,  ,40,   ,    ,    ,  fl FLST, 5,3,4,ORDE, 3 FITEM, 5,1 FITEM, 5,22 FITEM, 5, -23 CM, _Y,LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y LESIZE,     Y1, ,   ,30,   ,    ,    ,  .
: LSEL,
FLST, 5, 6,4,ORDE, 6.
,P51X CM, _Y1,LINE CMSEL,, _Y
FITEM, 5,2 FITEM, 5,20 FileNo.: 0801038.304                               Page A-I I of A-23 Revision: 1 F0306-011
: LESIZE, Y1,
,20, 1*
FLST, 5,3,4, ORDE, 3 FITEM, 5,4 FITEM, 5,8 FITEM, 5,38 CM, _Y,LINE
: LSEL,  
,P51X CM, Y1,LINE CMSEL,,__Y 1*
LESIZE,_Y1,  
,40, fl FLST, 5,3,4,ORDE, 3 FITEM, 5,1 FITEM, 5,22 FITEM, 5, -23 CM, _Y,LINE
: LSEL,  
,P51X CM, _Y1,LINE CMSEL,, _Y
: LESIZE, Y1,,  
,30, FLST, 5, 6,4,ORDE, 6.
FITEM, 5,2 FITEM, 5,20 FileNo.: 0801038.304 Page A-I I of A-23 Revision: 1 F0306-011


0     StructuralIntegrity Associates, Inc.
0 Structural Integrity Associates, Inc.
FITEM, 5, -21 FITEM, 5,26 FITEM, 5,29 FITEM, 5, -30 CM, _Y, LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y 1*
FITEM, 5, -21 FITEM, 5,26 FITEM, 5,29 FITEM, 5, -30 CM, _Y, LINE
LESIZE,   Y1,   , ,40, , , , ,I 1*
: LSEL,  
FLST, 5, 9, 4, ORDE, 2 FITEM, 5, 11 FITEM, 5, -19 CM, Y,LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,,__Y 1*
,,P51X CM, _Y1,LINE CMSEL,, _Y 1*
LESIZE,   Y1, ,  ,20, ,  , , ,i 1*
: LESIZE, Y1,  
Meshing FLST, 5, 18,5, ORDE, 2 FITEM, 5,1 FITEM, 5, -18 SCM, _Y,AREA ASEL, , , ,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S,_Y 1*
,40,  
MSHKEY, 1 AMESH, Y1 MSHKEY, 0 i*
,I 1*
CMDELE, Y CMDELE, _Y1 CMDELE,   Y2 1*
FLST, 5, 9, 4, ORDE, 2 FITEM, 5, 11 FITEM, 5, -19 CM, Y,LINE
    !Modify the safe end ID FLST, 2, 6, 5, ORDE, 2 FITEM, 2,1 FITEM, 2, -6 ACLEAR, P51X FLST, 2, 6, 5, ORDE, 2 File No.: 0801038.304                         Page A-12 of A-23 Revision: 1 F0306-01
: LSEL,  
,P51X CM, _Y1,LINE CMSEL,,__Y 1*
: LESIZE, Y1,  
,20,  
,i 1*
Meshing FLST, 5, 18,5, ORDE, 2 FITEM, 5,1 FITEM, 5, -18 SCM, _Y,AREA
: ASEL,  
,,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S,_Y 1*
MSHKEY, 1
: AMESH, Y1 MSHKEY, 0 i*
: CMDELE, Y
CMDELE, _Y1
: CMDELE, Y2 1*
!Modify the safe end ID FLST, 2, 6, 5, ORDE, 2 FITEM, 2,1 FITEM, 2, -6 ACLEAR, P51X FLST, 2, 6, 5, ORDE, 2 File No.: 0801038.304 Page A-12 of A-23 Revision: 1 F0306-01


V     StructuralIntegrity Associates, Inc.
V Structural Integrity Associates, Inc.
FITEM, 2, 1 FITEM, 2, -6 ADELE, P51X FLST,2,9, 4,ORDE,7 FITEM, 2,9 FITEM, 2,14 FITEM, 2, -17 FITEM, 2,26 FITEM, 2, -27 FITEM, 2,30 FITEM, 2, -31 LDELE,P51X, , .1 FLST, 2,3,4,ORDE, 3 FITEM, 2,10 FITEM, 2,28 FITEM, 2,32 LDELE,P51X, , .1 FLST, 3,2,3, ORDE, 2 FITEM, 3,3 FITEM, 3,6 KGEN,2,P51X, , ,-ro2+ri2l,           ,  , ,0 FLST, 3,1, 3,ORDE, 1 FITEM, 3,2 KGEN,2,P51X, , , ,L22,         , ,0 FLST, 3, 3,3, ORDE, 3 FITEM, 3,1 FITEM, 3, -2 FITEM, 3, 4 KGEN,2,P51X, , ,tv, , , ,0 FLST, 3,2, 3, ORDE, 2 FITEM, 3, 10 FITEM, 3,-li KGEN,2,P51X, , , ,-(L3-L21),           ,  ,0 FLST, 3, 1, 3, ORDE, 1 FITEM, 3,23 KGEN,2,P51X, , ,5,       ,  , ,0 LSTR,         23,         40 FLST,2,2,4,ORDE,2 FITEM, 2,9 FITEM, 2,12 LPTN, P51X LDELE,           16, , ,i FLST, 2,4,3 FITEM, 2, 11 FITEM, 2,23 FITEM, 2,41 FileNo.: 0801038.304                             Page A-13 of A-23 Revision: I F0306-0t1
FITEM, 2, 1 FITEM, 2, -6 ADELE, P51X FLST,2,9, 4,ORDE,7 FITEM, 2,9 FITEM, 2,14 FITEM, 2, -17 FITEM, 2,26 FITEM, 2, -27 FITEM, 2,30 FITEM, 2, -31 LDELE,P51X,  
.1 FLST, 2,3,4,ORDE, 3 FITEM, 2,10 FITEM, 2,28 FITEM, 2,32 LDELE,P51X,  
.1 FLST, 3,2,3, ORDE, 2 FITEM, 3,3 FITEM, 3,6 KGEN,2,P51X,  
,,-ro2+ri2l,  
,0 FLST, 3,1, 3,ORDE, 1 FITEM, 3,2 KGEN,2,P51X,  
,L22,  
,0 FLST, 3, 3,3, ORDE, 3 FITEM, 3,1 FITEM, 3, -2 FITEM, 3, 4 KGEN,2,P51X,  
,,tv,  
,0 FLST, 3,2, 3, ORDE, 2 FITEM, 3, 10 FITEM, 3,-li KGEN,2,P51X,  
,-(L3-L21),  
,0 FLST, 3, 1, 3, ORDE, 1 FITEM, 3,23 KGEN,2,P51X,  
,5,  
,0
: LSTR, 23, 40 FLST,2,2,4,ORDE,2 FITEM, 2,9 FITEM, 2,12 LPTN, P51X
: LDELE, 16,  
,i FLST, 2,4,3 FITEM, 2, 11 FITEM, 2,23 FITEM, 2,41 FileNo.: 0801038.304 Page A-13 of A-23 Revision: I F0306-0t1


VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
FITEM, 2,12 A, P51X FLST, 2,4,3 FITEM, 2,23 FITEM, 2, 8 FITEM, 2, 9 FITEM, 2,41 A, P51X FLST,2, 4,3 FITEM, 2, 8 FITEM, 2, 7 FITEM, 2, 6 FITEM, 2, 9 A, P51X FLST, 2, 4,3 FITEM, 2,7 FITEM, 2, 5 FITEM, 2,3 FITEM, 2, 6 A, P51X FLST, 2,4,3 FITEM, 2, 10 FITEM, 2,20 FITEM, 2,23 FITEM, 2, 11 A, P51X FLST, 2,4,3 FITEM, 2,20 FITEM, 2, 4 FITEM, 2,8 FITEM, 2,23 A, P51X FLST, 2,4,3 FITEM, 2, 4 FITEM, 2,2 FITEM, 2,7 FITEM, 2, 8 A, P51X FLST, 2, 4,3 FITEM, 2,2 FITEM, 2, 1 FITEM, 2, 5 FITEM, 2,7 A, P51X FLST,5,8,5,ORDE, 4 FITEM, 5,1 FITEM, 5, -6 File No.: 0801038.304                   Page A-14 of A-23 Revision: 1 F0306-OL
FITEM, 2,12 A, P51X FLST, 2,4,3 FITEM, 2,23 FITEM, 2, 8 FITEM, 2, 9 FITEM, 2,41 A, P51X FLST,2, 4,3 FITEM, 2, 8 FITEM, 2, 7 FITEM, 2, 6 FITEM, 2, 9 A, P51X FLST, 2, 4,3 FITEM, 2,7 FITEM, 2, 5 FITEM, 2,3 FITEM, 2, 6 A, P51X FLST, 2,4,3 FITEM, 2, 10 FITEM, 2,20 FITEM, 2,23 FITEM, 2, 11 A, P51X FLST, 2,4,3 FITEM, 2,20 FITEM, 2, 4 FITEM, 2,8 FITEM, 2,23 A, P51X FLST, 2,4,3 FITEM, 2, 4 FITEM, 2,2 FITEM, 2,7 FITEM, 2, 8 A, P51X FLST, 2, 4,3 FITEM, 2,2 FITEM, 2, 1 FITEM, 2, 5 FITEM, 2,7 A, P51X FLST,5,8,5,ORDE, 4 FITEM, 5,1 FITEM, 5, -6 File No.: 0801038.304 Page A-14 of A-23 Revision: 1 F0306-OL


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
FITEM, 5, 19 FITEM, 5,-20 CM, _Y, AREA ASEL, , , ,P51X CM, _Y1,AREA CMSEL,S, Y 1*
FITEM, 5, 19 FITEM, 5,-20 CM, _Y, AREA
CMSEL,S, Y1 AATT,         i,   ,    1,             0, CMSEL,S, Y CMDELE, _Y CMDELE, Y1 1*
: ASEL,  
FLST, 5, 4,4,ORDE, 4 FITEM, 5, 15 FITEM, 5, -16 FITEM, 5,26 FITEM, 5, 28 CM, _Y,LINE LSEL, , , ,P51X CM, Y1,LINE CMSEL,,_Y i*
,P51X CM, _Y1,AREA CMSEL,S, Y
LESIZE,   YI, , ,15,   ,  ,  ,  ,i 1*
1*
FLST, 5,4,4,ORDE, 4 FITEM, 5,31 FITEM, 5,48 FITEM, 5,50 FITEM, 5,52 CM, Y,LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y 1*
CMSEL,S, Y1
LESIZE,   Y1, , ,2, ,  ,  ,  1 FLST, 5,6, 4,ORDE, 6 FITEM, 5,9 FITEM, 5,-l0 FITEM, 5, 12 FITEM, 5, 14 FITEM, 5, 30 FITEM, 5,32 CM, _Y,LINE LSEL, , , ,P51X CM, Y1,LINE FileNo.: 0801038.304                         Page A-15 of A-23 Revision: I F0306-01!
: AATT, i,
1, 0,
CMSEL,S, Y
CMDELE, _Y
: CMDELE, Y1 1*
FLST, 5, 4,4,ORDE, 4 FITEM, 5, 15 FITEM, 5, -16 FITEM, 5,26 FITEM, 5, 28 CM, _Y,LINE
: LSEL,  
,,P51X CM, Y1,LINE CMSEL,,_Y i*
: LESIZE, YI,  
,15,  
,i 1*
FLST, 5,4,4,ORDE, 4 FITEM, 5,31 FITEM, 5,48 FITEM, 5,50 FITEM, 5,52 CM, Y,LINE
: LSEL,  
,P51X CM, _Y1,LINE CMSEL,, _Y 1*
: LESIZE, Y1,  
,2, 1
FLST, 5,6, 4,ORDE, 6 FITEM, 5,9 FITEM, 5,-l0 FITEM, 5, 12 FITEM, 5, 14 FITEM, 5, 30 FITEM, 5,32 CM, _Y,LINE
: LSEL,  
,P51X CM, Y1,LINE FileNo.: 0801038.304 Page A-15 of A-23 Revision: I F0306-01!


V     StructuralIntegrity Associates, Inc.
V Structural Integrity Associates, Inc.
CMSEL,, _Y 1*
CMSEL,, _Y 1*
LESIZE,   Y1, , , 6, ,  ,  ,  ,i 1*
: LESIZE, Y1,,  
FLST, 5,3,4, ORDE, 3 FITEM, 5, 11 FITEM, 5, 17 FITEM, 5,49 CM, _Y, LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y LESIZE,   Y1, , ,12,   ,  ,  ,    ,i 1*
, 6,  
FLST, 5,3, 4,ORDE, 3 FITEM, 5,27 FITEM, 5,29 FITEM, 5,51 CM, _Y,LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,,__Y LESIZE,   Y1, , ,25,   ,  ,  ,    ,i 1*
,i 1*
FLST, 5, 8, 5, ORDE, 4 FITEM, 5,1 FITEM, 5, -6 FITEM, 5,19 FITEM, 5,-20 CM, _Y,AREA ASEL, , , ,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y 1*
FLST, 5,3,4, ORDE, 3 FITEM, 5, 11 FITEM, 5, 17 FITEM, 5,49 CM, _Y, LINE
MSHKEY, 1 AMESH, Y1 MSHKEY, 0 i*
: LSEL,  
CMDELE, Y CMDELE, _Y1 CMDELE,   Y2 1*
,,P51X CM, _Y1,LINE CMSEL,, _Y
FLST, 2,2,5, ORDE, 2 FileNo.: 0801038.304                         Page A-16 of A-23 Revision: 1 F0306-01
: LESIZE, Y1,  
,12,  
,i 1*
FLST, 5,3, 4,ORDE, 3 FITEM, 5,27 FITEM, 5,29 FITEM, 5,51 CM, _Y,LINE
: LSEL,  
,P51X CM, _Y1,LINE CMSEL,,__Y
: LESIZE, Y1,,  
,25,  
,i 1*
FLST, 5, 8, 5, ORDE, 4 FITEM, 5,1 FITEM, 5, -6 FITEM, 5,19 FITEM, 5,-20 CM, _Y,AREA
: ASEL,  
,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y 1*
MSHKEY, 1
: AMESH, Y1 MSHKEY, 0 i*
: CMDELE, Y
CMDELE, _Y1
: CMDELE, Y2 1*
FLST, 2,2,5, ORDE, 2 FileNo.: 0801038.304 Page A-16 of A-23 Revision: 1 F0306-01


V StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
FITEM, 2,17 FITEM, 2, -18 ACLEAR,P51X csys, 0 k, 51,62/2,0,0 k, 52,62/2,60,0 LSTR,         51,   52 FLST, 2,2,5, ORDE, 2 FITEM, 2,17 FITEM, 2, -18 ADELE, P5IX iplo FLST, 2,4,4, ORDE, 4 FITEM, 2,39 FITEM, 2,41 FITEM, 2,43 FITEM, 2,53 LPTN, PSIX FLST, 2,2,4, ORDE, 2 FITEM, 2,60 FITEM, 2, -61 LDELE,P51X, , .1 FLST, 2,4,4 FITEM, 2,54 FITEM, 2, 62 FITEM, 2,55 FITEM, 2,44 AL, P51X FLST, 2,4,4 FITEM, 2,55 FITEM, 2,63 FITEM, 2,58 FITEM, 2,45 AL, P51X FLST,2,4,4 FITEM, 2,63 FITEM, 2,56 FITEM, 2,57 FITEM, 2,46 AL, P51X FLST, 2,4,4 FITEM, 2,47 FITEM, 2,59 FITEM, 2,57 FITEM, 2,62 AL, PSIX File No.: 0801038.304                   Page A-17 of A-23 Revision: 1 F0306-01
FITEM, 2,17 FITEM, 2, -18 ACLEAR,P51X csys, 0 k, 51,62/2,0,0 k,
52,62/2,60,0
: LSTR, 51, 52 FLST, 2,2,5, ORDE, 2 FITEM, 2,17 FITEM, 2, -18 ADELE, P5IX iplo FLST, 2,4,4, ORDE, 4 FITEM, 2,39 FITEM, 2,41 FITEM, 2,43 FITEM, 2,53 LPTN, PSIX FLST, 2,2,4, ORDE, 2 FITEM, 2,60 FITEM, 2, -61 LDELE,P51X,  
.1 FLST, 2,4,4 FITEM, 2,54 FITEM, 2, 62 FITEM, 2,55 FITEM, 2,44 AL, P51X FLST, 2,4,4 FITEM, 2,55 FITEM, 2,63 FITEM, 2,58 FITEM, 2,45 AL, P51X FLST,2,4,4 FITEM, 2,63 FITEM, 2,56 FITEM, 2,57 FITEM, 2,46 AL, P51X FLST, 2,4,4 FITEM, 2,47 FITEM, 2,59 FITEM, 2,57 FITEM, 2,62 AL, PSIX File No.: 0801038.304 Page A-17 of A-23 Revision: 1 F0306-01


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
CM, _Y, AREA ASEL,   ,  ,  ,        18 CM, _Y1,AREA CMSEL, S, _Y 1*
CM, _Y, AREA
CMSEL,S, Y1 AATT,           2,   ,    1,        0, CMSEL, S, _Y CMDELE, Y CMDELE,, Y1 FLST, 5,2,5, ORDE, 2 FITEM, 5, 17 FITEM, 5,22 CM, _Y, AREA ASEL, , , ,P51X CM, _Y1,AREA CMSEL,S, _Y 1*
: ASEL, 18 CM, _Y1,AREA CMSEL, S, _Y 1*
CMSEL,S, Y1 AATT,            3,  r    1,        0, CMSEL, S, _Y CMDELE, _Y CMDELE, __Y CM, Y, AREA ASEL, . . .            21 CM, _Y1,AREA CMSEL, S, Y CMSEL,S, Y1 AATT,            4,  j    1,        0, CMSEL, S, _Y CMDELE, Y CMDELE, _YI 1*
CMSEL,S, Y1
FLST, 5,3,4,ORDE, 3 FITEM, 5,54 FITEM, 5, -55 FITEM, 5,58 CM, _Y,LINE LSEL, , , ,P51X CM, Y1,LINE CMSEL,,__Y LESIZE,   Y1,   ,  ,8,   ,    , , ,i File No.: 0801038.304                         Page A- 18 of A-23 Revision: 1 F0306-011
: AATT, 2,
1, CMSEL, S, _Y
: CMDELE, Y
CMDELE,, Y1 FLST, 5,2,5, ORDE, 2 FITEM, 5, 17 FITEM, 5,22 CM, _Y, AREA
: ASEL,  
,P51X CM, _Y1,AREA CMSEL,S, _Y 1*
0, CMSEL,S, Y1
: AATT, CMSEL, S, _Y CMDELE, _Y CMDELE, __Y CM, Y, AREA
: ASEL, CM, _Y1,AREA CMSEL, S, Y
CMSEL,S, Y1
: AATT, CMSEL, S, _Y
: CMDELE, Y
CMDELE, _YI 1*
3, r 1,
21 4,
j 1,
0, 0,
FLST, 5,3,4,ORDE, 3 FITEM, 5,54 FITEM, 5, -55 FITEM, 5,58 CM, _Y,LINE
: LSEL,  
,,P51X CM, Y1,LINE CMSEL,,__Y
: LESIZE, Y1,  
,8,  
,i File No.: 0801038.304 Revision: 1 Page A-18 of A-23 F0306-011


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
FLST, 5,3,4,ORDE, 3 FITEM, 5, 56 FITEM, 5,-57 FITEM, 5,59 CM, _Y,LINE LSEL, , , ,P51X CM, _Y1,LINE CMSEL,, _Y 1*
FLST, 5,3,4,ORDE, 3 FITEM, 5, 56 FITEM, 5,-57 FITEM, 5,59 CM, _Y,LINE
LESIZE,   YI, ,  ,40, , ,  , ,i FLST, 5,2,5, ORDE, 2 FITEM, 5,17 FITEM, 5,-18 CM, Y,AREA ASEL, , , ,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, Y MSHKEY, 1 AMESH, Y1 MSHKEY, 0 L*
: LSEL,  
CMDELE, Y CMDELE, _Y1 CMDELE,   Y2 I*
,P51X CM, _Y1,LINE CMSEL,, _Y 1*
FLST, 5,2,5, ORDE, 2 FITEM, 5,21 FITEM, 5, -22 CM, Y,AREA ASEL, , , ,P51X CM, Y1,AREA CHKMSH, 'AREA' CMSEL,S, Y i*
: LESIZE, YI,  
MSHKEY, 1 AMESH, Y1 MSHKEY, 0 CMDELE, Y CMDELE, Y1 CMDELE, Y2 1*
,40,  
File No.: 0801038.304                         Page A-19 of A-23 Revision: 1 F0306-01
,i FLST, 5,2,5, ORDE, 2 FITEM, 5,17 FITEM, 5,-18 CM, Y,AREA
: ASEL,  
,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, Y
MSHKEY, 1
: AMESH, Y1 MSHKEY, 0 L*
: CMDELE, Y
CMDELE, _Y1
: CMDELE, Y2 I*
FLST, 5,2,5, ORDE, 2 FITEM, 5,21 FITEM, 5, -22 CM, Y,AREA
: ASEL,  
,P51X CM, Y1,AREA CHKMSH, 'AREA' CMSEL,S, Y
i*
MSHKEY, 1
: AMESH, Y1 MSHKEY, 0 CMDELE, Y
: CMDELE, Y1
: CMDELE, Y2 1*
File No.: 0801038.304 Page A-19 of A-23 Revision: 1 F0306-01


VStructuralIntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
    !Simulating Butter FLST, 2,2,5,ORDE, 2 FITEM,2,9 FITEM, 2, -10 ACLEAR, P51X FLST, 2,2,5, ORDE, 2 FITEM, 2,9 FITEM, 2, -10 ADELE, P51X KGEN,2,15,     ,  , ,11/16,   , ,0 KGEN,2,44,     ,  , ,-0.25,   , ,0 KGEN,2,14,     ,  , ,11/16-1.375*tan(7.5) , 0 KGEN,2,46,     ,  , ,-0.25,   , ,0 FLST, 2, 3, 4,ORDE, 3 FITEM, 2,2 FITEM, 2,20 FITEM, 2, -21 LDELE, P51X LSTR,         21,           44 LSTR,         44,           45 LSTR,         45,           15 LSTR,         17,           46 LSTR,         46,           47 LSTR,         47,           14 LSTR,         46,           44 LSTR,         45,           47 LSTR,         13,           16 FLST, 3,2, 3,ORDE, 2 FITEM, 3,46 FITEM, 3,-47 KGEN,2,P51X, , ,-0.25,         ,  ,0 LSTR,         48,           46 LSTR,         49,           47 FLST, 2,3,4,ORDE, 3 FITEM, 2,61 FITEM, 2,64 FITEM, 2, -65 LPTN, P51X FLST, 2,2,4,ORDE, 2 FITEM, 2,70 FITEM, 2, -71 LDELE,P51X, , .1 FLST, 2,4,4 FITEM, 2, 67 FITEM, 2,39 File No.: 0801038.304                             Page A-20 of A-23 Revision: 1 F0306-01
!Simulating Butter FLST, 2,2,5,ORDE, 2 FITEM,2,9 FITEM, 2, -10 ACLEAR, P51X FLST, 2,2,5, ORDE, 2 FITEM, 2,9 FITEM, 2, -10 ADELE, P51X KGEN,2,15,  
,11/16,  
,0 KGEN,2,44,  
,-0.25,  
,0 KGEN,2,14,  
,,11/16-1.375*tan(7.5) 0 KGEN,2,46,  
,-0.25,  
,0 FLST, 2, 3, 4,ORDE, 3 FITEM, 2,2 FITEM, 2,20 FITEM, 2, -21 LDELE, P51X
: LSTR, 21, 44
: LSTR, 44, 45
: LSTR, 45, 15
: LSTR, 17, 46
: LSTR, 46, 47
: LSTR, 47, 14
: LSTR, 46, 44
: LSTR, 45, 47
: LSTR, 13, 16 FLST, 3,2, 3,ORDE, 2 FITEM, 3,46 FITEM, 3,-47 KGEN,2,P51X,  
,,-0.25,  
,0
: LSTR, 48, 46
: LSTR, 49, 47 FLST, 2,3,4,ORDE, 3 FITEM, 2,61 FITEM, 2,64 FITEM, 2, -65 LPTN, P51X FLST, 2,2,4,ORDE, 2 FITEM, 2,70 FITEM, 2, -71 LDELE,P51X,  
.1 FLST, 2,4,4 FITEM, 2, 67 FITEM, 2,39 File No.: 0801038.304 Page A-20 of A-23 Revision: 1 F0306-01


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
FITEM, 2,68 FITEM, 2, 3 AL, P51X FLST, 2,4,4 FITEM, 2,39 FITEM, 2, 5 FITEM, 2, 2 FITEM, 2,53 AL, P51X FLST, 2,4,4 FITEM, 2,20 FITEM, 2, 60 FITEM, 2,53 FITEM, 2, 41 AL, P51X FLST, 2,4,4 FITEM, 2,72 FITEM, 2,68 FITEM, 2,69 FITEM, 2,41 AL, P51X FLST, 2,4,4 FITEM, 2,21 FITEM, 2,60 FITEM, 2,36 FITEM, 2,43 AL, P51X FLST, 2,4,4 FITEM, 2,66 FITEM, 2,69 FITEM, 2,35 FITEM, 2,43 AL, P51X CM, _Y, AREA ASEL, , , ,          10 CM, Y1,AREA CMSEL, S, _Y 1*
FITEM, 2,68 FITEM, 2, 3 AL, P51X FLST, 2,4,4 FITEM, 2,39 FITEM, 2, 5 FITEM, 2, 2 FITEM, 2,53 AL, P51X FLST, 2,4,4 FITEM, 2,20 FITEM, 2, 60 FITEM, 2,53 FITEM, 2, 41 AL, P51X FLST, 2,4,4 FITEM, 2,72 FITEM, 2,68 FITEM, 2,69 FITEM, 2,41 AL, P51X FLST, 2,4,4 FITEM, 2,21 FITEM, 2,60 FITEM, 2,36 FITEM, 2,43 AL, P51X FLST, 2,4,4 FITEM, 2,66 FITEM, 2,69 FITEM, 2,35 FITEM, 2,43 AL, P51X CM, _Y, AREA
CMSEL,S, Y1 AATT,           2, ,    1,       0, CMSEL, S, _Y CMDELE, Y CMDELE, Y1 1*
: ASEL, 10 CM, Y1,AREA CMSEL, S, _Y 1*
FLST, 5,3,5, ORDE, 3 FITEM, 5, 9 FileNo.: 0801038.304                         Page A-21 of A-23 Revision: 1 F0306-011
CMSEL,S, Y1
: AATT, 2,
1, 0,
CMSEL, S, _Y
: CMDELE, Y
: CMDELE, Y1 1*
FLST, 5,3,5, ORDE, 3 FITEM, 5, 9 FileNo.: 0801038.304 Page A-21 of A-23 Revision: 1 F0306-011


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
FITEM, 5,23 FITEM, 5,-24 CM, Y, AREA ASEL, , , ,P51X CM, Y1,AREA CMSEL,S, _Y 1*
FITEM, 5,23 FITEM, 5,-24 CM, Y, AREA
CMSEL,S, __Y AATT,           3,   ,  1,       0, CMSEL,S, Y CMDELE, Y CMDELE, _Y1 FLST, 5,2, 5, ORDE, 2 FITEM, 5,25 FITEM, 5, -26 CM, Y,AREA ASEL, , , ,P51X CM, _Y1,AREA CMSEL,S, Y 1,
: ASEL,  
CMSEL,S,   _YI AATT,           i,   ,  i,       0, CMSEL,S,   _Y CMDELE,     Y CMDELE,     Y1 1*
,P51X CM, Y1,AREA CMSEL,S, _Y 1*
FLST, 5,3,4,ORDE, 3 FITEM, 5,2 FITEM, 5,39 FITEM, 5,67 CM, Y,LINE LSEL, , , ,P51X CM, Y1,LINE CMSEL,, _Y i*
CMSEL,S, __Y
LESIZE,     YI, ,  ,10, ,  , ,
: AATT, 3,
FLST, 5, 6, 4,ORDE, 6 FITEM, 5,20 FITEM, 5,-21 FITEM, 5,41 FITEM, 5,43 FITEM, 5,66 FITEM, 5,72 CM, Y,LINE LSEL, , , ,P51X File No.: 0801038.304                         Page A-22 of A-23 Revision: 1 F0306-O.
1, 0,
CMSEL,S, Y
: CMDELE, Y
CMDELE, _Y1 FLST, 5,2, 5, ORDE, 2 FITEM, 5,25 FITEM, 5, -26 CM, Y,AREA
: ASEL,  
,P51X CM, _Y1,AREA CMSEL,S, Y
1, CMSEL,S, _YI
: AATT, i,
i, 0,
CMSEL,S, _Y
: CMDELE, Y
: CMDELE, Y1 1*
FLST, 5,3,4,ORDE, 3 FITEM, 5,2 FITEM, 5,39 FITEM, 5,67 CM, Y,LINE
: LSEL,  
,P51X CM, Y1,LINE CMSEL,, _Y i*
: LESIZE, YI,  
,10, FLST, 5, 6, 4,ORDE, 6 FITEM, 5,20 FITEM, 5,-21 FITEM, 5,41 FITEM, 5,43 FITEM, 5,66 FITEM, 5,72 CM, Y,LINE
: LSEL,  
,,P51X File No.: 0801038.304 Page A-22 of A-23 Revision: 1 F0306-O.


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
CM, _Y1, LINE CMSEL, , _Y LESIZE,   Y1,   , ,2, ,  ,  , ,i 1*
CM, _Y1, LINE CMSEL,, _Y
FLST, 5, 2, 5, ORDE, 2 FITEM,5, 9 FITEM, 5,-i0 CM, _Y,AREA ASEL, , , ,P51X CM, Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y 1*
: LESIZE, Y1,,  
MSHKEY,1 AMESH, _Y1 MSHKEY, 0 CMDELE,1Y CMDELE, Y1 CMDELE, _Y2 I*
,2,  
FLST, 5,4,5, ORDE, 2 FITEM, 5,23 FITEM, 5, -26 CM, _Y,AREA ASEL, , , ,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y MSHKEY, 1 AMESH, Y1 MSHKEY, 0 1*
,i 1*
CMDELE, Y CMDELE, _YI CMDELE,   Y2 1*
FLST, 5, 2, 5, ORDE, 2 FITEM,5, 9 FITEM, 5,-i0 CM, _Y,AREA
save finish File No.: 0801038.304                         Page A-23 of A-23 Revision: 1 F0306-01,
: ASEL,  
,P51X CM, Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y 1*
MSHKEY,1 AMESH, _Y1 MSHKEY, 0 CMDELE,1Y
: CMDELE, Y1 CMDELE, _Y2 I*
FLST, 5,4,5, ORDE, 2 FITEM, 5,23 FITEM, 5, -26 CM, _Y,AREA
: ASEL,  
,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y MSHKEY, 1
: AMESH, Y1 MSHKEY, 0 1*
: CMDELE, Y
CMDELE, _YI
: CMDELE, Y2 1*
save finish File No.: 0801038.304 Page A-23 of A-23 Revision: 1 F0306-01,


StructuralIntegrityAssociates, Inc.                 File No.: 0801038.305 CALCULATION PACKAGE                                 Project No.: 0801038 Quality Program Z Nuclear   [] Commercial PROJECT NAME:
Structural Integrity Associates, Inc.
File No.: 0801038.305 CALCULATION PACKAGE Project No.: 0801038 Quality Program Z Nuclear [] Commercial PROJECT NAME:
VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:
VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:
10163217 Amendment 5 CLIENT:                                             PLANT:
10163217 Amendment 5 CLIENT:
Entergy Nuclear Operations, Inc                   Vermont Yankee Nuclear Power Station CALCULATION TITLE:
PLANT:
Stress Analysis of Reactor Recirculation Outlet Nozzle Project Manager           Preparer(s) &
Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:
Document       Affected         Revision Description             Approval               Checker(s)
Stress Analysis of Reactor Recirculation Outlet Nozzle Project Manager Preparer(s) &
Revision       Pages                                       Signature & Date         Signatures & Date 01             - 16             Initial issue.                               Preparer:
Document Affected Revision Description Approval Checker(s)
Gary L. Stevens Computer Files                                       01/07/09             Tyler Novotny 01/07/09 Checker:
Revision Pages Signature & Date Signatures & Date 01  
R. D. Dixon 01/07/09 1         1-9, 11, 15     Revised per summary                               Preparer:
- 16 Initial issue.
Preparer:
Gary L. Stevens Computer Files 01/07/09 Tyler Novotny 01/07/09 Checker:
R. D. Dixon 01/07/09 1
1-9, 11, 15 Revised per summary Preparer:
contained in Section 1.1.
contained in Section 1.1.
Changes are marked with revision bars" in right-         0       9           TlrDNnt hand margin.                 03/09/09             Tyler D. Novotny 03/09/09 Checker:
Changes are marked with revision bars" in right-0 9
TlrDNnt hand margin.
03/09/09 Tyler D. Novotny 03/09/09 Checker:
Tim D. Gilman 03/09/09 Page 1 of 16 F0306-OIRO
Tim D. Gilman 03/09/09 Page 1 of 16 F0306-OIRO


VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
Table of Contents 1.0   OB JEC TIV E .................................................................................................................................           3 1.1   Changes Made in Revision 1 of this Calculation ...........................................................                                         3 2.0 METHODOLOGY ...............................................................................................................                               3 3.0 ASSUMPTIONS / DESIGN INPUTS .....................................................................................                                         4 4.0 CA LCU LA TION S ........................................................................................................................                 4 4.1   Finite Element Unit Pressure Stress Analysis .................................................................                                     4 4.2   Thermal Transient Stress Analysis ..................................................................................                               4 4.3   Determining Critical Stress Paths ..................................................................................                               5 4.4   Stress C alculation ...........................................................................................................                 . .6 4.5   Piping L oads ...............................................................................................................                       7 5.0 RESULTS OF ANALYSIS .....................................................................................................                                 8 6.0 REFEREN C E S .............................................................................................................................               9 List of Tables Table 1: Pressure Stress Intensity Results (1,000 psi) ......................................................................                                 .7 Table 2: Stresses Under Unit Pressure Load, psi ..................................                                                                           10 Table 3: Example Thermal Stress Result Output, psi .........................................................................                                 11 List of Figures Figure 1. RO Nozzle Internal Pressure Distribution ......................................................................                                   12 Figure 2. RO Nozzle Pressure Cap Load & Boundary Condition .................................................                                                 13 Figure 3. RO Nozzle Vessel Wall Boundary Condition ...............................................................                                           14 Figure 4. Safe End Critical Thermal Stress Intensity Location ..........................................................                                     15 Figure 5. Nozzle Blend Radius Limiting Pressure Stress Intensity Location .................................                                                 16 Figure 6. Limiting Stress Paths .....................................................................................................                       16 FileNo.: 0801038.305                                                                                                                                   Page 2 of 16 Revision: 1 F0306-OIRO
Table of Contents 1.0 O B JE C T IV E.................................................................................................................................
3 1.1 Changes Made in Revision 1 of this Calculation...........................................................
3 2.0 METHODOLOGY...............................................................................................................
3 3.0 ASSUMPTIONS / DESIGN INPUTS.....................................................................................
4 4.0 C A L C U L A T IO N S........................................................................................................................
4 4.1 Finite Element Unit Pressure Stress Analysis.................................................................
4 4.2 Thermal Transient Stress Analysis..................................................................................
4 4.3 Determining Critical Stress Paths..................................................................................
5 4.4 Stress C alculation...........................................................................................................  
.. 6 4.5 Piping L oads...............................................................................................................
7 5.0 RESULTS OF ANALYSIS.....................................................................................................
8 6.0 R E FE R E N C E S.............................................................................................................................
9 List of Tables Table 1: Pressure Stress Intensity Results (1,000 psi)......................................................................  
.7 Table 2: Stresses Under Unit Pressure Load, psi..................................
10 Table 3: Example Thermal Stress Result Output, psi.........................................................................
11 List of Figures Figure 1. RO Nozzle Internal Pressure Distribution......................................................................
12 Figure 2. RO Nozzle Pressure Cap Load & Boundary Condition.................................................
13 Figure 3. RO Nozzle Vessel Wall Boundary Condition...............................................................
14 Figure 4. Safe End Critical Thermal Stress Intensity Location..........................................................
15 Figure 5. Nozzle Blend Radius Limiting Pressure Stress Intensity Location.................................
16 Figure 6. Limiting Stress Paths.....................................................................................................
16 FileNo.: 0801038.305 Page 2 of 16 Revision: 1 F0306-OIRO


1.0     OBJECTIVE The objective of this calculation package is to obtain stress distributions for the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at the Vermont Yankee Nuclear Power Station.
1.0 OBJECTIVE The objective of this calculation package is to obtain stress distributions for the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at the Vermont Yankee Nuclear Power Station.
ANSYS [1] thermal transient and pressure stress analyses are performed, along with calculation of stresses due to attached piping loads. The stress results will be used for a subsequent ASME Code, Section III NB-3200 [2] fatigue usage calculation.
ANSYS [1] thermal transient and pressure stress analyses are performed, along with calculation of stresses due to attached piping loads. The stress results will be used for a subsequent ASME Code, Section III NB-3200 [2] fatigue usage calculation.
1.1   Changes Made in Revision 1 of this Calculation Description of changes made in Revision 1 of this calculation:
1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision 1 of this calculation:
: a. Transient 9 described in Section 4.3 was changed to more precisely match the Green's Function analysis. This also required modification of the input files VY_RONTRAN9-T.INP and VY RON TRAN9-S.INP.
: a. Transient 9 described in Section 4.3 was changed to more precisely match the Green's Function analysis. This also required modification of the input files VY_RONTRAN9-T.INP and VY RON TRAN9-S.INP.
: b. The input files VY_RON_TRAN2-T.INP and VY_RONTRAN2-S.INP were modified to include a finer time step around 601 seconds.
: b. The input files VY_RON_TRAN2-T.INP and VY_RONTRAN2-S.INP were modified to include a finer time step around 601 seconds.
Line 868: Line 1,982:
: e. Figure 4 was revised because Transient 9, which produced Figure 4, was modified.
: e. Figure 4 was revised because Transient 9, which produced Figure 4, was modified.
: f. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.
: f. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.
2.0     METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
[3]. A previously developed finite element model (FEM) [3] of the RO nozzle is used to perform thermal and pressure stress analyses using ANSYS [1]. A thermal transient analysis is performed for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads. For these loads, unit load analyses (based on finite element analysis for pressure and manual calculations for attached piping loads) are performed. All six components of the stress tensor are determined in the stress calculations.
[3]. A previously developed finite element model (FEM) [3] of the RO nozzle is used to perform thermal and pressure stress analyses using ANSYS [1]. A thermal transient analysis is performed for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads. For these loads, unit load analyses (based on finite element analysis for pressure and manual calculations for attached piping loads) are performed. All six components of the stress tensor are determined in the stress calculations.
The fatigue usage calculation and environmental fatigue usage analysis will be performed in a separate calculation package. That subsequent calculation will utilize the thermal and pressure stresses determined in this calculation, along with stresses due to attached piping loads provided in Tables 4 and 5 of Reference [3]. The stresses due to pressure and the attached piping loads will be scaled based on the temperature and pressure magnitudes during each individual transient, and the location being analyzed. The appropriate nozzle blend radius effects factor will also be applied to the total stresses for the nozzle blend radius location.
The fatigue usage calculation and environmental fatigue usage analysis will be performed in a separate calculation package. That subsequent calculation will utilize the thermal and pressure stresses determined in this calculation, along with stresses due to attached piping loads provided in Tables 4 and 5 of Reference [3]. The stresses due to pressure and the attached piping loads will be scaled based on the temperature and pressure magnitudes during each individual transient, and the location being analyzed. The appropriate nozzle blend radius effects factor will also be applied to the total stresses for the nozzle blend radius location.
FileNo.: 0801038.305                                                                                 Page 3 of 16 Revision: 1 F0306-O1RO
FileNo.: 0801038.305 Page 3 of 16 Revision: 1 F0306-O1RO


3.0       ASSUMPTIONS / DESIGN INPUTS Assumptions and design inputs were previously established in Section 3.0 of the Reference [3]
3.0 ASSUMPTIONS / DESIGN INPUTS Assumptions and design inputs were previously established in Section 3.0 of the Reference [3]
calculation. Assumption 3.1.3 of Reference [3] was verified in this calculation package by plotting the stress components of each transient in ANSYS. If the stress components plot did not contain a step change at the end of the transient, the steady state portion, the steady state time step assumed was determined to be adequate.
calculation. Assumption 3.1.3 of Reference [3] was verified in this calculation package by plotting the stress components of each transient in ANSYS. If the stress components plot did not contain a step change at the end of the transient, the steady state portion, the steady state time step assumed was determined to be adequate.
4.0 CALCULATIONS 4.1 Finite Element Unit Pressure Stress Analysis A uniform pressure of 1,000 psi was applied to the FEM along the inside surface of the RO nozzle and the RPV wall (Figure 1). A pressure load of 1,000 psi was used because it is easily scaled up or down to account for different pressures that occur during transients. In addition, a membrane stress "cap load" was applied to the modeled end of the piping attached to the RO nozzle safe end. This membrane stress was calculated as follows:
4.0 CALCULATIONS 4.1 Finite Element Unit Pressure Stress Analysis A uniform pressure of 1,000 psi was applied to the FEM along the inside surface of the RO nozzle and the RPV wall (Figure 1). A pressure load of 1,000 psi was used because it is easily scaled up or down to account for different pressures that occur during transients. In addition, a membrane stress "cap load" was applied to the modeled end of the piping attached to the RO nozzle safe end. This membrane stress was calculated as follows:
PD.
PD.
PDi 2 P
P PDi 2 Pcap =
Pcap =   2     2 where:
2 2
where:
P = Pressure = 1,000 psi unit load Di= Inner Diameter at end of model = 25.9375 in Do = Outer Diameter at end of model = 28.375 in Therefore, the membrane stress is 5,082 psi. The calculated value is given a negative sign in order for it to exert tension on the piping end of the model. The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, input file RONVY.INP]. The ANSYS input file VY RON P.INP contains the pressure loading. Figure 1 shows the applied 1,000 psi internal pressure distribution. At the vessel wall, a symmetric boundary condition is applied. At the piping end of the model, axial displacement is coupled to simulate the effect of the attached piping that is not modeled. Figure 2 and Figure 3 show the boundary conditions.
P = Pressure = 1,000 psi unit load Di= Inner Diameter at end of model = 25.9375 in Do = Outer Diameter at end of model = 28.375 in Therefore, the membrane stress is 5,082 psi. The calculated value is given a negative sign in order for it to exert tension on the piping end of the model. The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, input file RONVY.INP]. The ANSYS input file VY RON P.INP contains the pressure loading. Figure 1 shows the applied 1,000 psi internal pressure distribution. At the vessel wall, a symmetric boundary condition is applied. At the piping end of the model, axial displacement is coupled to simulate the effect of the attached piping that is not modeled. Figure 2 and Figure 3 show the boundary conditions.
4.2 Thermal Transient Stress Analysis The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, file RONVY.INP], and is used as input to the files in which the thermal transient and pressure stress analyses are performed.
4.2 Thermal Transient Stress Analysis The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, file RONVY.INP], and is used as input to the files in which the thermal transient and pressure stress analyses are performed.
For the thermal transient ANSYS analyses, previously defined thermal transients [3, Table 1] are evaluated, applying heat transfer coefficients [3, Table 2], as appropriate, based on the flow rates for each individual transient.
For the thermal transient ANSYS analyses, previously defined thermal transients [3, Table 1 ] are evaluated, applying heat transfer coefficients [3, Table 2], as appropriate, based on the flow rates for each individual transient.
Each thermal transient is evaluated in ANSYS to determine the resulting temperature distributions.
Each thermal transient is evaluated in ANSYS to determine the resulting temperature distributions.
The thermal results are used as input for the stress analysis for each transient. The boundary FileNo.: 0801038.305                                                                                 Page 4 of 16 Revision: 1 F0306-O1RO
The thermal results are used as input for the stress analysis for each transient. The boundary FileNo.: 0801038.305 Page 4 of 16 Revision: 1 F0306-O1RO


StructuralIntegrityAssociates, Inc.
Structural Integrity Associates, Inc.
conditions used for the pressure load case were also applied to the thermal stress cases. Figure 2 and Figure 3 show the application of these boundary conditions.
conditions used for the pressure load case were also applied to the thermal stress cases. Figure 2 and Figure 3 show the application of these boundary conditions.
All ANSYS input files for the thermal analyses, as listed below, are saved in the project computer files:
All ANSYS input files for the thermal analyses, as listed below, are saved in the project computer files:
RON VYINP: Geometry and material properties VYRON TRAN]-T.INP, VYRONTRAN]-S.INP: Transient 1, thermal and stress analyses VYRONTRAN2-TINP, VY_RONTRAN2-S.INP: Transient 2, thermal and stress analyses VY_RON TRAN3-T.INP, VYRONTRAN3-S.INP: Transient 3, thermal and stress analyses VYRONTRAN4-T.INP, VY RONTRAN4-S.INP: Transient 4, thermal and stress analyses VYRONTRAN5-T.INP, VYRONTRAN5-S.INP: Transient 5, thermal and stress analyses VY RON TRAN6-T.INP, VY RON TRAN6-S.INP: Transient 6, thermal and stress analyses VYRONTRAN7-T.INP, VYRONTRAN7-S.INP: Transient 7, thermal and stress analyses VYRONTRAN8-T.INP, VY RON TRAN8-S.INP: Transient 8, thermal and stress analyses VYRONTRAN9-TINP, VYRONTRAN9-S.INP: Transient 9, thermal and stress analyses VYRONTRANIO-T.INP, VY RON TRANIO-S.INP: Transient 10, thermal and stress analyses VYRON_TRAN]]-T.INP, VYRONTRAN1-US.INP: Transient 11, thermal and stress analyses VYRON_TRAN12-T.INP, VYRONTRAN12-S.INP: Transient 12, thermal and stress analyses 4.3 Determining Critical Stress Paths The thermal transient that is to be used in determining the critical stress path at the safe end was determined by the most severe temperature difference over the shortest amount of time. This transient, Transient 9, is intended to represent the worst case thermal transient. This occurs during the Improper Startup cycle per Reference [3, Table 1]. The thermal transient conditions are:
RON VYINP: Geometry and material properties VYRON TRAN]-T.INP, VYRONTRAN]-S.INP: Transient 1, thermal and stress analyses VYRONTRAN2-TINP, VY_RONTRAN2-S.INP: Transient 2, thermal and stress analyses VY_RON TRAN3-T.INP, VYRONTRAN3-S.INP: Transient 3, thermal and stress analyses VYRONTRAN4-T.INP, VY RONTRAN4-S.INP: Transient 4, thermal and stress analyses VYRONTRAN5-T.INP, VYRONTRAN5-S.INP: Transient 5, thermal and stress analyses VY RON TRAN6-T.INP, VY RON TRAN6-S.INP: Transient 6, thermal and stress analyses VYRONTRAN7-T.INP, VYRONTRAN7-S.INP: Transient 7, thermal and stress analyses VYRONTRAN8-T.INP, VY RON TRAN8-S.INP: Transient 8, thermal and stress analyses VYRONTRAN9-TINP, VYRONTRAN9-S.INP: Transient 9, thermal and stress analyses VYRONTRANIO-T.INP, VY RON TRANIO-S.INP: Transient 10, thermal and stress analyses VYRON_TRAN))-T.INP, VYRONTRAN1-US.INP: Transient 11, thermal and stress analyses VYRON_TRAN12-T.INP, VYRONTRAN12-S.INP: Transient 12, thermal and stress analyses 4.3 Determining Critical Stress Paths The thermal transient that is to be used in determining the critical stress path at the safe end was determined by the most severe temperature difference over the shortest amount of time. This transient, Transient 9, is intended to represent the worst case thermal transient. This occurs during the Improper Startup cycle per Reference [3, Table 1]. The thermal transient conditions are:
* 12% flow rate heat transfer coefficients.
12% flow rate heat transfer coefficients.
Thermal shock from 526&deg;F to 130'F along the inside surface of the nozzle safe end and piping and a blend radius and lower vessel thermal shock from 526 0F to 2680 F.
Thermal shock from 526&deg;F to 130'F along the inside surface of the nozzle safe end and piping and a blend radius and lower vessel thermal shock from 5260F to 2680F.
* Constant temperatures from previous step for 26 seconds
* Constant temperatures from previous step for 26 seconds
* Thermal shock from 130'F to 526&deg;F along the inside surface of the nozzle safe end and piping and a blend radius and lower vessel thermal shock from 268'F to 526&deg;F.
* Thermal shock from 130'F to 526&deg;F along the inside surface of the nozzle safe end and piping and a blend radius and lower vessel thermal shock from 268'F to 526&deg;F.
* Steady state temperature conditions following thermal shocks.
Steady state temperature conditions following thermal shocks.
* Constant temperature of 120'F on the outside surface of the model.
* Constant temperature of 120'F on the outside surface of the model.
The ANSYS input files for the analysis, as listed below, are saved in the project computer, files:
The ANSYS input files for the analysis, as listed below, are saved in the project computer, files:
RONVYINP. Geometry and material properties VYRONTR4N9-T.INP, VYRONTRAN9-S.INP:                   Thermal and stress analysis for the worst case transient for the safe end An interactive review of the worst case thenral stress results (which are controlling for the safe end) showed the critical location in the model to be at Node 6395. The location of Node 6395 is shown in FileNo.: 0801038.305                                                                                 Page 5 of 16 Revision: 1 F0306-O1RO
RONVYINP. Geometry and material properties VYRONTR4N9-T.INP, VYRONTRAN9-S.INP: Thermal and stress analysis for the worst case transient for the safe end An interactive review of the worst case thenral stress results (which are controlling for the safe end) showed the critical location in the model to be at Node 6395. The location of Node 6395 is shown in FileNo.: 0801038.305 Page 5 of 16 Revision: 1 F0306-O1RO


Figure 4. This location was selected since it possessed the highest stress intensity during the worst case thermal transient. This is the same location evaluated in Reference [4].
Figure 4. This location was selected since it possessed the highest stress intensity during the worst case thermal transient. This is the same location evaluated in Reference [4].
Line 904: Line 2,019:
The pressure stress intensities for the safe end and blend radius paths were extracted using the ANSYS file VY/RONP.INP. This produced one file, ROPRESSURE.lin, that contains results of the critical stress paths.
The pressure stress intensities for the safe end and blend radius paths were extracted using the ANSYS file VY/RONP.INP. This produced one file, ROPRESSURE.lin, that contains results of the critical stress paths.
Table 1 shows the final pressure stress intensity results for the safe end and blend radius. The results at the blend radius are slightly different from those reported in Table 2 of Reference [4] as a result of the revised material properties (i.e., temperature dependent material properties were used in the current evaluation vs. constant material properties in Reference [4]).
Table 1 shows the final pressure stress intensity results for the safe end and blend radius. The results at the blend radius are slightly different from those reported in Table 2 of Reference [4] as a result of the revised material properties (i.e., temperature dependent material properties were used in the current evaluation vs. constant material properties in Reference [4]).
Results were also extracted from the vessel portion of the model to verify the accuracy of the results obtained from the ANSYS model, and to check the results due to the use of the 2.0 multiplier on the vessel radius. These results are contained in the file RO PRESSURE.lin. The radius of the finite element model (FEM) was multiplied by a factor of 2.0 [4] to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is the intersection of two cylinders.
Results were also extracted from the vessel portion of the model to verify the accuracy of the results obtained from the ANSYS model, and to check the results due to the use of the 2.0 multiplier on the vessel radius. These results are contained in the file RO PRESSURE. lin. The radius of the finite element model (FEM) was multiplied by a factor of 2.0 [4] to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is the intersection of two cylinders.
The equation for the membrane hoop stress in a thin wall sphere is:
The equation for the membrane hoop stress in a thin wall sphere is:
0 (pressure)x (radius))
0 (pressure) x (radius))
S 2 x th~ickes Considering an actual vessel base metal radius, R, of 105.906 inches increased by a factor of 2.0, a vessel base metal thickness, t, of 5.4375 inches, and an applied pressure, P, of 1,000 psi, the calculated stress for a thin wall sphere is PR/(2t) = 19,477 psi. This compares very well with the remote vessel wall membrane hoop stress from the ANSYS result file, ROPRESSURE.lin, of FileNo.: 0801038.305                                                                                 Page 6 of 16 Revision: 1 F0306-O1 RO
S 2 x th~ickes Considering an actual vessel base metal radius, R, of 105.906 inches increased by a factor of 2.0, a vessel base metal thickness, t, of 5.4375 inches, and an applied pressure, P, of 1,000 psi, the calculated stress for a thin wall sphere is PR/(2t) = 19,477 psi. This compares very well with the remote vessel wall membrane hoop stress from the ANSYS result file, ROPRESSURE.lin, of FileNo.: 0801038.305 Page 6 of 16 Revision: 1 F0306-O1 RO


18,070 psi. Thus, considering the peak total pressure stress of 31,270 psi, the stress concentrating effect of the nozzle blend radius is 31,270/19,477 = 1.61. In other words, the peak nozzle blend radius stress is 1.61 times higher than nominal vessel wall stress for the axisyimnetric model.
18,070 psi. Thus, considering the peak total pressure stress of 31,270 psi, the stress concentrating effect of the nozzle blend radius is 31,270/19,477 = 1.61. In other words, the peak nozzle blend radius stress is 1.61 times higher than nominal vessel wall stress for the axisyimnetric model.
The equation for the membrane hoop stress in a thin wall cylinder is:
The equation for the membrane hoop stress in a thin wall cylinder is:
(radius)
((pressure) x (radius) k thickness j"
((pressure)x k       thickness       j" Based on the previous dimensions, the calculated stress for a cylinder without the 2.0 factor is 19,477 psi. Increasing this by a factor of 1.61 yields an expected peak nozzle blend radius stress of 31,358 psi, which would be expected from a cylindrical geometry that is representative of the nozzle configuration. Therefore, the result from the ANSYS file for the peak nozzle blend radius stress (31,270 psi) is close to the peak nozzle blend radius stress for a cylindrical geometry because of the use of the 2.0 multiplier. This is consistent with SI's experience where a factor of two increase in radius is typical for representing the 3-D effect in an axisymmetric model.
Based on the previous dimensions, the calculated stress for a cylinder without the 2.0 factor is 19,477 psi. Increasing this by a factor of 1.61 yields an expected peak nozzle blend radius stress of 31,358 psi, which would be expected from a cylindrical geometry that is representative of the nozzle configuration. Therefore, the result from the ANSYS file for the peak nozzle blend radius stress (31,270 psi) is close to the peak nozzle blend radius stress for a cylindrical geometry because of the use of the 2.0 multiplier. This is consistent with SI's experience where a factor of two increase in radius is typical for representing the 3-D effect in an axisymmetric model.
4.5 Piping Loads The piping loads were taken from Table 4 of Reference [3]. To determine the piping load stresses, the distances from the applied piping loads to the limiting stress locations were first determined. The limiting stress path locations from Section 4.3 are in the same locations assumed in Table 4 of Reference [3]; this means that no reconciliation of the lengths in Table 4 of Reference [3] is needed.
4.5 Piping Loads The piping loads were taken from Table 4 of Reference [3]. To determine the piping load stresses, the distances from the applied piping loads to the limiting stress locations were first determined. The limiting stress path locations from Section 4.3 are in the same locations assumed in Table 4 of Reference [3]; this means that no reconciliation of the lengths in Table 4 of Reference [3] is needed.
Reference [3, Section 4.1 ] methodology was used to calculate the piping load stresses. The piping loads and piping load stresses are found in Table 4 and Table 5 of Reference [3].
Reference [3, Section 4.1 ] methodology was used to calculate the piping load stresses. The piping loads and piping load stresses are found in Table 4 and Table 5 of Reference [3].
Table 1: Pressure Stress Intensity Results (1,000 psi)
Table 1: Pressure Stress Intensity Results (1,000 psi)
Membrane plus                   Total Stress Location                   Bending Stress                   Intensity Intensity                         (psi)
Membrane plus Total Stress Location Bending Stress Intensity Intensity (psi)
(psi)
(psi)
Safe End 11,350                         11,490 (Path 1 Inside)
Safe End (Path 1 Inside) 11,350 11,490 Blend Radius (h2nd 30,540 31,270 (Path 2 Inside)
Blend (h2nd Radius (Path 2 Inside)                  30,540                         31,270 FileNo.: 0801038.305                                                                               Page 7 of 16 Revision: 1 F0306-01RO
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5.0     RESULTS OF ANALYSIS A thennal transient analysis for each defined transient, as well as unit pressure stress and piping interface load analyses were performed for the RO nozzle at Vermont Yankee. All six components of the stress tensor were extracted from the ANSYS model at the two limiting path locations, which are the same two locations previously evaluated [4]. Table 2 provides the unit (1,000 psig) pressure stress analysis results. The unit pressure load results are used to choose the location to analyze at the
5.0 RESULTS OF ANALYSIS A thennal transient analysis for each defined transient, as well as unit pressure stress and piping interface load analyses were performed for the RO nozzle at Vermont Yankee. All six components of the stress tensor were extracted from the ANSYS model at the two limiting path locations, which are the same two locations previously evaluated [4]. Table 2 provides the unit (1,000 psig) pressure stress analysis results. The unit pressure load results are used to choose the location to analyze at the
      *nozzle blend radius and will be scaled up or down based on applied pressures in the fatigue analysis.
* nozzle blend radius and will be scaled up or down based on applied pressures in the fatigue analysis.
Table 5 of Reference [3] provides the piping stresses at the two critical locations. Table 3 shows an example of thermal stress results. The remaining thermal stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:
Table 5 of Reference [3] provides the piping stresses at the two critical locations. Table 3 shows an example of thermal stress results. The remaining thermal stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:
ROPRESSURE.lin: Unit pressure stress analysis results VYRONTRAN]-S.lin: Transient 1, thermal stress analysis results VYRONTRAN2-S.lin: Transient 2, thermal stress analysis results VYRON TRAN3-S.lin: Transient 3, thermal stress analysis results VY RONTRAN4-S.lin: Transient 4, thermal stress analysis results VYRONTRAN5-S.lin: Transient 5, thermal stress analysis results VYRON TRAN6-S. lin: Transient 6, thermal stress analysis results VYRONTRAN7-S. lin: Transient 7, thermal stress analysis results VYRONTRAN8-S.lin: Transient 8, thermal stress analysis results VYRON TRAN9-S. lin: Transient 9, thermal stress analysis results, VYRONTRAN]O-S.lin: Transient 10, thermal stress analysis results VYRONTRAN]1-S.lin: Transient 11, thermal stress analysis results VYRONTRAN12-S.lin: Transient 12, thermal stress analysis results A fatigue calculation using the methodology of Subarticle NB-3200 of Section III of the ASME Code [2] and an enviromnental fatigue usage analysis will be performed in a separate calculation package using the stress results from this calculation.
ROPRESSURE. lin: Unit pressure stress analysis results VYRONTRAN]-S.lin: Transient 1, thermal stress analysis results VYRONTRAN2-S.lin: Transient 2, thermal stress analysis results VYRON TRAN3-S.lin: Transient 3, thermal stress analysis results VY RONTRAN4-S.lin: Transient 4, thermal stress analysis results VYRONTRAN5-S.lin: Transient 5, thermal stress analysis results VYRON TRAN6-S. lin: Transient 6, thermal stress analysis results VYRONTRAN7-S. lin: Transient 7, thermal stress analysis results VYRONTRAN8-S.lin: Transient 8, thermal stress analysis results VYRON TRAN9-S. lin: Transient 9, thermal stress analysis results, VYRONTRAN]O-S.lin: Transient 10, thermal stress analysis results VYRONTRAN]1-S.lin: Transient 11, thermal stress analysis results VYRONTRAN12-S.lin: Transient 12, thermal stress analysis results A fatigue calculation using the methodology of Subarticle NB-3200 of Section III of the ASME Code [2] and an enviromnental fatigue usage analysis will be performed in a separate calculation package using the stress results from this calculation.
The results of this calculation are to be used in SI Calculation No. 081038.306, "Fatigue Analysis of Recirculation Outlet Nozzle."
The results of this calculation are to be used in SI Calculation No. 081038.306, "Fatigue Analysis of Recirculation Outlet Nozzle."
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File No.: 0801038.305 Page 8 of 16 Revision: 1 F0306-O1RO


==6.0     REFERENCES==
==6.0 REFERENCES==
: 1. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
: 1. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
: 2. ASME Boiler and Pressure Vessel Code, Section III, Subsection NB, 1998 Edition with 2000 Addenda.
: 2. ASME Boiler and Pressure Vessel Code, Section III, Subsection NB, 1998 Edition with 2000 Addenda.
: 3. SI Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Confirmatory Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle."
: 3. SI Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Confirmatory Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle."
: 4. SI Calculation No. VY-16Q-305, Revision 0, "Recirculation Outlet Stress History Development for Nozzle Green Function."
: 4. SI Calculation No. VY-16Q-305, Revision 0, "Recirculation Outlet Stress History Development for Nozzle Green Function."
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VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
Table 2: Stresses Under Unit Pressure Load, psi Membrane plus Bending                         Total Node     S       Sz,    S     SY   Syz Sx     x   SY     Sz     Sxy     Syz Sxz SE 6395 -955.2   4420   10390   15.26 0   0   -955.2 4912   10530   -222.6     0   0 BR   3829 -718.7 -951.7 25000   4708   0   0   -718.7 206.2 30150   733.2     0   0 FileNo.: 0801038.305                                                                   Page 10 of 16 Revision: 1 F0306-01RO
Table 2: Stresses Under Unit Pressure Load, psi Membrane plus Bending Total Node S
Sz S
SY Syz Sx x
SY Sz Sxy Syz Sxz SE 6395  
-955.2 4420 10390 15.26 0
0  
-955.2 4912 10530  
-222.6 0
0 BR 3829  
-718.7  
-951.7 25000 4708 0
0  
-718.7 206.2 30150 733.2 0
0 FileNo.: 0801038.305 Revision: 1 Page 10 of 16 F0306-01RO


V StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
Table 3: Example Thermal Stress Result Output, psi Total Transient Node     Time                 Membrane Plus Bending (s)     Sx       Sy       Sz     Sxy   Syz Sxz   Sx   Sy     Sz     Sxy Syz Sxz 0     -33     -3379       196     351   0   0   3539   139     209 0   0 3     -33     -3367     207     351   0   0   3518   160     209 0   0 13     -33     -3340     231     350   0   0   3493   180     208 .0   0 233     180     11400. 12840     210   0   0   180 16290 17350     -536 0   0 2213     -74     -5983     -2660     293   0   0   7056 -3558     322 0   0 2393     149     8475     9884       164   0   0   149 12580 13670     -416 0   0 6773     -51     -4443     -1020     320   0   0   5018 -1463     256 0   0 7193     231     12680     13780     145   0   0   231 17340 18140     -588 0   0 6395     7493     10     -142     2054     221   0   0   10   164 2398       45 0   0 11093   -40     -3276     -654     256   0   0   3669 -954     192 0   0 16457   -47     -4080     -479     352   0   0   4491 -773     244 0   0 16517   -41     -3813     -231     351   0   0   4095 -404     230 0   0 16518   -28     -3689     -110     350   0   0   3383   297     199 0   0 17118   -33     -3241     307     349   0   0   3393   255     204 0   0 17119     3     -2918     623     348   0   0     3 -1521 2098     125 0   0 57120     -33     -3283     279     350   0   0   3439   223     206 0   0 0     3078     2100     4262     554   0   0 3078 4281 5859     577 0   0 3     3078     2100     4262     554   0   0 3078 4280 5856     577 0   0 13   3078     2099     4263     554   0   0 3078 4278 5853     576 0   0 233     823     6811     -8426     -847   0   0   823 12480 38540     5953 0   0 2213   3002     -447     2916     683   0   0 3002 1782 -3944     -735 0   0 2393     799     3298     -10540     -506   0   0   799 9988 25870     4515 0   0 6773   2953       -85     3049     980   0   0 2953 2409 -2931     -397 0   0 7193   1539     6354     -2971     49   0   0 1539 9542 24620     4575 0   0 3829 7493   1642     7294     6946       137   0   0 1642 6282 20660     2675 0   0 11093   2290       364     2825     500   0   0 2290 2225   882     -131 0   0 16457   3195     285     3758     754   0   0 3195 3045   526     -230 0   0 16517   3191       304     3705     753   0   0 3191 3131   687     -181 0   0 16518   3182       300     3699     752   0   0 3182 3120   680     -180 0   0 17118   3157     1120     3848     706   0   0 3157 3802 3273     233   0 0 17119   3127     1109     3832     704   0   0 3127 3771 3247     235   0 0 57120   3077     2085     4216     543   0   0 3077 4274 5877     573   0 0 Note: Not all time steps are listed in this table.
Table 3: Example Thermal Stress Result Output, psi Transient Node Time Membrane Plus Bending Total (s)
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Sx Sy Sz Sxy Syz Sxz Sx Sy Sz Sxy Syz Sxz 0  
-33  
-3379 196 351 0
0  
-33
-3539 139 209 0
0 3  
-33  
-3367 207 351 0
0  
-33
-3518 160 209 0
0 13  
-33  
-3340 231 350 0
0  
-33
-3493 180 208  
.0 0
233 180 11400.
12840 210 0
0 180 16290 17350  
-536 0
0 2213  
-74  
-5983  
-2660 293 0
0  
-74
-7056  
-3558 322 0
0 2393 149 8475 9884 164 0
0 149 12580 13670  
-416 0
0 6773  
-51  
-4443  
-1020 320 0
0  
-51
-5018  
-1463 256 0
0 7193 231 12680 13780 145 0
0 231 17340 18140  
-588 0
0 6395 7493 10  
-142 2054 221 0
0 10 164 2398 45 0
0 11093  
-40  
-3276  
-654 256 0
0  
-40
-3669  
-954 192 0
0 16457  
-47  
-4080  
-479 352 0
0  
-47
-4491  
-773 244 0
0 16517  
-41  
-3813  
-231 351 0
0  
-41
-4095  
-404 230 0
0 16518  
-28  
-3689  
-110 350 0
0  
-28
-3383 297 199 0
0 17118  
-33  
-3241 307 349 0
0  
-33
-3393 255 204 0
0 17119 3  
-2918 623 348 0
0 3  
-1521 2098 125 0
0 57120  
-33  
-3283 279 350 0
0  
-33
-3439 223 206 0
0 0
3078 2100 4262 554 0
0 3078 4281 5859 577 0
0 3
3078 2100 4262 554 0
0 3078 4280 5856 577 0
0 13 3078 2099 4263 554 0
0 3078 4278 5853 576 0
0 233 823 6811  
-8426  
-847 0
0 823 12480 38540 5953 0
0 2213 3002  
-447 2916 683 0
0 3002 1782  
-3944  
-735 0
0 2393 799 3298  
-10540  
-506 0
0 799 9988 25870 4515 0
0 6773 2953  
-85 3049 980 0
0 2953 2409  
-2931  
-397 0
0 7193 1539 6354  
-2971 49 0
0 1539 9542 24620 4575 0
0 3829 7493 1642 7294 6946 137 0
0 1642 6282 20660 2675 0
0 11093 2290 364 2825 500 0
0 2290 2225 882  
-131 0
0 16457 3195 285 3758 754 0
0 3195 3045 526  
-230 0
0 16517 3191 304 3705 753 0
0 3191 3131 687  
-181 0
0 16518 3182 300 3699 752 0
0 3182 3120 680  
-180 0
0 17118 3157 1120 3848 706 0
0 3157 3802 3273 233 0
0 17119 3127 1109 3832 704 0
0 3127 3771 3247 235 0
0 57120 3077 2085 4216 543 0
0 3077 4274 5877 573 0
0 Note: Not all time steps are listed in this table.
File No.: 0801038.305 Revision: 1 Page 11 of 16 F0306-01RO


U     StructuralIntegrity Associates, Inc.
U Structural Integrity Associates, Inc.
1-,                                                                        ft WE PRES- NORM xw%
1 ft WE PRES-NORM xw%
11-         &#xfd; Figure 1. RO Nozzle Internal Pressure Distribution File No.: 0801038.305                                                         Page 12 of 16 Revision: 1 F0306-OIRO
11-  
&#xfd; Figure 1. RO Nozzle Internal Pressure Distribution File No.: 0801038.305 Revision: 1 Page 12 of 16 F0306-OIRO


StructuralIntegrityAssociates, Inc.
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      .......                                                                                                                        AN
AN 2...............
                                                                  .......... 2...............
Figure 2. RO Nozzle Pressure Cap Load & Boundary Condition File No.: 0801038.305 Revision: 1 Page 13 of 16 F0306-01 RO
                                                                              ..          ................ ..... ........ ... . .......................
Figure 2. RO Nozzle Pressure Cap Load & Boundary Condition File No.: 0801038.305                                                                                           Page 13 of 16 Revision: 1 F0306-01 RO


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Figure 3. RO Nozzle Vessel Wall Boundary Condition FileNo.: 0801038.305                                                       Page 14 of 16 Revision: 1 F0306-O1RO
Figure 3. RO Nozzle Vessel Wall Boundary Condition FileNo.: 0801038.305 Page 14 of 16 Revision: 1 F0306-O1RO


V     StructuralIntegrityAssociates, Inc.
V Structural Integrity Associates, Inc.
I M ,y , = R-.-..;, -R.
I M,y, = R-.-..;, -R.
Figure 4. Safe End Critical Thermal Stress Intensity Location File No.: 0801038.305                                                                     Page 15 of 16 Revision: 1 F0306-O1RO
Figure 4. Safe End Critical Thermal Stress Intensity Location File No.: 0801038.305 Revision: 1 Page 15 of 16 F0306-O1RO


StructuralIntegrity Associates, Inc.
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NODAL SOLUTION                                                        AM.N STEp=1
AM.N NODAL SOLUTION STEp=1
              .0114     (AVG~)
.0114 (AVG~)
DMV4~~9 S3P4
DMV4~~9 S3P4
                      '/4 Figure 5. Nozzle Blend Radius Limiting Pressure Stress Intensity Location Figure 6. Limiting Stress Paths File No.: 0801038.305                                                                   Page 16 of 16 Revision: I F0306-O1RO
'/4 Figure 5. Nozzle Blend Radius Limiting Pressure Stress Intensity Location Figure 6. Limiting Stress Paths File No.: 0801038.305 Revision: I Page 16 of 16 F0306-O1RO


V StructuralIntegrityAssociates, Inc.                       File No.: 0801038.306 CALCULATION PACKAGE                                 Project No.: 0801038 Quality Program Z Nuclear   E] Commercial PROJECT NAME:
V Structural Integrity Associates, Inc.
File No.: 0801038.306 CALCULATION PACKAGE Project No.: 0801038 Quality Program Z Nuclear E] Commercial PROJECT NAME:
VY Confirmatory Analyses for CS and RO Nozzles CONTRACT NO.:
VY Confirmatory Analyses for CS and RO Nozzles CONTRACT NO.:
10163217 Amendment 5 CLIENT:                                             PLANT:
10163217 Amendment 5 CLIENT:
Entergy Nuclear Operations, Inc.                 Vermont Yankee Nuclear Power Station CALCULATION TITLE:
PLANT:
Fatigue Analysis of Reactor Recirculation Outlet Nozzle D               Project Manager           Preparer(s) &
Entergy Nuclear Operations, Inc.
Document       Affected         Revision Description               Approval                 Checker(s)
Vermont Yankee Nuclear Power Station CALCULATION TITLE:
Revision       Pages                                         Signature & Date       Signatures & Date 01             - 18             Initial issue.
Fatigue Analysis of Reactor Recirculation Outlet Nozzle D
Gary L. Stevens           Tyler Novotny Computer Files                                       01/07/09                   01/07/09 Jennifer E. Smith 01/07/09 1     1-4,6-12, 14-19     Revised per summary       ,/                     Preparer:
Project Manager Preparer(s) &
Document Affected Revision Description Approval Checker(s)
Revision Pages Signature & Date Signatures & Date 01  
- 18 Initial issue.
Gary L. Stevens Tyler Novotny Computer Files 01/07/09 01/07/09 Jennifer E. Smith 01/07/09 1
1-4,6-12, 14-19 Revised per summary  
,/
Preparer:
contained in Section 1.1.
contained in Section 1.1.
LL                   .'t44   P     a Computer Files   Changes are marked with "revision bars" in right-       Gary L Stevens hand margin.                 03/09/09             Tyler D. Novotny 03/09/09 Checker:
LL  
.'t44 P
a Computer Files Changes are marked with "revision bars" in right-Gary L Stevens hand margin.
03/09/09 Tyler D. Novotny 03/09/09 Checker:
William F. Weitze 03/09/09 Page 1 of 19 F0306-OIRO
William F. Weitze 03/09/09 Page 1 of 19 F0306-OIRO


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Table of Contents 1.0   O B JEC TIVE .................................................................................................................................       3 1.1     Changes Made in Revision I of this Calculation ...........................................................                                     3 2.0   M ETH OD OLO G Y ..............................................................................................................                       3 3.0   D ESIG N IN PU TS .........................................................................................................................         4 3.1     Stress C alculation ..........................................................................................................                 4 3.2     Fatigue Usage Analysis, General ...................................................................................                           4 3.3     Event Cycles, VESLFA T ..............................................................................................                           5 3.4     Material Properties, VESLFAT ......................................                                                                             5 3.5     Stress Indices ..............................................................................................................                 &#xfd;6 4.0   C A L C U L A TION S .........................................................................................................................       6 5.0   RESULTS OF AN ALY SIS .....................................................................................................                           7
Table of Contents 1.0 O B JE C T IV E.................................................................................................................................
3 1.1 Changes Made in Revision I of this Calculation...........................................................
3 2.0 M ETH OD OLO G Y..............................................................................................................
3 3.0 D E SIG N IN PU T S.........................................................................................................................
4 3.1 Stress C alculation..........................................................................................................
4 3.2 Fatigue Usage Analysis, General...................................................................................
4 3.3 Event Cycles, V ESLFA T..............................................................................................
5 3.4 Material Properties, VESLFAT......................................
5 3.5 Stress Indices..............................................................................................................  
&#xfd;6 4.0 C A L C U L A T IO N S.........................................................................................................................
6 5.0 RESULTS OF AN A LY SIS.....................................................................................................
7


==6.0   CONCLUSION==
==6.0 CONCLUSION==
S AND DISCUSSIONS ...............................................................................                                         7 7.0   R EFER EN C ES .............................................................................................................................         8 List of Tables Table   1: Safe End Load Sets as Input to VESLFAT .......................................................................                                 9 Table   2: Nozzle Blend Radius Load Sets as Input to VESLFAT .......................                                                                     I1......
S AND DISCUSSIONS...............................................................................
Table   3: Temperature-Dependent Material Properties for VESLFAT (3)                                                     ............................ 12 Table   4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves .........................................                                           13 Table   5: Pressure and Attached Piping Unit Load Case Stress Components ................................                                                 14 Table   6: Fatigue Usage Calculation for the Safe End .................................                                                                   15 Table 7: Fatigue Usage Calculation for the Nozzle Blend Radius .................................................                                         16 Table 8: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location .......................                                                       17 Table 9: Linearized Stress Files Compiled for VY-RO-StressResults.xls ......................................                                             19 File No.: 0801038.306                                                                                                                                       Page 2 of 19 Revision: 1 F0306-01RO
7 7.0 R E FE R E N C E S.............................................................................................................................
8 List of Tables Table 1: Safe End Load Sets as Input to VESLFAT.......................................................................
9 Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT.......................
1......
I Table 3: Temperature-Dependent Material Properties for VESLFAT (3)  
............................ 12 Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves.........................................
13 Table 5: Pressure and Attached Piping Unit Load Case Stress Components................................
14 Table 6: Fatigue Usage Calculation for the Safe End.................................
15 Table 7: Fatigue Usage Calculation for the Nozzle Blend Radius.................................................
16 Table 8: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location.......................
17 Table 9: Linearized Stress Files Compiled for VY-RO-StressResults.xls...................................... 19 File No.: 0801038.306 Page 2 of 19 Revision: 1 F0306-01RO


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1.0       OBJECTIVE The objective of this calculation package is to perform an ASME Code, Section III fatigue usage evaluation and a plant-specific evaluation of reactor water environmental effects for the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at the Vermont Yankee Nuclear Power Station.
1.0 OBJECTIVE The objective of this calculation package is to perform an ASME Code, Section III fatigue usage evaluation and a plant-specific evaluation of reactor water environmental effects for the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at the Vermont Yankee Nuclear Power Station.
1.1     Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:
1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:
: a. Editorial changes were made to Table 1 to more precisely describe the transient load sets.
: a.
: b. All but one of the changes made to Table 2 were editorial to more precisely describe the portions of the transients. The one non-editorial change was to move a time split in Transient 9 to better catch a stress peak or stress valley.
Editorial changes were made to Table 1 to more precisely describe the transient load sets.
: c. Table 3 and the corresponding VESLFAT input file were revised to reflect actual material properties for the safe end. Revision 0 of this calculation tabulated SA-1 82 F304 (18Cr -8Ni) properties, but actually used properties for an Alloy 600 material.
: b.
: d. Table 5 was changed to eliminate the application ofKt = 1.53 to the nozzle corner piping loads.
All but one of the changes made to Table 2 were editorial to more precisely describe the portions of the transients. The one non-editorial change was to move a time split in Transient 9 to better catch a stress peak or stress valley.
: e. Tables 6, 7, and 8 were revised to reflect the new fatigue usage and environmental assisted fatigue summaries as a result of the changes associated with Bullets b and c above.
: c.
: f. Table 8 was revised for editorial changes.
Table 3 and the corresponding VESLFAT input file were revised to reflect actual material properties for the safe end. Revision 0 of this calculation tabulated SA-1 82 F304 (18Cr -8Ni) properties, but actually used properties for an Alloy 600 material.
: g. The results of various sensitivity studies on fatigue usage were added to Section 5.0.
: d.
: h. Revision of CUF values in Sections 5.0 and 6.0 to reflect revised analyses.
Table 5 was changed to eliminate the application ofKt = 1.53 to the nozzle corner piping loads.
: i. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.
: e.
2.0       METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
Tables 6, 7, and 8 were revised to reflect the new fatigue usage and environmental assisted fatigue summaries as a result of the changes associated with Bullets b and c above.
: f.
Table 8 was revised for editorial changes.
: g.
The results of various sensitivity studies on fatigue usage were added to Section 5.0.
: h.
Revision of CUF values in Sections 5.0 and 6.0 to reflect revised analyses.
: i.
All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.
2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package
[2]. Based on that methodology, thermal stresses, pressure stresses, and attached piping load stresses were developed in the Reference [1 ] calculation for use in this fatigue calculation. The thermal stresses are added to pressure stresses and attached piping load stresses'. Both the pressure and piping load stresses are scaled based on the magnitudes of the pressure and nozzle fluid temperature during each transient. All six components of the stress tensor from the stress results are used in the fatigue calculation.
[2]. Based on that methodology, thermal stresses, pressure stresses, and attached piping load stresses were developed in the Reference [1 ] calculation for use in this fatigue calculation. The thermal stresses are added to pressure stresses and attached piping load stresses'. Both the pressure and piping load stresses are scaled based on the magnitudes of the pressure and nozzle fluid temperature during each transient. All six components of the stress tensor from the stress results are used in the fatigue calculation.
Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 70'F and the full values are reached at a reactor design temperature of 575'F [2, Assumption 3.1.7]. In addition, design seismic and deadweight loads are also included and scaled in combination with the thermal loads for each transient. This combination, coupled with assigning the stress due to these loads the same sign as the thermal stress, is considered to be a very conservative treatment of the loads overall in that deadweight and design seismic loads are considered and scaled for every transient.
Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 70'F and the full values are reached at a reactor design temperature of 575'F [2, Assumption 3.1.7]. In addition, design seismic and deadweight loads are also included and scaled in combination with the thermal loads for each transient. This combination, coupled with assigning the stress due to these loads the same sign as the thermal stress, is considered to be a very conservative treatment of the loads overall in that deadweight and design seismic loads are considered and scaled for every transient.
File No.: 0801038.306                                                                                                   Page 3 of 19 Revision: 1 F0306-01RO
File No.: 0801038.306 Page 3 of 19 Revision: 1 F0306-01RO


StructuralIntegrity Associates, Inc.
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The fatigue calculation is performed for both the limiting safe end and nozzle blend radius locations, as determined in the Reference [1] calculation, and uses the methodology of Subarticle NB-3200 of Section III of the ASME Code [3]. An environmental fatigue usage analysis is also performed in this calculation applying the methodology and associated environmental fatigue multipliers described in Reference [6].
The fatigue calculation is performed for both the limiting safe end and nozzle blend radius locations, as determined in the Reference [1] calculation, and uses the methodology of Subarticle NB-3200 of Section III of the ASME Code [3]. An environmental fatigue usage analysis is also performed in this calculation applying the methodology and associated environmental fatigue multipliers described in Reference [6].
3.0     DESIGN INPUTS 3.1 Stress Calculation Linearized stress components at Node 6395 (limiting safe end path at inside surface) and Node 3829 (limiting nozzle blend radius path at inside surface) are used for the fatigue usage calculation, as shown in Figure 6 of Reference [1]. For the nozzle blend radius location, the stresses used in the evaluation are for the base metal only; that is, the cladding material is unselected prior to stress extraction. The stress components from the thermal stress analyses are combined with stress components due to pressure and piping loads. The linearized thermal stress components for each transient are taken from the relevant output files in the Reference [1] calculation (a sample of which was provided in Table 3 of Reference [1]). The unit pressure stress component results are taken from Table 2 of Reference [1]. Piping load stress components are taken from Table 5 of the Reference [2] calculation.
3.0 DESIGN INPUTS 3.1 Stress Calculation Linearized stress components at Node 6395 (limiting safe end path at inside surface) and Node 3829 (limiting nozzle blend radius path at inside surface) are used for the fatigue usage calculation, as shown in Figure 6 of Reference [1]. For the nozzle blend radius location, the stresses used in the evaluation are for the base metal only; that is, the cladding material is unselected prior to stress extraction. The stress components from the thermal stress analyses are combined with stress components due to pressure and piping loads. The linearized thermal stress components for each transient are taken from the relevant output files in the Reference [1] calculation (a sample of which was provided in Table 3 of Reference [1]). The unit pressure stress component results are taken from Table 2 of Reference [1]. Piping load stress components are taken from Table 5 of the Reference [2] calculation.
3.2 Fatigue Usage Analysis, General Structural Integrity's VESLFAT program [4] is used to perform the fatigue usage calculation in accordance with the fatigue usage portion of ASME Code, Section III, Subarticle NB-3200 [3].
3.2 Fatigue Usage Analysis, General Structural Integrity's VESLFAT program [4] is used to perform the fatigue usage calculation in accordance with the fatigue usage portion of ASME Code, Section III, Subarticle NB-3200 [3].
VESLFAT performs the analysis required by NB-3222.4(e) [3] for Service Levels A and B conditions defined by the user. The VESLFAT program computes the primary-plus-secondary and total stress ranges for all events and performs a correction for elastic-plastic analysis, if necessary.
VESLFAT performs the analysis required by NB-3222.4(e) [3] for Service Levels A and B conditions defined by the user. The VESLFAT program computes the primary-plus-secondary and total stress ranges for all events and performs a correction for elastic-plastic analysis, if necessary.
The program computes the stress intensity range based on the stress component ranges for all event pairs [3, NB-3216.2]. The program evaluates the stress ranges for primary-plus-secondary and primary-plus-secondary-plus-peak stresses based on all six components of stress (3 normal and 3 shear stresses). If the primary-plus-secondary stress intensity range is greater than 3 Sm, the total stress range must be increased by the simplified elastic-plastic strain correction factor, Ke, as described in NB-3228.5 [3]. The design stress intensity, Sm, is specified as a function of temperature. The input maximum temperature for both states of a load set pair is used to establish the S,, value used in the fatigue calculations from the user-defined input values.
The program computes the stress intensity range based on the stress component ranges for all event pairs [3, NB-3216.2]. The program evaluates the stress ranges for primary-plus-secondary and primary-plus-secondary-plus-peak stresses based on all six components of stress (3 normal and 3 shear stresses). If the primary-plus-secondary stress intensity range is greater than 3 Sm, the total stress range must be increased by the simplified elastic-plastic strain correction factor, Ke, as described in NB-3228.5 [3]. The design stress intensity, Sm, is specified as a function of temperature. The input maximum temperature for both states of a load set pair is used to establish the S,, value used in the fatigue calculations from the user-defined input values.
When more than one stress set is defined for either of the event pair loadings, the stress differences are determined for all of the potential stress pairs, and the pair producing the largest alternating total stress intensity (Salt), including any effects of Ke, is used. The principal stresses for the stress ranges are determined by solving for the roots of the following cubic equation2:
When more than one stress set is defined for either of the event pair loadings, the stress differences are determined for all of the potential stress pairs, and the pair producing the largest alternating total stress intensity (Salt), including any effects of Ke, is used. The principal stresses for the stress ranges are determined by solving for the roots of the following cubic equation2:
S3 _ (Tx   -+- yY+ O-z)S2 + (C3x Cy -+ C7 a, z + a,-7    - ,y2   _ Sxz2 _ Syz2)s 2Note that cy., ay, az, etc. are used synonymously with Sx, S,, S,, etc., in this calculation.
S3 _ (Tx  
File No.: 0801038.306                                                                                       Page 4 of 19 Revision: 1 F0306-OIRO
-+- y Y+ O-z)S2 + (C3x Cy -+ C7 z
a, + a,,y2
_ Sxz2 _ Syz2)s 2 Note that cy., ay, az, etc. are used synonymously with Sx, S,, S,, etc., in this calculation.
File No.: 0801038.306 Page 4 of 19 Revision: 1 F0306-OIRO


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VStructural Integrity Associates, Inc.
                      - (Cy"Gy a, + 2 rxy Tz "*yz - CTz Ty2 _ *y , 2 _ Cx TyZ2 o The stress intensities for the event pairs are reordered in decreasing order of Sait, including a correction for the ratio of modulus of elasticity (E) from the fatigue curve divided by E from the material evaluated at the maximum event temperature. This allows a fatigue table to be created to eliminate the number of cycles available for each of the transient events. This fatigue table is based on a worst-case progressive pairing of events in order of the most severe alternating stress to the least severe, allowing determination of a bounding fatigue usage per NB-3222.4(e) [3]. For each load set pair in the fatigue table, the allowable number of cycles is determined based on Salt.
- (Cy" Gy a, + 2 rxy Tz "*yz - CTz Ty2 _ *y,
3.3     Event Cycles, VESLFAT For the Vermont Yankee RO nozzle analysis, transients that consist of combined stress peaks or valleys are split so that each successive peak or valley is treated separately. Therefore, there are 61 load sets based on the combined stress changes for the safe end, and 46 load sets based on the combined stress changes for the nozzle blend radius location. The reason the number of load sets are not equal for each path is because the time history stress results of those paths differ. Tables 1 and 2 show the load sets applicable to plant operation, with cycle counts per Table I of Reference [2].
2 _ Cx TyZ2 o
These are used as input to VESLFAT for the safe end and nozzle blend radius locations, respectively. The cycle counts of Reference [2, 7] consider 60 years of operation. The data from Table 1 is entered into the VESLFAT input files VY-RO-VFAT-1i.CYC (safe end) and the data from Table 2 is entered into the file VY-RO- VFAT-21. CYC (nozzle blend radius).
The stress intensities for the event pairs are reordered in decreasing order of Sait, including a correction for the ratio of modulus of elasticity (E) from the fatigue curve divided by E from the material evaluated at the maximum event temperature. This allows a fatigue table to be created to eliminate the number of cycles available for each of the transient events. This fatigue table is based on a worst-case progressive pairing of events in order of the most severe alternating stress to the least severe, allowing determination of a bounding fatigue usage per NB-3222.4(e) [3]. For each load set pair in the fatigue table, the allowable number of cycles is determined based on Salt.
3.4     Material Properties, VESLFAT Material properties are entered in VESLFAT input files VY-RO-VFAT-]I.FDT (safe end) and VY-RO-VFAT-2I.FDT (nozzle blend radius). Table 3 lists the temperature-dependent material properties used in the analysis [5]. Table 4 lists the fatigue curve for the nozzle blend radius and safe end materials
3.3 Event Cycles, VESLFAT For the Vermont Yankee RO nozzle analysis, transients that consist of combined stress peaks or valleys are split so that each successive peak or valley is treated separately. Therefore, there are 61 load sets based on the combined stress changes for the safe end, and 46 load sets based on the combined stress changes for the nozzle blend radius location. The reason the number of load sets are not equal for each path is because the time history stress results of those paths differ. Tables 1 and 2 show the load sets applicable to plant operation, with cycle counts per Table I of Reference [2].
These are used as input to VESLFAT for the safe end and nozzle blend radius locations, respectively. The cycle counts of Reference [2, 7] consider 60 years of operation. The data from Table 1 is entered into the VESLFAT input files VY-RO-VFAT-1i.CYC (safe end) and the data from Table 2 is entered into the file VY-RO-VFAT-21. CYC (nozzle blend radius).
3.4 Material Properties, VESLFAT Material properties are entered in VESLFAT input files VY-RO-VFAT-]I.FDT (safe end) and VY-RO-VFAT-2I.FDT (nozzle blend radius). Table 3 lists the temperature-dependent material properties used in the analysis [5]. Table 4 lists the fatigue curve for the nozzle blend radius and safe end materials
[3, Appendix I, Table 1-9.1 and Figure 1-9.1 (UTS < 80.0 ksi) for the nozzle blend radius, and Tables 1-9.1 and 1-9.2.2 (Curve C) and Figures 1-9.2.1 and 1-9.2.2 for the safe end location]. Curve C is selected for the safe end location because it is the most conservative curve among the three extended curves for austenitic steel. VESLFAT automatically scales the stresses by the ratio of E on the fatigue curve to E in the analysis, for the purposes of determining allowable numbers of cycles, as required by the ASME Code.
[3, Appendix I, Table 1-9.1 and Figure 1-9.1 (UTS < 80.0 ksi) for the nozzle blend radius, and Tables 1-9.1 and 1-9.2.2 (Curve C) and Figures 1-9.2.1 and 1-9.2.2 for the safe end location]. Curve C is selected for the safe end location because it is the most conservative curve among the three extended curves for austenitic steel. VESLFAT automatically scales the stresses by the ratio of E on the fatigue curve to E in the analysis, for the purposes of determining allowable numbers of cycles, as required by the ASME Code.
Other material properties are input as follows:
Other material properties are input as follows:
Line 1,022: Line 2,340:
E from fatigue curve = 28,300 ksi [3, Appendix 1, Figure 1-9.2] for the safe end location.
E from fatigue curve = 28,300 ksi [3, Appendix 1, Figure 1-9.2] for the safe end location.
E from fatigue curve = 30,000 ksi [3, Appendix I, Figure 1-9.1] for the nozzle blend radius location.
E from fatigue curve = 30,000 ksi [3, Appendix I, Figure 1-9.1] for the nozzle blend radius location.
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3.5     Stress Indices The limiting stress path for the RO nozzle safe end is defined in Reference [1]. The stresses caused by the piping were hand calculated and do require a stress concentration factor, if appropriate. The stress concentration factor for the safe end location is 1.53 [2, Section 3.8]. This value is conservatively used for both the C2 and K2 values required by the ASME Code [3, NB-3600]. The piping loads are relatively minor in comparison to the other loads this nozzle experiences so the conservative C2 and K2 values will have a small impact on the analysis. Table 5 shows the piping loads after applying the C2 and K2 values as appropriate.
3.5 Stress Indices The limiting stress path for the RO nozzle safe end is defined in Reference [1]. The stresses caused by the piping were hand calculated and do require a stress concentration factor, if appropriate. The stress concentration factor for the safe end location is 1.53 [2, Section 3.8]. This value is conservatively used for both the C2 and K2 values required by the ASME Code [3, NB-3600]. The piping loads are relatively minor in comparison to the other loads this nozzle experiences so the conservative C2 and K2 values will have a small impact on the analysis. Table 5 shows the piping loads after applying the C2 and K2 values as appropriate.
4.0     CALCULATIONS Table 5 contains the stress components at the locations of interest for the 1,000 psi unit pressure stress case [1, Table 2]. Table 5 also contains the stress components for the attached piping load unit stress case [2, Table 5], which correspond to a reactor design temperature of 575&deg;F [2, Section 3.1.7].
4.0 CALCULATIONS Table 5 contains the stress components at the locations of interest for the 1,000 psi unit pressure stress case [1, Table 2]. Table 5 also contains the stress components for the attached piping load unit stress case [2, Table 5], which correspond to a reactor design temperature of 575&deg;F [2, Section 3.1.7].
The attached piping load stress components were applied assuming the same signs as the thermal stress, which yields the largest stress component ranges.
The attached piping load stress components were applied assuming the same signs as the thermal stress, which yields the largest stress component ranges.
The calculations of all of the VESLFAT stress inputs are automated in Excel workbooks VY-RO-VFAT-li.xls (safe end) and VY-RO-VFAT-2i.xls (nozzle blend radius). These files are organized with sheets labeled as follows:
The calculations of all of the VESLFAT stress inputs are automated in Excel workbooks VY-RO-VFAT-li.xls (safe end) and VY-RO-VFAT-2i.xls (nozzle blend radius). These files are organized with sheets labeled as follows:
Line 1,035: Line 2,353:
* VESLFAT: Contains the VESLFAT stress input, as obtained from the Rearranger sheets.
* VESLFAT: Contains the VESLFAT stress input, as obtained from the Rearranger sheets.
Load set numbers are entered on this sheet, as defined in Table 1 and Table 2. These sheets are saved to VESLFAT input files VY-RO-VFAT-li.STR (safe end) and VY-RO-VFAT-2i.STR (nozzle blend radius).
Load set numbers are entered on this sheet, as defined in Table 1 and Table 2. These sheets are saved to VESLFAT input files VY-RO-VFAT-li.STR (safe end) and VY-RO-VFAT-2i.STR (nozzle blend radius).
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5.0     RESULTS OF ANALYSIS Table 6 and Table 7 provide the detailed calculated 60-year fatigue usage, as obtained from VESLFAT output files VY-RO-VFAT-11.FAT (safe end) and VY-RO-VFAT-2LFAT (nozzle blend radius). All VESLFAT input and output files are saved in the project computer files associated with this calculation.
5.0 RESULTS OF ANALYSIS Table 6 and Table 7 provide the detailed calculated 60-year fatigue usage, as obtained from VESLFAT output files VY-RO-VFAT-11.FAT (safe end) and VY-RO-VFAT-2LFAT (nozzle blend radius). All VESLFAT input and output files are saved in the project computer files associated with this calculation.
From Table 6, the safe end cumulative usage factor (CUF) is 0.00308 for 60 years. From Table 7, the nozzle blend radius CUF is 0.0 175 for 60 years.
From Table 6, the safe end cumulative usage factor (CUF) is 0.00308 for 60 years. From Table 7, the nozzle blend radius CUF is 0.0 175 for 60 years.
From Table 1 of Reference [6], it was determined that hydrogen water chemistry (HWC) is available for 47% of the total 60-year operating period, and normal water chemistry (NWC) is present for the remaining 53% of the total 60-year operating period. From Table 1 of Reference [6], the dissolved oxygen values for the recirculation line (which is applicable to the RO nozzle) are 48 ppb for HWC conditions and 122 ppb for NWC conditions.
From Table 1 of Reference [6], it was determined that hydrogen water chemistry (HWC) is available for 47% of the total 60-year operating period, and normal water chemistry (NWC) is present for the remaining 53% of the total 60-year operating period. From Table 1 of Reference [6], the dissolved oxygen values for the recirculation line (which is applicable to the RO nozzle) are 48 ppb for HWC conditions and 122 ppb for NWC conditions.
Line 1,045: Line 2,363:
As a part of fatigue analysis calculations, it was noted that using Fy = -20 kips in the piping loads caused a slightly higher total stress intensity. However, the change was determined to have an insignificant effect on fatigue usage results. In addition, the effect of modeling the distinct material properties of both Type F304 and Type F316 in the ANSYS analysis (as opposed to using 18Cr-8Ni properties) was determined to have an insignificant effect on fatigue usage results. Finally, the effect of applying a minimum temperature of 130'F for thermal boundary Region 2 (see Figure 1 of Reference [2]) was determined to have an insignificant effect on fatigue usage results. These investigations and associated results are contained in the project files.
As a part of fatigue analysis calculations, it was noted that using Fy = -20 kips in the piping loads caused a slightly higher total stress intensity. However, the change was determined to have an insignificant effect on fatigue usage results. In addition, the effect of modeling the distinct material properties of both Type F304 and Type F316 in the ANSYS analysis (as opposed to using 18Cr-8Ni properties) was determined to have an insignificant effect on fatigue usage results. Finally, the effect of applying a minimum temperature of 130'F for thermal boundary Region 2 (see Figure 1 of Reference [2]) was determined to have an insignificant effect on fatigue usage results. These investigations and associated results are contained in the project files.


==6.0     CONCLUSION==
==6.0 CONCLUSION==
S AND DISCUSSIONS Detailed fatigue calculations for the Vermont Yankee RO nozzle were performed based on the results of stress analyses previously performed [1]. The thermal stresses were combined with stresses due to pressure and attached piping loads, both of which were scaled based on the magnitudes of the pressure and metal temperature during each thermal transient. All six components of the stress tensor were used for the fatigue calculations. The fatigue calculations were performed at previously-determined limiting locations in the safe end and nozzle blend radius, and used the methodology of Subarticle NB-3200 of Section III of the ASME Code [3].
S AND DISCUSSIONS Detailed fatigue calculations for the Vermont Yankee RO nozzle were performed based on the results of stress analyses previously performed [1]. The thermal stresses were combined with stresses due to pressure and attached piping loads, both of which were scaled based on the magnitudes of the pressure and metal temperature during each thermal transient. All six components of the stress tensor were used for the fatigue calculations. The fatigue calculations were performed at previously-determined limiting locations in the safe end and nozzle blend radius, and used the methodology of Subarticle NB-3200 of Section III of the ASME Code [3].
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The 60-year CUT for the safe end location was'determined to be 0.00308 and the CUF for the nozzle blend radius location was determined to be 0.0175. Both values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.
The 60-year CUT for the safe end location was'determined to be 0.00308 and the CUF for the nozzle blend radius location was determined to be 0.0175. Both values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.
Detailed EAF assessments were also performed for the two RO nozzle locations. The 60-year EAF CUF for the safe end location was determined to be 0.0360. The 60-year EAF CUF for the nozzle blend radius location was determined to be 0.111 using temperature-dependent Fen multipliers for each load pair. Both values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.
Detailed EAF assessments were also performed for the two RO nozzle locations. The 60-year EAF CUF for the safe end location was determined to be 0.0360. The 60-year EAF CUF for the nozzle blend radius location was determined to be 0.111 using temperature-dependent Fen multipliers for each load pair. Both values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.


==7.0     REFERENCES==
==7.0 REFERENCES==
: 1. Structural Integrity Associates Calculation No. 0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle."
: 1. Structural Integrity Associates Calculation No. 0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle."
: 2. Structural Integrity Associates Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle."
: 2. Structural Integrity Associates Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle."
Line 1,062: Line 2,380:
: 7. Entergy Design Input Record (DIR) EC No. 1773, DIR. Revision 1, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-1 6Q-209.
: 7. Entergy Design Input Record (DIR) EC No. 1773, DIR. Revision 1, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-1 6Q-209.
: 8. Deleted (not used in this calculation).
: 8. Deleted (not used in this calculation).
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Table 1: Safe End Load Sets as Input to VESLFAT VESLFAT                 Start ties Transient Time, see Temp Change  Pressure Change Cycles Load Set 1        lTrnl       0         Up            Up        300 2      2Tml       1616.4       Up            Up        300 3        1Tm2         0       Down          None        300 4      2Trn2_       0.4       Down          None        300 5      3Trn2       301     Down          None        300 6      4Trn2_     601.4       Down          None        300 7        1Trn3        0         Up          None        10 8      2Trn3       250       Up          None        10 9      3Tm3_       2050     Down          None        10 10      4Tm3_       2960   Up & Down        None        10 11      5Trn3_     5560     Down          None        10 12        lTrn4_       0       None            Up        10 13      2Trn4         2       None      Up & Down       10 14      3Trn4_        7      Down           Down         10 15      4Tm4_        46    Down & Up       None        10 16      5Tn4_        992    Up & Down       Down         10 17      6Tin4      2294    Down & Up    Down & Up       10 18      7Trn4_      3050    Up & Down     Up & Down       10 19      8Trn4_      6899    Down & Up       Down        10 20      9Trn4      7745        Up          Down        10 21      1OTm4_      8645        Up           Down        10 22      11Trn4_    11057        Up             Up         10 23      12Tin4    16166    Up & Down         Up         10 24      13Tm4_    16818      None         None         10 25      14Trn4    17118      Down         None         10 26        1Tn5_        0      None           Up         60 27        2Trn5        1.5      None      Up & Down       60 28        3Trn5        24        Up        Down & Up       60 29        4Trn5      2310      Down           None       60 30        5Trn5      2611      None         None         60 31        6Trn5    2911.4      Down          None       60 32        1Trn6        0      None           Up         1 33        2Trn6        0.6      None      Up & Down       1 34        3Trn6        20        Up        Down & Up       1 35        4Trn6_    2312      Down          None 36        5Tm6_      2613      None           None 37       6Tin6     2913.6     Down          None File No.: 0801038.306                                                                   Page 9 of 19 Revision: I F0306-O1RO
Table 1: Safe End Load Sets as Input to VESLFAT VESLFAT Load Set 1
2 3
4 5
6 7
8 9
10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Start Transient ties Time, see lTrnl 0
2Tml 1616.4 1Tm2 0
2Trn2_
0.4 3Trn2 301 4Trn2_
601.4 1 Trn3 0
2Trn3 250 3Tm3_
2050 4Tm3_
2960 5Trn3_
5560 lTrn4_
0 2Trn4 2
3Trn4_
7 4Tm4_
46 5Tn4_
992 6Tin4 2294 7Trn4_
3050 8Trn4_
6899 9Trn4 7745 1OTm4_
8645 11Trn4_
11057 12Tin4 16166 13Tm4_
16818 14Trn4 17118 1 Tn5_
0 2Trn5 1.5 3Trn5 24 4Trn5 2310 5Trn5 2611 6Trn5 2911.4 1Trn6 0
2Trn6 0.6 3Trn6 20 4Trn6_
2312 5Tm6_
2613 Temp Change Pressure Change Up Up Down Down Down Down Up Up Down Up & Down Down None None Down Down & Up Up & Down Down & Up Up & Down Down & Up Up Up Up Up & Down None Down None None Up Down None Down None None Up Down None Down Up Up None None None None None None None None None Up Up & Down Down None Down Down & Up Up & Down Down Down Down Up Up None None Up Up & Down Down & Up None None None Up Up & Down Down & Up None None None Cycles 300 300 300 300 300 300 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 60 60 60 60 60 60 1
1 1
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VStructural IntegrityAssociates, Inc.
VStructural Integrity Associates, Inc.
Table 1 (continued): Safe End Load Sets as Input to VESLFAT VESLFAT               Start ties Transient Time, see Temp Change Pressure Change Cycles Load Set 38      lTmn7       0       Down          Down 39      2Trn7       37.5     Down          Down 40      3Trn7       600     Down          Down 41      4Trn7     4443       Down          Down 42      1Trn8         0       None          Down        228 43      2Tm8_         3       Up        Down & Up      228 44      3Trn8_     2295     Down          None        228 45      4Trn8       3927     None          None        228 46      1Trn9         0       Down          None 47      2Trn9       0.12   Down & Up      None 48      3Trn9     27.92       Up          None 49      4Trn9     290.15     None          None 50      1TmlO_       0       Down          Down        300 51    2Trnm0     730.8     Down          Down        300 52    3TmlO_       6314     Down          Down        300 53    4Tm 10       6844     Down          Down        300 54    5TrnlO     9555       Down          Down        300 1
Table 1 (continued): Safe End Load Sets as Input to VESLFAT VESLFAT Load Set 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 Start Transient ties Time, see lTmn7 0
55    6TrnlO     14937     Down          Down        300 10 56      1Trnl 1       0       None          None        120 57    2Tml 1-       0       None          Up        120 58      3Trnl 1       0       None         Down       120 59      1Trnl2        0      None         None         1 60    2Trnl2        0      None           Up 61      3Trnl2        0      None         Down File No.: 0801038.306                                                                 Page 10 of 19 Revision: 1 F0306-0IRO
2Trn7 37.5 3Trn7 600 4Trn7 4443 1Trn8 0
2Tm8_
3 3Trn8_
2295 4Trn8 3927 1Trn9 0
2Trn9 0.12 3Trn9 27.92 4Trn9 290.15 1TmlO_
0 2Trnm0 730.8 3TmlO_
6314 4Tm 10 6844 5TrnlO 9555 6TrnlO 14937 1Trnl 1 0
2Tml 1-0 3Trnl 1 0
1Trnl2 0
2Trnl2 0
3Trnl2 0
Temp Change Pressure Change Cycles Down Down Down Down None Up Down None Down Down & Up Up None Down Down Down Down Down Down None None None None None None Down Down Down Down Down Down & Up None None None None None None Down Down Down Down Down Down None Up Down None Up Down 228 228 228 228 300 300 300 300 300 300 120 120 120 1
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Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT Start VESLFAT Transient Time, Temp Change  Pressure Change Cycles Load Set sec 1      1Tml       0     Up              Up        300 2      2Tml   808.2     Up              Up        300 3      1Trn2       0   Down            None      300 4      2Trn2_     0.4   Down            None      300 5    3Trn2_   401     Down            None      300 6      1Trn3_     0     Up            None        10 7      2Trn3   250   Up & Down          None        10 8      3Trn3   2325   Down & Up          None        10 9    4Trn3_   3510   Up & Down          None        10 10      5Trn3_ 5060     Down            None        10 11      1Trn4_     0     None            Up        10 12      2Trn4_     2     None        Up & Down      10 13      3Trn4_     7   Down            Down        10 14    4Trn4_     46   Down & Up          None        10 15      5Trn4_   1091 Up & Down         Down         10 16      6Trn4_  2348  Down & Up      Down & Up       10 17      7Trn4_  3269  Up & Down     Up & Down       10 18      8Tm4_    6983  Down & Up         Down         10 19      9Trn4_  7745      Up        Down & Up       10 20    1OTrn4_  13839  Up & Down           Up         10 21    l1Trn4_  16918    Down           None       10 22    12Tn4_  18986    None           None       10 23      1Tn5_      0    None       Up & Down       60 24      2Tn5_      24  Up & Down     Down & Up       60 25      3Trn5_  2611    Down            None       60 26      1Trn6_      0    None             Up         1 27      2Tm6_    0.6    None         Up & Down      1 28      3Trn6_    20  Up & Down       Down & Up 29      4Trn6_  2663    Down            None 30      lTrn7      0    Down           Down 31      2Trn7_  37.5    Down           Down 32      3Trn7_  2247    Down            Down 33      1Trn8      0    None            Down      228 File No.: 0801038.306                                                               Page 11 of 19 Revision: 1 F0306-0IRO
Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT VESLFAT Load Set 1
2 3
4 5
6 7
8 9
10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 Start Transient
: Time, sec 1Tml 0
2Tml 808.2 1Trn2 0
2Trn2_
0.4 3Trn2_
401 1Trn3_
0 2Trn3 250 3Trn3 2325 4Trn3_
3510 5Trn3_
5060 1Trn4_
0 2Trn4_
2 3Trn4_
7 4Trn4_
46 5Trn4_
1091 6Trn4_
2348 7Trn4_
3269 8Tm4_
6983 9Trn4_
7745 1OTrn4_
13839 l1Trn4_
16918 12Tn4_
18986 1 Tn5_
0 2Tn5_
24 3Trn5_
2611 1Trn6_
0 2Tm6_
0.6 3Trn6_
20 4Trn6_
2663 lTrn7 0
2Trn7_
37.5 3Trn7_
2247 1 Trn8 0
Temp Change Pressure Change Cycles Up Up Down Down Down Up Up & Down Down & Up Up & Down Down None None Down Down & Up Up & Down Down & Up Up & Down Down & Up Up Up & Down Down None None Up & Down Down None None Up & Down Down Down Down Down None Up Up None None None None None None None None Up Up & Down Down None Down Down & Up Up & Down Down Down & Up Up None None Up & Down Down & Up None Up Up & Down Down & Up None Down Down Down Down 300 300 300 300 300 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 60 60 60 1
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Structural Integrity Associates, Inc.
Table 2 (continued): Nozzle Blend Radius Load Sets as Input to VESLFAT Start VESLFAT Transient     Time,       Temp Change     Pressure Change         Cycles Load Set sec 34           2Trn8_         3        Up & Down        Down & Up              228 35          3Trn8_       2025          Down                None              228 36          1Trn9_         0           Down                None                1 1
Table 2 (continued): Nozzle Blend Radius Load Sets as Input to VESLFAT VESLFAT Load Set Transient Start
37          2Trn9_          9             Up                None 38          3Trn9_        58           None                None                1 39                          0           Down                Down              300 1I1Tml0I Trnl 0 40        2Tml0          313.2         Down               Down               300 41          1Trnl 1          0          None               None               120 42                          0          None                 Up               120 3Trnll                                                              120 43                          0          None               Down 44          1Trnl2          0          None               None               1 45        2Trnl2_          0          None                 Up               1 46        3Trnl2_          0          None               Down               1 Table 3: Temperature-Dependent Material Properties for VESLFAT (3)
: Time, sec Temp Change Pressure Change Cycles 34 35 36 37 38 39 40 41 42 43 44 45 46 2Trn8_
Material             T, 'F   E x 106, psi   S., ksi      Sy, ksi SA-508 Class 2            70        27.8          26.7         50.0 (nozzle blend radius(2))      200        27.1          26.7        47.0 300        26.7         26.7         45.5 400        26.1          26.7         44.2 500        25.7         26.7         43.2 600        25.2         26.7        42.1 SA-182 F316              70        28.3          20          30 (Safe End (1))          200        27.6          20          25.9 300        27.0          20          23.4 400        26.5          19.3        21.4 500        25.8          18.0        20.0 600        25.3          17.0        18.9 Notes:
3Trn8_
: 1. For the safe end material, SA-182 F316 (16Cr- 12Ni- 2Mo) austenitic stainless steel properties are used.
1Trn9_
: 2. For the nozzle blend radius material, SA508 Class 2 material properties are used (3/4Ni-1/2Mo-1/3Cr-V), per Reference [2].
2Trn9_
: 3. All values are taken from Reference [5].
3Trn9_
: 4. SA-508 Class 2 in the Code of Construction is the same as SA-508 Gr. 2 Class 2 in the 1998 ASME Code [5].
1 Trnl 0 I1Tml0I 2Tml0 1 Trnl 1 3Trnll 1Trnl2 2Trnl2_
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3Trnl2_
3 2025 0
9 58 0
313.2 0
0 0
0 0
0 Up & Down Down Down Up None Down Down None None None None None None Down & Up None None None None Down Down None Up Down None Up Down 228 228 1
1 1
300 300 120 120 120 1
1 1
Table 3: Temperature-Dependent Material Properties for VESLFAT (3)
Material SA-508 Class 2 (nozzle blend radius(2))
T, 'F 70 200 300 400 500 600 70 200 300 400 500 600 E x 106, psi 27.8 27.1 26.7 26.1 25.7 25.2 28.3 27.6 27.0 26.5 25.8 25.3 S., ksi 26.7 26.7 26.7 26.7 26.7 26.7 20 20 20 19.3 18.0 17.0 Sy, ksi 50.0 47.0 45.5 44.2 43.2 42.1 30 25.9 23.4 21.4 20.0 18.9 SA-182 F316 (Safe End (1))
Notes:
: 1.
For the safe end material, SA-182 F316 (16Cr-12Ni-2Mo) austenitic stainless steel properties are used.
: 2.
For the nozzle blend radius material, SA508 Class 2 material properties are used (3/4Ni-1/2Mo-1/3Cr-V), per Reference [2].
: 3.
All values are taken from Reference [5].
: 4.
SA-508 Class 2 in the Code of Construction is the same as SA-508 Gr. 2 Class 2 in the 1998 ASME Code [5].
File No.: 0801038.306 Revision: I Page 12 of 19 F0306-0IRO


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Structural Integrity Associates, Inc.
Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves Sa, ksi         Sa, ksi Number of Cycles       Carbon/Low Alloy (1)   Austenitic 10                 580             708 20                  410            512 50                275            345 100                205            261 200                  155            201 500                  105            148 1000                  83              119 2000                  64              97 5000                  48              76 10000                  38              64 20000                  31            55.5 50000                  23            46.3 100000                  20            40.8 200000                16.5            35.9 500000                13.5            31 1000000                12.5            28.2 2.E+06                N/A            22.8(2) 5.E+06                N/A            18.4(2) 1.E+07                N/A            16.4(2) 2.E+07                N/A            15.2(2)
Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves Sa, ksi Sa, ksi Number of Cycles Carbon/Low Alloy (1)
                                                                          ]4.3 (2) 5.E+07                N/A 1.E+08                N/A            14.1(2) 1.E+09              N/A            13.9(2) 1.E+10                N/A            13.7(2) 1.E+1I                N/A            13.6(2)
Austenitic 10 20 50 100 200 500 1000 2000 5000 10000 20000 50000 100000 200000 500000 1000000 2.E+06 5.E+06 1.E+07 2.E+07 5.E+07 1.E+08 1.E+09 1.E+10 1.E+1I 580 410 275 205 155 105 83 64 48 38 31 23 20 16.5 13.5 12.5 N/A N/A N/A N/A N/A N/A N/A N/A N/A 708 512 345 261 201 148 119 97 76 64 55.5 46.3 40.8 35.9 31 28.2 22.8(2) 18.4(2) 16.4(2) 15.2(2)
]4.3 (2) 14.1(2) 13.9(2) 13.7(2) 13.6(2)
Note:
Note:
: 1. Using UTS _ 80 ksi curve.
1.
: 2. Using Curve C for austenitic steel.
2.
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Using UTS _ 80 ksi curve.
Using Curve C for austenitic steel.
File No.: 0801038.306 Revision: 1 Page 13 of 19 F0306-OIRO


VStructural Integrity Associates, Inc.
VStructural Integrity Associates, Inc.
Table 5: Pressure and Attached Piping Unit Load Case Stress Components Node                   Membrane plus Bending (1)                                                   Total (1) t 5      t 5 d(2)                   SY           S       S,                 yz       S"         SY.       S z     Sx     Sxz     ) SyZ   )
Table 5: Pressure and Attached Piping Unit Load Case Stress Components Node Membrane plus Bending (1)
Pressure (3)   6395       -955.2       4420       10390     15.26       0       0       -955.2     4912       10530   -222.6       0         0 3829       -718.7     -951.7     25000     4708       0       0       -718.7     206.2     30150     733.2       0         0 4
Total (1) d(2)
ping( )       6395         0         7930         0       831     2066       0         0       12133         0       1271     3160       0 3829         0         218           0         42       49       0         0         218         0       42       49         0 Nuotes: I. All stress values are in uILts o psI.
SY S
: 2. The safe end location is represented by Node 6395, and the nozzle blend radius location is represented by Node 3829.
S, yz S"
: 3. The stresses for both nodes represent the stress due to an applied pressure of 1,000 psig.
SY.
: 4. Piping stresses for both locations represent the stress due to full attached piping loads at an RPV temperature of 575'F.
S z
: 5. Syz and S_ components have been rearranged from the ANSYS output in order to be in correct order for VESLFAT.
Sx Sxz t 5 )
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SyZ t 5 )
Pressure (3) 6395  
-955.2 4420 10390 15.26 0
0  
-955.2 4912 10530  
-222.6 0
0 3829  
-718.7  
-951.7 25000 4708 0
0  
-718.7 206.2 30150 733.2 0
0 ping(4) 6395 0
7930 0
831 2066 0
0 12133 0
1271 3160 0
3829 0
218 0
42 49 0
0 218 0
42 49 0
Nuotes:
I.
2.
3.
4.
5.
All stress values are in uILts o psI.
The safe end location is represented by Node 6395, and the nozzle blend radius location is represented by Node 3829.
The stresses for both nodes represent the stress due to an applied pressure of 1,000 psig.
Piping stresses for both locations represent the stress due to full attached piping loads at an RPV temperature of 575'F.
Syz and S_ components have been rearranged from the ANSYS output in order to be in correct order for VESLFAT.
File No.: 0801038.306 Revision: 1 Page 14 of 19 F0306-0IRO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
Table 6: Fatigue Usage Calculation for the Safe End Load       Desc. Load     Desc.                                         Salt
Table 6: Fatigue Usage Calculation for the Safe End Load Desc.
          #a         #1       #2       #2       n (cycles)   Sn (psi)       Ke       Si)     Nallow
Load Desc.
          #1         #1       #2       #2                                           (psi)                   U 47       2Trn9       48     3Trn9_         1         79715       2.62   169777     331.52     0.00302 15       4Trn4_     49     4Trn9_         1         30275         1     23722     1757500     0.00000 15       4Trn4_     28     3Trn5           9         29755         1     23610     1784800     0.00001 19       8Trn4       28     3Trn5         10         26926         1     21352     2647400     0.00000 17       6Trn4_     28     3Trn5_         10         25213         1     20492     3155800     0.00000 28       3Trn5_     39     2Trn7_         1         20321         1     16926     8269400     0.00000 18       7Trn4       28     3Trn5_         10         19961         1     16731     8866300     0.00000 28       3Trn5       44     3Trn8_         20           4606         1     16450     9819700     0.00000 34       3Trn6_     44     3Trn8           1           4606         1     16450     9819700     0.00000 43       2Trn8_     44     3Trn8_       207           4606         1     16450     9819700     0.00002 6       4Trn2_     43     2Trn8_         21           4028         1     16176   11335000     0.00000 6       4Trn2_     35     4Trn6_         1           3519         1     15752   14441000     0.00000 6       4Trn2       29     4Trn5         60           3484         1     15637   15446000     0.00000 6       4Trn2_     22     11Trn4_       10         11783         1     15613   15666000     0.00000 6       4Trn2_     23     12Trn4_       10           3202         1     15588   15895000     0.00000 2       2Trnl_       6     4Trn2_       198           3193         1     15583   15936000     0.00001 2       2Trnl       31     6Trn5         60           3319         1     15531   16430000     0.00000 2       2Trnl       37     6Trn6           1           3319         1     15531   16430000     0.00000 2       2Trnl1     25     14Trn4_       10           1702         1     15055   23098000     0.00000 2       2Trnl_     40     3Trn7_         1         18894         1     14987   24732000     0.00000 2       2Trnl_     16     5Trn4_         10           5069         1     14487   41157000     0.00000 33       2Trn6       52     3Trnl_0         1         12380         1     14460   42317000     0.00000 13       2Trn4       52     3Trnl0         10         10470         1     13875   1.336E+09     0.00000 50       1Trnl0_     52     3Trnl0_       289           9634         1     13841   1.968E+09     0.00000 50       1TrnlO     53     4Trnl0         11         18796         1     13770   4.465E+09     0.00000 3       1Trn2       53     4Trnl0         289         18795         1     13769   4.491E+09     0.00000 Total     0.00308 Usage =
Salt
Note:       All other load pairs have an alternating stress, Saft, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
#a  
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#1  
#2  
#2 n (cycles)
Sn (psi)
Ke Si)
Nallow U
#1  
#1  
#2  
#2 (psi) 47 2Trn9 48 3Trn9_
1 79715 2.62 169777 331.52 0.00302 15 4Trn4_
49 4Trn9_
1 30275 1
23722 1757500 0.00000 15 4Trn4_
28 3Trn5 9
29755 1
23610 1784800 0.00001 19 8Trn4 28 3Trn5 10 26926 1
21352 2647400 0.00000 17 6Trn4_
28 3Trn5_
10 25213 1
20492 3155800 0.00000 28 3Trn5_
39 2Trn7_
1 20321 1
16926 8269400 0.00000 18 7Trn4 28 3Trn5_
10 19961 1
16731 8866300 0.00000 28 3Trn5 44 3Trn8_
20 4606 1
16450 9819700 0.00000 34 3Trn6_
44 3Trn8 1
4606 1
16450 9819700 0.00000 43 2Trn8_
44 3Trn8_
207 4606 1
16450 9819700 0.00002 6
4Trn2_
43 2Trn8_
21 4028 1
16176 11335000 0.00000 6
4Trn2_
35 4Trn6_
1 3519 1
15752 14441000 0.00000 6
4Trn2 29 4Trn5 60 3484 1
15637 15446000 0.00000 6
4Trn2_
22 11Trn4_
10 11783 1
15613 15666000 0.00000 6
4Trn2_
23 12Trn4_
10 3202 1
15588 15895000 0.00000 2
2Trnl_
6 4Trn2_
198 3193 1
15583 15936000 0.00001 2
2Trnl 31 6Trn5 60 3319 1
15531 16430000 0.00000 2
2Trnl 37 6Trn6 1
3319 1
15531 16430000 0.00000 2
2Trnl1 25 14Trn4_
10 1702 1
15055 23098000 0.00000 2
2Trnl_
40 3Trn7_
1 18894 1
14987 24732000 0.00000 2
2Trnl_
16 5Trn4_
10 5069 1
14487 41157000 0.00000 33 2Trn6 52 3Trnl_0 1
12380 1
14460 42317000 0.00000 13 2Trn4 52 3Trnl0 10 10470 1
13875 1.336E+09 0.00000 50 1Trnl0_
52 3Trnl0_
289 9634 1
13841 1.968E+09 0.00000 50 1TrnlO 53 4Trnl0 11 18796 1
13770 4.465E+09 0.00000 3
1Trn2 53 4Trnl0 289 18795 1
13769 4.491E+09 0.00000 Total 0.00308 Usage =
Note:
All other load pairs have an alternating stress, Saft, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
File No.: 0801038.306 Page 15 of 19 Revision: I F0306-O1RO


V StructuralIntegrity Associates, Inc.
V Structural Integrity Associates, Inc.
Table 7: Fatigue Usage Calculation for the Nozzle Blend Radius Load     Desc. Load     Desc.       n                           Salt Nallow        U
Table 7: Fatigue Usage Calculation for the Nozzle Blend Radius Load Desc.
            #1         #1       #2       #2     (cycles)   S   (psi)     Ke   (psi) 1Trnl1       14     4Trn4_       10       21902       1.00 43085       6889      0.0015 1Trnl_      37    2Trn9_        1      21390       1.00 32177     17617      0.0001 12    1Trn1_      16    6Trn4_      10        15100       1.00 31137     19701      0.0005 1    1Trnl_      27    2Trn6_        1      42381       1.00 27020     30496      0.0000 2    2Trnl_      45    2Trn12_        1      45773       1.00 26852     31084      0.0000 1    1Trnl_      15    5Trn4_      10        18457       1.00 26707     31604      0.0003 2    lTrnl_      18    8Trn4_      10        13066       1.00 26562     32139      0.0003 1    1Trnl_      36    1Trn9_        1      28617       1.00 24546     40947      0.0000 2                                              34179       1.00 24042     43643      0.0002 1    1Trn1_      13    3Trn4_      10 1    1Trnl_      38    3Trn9_        1      25904       1.00 23939     44218      0.0000 1    1Trn1_      12    2Trn4_      10      36762       1.00 23612     46129      0.0002 1    1Trnl_      23    1Trn5_      60      35051       1.00 22617     54348      0.0011 11    1Trn1_      17    7Trn4_      10      22210       1.00 22533     55358      0.0002 2    1Trnl_        5    3Trn2_      166      29847       1.00 22312     58126      0.0029 2    2Trnl_        5    3Trn2_      134      29301       1.00 22309     58168      0.0023 2    2Trnl_      28    3Trn6_        1      33856       1.00 22227     59234      0.0000 2    2Trn 1      11    1Trn4_      10      33460       1.00 21959     62919      0.0002 2    2Trnl1      26    1Trn6_        1      32908       1.00 21661     67330      0.0000 2    2Trnl_      25    3Trn5_      68      29068       1.00 21226     74454      0.0008 2    2Trnl1      29    4Trn6_        1      29068       1.00 21226     74454      0.0000 2    2Trnl1        8    3Trn3_      10      29847       1.00 21214     74661      0.0001 2Trnl_        4    2Trn2_      82      30245       1.00 21092     76819      0.0011 4    2Trn2_      41    1Trn 11      120      32229       1.00 20851     81328      0.0015 4    2Trn2_      32    3Trn7_        1      30983       1.00 20125     96967      0.0000 4    2Trn2_      40    2Trn 10_      97        30982       1.00 20124     96981      0.0010 10      5Trn3_      40    2Trn 10_      10        31344       1.00 20033     99198      0.0001 35      3Trn8_      40    2Trn 10_    193      29931       1.00   19888     102050      0.0019 35      3Trn8_      43    3Trnl 1_      35      29651       1.00   19696     105678      0.0003 9    4Trn3_      43    3Trn  11_    10        30915       1.00   19357     112494      0.0001 7    2Trn3_      46    3Trn12_        1        30523       1.00   19349     112655      0.0000 7    2Trn3_      44    1Trn12_        1        30523       1.00   19349     112655      0.0000 7    2Trn3_      43    3Trn 11        8        30523       1.00   19349     112655      0.0001 3    1Trn2_      43    3Trn 11_      67        31236       1.00   19331     113042      0.0006 3    1Trn2_      19    9Trn4_      10        23810       1.00   16958     181219      0.0001 31    2Trn7_      42    2Trnl I        1        27376       1.00   11515     infinite   0.0000 Total     0.0175 Usage =
Load Desc.
Note:       All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
n Salt
File No.: 0801038.306                                                                                   Page 16 of 19 Revision: 1 F0306-O1RO
#1  
#1  
#2  
#2 (cycles)
S (psi)
Ke (psi) 2 2
1 1
2 1
2 1
1 1
1 1
11 2
2 2
2 2
2 2
2 4
4 4
10 35 35 9
7 7
7 3
3 31 1Trnl1 14 4Trn4_
1Trnl_
37 2Trn9_
1Trn1_
16 6Trn4_
1Trnl_
27 2Trn6_
2Trnl_
45 2Trn12_
1Trnl_
15 5Trn4_
lTrnl_
18 8Trn4_
1Trnl_
36 1Trn9_
1Trn1_
13 3Trn4_
1Trnl_
38 3Trn9_
1Trn1_
12 2Trn4_
1Trnl_
23 1Trn5_
1Trn1_
17 7Trn4_
1Trnl_
5 3Trn2_
2Trnl_
5 3Trn2_
2Trnl_
28 3Trn6_
2Trn 1 11 1Trn4_
2Trnl1 26 1Trn6_
2Trnl_
25 3Trn5_
2Trnl1 29 4Trn6_
2Trnl1 8
3Trn3_
2Trnl_
4 2Trn2_
2Trn2_
41 1Trn 11 2Trn2_
32 3Trn7_
2Trn2_
40 2Trn 10_
5Trn3_
40 2Trn 10_
3Trn8_
40 2Trn 10_
3Trn8_
43 3Trnl 1_
4Trn3_
43 3Trn 11_
2Trn3_
46 3Trn12_
2Trn3_
44 1Trn12_
2Trn3_
43 3Trn 11 1Trn2_
43 3Trn 11_
1Trn2_
19 9Trn4_
2Trn7_
42 2Trnl I 10 1
10 1
1 10 10 1
10 1
10 60 10 166 134 1
10 1
68 1
10 82 120 1
97 10 193 35 10 1
1 8
67 10 1
21902 1.00 43085 21390 1.00 32177 15100 1.00 31137 42381 1.00 27020 45773 1.00 26852 18457 1.00 26707 13066 1.00 26562 28617 1.00 24546 34179 1.00 24042 25904 1.00 23939 36762 1.00 23612 35051 1.00 22617 22210 1.00 22533 29847 1.00 22312 29301 1.00 22309 33856 1.00 22227 33460 1.00 21959 32908 1.00 21661 29068 1.00 21226 29068 1.00 21226 29847 1.00 21214 30245 1.00 21092 32229 1.00 20851 30983 1.00 20125 30982 1.00 20124 31344 1.00 20033 29931 1.00 19888 29651 1.00 19696 30915 1.00 19357 30523 1.00 19349 30523 1.00 19349 30523 1.00 19349 31236 1.00 19331 23810 1.00 16958 27376 1.00 11515 Nallow U
6889 0.0015 17617 0.0001 19701 0.0005 30496 0.0000 31084 0.0000 31604 0.0003 32139 0.0003 40947 0.0000 43643 0.0002 44218 0.0000 46129 0.0002 54348 0.0011 55358 0.0002 58126 0.0029 58168 0.0023 59234 0.0000 62919 0.0002 67330 0.0000 74454 0.0008 74454 0.0000 74661 0.0001 76819 0.0011 81328 0.0015 96967 0.0000 96981 0.0010 99198 0.0001 102050 0.0019 105678 0.0003 112494 0.0001 112655 0.0000 112655 0.0000 112655 0.0001 113042 0.0006 181219 0.0001 infinite 0.0000 Total 0.0175 Usage =
Note:
All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.
File No.: 0801038.306 Revision: 1 Page 16 of 19 F0306-O1RO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
Table 8: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location VY RO flozzle Corner Environmental Fatique Calculation CUF Calculation from file NrY-RO-VFAT-2i.fat:
Table 8: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location VY RO flozzle Corner Environmental Fatique Calculation CUF Calculation from file NrY-RO-VFAT-2i.fat:
Index     Load.#1: Description#1     1 (cycles)(5 Load#21Description#2':n2Icycles)(5) (cycles) (5: Sr,(pi) K   S.(psi)   1`.1       U S         I           Trn_           300       14 i   4Trn4_
Index Load.#1: Description#1 1 (cycles)(5 Load#21Description#2':n2Icycles)(5)
4           10         10         21902 1.00 43085   6889     0.0015 2                     1Trn1_          290       3r       2Trn9             1           1         21390 1.00   32177 17617     0.0001 3         1           1Trnl       I   289       16 i   6Trn4_           10         10         15100 1.00   31137 19701     0.0005 4         1         lTrnl           279       27       2Trn6     i       1           1         42381 1.00 .27020 30496     0.0000 5         2           27rnl           30G       451     2Trn 12           1                     45773 1.00 26852   31054     0.0000 6         1         1Trnl_
(cycles) (5:
l                -78       18s      5Trn_4   i     10         10         18457 1.00 26707   31604     0,0003 7         1               1Trnt       268       18 i   8Trn4_   i     10         10         13066 1.00   26562 32139     0.0003 8         1n         125nl           L8         36       1Trn9             1           1         28617 1.00 24546   40947     0.0000 9         '1         lTrn     i     257       13       3Trn 4-         10         10         34179 1.00 24042   43643     0.0002 10         1i         1Trnl_           247       38       3Trn 9_           1           1         25904 1.00 23939   44218     0.0000 11         1           Trl           246       12 1     2Trn4           10         10         36762 1.00 23,612 46129     0.0002 12         1           Trnl           2        23       I1Trn5_   i     60         60         35051 1.00 22617     4348   0.0011 13         1         ITrnl           176       17       7Trn_           10         10         22210 1.00   22533 55358     0.0002 14         1       ITrnl               16,6               3Trn2           300         166         29847 1.00   22312 58126     0.0029 15         :2         2Trnl           299         5       3Trn2           134         134         29301 1.00 22309   E5168     0.0023 16         2           27rnl           165       28       3Trn6             1           1         33856 1.00 22227   59234     0.0000 17         2         .2Trnl 1         1S4       11       1Trn4     1     10         10         33460 1.00   21959 62919     0.0002 18         2           2Trnl           1         26       1 rn6             1           1         32908 1.00   21661 67330     0.0000 19         2           2Trnl1          153       25       3TrnS           60         60         29068 1.00   21226 74454     0.0008 20         2         2T rn     i       93       29       dTrn6_           1           1         29068 1.00   21226 74454     0.0000 21         2           27rnl             R2       8 i   3Trn3           10         10         29847 1.00   21214 74661     0.0001 22         2           2Trnl             82         4     2Trn2           300         82         30245 1.00   21092 76819     0.001.1 23         4             m 2rn2_            218       41 1   1Trn11-   1     120         120
Sr,(pi)
* 32229 1.00 20851   81328     0.0015 24         4         2Trn2             98       32       3Trn7             1           1         30983 1.00   20125 06967     0.0000 25         .4         2Trn2             Q7       40 1         O 2Trnl10-         300         97         30082 1.00   20124     n- 1   0.0010 26         10           5Trn3           10       do     2Trn10_   i     203         10         31344 1.00   20033 99198     0.0001 27         35           7 mTrn         228       40     2Trn 10         193         193         29931 1.00   19589 102050     0.0019 28         35-         3Trn_             35       43     3Trnh1           120         35         29651 1.00   19698 105678     0.0003 29         9         4Trn3             10       43     3Trn11    1     85         10         30915 1.00   19357 112494     0.0001 4
K S.(psi) 1`.1 U
30         7         2Trn3             10               3Trn12     i       1           1         30523 1.00   19349 112655     0.0000 31         7         2Trn3             9       44     1Trn12i           1           1         30523 1.00   19349 112655     0.0000 32         7         2Trn3             8       43   J3Trnl1             75           8         30523 1.00   19349 112655     0.0001 33         3           lTrn2         300       43     3Trn11           67         67         31236 1.00   19331 113042     0.0006 34         3           tTrn2           233       19       9Trn4     i     10         10         23810 1.00   16958 181219     0.0001 35   ,    31         2Tmn_             1       42     2T1rn1_   1     120         1.       27376 1.00   11515 infinte   0.0000 Total, U = 0.0175 File No.: 0801038.306                                                                                                                                       Page 17 of 19 Revision: 1 F0306-O1RO
S I
Trn_
300 14 i
4Trn4_
4 10 10 21902 1.00 43085 6889 0.0015 2
1 Trn1_
290 3r 2Trn9 1
1 21390 1.00 32177 17617 0.0001 3
1 1Trnl I
289 16 i
6Trn4_
10 10 15100 1.00 31137 19701 0.0005 4
1 lTrnl 279 27 2Trn6 i
1 1
42381 1.00  
.27020 30496 0.0000 5
2 27rnl 30G 451 2Trn 12 1
45773 1.00 26852 31054 0.0000 6
1 l
1Trnl_  
-78 18 s 5Trn_4 i
10 10 18457 1.00 26707 31604 0,0003 7
1 1Trnt 268 18 i
8Trn4_
i 10 10 13066 1.00 26562 32139 0.0003 8
1n 125nl L8 36 1Trn9 1
1 28617 1.00 24546 40947 0.0000 9  
'1 lTrn i
257 13 3Trn 4-10 10 34179 1.00 24042 43643 0.0002 10 1i 1Trnl_
247 38 3Trn 9_
1 1
25904 1.00 23939 44218 0.0000 11 1
Trl 246 12 1
2Trn4 10 10 36762 1.00 23,612 46129 0.0002 12 1
2 Trnl 23 I1Trn5_
i 60 60 35051 1.00 22617 4348 0.0011 13 1
ITrnl 176 17 7Trn_
10 10 22210 1.00 22533 55358 0.0002 14 1
ITrnl 16,6 3Trn2 300 166 29847 1.00 22312 58126 0.0029 15
:2 2Trnl 299 5
3Trn2 134 134 29301 1.00 22309 E5168 0.0023 16 2
27rnl 165 28 3Trn6 1
1 33856 1.00 22227 59234 0.0000 17 2  
.2Trnl 1
1S4 11 1Trn4 1
10 10 33460 1.00 21959 62919 0.0002 18 2
2Trnl 1
26 1 rn6 1
1 32908 1.00 21661 67330 0.0000 19 2
2Trnl 1 153 25 3TrnS 60 60 29068 1.00 21226 74454 0.0008 20 2
2T rn i
93 29 dTrn6_
1 1
29068 1.00 21226 74454 0.0000 21 2
27rnl R2 8
i 3Trn3 10 10 29847 1.00 21214 74661 0.0001 22 2
2Trnl 82 4
2Trn2 300 82 30245 1.00 21092 76819 0.001.1 23 4
2rn2_
m 218 41 1
1Trn11-1 120 120
* 32229 1.00 20851 81328 0.0015 24 4
2Trn2 98 32 3Trn7 1
1 30983 1.00 20125 06967 0.0000 25  
.4 2Trn2 Q7 40 1
2Trnl10-O 300 97 30082 1.00 20124 n-1 0.0010 26 10 5Trn3 10 do 2Trn10_
i 203 10 31344 1.00 20033 99198 0.0001 27 35 7 mTrn 228 40 2 Trn 10 193 193 29931 1.00 19589 102050 0.0019 28 35-3Trn_
35 43 3Trnh1 120 35 29651 1.00 19698 105678 0.0003 29 9
4Trn3 10 43 3 Trn11 1
85 10 30915 1.00 19357 112494 0.0001 30 7
2Trn3 10 4
3Trn12 i
1 1
30523 1.00 19349 112655 0.0000 31 7
2Trn3 9
44 1Trn12i 1
1 30523 1.00 19349 112655 0.0000 32 7
2Trn3 8
43 J3Trnl1 75 8
30523 1.00 19349 112655 0.0001 33 3
lTrn2 300 43 3Trn11 67 67 31236 1.00 19331 113042 0.0006 34 3
tTrn2 233 19 9Trn4 i
10 10 23810 1.00 16958 181219 0.0001 35 31 2Tmn_
1 42 2T1rn1_
1 120
: 1.
27376 1.00 11515 infinte 0.0000 Total, U =
0.0175 File No.: 0801038.306 Revision: 1 Page 17 of 19 F0306-O1RO


Structural Integrity Associates, Inc.
Structural Integrity Associates, Inc.
Table 8 (continued): EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location EAF Calcuatina                       IIWC DO   rIlVLC 00 ndW8~,"uskumTh I.'4.r~/FI       48       122     ppb Transient Maximum Temperatures:                                                                                                                                            % HWC=   47%       53%       =% IIWc
Table 8 (continued): EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location EAF Calcuatina IIWC DO rIlVLC 00 ndW8~,"uskumTh I.'4.r~/FI 48 122 ppb
                                                                      ~'~iY..OA..~JFAT.Ji ~i I TMAX (TF)(1)          TMAX (-1              Fen (Z)
% HWC =
(3)
47%
Uanv (3)  -
53%  
Index   Load #1I Desc. #1 Load #2 Desc #2             Line#       T 1(4) st1(4   72(4) s2 (4) Sn (psi) T Fi)(1)                                                                                       Uenv 1         1       lTrnl_       14       4Trn4       176           "1     3       14   18   21902       339 2           1       ITrnl       37       2Trn9_     6065           /   3       37   62     21390       437 3         1       ITrnl _     16       6Trne_     1060           I     3       16   7     15100       329 4         1       1Trn 1       27       2Trn6_     3734         1     3       27   8     42301       526 5         2     2Trnl_       45       2Trn12     20'1558         2     1       45     1   45773       120                                                                   2.45 6           1       iTrno       15 is          5Tro4 4      1927         1     3       15   49     13457       394                                                         201      2-45    4.46          0.001 7                   1Trnn       10         -
=% IIWc Transient Maximum Temperatures:
0Trn      223M           I     3       18   10   1300*       335                                     335                  100    2.45      3.04        0.001 8         I     1Trn 1       36       1Trn_       5657         1     3       3M   41   20617       405                                     495                  257    2.45      0.50        0.000 9           1     1Trn I       13       3Trn 4     1651         1     3       13   15   34179       516                                     516                  269    2.45      9.03        0.001 10         1       iTrnl _     30       3-rnS       6657
~'~iY..OA..~JFAT.Ji ~i I Index Load #1I Desc. #1 Load #2 Desc #2 Line#
                                                                    -          I      3       38     1   25904       490                                     490                  254    2.45      8.31        0U000 4                                                                                                    526                  274    2.45    10.49        0.001 11           I     ITrnl         12       2Trn _      1599         1     3       12     3   36762       526 12         1       1Trnl_     23       1Trn5       311t5         1     3       23   27     35051       526                                     520                  274    2.45    10.49        0.007 13         1       1Trnl_       17       7Trn4     2152         1     3       17   5&   22210       426                                     426                  219    2.45      5.4.        0.001 14         1       ITrnl_       5       3Trn2_       952         1     3       5   80   29847       530                                      530                 277    2.45    10.76        0.020 15         2     2TrnI 1                 ITrr2_     8718         2     1       5   79     29301       530                                     530                  277    2.45    10.76          0.016 16         2     2Trn1l       20         5Trno_   9R727         2     1       28     1   33856       526                                     526                  274    2.45    10.49          0.000 17         2     2Trn 1 _      11         ITrn4 _   42455         2     1       11   4     33460       526                                     526                  274    2.40    10.49          0.001 18         2     2Trn1_        26       ITrn6_     98465         2     1       26   3     32900       526                                     52,                  274    2.45    10.49          0.000 2Trn I_       25       3irn5     89557         2     1       25   22     29068       529                                     520                  276    2.45    10.60          0.005 19          2 20         2     2Trn I       29       4Trn_     105503         2     1       29   21     29060       529                                     520                  276    2.45    10.69          0.000 21         2     2Trn 1         8       3Trn3_     35.741         2     1       8   5     29047       528                                     520                  276    2.45    10.63          0.001 T                                                                                                                                                    204    2.45    11.71          0.008 22         2     2 rnl_         4       2Trn2_     7777         2     1       4   7     30245       5-43                                     543 23         4     2Trn2         41       1Trnl     233450         4     7       41     1   32229       543                                      543                 204    2.45    11.71          0.011 24         4     2Trn2         32       3Trn7_   223647         4     7       32   126   30983       543                                      543                  204    2.45    11,71          0.000 543                                      543                 2M4    2.45    11.71          0.007 25         4     2Trn2_       40       2-r7ln10- 232587         4     7       40   209   30982 26         '10     5Trn 3       40       2Trnl 0   1138571       10     21       40   209   31344       527                                     527                  275    2.45    10.56          0.001 27         35     3TrnO         40       2Trn10_   28?1140         35     51     40   209   2S931       528                                     520                  276    2.45    10.63          0.013 20         35     3Trn.         43       3Trohl _ 2910647         35     51     43    1   29651       520                                     528                  276    2.45    10.63          0.002 29         9     4Trn_         43       3Trn 11- 106932C         C     28       43     1   30915       536                                     536-                280    2.45    11.19          0.001 2Trn3         46       3Trn 12_ 066274         7     42     46     1   30523       536                                      536                 280    2.45    11.19          0.000 30          7 31         7     2Trn 3       44       1Trn12   860190         7     42     44     1   30523       536                                     536                  260    2.45    11.19          0.000 32         7     27rn 3       43       3Trn11     860148         7     42       43     I   30523       536                                      536                 280    2.45    11.19          0.001 33         3     1Trn2_       43       3TrolI   206618         3     1       43     1   31236       549                                      549                 257    2.45    12.18          0.005 34         3     1Trn2         19       9T"rn _   203153         3     1       19   94   23810       549                                     549                  267    2.45    12.18          0.000 35         31     2Trtn         42       2Trnl 1 26255.22       :31     809     42     1   27376       339                                     339                 171     2.45     3.12         0.000 Total, U =   0.411 Overall Fen =     0,32 Notes:   1. T,,- is the maximum temperature of the two paired load states, and represents the metal (nodal) temperature at the location being analyzed. This.
T 1(4) st1(4 72(4) s2 (4) Sn (psi) T Fi) (1) 1 1
lTrnl_
14 4Trn4 176 "1
3 14 18 21902 339 2
1 ITrnl 37 2Trn9_
6065  
/
3 37 62 21390 437 3
1 ITrnl _
16 6Trne_
1060 I
3 16 7
15100 329 4
1 1Trn 1 27 2Trn6_
3734 1
3 27 8
42301 526 5
2 2Trnl_
45 2Trn12 20'1558 2
1 45 1
45773 120 6
1 iTrno is 15 5Tro4 1927 1
3 15 49 13457 394 7
1Trnn 10 0Trn 4
223M I
3 18 10 1300*
335 8
I 1Trn 1 36 1Trn_
5657 1
3 3M 41 20617 405 9
1 1Trn I 13 3Trn 4 1651 1
3 13 15 34179 516 10 1
iTrnl _
30 3-rnS 6657 I
3 38 1
25904 490 11 I
ITrnl 12 2Trn 4
1599 1
3 12 3
36762 526 12 1
1Trnl_
23 1Trn5 311t5 1
3 23 27 35051 526 13 1
1Trnl_
17 7Trn4 2152 1
3 17 5&
22210 426 14 1
ITrnl_
5 3Trn2_
952 1
3 5
80 29847 530 15 2
2TrnI 1 ITrr2_
8718 2
1 5
79 29301 530 16 2
2Trn1l 20 5Trno_
9R727 2
1 28 1
33856 526 17 2
2Trn 1
11 ITrn4 _
42455 2
1 11 4
33460 526 18 2
2Trn 1_
26 ITrn6_
98465 2
1 26 3
32900 526 19 2
2Trn I_
25 3irn5 89557 2
1 25 22 29068 529 20 2
2Trn I 29 4Trn_ 105503 2
1 29 21 29060 529 21 2
2Trn 1 8
3Trn3_
35.741 2
1 8
5 29047 528 22 2
2 T rnl_
4 2Trn2_
7777 2
1 4
7 30245 5-43 23 4
2Trn2 41 1Trnl 233450 4
7 41 1
32229 543 24 4
2Trn2 32 3Trn7_
223647 4
7 32 126 30983 543 25 4
2Trn2_
40 2-r7ln 10-232587 4
7 40 209 30982 543 26  
'10 5Trn 3 40 2Trnl 0 1138571 10 21 40 209 31344 527 27 35 3TrnO 40 2Trn10_
28?1140 35 51 40 209 2S931 528 20 35 3Trn.
43 3Trohl _
2910647 35 51 4 3 1
29651 520 29 9
4Trn_
43 3Trn 11-106932C C
28 43 1
30915 536 30 7
2Trn3 46 3Trn 12_
066274 7
42 46 1
30523 536 31 7
2Trn 3 44 1Trn12 860190 7
42 44 1
30523 536 32 7
27rn 3 43 3Trn11 860148 7
42 43 I
30523 536 33 3
1Trn2_
43 3TrolI 206618 3
1 43 1
31236 549 34 3
1Trn2 19 9T"rn _
203153 3
1 19 94 23810 549 35 31 2Trtn 42 2Trnl 1 26255.22
:31 809 42 1
27376 339 Uanv (3) -
TMAX (TF) (1)
TMAX (-1 Fen (Z)
Uenv (3) 2.45 201 2-45 4.46 0.001 335 100 2.45 3.04 0.001 495 257 2.45 0.50 0.000 516 269 2.45 9.03 0.001 490 254 2.45 8.31 0U000 526 274 2.45 10.49 0.001 520 274 2.45 10.49 0.007 426 219 2.45 5.4.
0.001 530 277 2.45 10.76 0.020 530 277 2.45 10.76 0.016 526 274 2.45 10.49 0.000 526 274 2.40 10.49 0.001 52, 274 2.45 10.49 0.000 520 276 2.45 10.60 0.005 520 276 2.45 10.69 0.000 520 276 2.45 10.63 0.001 543 204 2.45 11.71 0.008 543 204 2.45 11.71 0.011 543 204 2.45 11,71 0.000 543 2M4 2.45 11.71 0.007 527 275 2.45 10.56 0.001 520 276 2.45 10.63 0.013 528 276 2.45 10.63 0.002 536-280 2.45 11.19 0.001 536 280 2.45 11.19 0.000 536 260 2.45 11.19 0.000 536 280 2.45 11.19 0.001 549 257 2.45 12.18 0.005 549 267 2.45 12.18 0.000 339 171 2.45 3.12 0.000 Total, U =
0.411 Overall Fen =
0,32 Notes:
: 1. T,,- is the maximum temperature of the two paired load states, and represents the metal (nodal) temperature at the location being analyzed. This.
which is included as '" in the'Translent Maximum Temperatures" table above. determined from the VESLFAT output.
which is included as '" in the'Translent Maximum Temperatures" table above. determined from the VESLFAT output.
: 2. F_ values computed using the low alloy steel equation from Section 3.0 of Reference [6], with S* conservatively set to a maximuinvalue of 0.015, and tha transformed strain rate conservatively set to a minirmumvalue of In (0.001) =-6.90, for ali load pairs.
: 2. F_ values computed using the low alloy steel equation from Section 3.0 of Reference [6], with S* conservatively set to a maximuinvalue of 0.015, and tha transformed strain rate conservatively set to a minirmumvalue of In (0.001) = -6.90, for ali load pairs.
: 3. U_, = [U x HIWCF_ x % HWC) + (Ux NIWCF.,x % NWVC1.
: 3. U_, = [U x HIWC F_ x % HWC) + (U x NIWC F., x % NWVC1.
: 4. T1 and T2 represent the load number for Load #1 and Load #2, respectively, and s l and s2 represent the state number for each of those loads.
: 4. T1 and T2 represent the load number for Load #1 and Load #2, respectively, and s l and s2 represent the state number for each of those loads.
: 5. For each load pair, n- is the number of available cycles for Load #1, n. is the number of available cycles for Load 62. and n Lsthe available number of cycles for the load pair (i.e.. the minimum of n, and nz).
: 5. For each load pair, n-is the number of available cycles for Load #1, n. is the number of available cycles for Load 62. and n Ls the available number of cycles for the load pair (i.e.. the minimum of n, and nz).
File No.: 0801038.306                                                                                                                                                                                           Page 18 of 19 Revision: I F0306-01 RO
File No.: 0801038.306 Revision: I Page 18 of 19 F0306-01 RO


StructuralIntegrity Associates, Inc.
Structural Integrity Associates, Inc.
Table 9: Linearized Stress Files Compiled for VY-RO-StressResults.xls Filename                     Description VY RONTRAN1-S.csv             Transient 1 linearized stress VYRONTRAN2-S.csv             Transient 2 linearized stress VY RON TRAN3-S.csv           Transient 3 linearized stress VY RON TRAN4-S.csv           Transient 4 linearized stress VY RON TRAN5-S.csv           Transient 5 linearized stress VY RON TRAN6-S.csv           Transient 6 linearized stress VY RONTRAN7-S.csv             Transient 7 linearized stress VY RON TRAN8-S.csv           Transient 8 linearized stress VY RON TRAN9-S.csv           Transient 9 linearized stress VYRON_ TRAN1O-S.csv         Transient 10 linearized stress VY RON TRAN11-S.csv         Transient 11 linearized stress VY RONTRAN12-S.csv           Transient 12 linearized stress Note: All files are from the Reference [1] supporting computer files.
Table 9: Linearized Stress Files Compiled for VY-RO-StressResults.xls Filename Description VY RONTRAN1-S.csv VYRONTRAN2-S.csv VY RON TRAN3-S.csv VY RON TRAN4-S.csv VY RON TRAN5-S.csv VY RON TRAN6-S.csv VY RONTRAN7-S.csv VY RON TRAN8-S.csv VY RON TRAN9-S.csv VYRON_ TRAN1O-S.csv VY RON TRAN11-S.csv VY RONTRAN12-S.csv Transient 1 linearized stress Transient 2 linearized stress Transient 3 linearized stress Transient 4 linearized stress Transient 5 linearized stress Transient 6 linearized stress Transient 7 linearized stress Transient 8 linearized stress Transient 9 linearized stress Transient 10 linearized stress Transient 11 linearized stress Transient 12 linearized stress Note: All files are from the Reference [1] supporting computer files.
File No.: 0801038.306                                                                     Page 19 of 19 Revision: 1 F0306-OIRO
File No.: 0801038.306 Revision: 1 Page 19 of 19 F0306-OIRO


Hearing Docket From:                 Travieso-Diaz, Matias F. [matias.travieso-diaz@pillsburylaw.com]
Hearing Docket From:
Sent:                 Tuesday, March 10, 2009 3:02 PM To:                   Alex Karlin; Richard Wardwell; whrcville@embarqmail.com; secy@nrc.gov; Hearing Docket; Susan Uttal; Lloyd Subin; Maxwell Smith; Sarah.hofmann@state.vt.us; aroisman@nationallegalscholars.com; peter.roth@doj.nh.gov; Matthew.Brock@state.ma.us; Zachary Kahn; Mr. Raymond Shadis; OCAAMAIL Resource Cc:                   Lewis, David R.; Nelson, Blake J.
Travieso-Diaz, Matias F. [matias.travieso-diaz@pillsburylaw.com]
Sent:
Tuesday, March 10, 2009 3:02 PM To:
Alex Karlin; Richard Wardwell; whrcville@embarqmail.com; secy@nrc.gov; Hearing Docket; Susan Uttal; Lloyd Subin; Maxwell Smith; Sarah.hofmann@state.vt.us; aroisman@nationallegalscholars.com; peter.roth@doj.nh.gov; Matthew.Brock@state.ma.us; Zachary Kahn; Mr. Raymond Shadis; OCAAMAIL Resource Cc:
Lewis, David R.; Nelson, Blake J.


==Subject:==
==Subject:==
Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc. (Vermont Yankee Nuclear Power Station), Docket No. 50-271-LR, ASLBP No. No. 06-849-03-LR (Part 1 of 3)
Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc. (Vermont Yankee Nuclear Power Station), Docket No. 50-271-LR, ASLBP No. No. 06-849-03-LR (Part 1 of 3)
Attachments:           Letter to ASLB enclosing revised calculations .pdf In accordance with the provisions of the Board's Partial Initial Decision (Ruling on Contentions 2A, 2B, 3, and 4), LBP-08-25, 68 N.R.C.                   _    (Nov. 24, 2008), slip op. at 67,.and the Board's Order (Clarifying Deadline for Filing New or Amended Contentions) (Mar. 9, 2009), Entergy has revised and issued its final calculations of record for the confirmatory environmentally assisted fatigue (CUFen) analyses on the reactor pressure vessel core spray (CS) and recirculation outlet (RO) nozzles at the Vermont Yankee Nuclear Power Station. These revised analyses are presented in the following Structural Integrity Associates, Inc. (SIA) calculations: Calculation No.
Attachments:
Letter to ASLB enclosing revised calculations.pdf In accordance with the provisions of the Board's Partial Initial Decision (Ruling on Contentions 2A, 2B, 3, and 4), LBP-08-25, 68 N.R.C.
(Nov. 24, 2008), slip op. at 67,.and the Board's Order (Clarifying Deadline for Filing New or Amended Contentions) (Mar. 9, 2009), Entergy has revised and issued its final calculations of record for the confirmatory environmentally assisted fatigue (CUFen) analyses on the reactor pressure vessel core spray (CS) and recirculation outlet (RO) nozzles at the Vermont Yankee Nuclear Power Station. These revised analyses are presented in the following Structural Integrity Associates, Inc. (SIA) calculations: Calculation No.
0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.303, Revision 1, "Fatigue Analysis of Reactor Core Spray Nozzle;"
0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.303, Revision 1, "Fatigue Analysis of Reactor Core Spray Nozzle;"
Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle;" Calculation No.
Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle;" Calculation No.
0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle;" and Calculation No. 0801038.306, Revision 1, "Fatigue Analysis of Reactor Recirculation Outlet Nozzle." Calculation 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle" has not been revised so that the version sent to the parties on January 8, 2009 remains the final calculation of record. Entergy is serving at this time electronic copies of those analyses on the parties to the above captioned proceeding.
0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle;" and Calculation No. 0801038.306, Revision 1, "Fatigue Analysis of Reactor Recirculation Outlet Nozzle." Calculation 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle" has not been revised so that the version sent to the parties on January 8, 2009 remains the final calculation of record. Entergy is serving at this time electronic copies of those analyses on the parties to the above captioned proceeding.
The methodology applied in the referenced CS and RO confirmatory analyses is in accordance with the approach-used in the SIA calculations for the feedwater nozzle that were introduced into evidence in this proceeding, and contains no significantly different scientific or technical judgments from those used in the feedwater nozzle calculations. See Calculation 0801038.301 at 4, n.1 and Calculation 0801038.304 at 4, n.1.
The methodology applied in the referenced CS and RO confirmatory analyses is in accordance with the approach-used in the SIA calculations for the feedwater nozzle that were introduced into evidence in this proceeding, and contains no significantly different scientific or technical judgments from those used in the feedwater nozzle calculations. See Calculation 0801038.301 at 4, n.1 and Calculation 0801038.304 at 4, n.1.
As set forth in the referenced revised calculations, the limiting calculated                 CUFenS for the CS and RO nozzles are less than unity and are therefore acceptable.
As set forth in the referenced revised calculations, the limiting calculated CUFenS for the CS and RO nozzles are less than unity and are therefore acceptable.
Hard copies are also being sent today by overnight mail to the NRC Staff, the New England Coalition and the Vermont Department of Public Service.
Hard copies are also being sent today by overnight mail to the NRC Staff, the New England Coalition and the Vermont Department of Public Service.
1
1
Line 1,158: Line 3,013:
This submittal comprises three electronic messages. This first message, attaching Entergy's cover letter, is being transmitted to the entire service list. The second message, comprising the calculation package for the CS nozzle, is being transmitted only to the parties (including interested States). The third message, comprising the calculation package for the RO nozzle, is being forwarded only to the parties (including interested States).
This submittal comprises three electronic messages. This first message, attaching Entergy's cover letter, is being transmitted to the entire service list. The second message, comprising the calculation package for the CS nozzle, is being transmitted only to the parties (including interested States). The third message, comprising the calculation package for the RO nozzle, is being forwarded only to the parties (including interested States).
If you have any difficulty opening this attachment, please contact me at the number below.
If you have any difficulty opening this attachment, please contact me at the number below.
Matias F. Travieso-Diaz I Pillsbury Winthrop Shaw Pittman LLP Tel: 202.663.8142 I Fax: 202.663.8007 I Cell: 703.472.6463 2300 "N"Street, NW I Washington, DC 20037-1122 Email: matias.travieso-diaz(cpillsburylaw.com-Bio: www.pillsburylaw.com/matias.travieso-diaz
Matias F. Travieso-Diaz I Pillsbury Winthrop Shaw Pittman LLP Tel: 202.663.8142 I Fax: 202.663.8007 I Cell: 703.472.6463 2300 "N" Street, NW I Washington, DC 20037-1122 Email: matias.travieso-diaz(cpillsburylaw.com-Bio: www.pillsburylaw.com/matias.travieso-diaz
* Internal Revenue Service regulations generally provide that, for the purpose of avoiding federal tax penalties, a taxpayer may rely only on formal written advice meeting specific requirements. Any tax advice in this message does not meet those requirements. Accordingly, any such tax advice was not intended or written to be used, and it cannot be used, for the purpose of avoiding federal tax penalties that may be imposed on you or for the purpose of promoting, marketing or recommending to another party any tax-related matters.
* Internal Revenue Service regulations generally provide that, for the purpose of avoiding federal tax penalties, a taxpayer may rely only on formal written advice meeting specific requirements. Any tax advice in this message does not meet those requirements. Accordingly, any such tax advice was not intended or written to be used, and it cannot be used, for the purpose of avoiding federal tax penalties that may be imposed on you or for the purpose of promoting, marketing or recommending to another party any tax-related matters.
2
2


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==Subject:==
==Subject:==
Line 1,181: Line 3,036:
From: "Travieso-Diaz, Matias F." <matias.travieso-diaz@pillsburylaw.com>
From: "Travieso-Diaz, Matias F." <matias.travieso-diaz@pillsburylaw.com>
To: <ask2@nrc.gov>, <rew@nrc.gov>, <whrcville@embarqmail.com>, <secy@nrc.gov>,
To: <ask2@nrc.gov>, <rew@nrc.gov>, <whrcville@embarqmail.com>, <secy@nrc.gov>,
        <hearingdocket@nrc.gov>, <susan.uttal@nrc.gov>, <Ibs3@nrc.gov>,
<hearingdocket@nrc.gov>, <susan.uttal@nrc.gov>, <Ibs3@nrc.gov>,
        <maxwell.smith@nrc.gov>, <Sarah.hofmann@state.vt.us>,
<maxwell.smith@nrc.gov>, <Sarah.hofmann@state.vt.us>,
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<Matthew. Brock@state.ma.us>, <zachary.kahn@nrc.gov>, "Mr. Raymond Shadis"
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CC: "Lewis, David R." <david.lewis@pillsburylaw.com>, "Nelson, Blake J."
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Latest revision as of 12:41, 14 January 2025

Final Calculations of Record for the Confirmatory Environmentally Assisted Fatigue (Cufen) Analyses on the Reactor Pressure Vessel Core Spray (CS) and Recirculation Outlet (RO) Nozzles at Vermont Yankee
ML090840422
Person / Time
Site: Vermont Yankee File:NorthStar Vermont Yankee icon.png
Issue date: 03/10/2009
From: Travieso-Diaz M
Entergy Nuclear Vermont Yankee, Entergy Operations, Pillsbury, Winthrop, Shaw, Pittman, LLP
To: Karlin A, Wendy Reed, Richard Wardwell
Atomic Safety and Licensing Board Panel
SECY RAS
References
50-271-LR, ASLBP 06-849-03-LR, RAS M-411
Download: ML090840422 (119)
v • d • e


Text

1) A i

t I

ti COPY 2300 N Street, N.W.

Tel 202.663.8000 Washington, D.C. 20037-1 128 F~ax 202.663.8007 www.pillsburylaw.coni MATIAS F. TRAVwEso-DIAZ 202-663-8142 DOCKETED Matias.travieso-diaz@pillsburylaw.comn USNRC March 10, 2009 (3:02pm)

March 10, 2009 OFFICE OF SECRETARY RULEMAKINGS AND ADJUDICATIONS STAFF Alex S. Karlin, Esq., Chairman Administrative Judge Atomic Safety and Licensing Board Dr. William H. Reed Mail Stop T-3 F23 Atomic Safety and Licensing Board U.S. Nuclear Regulatory Commission Mail Stop T-3 F23 Washington, D.C. 20555-0001 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 Administrative Judge Dr. Richard E. Wardwell Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, D.C. 20555-0001 In the Matter of Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc.

(Vermont Yankee Nuclear Power Station)

Docket No. 50-271-LR; ASLBP No. 06-849-03-LR Gentlemen:

In accordance with the provisions of the Board's Partial Initial Decision (Ruling on Contentions 2A, 2B, 3, and 4), LBP-08-25, 68 N.R.C.

(Nov. 24, 2008), slip op. at 67, and the Board's Order (Clarifying Deadline for Filing New or Amended Contentions) (Mar. 9, 2009),

Entergy has revised and issued its final calculations of record for the confirmatory environmentally assisted fatigue (CUFen) analyses on the reactor pressure vessel core spray (CS) and recirculation outlet (RO) nozzles at the Vermont Yankee Nuclear Power Station. These revised analyses are presented in the following Structural Integrity Associates, Inc. (SIA) calculations: Calculation No. 0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.303, Revision 1, "Fatigue Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle;" Calculation No.

0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle;" and Calculation No. 0801038.306, Revision 1, "Fatigue Analysis of Reactor Recirculation Outlet Nozzle." Calculation 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle" has not been revised so that the version sent to the parties on January 8, 2009 remains the final calculation of record.

O37~

T-o

-5

March 10, 2009 Page 2 Entergy is serving at this time electronic copies of those analyses on the parties to the above captioned proceeding. Hard copies are also being sent today by overnight mail to the NRC Staff, the New England Coalition and the Vermont Department of Public Service.

The methodology applied in the referenced CS and RO confirmatory analyses is in accordance with the approach used in the SIA calculations for the feedwater nozzle that were introduced into evidence in this proceeding, and contains no significantly different scientific or technical judgments from those used in the feedwater nozzle calculations. See Calculation 0801038.301 at 4, n.1 and Calculation 0801038.304 at 4, n. 1.

As set forth in the referenced revised calculations, the limiting calculated CUFenS for the CS and RO nozzles are less than unity and are therefore acceptable.

Sincerely, Matias F. Travieso-Diaz Counsel for Entergy cc: Service List Pillsbury Winthrop Shaw Pittman LLP

CERTIFICATE OF SERVICE I hereby certify that copies of the foregoing letter were served on the persons listed below by deposit in the U.S. Mail, first class, postage prepaid; where indicated by an asterisk, by electronic mail; and where indicated by a double asterisk, by both overnight and electronic mail, this 1 0 th day of March, 2009.

  • Administrative Judge Alex S. Karlin, Esq., Chairman Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 ask2(@nrc.gov
  • Administrative Judge Dr. William H. Reed 1819 Edgewood Lane Charlottesville, VA 22902 whrcville(ieinbarqmail.com
  • Office of Commission Appellate Adjudication Mail Stop 0-16 C1 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 OCAAmaila~nrc.gov
  • Lloyd Subin, Esq.
  • Susan L. Uttal, Esq.
  • Maxwell C. Smith, Esq.

Office of the General Counsel Mail Stop O-15-D21 U.S. Nuclear Regulatory Commission Washington, D.C. 20555-0001 LBS3@(cnrc.gov; susan.uttal(ynrc.gov; maxwell.smith(ai)nrc. gov

  • Administrative Judge Dr. Richard E. Wardwell Atomic Safety and Licensing Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 rew(anrc.gov
  • Secretary Att'n: Rulemakings and Adjudications Staff Mail Stop 0-16 CI U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 secy(anrc.gov, hearingdocket(Dnrc. gov Atomic Safety and Licensing.Board Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001
    • Sarah Hofmann, Esq.

Director of Public Advocacy Department of Public Service 112 State Street - Drawer 20 Montpelier, VT 05620-2601 Sarah.hofinann(state.vt.us Pillsbury Winthrop Shaw Pittman LLP

    • Anthony Z. Roisman, Esq.

National Legal Scholars Law Firm 84 East Thetford Road Lyme, NH 03768 aroisman(-,nationalleaalscholars.com

    • Raymond Shadis 37 Shadis Road PO Box 98 Edgecomb, ME 04556 shadis(lprexar.comr
  • Peter L. Roth, Esq.

Office of the New Hampshire Attorney General 33 Capitol Street Concord, NH 03301 Peter.roth(adoi.nh.gov

  • Matthew Brock, Esq.

Assistant Attorney General Environmental Protection Division Office of the Attorney General One Ashburton Place, 18th Floor Boston, MA 02108 Matthew.Brocke,state.ma.us

  • Zachary Kahn, Esq.

Atomic Safety and Licensing Board Panel Mail Stop T-3 F23 U.S. Nuclear Regulatory Commission Washington, DC 20555-0001 zachary.kalmn(arc. gov Matias F. Tr*avieso-Diaz Pillsbury Winthrop Shaw Pittman LLP

V Structural Integrity Associates, Inc.

File No.: 0801038.302 CALCULATION PACKAGE Project No.: 0801038 Quality Program E Nuclear E-Commercial PROJECT NAME:

VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:

10163217 Amendment 5 CLIENT:

PLANT:

Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:

Stress Analysis of Reactor Core Spray Nozzle Document Affected Project Manager Preparer(s) &

DocumentsAfted Revision Description Approval Checker(s)

Revision Pages Signature & Date Signatures & Date 01

- 15 Initial issue.

Gary L. Stevens Tyler D. Novotny Computer Files 01/06/09 01/06/09 Jennifer D. Correa

.01/06/09 1

1-3,7-8,11 Revised per summary

/

Preparer:

contained in Section 1.1.

/

&1t@

/

Computer Files Changes are marked with revision bars" in right-Stevens hand margin.

03/09/09 Tyler D. Novotny 03/09/09 Checker:

Tim D. Gilman 03/09/09 Page 1 of 15 F0306-O1RO

Structural Integrity Associates, Inc.

Table of Contents 1.0 O B JE C T IV E................................................................................................................................

3 1.1 Changes Made in Revision 1 of this Calculation...........................................................

3 2.0 METHODOLOGY..............................................................................................................

3 3.0 ASSUMPTIONS / DESIGN INPUTS.....................................................................................

3 4.0 C A L C U L A T IO N S........................................................................................................................

3 4.1 Finite Element Unit Pressure Stress Analysis...............................

3 4.2 Thenr al Transient Stress Analysis................................................................................

4 4.3 Determining Critical Stress Paths.................................................................................

.5 4.4 Stress C alculation..........................................................................................................

5 4.5 P ip in g L o ad s..............................

7 5.0 RESULTS OF ANALYSIS.....................................................................................................

8 6.0 R E FE R E N C E S............................................................................................................................

8 List of Tables Table 1: Pressure Results (1,000 psi).............................................................................................

6 Table 2: Stresses Under Unit Pressure Load, psi...................................

9 Table 3: Membrane Plus Bending Stresses Due to Piping Loads................................................

10 Table 4: Example Thermal Stress Result Output, psi.....................................................................

11 List of Figures Figure 1. Core Spray Nozzle Internal Pressure Distribution.......................

12 Figure 2. Core Spray Nozzle Pressure Cap Load & Boundary Condition..................

13 Figure 3. Core Spray Nozzle Vessel Wall Boundary Condition 14 Figure 4. Lim iting Stress Paths.................................

15 FileNo.: 0801038.302 Page 2 of 15 Revision: 1 F0306-01RO

VStructural Integrity Associates, Inc.

1.0 OBJECTIVE The objective of this calculation package is to obtain stress distributions for the reactor pressure vessel (RPV) core spray (CS) nozzle at the Vermont Yankee Nuclear Power Station. ANSYS [1]

thernal transient and pressure stress analyses are performed, along with calculation of stresses due to attached piping loads. The stress results will be used for a subsequent ASME Code,Section III NB-3200 [2] fatigue usage calculation.

1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision 1 of this calculation:

a. All changes marked throughout this calculation are editorial changes made to the text of the calculation package.

2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package

[3]. A previously developed finite element model (FEM) [3] of the CS nozzle is used to perform thermal and pressure stress analyses using ANSYS [1]. A thermal transient analysis is performed for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads. For these loads, unit load analyses (based on finite element analysis for pressure and manual calculations for attached piping loads) are performed. All six components of the stress tensor are determined in the stress calculations.

The fatigue usage calculation and environmental fatigue usage analysis will be performed in a separate calculation package. That subsequent calculation will utilize the thermal and pressure stresses determined in this calculation, along with stresses due to attached piping loads provided in Table 3. The stresses due to pressure and the attached piping loads will be scaled based on the temperature and pressure magnitudes during each individual transient, and the location being analyzed. From the Reference [3] calculation, the FEM includes a factor of two on the modeled RPV radius to account for the 3-D effects of two intersecting cylinders at the nozzle blend radius location.

3.0 ASSUMPTIONS / DESIGN INPUTS Assumptions and design inputs were previously established in Section 3.1 of the Reference [3]

calculation.

4.0 CALCULATIONS 4.1 Finite Element Unit Pressure Stress Analysis A uniform pressure of 1,000 psi was applied to the FEM along the inside surface of the CS nozzle and the RPV wall (Figure 1). A pressure load of 1,000 psi was used because it is easily scaled up or FileNo.: 0801038.302 Page 3 of 15 Revision: 1 F0306-O1RO

Structural Integrity Associates, Inc.

down to account for different pressures that occur during transients. In addition, a membrane stress "cap load" was applied to the modeled end of the piping attached to the core spray nozzle safe end.

This membrane stress was calculated as follows:

p* Di2 cap 2

2 Do - Di where:

P = Pressure = 1,000 psi unit load Di= Inner Diameter at end of model = 9.834 in Do = Outer Diameter at end of model = 10.815 in Therefore, the membrane stress is 4,774 psi. The calculated value is given a negative sign in order for it to exert tension on the piping end of the model. The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, input file VYCSNGEOMINP].

The ANSYS input file VY 16Q_P.INP, as obtained from Appendix A of Reference [5], contains the pressure loading. Figure 1 shows the applied 1,000 psi internal pressure distribution. At the vessel wall, a symmetric boundary condition is applied. At the piping end of the model, axial displacement is coupled to simulate the effect of the attached piping that is not modeled. Figure 2 and Figure 3 show the boundary conditions.

4.2 Thermal Transient Stress Analysis The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, file VYCSNGEOM.INP], and is used as input to the files in which the thermal transient and pressure stress analyses are performed.

For the thermal transient ANSYS analyses, previously defined thernal transients [3, Table 2] are evaluated, applying heat transfer coefficients [3, Tables 4 through Table 18], as appropriate, based on the flow rates for each individual transient.

Each thermal transient is evaluated in ANSYS to determine the resulting temperature distributions.

The thermal results are used as input for the stress analysis for each transient. The boundary conditions used for the pressure load case were also applied to the thermal stress cases. Figure 2 and Figure 3 show the application of these boundary conditions.

All ANSYS input files for the thennal analyses, as listed below, are saved in the project computer files:

VY_CSNGEOM.INP: Geometry and material properties VY_16QTRAAN2-T.INP, VY 16QTRAN2-S.INP: Transient 2, thermal and stress analyses VY_16QTRAN3-T.INP, VY 16QTRAN3-S.INP: Transient 3, thermal and stress analyses VTY_ 6QTRAN11-T.INP, VYI 16QTRAN11-S.INP: Transient 11, thermal and stress analyses FileNo.: 0801038.302 Page 4 of 15 Revision: I F0306-O1RO

Structural Integrity Associates, Inc.

VY_16QTRAN14-T.JNP, VY 16QTRAN14-S.INP: Transient 14, thermal and stress analyses VYý_]6QTRAN21-23-T.INP, VY_ 6Q_TRAN21-23-S.INP: Transient 21-23, thermal and stress analyses VY_16QTRAN24-T.INP, VY 16QTRAN24-S.JNP: Transient 24, thermal and stress analyses VY_16QTRAN30-T.INP, VY 16QTRAN30-S.INP: Transient 30, thermal and stress analyses 4.3 Determining Critical Stress Paths From Section 4.0 of Reference [5], the critical location in the safe end was determined to be at Node 3719. This location was selected since it possessed the highest stress intensity during the worst case thermal transient.

Also from Section 4.0 of Reference [5], the critical stress location in the nozzle blend radius was chosen based upon the highest pressure stress (which is controlling in the nozzle blend radius). The pressure stress results showed the critical location in the nozzle blend radius to be at Node 2166.

Figure 4 shows the two critical stress paths that will be used to find the linearized stresses at the safe end and nozzle blend radius.

4.4 Stress Calculation Linearized stresses from Node 3719 (safe end inside surface) and Node 2166 (nozzle blend radius inside surface of base metal) are used for the fatigue usage analysis, as shown in Figure 4. For the nozzle blend radius location, the stresses used are for the base metal only; the cladding material is unselected prior to stress extraction.

The pressure stress intensities for the safe end and blend radius paths were extracted using the ANSYS file VY_]6QP.INP. This produced one file, PRESSURE. lin, which contains results of the critical stress paths.

Table 1 shows the final pressure results for the safe end and blend radius. These results are slightly different from those reported in Table 14 of Reference [5] as a result of the revised material properties (i.e., temperature dependent material properties were used in the current evaluation vs. constant material properties in Reference [5]).

FileNo.: 0801038.302 Page 5 of 15 Revision: 1 F0306-O1RO

VStructural Integrity Associates, Inc.

Table 1: Pressure Results (1,000 psi)

Membrane plus Total Stress Location Bending Stress Intensit Intensity (psi)

(psi)

Safe End 12,030 12,070 Blend Radius 30,720 36,150 Results were also extracted from the vessel portion of the model to verify the accuracy of the results obtained from the ANSYS model, and to check the results due to the use of the 2.0 multiplier on the vessel radius. These results are contained in the file PRESSURE. lin. The radius of the finite element model (FEM) was multiplied by a factor of 2.0 [3] to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is the intersection of two cylinders.

The equation for the membrane hoop stress in a sphere is:

(pressure) x (radius) 2 x thickness Considering a vessel base metal radius, R, of 105.906 inches increased by a factor of 2.0, a vessel base metal thickness, t, of 5.4375 inches, and an applied pressure, P, of 1,000 psi, the calculated stress for a sphere is PR/(2t) = 19,477 psi. This compares very well with the remote vessel wall membrane hoop stress from the ANSYS result file, PRESSURE.lin, of 18,960 psi. Thus, considering the peak total pressure stress of 36,150 psi reported above, the stress concentrating effect of the nozzle comer is 36,150/19,477 = 1.86. In other words, the peak nozzle comer stress is 1.86 times higher than nominal vessel wall stress for the axisymmetric model.

The equation for the membrane hoop stress in a cylinder is:

((pressure) x (radius))

thickness I Based on the previous dimensions, the calculated stress for a cylinder without the 2.0 factor is 19,477 psi. Increasing this by a factor of 1.86 yields an expected peak nozzle comer stress of 36,227 psi, which would be expected from a cylindrical geometry that is representative of the nozzle configuration. Therefore, the result from the ANSYS file for the peak nozzle comer stress (36,150 psi) is close to the peak nozzle comer stress for a cylindrical geometry because of the use of the 2.0 File No.: 0801038.302 Page 6 of 15 Revision: 1 F0306-OIRO

Structural Integrity Associates, Inc.

multiplier. This is consistent with SI's experience where a factor of two increase in radius is typical for representing the 3-D effect in an axisymmetric model.

4.5 Piping Loads The piping loads per Reference [4] are as follows:

F, = 2,500 lbs Mx= 264,000 in-lb Fy = 4,600 lbs My= 85,200 in-lb F, = 1,700 lbs Mz= 105,600 in-lb The point of loads application is at the intersection between the safe end-to-pipe weld [4, 61]

Therefore, the safe end critical location is 0.303 inches and the nozzle blend radius is 30.817 inches from the load application point. (The nozzle blend radius location was measured from approximately the middle of the critical stress path for the blend radius and applied to the inside blend radius location along the critical stress path.) From general structural mechanics, the membrane plus bending stresses at the inside surface of a thick-walled cylinder are:

cyzl = axial stress due to axial force = Fz/A cy, = axial stress due to bending moment = Mxy(ID/2)/I (z =

Tzl 5"z2

,re = shear stress due to torsion = Mz(ID/2)/J z = shear stress due to shear force = 2Fxy/A, where Fx, Fy, Fz, M,, My, and Mz are forces and moments at the pipe-to-safe end weld M* = moment about x axis translated by length z = -L = M, - Fy L MyL = moment about y axis translated by length z = -L = My + Fx L Mxy = resultant bending moment = (MxL 2 + MyL2)0.5 Fxy = resultant shear force = (Fx2 + Fy2)0.5 ID, OD = inside and outside diameters A = area of cross section = (it/4)(OD 2 - ID2)

I = moment of inertia = (7/64)(OD 4 - ID 4)

J = polar moment of inertia = (7/32)(0D4 - ID4)

The piping load stress calculations for these locations are shown in Table 3.

The piping loads tabulated in and pictorially shown in Reference [4] were applied by CB&I at the safe end-to-pipe weld. Refer to Reference [6], page 9 of 13; CB&I RPV Stress Report, Section S7.

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5.0 RESULTS OF ANALYSIS A thermal transient analysis for each defined transient, as well as unit pressure stress and piping interface load analyses were performed for the CS nozzle at Vermont Yankee. All six components of the stress tensor were extracted from the ANSYS model at the two limiting path locations. Table 2 provides the unit pressure stress analysis results. The unit pressure load results are used to choose the location to analyze at the nozzle blend radius and will be scaled up or down based on applied pressures for the final fatigue analysis. Table 3 provides the piping stresses at the two critical locations. Table 4 shows an example of thermal stress results. The remaining thermal stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:

PRESSURE. lin: Unit pressure stress analysis results VY_16QTRAN2-S. lin: Transient 2, thermal stress analysis results VY_ 6QTRAN3-S. lin: Transient 3, thermal stress analysis results VY_16QTRANll-S.lin: Transient 11, thermal stress analysis results VY_16QTRAN14-S.lin: Transient 14, thernal stress analysis results VY_16QTRAN21-23-S. lih: Transient 21-23, thermal stress analysis results VY_16QTRAN24-S. lin: Transient 24, thermal stress analysis results VY_]6Q TRAN3 0-S. lin: Transient 30, thermal stress analysis results A fatigue calculation using the methodology of Subarticle NB-3200 of Section III of the ASME Code [2] and an environmental fatigue usage analysis will be performed in a separate calculation package using the stress results from this calculation.

The results of this calculation are used in a subsequent SIA Calculation No. 0801038.303, "Fatigue Analysis of Core Spray Nozzle."

6.0 REFERENCES

1. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
2. ASME Boiler and Pressure Vessel Code,Section III, Subsection-NB, 1998 Edition with 2000 Addenda.
3. SI Calculation No. 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle."
4. VY Drawing 5920-0024, Revision 11, Sht. No. 7, "Reactor Vessel," (GE Drawing No.

919D294), SI File No. VY-05Q-241.

5. SI Calculation No. VY-16Q-309, Revision 1, "Core Spray Nozzle Green's Functions."
6. Entergy Design Input Record (DIR), Rev. 1, EC No. 1773, Rev. 0, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-16Q-209.

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Table 2: Stresses Under Unit Pressure Load, psi Membrane plus Bending Total Node S

SY Sz Sxy Syz Sxz SX S

Sz Sxy Syz Sxz SafeEnd 3719

-1011 4829 11010

-104.8 0

0

-1011 4912 11050

-85.31 0

0 Blend Radius 2166

-1052 1657 25960 4886 0

0

-1052 1720 35050 348.9 0

0 FileNo.: 0801038.302 Revision: 1 Page 9 of 15 F0306-01RO

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Table 3: Membrane Plus Bending Stresses Due to Piping Loads Safe End Blend Radius Fx, kip 2.5 2.5 Fy, kip 4.6 4.6 F,, kip 1.7 1.7 Mx, kip-in 264 264 My, kip-in 85.2 85.2 M,, kip-in 105.6 105.6 L, in 0.30 30.82 MxL, kip-in 262.61 122.24 MyL, kip-in 85.96 162.24 MxY, kip-in 276.32 203.14 Fy,, kip-in 5.24 5.24 OD, in 10.82 24.25 ID, in 9.834 12.125 A, in2 15.91 346.40 I, in4 212.46 15914.32 J, in4 424.93 31828.64 a.,, ksi 0.107 0.005 az2, ksi 6.395 0.077 oz, ksi 6.502 0.082 "ro, ksi 1.222 0.020 cz, ksi 0.658 0.030 Note: The axial and shear stresses are expressed in a local coordinate system with r radial (X in ANSYS coordinates), 0 circumferential (Z in ANSYS coordinates), and Z axial (Y in ANSYS coordinates) components with respect to the nozzle centerline.

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Table 4: Example Thermal Stress Result Output, psi Transient Node Time Membrane Plus Bending Total I I (s)

I.Sx Sy Sz Sxy Syz Sxz' Sx Sy Sz Sxy Syz Sxz 3719 0

10.002 123.23 1716.1 6984.8 7946.2 8919 16055 16164 16304 19448 20622 29155 32155 40155 50155 65155 66165 48 49 52 124 380 430 482 845

-849 850 851 851 851 851 851 851 851 851 288 280 197 467 1918 2206 2506 4684 4707 4831 5001 5002 5002 5002 5002 5002 5002 5002 696 689 644 1587 5199 5907 6638 11830 11880 12000 12110 12110 12110 12110 12110 12110 12110 12110

-50

-50

-53

-123

-385

-436

-489

-857

-861

-864

-870

-870

-870

-870

-870

-870

-870

-870 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 48 49 52 124 380 430 482 845 849 850 851 851 851 851 851 851 851 851

-11

-131

-293

-358

-365

-371

-352

-352

-219

-45

-44

-44

-44

-44

-44

-44

-44 641

-86 630

-86 561

-89 1413

-212 4733

-663 5384

-752 6056

-843 10830

-1487 10880

-1494 11020

-1500 11140

-1506 11140

-1506 11140

-1506 11140

-1506 11140

-1506 11140

-1506 11140

-1506 11140

-1506 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 3

2166 0

10.002 123.23 1716.1 6984.8 7946.2 8919 16055 16164 16304

.19448 20622 29155 32155 40155 50155 65155 66165 86

-140 87

-141 109

-210 310

-1469 794

-2777 882

-3032 973

-3298 1553

-5119 1562

-5143 1545

-5079 1433

-3608 1422

-3508 1409

-3451 1409

-3452 1409

-3452 1409

-3452 1409

-3452 1409

-3452 1025 1030 1224 2676 8114 8912 9762 14660 14730 14620 14270 14050 13540 13520 13510 13510 13510 13510 44 44 60 359 775 812 859 1049 1051 1032 632 566 461 459 458 458 458 458 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 87 109 310 794 882 973 1553

-18930 1562

-19040 1545

-18980 1433

-18220 1422

-18180 1409

-18140 1409

-18140 1409

-18140 1409

-18140 1409

-18140 1409

-18140 1409

-18140

-1084

-1242

-3331

-9114

-10220

-11350

-628

-68

-955

-70

-4776

-184

-9547

-537

-10520

-607

-11470

-678

-18300

-1177

-18390

-1184

-18070

-1190

-14130

-1169

-13900

-1169

-13810,

-1173

-13810

-1173

-13810

-1173

-13810

-1173

-13810

-1173

-13810

-1173

-13810

-1173 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 0

0 Note: Not all time steps are listed in this table.

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Figure 1. Core Spray Nozzle Internal Pressure Distribution File No.: 0801038.302 Revision: 1 Page 12 of 15 F0306-O1RO

Structural Intearity Associates, Inc.

  • Structurai Integrity Associates, inc.

Core Spray Nozzle Finite Element Model Figure 2. Core Spray Nozzle Pressure Cap Load & Boundary Condition File No.: 0801038.302 Revision: 1 Page 13 of 15 F0306-01RO

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Core Spray Nozzle Finite Element Model Figure 3. Core Spray Nozzle Vessel Wall Boundary Condition FileNo.: 0801038.302 Revision: 1 Page 14 of 15 F0306-O1RO

V Structural Integrity Associates, Inc.

V~~~~rd~N dpa

-0:1 pi3t l~~l NodE 2166 C-r

$pray :hzerirnre zl--es

-o1q, Figure 4. Limiting Stress Paths FileNo.: 0801038.302 Revision: 1 Page 15 of 15 F0306-01RO

J V Structural Integrity Associates, Inc. File No.: 0801038.303 Project No.: 0801038, CALCULATION PACKAGE

,Quality Program Z Nuclear L! Commercial PROJECT NAME:

VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:

10163217 Amendment 5 CLIENT:

PLANT:

Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:

Fatigue Analysis of Reactor Core Spray Nozzle, Document Affected Project Manager Preparer(s) &

Revision Pages Revision Description Approval Checker(s)

Signature & Date Signatures & Date 0

1 - 18 Initial issue.

Gary L. Stevens Tyler Novotny Computer Files.

01/06/09 01/06/09 W. F. Weitze 01/06/09 1

1-3, 5-8, 11-12, Revised per summary Preparer:

17-18 contained in Section 1.1.

/

Changes are marked with Gary L. Stevens Computer Files.

"revision bars" in right-hand margin.

03/09/09 Tyler D. Novotny 03/09/09 Checker:

Tim D. Gilman 03/09/09 Page 1 of 18 F0306-O1RO

VStructural Integrity Associates, Inc.

Table of Contents 1.0 O B JE C T IV E.................................................................................................................................

3 1.1 Changes Made in Revision 1 of this Calculation...........................

3 2.0 M E TH O D O L O G Y...........................................................................................

................... 3 3.0 D E SIG N IN P U T S.........................................................................................................................

3 3.1 Stress C alculation..........................................................................................................

3 3.2 Fatigue U sage A nalysis, General..................................................................................

4 3.3 Event Cycles, V ESLFA T...............................................................................................

4 3.4 M aterial Properties, VESLFA T.....................................................................................

5 3.5 Stress Indices.............................................................................................................

5 4.0 C A L C U L A T IO N S.........................................................................................................................

6 5.0 RESULTS OF ANALYSIS.............................................

7

6.0 CONCLUSION

S AND DISCUSSIONS...............................................................................

7 7.0 R E FE R E N C E S.............................................................

8 List of Tables Table 1: Safe End Load Sets as Input to VESLFAT.......................................................................

9 Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT.......................................................

10 Table 3: Temperature-Dependent Material Properties for VESLFAT....................

11 Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves....................

12 Table 5: Pressure and Attached Piping Unit LoadCase Stress Components.................................

13 Table 6: Fatigue Usage Calculation for the Safe End (Inconel).......

13 Table 7: Fatigue Usage Calculation for the Safe End (Stainless Steel)..........................................

14 Table 8: Fatigue Usage Calculation for the Nozzle Blend Radius 15 Table 9: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location........................

16 Table 10: Linearized Stress Files Compiled for VY-StressResults.xls......................

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1.0 OBJECTIVE The objective of this calculation package is to perform an ASME Code,Section III fatigue usage evaluation and a plant-specific evaluation of reactor water environmental effects for the reactor pressure vessel (RPV) core spray (CS) nozzle at the Vermont Yankee Nuclear Power Station.

1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:

a. Changed Reference [1] to reflect revision of that document.
b. All other changes marked throughout this calculation are editorial changes made to the text of the calculation package.

2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package

[2]. Based on that methodology, thermal stresses, pressure stresses, and attached piping load stresses were developed in the Reference [1] calculation for use in a fatigue calculation. The thermal stresses are added to pressure stresses and attached piping load stresses1. Both the pressure and piping' load stresses are scaled based on the magnitudes of the pressure and nozzle temperature during each transient. All six components of the stress tensor from the stress results are used in the fatigue calculation.

The fatigue calculation is performed for both of the limiting safe end and nozzle blend radius locations, as determined in the Reference [1] calculation, and uses the methodology of Subarticle NB-3200 of Section III of the ASME Code [3]. An environmental fatigue usage analysis is also performed in this calculation applying the methodology described in Reference [6].

3.0 DESIGN INPUTS 3.1 Stress Calculation Linearized stress components at Node 3719 (limiting safe end path at inside surface) and Node 2166 (limiting nozzle blend radius path at inside surface) are used for the fatigue usage calculation, as shown in Figure 4 of Reference [1]. For the nozzle blend radius location, the stresses used in the evaluation are for the base metal only; that is, the cladding material is unselected prior to stress extraction. The stress components from the thermal stress analyses are combined with stress components due to pressure and piping loads. The linearized thermal stress components for each Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 70'F and the full values are reached at a reactor design temperature of 575F [2, Assumption 3.1.7]. In addition, design seismic and deadweight loads are also included and scaled in combination with the thermal loads for each transient. This combination, coupled with assigning the stress due to these loads the same sign as the thermal stress, is considered to be a very conservative treatment of the loads overall in that deadweight and design seismic loads are considered and scaled for every transient.

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transient are taken from the relevant output files associated with the Reference [1] calculation (a sample of which was provided in Table 4 of Reference [1]). The unit pressure stress component results are taken from Table 2 of Reference [1]. Piping load stress components are taken from Table 3 of the Reference [I] calculation.

3.2 Fatigue Usage Analysis, General Structural Integrity's VESLFAT program [4] is used to perform the fatigue usage calculation in accordance with the fatigue usage portion of ASME Code Subarticle NB-3200 [3]. VESLFAT performs the analysis required by NB-3222.4(e) [3] for Service Levels A and B conditions defined by the user. The VESLFAT program computes the primary-plus-secondary and total stress ranges for all events and performs a correction for elastic-plastic analysis, if necessary.

The program computes the stress intensity range based on the stress component ranges for all event pairs [3, NB-3216.2]. The program evaluates the stress ranges for primary-plus-secondary and primary-plus-secondary-plus-peak stresses based on all six components of stress (3 normal and 3 shear stresses). If the primary-plus-secondary stress intensity range is greater than 3 Sm, the total stress range must be increased by the simplified elastic-plastic strain correction factor Ke, as described in NB-3228.5 [3]. The design stress intensity, Sm, is specified as a function of temperature. The input maximum temperature for both states of a load set pair is used to determine the temperature that Sm is determined from the user-defined values.

When more than one stress set is defined for either of the event pair loadings, the stress differences are determined for all of the potential stress pairs, saving the maximum for the event pair, based on the pair producing the largest alternating total stress intensity (Salt), including any effects of Ke. The principal stresses for the stress ranges are determined by solving for the roots of the following cubic equation2:

S3 _ (aix "+ aiy +k (iz)S2 -+- ((x (y y + a (y (iz + (iz U, - Sxyz -x2

-X 2 _ yz2 )S

- ((Fxa (y Uz + 2 rxy Txz T"yz - Uz Cxy

-2 (y Txz -_ax Tyz )

0 The stress intensities for the event pairs are reordered in decreasing order of Salt, including a correction for the ratio of modulus of elasticity (E) from the fatigue curve divided by E from the material evaluated at the maximum event temperature. This allows a fatigue table to be created to eliminate the number of cycles available for each of the transient events. This fatigue table is based on a worst-case progressive pairing of events in order of the most severe alternating stress to the least severe, allowing determination of a bounding fatigue usage per NB-3222.4(e) [3]. For each load set pair in the fatigue table, the allowable number of cycles is determined based on Salt.

3.3 Event Cycles, VESLFAT For the Vermont Yankee CS nozzle analysis, transients that consist of combined stress ramps are split so that each successive ramp is treated separately. Therefore, there are 25 load sets based on the combined stress changes for the safe end, and 27 load sets based on the combined stress changes 2 Note that a., a,, a,, etc. are used synonymously with S,, S,,, S., etc., in this calculation.

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for the nozzle blend radius location. The reason the number of load sets are not equal for each path is because the time history stress results of those paths differ. Tables 1 and 2 show the load sets applicable to plant operation, with cycle counts per Table 2 of Reference [2], used as input to VESLFAT for the safe end and nozzle blend radius locations, respectively. The cycle counts of Reference [2] consider 60 years of operation; see Reference [8] for the numbers of cycles. The data from Table I is entered into the VESLFAT input files VY-VFA T-1I. CYC (safe end-Inconel) and VY-VFAT2-1I. CYC (safe end-Stainless Steel), and the data from Table 2 is entered into the. file VY-VFA T-21. CYC (nozzle blend radius).

3.4 Material Properties, VESLFAT Material properties are entered in VESLFAT input files VY-VFAT-]1.FDT (safe end-Inconel), VY-VY-VFAT2-1LFDT (safe end-Stainless Steel) and VY-VFAT-2I.FDT (nozzle blend radius). Table 3 lists the temperature-dependent material properties used in the analysis [5]. Table 4 lists the fatigue curve for the nozzle and safe end materials [3, Appendix I, Table 1-9.1 and Figure 1-9.1 (UTS < 80.0 ksi) for the nozzle blend radius, and Tables 1-9.1 and 1-9.2.2 (Curve C) and Figures 1-9.2.1 and 1-9.2.2 for both safe end locations]. Curve C is selected because it is the most conservative curve among the three extended curves for austenitic steel. VESLFAT automatically scales the stresses by the ratio of E on the fatigue curve to E in the analysis, for purposes of determining allowable numbers of cycles, as required by the ASME Code.

Other material properties are input as follows:

m 1.7, n = 0.3, parameters used to calculate Ke for the safe end location (both materials) [3, Table NB-3228.5(b)-1]

m = 2.0, n = 0.2, parameters used to calculate K, for the nozzle blend radius location [3, Table NB-3228.5(b)-I]

E from fatigue curve = 28,300 ksi [3, Appendix I, Figure 1-9.2] for the safe end locations.

E from fatigue curve = 30,000 ksi [3, Appendix I, Figure 1-9.1 ] for the nozzle blend radius location.

3.5 Stress Indices Stress indices are calculated per Reference [2, Section 3.8]. For the safe end location and using the ANSYS thermal stress results, the membrane plus bending stress results are multiplied by K3 and then are added to the peak thermal stress results to yield total thermal stress, taking guidance from Equation 11 of NB-3600 [3]. The total thermal stresses are then added to the total piping and total pressure stresses.

C1 = C2 = C3 = 1, because the ANSYS model is sufficient to account for the effects of gross structural discontinuity. The path for Node 2166 does not contain a weld and, therefore, does not take the same guidance from NB-3600. However, the path for Node 3719 uses guidance and the following values from NB-3600 for an "as welded girth butt weld":

K1 = 1.2, From Table 3681(a)-I of NB-3600 [3]

K 2 = 1.8, From Table 3681(a)-I of NB-3600 [3]

K3 = 1.7, From Table 3681(a)-I of NB-3600 [3]

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The K values listed above are used to multiply the Membrane plus Bending stress results of the pressure load and piping load to yield Total Stress. So, Ki * (Memb+Bend)pressure = Total Stresspressure and K2 * (Memb+Bend)piping = Total StressPiping.

4.0 CALCULATIONS Table 5 contains the stress components at the locations of interest for the 1,000 psi unit pressure stress case [1, Table 2]. Table 5 also contains the stress components for the attached piping load unit stress case [1, Table 3], which correspond to a reactor design temperature of 575'F [2, Section 3.1.7].

The attached piping load stress components were applied assuming the same signs as the thermal stress, which yields the largest stress component ranges.

The stress indices for each location and loading scenario are calculated in the previous section. These stress indices are used in the Excel workbooks described below.

The calculations of all of the VESLFAT stress inputs are automated in Excel workbooks VY-VFAT-]i.xls (safe end-both materials) and VY-VFAT-2i.xls (nozzle blend radius). These files are organized with sheets labeled as follows:

Overview: Contains general information.

  • Other Stresses: Contains pressure and attached piping load stresses. As shown in Table 5, the pressure and thermal stresses use the membrane-plus-bending and total stress from the finite element analysis [1], and include stress indices where appropriate.

Rearranger: There are 7 Rearranger sheets, one for each thermal transient as analyzed by ANSYS. In these sheets, thermal stresses are copied from Excel workbook VY-StressResults.xls, and rearranged to conform to VESLFAT input format (including switching the shear stress components Sxz and Syz as required by VESLFAT). VY-StressResults.xls contains the results of the ANSYS stress linearization for each transient. The files contained within this workbook are shown in Table 10. Time-varying scale factors for the attached piping loads (based on path metal temperature) and pressure are determined, and used to scale the unit load case stresses, which are then added to the thermal stresses. Since the attached piping loads can act in any direction, the stresses due to the attached piping loads are assigned the same sign as the thermal stresses to maximize the component stresses.

Algebraic summation of all six stress components is performed for pressure, piping loads, and thermal stresses at each transient time step. The VESLFAT stress input also includes time-varying metal temperature, as obtained from the ANSYS output, which is used to determine temperature-dependent properties from the values in Table 3.

VESLFAT: Contains the VESLFAT stress input, as obtained from the Rearranger sheets.

Load set numbers are entered on this sheet, as defined in Table I and Table 2. These sheets are saved to VESLFAT input files VY-VFAT-]i.STR (safe end-Inconel), VY-VFAT2-1i.STR (safe end-Stainless Steel), and VY-VFAT-2i.STR (nozzle blend radius).

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5.0 RESULTS OF ANALYSIS Table 6, Table 7 and Table 8 provide the detailed calculated 60-year fatigue usage, as obtained from VESLFAT output files VY-VFAT-11.FAT (safe end-Inconel), VY-VFAT2-1LFAT (safe end-Stainless Steel), and VY-VFAT-2L.FAT (nozzle blend radius). All VESLFAT input and output files are saved in the project computer files associated with this calculation.

From Table 6, the safe end (Inconel) cumulative usage factor (CUF) is 0.000174 for 60 years. From Table 7, the safe end (Stainless Steel) cumulative usage factor (CUF) is 0.000742 for 60 years.

From Table 8, the nozzle blend radius CUF is 0.0171 for 60 years.

From Table 1 of Reference [6], it was determined that hydrogen water chemistry (HWC) is available for 47% of the total 60-year operating period, and normal water chemistry (NWC) is present for the remaining 53% of the total 60-year operating period. From Table 1 of Reference [6], the dissolved oxygen values for the RPV upper vessel region (which is applicable to the CS nozzles) are 97 ppb for HWC conditions and 114 ppb for NWC conditions.

For the safe end location (Inconel), the environmental fatigue factor is determined based on Alloy 600 methodology consistent with Reference [7]. The overall Fen (fatigue life correction factor), per Reference [7], is 1.49 and can be applied to the CS nozzle safe end (Inconel) location based on identical materials, i.e. SB-166. The resulting Environmentally Assisted Fatigue (EAF) adjusted CUF value is 0.000174 x 1.49 = 0.000259, which is less than the allowable value of 1.0 and is therefore acceptable.

For the stainless steel piping, the environmental fatigue factors for post-HWC and pre-HWC are both 8.36 from Table 4 of Reference [6]. The overall environmental multiplier is 8.36. It results in an EAF adjusted CUF of 8.36 x 0.000742 = 0.00620 for 60 years, which is acceptable (i.e., less than the allowable value of 1.0).

Based on the detailed CUF calculation shown in Table 8, a detailed EAF adjusted CUF evaluation on a load-pair basis is provided for the nozzle blend radius location in Table 9. The overall Fen is 8.20.

The resulting EAF adjusted CUF value is 0.0171 x 8.20 = 0.140, which is less than the allowable value of 1.0 and is therefore acceptable.

6.0 CONCLUSION

S AND DISCUSSIONS Detailed fatigue calculations for the Vermont Yankee CS nozzle were performed based on the results of stress analyses previously performed [1]. The thermal stresses were combined with stresses due to pressure and attached piping loads, both of which were scaled based on the magnitudes of the pressure and metal temperature during each thermal transient. All six components of the stress tensor were used for the fatigue calculations. The fatigue calculations were performed at previously-determined limiting locations in the safe end and nozzle blend radius, and used the methodology of Subarticle NB-3200 of Section III of the ASME Code [3].

The 60-year CUF for the safe end location (Inconel) was determined to be 0.000 174, the safe end location (Stainless Steel) was determined to be 0.000742, and the CUF for the nozzle blend radius File No.: 0801038.303 Page 7 of 18 Revision: 1 F0306-O1RO

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location was determined to be 0.0171. All three values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.

Detailed EAF assessments were also performed for the two CS nozzle locations. The 60-year EAF CUF for the safe end location was determined to be 0.000259 using standard Alloy 600 methodology

[7]. The 60-year EAF CUF for the safe end location (Stainless Steel) was determined to be 0.00620.

The 60-year EAF CUF for the nozzle blend radius location was determined to be 0.140 using temperature-dependent Fen multipliers for each load pair. All EAF CUF values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.

7.0 REFERENCES

1. Structural Integrity Associates Calculation No. 0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle."
2. Structural Integrity Associates Calculation No. 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle."
3. ASME Boiler and Pressure Vessel Code,Section III, 1998 Edition with 2000 Addenda.
4. VESLFAT, Version 1.42, 02/06/07, Structural Integrity Associates.
5. ASME Boiler and Pressure Vessel Code,Section II, Part D-Properties, 1998 Edition with 2000 Addenda.
6. SI Calculation No. VY-16Q-303, Revision 0, "Environmental Fatigue Evaluation of Reactor Recirculation Inlet Nozzle and Vessel Shell/Bottom Head."
7. EPRI Report No. TR-105759, "An Environmental Factor Approach to Account for Reactor Water Effects in Light Water Reactor Pressure Vessel and Piping Fatigue Evaluations,"

December 1995.

8. Entergy Design Input Record (DIR) EC No. 1773, DIR. Revision 1, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-16Q-209.

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Table 1: Safe End Load Sets as Input to VESLFAT VESLFAT Load Set 2

3 4

5 6

7 8

9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 Start Transient tiee Time, sec Tm2 T1_

0 Trn2T2_

0 Trn2T3_

0 1Tm3r 0

2Trn3 56.6 I1Tml 1-0 2Trnl 1 5

3Tml 1 26.962 4Trn I 1 207.34 5TrnIl 1 1734.9 6Trnl 1 2332.6 7Trnl 1 5625.1 8Trnl 1 7125.4 9Trnl 1 14315 1OTrnl 1 16749 lTrnl4 0

2Tm14 270 lTrn21 0

2Trn2l 17.00 Tn24_TI_

0 Tn24 T2 0

Tn24_T3_

0 1Trn3O 0

2Trn3O 12.2 3Trn3O 631 Temp Change Pressure Change None None None Up Up None Down Down Down & Up Up & Down Down & Up Up & Down Down & Up Up & Down Down Down Down Down Down None None None Down Down None None Up Down Up Up Up & Down Down None None Down Down & UP Up & Down Down & Up Up None Down Down Down Down None Up Down Down Down Down Cycles 120 120 120 300 300 10 10 10 10 10 10 10 10 10 10 1

1 300 300 1

1 1

1 1

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Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT VESLFAT Load Set Transient Structurai Integrity Associates, Inc.

Trn2_TI Trn2_T2_

Trn2_T3_

1Trn3_

2Trn3 ITrnll1 2Trn I1_

3Trnl 1 4Trnl 1 5Trnl I 6Trn 11 7Trnl I 8Trnl I 9Trnll1 1Trnl4_

2 Tm14 2Trnl4_

3Tm14 1Tmn21I 2Tin21I 3Tm2l1 Tn24_Ti1 Tn24 T2 Tn24_T3_

1Tm30_

2Tmn3O 3Tmn30 4Tmn30_

Start

Time, sec 0

0 0

.0 56.6 0

5 142.64 1655.2 2302.7 3193.7 7255.1 9913 12514 0

40 1200 0

32.15 6462.7 0

0 0

0 1.2 25 3331 Temp Change Pressure Change Cycles None None None Up Up None Down Down & Up Up & Down Down & Up Up & Down Down & Up Up Up and Down Down Down Down Down Down Down None None None None Down Down Down None Up Down Up Up Up & Down Down None Down Down & Up Up & Down Down Down & Up Up Down Down Down Down Down None None Up Down Down Down Down Down 120 120 120 300 300 10 10 10 10 10 10 10 10 10 300 300 300 1

1 1

1 1

1 1

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Table 3: Temperature-Dependent Material Properties for VESLFAT (4)

Material T, OF E x 106, psi S., ksi Sy, ksi SB-166 Inconel

.(safe end(')

  • SA-508 Class 2(5)

(Nozzle blend radius (2))

70 200 300 400 500 600 70 200 300 400 500 600 70 200 300 400 500 600 31.0 30.2 29.8 29.5 29.0 28.7 27.8 27.1 26.7 26.1 25.7 25.2 28.3 27.6 27.0 26.5 25.8 25.3 23.3 23.3 23.3 23.3 23.3 23.3 26.7 26.7 26.7 26.7 26.7 26.7 20 20 20 18.7 17.5 16.4 35.0 32.0 31.2 30.7 30.3 29.9 50.0 47.0 45.5 44.2 43.2 42.1 30 25 22.4 20.7 19.4 18.4 SA-312 TP 304 (Core Spray Piping 8 x 10 Reducer (3))

Notes:

1.

For the safe end material, SB-166 Inconel properties are used (72Ni-15Cr-8Fe), per Reference [2]. Annealed heat treatment is conservatively assumed for Sm and Sy values.

2.

For the nozzle blend radius material, SA508 Class 2 material properties are used (3/4Ni-1/2Mo-1/3Cr-V), per Reference [2].

3.

For the nozzle safe end extension material, SA-312 TP304 material properties are used (18Cr-8Ni), per Reference [2].

4.

All values are taken from Reference [5].

5.

SA-508 Class 2 in the Code of Construction is the same as SA-508 Gr. 2 Class 2 in the 1998 ASME Code [5]

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Table 4: Carbon/Low Alloy Steel and Stainless Steel/Nickel Alloy Fatigue Curves Number of Cycles Sa, ksi Carbon/Low Alloy (1)

S,, ksi Austenitic/Nickel Alloy 10 20 50 100 200 500 1000 2000 5000 10000 20000 50000 100000 200000 500000 1000000 2.E+06 5.E+06 1.E+07 2.E+07 5.E+07 1.E+08 1.E+09 1.E+10 1.E+311 580 410 275 205 155 105 83 64 48 38 31 23 20 16.5 13.5 12.5 N/A N/A N/A N/A N/A N/A N/A N/A N/A 708 512 345 261 201 148 119 97 76 64 55.5 46.3 40.8 35.9 31 28.2 22.8(2) 18.4(2) 16.4(2) 15.2(2) 14.3(2) 14.1(2) 13.9(2) 13.7(2) 13.6(2)

Note:

1. Using UTS _ 80 ksi curve.
2.

Using Curve C for austenitic steel/nickel alloy.

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Table 5: Pressure and Attached Piping Unit Load Case Stress Components Membrane plus Bending (1)

Total )

Node S

y"(

s)

(5)

Sy S

Sx Sz(s5)

Load (2)

Sx SY Sz Sy Sxz S

S S

Sxz yZ Pressure(3) 3719

-1011 4829 11010

-104.8 0

0

-1011 4912 11050

-85.31 0

0 2166

-1052 1657 25960 4886 0

0

-1052 1720 35050 348.9 0

0 Piping(4) 3719 0

6502 0

658 1222 0

0 11704 0

1184 2200 0

2166 0

82 0

30 20 0

0 82 0

30 20 0

'MnM, 1

All otr*-oc,an or*

m

, nnitc nfendf 2.

3.

4.

5.

The safe end location is represented by Node 3719, and the nozzle blend radius location is represented by Node 2166.

The stresses for both nodes represent the stress due to an applied pressure of 1,000 psig.

Piping stresses for both locations represent the stress due to full attached piping loads at an RPV temperature of 575'F.

Sy. and S. components have been rearranged from the ANSYS output in order to be in correct order for VESLFAT.

Table 6: Fatigue Usage Calculation for the Safe End (Inconel)

Load

  1. 1 Load Desc. #1
  1. 2 Salt Desc. #2 n (cvcles)

Sn (psi)

Ke (psi)

Nallow U

24 17 5

5 5

5 5

5 5

5 5

4 4

1 19 19 3

3 2Trn3O 2Trn 14 2Trn3_

2Trn3 2Trn3 2Tm3_

2Trn3 2Trn3_

2Trn3_

2Trn3_

2Trn3_

1Trn3_

1Trn3_

Trn2_Ti1 2Trn2l_

2Trn2l1 Trn2_T3_

Trn2_T3_

25 23

.8 9

6 7

10 14 11 15

.12 5

19 19 20 22 19 18 3Trn3O_

1Trn30 3Trn 1_

4Trn 11_

1 Trn 11 2Tn I I_

5Trnl 1_

9Trn 1I-6Trnl 1_

1OTrnl 11 7Trnl 1 2Trn3_

2Trn21l 2Trn2l_

Tn24_TI1 Tn24_T3_

2Tm2l_

1Trn21 1

1 10 10 10 10 10 10 10 10 10 210 90 120 1

1 88 32 67883 44360 26107 25551 24728 24429 23571 23593 23214 23358 23247 23000 22979 22979 22383 22383 22383 22389 63663 48903 18347 17850 16797 16784 16559 16507 16399 16262 15968 15922 15914 15899 15552 15552 15552 15549 10260 37919 5088300 6002500 8657500 8698300 9436700 9615800 10007000 10800000 12760000 13097000 13155000

.13273000 16233000 16233000 16233000 16263000 Total Usage 0.000098 0.000026 0.000002 0.000002 0.000001 0.000001 0.000001 0.000001 0.000001 0.000001 0.000001 0.000016 0.000007 0.000009 0.000000 0.000000 0.000005 0.000002 0.000174 Note:

All other load pairs have an alternating stress, they do not contribute to fatigue usage.

Salt, that is below the endurance limit of the fatigue curve. Therefore, File No.: 0801038.303 Page 13 of 18 Revision: 1 F0306-0IRO

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Table 7: Fatigue Usage Calculation for the Safe End (Stainless Steel)

Load

  1. 1 24 17 5

5 5

5 5

5 5

5 4

4 1

19 19 3

3 Desc. #1 2Trn3O 2Trn 14 2Trn3 2Trn3 2Trn3 2Trn3_

2Trn3_

2Trn3_

2Trn3_

2Trn3_

1 Trn3_

1Trn3_

Trn2 T1 2Trn21 2Trn2l Trn2 T3 Trn2_T3_

Load

  1. 2 25 23 8

9 6

7 14 10 15 11 5

19 19 20 22 19 18 Desc. #2 3Trn3O_

1 Trn30 3Trn 11_

4Trn 11_

1 Trn 11 2Trnl 1_

9Trnl 1_

5Trnl 11 1OTrnl 11 6Trn 1I-2Trn3_

2Trn2l_

2Trn2l_

Tn24 Ti Tn24_T3_

2Trn2l 1Trn21_

n (cycles) 1 1

10 10 10 10 10 10 10 10 22 Sn (psi) 68465 44360 26107 25551 24728 24429 23593 23626 23358 23214 23000 22979 22979 22383 22383 22383 22389 Ke 1.47 1

1 1

1 1

1 1

1 1

1 1

1 1

1 1

1 Salt (psi) 101779 54103 20551 19856 18923 18905 18620 18525 18336 18295 17975 17967 17949 17557 17557 17557 17554 Nallow 1699.05 22751 3117000 3611400 4435200 4453400 4752000 4857700 5106400 5175200 5755400 5772000 5806200 6632000 6632000 6632000 6640000 Total Usage =

U 0.000589 0.000044 0.000003 0.000003 0.000002 0.000002 0.000002 0.000002 0.000002 0.000002 0.000038 0.000014 0.000021 0.000000 0.000000 0.000015 0.000003 0.000742 Note:

All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.

File No.: 0801038.303 Revision: 1 Page 14 of 18 F0306-01RO

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Table 8: Fatigue Usage Calculation for the Nozzle Blend Radius Load Load n

Salt

  1. 1 L

Desc. #1

  1. 2 Desc. #2 (cycles)

Sn (psi)

Ke (psi)

Nallow U

25 2Trn3O0 26 3Trn3O0 8

3Trnl 1_

13 8Trnl 1_

19 2Trn21 22 Tn24_T2_

7 2Trnl 1 27 4Trn3O0 4

1Trn3_

7 2Trnl 1_

10 5Trn11 _

19 2Trn21l 1

Trn2 TI 6

1Trn 11 2

Trn2_T2_

19

2Trn21, 12 7Trnl 1 19 2Trn21 1

Trn2_Ti1 9

4Trnl 1 4

1Trn3_

11 6Trn 11_

1 Trn2 T1 5

2Trn3 4

1Trn3_

5 2Trn3_

4 1Trn3_

24 lTrn30-4 1Trn3_

18 1Trn21_

17 3Trn14_

18 1Trn21_

18 1Trn21_

20 3Trn21_

19 2Trn21_

20 3Trn21_

3 Trn2_T3_

19 2Trn21l 3

Trn2 T3 14 9Trn 11_

3 Trn2_T3_

15 1Trn14_

3 Trn2_T3_

16 2Trn14_

1 51402 1.00 44455 6278 0.0002 10 15961 1.00 39383 8994 0.0011 1

39644 1.00 34138 14404 0.0001 1

38618 1.00 27466 28999 0.0000 9

36665 1.00 27150 30048 0.0003 10 15935 1.00 26332 33005 0.0003 10 49693 1.00 25486 36486 0.0003 120 25423 1.00 24010 43822 0.0027 10 13983 1.00 23200 48691 0.0002 10 47005 1.00 22776 52484 0.0002 10 35885 1.00 22731 53008 0.0002 100 44974 1.00 22190 59737 0.0017 200 44974 1.00 22190 59737 0.0033 1

44912 1.00 22187 59767 0.0000 80 44912 1.00 22187 59767 0.0013 1

44598 1.00 21478 70216 0.0000 219 43608 1.00 21218 74590 0.0029 81 43426 1.00 21130 76147 0.0011 78 43219 1.00 21117 76367 0.0010 10 43408 1.00 21016 78221 0.0001 1

42722 1.00 20993 78639 0.0000 1

41044 1.00 20341 91957 0.0000 Total 0.0171 Usage =

Note:

All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.

File No.: 0801038.303 Revision: 1 Page 15 of 18 F0306-OIRO

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Table 9: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location VY CS Nozzle Corner Environmental Fatigue Calculation CUF Calculation from file VY-VFAT-2i.fat:

Index Load #1: Description #1: n1 (cycles) t5) Load #2& Description #2i n2 (cycles) t5 ycles} 's SK psi t

lt (psi}

Nallmy U

1 25 2Trn30_

1 26 i

3Trn3O_

1 1

51402 1.00 44455 6278 0.0002 2

8 i

3Trnl_

10 13 i

8Trn11_

i 10 10 15961 1-00 39383 8994 0.0011 3

19 i

2Trn21 300 22 Tn24 T2 1

1 39644 1.00 34138 14404 0-0001 4

7 2Trnl1 10 27 4Trn30 1

1 38618 1-00 27466 28999 0.0000 5

4 1Trn3 300 7

2Trn11-9 9

36665 1.00 27150 30048 0.0003 6

10 5Trn11 10 19 2Trn21 299 10 15935 1.00 26332 33005 0.0003 7

1 1

Trn2 TI 120 6

iTrnl 1 10 10 49693 1.00 25486.

36486 0.0003 8

2 Trn2 T2 120 19 2Trn2l 289 120 25423 1.00 24010 43822 0.0027 9

12 7Tlr 11 i

10 19 i

2Trn21-169 10 13983 1.00 23200 48691 0.0002 10 1

ITrn2 Ti 110 9

4Trn11 10 10 47005 1.00 22776 52484 0.0002 11 4

1Trn3 291 11 6Trn11-10 10 35885 1.00 22731 53008 0.0002 12 1

Trn2 T1 100 5

2Trn3 300 100 44974 1.00 22190 59737 0.0017 13 4

1Tr,3 281 2Trn3 200 200 44974 1.00 22190 59737 0.0033 14 4

1Trn3 81 24 OTrn3_

1 1

44912 1.00 22187 59767 0.0000 15 4

lTrn3 80 18 1 Trn21 300 80 44912 1.00 22187 59767 0.0013 16 17 3Trn14 1

18 1Trn21_

220 1

44598 1.00 21478 70216 0.0000 17 18 1Trn21 i

219 20 i

3Trn21 i

300 219 43608 1.00 21218 74590 0.0029 18 19 2Trn21 159 20 i

3Trn21 81 81 43426 1.00 21130 76147 0.0011 19 3

Trn2 T3 120 19 2Trn21 78 78 43219 1.00 21117 76367 0.0010 20 3

Trn2 T3 42 14 9Trn11-10 10 43408 1.00 21016 78221 0.0001 21 3

Trn2 T3 32 15 1 Tm14-1 1

42722 1.00 20993 78639 0.0000 22 3

Trn2 T3-31 16 1

2Trn14 1

1 41044 1.00 20341 91957 0.1000 Total, U =

0.0171 File No.: 0801038.303 Revision: I Page 16 of 18 F0306-0IRO

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Table 9 (Continued): EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location EAF Calculations:

(00 and HWCINWC inputs fromTable 1 of Reference [6})

%, HWC =

HWC DO 97 0.47 HWC D0O 114 0.53 ppb

=% NWC Transient Maximum Temperatures:

Frnm "V'Y-VtFAT-2i AlII '

Index Load #1 Desc. #1 Load #21 Desc.#2 Line #

Ti (4) si(4) T2(4) s2(4] Sn (psi) T (IF) (1) 1 25 2Trn30-26 3Trn3O 591851 25 15 26 30 51402 543 2

B 3Trnhl _

13 UTrnh 1 -

127122 8

30 13 14 15961 3D1 3

19 2Trn21 22 Tn24 T.2 574137 19 20 22 39644 359 4

7 2Trnl 1 27 4Trn30 107543 7

32 27 17 3561t 465 5

4 lTrn3_

7 2Trnill 3921 4

1 7

32 36f665 465 6

10 5Trn 1-19 2Trn2l 24a,706 10 67 19 20 15935 389 7

1 Trn2 Tl 6

lTrn 1.

70 1

1 6

4 49693 526 5

2 Trn2 T2_

19 2Trn21_

2028 2

1 19 20 25423 389 9

12 Tfrn 1I-19 2Trn2i_

391806 12 30

.19 20 13983 3&9 10

.1 Trn2_Ti1 9

4Trnll 161 1

1 9

1 47005 434 11 4

1Trn3_

11 6Trnl 11 5546 4

1 11 1

35655 348 12 1

Trn2_TI_

5 2Trn3_

56 1

1 5

42 44974 549 13 4

lTrn3 5

2Trn3_

3475 4

t1 5

42 44974 549 14 4

iTrn3_

24 1Trn30_

10815 4

1 24 1

44912 549 15 4

ITrn3_

15 i

Trn21_

1016 4

1 18 1

44912 549 16 r 17 3Trn14_

18 1Trn21_

53601 3 17 111 16 1

44596 549 17 15 lTrn2i_

20 3Trn21 571713 18 1

20 39 43605 549 15 19 2Trn21 20 3Trn21 573512 19 1

20 39 43426 549 19 3

Trn2 T3 19 2Trn21_

3151 3

1 1,9 1

43219 549 20 3

Trn2 T3 14 9Trnll_

296-5 3

1 14 155 43405 524 21 3

Trn2 T3 15 lTrn14 2979 3

1 15 1

42722 526 22 3

Trnm2T3 16

, 2Trn 14_

2953 3

1 16 1

41044

524, TMAX -F) (1)

TMAX ('C)

HWC Fen (2) NWC Fen (2) Uenv (3) 543 2.54 6.49 10.65 0.002 391 199 3.68 4.22 0.005 389 1 5'8 3.54 4.17 01.000 145 241 I

5.65 6.62 0.000 465 241 5.63 6.62 0.002 359 198 3.84 4.17 0.001 526 274 7.78 9.60 D.002 389 198 3.64 4.17 0.011 359 198 3.84 4.17 0.001 434 223 4.34 5.48 01.001 345 176 3.11 3.25 01.001 549 267 8.76 11.05 0.017 549 287 6.76 11.05 0.033 549 287 8.76 11.05 01.000 549 257 6.76 11.05 U..013 549 287 8.76 11.05

.0.000 549 287 8.76 11.05 0.029 549 297 6.76 11.05 0c.011 549 287 8.76a 11.05 01.010 524 273 7.70 49 0.001 526 274 7.75 9.60 0.000 524 273 7.70 9.89 01.000 Total. U =

Overall Fen Notes:

1. Tv,,., is the maximum temperature of the two paired load states, and represents the metal (nodal) temperature at the location being analzed. This, which is include-d as 'T in the'Transient Maximum Temperatures7' table above. determined from the VESLFAT
2. F, values computed using the low alloy steel equation from Section 3.0 of Reference [61 with S' conservatively set to a maximum value of 0.0 15. and the transtformed strain rate conservat~rely set to a minimum value of In (0.00t1) = 508 for all load
3. U*, = [U x HWC F, x % HWCI

[U x NWC F_. x % NWC1.

4. T1 and 72 represent the load number for Load #1 and Load #2, respectively, and sl and s2 represent the state number for each
5. For each load pair, nj is the number of available cycles for Load #1, n-is the number of available cycles for Load #2, and n is the available number of cycles for the load pair (i.e., the minimum of nj and n.).

0.140 8.20 File No.: 0801038.303 Revision: 1 Page 17 of 18 F0306-OI RO

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Table 10: Linearized Stress Files Compiled for VY-StressResults.xls Filename Description vyl 6qtran2-s.csv vyl 6q_tran3-s.csv vy_l 6q_tranl 1-s.csv vyl 6q_tran 1 4-s.csv vyl 6q_tran21-23-s.csv vyl 6q_tran24-s.csv vyl 6q_tran30-s.csv Transient 2 linearized stress Transient 3 linearized stress Transient 11 linearized stress Transient 14 linearized stress Transients 21-23 linearized stress Transient 24 linearized stress Transient 30 linearized stress Note: All files are from the supporting computer files associated with Reference [1].

File No.: 0801038.303 Revision: I Page 18 of 18 F0306-OIRO

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File No.: 0801038.304 CALCULATION PACKAGE Project No.: 0801038 Quality Program: Z Nuclear

[ Commercial PROJECT NAME:

VY Confirmatory Analysis for CS and RO Nozzles CONTRACT NO.:

10163217 Amendment 5 CLIENT:

PLANT:

Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:

Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle Document Affected Project Manager Preparer(s) &

Documen afe Revision Description Approval Checker(s)

Revision Pages Signature & Date Signatures & Date 01

- 20, Initial issue.

Preparers:

Appendix:

Gary L. Stevens Michael J. Minard A-I - A-23 01/07/09 01/07/09 Computer files.

Tyler D. Novotny 01/07/09 Checker:

Terry J. Herrmann 01/07/09 1

1-8,10,11, Revised per summary.

/

Preparer:

13-20, contained in Section 1.1.

0( 11Z64-A-2 Changes are marked with "revision bars" in Gary L. Stevens right-hand margin.

03/09/09 Tyler D. Novotny 03/09/09 Checker:

William Weitze 03/09/09 Page 1 of 20 F0306-01 RO

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Table of Contents 1.0 OBJECTIVE............................................................................................................

4 1.1 Changes M ade in Revision 1 of this Calculation..........................................

4 2.0 M ETHODOLOGY...................................................................................................

4 3.0 ASSUM PTIONS / DESIGN INPUTS.......................................................................

5 3.1 Assumptions...............................................................................................

.. 5 3.2 ASM E Code Edition.....................................................................................

5 3.3 Transients......................................................................................................

6 3.4 Heat Transfer Coefficients.............................................................

...... 6 3.5 Finite Element M odel..................................................................................

8 3.6 Nozzle Blend Radius Pressure Stress..........................................................

8 3.7 Piping Interface Loads...............................................................................

......... 8 3.8 SCFs, Safe End............................................................................................

9 3.9 Environmental Fatigue M ultipliers................................................................

9 4.0 CALCULATIONS.................................................................................................

13 4.1 Piping Interface Loads....................................

13 5.0 RESULTS OF ANALYSIS.....................................................................................

18

6.0 REFERENCES

19 APPENDIX A: ANSYS INPUT FILE: RON VY.INP.................................................

A-1 FileNo.: 0801038.304 Page 2 of 20 Revision: 1 F0306-01!

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List of Tables Table 1: Vessel and Nozzle/Safe End Transients.............................................................

10 Table 2: H eat Transfer Coefficients.......................................................................................

11 Table 3: Temperature-Dependent Material Properties...........................................................

11 Table 4: Recirculation Outlet Nozzle Attached Piping Loads and Dimensions [9, 11]......... 14 Table 5: Membrane Plus Bending Stresses Due to Piping Loads....................................

14 Table 6: 0% Flow Regions I and 3 Heat Transfer Coefficients.......................................

15 Table 7: 0% Flow Region 5 Heat Transfer Coefficient...................................................

16 List of Figures Figure 1: Nozzle and Vessel Wall Thermal Boundaries...................................................

12 Figure 2: Coordinate System for Forces and Moments.....................................................

17 Figure 3: RO Nozzle and Safe End Geometry [20]..........................................................

17 File No.: 0801038.304 Revision: 1 Page 3 of 20 F0306-01I

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1.0 OBJECTIVE The objective of this calculation package is to establish the design inputs and methodology to be used for an ASME Code,Section III fatigue usage calculation of the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at Vermont Yankee Nuclear Power Station (VYNPS)1.

This calculation, along with subsequent calculations for stress and fatigue, are being performed to assess the impact of using finite element analysis using all six components of stress in lieu of the Green's Function approach used in SI project VY-16Q [4, 7, and 11]. Therefore, to the extent possible, inputs from that project will be maintained and used.

1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:

a. Transient 9 described in Table 1 was changed to more precisely match the Green's Function analysis.
b. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.

2.0 METHODOLOGY A detailed fatigue usage calculation of the RO nozzle will be performed using the methodology of Subarticle NB-3200 of Section III of the ASME Code [1]. The 1998 Edition includingthe 2000 Addenda of the ASME Code [10] is also used for material properties. Only the fatigue calculation portion of the ASME Code methodology will be used and the analysis will be a fatigue assessment only, not a complete ASME Code analysis.

Finite element analysis will be performed using a previously-developed axisymmetric finite element model (FEM) of the RO nozzle [7]. Thermal transient analysis will-be performed using the FEM for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads; for these loads' unit load analyses (finite element analysis for pressure, and manual calculations for piping loads) will be performed. The stresses from these analyses will be scaled appropriately based on the magnitude of the pressure and piping loads during each thermal transient, and combined with stresses from the thermal transients. Other stress concentration factors (SCFs) will be applied as appropriate.

All six components of the stress tensor will be used for stress calculations. The stress components for the non-axisymmetric loads (shear and moment piping loads) can have opposite signs depending upon which side of the nozzle is being. examined. Therefore, when combining stress components from these loads with stress components from thermal transients and other loads, the signs of the stress components will be adjusted to maximize the magnitude of the stress component ranges. The fatigue analysis will be performed at locations that were determined in a previous calculation [4]. Stresses will be linearized at these locations.

The methodology described and applied herein and in the two additional recirculation outlet nozzle fatigue calculations is in accordance with the approach used in the SIA calculations for the feedwater nozzle [16, 17, 18] and contains no significantly different scientific or technical judgments used in those calculations.

File No.: 0801038.304 Page 4 of 20 Revision: 1 F0306-01:

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The linearized primary plus secondary membrane plus bending stress will be used to determine the value of Ke to be used in the simplified elastic-plastic analysis in accordance with ASME Code NB-3200 methodology. Environmental fatigue multipliers will be applied in accordance with NUREG/CR-6583 [2]

for the low alloy steel forging and NUREG/CR-5704 [15.] for the stainless steel safe end.

3.0 ASSUMPTIONS / DESIGN INPUTS 3.1 Assumptions

1. Extended power uprate (EPU) effects are considered as being applied to the entire 60-year period of operation. The higher pressures, flows, and temperatures at uprate conditions are used in determining and applying heat transfer coefficients [4, Section 3.2] [11, Section 4.1].
2. The Boltup transientdoes not affect the RO nozzle because there is no pressure or temperature change, and the nozzle is sufficiently removed from the vicinity of the flange such that stresses due to head stud tensioning are insignificant at the nozzle location [8]. The Boltup transient is therefore excluded from the transients analyzed.
3. For the blend radius and safe end transient definitions, steady state condition time steps were assumed to be 5,000 seconds for Transients 3, 5, 6, 8, 9, and 40,000 seconds for Transients 1, 2, 4, 7, 10.
4. The effect of non-uniform geometries is judged to be insignificant for flow inside the safe end, because of the smooth transition and small, geometry changes, as shown in Figure 3. The nominal inner diameter for all heat transfer regions was used to calculate heat transfer coefficients.
5. Density, p, and Poisson's ratio, v, used in the FEM are assumed typical values of p = 0.283 lb/in 3 and v = 0.3, respectively.
6. For purposes of linearizing stress at the nozzle blend radius, the cladding is ignored'.
7. Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 707F and the full values are reached at reactor design temperature, 575°F, as was done in the previous analysis [11, Section 3.4].
8. Consistent with Reference [4], 12% of the available temperature difference (AT) between the fluid and surface was assumed for all natural convection thermal heat transfer coefficients.
9. The instant temperature change for transients is assumed as a 1-second time step.

3.2 ASME Code Edition The analysis will be performed in a manner consistent with the fatigue usage rules in NB-3200 of Section III of the ASME Code; the 1998 Edition with Addenda through 2000 [1] will be used, for consistency with the previous analysis [11].

File No.: 0801038.304 Page 5 of 20 Revision: 1 F0306-01I

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3.3 Transients Previously developed thermal and pressure transients [11 Tables 2 and 3] are used for this analysis. The transients to be evaluated are shown in Table 1. For each transient, the time, nozzle fluid temperature, RPV pressure, percent reactor recirculation flow rate, and number of cycles are included. In some cases, flow rates and nozzle temperature values from the nozzle thermal cycle diagram [8, Attachment 1, p. 4] are used' to reduce excess conservatism. Note that the only difference between the vessel and the safe end/nozzle transients is the temperature difference between the two regions for Transient 9.

At the inside surface of the RPV, the Region B or BI bulk fluid temperature from the reactor thermal cycle diagram [8, Attachment 1, p. 2] shall be applied.

3.4 Heat Transfer Coefficients Heat transfer coefficients are calculated at 300' F, as in the previous analysis [4]. The heat transfer coefficients for the 100% flow and 50% flow cases were calculated from Reference [5] as follows:

K =0.8

(

0.2 S3 h°-25 DDf Where:

hDf= the heat transfer coefficient at a Diameter and flow rate h300 = the heat transfer coefficient from Reference [5] at 300°F,f= 25 ft/sec, and D= 26" =,4,789 BTU/hr-ft2_OF fif= the flow velocity corresponding to hDf (ft/sec)

DDf= the diameter corresponding to hDf(in)

The heat transfer coefficients for 0% flow were calculated in spreadsheet HTCOEF.xls for natural convection and are shown in Tables 6 and 7.

As shown in Figure 1, the following heat transfer coefficients were applied:

Region 1 The heat transfer coefficient, h, for 100% flow is 4789 17-36)

"82-0.82

=3583 BTU/hr-ft2-°F at 300TF, where 17.364 ft/sec is converted from 28,294 GPM and 25.8 in ID [20].

(8.6821~ 0(

26 >0.2 The heat transfer coefficient, h, for 50% flow is 4789 -

J = 2058 BTU/hr-ft2 -

'F at 300TF, where 8.682 ft/sec is converted from 14,147 GPM and 25.8 in ID [20].

The heat transfer coefficient, h, for 12% flow is 4789 (-2.084) 08 26 0.82 =657 BTU/hr-ft2-°F at 300'F, where 2.084 ft/sec is converted from 3,395 GPM and 25.8 in ID [20].

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The heat transfer coefficient, h, for 0% flow is 112 BTU/hr-ft2-°F at 300'F. (Table 6, for natural convection)

Region 2 The heat transfer coefficient for Region 2 is linearly transitioned from the value of the heat transfer coefficient used in Region I to the value used for Region 3.

Region 3 (the point between Region 2 and Region 4)

The inside diameter of Region 3, as measured on the ANSYS model, is 35.49 inches.

The heat transfer coefficient, h, for 100% flow is 4789 (9.176_0.g (26

)

2018 BTU/hr-ft2-25__

35.49 OF at 300'F, where 9.176 ft/sec is converted from 28,294 GPM and 35.49 in. ID.

The heat transfer coefficient, h, for 50% flow is 4789 4.5) 08 26 0.2 = 1159 BTU/hr-ft2-

___ 25 35.49)I OF at 300TF, where 4.588 ft/sec is converted from 14,147 GPM and 35.49. in. ID.

The heat transfer coefficient, h, for 12% flow is 4789

- 370 BTU/hr2ft -.F

\\ ~~~~25

)

35-.49

=7BU/-f2° at 300°F, where 1.101 ft/sec is converted from 3,395 GPM and 35.49 in. ID.

The heat transfer coefficient, h, for 0% flow is 112 BTU/hr-ft2-°F at 300'F. using the same HTC as Region 1 (Table 6, for natural convection)

Region 4 The heat transfer coefficient for Region 4 (Nozzle Blend Radius).is linearly transitioned from the value of the heat transfer coefficient used in Region 3 to the value used in Region 5.

Region 5 A value of 0.5 x Region 1 HTC from Reference [5, page I-T9-4, 6] is used to simulate the interior of the RPV shell for all conditions.

The heat transfer coefficient, h, for 100% flow is 0.5 x 3583.3 = 1,792 BTU/hr-ft2-OF at 3000F.

The heat transfer coefficient, h, for 50%flow is 0.5 x 2058.1 1029 BTU/hr-ft2-OF at 3000F.

The heat transfer coefficient, h, for 12% flow is 0.5 x 657.2= 329 BTU/hr-ft2-OF at 3000F.

The heat transfer coefficient, h, for 0% flow is 101 BTU/hr-ft2-OF at 300°F. (Table 7, for natural convection) by using 40 in. hydraulic diameter [5].

File No.: 0801038.304 Page 7 of20 Revision: 1 F0306-011

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Region 6 The heat transfer coefficient, h, is 0.4 BTU/hr-ft2-OF [5].

A summary of the heat transfer coefficients (HTC) to be used is shown in Table 2.

3.5 Finite Element Model The ANSYS program [6] will be used to perform the finite element analysis. A previously developed axisymmetric model will be used [7, file RONVYINP], except that temperature-dependent material properties will be used. Table 3 shows the applicable material properties [10].

Stresses will be extracted and linearized at two locations, both on the inside surface of the model, one at the safe end, and one at the blend radius, as was done previously [4].

3.6 Nozzle Blend Radius Pressure Stress The axisymmetric model has the effect of modeling the cylindrical RPV as spherical. The following paragraphs describe the details of the modeling used to account for the differences in this approximation and the actual geometry of two intersecting cylinders.

The radius of the vessel in the finite element model was multiplied by a factor of 2 to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is a cylinder. The equation for the membrane hoop stress for a sphere is:

(pressure) x (radius) 2 x thickness The equation for the membrane hoop stress in a cylinder is:

(pressure) x (radius) thickness The factor of two was verified in Reference [4], where actual stress results were compared to the results of this analytical form.

The pressure stress components for the safe end and blend radius paths will be extracted using ANSYS [6].

3.7 Piping Interface Loads Per Reference [9, 11], the RO nozzle piping loads, which conservatively use the design loads for the seismic, thermal and deadweight load combination, are stated in Table 4 along with relevant dimensions.

The coordinate system used for these are shown in Figure 2 and is consistent with Reference [9]. The finite element model coordinate system is shown in Figure 1.

File No.: 0801038.304 Page 8 of 20 Revision: 1 F0306-01

Structural Integrity Associates, Inc.

3.8 SCFs, Safe End At the safe end inside surface, guidance is taken from the piping analysis rules in Subarticle NB-3600 of Section III of the ASME Code [1]. The stresses caused by the piping will be hand calculated and require a stress concentration factor, if appropriate. The stress concentration factor for the safe end location is 1.53 [5, page I-S9-4E, Table 5]. This value is conservatively used for both the C2 and K2 values required by the ASME code [1, NB-3600]. The piping loads are relatively minor in comparison to the other loads this nozzle experiences so the conservative C2 and K2 values will have a small impact on the analysis.

These factors are conservatively applied to all six components of the stress tensor.

3.9 Environmental Fatigue Multipliers The environmental fatigue multipliers for the safe end will be calculated in accordance with NUREG/CR-5704 methodology [15], and the environmental fatigue multipliers for the nozzle blend radius will be calculated in accordance with NUREG/CR-6583 methodology [2].

File No.: 0801038.304 Revision: 1 Page 9 of 20 F0306-01.

Structural Integrity Associates, Inc.

Table 1: Vessel and Nozzle/Safe End Transients Transient Time Temp Time Step Pressure Flow Rate Transient Time Temp Time Step Pressure Flow Rate Number LS L

U

  • psg)

(GPMI Number La}

JLM

("F L"s Lpsi (GPM)

1. Normal Startup with 0

100 0

14147.0

6. Reactor Overpressure 0

526 1010 28294 Heatup at 10 0*F/hr 16164 549 16164 1010 (50%)

1 Cycle (1,2) 2 526 2

1375 (100%)

300 Cycles (2) 56164 549 40000 1010 32 526 30 940

2. Turbine Roll and 0

549 1010 28294 1832 526 1800 940 Increase to Rated Power 1

542 1

1010 (100%)

2252 549 420 1010 300 Cycles (1, 2) 601 542 600 1010 2312 549 60 1010 602 526 1

1010 2313 542 1

1010 40602 526 40000 1010 1

2913 542 600 1010

3. Loss of Feedwater 0

526 1010 28294 2914 526 1

1010 Heaters 1800 542 1800 1010 (100%)

7914 526 5000 1010 Turbine Trip 25% Power 2100 542 300 1010

7. SRV Blowdown 0

526 1010 28294 10 Cycles (2) 2460 526 360 1010 1 Cycle (2) 600 375 600 170 (100%)

3060 526 600 1010 11580 70 10980 50 3960 542 900 1010 51580 70 40000 50 4260 542 300 1010

8. SCRAM Other 0

526 1010 28294 6060 526 1800 1010 228 Cycles (1, 2) 15 526 15 940 (100%)

11060 526 5000 1010 1815 526 1800 940

4. Loss of Feedwater 0

526 1010 0

2235 549 420 1010 Pumps 3

526 3

1190 (0%)

2295 549 60 1010 10 Cycles (1,2) 13 526 10 1135 2296 542 1

1010 233 300 220 1135 2356 542 60 1010 2213 500 1980 1135 2357 526 1

1010 2393 300 180 885 7357 526 5000 1010 6773 500 4380 1135

9. Improper Startup 0

526 1010 3395 7193 300 420 675 14147 1 Cycle (1, 2) 1 130O 1

1010 (12%)

7493 300 300 675 (50%)

27 130 26 1010 11093 400 3600 240 28 526 1

1010 16457 549 5364 1010 5028 526 5000 1010 16517 549 60 1010

10. Shutdown 0

549 1010 14147 16518 542 1

1010 28294 300 Cycles (2) 6264 375 6264 170 (50%)

17118 542 600 1010 (100%)

6864 330 600 88 17119 526 1

1010 16224 70 9360 50 57119 526 40000 1010 56224 70 40000 50

5. Turbine Generator Trip 60 Cycles (1, 2) 0 10 15 30 1830 2250 2310 2311 2911 2912 7912 526 526 526 526 526 549 549 542 542 526 526 10 5

15 1800 420 60 1

600 1

5000 1010 1135 1135 940 940 1010 1010 1010 1010 1010 1010 28294 (100%)

11. Design Hydrostatic Test 120 Cvcles (2) 100 0

1100 50 1981 (7%)

12. Hydrostatic Test 100 50 1981 1 Cycle (2)

I 1563 3 (7%)

_____ ______ j 50

1. The instant temperature change is assumed as 1-second time step.
2. The number of cycles is for 60 years [8].
3. 130'F is the Region I temperature for Transient 9, whereas the blend radius is at 268°F and the vessel is at 2687F, as was modeled previously [ 11].

File No.: 0801038.304 Revision: 1 Page 10 of 20 F0306-01

VStructural Integrity Associates, Inc.

Table 2: Heat Transfer Coefficients Flow Rate Thermal Region 100%

50%

12%

0% (Natural 1

Convection)

Region 1 3583 2058 657 112 Region 2 Linear transition from Region 1 and Region 3 values Region 3 2018 1159 370 112 Region 4 Linear transition from Region 3 and Region 5 values Region 5 1792 1029 329 101 Region 6 0.4 for all flow rates Note: All Heat transfer coefficients are in units of BTU/hr-ft2 -°F and are evaluated at 300'F.

Table 3: Temperature-Dependent Material Properties Material No.

Young's Tempera-

Modulus, Description ture, *F E x 106 (psi)

Mean Coefficient of Thermal Expansion, ax 10,6 (in/in- 0F)

Conductivity, k

(BTU/hr-ft-°F)

(see Note 1)

Diffusivity, d

(ft2/hr)

Specific Heat, cp (BTU/ibm-*F)

(see Note 4) 4 SA533 Grade B, 70 29.2 7.0 23.5 0.458 0.105

[Vessel Wall]

.200 28.5 7.3 23.6 0.425 0.114 (Mn-1/2AMo-1/2/2Ni) 300 28.0 7.4 23.4 0.401 0.119 400 27.4 7.6 23.1 0.378 0.125 500 27.0 7.7 22.7 0.356 0.130 600 26.4 7.8 22.2 0.336 0.135 2

SA-508 Class 2 70 27.8 6.4 23.5 0.458 0.105

[Nozzle Forging]

200 27.1 6.7 23.6 0.425 0.114 300 26.7 6.9 23.4 0.401 0.119 400 26.1 7.1 23.1 0.378 0.125 500 25.7 7.3 22.7 0.356 0.130 (See Note 2) 600 25.2 7.4 22.2 0.336 0.135 1,3 SA 240 Type 70 28.3 8.5 8.6 0:151 0.116 304, SS Clad, 200 27.6 8.9 9.3 0.156 0.122 SA 182 Type 300 27.0 9.2 9.8 0.160 0.125 F316 400 26.5 9.5 10.4 0.165 0.129

[Clad, Safe End]

500 25.8 9.7 10.9 0.170 0.131 (see Note 3) 600 25.3 9.8 11.3 0.174 0.133 Notes:

1.

2.

3.

4.

Convert to BTU/see-in-°F for input to ANSYS.

Properties of A508 Class II are used (3/4Ni-I/2Mo-1/3Cr-V).

Properties of 18Cr - 8Ni austenitic stainless steel are used.

Calculated as [k/(pd)]/122.

FileNo.: 0801038.304 Revision: I Page 11 of 20 F0306-01I

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AFLEAS 10*.T NULN Region 5 Region 6 Region 4 RegRion 2 Region 3 Recirc Outlet Nozzle Finite Element Model APP, 19 2007 13:35:14 Region 1 x

Figure 1: Nozzle and'Vessel Wall Thermal Boundaries File No.: 0801038.304 Revision: 1 Page 12 of 20 F0306-01

VStructural Integrity Associates, Inc.

4.0 CALCULATIONS 4.1 Piping Interface Loads From general structural mechanics [14], the membrane plus bending stresses at the inside surface of a thick-walled cylinder are:

az, = axial stress due to axial force = Fz/A cz, = axial stress due to bending moment = Mxy(ID/2)/I cz = czI + cyz2 TrO =.shear stress due to torsion = Mz(ID/2)/J Trz = shear stress due to shear force = 2Fxy/A, where F,, Fy, Fz, Mx, My, and M, are forces and moments at the pipe-to-safe end weld MxL = moment about x axis translated by length z = -L = M, - Fy L MyL = moment about y axis translated by length z = -L = My + Fx L Mxy = resultant bending moment = (MxL2 + MyL2 )0 5 Fxy = resultant shear force = (Fx2 F y2)0'5 ID, OD = inside and outside diameters A = area of cross section = (n/4)(OD 2 - ID 2)

I = moment of inertia = (ir/64)(OD4 - ID4)

J = polar moment of inertia = (70/32)(0D 4 - ID4)

The shear stresses are expressed in a local coordinate system with r radial (X in ANSYS coordinates), 0 circumferential (Z in ANSYS coordinates), and Z axial (Y in ANSYS coordinates). Tables 4 and 5 show the calculation of stresses; ID, OD, and L are taken from the previous piping load stress calculations [11, Section 3.4]. Forces and moments are taken from Reference 11, Table 1. Note that the IDs shown in Table 4 for the safe end and nozzle blend radius (25.938" and 37.368", respectively) represent the two most limiting locations for the nozzle (See Figure 3), and therefore do not represent the ID values where the HTCs were calculated.

File No.: 0801038.304 Page 13 of 20 Revision: 1 F0306-01:

Structural Integrity Associates, Inc.

Table 4: Recirculation Outlet Nozzle Attached Piping Loads and Dimensions [9, 11]

Safe End Nozzle Blend Radius Fx, kip 20.0 20.0 Fy, kip 20.0 20.0 F,, kip 30.0 30.0 Mx, kip-in 2004.0 2004.0 My, kip-in 3000.0 3000.0 Mz, kip-in 2004.0 2004.0 L, in 4.25 42.77 OD, in 28.38 55.88 ID, in 25.938 37.368 Table 5: Membrane Plus Bending Stresses Due to Piping Loads MxL, kip-in MyL, kip-in Mxy, kip-in F,,, kip-in A, in2 I, in4 J, in4 UYzi, ksi az, ksi cz, ksi

'rrO, ksi Tz, ksi Safe End 1919.00 3085.00 3633.15 28.28 104.18 9624.85 19249.69 0.288 4.895 5.183 1.350 0.543 Blend Radius 1148.60 3855.40 4022.86 28.28 1355.76 382912.48 765824.95 0.022 0.196 0.218 0.049 0.042 FileNo.: 0801038.304 Revision: 1 Page 14 of 20 F0306-01.

V Structural Integrity Associates, Inc.

Table 6: 0% Flow Regions 1 and 3 Heat Transfer Coefficients Pipe Inside Diameter, D =:

L..

inche- =

2.150 ft

\\ '

0.655 mn Outer Pipe, Inside radius, r.=,

12.9 inches =

1.075 ft 0.328 m

Inner Pipe Outside Diameter, D inches 0.000 ft 0.000 mi Inner Pipe, Outside radius, r, =

0 inches 0.000 ft 0.000 m

Fluid Velocity, V =

0.000 Itsec eOoo *' gpm=

0.

rlb/br Characteristic Length, L = D = r 2.150 ft =

0.655 m

T.. --..

AT : assumed to be 12% of fluid temperature =

8 0.40 12.00 r 24.00 36.00 40.00 60.00 72.00 "F

=

4.67 6.67 13.33 20.00 26.67 33.33 40.00 TC Value at Fluid Temperature. T [121 Units Conversion 70 100 200 300 400 500 600 F

Water Property Factor [19]

21.11 37.78 93.33 148.89 204.44 260.00 315.56 2C k

1.7307 0.5997 0.6300 0.67B4 0.63,-

0.6611 0.6040 0.5071 W/rr-C (Termal Conductivity) 0.3465 0.3640 0.30920 0.3950 0.382D 0.3490 02930 Btulhr-ft-'F k*.........

  • ..........o:

s ".........:*.*............*.o.

2 o......... f.L.r.:.-.'...

c; 4.109 4.165 4,179 4.229 4.313 4.522 4.902 6.322 kJlkg-=C (Seii~a)1.000 09 1.010 1.030 1,080 1.190 1.510 Btu/Ibnn.F

.............~ ~

~ ~ ~ ~ ~ ~ ~ ~~~~~~~~-

s !!.e.t...........................o......................oo......... o.3.o.........

......... =.9o....

.......!.=o...............

u..........

.916.01 97.1 004.7 982.7 917.6 650.6 784.9 679.2 t'gIm3 (Density) 62.3 62.1 60.1, 57.3 53.6 49.0 42.4 lbrnift

..................o*. *.....................................................

............... 6 :............

............................ 5 f.o..................

1.8 1.896E-04 3.24E-04 6.66E-04 1.016-03 1.40E-03 1.90E-03 3.15E-03 n*i:'_C (Volumetric: Rate of Expansion).

1:05E-04 1.80E-04 3.70E-04 15.60E-04 7.800E-04 1.10E-03 1.756E-03 felft-F

..... f.o.....

  • .o.t I..
  • n....

....,.o o.f......

o* ?*........ !.*........

1 0.3046 9.006 9.80f 9.,06 9.806 9.306 9.606 ME.606 Ms (Gravitational Constant) 32.17 32.17 32.17 32.17

32.17 32.17 32.17
  • s; M

1.4681 9.86E-04 6.926-04 3.07E-04 1.93E-04 1.38-04 1.04E-04 8.62E-015 lgm-s (Dy~namic Viscosity) 6.869-04 4.58E-04 2.06E-04 1.306-04 9.306-05 7.006-05 5.796-05 lbnrdft-s

  • t V...o..................................................**EO.

0..-....*O................O-.

7.O................. SZ*.5..........

0.......

Pr 6.980 4.510 1.910 1.220 0.950 0.859 1.070 (Prandtl Number)

Calculated Parameter Formula 70 100 200 300 4S0 500 T00 ReynoldMs Number, Re pVO/ft 0

0 0

0 0

0 0

GrasheofNumber. Gr gATL-/(Ip}

2441754517 1.2,97E+10 2.417E÷11 1.252E+12 3.9768E+12 1.034-+13 2.16049E+13 Grashof Number, Gr, gAAT(r.-rj)-'/(u~p-3.05E+08 1.506+D9 3.026+10 1.576+11 4.97E+11 1.29E612 2.70E+12 Rayleigh Number. Ru GrPr 170434-46531 5.7265E÷10 4.616.+11 1.528ME12 3.77770+12 8.8836+12 2.311726+13 Rayleigh Number, Ru GrPr 2.1356-09 7.16E+09 5.77E+10 1.91E611 4.72E+11 1.116+12 2.696.12 From [19):

Inside Surface Natural Convection Heat Transfer Coefficient:

Case:

Enclosed cylinder C

n'0.55l n= =fl H*,

C(OrPr)7'IL 181.85 258.65 46934 637.80 7"/'73.57 875.17 933.22 Wnr-'C 32.03 45.55 82.66

,i-,112.34U,.

136.24 154.13 164.35 Btufhr-ft:-*F FileNo.: 0801038.304 Revision: I Page 15 of 20 F0306-01.

VStructural Integrity Associates, Inc.

Table 7: 0% Flow Region 5 Heat Transfer Coefficient Pipe Inside Diameter, D =

.40..O0OW?Ž inches =

3.333 ft

=

1.016 m

Outer Pipe, Inside radius, r, =

20 inches =

1.667 ft 0.508 m

Inner Pipe Outside Diameter, D =

inches =

0.000 ft

= 0.600 m

Inner Pipe, Outside radius, r, =

0 inches =

0.000 ft 0.000 m

Fluid Velocity, V =

00,00 fusec 0

D pm=

0 Mitlhr Characteristic Length, L = D =

3.333 ft =

1.016 m

T_

T Lt = assumed to be 12% of fluid temperature =

0.40 12,00 24.00 3M.00, 46.00, 60.00 4.67 6.67 13.33 20.00 25.67 33.33 72.00

'F 40.00

=C Value at Fluid Temperature, T [121 Units Conversion 70 100 200 300 400 000 600

'F Water Property Factor [19]

21.11 37.78 93.33 140.89 204.44 260,00 3105.6

'C k

1.7307 0.5997 0.6300 0.6784 0.6636 0.6M11 0.6040 0.5071 W/M-lC (Thermal Conductivity) 0.a4605 0.36.40 0.3020 0.3950 0.3E20 0.3490 0.2930 tu/tir-ft-'F

... c *.

)........................................... o.....................

    • o..........:*.*.........z*
0.

Lo 0.3.*.

0

  • ~,
c.

4.1069 4.185 4.179 4229 4.313 4.522 4.002 6.322 Ij/Vg-'C (Specific Heat) 1.000 0.990 1.010 1.030 1.050 1.190 1.510 Btu'lbm-'F O

16.018 997.1 994.7 S62.7 917.8 056.6 784.0 679.2 kginý (Density) 62.3 62.1 60.1 57.3 5316 49.0 42.4 lbn~fe 1.0 1.0E-04

-:24-6..66-04 1.01E-03 1.400-03 1.9-SE3.

3.15E-03 m

r/m, C (Volumetric Rate of E*pansion) 1.05E-04 1.00E-04 3.730-34 5.605-04 7.80E-04 1.1OE-03 1.7zE-03

'/f-=F 9

0.3042 9.5,06 9.006

.9.006 9.006 9.806 9.805 9.606 tV':

(Graygaittinal Constant) 32.17 32.17 32.17 32.17 32.17 32.17 32.17 is.

/4"...........1.

14 S 99 E 0 2 -4 30 6 0

. 3 -4

1.

E-4"..................................1.

E-A1.4081 9.96E-114 6.82f-04 3.07E0-4 1.93E-04 1.38E-04 1.0,4E-D4 8.62E-05 kg~nm-s namic Viscosity) 6.69E-04 4.56E0-4 2.06E--04 1.30E-04 9.300-05 7.00--05 1.19E-01 infft-s

.P....

..r 6.............

"...1".......... *b Y*

  • 6* "........ "7*.............. ;*..............

Pr6.900 4.5110 1.910 1.220 0.9150 0.659 1.00 (Prandtl Number)

Calculated Parameter Formula 70 100 200 300 400 500 600

'F Reynold's Number, Re pVDat 0

0 0

0 0

0 0

GrashofNumb*er, Or g*ATL=/r4p}u 90S'9,61160-4.73190410 9.006E011 4.667E.ý12 1,.461S9E'13 3.854E+13 6.05143E+13 Grashof Number, Gr, gALT(rr,-?/(ta)a 1.14E49 5.915049 1.13E011 5.083011 1.85,+12 4.825-12 1.01E-13 Rayleigh Number, Ra GrPr 63515209008 2.134t1611 1.72E-12 5.69305÷12 1,40755413 3.315013 8.61503E+13 Rayleigh Number, Ra Gr5Pr 7.94E01-2.67E+10 2.15E-11 7.12E011 1.76E+12 4.145-12 1.08E+13 Fro m f191:

Inside Surface Natural Convection Hleat Transfer Coefficient:,

Case:

Enclosed cylinder C =

(1 n

,.-3-°'

.*)-.".

H..

C(GrPrY65WL 162*97 231.79 420.60 571.E6 693.25 704.30 836.32 W

.r.--C 2&.70 40.82 74.07

.103.6.O.

122.09 138.13 147.29 Btu/hr-ft:_F File No.: 0801038.304 Revision: 1 Page 16 of 20 F0306-01

Structural Integrity Associates, Inc.

+

I

"* I tMz Y,

S7Z Z

Figure 2: Coordinate System for Forces and Moments SST CLAD 103.00 R MIN LOW ALLOY STEEL NOZZLE SA 508 CL IIt 2.50 R,

REPLACEMENT PIPE SUPPLIED BY OTHERS I25.40 MIN 0 25.93 '_:'0, NOTE: NOZZLE DIMENSIONS ARE REFERENCE DIMENSIONS IN INCHES 14

-EXISTING SST (308 LI OVERLAY Figure 3: RO Nozzle and Safe End Geometry [201 File No.: 0801038.304 Revision: I Page 17 of 20 F0306-01

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5.0 RESULTS OF ANALYSIS This calculation package specifies the ASME Code Edition, finite element model, thermal and pressure transients (Table 1), and HTCs (Table 2) to be used in a fatigue usage calculation of the RO nozzle at Vermont Yankee. Thermal transient and pressure stress components will be calculated using ANSYS [6]

and will be combined with piping loads in subsequent calculations.

Linearized stress components will be used for the fatigue usage calculation. For the nozzle blend radius location, the stresses used in the evaluation will be for the base metal only; that is, the cladding material will be unselected prior to stress extraction consistent with ASME Code rules and Reference [13].

The fatigue usage calculation will consider all six stress components, and will be performed using the rules of Subarticle NB-3200 of Section III of the ASME Code [1]. Calculated fatigue usage factors will be multiplied by the appropriate environmental fatigue multipliers computed for each location.

The results of this calculation are to be used in SIA calculations: No. 081038.305, Stress Analysis of Reactor Recirculation Outlet Nozzle and No. 081038.306, Fatigue Analysis of Recirculation Outlet Nozzle File No.: 0801038.304 Revision: 1 Page 18 of 20 F0306-01I

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6.0 REFERENCES

1. American Society of Mechanical Engineers, Boiler and Pressure Vessel Code,Section III, Subsection NB, 1998 Edition, with Addenda through year 2000.
2. NUREG/CR-6583 (ANL-97/18), "Effects of LWR Coolant Environments on Fatigue Design Curves of Carbon and Low-Alloy Steels," March 1998.
3. J. P. Holman, "Heat Transfer," 5th Edition, McGraw Hill Inc.; 1981.
4. Structural Integrity Associates Calculation No. VY-16Q-305, Revision 0, "Recirculation Outlet Stress History Development for Nozzle Green Function."
5. CB&I, RPV Stress Report Sections S9 "Stress Analysis Recirculation Outlet Nozzle Vermont Yankee Reactor Vessel." and T9 "Thermal Analysis Recirculation Outlet Nozzle Vermont Yankee Reactor Vessel." CB&I Contract 9-620 1, SI File No. VY-16Q-204.
6. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
7. Structural Integrity Associates Calculation No. VY-16Q-304, Revision 0, "Recirculation Outlet Nozzle Finite Element Model."
8. Entergy Design Input Record (DIR), Rev. 1, EC No. 1773, Rev. 0, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-16Q-209.
9. GE Drawing No. 919D294, Revision 11, Sheet 7, "Reactor Vessel, Spec. Control," SI File No. VY-05Q-241.
10. American Society of Mechanical Engineers, Boiler and Pressure Vessel Code,Section II, Part D, 1998 Edition, with Addenda through year 2000.
11. Structural Integrity Associates Calculation No. VY-1 6Q-306, Revision 0, "Fatigue Analysis of Recirculation Outlet Nozzle."
12. N. P. Cheremisinoff, "Heat Transfer Pocket Handbook," Gulf Publishing Co., 1984.
13. NUREG/CR-6260 (INEL-95/0045), "Application of NUREG/CR-5999 Interim Fatigue Curves to Selected Nuclear Power Plant Components," March 1995.
14. Warren C. Young, "Roark's Formulas for Stress & Strain," Sixth Edition, McGraw-Hill Book Company, 1989.
15. NUREG/CR-5704, "Effects of LWR Coolant Environments on Fatigue Design Curves of Austenitic Stainless Steels," April, 1999.

FileNo.: 0801038.304 Page 19 of 20 Revision: 1 f0306-01i

V Structural Integrity Associates, Inc.

16. SI Calculation No. VY-19Q-301, Revision 0, "Design Inputs and Methodology for ASME Code Confirmatory Fatigue Usage Analysis of Reactor Feedwater Nozzle."
17. SI Calculation No. VY-19Q-302, Revision 0, "ASME Code Confirmatory Fatigue Evaluation of Reactor Feedwater Nozzle."
18. SI Calculation No. VY-19Q-303, Revision 0, "Feedwater Nozzle Environmental Fatigue Evaluation."
19. J. P. Holman, "Heat Transfer," 4th Edition, McGraw Hill Inc., 1976.
20. GE Stress Report 23A4316, Revision 0, "Stress Report-Reactor Vessel Recirculation Outlet Safe End," SI File No. VY-16-204.

File No.: 0801038.304 Revision: 1 Page 20 of 20 F0306-01

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APPENDIX A:

ANSYS Input File: RONVY.INP FileNo.: 0801038.304 Revision: 1 Page A-I of A-23 F0306-O1F

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ANSYS Input File: RONVY.INP finish

/clear, start

/prep7

/title, Recirc Outlet Nozzle Finite Element Model

/com,

PLANE42, 2-D Solid et,1,PLANE42,,,1

!Axisymmetric

/com,

/com, Material Properties

/corn,

MPTEMP,

, 70,200,300,400,500,600 tmp = 3600*12

! hr-ft to sec-in

/COM, Material #1 Safe-End and Portion of Piping (SA-182 F316) 8Ni)

MPDATA,EX

,1,, 28.3e6, 27.6e6, 27.0e6, 26.5e6, 25.8e6, MPDATA,ALPX,I,

, 8.5e-6, 8.9e-6, 9.2e-6, 9.5e-6, 9.7e-6, 6

(18Cr-25.3e6 9.8e-

MPDATA, KXX,1I,,

8.6/tmp, 9.3/tmp, 9.8/tmp, 10.4/tmp, 10.9/tmp, 11.3/tmp

MPDATA, C,1,

, 0.116, 0.122, 0.125, 0.129, 0.131, 0.133 mp, nuxy, 1, 0. 3 mp, dens, 1,0.283

/COM, Material #2 (Nozzle Forging) SA-508 Class 2 (3/4Ni-I/2Mo-I/3Cr-V)

MPDATA,EX

,2,

, 27.8e6, 27.1e6, 26.7e6, 26.1e6, 25.7e6, 25.2e6 MPDATA,ALPX,2,

, 6.4e-6, 6.7e-6, 6.9e-6, 7.le-6, 7.3e-6, 7.4e-6

MPDATA, KXX,2,

, 23.5/tmp, 23.6/tmp, 23.4/tmp, 23.1/tmp, 22.7/tmp, 22.2/tmp

MPDATA, C,2,

, 0.105, 0.114, 0.119, 0.125, 0.130, mp, nuxy, 2, 0. 3 mp, dens, 2,0.283 0.135

/COM, Material #3 (Cladding) SA-240 Type 304 (18Cr-8Ni)

MPDATA,EX

,3,

, 28.3e6, 27.6e6, 27.0e6, 26.5e6, 25.8e6, MPDATA,ALPX,3,

, 8.5e-6, 8.9e-6, 9.2e-6, 9.5e-6, 9.7e-6, 6

25.3e6

9. 8e-
MPDATA, KXX,3,

, 8.6/tmp, 9.3/tmp, 9.8/tmp, 10.4/tmp, 10.9/tmp, 11.3/tmp

MPDATA, C,3,

, 0.116, 0.122, 0.125, 0.129, 0.131, 0.133 mp, nuxy, 3, 0.3 File No.: 0801038.304 Revision: 1 Page A-2 of A-23 F0306-01I

Structural Integrity Associates, Inc.

mp, dens, 3,0.283

/COM, Material #4 (Vessel) SA-533, GR.

B (Mn-1/2Mo-1/2Ni)-

MPDATA,EX 14,

, 29.2e6, 28.5e6, 28.0e6, 27.4e6, 27.0e6, 26.4e6 MPDATA,ALPX,4,

, 7.0e-6, 7.3e-6, 7.4e-6, 7.6e-6, 7.7e-6, 7.8e-6

MPDATA, KXX,4,

, 23.5/tmp, 23.6/tmp, 23.4/tmp, 23.1/tmp, 22.7/tmp, 22.2/tmp

MPDATA, C,4,

, 0.105, 0.114, 0.119, 0.125, 0.130, 0.135 mp, nuxy, 4, 0. 3 mp,dens,4, 0.283

  • AFUN, DEG

/com,

      • Geometric Parameters *
  • set,vira, (103+3/16)

!Actual Vessel Inner Radius to base metal used for model

  • set,vir,2.0*vira

!2.0 time of Vessel Inner Radius to base metal used for model

  • settvw,5+5/8-3/16

!Vessel Wall Thickness

  • set, ril, 25.75/2
  • setrol 28.375/2
  • set,L1,5
  • set, ro2,28.375/2
  • set, L2,4.25
  • set, ro3,28.875/2
  • set, ro4,48.75/2
  • set, L3, 1.5
  • set, L4, 5.25
  • set, L5,7+1/16
  • set, L6, 12+13/16
  • setL7,9+7/8
  • set,L8, 9+3/8
  • set,L9, 31+15/16
  • set, L0, L9-12-13/16-tvw
  • set, ra, 7
  • set, rb, 1
  • set, rc, 5.25
  • set, rd, 2.5
  • set, tv, 3/16
  • set,dimA,vir-(tv*2.0)+L9+11+Ll

!Vessel Centerline to End of Safe End used for model

  • set,L21,1
  • set, L22,4.25
  • set,ri21, (25+15/16)/2

/com, Geometry File No.: 0801038.304 Page A-3 of A-23 Revision: 1 F0306-01,

VStructural Integrity Associates, Inc.

local, 13,0,, dimA,,.

csys, 13

/com, Begin at end of Safe-End Carbon Section k,

9, ril,

-1*(dimA) k, 2,f ril+tv, -l*(dimA) k, 3,

rol, -!*(dimA) k, 4,

ril,

-l*(dimA-Ll) k, 5,

ril+tv, -l*(dimA-Ll) k, 6,

rol, -l*(dimA-Ll) k, 7,

ril,

-T*(dimA-Ly-L2) k, 8, ril+tv, -1*(dimA-L5-L2) k, 9f ro2, -r*(dimA-Li-L2) k, 10, ril,

-I*(dimA-LI-L2-,L3) k,22, ril+tv, -I*(dimA-LI-L2-L3) k, 12,

1o3,

-r*(dimA-Lb-L2-L3) k, 13,

ril,

-1*(dimA.Ll-L2-L3-L4) k, 24, ril+tv, -I*(dimA-LI-L2-L3-L4) k, 15,

ro3,

-1*(dimA-Lt-L2-L3-L4) k, 16,

ril,

-1*(dimA-Lt-L2-L3-L4-L5) k, 17, ril+tv, -

t*(dimA-Ln-L2-L3-L4-L5) k, 18,

ro3,

-1*(dirtA-LP-L2-L3-L4-L5) k,19, ro4, -0*(dimA-LI-L2-L3-L4-L5-L7)! Temporary Point 1, 19, 18 1,18,15 fillc, 29,i3, 2,ira k,22, ro4+(LS+6)*tan(15),

-I*(dimA-LI-L2-L3-L4-L5-L7-(L8+6) 1, 19, 22 LFILLT, 1i, 4, rb k,

25,

ril,

-I*(dimA-LI-L2-L3-L4-L6) k, 26, ril+tv, -I*(dimA-Ll-L2-L3-L4-L6) k, 27, ril+(Ll0+tvw+ltv+4)*tan(15),

-l*(vir-tv-4) k, 28, ril+tv+(L10+tvw+t~v+4)*tan(15),

-l*(vir-tv-4) k,29, (vir+tvw+tv) tsin (45). -l* (vir+tvw+tv) *cos (45) k,30, 0,

-l*(vir+tvw+tv)

!Temporary Point k,31.,

0, 0 ! Temporary Point larc, 29, 30, 31, vir+tvw+tv k,32,

(.vir+tv)*sin(45), -1*(vir+tv)*cos(45)

File No.: 0801038.304 Page A-4 of A-23 Revision: I F0306-01I

Structural Integrity Associates, Inc.

k,33, 0,

-1*(vir+tv)

Temporary Point larc, 32, 33, 31,vir+tv k,34, vir*sin(45),

-1*vir*cos(45) k,35, 0,

-l*vir Temporary Point larc, 34,35,31,vir

LSTR, 4,

5

LSTR, 5,

6

LSTR, 6,

9

LSTR, 9,

12

LSTR, 12, 15
LSTR, 5,

8

LSTR, 4,

7

LSTR, 7,

10

LSTR, 8,

11

LSTR, 11, 14
LSTR, i0, 13
LSTR, 13, 16
LSTR, 14, 17
LSTR, 16, 25
LSTR, 17, 26
LSTR, 26, 28
LSTR, 25, 27
LSTR, 4,

1

LSTR, 1,

2

LSTR, 2,

3

LSTR, 3,

6

LSTR, 5,

2

LSTR, 7,

8

LSTR, 8,

9

LSTR, 12, 11
LSTR, 11, 10
LSTR, 13, 14
LSTR, 14, 15 FLST, 2,2,4, ORDE, 2 FITEM, 2,4 FITEM, 2, 6 LPTN, P51X FLST, 2,2, 4, ORDE, 2 FITEM, 2,8 FITEM, 2,25 LPTN, P51X FLST, 2,2,4,ORDE, 2 FileNo.: 0801038.304 Revision: 1 Page A-5 of A-23 F0306-01

V Structural Integrity Associates, Inc.

FITEM, 2, 7 FITEM, 2,24 LPTN, P51X FLST, 2, 6, 4, ORDE, 6 FITEM, 2, 6 FITEM, 2,25 FITEM, 2,37 FITEM, 2,40 FITEM, 2,42 FITEM, 2,44 LDELE,P51X,

.1 LFILLT,4,41,rd, 1*

LFILLT, 43, 8, rd,.

LFILLT, 39, 38, rc, FLST, 2,3, 4,ORDE, 3 FITEM, 2,1 FITEM, 2,3 FITEM, 2,5 LCOMB,P51X,

,0

LSTR, 16, 17
LSTR, 17, 21
LSTR, 25, 26
LSTR, 26, 24
LSTR, 22, 30
LSTR, 30, 35
LSTR, 27, 28
LSTR, 28, 33
LSTR, 29, 32
LSTR, 32, 34 k,39, 0,

-1*(vir+tvw+tv)

!Create Areas FLST, 2,4,4 FITEM, 2,27 FITEM, 2,30 FITEM, 2,26 FITEM, 2, 9 AL, P51X, FLST, 2,4,4 FITEM, 2,28 File No.: 0801038.304 Page A-6 of A-23 Revision: 1 F0306-011

V Structural Integrity Associates, Inc.

FITEM, 2,29 FITEM, 2, 10 FITEM, 2,30 AL, P51X FLST, 2,4,4 FITEM, 2, 11 FITEM, 2,32 FITEM, 2, 10 FITEM, 2, 14 AL, P51X FLST, 2,4,4 FITEM, 2, 15 FITEM, 2, 14 FITEM, 2, 9 FITEM, 2, 31 AL, P51X FLST, 2,4,4 FITEM,2,32 FITEM, 2,33 FITEM, 2, 12 FITEM, 2, 17 AL, P51X FLST, 2,4,4 FITEM, 2, 16 FITEM, 2, 17 FITEM, 2,31 FITEM, 2,34 AL, P51X FLST, 2,4,4 FITEM, 2,36 FITEM, 2, 13 FITEM, 2,33 FITEM, 2, 18 AL, P51X FLST, 2, 4, 4 FITEM, 2, 19 FITEM, 2, 18 FITEM, 2,35 FITEM, 2,34 AL, P51X FLST, 2,4,4 FITEM, 2,2 FITEM, 2, 5 FITEM, 2,36 FITEM, 2,21 AL, P51X FLST, 2,4,4 File No.: 0801038.304 Page A-7 of A-23 Revision: 1 F0306-01

Structural Integrity Associates, Inc.

FITEM, 2,20 FITEM, 2, 21 FITEM, 2, 3 FITEM, 2,35 AL, P51X FLST, 2,4,4 FITEM, 2, 1 FITEM, 2,37 FITEM, 2,23 FITEM, 2,5 AL, P51X FLST, 2,4,4 FITEM, 2,22 FITEM, 2,23 FITEM, 2,25 FITEM, 2,3 AL, P51X FLST, 2,4,4 FITEM, 2,38 FITEM, 2,42 FITEM, 2,37 FITEM, 2, 8 AL, P51X FLST, 2,4,4 FITEM, 2, 4 FITEM, 2,8 FITEM, 2,25 FITEM, 2,40 AL, PSIX FLST, 2,4,,4 FITEM, 2,24 FITEM, 2,45 FITEM, 2,7 FITEM, 2,42 AL, P51X FLST, 2,4,4 FITEM, 2, 6 FITEM, 2, 7 FITEM, 2,44 FITEM, 2,40 AL, P51X FLST, 2,4,4 FITEM, 2, 41 FITEM, 2,43 FITEM, 2, 47 FITEM, 2,44 AL, P51X File No.: 0801038.304 Page A-8 of A-23 Revision: 1 F0306-01.

VStructural Integrity Associates, Inc.

FLST, 2, 4,4 FITEM, 2,39 FITEM, 2, 46 FITEM, 2, 45 FITEM, 2,43 AL, P51X define materials FLST, 5,8,5, ORDE, 2 FITEM, 5,1 FITEM, 5, -8 CM, Y,AREA

ASEL,

,P51X CM, Y1,AREA CMSEL,S,_Y 1*

CMSEL,S, _YI

AATT, 1,,

1, 0,

CMSEL,S, Y

CMDELE, Y
CMDELE, Y1 1*

FLST, 5,5,5, ORDE, 5 FITEM, 5,9 FITEM, 5,11 FITEM, 5,13 FITEM, 5,15 FITEM, 5,18 CM, _Y,AREA

ASEL,

,P51X CM, _Y1,AREA CMSEL,S, Y

I*

CMSEL,S, Y1

AATT, 2,

1, 0,

CMSEL,S, Y

CMDELE, _Y

CMDELE, Y1 FLST, 5,5,5, ORDE, 5 FITEM, 5,10 FITEM, 5,12 FITEM, 5,14 FITEM, 5,16 FITEM, 5, -17 CM, _Y,AREA
ASEL,

,P51X File No.: 0801038.304 Page A-9 of A-23 Revision: I F0306-01:

V Structural Integrity Associates, Inc.

CM, _Y, AREA CMSEL, S, _Y CMSEL,S,_YI

AATT, 3,

1, 0,

CMSEL, S, _Y

CMDELE, Y
CMDELE, Y1 I*

!/com, Map mesh areas FLST, 5,10,4,ORDE, 10 FITEM, 5,5 FITEM, 5, 10 FITEM, 5,28 FITEM, 5,32 FITEM, 5,-33 FITEM, 5,36 FITEM, 5,-37 FITEM, 5,42 FITEM, 5,45 FITEM, 5, -46 CM, _Y,LINE

LSEL,

,P51X CM, Y1,LINE CMSEL,, _Y

LESIZE, Y1,,

,15,

,i 1*

FLST, 5,10,4, ORDE, 10 FITEM, 5,3 FITEM, 5,9 FITEM, 5,25 FITEM, 5,27 FITEM, 5,31 FITEM, 5,34 FITEM, 5,-35 FITEM, 5,40 FITEM, 5, 44 FITEM, 5,47 CM, Y,LINE

LSEL,

,P51X CM, YI,LINE CMSEL,, _Y I*

LESIZE,

.Y1,

,2, 1*

File No.: 0801038.304 Page A-10 of A-23 Revision: I F0306-011

V Structural Integrity Associates, Inc.

FLST, 5,3,4, ORDE, 3 FITEM., 5, 39 FITEM, 5, 41 FITEM, 5,43 CM, _Y, LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,, _Y

LESIZE, YI,

,80, l

1*

FLST,5,3,4,ORDE,3 FITEM, 5,6 FITEM, 5, -7 FITEM,5,24 CM, _Y,LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,, _Y

LESIZE, Y1,

,20, 1*

FLST, 5,3,4, ORDE, 3 FITEM, 5,4 FITEM, 5,8 FITEM, 5,38 CM, _Y,LINE

LSEL,

,P51X CM, Y1,LINE CMSEL,,__Y 1*

LESIZE,_Y1,

,40, fl FLST, 5,3,4,ORDE, 3 FITEM, 5,1 FITEM, 5,22 FITEM, 5, -23 CM, _Y,LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,, _Y

LESIZE, Y1,,

,30, FLST, 5, 6,4,ORDE, 6.

FITEM, 5,2 FITEM, 5,20 FileNo.: 0801038.304 Page A-I I of A-23 Revision: 1 F0306-011

0 Structural Integrity Associates, Inc.

FITEM, 5, -21 FITEM, 5,26 FITEM, 5,29 FITEM, 5, -30 CM, _Y, LINE

LSEL,

,,P51X CM, _Y1,LINE CMSEL,, _Y 1*

LESIZE, Y1,

,40,

,I 1*

FLST, 5, 9, 4, ORDE, 2 FITEM, 5, 11 FITEM, 5, -19 CM, Y,LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,,__Y 1*

LESIZE, Y1,

,20,

,i 1*

Meshing FLST, 5, 18,5, ORDE, 2 FITEM, 5,1 FITEM, 5, -18 SCM, _Y,AREA

ASEL,

,,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S,_Y 1*

MSHKEY, 1

AMESH, Y1 MSHKEY, 0 i*
CMDELE, Y

CMDELE, _Y1

CMDELE, Y2 1*

!Modify the safe end ID FLST, 2, 6, 5, ORDE, 2 FITEM, 2,1 FITEM, 2, -6 ACLEAR, P51X FLST, 2, 6, 5, ORDE, 2 File No.: 0801038.304 Page A-12 of A-23 Revision: 1 F0306-01

V Structural Integrity Associates, Inc.

FITEM, 2, 1 FITEM, 2, -6 ADELE, P51X FLST,2,9, 4,ORDE,7 FITEM, 2,9 FITEM, 2,14 FITEM, 2, -17 FITEM, 2,26 FITEM, 2, -27 FITEM, 2,30 FITEM, 2, -31 LDELE,P51X,

.1 FLST, 2,3,4,ORDE, 3 FITEM, 2,10 FITEM, 2,28 FITEM, 2,32 LDELE,P51X,

.1 FLST, 3,2,3, ORDE, 2 FITEM, 3,3 FITEM, 3,6 KGEN,2,P51X,

,,-ro2+ri2l,

,0 FLST, 3,1, 3,ORDE, 1 FITEM, 3,2 KGEN,2,P51X,

,L22,

,0 FLST, 3, 3,3, ORDE, 3 FITEM, 3,1 FITEM, 3, -2 FITEM, 3, 4 KGEN,2,P51X,

,,tv,

,0 FLST, 3,2, 3, ORDE, 2 FITEM, 3, 10 FITEM, 3,-li KGEN,2,P51X,

,-(L3-L21),

,0 FLST, 3, 1, 3, ORDE, 1 FITEM, 3,23 KGEN,2,P51X,

,5,

,0

LSTR, 23, 40 FLST,2,2,4,ORDE,2 FITEM, 2,9 FITEM, 2,12 LPTN, P51X
LDELE, 16,

,i FLST, 2,4,3 FITEM, 2, 11 FITEM, 2,23 FITEM, 2,41 FileNo.: 0801038.304 Page A-13 of A-23 Revision: I F0306-0t1

VStructural Integrity Associates, Inc.

FITEM, 2,12 A, P51X FLST, 2,4,3 FITEM, 2,23 FITEM, 2, 8 FITEM, 2, 9 FITEM, 2,41 A, P51X FLST,2, 4,3 FITEM, 2, 8 FITEM, 2, 7 FITEM, 2, 6 FITEM, 2, 9 A, P51X FLST, 2, 4,3 FITEM, 2,7 FITEM, 2, 5 FITEM, 2,3 FITEM, 2, 6 A, P51X FLST, 2,4,3 FITEM, 2, 10 FITEM, 2,20 FITEM, 2,23 FITEM, 2, 11 A, P51X FLST, 2,4,3 FITEM, 2,20 FITEM, 2, 4 FITEM, 2,8 FITEM, 2,23 A, P51X FLST, 2,4,3 FITEM, 2, 4 FITEM, 2,2 FITEM, 2,7 FITEM, 2, 8 A, P51X FLST, 2, 4,3 FITEM, 2,2 FITEM, 2, 1 FITEM, 2, 5 FITEM, 2,7 A, P51X FLST,5,8,5,ORDE, 4 FITEM, 5,1 FITEM, 5, -6 File No.: 0801038.304 Page A-14 of A-23 Revision: 1 F0306-OL

Structural Integrity Associates, Inc.

FITEM, 5, 19 FITEM, 5,-20 CM, _Y, AREA

ASEL,

,P51X CM, _Y1,AREA CMSEL,S, Y

1*

CMSEL,S, Y1

AATT, i,

1, 0,

CMSEL,S, Y

CMDELE, _Y

CMDELE, Y1 1*

FLST, 5, 4,4,ORDE, 4 FITEM, 5, 15 FITEM, 5, -16 FITEM, 5,26 FITEM, 5, 28 CM, _Y,LINE

LSEL,

,,P51X CM, Y1,LINE CMSEL,,_Y i*

LESIZE, YI,

,15,

,i 1*

FLST, 5,4,4,ORDE, 4 FITEM, 5,31 FITEM, 5,48 FITEM, 5,50 FITEM, 5,52 CM, Y,LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,, _Y 1*

LESIZE, Y1,

,2, 1

FLST, 5,6, 4,ORDE, 6 FITEM, 5,9 FITEM, 5,-l0 FITEM, 5, 12 FITEM, 5, 14 FITEM, 5, 30 FITEM, 5,32 CM, _Y,LINE

LSEL,

,P51X CM, Y1,LINE FileNo.: 0801038.304 Page A-15 of A-23 Revision: I F0306-01!

V Structural Integrity Associates, Inc.

CMSEL,, _Y 1*

LESIZE, Y1,,

, 6,

,i 1*

FLST, 5,3,4, ORDE, 3 FITEM, 5, 11 FITEM, 5, 17 FITEM, 5,49 CM, _Y, LINE

LSEL,

,,P51X CM, _Y1,LINE CMSEL,, _Y

LESIZE, Y1,

,12,

,i 1*

FLST, 5,3, 4,ORDE, 3 FITEM, 5,27 FITEM, 5,29 FITEM, 5,51 CM, _Y,LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,,__Y

LESIZE, Y1,,

,25,

,i 1*

FLST, 5, 8, 5, ORDE, 4 FITEM, 5,1 FITEM, 5, -6 FITEM, 5,19 FITEM, 5,-20 CM, _Y,AREA

ASEL,

,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y 1*

MSHKEY, 1

AMESH, Y1 MSHKEY, 0 i*
CMDELE, Y

CMDELE, _Y1

CMDELE, Y2 1*

FLST, 2,2,5, ORDE, 2 FileNo.: 0801038.304 Page A-16 of A-23 Revision: 1 F0306-01

V Structural Integrity Associates, Inc.

FITEM, 2,17 FITEM, 2, -18 ACLEAR,P51X csys, 0 k, 51,62/2,0,0 k,

52,62/2,60,0

LSTR, 51, 52 FLST, 2,2,5, ORDE, 2 FITEM, 2,17 FITEM, 2, -18 ADELE, P5IX iplo FLST, 2,4,4, ORDE, 4 FITEM, 2,39 FITEM, 2,41 FITEM, 2,43 FITEM, 2,53 LPTN, PSIX FLST, 2,2,4, ORDE, 2 FITEM, 2,60 FITEM, 2, -61 LDELE,P51X,

.1 FLST, 2,4,4 FITEM, 2,54 FITEM, 2, 62 FITEM, 2,55 FITEM, 2,44 AL, P51X FLST, 2,4,4 FITEM, 2,55 FITEM, 2,63 FITEM, 2,58 FITEM, 2,45 AL, P51X FLST,2,4,4 FITEM, 2,63 FITEM, 2,56 FITEM, 2,57 FITEM, 2,46 AL, P51X FLST, 2,4,4 FITEM, 2,47 FITEM, 2,59 FITEM, 2,57 FITEM, 2,62 AL, PSIX File No.: 0801038.304 Page A-17 of A-23 Revision: 1 F0306-01

Structural Integrity Associates, Inc.

CM, _Y, AREA

ASEL, 18 CM, _Y1,AREA CMSEL, S, _Y 1*

CMSEL,S, Y1

AATT, 2,

1, CMSEL, S, _Y

CMDELE, Y

CMDELE,, Y1 FLST, 5,2,5, ORDE, 2 FITEM, 5, 17 FITEM, 5,22 CM, _Y, AREA

ASEL,

,P51X CM, _Y1,AREA CMSEL,S, _Y 1*

0, CMSEL,S, Y1

AATT, CMSEL, S, _Y CMDELE, _Y CMDELE, __Y CM, Y, AREA
ASEL, CM, _Y1,AREA CMSEL, S, Y

CMSEL,S, Y1

AATT, CMSEL, S, _Y
CMDELE, Y

CMDELE, _YI 1*

3, r 1,

21 4,

j 1,

0, 0,

FLST, 5,3,4,ORDE, 3 FITEM, 5,54 FITEM, 5, -55 FITEM, 5,58 CM, _Y,LINE

LSEL,

,,P51X CM, Y1,LINE CMSEL,,__Y

LESIZE, Y1,

,8,

,i File No.: 0801038.304 Revision: 1 Page A-18 of A-23 F0306-011

Structural Integrity Associates, Inc.

FLST, 5,3,4,ORDE, 3 FITEM, 5, 56 FITEM, 5,-57 FITEM, 5,59 CM, _Y,LINE

LSEL,

,P51X CM, _Y1,LINE CMSEL,, _Y 1*

LESIZE, YI,

,40,

,i FLST, 5,2,5, ORDE, 2 FITEM, 5,17 FITEM, 5,-18 CM, Y,AREA

ASEL,

,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, Y

MSHKEY, 1

AMESH, Y1 MSHKEY, 0 L*
CMDELE, Y

CMDELE, _Y1

CMDELE, Y2 I*

FLST, 5,2,5, ORDE, 2 FITEM, 5,21 FITEM, 5, -22 CM, Y,AREA

ASEL,

,P51X CM, Y1,AREA CHKMSH, 'AREA' CMSEL,S, Y

i*

MSHKEY, 1

AMESH, Y1 MSHKEY, 0 CMDELE, Y
CMDELE, Y1
CMDELE, Y2 1*

File No.: 0801038.304 Page A-19 of A-23 Revision: 1 F0306-01

VStructural Integrity Associates, Inc.

!Simulating Butter FLST, 2,2,5,ORDE, 2 FITEM,2,9 FITEM, 2, -10 ACLEAR, P51X FLST, 2,2,5, ORDE, 2 FITEM, 2,9 FITEM, 2, -10 ADELE, P51X KGEN,2,15,

,11/16,

,0 KGEN,2,44,

,-0.25,

,0 KGEN,2,14,

,,11/16-1.375*tan(7.5) 0 KGEN,2,46,

,-0.25,

,0 FLST, 2, 3, 4,ORDE, 3 FITEM, 2,2 FITEM, 2,20 FITEM, 2, -21 LDELE, P51X

LSTR, 21, 44
LSTR, 44, 45
LSTR, 45, 15
LSTR, 17, 46
LSTR, 46, 47
LSTR, 47, 14
LSTR, 46, 44
LSTR, 45, 47
LSTR, 13, 16 FLST, 3,2, 3,ORDE, 2 FITEM, 3,46 FITEM, 3,-47 KGEN,2,P51X,

,,-0.25,

,0

LSTR, 48, 46
LSTR, 49, 47 FLST, 2,3,4,ORDE, 3 FITEM, 2,61 FITEM, 2,64 FITEM, 2, -65 LPTN, P51X FLST, 2,2,4,ORDE, 2 FITEM, 2,70 FITEM, 2, -71 LDELE,P51X,

.1 FLST, 2,4,4 FITEM, 2, 67 FITEM, 2,39 File No.: 0801038.304 Page A-20 of A-23 Revision: 1 F0306-01

Structural Integrity Associates, Inc.

FITEM, 2,68 FITEM, 2, 3 AL, P51X FLST, 2,4,4 FITEM, 2,39 FITEM, 2, 5 FITEM, 2, 2 FITEM, 2,53 AL, P51X FLST, 2,4,4 FITEM, 2,20 FITEM, 2, 60 FITEM, 2,53 FITEM, 2, 41 AL, P51X FLST, 2,4,4 FITEM, 2,72 FITEM, 2,68 FITEM, 2,69 FITEM, 2,41 AL, P51X FLST, 2,4,4 FITEM, 2,21 FITEM, 2,60 FITEM, 2,36 FITEM, 2,43 AL, P51X FLST, 2,4,4 FITEM, 2,66 FITEM, 2,69 FITEM, 2,35 FITEM, 2,43 AL, P51X CM, _Y, AREA

ASEL, 10 CM, Y1,AREA CMSEL, S, _Y 1*

CMSEL,S, Y1

AATT, 2,

1, 0,

CMSEL, S, _Y

CMDELE, Y
CMDELE, Y1 1*

FLST, 5,3,5, ORDE, 3 FITEM, 5, 9 FileNo.: 0801038.304 Page A-21 of A-23 Revision: 1 F0306-011

Structural Integrity Associates, Inc.

FITEM, 5,23 FITEM, 5,-24 CM, Y, AREA

ASEL,

,P51X CM, Y1,AREA CMSEL,S, _Y 1*

CMSEL,S, __Y

AATT, 3,

1, 0,

CMSEL,S, Y

CMDELE, Y

CMDELE, _Y1 FLST, 5,2, 5, ORDE, 2 FITEM, 5,25 FITEM, 5, -26 CM, Y,AREA

ASEL,

,P51X CM, _Y1,AREA CMSEL,S, Y

1, CMSEL,S, _YI

AATT, i,

i, 0,

CMSEL,S, _Y

CMDELE, Y
CMDELE, Y1 1*

FLST, 5,3,4,ORDE, 3 FITEM, 5,2 FITEM, 5,39 FITEM, 5,67 CM, Y,LINE

LSEL,

,P51X CM, Y1,LINE CMSEL,, _Y i*

LESIZE, YI,

,10, FLST, 5, 6, 4,ORDE, 6 FITEM, 5,20 FITEM, 5,-21 FITEM, 5,41 FITEM, 5,43 FITEM, 5,66 FITEM, 5,72 CM, Y,LINE

LSEL,

,,P51X File No.: 0801038.304 Page A-22 of A-23 Revision: 1 F0306-O.

Structural Integrity Associates, Inc.

CM, _Y1, LINE CMSEL,, _Y

LESIZE, Y1,,

,2,

,i 1*

FLST, 5, 2, 5, ORDE, 2 FITEM,5, 9 FITEM, 5,-i0 CM, _Y,AREA

ASEL,

,P51X CM, Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y 1*

MSHKEY,1 AMESH, _Y1 MSHKEY, 0 CMDELE,1Y

CMDELE, Y1 CMDELE, _Y2 I*

FLST, 5,4,5, ORDE, 2 FITEM, 5,23 FITEM, 5, -26 CM, _Y,AREA

ASEL,

,P51X CM, _Y1,AREA CHKMSH, 'AREA' CMSEL,S, _Y MSHKEY, 1

AMESH, Y1 MSHKEY, 0 1*
CMDELE, Y

CMDELE, _YI

CMDELE, Y2 1*

save finish File No.: 0801038.304 Page A-23 of A-23 Revision: 1 F0306-01,

Structural Integrity Associates, Inc.

File No.: 0801038.305 CALCULATION PACKAGE Project No.: 0801038 Quality Program Z Nuclear [] Commercial PROJECT NAME:

VY Confirmatory Analysis for the CS and RO Nozzles CONTRACT NO.:

10163217 Amendment 5 CLIENT:

PLANT:

Entergy Nuclear Operations, Inc Vermont Yankee Nuclear Power Station CALCULATION TITLE:

Stress Analysis of Reactor Recirculation Outlet Nozzle Project Manager Preparer(s) &

Document Affected Revision Description Approval Checker(s)

Revision Pages Signature & Date Signatures & Date 01

- 16 Initial issue.

Preparer:

Gary L. Stevens Computer Files 01/07/09 Tyler Novotny 01/07/09 Checker:

R. D. Dixon 01/07/09 1

1-9, 11, 15 Revised per summary Preparer:

contained in Section 1.1.

Changes are marked with revision bars" in right-0 9

TlrDNnt hand margin.

03/09/09 Tyler D. Novotny 03/09/09 Checker:

Tim D. Gilman 03/09/09 Page 1 of 16 F0306-OIRO

VStructural Integrity Associates, Inc.

Table of Contents 1.0 O B JE C T IV E.................................................................................................................................

3 1.1 Changes Made in Revision 1 of this Calculation...........................................................

3 2.0 METHODOLOGY...............................................................................................................

3 3.0 ASSUMPTIONS / DESIGN INPUTS.....................................................................................

4 4.0 C A L C U L A T IO N S........................................................................................................................

4 4.1 Finite Element Unit Pressure Stress Analysis.................................................................

4 4.2 Thermal Transient Stress Analysis..................................................................................

4 4.3 Determining Critical Stress Paths..................................................................................

5 4.4 Stress C alculation...........................................................................................................

.. 6 4.5 Piping L oads...............................................................................................................

7 5.0 RESULTS OF ANALYSIS.....................................................................................................

8 6.0 R E FE R E N C E S.............................................................................................................................

9 List of Tables Table 1: Pressure Stress Intensity Results (1,000 psi)......................................................................

.7 Table 2: Stresses Under Unit Pressure Load, psi..................................

10 Table 3: Example Thermal Stress Result Output, psi.........................................................................

11 List of Figures Figure 1. RO Nozzle Internal Pressure Distribution......................................................................

12 Figure 2. RO Nozzle Pressure Cap Load & Boundary Condition.................................................

13 Figure 3. RO Nozzle Vessel Wall Boundary Condition...............................................................

14 Figure 4. Safe End Critical Thermal Stress Intensity Location..........................................................

15 Figure 5. Nozzle Blend Radius Limiting Pressure Stress Intensity Location.................................

16 Figure 6. Limiting Stress Paths.....................................................................................................

16 FileNo.: 0801038.305 Page 2 of 16 Revision: 1 F0306-OIRO

1.0 OBJECTIVE The objective of this calculation package is to obtain stress distributions for the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at the Vermont Yankee Nuclear Power Station.

ANSYS [1] thermal transient and pressure stress analyses are performed, along with calculation of stresses due to attached piping loads. The stress results will be used for a subsequent ASME Code,Section III NB-3200 [2] fatigue usage calculation.

1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision 1 of this calculation:

a. Transient 9 described in Section 4.3 was changed to more precisely match the Green's Function analysis. This also required modification of the input files VY_RONTRAN9-T.INP and VY RON TRAN9-S.INP.
b. The input files VY_RON_TRAN2-T.INP and VY_RONTRAN2-S.INP were modified to include a finer time step around 601 seconds.
c. A Kt value of 1.53 that was conservatively applied to piping loads at blend radius was changed to Kt = 1.0 to match the Green's Function analysis.
d. Table 3 was revised because the input file VYRONTRAN4-T.INP was updated to correct a conservative misapplication of a temperature ramp rate.
e. Figure 4 was revised because Transient 9, which produced Figure 4, was modified.
f. All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.

2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package

[3]. A previously developed finite element model (FEM) [3] of the RO nozzle is used to perform thermal and pressure stress analyses using ANSYS [1]. A thermal transient analysis is performed for each defined transient. Concurrent with the thermal transients are pressure and piping interface loads. For these loads, unit load analyses (based on finite element analysis for pressure and manual calculations for attached piping loads) are performed. All six components of the stress tensor are determined in the stress calculations.

The fatigue usage calculation and environmental fatigue usage analysis will be performed in a separate calculation package. That subsequent calculation will utilize the thermal and pressure stresses determined in this calculation, along with stresses due to attached piping loads provided in Tables 4 and 5 of Reference [3]. The stresses due to pressure and the attached piping loads will be scaled based on the temperature and pressure magnitudes during each individual transient, and the location being analyzed. The appropriate nozzle blend radius effects factor will also be applied to the total stresses for the nozzle blend radius location.

FileNo.: 0801038.305 Page 3 of 16 Revision: 1 F0306-O1RO

3.0 ASSUMPTIONS / DESIGN INPUTS Assumptions and design inputs were previously established in Section 3.0 of the Reference [3]

calculation. Assumption 3.1.3 of Reference [3] was verified in this calculation package by plotting the stress components of each transient in ANSYS. If the stress components plot did not contain a step change at the end of the transient, the steady state portion, the steady state time step assumed was determined to be adequate.

4.0 CALCULATIONS 4.1 Finite Element Unit Pressure Stress Analysis A uniform pressure of 1,000 psi was applied to the FEM along the inside surface of the RO nozzle and the RPV wall (Figure 1). A pressure load of 1,000 psi was used because it is easily scaled up or down to account for different pressures that occur during transients. In addition, a membrane stress "cap load" was applied to the modeled end of the piping attached to the RO nozzle safe end. This membrane stress was calculated as follows:

PD.

P PDi 2 Pcap =

2 2

where:

P = Pressure = 1,000 psi unit load Di= Inner Diameter at end of model = 25.9375 in Do = Outer Diameter at end of model = 28.375 in Therefore, the membrane stress is 5,082 psi. The calculated value is given a negative sign in order for it to exert tension on the piping end of the model. The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, input file RONVY.INP]. The ANSYS input file VY RON P.INP contains the pressure loading. Figure 1 shows the applied 1,000 psi internal pressure distribution. At the vessel wall, a symmetric boundary condition is applied. At the piping end of the model, axial displacement is coupled to simulate the effect of the attached piping that is not modeled. Figure 2 and Figure 3 show the boundary conditions.

4.2 Thermal Transient Stress Analysis The FEM geometry input file is taken from the calculation that specifies the design and methodology inputs [3, file RONVY.INP], and is used as input to the files in which the thermal transient and pressure stress analyses are performed.

For the thermal transient ANSYS analyses, previously defined thermal transients [3, Table 1 ] are evaluated, applying heat transfer coefficients [3, Table 2], as appropriate, based on the flow rates for each individual transient.

Each thermal transient is evaluated in ANSYS to determine the resulting temperature distributions.

The thermal results are used as input for the stress analysis for each transient. The boundary FileNo.: 0801038.305 Page 4 of 16 Revision: 1 F0306-O1RO

Structural Integrity Associates, Inc.

conditions used for the pressure load case were also applied to the thermal stress cases. Figure 2 and Figure 3 show the application of these boundary conditions.

All ANSYS input files for the thermal analyses, as listed below, are saved in the project computer files:

RON VYINP: Geometry and material properties VYRON TRAN]-T.INP, VYRONTRAN]-S.INP: Transient 1, thermal and stress analyses VYRONTRAN2-TINP, VY_RONTRAN2-S.INP: Transient 2, thermal and stress analyses VY_RON TRAN3-T.INP, VYRONTRAN3-S.INP: Transient 3, thermal and stress analyses VYRONTRAN4-T.INP, VY RONTRAN4-S.INP: Transient 4, thermal and stress analyses VYRONTRAN5-T.INP, VYRONTRAN5-S.INP: Transient 5, thermal and stress analyses VY RON TRAN6-T.INP, VY RON TRAN6-S.INP: Transient 6, thermal and stress analyses VYRONTRAN7-T.INP, VYRONTRAN7-S.INP: Transient 7, thermal and stress analyses VYRONTRAN8-T.INP, VY RON TRAN8-S.INP: Transient 8, thermal and stress analyses VYRONTRAN9-TINP, VYRONTRAN9-S.INP: Transient 9, thermal and stress analyses VYRONTRANIO-T.INP, VY RON TRANIO-S.INP: Transient 10, thermal and stress analyses VYRON_TRAN))-T.INP, VYRONTRAN1-US.INP: Transient 11, thermal and stress analyses VYRON_TRAN12-T.INP, VYRONTRAN12-S.INP: Transient 12, thermal and stress analyses 4.3 Determining Critical Stress Paths The thermal transient that is to be used in determining the critical stress path at the safe end was determined by the most severe temperature difference over the shortest amount of time. This transient, Transient 9, is intended to represent the worst case thermal transient. This occurs during the Improper Startup cycle per Reference [3, Table 1]. The thermal transient conditions are:

12% flow rate heat transfer coefficients.

Thermal shock from 526°F to 130'F along the inside surface of the nozzle safe end and piping and a blend radius and lower vessel thermal shock from 5260F to 2680F.

  • Constant temperatures from previous step for 26 seconds
  • Thermal shock from 130'F to 526°F along the inside surface of the nozzle safe end and piping and a blend radius and lower vessel thermal shock from 268'F to 526°F.

Steady state temperature conditions following thermal shocks.

  • Constant temperature of 120'F on the outside surface of the model.

The ANSYS input files for the analysis, as listed below, are saved in the project computer, files:

RONVYINP. Geometry and material properties VYRONTR4N9-T.INP, VYRONTRAN9-S.INP: Thermal and stress analysis for the worst case transient for the safe end An interactive review of the worst case thenral stress results (which are controlling for the safe end) showed the critical location in the model to be at Node 6395. The location of Node 6395 is shown in FileNo.: 0801038.305 Page 5 of 16 Revision: 1 F0306-O1RO

Figure 4. This location was selected since it possessed the highest stress intensity during the worst case thermal transient. This is the same location evaluated in Reference [4].

A critical stress location in the nozzle blend radius will also be analyzed. This location is chosen based upon the highest pressure stress (which is controlling in the nozzle blend radius) in the base metal. An interactive review of the pressure stress intensity results showed the critical location in the nozzle blend radius to be at Node 3829 (Figure 5). This is the same location evaluated in Reference [4].

Figure 6 shows the two critical stress paths that will be used to extract the linearized stresses at the safe end and nozzle blend radius.

4.4 Stress Calculation Linearized stresses from Node 6395 (safe end inside surface) and Node 3829 (nozzle blend radius inside surface of base metal) are used for the fatigue usage analysis, as shown in Figure 6. For the nozzle blend radius location, the stresses used are for the base metal only; since the cladding is of the integrally bonded type and is less than 10% of the total thickness of the section the material is unselected prior to stress extraction, per NB-3 122.3 [2].

The pressure stress intensities for the safe end and blend radius paths were extracted using the ANSYS file VY/RONP.INP. This produced one file, ROPRESSURE.lin, that contains results of the critical stress paths.

Table 1 shows the final pressure stress intensity results for the safe end and blend radius. The results at the blend radius are slightly different from those reported in Table 2 of Reference [4] as a result of the revised material properties (i.e., temperature dependent material properties were used in the current evaluation vs. constant material properties in Reference [4]).

Results were also extracted from the vessel portion of the model to verify the accuracy of the results obtained from the ANSYS model, and to check the results due to the use of the 2.0 multiplier on the vessel radius. These results are contained in the file RO PRESSURE. lin. The radius of the finite element model (FEM) was multiplied by a factor of 2.0 [4] to account for the fact that the vessel portion of the axisymmetric model is a sphere, but the true geometry is the intersection of two cylinders.

The equation for the membrane hoop stress in a thin wall sphere is:

0 (pressure) x (radius))

S 2 x th~ickes Considering an actual vessel base metal radius, R, of 105.906 inches increased by a factor of 2.0, a vessel base metal thickness, t, of 5.4375 inches, and an applied pressure, P, of 1,000 psi, the calculated stress for a thin wall sphere is PR/(2t) = 19,477 psi. This compares very well with the remote vessel wall membrane hoop stress from the ANSYS result file, ROPRESSURE.lin, of FileNo.: 0801038.305 Page 6 of 16 Revision: 1 F0306-O1 RO

18,070 psi. Thus, considering the peak total pressure stress of 31,270 psi, the stress concentrating effect of the nozzle blend radius is 31,270/19,477 = 1.61. In other words, the peak nozzle blend radius stress is 1.61 times higher than nominal vessel wall stress for the axisyimnetric model.

The equation for the membrane hoop stress in a thin wall cylinder is:

((pressure) x (radius) k thickness j"

Based on the previous dimensions, the calculated stress for a cylinder without the 2.0 factor is 19,477 psi. Increasing this by a factor of 1.61 yields an expected peak nozzle blend radius stress of 31,358 psi, which would be expected from a cylindrical geometry that is representative of the nozzle configuration. Therefore, the result from the ANSYS file for the peak nozzle blend radius stress (31,270 psi) is close to the peak nozzle blend radius stress for a cylindrical geometry because of the use of the 2.0 multiplier. This is consistent with SI's experience where a factor of two increase in radius is typical for representing the 3-D effect in an axisymmetric model.

4.5 Piping Loads The piping loads were taken from Table 4 of Reference [3]. To determine the piping load stresses, the distances from the applied piping loads to the limiting stress locations were first determined. The limiting stress path locations from Section 4.3 are in the same locations assumed in Table 4 of Reference [3]; this means that no reconciliation of the lengths in Table 4 of Reference [3] is needed.

Reference [3, Section 4.1 ] methodology was used to calculate the piping load stresses. The piping loads and piping load stresses are found in Table 4 and Table 5 of Reference [3].

Table 1: Pressure Stress Intensity Results (1,000 psi)

Membrane plus Total Stress Location Bending Stress Intensity Intensity (psi)

(psi)

Safe End (Path 1 Inside) 11,350 11,490 Blend Radius (h2nd 30,540 31,270 (Path 2 Inside)

FileNo.: 0801038.305 Page 7 of 16 Revision: 1 F0306-01RO

5.0 RESULTS OF ANALYSIS A thennal transient analysis for each defined transient, as well as unit pressure stress and piping interface load analyses were performed for the RO nozzle at Vermont Yankee. All six components of the stress tensor were extracted from the ANSYS model at the two limiting path locations, which are the same two locations previously evaluated [4]. Table 2 provides the unit (1,000 psig) pressure stress analysis results. The unit pressure load results are used to choose the location to analyze at the

  • nozzle blend radius and will be scaled up or down based on applied pressures in the fatigue analysis.

Table 5 of Reference [3] provides the piping stresses at the two critical locations. Table 3 shows an example of thermal stress results. The remaining thermal stress results are contained in the ANSYS output files, listed below, which are saved in the project computer files:

ROPRESSURE. lin: Unit pressure stress analysis results VYRONTRAN]-S.lin: Transient 1, thermal stress analysis results VYRONTRAN2-S.lin: Transient 2, thermal stress analysis results VYRON TRAN3-S.lin: Transient 3, thermal stress analysis results VY RONTRAN4-S.lin: Transient 4, thermal stress analysis results VYRONTRAN5-S.lin: Transient 5, thermal stress analysis results VYRON TRAN6-S. lin: Transient 6, thermal stress analysis results VYRONTRAN7-S. lin: Transient 7, thermal stress analysis results VYRONTRAN8-S.lin: Transient 8, thermal stress analysis results VYRON TRAN9-S. lin: Transient 9, thermal stress analysis results, VYRONTRAN]O-S.lin: Transient 10, thermal stress analysis results VYRONTRAN]1-S.lin: Transient 11, thermal stress analysis results VYRONTRAN12-S.lin: Transient 12, thermal stress analysis results A fatigue calculation using the methodology of Subarticle NB-3200 of Section III of the ASME Code [2] and an enviromnental fatigue usage analysis will be performed in a separate calculation package using the stress results from this calculation.

The results of this calculation are to be used in SI Calculation No. 081038.306, "Fatigue Analysis of Recirculation Outlet Nozzle."

File No.: 0801038.305 Page 8 of 16 Revision: 1 F0306-O1RO

6.0 REFERENCES

1. ANSYS, Release 8.1 (w/Service Pack 1), ANSYS, Inc., June 2004.
2. ASME Boiler and Pressure Vessel Code,Section III, Subsection NB, 1998 Edition with 2000 Addenda.
3. SI Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Confirmatory Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle."
4. SI Calculation No. VY-16Q-305, Revision 0, "Recirculation Outlet Stress History Development for Nozzle Green Function."

File No.: 0801038.305 Revision: 1 Page 9 of 16 F0306-O1RO

VStructural Integrity Associates, Inc.

Table 2: Stresses Under Unit Pressure Load, psi Membrane plus Bending Total Node S

Sz S

SY Syz Sx x

SY Sz Sxy Syz Sxz SE 6395

-955.2 4420 10390 15.26 0

0

-955.2 4912 10530

-222.6 0

0 BR 3829

-718.7

-951.7 25000 4708 0

0

-718.7 206.2 30150 733.2 0

0 FileNo.: 0801038.305 Revision: 1 Page 10 of 16 F0306-01RO

V Structural Integrity Associates, Inc.

Table 3: Example Thermal Stress Result Output, psi Transient Node Time Membrane Plus Bending Total (s)

Sx Sy Sz Sxy Syz Sxz Sx Sy Sz Sxy Syz Sxz 0

-33

-3379 196 351 0

0

-33

-3539 139 209 0

0 3

-33

-3367 207 351 0

0

-33

-3518 160 209 0

0 13

-33

-3340 231 350 0

0

-33

-3493 180 208

.0 0

233 180 11400.

12840 210 0

0 180 16290 17350

-536 0

0 2213

-74

-5983

-2660 293 0

0

-74

-7056

-3558 322 0

0 2393 149 8475 9884 164 0

0 149 12580 13670

-416 0

0 6773

-51

-4443

-1020 320 0

0

-51

-5018

-1463 256 0

0 7193 231 12680 13780 145 0

0 231 17340 18140

-588 0

0 6395 7493 10

-142 2054 221 0

0 10 164 2398 45 0

0 11093

-40

-3276

-654 256 0

0

-40

-3669

-954 192 0

0 16457

-47

-4080

-479 352 0

0

-47

-4491

-773 244 0

0 16517

-41

-3813

-231 351 0

0

-41

-4095

-404 230 0

0 16518

-28

-3689

-110 350 0

0

-28

-3383 297 199 0

0 17118

-33

-3241 307 349 0

0

-33

-3393 255 204 0

0 17119 3

-2918 623 348 0

0 3

-1521 2098 125 0

0 57120

-33

-3283 279 350 0

0

-33

-3439 223 206 0

0 0

3078 2100 4262 554 0

0 3078 4281 5859 577 0

0 3

3078 2100 4262 554 0

0 3078 4280 5856 577 0

0 13 3078 2099 4263 554 0

0 3078 4278 5853 576 0

0 233 823 6811

-8426

-847 0

0 823 12480 38540 5953 0

0 2213 3002

-447 2916 683 0

0 3002 1782

-3944

-735 0

0 2393 799 3298

-10540

-506 0

0 799 9988 25870 4515 0

0 6773 2953

-85 3049 980 0

0 2953 2409

-2931

-397 0

0 7193 1539 6354

-2971 49 0

0 1539 9542 24620 4575 0

0 3829 7493 1642 7294 6946 137 0

0 1642 6282 20660 2675 0

0 11093 2290 364 2825 500 0

0 2290 2225 882

-131 0

0 16457 3195 285 3758 754 0

0 3195 3045 526

-230 0

0 16517 3191 304 3705 753 0

0 3191 3131 687

-181 0

0 16518 3182 300 3699 752 0

0 3182 3120 680

-180 0

0 17118 3157 1120 3848 706 0

0 3157 3802 3273 233 0

0 17119 3127 1109 3832 704 0

0 3127 3771 3247 235 0

0 57120 3077 2085 4216 543 0

0 3077 4274 5877 573 0

0 Note: Not all time steps are listed in this table.

File No.: 0801038.305 Revision: 1 Page 11 of 16 F0306-01RO

U Structural Integrity Associates, Inc.

1 ft WE PRES-NORM xw%

11-

ý Figure 1. RO Nozzle Internal Pressure Distribution File No.: 0801038.305 Revision: 1 Page 12 of 16 F0306-OIRO

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AN 2...............

Figure 2. RO Nozzle Pressure Cap Load & Boundary Condition File No.: 0801038.305 Revision: 1 Page 13 of 16 F0306-01 RO

Structural Integrity Associates, Inc.

Figure 3. RO Nozzle Vessel Wall Boundary Condition FileNo.: 0801038.305 Page 14 of 16 Revision: 1 F0306-O1RO

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I M,y, = R-.-..;, -R.

Figure 4. Safe End Critical Thermal Stress Intensity Location File No.: 0801038.305 Revision: 1 Page 15 of 16 F0306-O1RO

Structural Integrity Associates, Inc.

AM.N NODAL SOLUTION STEp=1

.0114 (AVG~)

DMV4~~9 S3P4

'/4 Figure 5. Nozzle Blend Radius Limiting Pressure Stress Intensity Location Figure 6. Limiting Stress Paths File No.: 0801038.305 Revision: I Page 16 of 16 F0306-O1RO

V Structural Integrity Associates, Inc.

File No.: 0801038.306 CALCULATION PACKAGE Project No.: 0801038 Quality Program Z Nuclear E] Commercial PROJECT NAME:

VY Confirmatory Analyses for CS and RO Nozzles CONTRACT NO.:

10163217 Amendment 5 CLIENT:

PLANT:

Entergy Nuclear Operations, Inc.

Vermont Yankee Nuclear Power Station CALCULATION TITLE:

Fatigue Analysis of Reactor Recirculation Outlet Nozzle D

Project Manager Preparer(s) &

Document Affected Revision Description Approval Checker(s)

Revision Pages Signature & Date Signatures & Date 01

- 18 Initial issue.

Gary L. Stevens Tyler Novotny Computer Files 01/07/09 01/07/09 Jennifer E. Smith 01/07/09 1

1-4,6-12, 14-19 Revised per summary

,/

Preparer:

contained in Section 1.1.

LL

.'t44 P

a Computer Files Changes are marked with "revision bars" in right-Gary L Stevens hand margin.

03/09/09 Tyler D. Novotny 03/09/09 Checker:

William F. Weitze 03/09/09 Page 1 of 19 F0306-OIRO

Structural Integrity Associates, Inc.

Table of Contents 1.0 O B JE C T IV E.................................................................................................................................

3 1.1 Changes Made in Revision I of this Calculation...........................................................

3 2.0 M ETH OD OLO G Y..............................................................................................................

3 3.0 D E SIG N IN PU T S.........................................................................................................................

4 3.1 Stress C alculation..........................................................................................................

4 3.2 Fatigue Usage Analysis, General...................................................................................

4 3.3 Event Cycles, V ESLFA T..............................................................................................

5 3.4 Material Properties, VESLFAT......................................

5 3.5 Stress Indices..............................................................................................................

ý6 4.0 C A L C U L A T IO N S.........................................................................................................................

6 5.0 RESULTS OF AN A LY SIS.....................................................................................................

7

6.0 CONCLUSION

S AND DISCUSSIONS...............................................................................

7 7.0 R E FE R E N C E S.............................................................................................................................

8 List of Tables Table 1: Safe End Load Sets as Input to VESLFAT.......................................................................

9 Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT.......................

1......

I Table 3: Temperature-Dependent Material Properties for VESLFAT (3)

............................ 12 Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves.........................................

13 Table 5: Pressure and Attached Piping Unit Load Case Stress Components................................

14 Table 6: Fatigue Usage Calculation for the Safe End.................................

15 Table 7: Fatigue Usage Calculation for the Nozzle Blend Radius.................................................

16 Table 8: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location.......................

17 Table 9: Linearized Stress Files Compiled for VY-RO-StressResults.xls...................................... 19 File No.: 0801038.306 Page 2 of 19 Revision: 1 F0306-01RO

VStructural Integrity Associates, Inc.

1.0 OBJECTIVE The objective of this calculation package is to perform an ASME Code,Section III fatigue usage evaluation and a plant-specific evaluation of reactor water environmental effects for the reactor pressure vessel (RPV) recirculation outlet (RO) nozzle at the Vermont Yankee Nuclear Power Station.

1.1 Changes Made in Revision 1 of this Calculation Description of changes made in Revision I of this calculation:

a.

Editorial changes were made to Table 1 to more precisely describe the transient load sets.

b.

All but one of the changes made to Table 2 were editorial to more precisely describe the portions of the transients. The one non-editorial change was to move a time split in Transient 9 to better catch a stress peak or stress valley.

c.

Table 3 and the corresponding VESLFAT input file were revised to reflect actual material properties for the safe end. Revision 0 of this calculation tabulated SA-1 82 F304 (18Cr -8Ni) properties, but actually used properties for an Alloy 600 material.

d.

Table 5 was changed to eliminate the application ofKt = 1.53 to the nozzle corner piping loads.

e.

Tables 6, 7, and 8 were revised to reflect the new fatigue usage and environmental assisted fatigue summaries as a result of the changes associated with Bullets b and c above.

f.

Table 8 was revised for editorial changes.

g.

The results of various sensitivity studies on fatigue usage were added to Section 5.0.

h.

Revision of CUF values in Sections 5.0 and 6.0 to reflect revised analyses.

i.

All remaining changes marked throughout this calculation are editorial changes made to the text of the calculation package.

2.0 METHODOLOGY The methodology to be used for this evaluation was established in a previous calculation package

[2]. Based on that methodology, thermal stresses, pressure stresses, and attached piping load stresses were developed in the Reference [1 ] calculation for use in this fatigue calculation. The thermal stresses are added to pressure stresses and attached piping load stresses'. Both the pressure and piping load stresses are scaled based on the magnitudes of the pressure and nozzle fluid temperature during each transient. All six components of the stress tensor from the stress results are used in the fatigue calculation.

Stress components due to piping loads are scaled assuming no stress occurs at an ambient temperature of 70'F and the full values are reached at a reactor design temperature of 575'F [2, Assumption 3.1.7]. In addition, design seismic and deadweight loads are also included and scaled in combination with the thermal loads for each transient. This combination, coupled with assigning the stress due to these loads the same sign as the thermal stress, is considered to be a very conservative treatment of the loads overall in that deadweight and design seismic loads are considered and scaled for every transient.

File No.: 0801038.306 Page 3 of 19 Revision: 1 F0306-01RO

Structural Integrity Associates, Inc.

The fatigue calculation is performed for both the limiting safe end and nozzle blend radius locations, as determined in the Reference [1] calculation, and uses the methodology of Subarticle NB-3200 of Section III of the ASME Code [3]. An environmental fatigue usage analysis is also performed in this calculation applying the methodology and associated environmental fatigue multipliers described in Reference [6].

3.0 DESIGN INPUTS 3.1 Stress Calculation Linearized stress components at Node 6395 (limiting safe end path at inside surface) and Node 3829 (limiting nozzle blend radius path at inside surface) are used for the fatigue usage calculation, as shown in Figure 6 of Reference [1]. For the nozzle blend radius location, the stresses used in the evaluation are for the base metal only; that is, the cladding material is unselected prior to stress extraction. The stress components from the thermal stress analyses are combined with stress components due to pressure and piping loads. The linearized thermal stress components for each transient are taken from the relevant output files in the Reference [1] calculation (a sample of which was provided in Table 3 of Reference [1]). The unit pressure stress component results are taken from Table 2 of Reference [1]. Piping load stress components are taken from Table 5 of the Reference [2] calculation.

3.2 Fatigue Usage Analysis, General Structural Integrity's VESLFAT program [4] is used to perform the fatigue usage calculation in accordance with the fatigue usage portion of ASME Code,Section III, Subarticle NB-3200 [3].

VESLFAT performs the analysis required by NB-3222.4(e) [3] for Service Levels A and B conditions defined by the user. The VESLFAT program computes the primary-plus-secondary and total stress ranges for all events and performs a correction for elastic-plastic analysis, if necessary.

The program computes the stress intensity range based on the stress component ranges for all event pairs [3, NB-3216.2]. The program evaluates the stress ranges for primary-plus-secondary and primary-plus-secondary-plus-peak stresses based on all six components of stress (3 normal and 3 shear stresses). If the primary-plus-secondary stress intensity range is greater than 3 Sm, the total stress range must be increased by the simplified elastic-plastic strain correction factor, Ke, as described in NB-3228.5 [3]. The design stress intensity, Sm, is specified as a function of temperature. The input maximum temperature for both states of a load set pair is used to establish the S,, value used in the fatigue calculations from the user-defined input values.

When more than one stress set is defined for either of the event pair loadings, the stress differences are determined for all of the potential stress pairs, and the pair producing the largest alternating total stress intensity (Salt), including any effects of Ke, is used. The principal stresses for the stress ranges are determined by solving for the roots of the following cubic equation2:

S3 _ (Tx

-+- y Y+ O-z)S2 + (C3x Cy -+ C7 z

a, + a,,y2

_ Sxz2 _ Syz2)s 2 Note that cy., ay, az, etc. are used synonymously with Sx, S,, S,, etc., in this calculation.

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- (Cy" Gy a, + 2 rxy Tz "*yz - CTz Ty2 _ *y,

2 _ Cx TyZ2 o

The stress intensities for the event pairs are reordered in decreasing order of Sait, including a correction for the ratio of modulus of elasticity (E) from the fatigue curve divided by E from the material evaluated at the maximum event temperature. This allows a fatigue table to be created to eliminate the number of cycles available for each of the transient events. This fatigue table is based on a worst-case progressive pairing of events in order of the most severe alternating stress to the least severe, allowing determination of a bounding fatigue usage per NB-3222.4(e) [3]. For each load set pair in the fatigue table, the allowable number of cycles is determined based on Salt.

3.3 Event Cycles, VESLFAT For the Vermont Yankee RO nozzle analysis, transients that consist of combined stress peaks or valleys are split so that each successive peak or valley is treated separately. Therefore, there are 61 load sets based on the combined stress changes for the safe end, and 46 load sets based on the combined stress changes for the nozzle blend radius location. The reason the number of load sets are not equal for each path is because the time history stress results of those paths differ. Tables 1 and 2 show the load sets applicable to plant operation, with cycle counts per Table I of Reference [2].

These are used as input to VESLFAT for the safe end and nozzle blend radius locations, respectively. The cycle counts of Reference [2, 7] consider 60 years of operation. The data from Table 1 is entered into the VESLFAT input files VY-RO-VFAT-1i.CYC (safe end) and the data from Table 2 is entered into the file VY-RO-VFAT-21. CYC (nozzle blend radius).

3.4 Material Properties, VESLFAT Material properties are entered in VESLFAT input files VY-RO-VFAT-]I.FDT (safe end) and VY-RO-VFAT-2I.FDT (nozzle blend radius). Table 3 lists the temperature-dependent material properties used in the analysis [5]. Table 4 lists the fatigue curve for the nozzle blend radius and safe end materials

[3, Appendix I, Table 1-9.1 and Figure 1-9.1 (UTS < 80.0 ksi) for the nozzle blend radius, and Tables 1-9.1 and 1-9.2.2 (Curve C) and Figures 1-9.2.1 and 1-9.2.2 for the safe end location]. Curve C is selected for the safe end location because it is the most conservative curve among the three extended curves for austenitic steel. VESLFAT automatically scales the stresses by the ratio of E on the fatigue curve to E in the analysis, for the purposes of determining allowable numbers of cycles, as required by the ASME Code.

Other material properties are input as follows:

m = 1.7, n = 0.3, parameters used to calculate Ke for the safe end location [3, Table NB-3228.5(b)-1]

m = 2.0, n = 0.2, parameters used to calculate Ke for the nozzle blend radius location [3, Table NB-3228.5(b)-1]

E from fatigue curve = 28,300 ksi [3, Appendix 1, Figure 1-9.2] for the safe end location.

E from fatigue curve = 30,000 ksi [3, Appendix I, Figure 1-9.1] for the nozzle blend radius location.

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3.5 Stress Indices The limiting stress path for the RO nozzle safe end is defined in Reference [1]. The stresses caused by the piping were hand calculated and do require a stress concentration factor, if appropriate. The stress concentration factor for the safe end location is 1.53 [2, Section 3.8]. This value is conservatively used for both the C2 and K2 values required by the ASME Code [3, NB-3600]. The piping loads are relatively minor in comparison to the other loads this nozzle experiences so the conservative C2 and K2 values will have a small impact on the analysis. Table 5 shows the piping loads after applying the C2 and K2 values as appropriate.

4.0 CALCULATIONS Table 5 contains the stress components at the locations of interest for the 1,000 psi unit pressure stress case [1, Table 2]. Table 5 also contains the stress components for the attached piping load unit stress case [2, Table 5], which correspond to a reactor design temperature of 575°F [2, Section 3.1.7].

The attached piping load stress components were applied assuming the same signs as the thermal stress, which yields the largest stress component ranges.

The calculations of all of the VESLFAT stress inputs are automated in Excel workbooks VY-RO-VFAT-li.xls (safe end) and VY-RO-VFAT-2i.xls (nozzle blend radius). These files are organized with sheets labeled as follows:

  • Overview: Contains general information.
  • Other Stresses: Contains pressure and attached piping load stresses. As shown in Table 5, the pressure stresses use the membrane-plus-bending and total stress from the finite element analysis [1].
  • Rearranger: There are 12 Rearranger sheets, one for each thermal transient as analyzed by ANSYS. In these sheets, thermal stresses are copied from Excel workbook VY-RO-StressResults.xls, and rearranged to conform to VESLFAT input format (including switching the shear stress components Sx, and Sy, as required by VESLFAT). VY-RO-StressResults.xls contains the results of the ANSYS stress linearization for each transient. The files contained within this workbook are shown in Table 9. Time-varying scale factors for the attached piping loads (based on path metal temperature) and pressure are determined, and used to scale the unit load case stresses, which are then added to the thermal stresses. Since the attached piping loads can act in any direction, the stresses due to the attached piping loads are assigned the same sign as the thermal stresses to maximize the component stresses.

Algebraic summation of all six stress components is performed for pressure, piping loads, and thermal stresses at each transient time step. The VESLFAT stress input also includes time-varying metal temperature, as obtained from the ANSYS output, which is used to determine temperature-dependent properties from the values in Table 3.

  • VESLFAT: Contains the VESLFAT stress input, as obtained from the Rearranger sheets.

Load set numbers are entered on this sheet, as defined in Table 1 and Table 2. These sheets are saved to VESLFAT input files VY-RO-VFAT-li.STR (safe end) and VY-RO-VFAT-2i.STR (nozzle blend radius).

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5.0 RESULTS OF ANALYSIS Table 6 and Table 7 provide the detailed calculated 60-year fatigue usage, as obtained from VESLFAT output files VY-RO-VFAT-11.FAT (safe end) and VY-RO-VFAT-2LFAT (nozzle blend radius). All VESLFAT input and output files are saved in the project computer files associated with this calculation.

From Table 6, the safe end cumulative usage factor (CUF) is 0.00308 for 60 years. From Table 7, the nozzle blend radius CUF is 0.0 175 for 60 years.

From Table 1 of Reference [6], it was determined that hydrogen water chemistry (HWC) is available for 47% of the total 60-year operating period, and normal water chemistry (NWC) is present for the remaining 53% of the total 60-year operating period. From Table 1 of Reference [6], the dissolved oxygen values for the recirculation line (which is applicable to the RO nozzle) are 48 ppb for HWC conditions and 122 ppb for NWC conditions.

For the stainless steel piping, the environmental fatigue factors for post-HWC and pre-HWC are 15.35 and 8.36 from Table 2 of Reference [6]. The overall environmental multiplier is found by (15.35 x 47% + 8.36 x 53%), which equals 11.645, conservatively rounded upto 11.7. Therefore, the overall environmental multiplier is 11.7, which results in an EAF adjusted CUF of 11.7 x 0.00308 0.0360 for 60 years, which is acceptable (i.e., less than the allowable value of 1.0).

Based on the detailed CUF calculation shown in Table 7, a detailed EAF adjusted CUF evaluation on a load-pair basis is provided for the nozzle blend radius location in Table 8. The EAF usage from Table 8 is 0.111 for 60 years, which is less than the allowable value of 1.0 and is therefore acceptable. The effective overall Fen is 0.111/0.0175 = 6.32.

As a part of fatigue analysis calculations, it was noted that using Fy = -20 kips in the piping loads caused a slightly higher total stress intensity. However, the change was determined to have an insignificant effect on fatigue usage results. In addition, the effect of modeling the distinct material properties of both Type F304 and Type F316 in the ANSYS analysis (as opposed to using 18Cr-8Ni properties) was determined to have an insignificant effect on fatigue usage results. Finally, the effect of applying a minimum temperature of 130'F for thermal boundary Region 2 (see Figure 1 of Reference [2]) was determined to have an insignificant effect on fatigue usage results. These investigations and associated results are contained in the project files.

6.0 CONCLUSION

S AND DISCUSSIONS Detailed fatigue calculations for the Vermont Yankee RO nozzle were performed based on the results of stress analyses previously performed [1]. The thermal stresses were combined with stresses due to pressure and attached piping loads, both of which were scaled based on the magnitudes of the pressure and metal temperature during each thermal transient. All six components of the stress tensor were used for the fatigue calculations. The fatigue calculations were performed at previously-determined limiting locations in the safe end and nozzle blend radius, and used the methodology of Subarticle NB-3200 of Section III of the ASME Code [3].

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The 60-year CUT for the safe end location was'determined to be 0.00308 and the CUF for the nozzle blend radius location was determined to be 0.0175. Both values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.

Detailed EAF assessments were also performed for the two RO nozzle locations. The 60-year EAF CUF for the safe end location was determined to be 0.0360. The 60-year EAF CUF for the nozzle blend radius location was determined to be 0.111 using temperature-dependent Fen multipliers for each load pair. Both values are less than the ASME Code allowable value of 1.0, and are therefore acceptable.

7.0 REFERENCES

1. Structural Integrity Associates Calculation No. 0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle."
2. Structural Integrity Associates Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle."
3. ASME Boiler and Pressure Vessel Code,Section III, 1998 Edition with 2000 Addenda.
4. VESLFAT, Version 1.42, 02/06/07, Structural Integrity Associates.
5. ASME Boiler and Pressure Vessel Code,Section II, Part D-Properties, 1998 Edition with 2000 Addenda.
6. SI Calculation No. VY-16Q-303, Revision 0, "Environmental Fatigue Evaluation of Reactor Recirculation Inlet Nozzle and Vessel Shell/Bottom Head."
7. Entergy Design Input Record (DIR) EC No. 1773, DIR. Revision 1, "Environmental Fatigue Analysis for Vermont Yankee Nuclear Power Station," 7/26/07, SI File No. VY-1 6Q-209.
8. Deleted (not used in this calculation).

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Table 1: Safe End Load Sets as Input to VESLFAT VESLFAT Load Set 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Start Transient ties Time, see lTrnl 0

2Tml 1616.4 1Tm2 0

2Trn2_

0.4 3Trn2 301 4Trn2_

601.4 1 Trn3 0

2Trn3 250 3Tm3_

2050 4Tm3_

2960 5Trn3_

5560 lTrn4_

0 2Trn4 2

3Trn4_

7 4Tm4_

46 5Tn4_

992 6Tin4 2294 7Trn4_

3050 8Trn4_

6899 9Trn4 7745 1OTm4_

8645 11Trn4_

11057 12Tin4 16166 13Tm4_

16818 14Trn4 17118 1 Tn5_

0 2Trn5 1.5 3Trn5 24 4Trn5 2310 5Trn5 2611 6Trn5 2911.4 1Trn6 0

2Trn6 0.6 3Trn6 20 4Trn6_

2312 5Tm6_

2613 Temp Change Pressure Change Up Up Down Down Down Down Up Up Down Up & Down Down None None Down Down & Up Up & Down Down & Up Up & Down Down & Up Up Up Up Up & Down None Down None None Up Down None Down None None Up Down None Down Up Up None None None None None None None None None Up Up & Down Down None Down Down & Up Up & Down Down Down Down Up Up None None Up Up & Down Down & Up None None None Up Up & Down Down & Up None None None Cycles 300 300 300 300 300 300 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 60 60 60 60 60 60 1

1 1

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Table 1 (continued): Safe End Load Sets as Input to VESLFAT VESLFAT Load Set 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 Start Transient ties Time, see lTmn7 0

2Trn7 37.5 3Trn7 600 4Trn7 4443 1Trn8 0

2Tm8_

3 3Trn8_

2295 4Trn8 3927 1Trn9 0

2Trn9 0.12 3Trn9 27.92 4Trn9 290.15 1TmlO_

0 2Trnm0 730.8 3TmlO_

6314 4Tm 10 6844 5TrnlO 9555 6TrnlO 14937 1Trnl 1 0

2Tml 1-0 3Trnl 1 0

1Trnl2 0

2Trnl2 0

3Trnl2 0

Temp Change Pressure Change Cycles Down Down Down Down None Up Down None Down Down & Up Up None Down Down Down Down Down Down None None None None None None Down Down Down Down Down Down & Up None None None None None None Down Down Down Down Down Down None Up Down None Up Down 228 228 228 228 300 300 300 300 300 300 120 120 120 1

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Table 2: Nozzle Blend Radius Load Sets as Input to VESLFAT VESLFAT Load Set 1

2 3

4 5

6 7

8 9

10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 Start Transient

Time, sec 1Tml 0

2Tml 808.2 1Trn2 0

2Trn2_

0.4 3Trn2_

401 1Trn3_

0 2Trn3 250 3Trn3 2325 4Trn3_

3510 5Trn3_

5060 1Trn4_

0 2Trn4_

2 3Trn4_

7 4Trn4_

46 5Trn4_

1091 6Trn4_

2348 7Trn4_

3269 8Tm4_

6983 9Trn4_

7745 1OTrn4_

13839 l1Trn4_

16918 12Tn4_

18986 1 Tn5_

0 2Tn5_

24 3Trn5_

2611 1Trn6_

0 2Tm6_

0.6 3Trn6_

20 4Trn6_

2663 lTrn7 0

2Trn7_

37.5 3Trn7_

2247 1 Trn8 0

Temp Change Pressure Change Cycles Up Up Down Down Down Up Up & Down Down & Up Up & Down Down None None Down Down & Up Up & Down Down & Up Up & Down Down & Up Up Up & Down Down None None Up & Down Down None None Up & Down Down Down Down Down None Up Up None None None None None None None None Up Up & Down Down None Down Down & Up Up & Down Down Down & Up Up None None Up & Down Down & Up None Up Up & Down Down & Up None Down Down Down Down 300 300 300 300 300 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 10 60 60 60 1

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Table 2 (continued): Nozzle Blend Radius Load Sets as Input to VESLFAT VESLFAT Load Set Transient Start

Time, sec Temp Change Pressure Change Cycles 34 35 36 37 38 39 40 41 42 43 44 45 46 2Trn8_

3Trn8_

1Trn9_

2Trn9_

3Trn9_

1 Trnl 0 I1Tml0I 2Tml0 1 Trnl 1 3Trnll 1Trnl2 2Trnl2_

3Trnl2_

3 2025 0

9 58 0

313.2 0

0 0

0 0

0 Up & Down Down Down Up None Down Down None None None None None None Down & Up None None None None Down Down None Up Down None Up Down 228 228 1

1 1

300 300 120 120 120 1

1 1

Table 3: Temperature-Dependent Material Properties for VESLFAT (3)

Material SA-508 Class 2 (nozzle blend radius(2))

T, 'F 70 200 300 400 500 600 70 200 300 400 500 600 E x 106, psi 27.8 27.1 26.7 26.1 25.7 25.2 28.3 27.6 27.0 26.5 25.8 25.3 S., ksi 26.7 26.7 26.7 26.7 26.7 26.7 20 20 20 19.3 18.0 17.0 Sy, ksi 50.0 47.0 45.5 44.2 43.2 42.1 30 25.9 23.4 21.4 20.0 18.9 SA-182 F316 (Safe End (1))

Notes:

1.

For the safe end material, SA-182 F316 (16Cr-12Ni-2Mo) austenitic stainless steel properties are used.

2.

For the nozzle blend radius material, SA508 Class 2 material properties are used (3/4Ni-1/2Mo-1/3Cr-V), per Reference [2].

3.

All values are taken from Reference [5].

4.

SA-508 Class 2 in the Code of Construction is the same as SA-508 Gr. 2 Class 2 in the 1998 ASME Code [5].

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Table 4: Carbon/Low Alloy Steel and Stainless Steel Fatigue Curves Sa, ksi Sa, ksi Number of Cycles Carbon/Low Alloy (1)

Austenitic 10 20 50 100 200 500 1000 2000 5000 10000 20000 50000 100000 200000 500000 1000000 2.E+06 5.E+06 1.E+07 2.E+07 5.E+07 1.E+08 1.E+09 1.E+10 1.E+1I 580 410 275 205 155 105 83 64 48 38 31 23 20 16.5 13.5 12.5 N/A N/A N/A N/A N/A N/A N/A N/A N/A 708 512 345 261 201 148 119 97 76 64 55.5 46.3 40.8 35.9 31 28.2 22.8(2) 18.4(2) 16.4(2) 15.2(2)

]4.3 (2) 14.1(2) 13.9(2) 13.7(2) 13.6(2)

Note:

1.

2.

Using UTS _ 80 ksi curve.

Using Curve C for austenitic steel.

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Table 5: Pressure and Attached Piping Unit Load Case Stress Components Node Membrane plus Bending (1)

Total (1) d(2)

SY S

S, yz S"

SY.

S z

Sx Sxz t 5 )

SyZ t 5 )

Pressure (3) 6395

-955.2 4420 10390 15.26 0

0

-955.2 4912 10530

-222.6 0

0 3829

-718.7

-951.7 25000 4708 0

0

-718.7 206.2 30150 733.2 0

0 ping(4) 6395 0

7930 0

831 2066 0

0 12133 0

1271 3160 0

3829 0

218 0

42 49 0

0 218 0

42 49 0

Nuotes:

I.

2.

3.

4.

5.

All stress values are in uILts o psI.

The safe end location is represented by Node 6395, and the nozzle blend radius location is represented by Node 3829.

The stresses for both nodes represent the stress due to an applied pressure of 1,000 psig.

Piping stresses for both locations represent the stress due to full attached piping loads at an RPV temperature of 575'F.

Syz and S_ components have been rearranged from the ANSYS output in order to be in correct order for VESLFAT.

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Table 6: Fatigue Usage Calculation for the Safe End Load Desc.

Load Desc.

Salt

  1. a
  1. 1
  1. 2
  1. 2 n (cycles)

Sn (psi)

Ke Si)

Nallow U

  1. 1
  1. 1
  1. 2
  1. 2 (psi) 47 2Trn9 48 3Trn9_

1 79715 2.62 169777 331.52 0.00302 15 4Trn4_

49 4Trn9_

1 30275 1

23722 1757500 0.00000 15 4Trn4_

28 3Trn5 9

29755 1

23610 1784800 0.00001 19 8Trn4 28 3Trn5 10 26926 1

21352 2647400 0.00000 17 6Trn4_

28 3Trn5_

10 25213 1

20492 3155800 0.00000 28 3Trn5_

39 2Trn7_

1 20321 1

16926 8269400 0.00000 18 7Trn4 28 3Trn5_

10 19961 1

16731 8866300 0.00000 28 3Trn5 44 3Trn8_

20 4606 1

16450 9819700 0.00000 34 3Trn6_

44 3Trn8 1

4606 1

16450 9819700 0.00000 43 2Trn8_

44 3Trn8_

207 4606 1

16450 9819700 0.00002 6

4Trn2_

43 2Trn8_

21 4028 1

16176 11335000 0.00000 6

4Trn2_

35 4Trn6_

1 3519 1

15752 14441000 0.00000 6

4Trn2 29 4Trn5 60 3484 1

15637 15446000 0.00000 6

4Trn2_

22 11Trn4_

10 11783 1

15613 15666000 0.00000 6

4Trn2_

23 12Trn4_

10 3202 1

15588 15895000 0.00000 2

2Trnl_

6 4Trn2_

198 3193 1

15583 15936000 0.00001 2

2Trnl 31 6Trn5 60 3319 1

15531 16430000 0.00000 2

2Trnl 37 6Trn6 1

3319 1

15531 16430000 0.00000 2

2Trnl1 25 14Trn4_

10 1702 1

15055 23098000 0.00000 2

2Trnl_

40 3Trn7_

1 18894 1

14987 24732000 0.00000 2

2Trnl_

16 5Trn4_

10 5069 1

14487 41157000 0.00000 33 2Trn6 52 3Trnl_0 1

12380 1

14460 42317000 0.00000 13 2Trn4 52 3Trnl0 10 10470 1

13875 1.336E+09 0.00000 50 1Trnl0_

52 3Trnl0_

289 9634 1

13841 1.968E+09 0.00000 50 1TrnlO 53 4Trnl0 11 18796 1

13770 4.465E+09 0.00000 3

1Trn2 53 4Trnl0 289 18795 1

13769 4.491E+09 0.00000 Total 0.00308 Usage =

Note:

All other load pairs have an alternating stress, Saft, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.

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Table 7: Fatigue Usage Calculation for the Nozzle Blend Radius Load Desc.

Load Desc.

n Salt

  1. 1
  1. 1
  1. 2
  1. 2 (cycles)

S (psi)

Ke (psi) 2 2

1 1

2 1

2 1

1 1

1 1

11 2

2 2

2 2

2 2

2 4

4 4

10 35 35 9

7 7

7 3

3 31 1Trnl1 14 4Trn4_

1Trnl_

37 2Trn9_

1Trn1_

16 6Trn4_

1Trnl_

27 2Trn6_

2Trnl_

45 2Trn12_

1Trnl_

15 5Trn4_

lTrnl_

18 8Trn4_

1Trnl_

36 1Trn9_

1Trn1_

13 3Trn4_

1Trnl_

38 3Trn9_

1Trn1_

12 2Trn4_

1Trnl_

23 1Trn5_

1Trn1_

17 7Trn4_

1Trnl_

5 3Trn2_

2Trnl_

5 3Trn2_

2Trnl_

28 3Trn6_

2Trn 1 11 1Trn4_

2Trnl1 26 1Trn6_

2Trnl_

25 3Trn5_

2Trnl1 29 4Trn6_

2Trnl1 8

3Trn3_

2Trnl_

4 2Trn2_

2Trn2_

41 1Trn 11 2Trn2_

32 3Trn7_

2Trn2_

40 2Trn 10_

5Trn3_

40 2Trn 10_

3Trn8_

40 2Trn 10_

3Trn8_

43 3Trnl 1_

4Trn3_

43 3Trn 11_

2Trn3_

46 3Trn12_

2Trn3_

44 1Trn12_

2Trn3_

43 3Trn 11 1Trn2_

43 3Trn 11_

1Trn2_

19 9Trn4_

2Trn7_

42 2Trnl I 10 1

10 1

1 10 10 1

10 1

10 60 10 166 134 1

10 1

68 1

10 82 120 1

97 10 193 35 10 1

1 8

67 10 1

21902 1.00 43085 21390 1.00 32177 15100 1.00 31137 42381 1.00 27020 45773 1.00 26852 18457 1.00 26707 13066 1.00 26562 28617 1.00 24546 34179 1.00 24042 25904 1.00 23939 36762 1.00 23612 35051 1.00 22617 22210 1.00 22533 29847 1.00 22312 29301 1.00 22309 33856 1.00 22227 33460 1.00 21959 32908 1.00 21661 29068 1.00 21226 29068 1.00 21226 29847 1.00 21214 30245 1.00 21092 32229 1.00 20851 30983 1.00 20125 30982 1.00 20124 31344 1.00 20033 29931 1.00 19888 29651 1.00 19696 30915 1.00 19357 30523 1.00 19349 30523 1.00 19349 30523 1.00 19349 31236 1.00 19331 23810 1.00 16958 27376 1.00 11515 Nallow U

6889 0.0015 17617 0.0001 19701 0.0005 30496 0.0000 31084 0.0000 31604 0.0003 32139 0.0003 40947 0.0000 43643 0.0002 44218 0.0000 46129 0.0002 54348 0.0011 55358 0.0002 58126 0.0029 58168 0.0023 59234 0.0000 62919 0.0002 67330 0.0000 74454 0.0008 74454 0.0000 74661 0.0001 76819 0.0011 81328 0.0015 96967 0.0000 96981 0.0010 99198 0.0001 102050 0.0019 105678 0.0003 112494 0.0001 112655 0.0000 112655 0.0000 112655 0.0001 113042 0.0006 181219 0.0001 infinite 0.0000 Total 0.0175 Usage =

Note:

All other load pairs have an alternating stress, Salt, that is below the endurance limit of the fatigue curve. Therefore, they do not contribute to fatigue usage.

File No.: 0801038.306 Revision: 1 Page 16 of 19 F0306-O1RO

Structural Integrity Associates, Inc.

Table 8: EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location VY RO flozzle Corner Environmental Fatique Calculation CUF Calculation from file NrY-RO-VFAT-2i.fat:

Index Load.#1: Description#1 1 (cycles)(5 Load#21Description#2':n2Icycles)(5)

(cycles) (5:

Sr,(pi)

K S.(psi) 1`.1 U

S I

Trn_

300 14 i

4Trn4_

4 10 10 21902 1.00 43085 6889 0.0015 2

1 Trn1_

290 3r 2Trn9 1

1 21390 1.00 32177 17617 0.0001 3

1 1Trnl I

289 16 i

6Trn4_

10 10 15100 1.00 31137 19701 0.0005 4

1 lTrnl 279 27 2Trn6 i

1 1

42381 1.00

.27020 30496 0.0000 5

2 27rnl 30G 451 2Trn 12 1

45773 1.00 26852 31054 0.0000 6

1 l

1Trnl_

-78 18 s 5Trn_4 i

10 10 18457 1.00 26707 31604 0,0003 7

1 1Trnt 268 18 i

8Trn4_

i 10 10 13066 1.00 26562 32139 0.0003 8

1n 125nl L8 36 1Trn9 1

1 28617 1.00 24546 40947 0.0000 9

'1 lTrn i

257 13 3Trn 4-10 10 34179 1.00 24042 43643 0.0002 10 1i 1Trnl_

247 38 3Trn 9_

1 1

25904 1.00 23939 44218 0.0000 11 1

Trl 246 12 1

2Trn4 10 10 36762 1.00 23,612 46129 0.0002 12 1

2 Trnl 23 I1Trn5_

i 60 60 35051 1.00 22617 4348 0.0011 13 1

ITrnl 176 17 7Trn_

10 10 22210 1.00 22533 55358 0.0002 14 1

ITrnl 16,6 3Trn2 300 166 29847 1.00 22312 58126 0.0029 15

2 2Trnl 299 5

3Trn2 134 134 29301 1.00 22309 E5168 0.0023 16 2

27rnl 165 28 3Trn6 1

1 33856 1.00 22227 59234 0.0000 17 2

.2Trnl 1

1S4 11 1Trn4 1

10 10 33460 1.00 21959 62919 0.0002 18 2

2Trnl 1

26 1 rn6 1

1 32908 1.00 21661 67330 0.0000 19 2

2Trnl 1 153 25 3TrnS 60 60 29068 1.00 21226 74454 0.0008 20 2

2T rn i

93 29 dTrn6_

1 1

29068 1.00 21226 74454 0.0000 21 2

27rnl R2 8

i 3Trn3 10 10 29847 1.00 21214 74661 0.0001 22 2

2Trnl 82 4

2Trn2 300 82 30245 1.00 21092 76819 0.001.1 23 4

2rn2_

m 218 41 1

1Trn11-1 120 120

  • 32229 1.00 20851 81328 0.0015 24 4

2Trn2 98 32 3Trn7 1

1 30983 1.00 20125 06967 0.0000 25

.4 2Trn2 Q7 40 1

2Trnl10-O 300 97 30082 1.00 20124 n-1 0.0010 26 10 5Trn3 10 do 2Trn10_

i 203 10 31344 1.00 20033 99198 0.0001 27 35 7 mTrn 228 40 2 Trn 10 193 193 29931 1.00 19589 102050 0.0019 28 35-3Trn_

35 43 3Trnh1 120 35 29651 1.00 19698 105678 0.0003 29 9

4Trn3 10 43 3 Trn11 1

85 10 30915 1.00 19357 112494 0.0001 30 7

2Trn3 10 4

3Trn12 i

1 1

30523 1.00 19349 112655 0.0000 31 7

2Trn3 9

44 1Trn12i 1

1 30523 1.00 19349 112655 0.0000 32 7

2Trn3 8

43 J3Trnl1 75 8

30523 1.00 19349 112655 0.0001 33 3

lTrn2 300 43 3Trn11 67 67 31236 1.00 19331 113042 0.0006 34 3

tTrn2 233 19 9Trn4 i

10 10 23810 1.00 16958 181219 0.0001 35 31 2Tmn_

1 42 2T1rn1_

1 120

1.

27376 1.00 11515 infinte 0.0000 Total, U =

0.0175 File No.: 0801038.306 Revision: 1 Page 17 of 19 F0306-O1RO

Structural Integrity Associates, Inc.

Table 8 (continued): EAF Fatigue Usage Calculation for the Nozzle Blend Radius Location EAF Calcuatina IIWC DO rIlVLC 00 ndW8~,"uskumTh I.'4.r~/FI 48 122 ppb

% HWC =

47%

53%

=% IIWc Transient Maximum Temperatures:

~'~iY..OA..~JFAT.Ji ~i I Index Load #1I Desc. #1 Load #2 Desc #2 Line#

T 1(4) st1(4 72(4) s2 (4) Sn (psi) T Fi) (1) 1 1

lTrnl_

14 4Trn4 176 "1

3 14 18 21902 339 2

1 ITrnl 37 2Trn9_

6065

/

3 37 62 21390 437 3

1 ITrnl _

16 6Trne_

1060 I

3 16 7

15100 329 4

1 1Trn 1 27 2Trn6_

3734 1

3 27 8

42301 526 5

2 2Trnl_

45 2Trn12 20'1558 2

1 45 1

45773 120 6

1 iTrno is 15 5Tro4 1927 1

3 15 49 13457 394 7

1Trnn 10 0Trn 4

223M I

3 18 10 1300*

335 8

I 1Trn 1 36 1Trn_

5657 1

3 3M 41 20617 405 9

1 1Trn I 13 3Trn 4 1651 1

3 13 15 34179 516 10 1

iTrnl _

30 3-rnS 6657 I

3 38 1

25904 490 11 I

ITrnl 12 2Trn 4

1599 1

3 12 3

36762 526 12 1

1Trnl_

23 1Trn5 311t5 1

3 23 27 35051 526 13 1

1Trnl_

17 7Trn4 2152 1

3 17 5&

22210 426 14 1

ITrnl_

5 3Trn2_

952 1

3 5

80 29847 530 15 2

2TrnI 1 ITrr2_

8718 2

1 5

79 29301 530 16 2

2Trn1l 20 5Trno_

9R727 2

1 28 1

33856 526 17 2

2Trn 1

11 ITrn4 _

42455 2

1 11 4

33460 526 18 2

2Trn 1_

26 ITrn6_

98465 2

1 26 3

32900 526 19 2

2Trn I_

25 3irn5 89557 2

1 25 22 29068 529 20 2

2Trn I 29 4Trn_ 105503 2

1 29 21 29060 529 21 2

2Trn 1 8

3Trn3_

35.741 2

1 8

5 29047 528 22 2

2 T rnl_

4 2Trn2_

7777 2

1 4

7 30245 5-43 23 4

2Trn2 41 1Trnl 233450 4

7 41 1

32229 543 24 4

2Trn2 32 3Trn7_

223647 4

7 32 126 30983 543 25 4

2Trn2_

40 2-r7ln 10-232587 4

7 40 209 30982 543 26

'10 5Trn 3 40 2Trnl 0 1138571 10 21 40 209 31344 527 27 35 3TrnO 40 2Trn10_

28?1140 35 51 40 209 2S931 528 20 35 3Trn.

43 3Trohl _

2910647 35 51 4 3 1

29651 520 29 9

4Trn_

43 3Trn 11-106932C C

28 43 1

30915 536 30 7

2Trn3 46 3Trn 12_

066274 7

42 46 1

30523 536 31 7

2Trn 3 44 1Trn12 860190 7

42 44 1

30523 536 32 7

27rn 3 43 3Trn11 860148 7

42 43 I

30523 536 33 3

1Trn2_

43 3TrolI 206618 3

1 43 1

31236 549 34 3

1Trn2 19 9T"rn _

203153 3

1 19 94 23810 549 35 31 2Trtn 42 2Trnl 1 26255.22

31 809 42 1

27376 339 Uanv (3) -

TMAX (TF) (1)

TMAX (-1 Fen (Z)

Uenv (3) 2.45 201 2-45 4.46 0.001 335 100 2.45 3.04 0.001 495 257 2.45 0.50 0.000 516 269 2.45 9.03 0.001 490 254 2.45 8.31 0U000 526 274 2.45 10.49 0.001 520 274 2.45 10.49 0.007 426 219 2.45 5.4.

0.001 530 277 2.45 10.76 0.020 530 277 2.45 10.76 0.016 526 274 2.45 10.49 0.000 526 274 2.40 10.49 0.001 52, 274 2.45 10.49 0.000 520 276 2.45 10.60 0.005 520 276 2.45 10.69 0.000 520 276 2.45 10.63 0.001 543 204 2.45 11.71 0.008 543 204 2.45 11.71 0.011 543 204 2.45 11,71 0.000 543 2M4 2.45 11.71 0.007 527 275 2.45 10.56 0.001 520 276 2.45 10.63 0.013 528 276 2.45 10.63 0.002 536-280 2.45 11.19 0.001 536 280 2.45 11.19 0.000 536 260 2.45 11.19 0.000 536 280 2.45 11.19 0.001 549 257 2.45 12.18 0.005 549 267 2.45 12.18 0.000 339 171 2.45 3.12 0.000 Total, U =

0.411 Overall Fen =

0,32 Notes:

1. T,,- is the maximum temperature of the two paired load states, and represents the metal (nodal) temperature at the location being analyzed. This.

which is included as '" in the'Translent Maximum Temperatures" table above. determined from the VESLFAT output.

2. F_ values computed using the low alloy steel equation from Section 3.0 of Reference [6], with S* conservatively set to a maximuinvalue of 0.015, and tha transformed strain rate conservatively set to a minirmumvalue of In (0.001) = -6.90, for ali load pairs.
3. U_, = [U x HIWC F_ x % HWC) + (U x NIWC F., x % NWVC1.
4. T1 and T2 represent the load number for Load #1 and Load #2, respectively, and s l and s2 represent the state number for each of those loads.
5. For each load pair, n-is the number of available cycles for Load #1, n. is the number of available cycles for Load 62. and n Ls the available number of cycles for the load pair (i.e.. the minimum of n, and nz).

File No.: 0801038.306 Revision: I Page 18 of 19 F0306-01 RO

Structural Integrity Associates, Inc.

Table 9: Linearized Stress Files Compiled for VY-RO-StressResults.xls Filename Description VY RONTRAN1-S.csv VYRONTRAN2-S.csv VY RON TRAN3-S.csv VY RON TRAN4-S.csv VY RON TRAN5-S.csv VY RON TRAN6-S.csv VY RONTRAN7-S.csv VY RON TRAN8-S.csv VY RON TRAN9-S.csv VYRON_ TRAN1O-S.csv VY RON TRAN11-S.csv VY RONTRAN12-S.csv Transient 1 linearized stress Transient 2 linearized stress Transient 3 linearized stress Transient 4 linearized stress Transient 5 linearized stress Transient 6 linearized stress Transient 7 linearized stress Transient 8 linearized stress Transient 9 linearized stress Transient 10 linearized stress Transient 11 linearized stress Transient 12 linearized stress Note: All files are from the Reference [1] supporting computer files.

File No.: 0801038.306 Revision: 1 Page 19 of 19 F0306-OIRO

Hearing Docket From:

Travieso-Diaz, Matias F. [matias.travieso-diaz@pillsburylaw.com]

Sent:

Tuesday, March 10, 2009 3:02 PM To:

Alex Karlin; Richard Wardwell; whrcville@embarqmail.com; secy@nrc.gov; Hearing Docket; Susan Uttal; Lloyd Subin; Maxwell Smith; Sarah.hofmann@state.vt.us; aroisman@nationallegalscholars.com; peter.roth@doj.nh.gov; Matthew.Brock@state.ma.us; Zachary Kahn; Mr. Raymond Shadis; OCAAMAIL Resource Cc:

Lewis, David R.; Nelson, Blake J.

Subject:

Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc. (Vermont Yankee Nuclear Power Station), Docket No. 50-271-LR, ASLBP No. No. 06-849-03-LR (Part 1 of 3)

Attachments:

Letter to ASLB enclosing revised calculations.pdf In accordance with the provisions of the Board's Partial Initial Decision (Ruling on Contentions 2A, 2B, 3, and 4), LBP-08-25, 68 N.R.C.

(Nov. 24, 2008), slip op. at 67,.and the Board's Order (Clarifying Deadline for Filing New or Amended Contentions) (Mar. 9, 2009), Entergy has revised and issued its final calculations of record for the confirmatory environmentally assisted fatigue (CUFen) analyses on the reactor pressure vessel core spray (CS) and recirculation outlet (RO) nozzles at the Vermont Yankee Nuclear Power Station. These revised analyses are presented in the following Structural Integrity Associates, Inc. (SIA) calculations: Calculation No.

0801038.302, Revision 1, "Stress Analysis of Reactor Core Spray Nozzle;" Calculation No. 0801038.303, Revision 1, "Fatigue Analysis of Reactor Core Spray Nozzle;"

Calculation No. 0801038.304, Revision 1, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Recirculation Outlet Nozzle;" Calculation No.

0801038.305, Revision 1, "Stress Analysis of Reactor Recirculation Outlet Nozzle;" and Calculation No. 0801038.306, Revision 1, "Fatigue Analysis of Reactor Recirculation Outlet Nozzle." Calculation 0801038.301, Revision 0, "Design Inputs and Methodology for ASME Code Fatigue Usage Analysis of Reactor Core Spray Nozzle" has not been revised so that the version sent to the parties on January 8, 2009 remains the final calculation of record. Entergy is serving at this time electronic copies of those analyses on the parties to the above captioned proceeding.

The methodology applied in the referenced CS and RO confirmatory analyses is in accordance with the approach-used in the SIA calculations for the feedwater nozzle that were introduced into evidence in this proceeding, and contains no significantly different scientific or technical judgments from those used in the feedwater nozzle calculations. See Calculation 0801038.301 at 4, n.1 and Calculation 0801038.304 at 4, n.1.

As set forth in the referenced revised calculations, the limiting calculated CUFenS for the CS and RO nozzles are less than unity and are therefore acceptable.

Hard copies are also being sent today by overnight mail to the NRC Staff, the New England Coalition and the Vermont Department of Public Service.

1

This submittal comprises three electronic messages. This first message, attaching Entergy's cover letter, is being transmitted to the entire service list. The second message, comprising the calculation package for the CS nozzle, is being transmitted only to the parties (including interested States). The third message, comprising the calculation package for the RO nozzle, is being forwarded only to the parties (including interested States).

If you have any difficulty opening this attachment, please contact me at the number below.

Matias F. Travieso-Diaz I Pillsbury Winthrop Shaw Pittman LLP Tel: 202.663.8142 I Fax: 202.663.8007 I Cell: 703.472.6463 2300 "N" Street, NW I Washington, DC 20037-1122 Email: matias.travieso-diaz(cpillsburylaw.com-Bio: www.pillsburylaw.com/matias.travieso-diaz

  • Internal Revenue Service regulations generally provide that, for the purpose of avoiding federal tax penalties, a taxpayer may rely only on formal written advice meeting specific requirements. Any tax advice in this message does not meet those requirements. Accordingly, any such tax advice was not intended or written to be used, and it cannot be used, for the purpose of avoiding federal tax penalties that may be imposed on you or for the purpose of promoting, marketing or recommending to another party any tax-related matters.

2

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Entergy Nuclear Vermont Yankee, LLC, and Entergy Nuclear Operations, Inc. (Vermont Yankee Nuclear Power Station), Docket No.

50-271-LR, ASLBP No. No. 06-849-03-LR (Part 1 of 3)

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