Text

Sentinel 5S Radiation,Structural & Thermal Evaluation (Application for Type B(U) Package Approval)
	ML20138P051
Person / Time
Site:	07109205
Issue date:	09/30/1985
From:	; TELEDYNE ENERGY SYSTEMS
To:	;
Shared Package
ML20138P049	List: ML20138P046; ML20138P051;
References
	TES-3205, NUDOCS 8511060344
	Download: ML20138P051 (175)
	v • d • e

{{#Wiki_filter:}/-f)$$ /2a a LJ//4 Q WN /d/}6lX SENTINEL SS RADIATION, STRUCTURAL AND TilERMAL EVALUATION (Application for Type B(U) Package Approval) TES-3205 September 1935 O WTELEDYNE ENERGY SYSTEMS 110 W. Timonium Road Timonium, Maryland 21093 O m>wn sma.. 3 PDR

TABLE OF CONTENTS O Section Description Page 1 GENERAL INFORMATION 1-1 1.1 Introduction 1-1 1.2 Package Description 1.1 2 STRUCTURAL EVALUATION 2-1 2.1 Structural Design 2-1 2.2 Weights and Center of Gravity 2-2 2.3 Mechanical Properties of Materials 2-2 2.4 General Standards for All Packages 2-2 2.5 Standards for Type B and Large Quantity Packaging 2-14 2.6 Normal Conditions of Transport 2-10 2.7 Hypothetical Accident Conditions 2-18 2.8 Special Form 2-35 2.9 Fuel Rods 2-47 2.10 Appendix 2-47 3 THERMAL EVALUATION 3-1 3.1 Discussion 3-1 O 3.2 Summary of Thermal Properties of Materials 3-2 3.3 Technical Specifications of Components 3-8 3.4 Thermal Evaluation for Normal Conditions of Transport 3-0 3.5 Hypothetical Accident Thermal Evaluation 3-21 3.6 Appendix 3-31 4 COhTAlhWEhT 4-1 4.1 Containment Boundary 4-1 4.2 Requirements for Normal Conditions of Transport 4-2 4.3 Containment Requirements for the Hypothetical Accident Conditions 4-2 4.4 Appendix 4-3 5 SHIELDING EVALUATION 5-1 5.1 Discussion and Results 5-1 5.2 Source Specification 5-1 5.3 Model Specification 5-3 5.4 Shielding Evaluation 5-6 5.5 Appendix - References 5-9 6 CRITICALITY EVALUATION 6 ' O t TES-3205 11 l i 1

TABLE OF CONTENTS (Cont'd.) Section Description Page 7 OPERATING PROCEDURES 7-1 7.1 Procedures for Ioading the Package 7-1 7.2 Procedures for Unloading the Package 7-2

7. 3 Preparation of an Empty Package for Transport 7-3 7.4 Appendix 7-4 8

ACCEPTANCE TESTS AND MAINTENANCE PROGRAM 8-1 8.1 Acceptance Tests 8-1 8.2 Maintenance Program 8-3 Appendix A QUALITY ASSURANCE A-1 O I i 4 i i 4 i !O TES-3205 l f fil t

1. GENERAL INFORMATION O This document is the application for approval of the package for transportation l of the Sentinel SS Radioisotope Thermoelectric Generator (RTG) as a type B (U) pack-age containing special form radioactive material. The package has been designed to meet the current requirements of the U.S. Nuclear Regulatory Commission as pro-videdin Title 10, Code of Federal Regulations, Part 71, and of the International Atomic i Energy Agency as provided in EAEA Safety Se-les No. 6, Regulations for the Safe Transport of Radioactive Materials,1973 revised edition (as amended), published in j 1979. This report has been prepared in accordance with the instructions and format of to U.S. NRC Regulatory Guide 7.9, Revision 1, January 1980, modified as re-quired to conform with the current regulations. Quality Assurance Program informa-tion (as required by Para. 71.37)is provided in Appendix A of this report. 4 The new package utilizes an existing shipping cask for the transport of a newly designed model of radioisotope thermoelectric generator (RTG) to be designated as l SenMnel 5S. The shipping cask proposed for use with the new RTG is part of the pack-l j age identified as Sentinel 8S approved by Certificate of Compliance No. 9085 and IAEA Certificate of CO.npetent Authority No. USA /9085/B. In addition, the cask is also part of the packtie identified as Sentinel IS approved by Certificate of Compliance No. 9153 and IAEA Certificate of Competent Authority No. USA /9153/B. 1.1 Introduction The Sentinel SS RTG is a thermoelectric generator designed for terrestrial operation to produce an electrical output of 5 watts, minimum, at the end of a 5 year service life, ne units internal shielding has been reduced to provide a lightweight L generator for unique installation requirements. In the transportation mode, the gen-4 erator requires a massive steel shipping cask to meet radiation levels established by NRC and IAEA regulations. The RTG mounted in its steel shipping cask constitutes l the Sedinel SS package. The packages are designed to be transported in the non-exclusive mode and will have a transport index of 10 or less, 1.2 Package Description

1. 2.1 Packaging i

In the shipping configuration, the Sentinel SS Radioisotope Thermoelectric Generator (RTG) is preloaded into a massive, low carbon steel, shipping cask. The - generator is positioned within the cask by 3 centering fins. The prescribed preload - .is obtained by compressing a silicone rubber pad between the RTG and the cask lid, A welded, structural member is used between the RTG head and the rubber pad to transmit the load to a machined surface on the RTG head. The packaging for shipment is shown on Figure 1.1. lO TES-3205 I 1-1 I l

The RTG houses the fuel, which is doubly encapsulated in a fuel capsule assem-bly, and which in turn is contained within a shield assembly. ne shield assembly is preloaded within the generator and is largely surrounded by thermal insulation. The shield assembly provides the required radiation attenuation following the sequential series of hypothetical accident conditions detailed in 10 CFR 71. 73 %e shipping cask and the generator and its components are discussed further in the following paragraphs. Component weight breakdown is shown in Table 1.1.

1. 2.1.1 Ship)ing Cask.

De shipping cask is in the form of a cylindrical body with a plug type Ltd. De cask body is welded to rectangular steel stmetural tubing to form a pallet to facilitate handling by fork tmek. The cask is also equipped with 3 ring bolts, each with a rated capacity of 25,000 pounds, for use with a special sling for handling by overhead crane. The cask body is machined from a solid steel forged billet meeting ASTM-A-181 Grade 2 specifications. ne cask lid is machined from ASTM-A-36 hot rolled steel plate and the pallet members are fabricated from ASTM-A-500 cold formed rectangular tubing and A-181 M 1020 hot rolled steel plates welded together. The cask lid is bolted to the body to form the codainer for the generator. Cask details am shown on Figure 1.2. %e shipping cask provides additional radiation shielding to meet the regulations, during normal transport conditions. He cask will form the external container of the type B (U) package and will be O appropriately marked with Category III yellow labels. De maximum calculated trans-port index is 3. The cask lid is bolted to the body by 12 -3/4 inch square head bolts recessed in a cavity designed such that special tools are required for installation or removal to negate inadvertent opening of the package. One of the bolts employs a lead seal. %e cask body is designed such that electrical cables from the RTG am routed to a connector in the cask wall. His feature enables checkout of the RTG without opening the cask and with very minimal radiation exposure to personnel.

1. 2.1. 2 Radioisotope Thermoelectric Generator (RTG).

The thermoelectric generator is made up of the following components: the fuel or radionuclide; the fuel capsule assembly, which provides double encapsulation of the fuel and which is defined as the containment vessel; the idernal shield assembly, which serves to retain the fuel capsule in its correct position and to provide sufficient shielding to pmtect workers engaged in the installation of the RTG; thermal insulation, a thermoelectric module; shield preload components; and a finned generator housing and lid assembly which contain all of the previously medioned components. The housing and lid are welded assemblies fabricated from 6061-T6 aluminum alloy. he Sentinel SS RTG assembly Ja shown in Figure 1.3. De table of this figure provides nomenclature and identifies the materials of construction. s O j TES-3205 l 1-2 L

TABLE 1.I SENTINEL SS PACKAGE - WEIGHT AND BALANCE STATEMENT Weight, Ibs X, in.

5, in. *
RTG Assembly Shield (body + plug) 167.39 8.15 Fuel Capsule Assembly 10.78 6,16 (less fuel)

Fuel 1.65 6.16 i Connectors .80

15. O T/E Module Assembly 1.23 13.2 Bellows

.37 13.04 Insulation 16,27 7.37 Bellows Plate 1.82 12.15 Removable Fins 21.98

9. 76 I

Housing Cylindrical Shell 18.08 8.86 l Upper Closure 11,21

14. 73 Lower Closure 11.23

.59 Fin Stubs 5.50 12.46 Getter Ring 1.61 9.14 Preload Support Ring -Macor .37 13.52 Springs .69 1.34 Spring Support 3.19 1.52 Seal Ring 2.05 13.94 RTG Assembly (Total) 276.2 8.27 18.77 Shipping Cask Body and Pallet 6016.3 16.04 RTG Support Structure 11.6 30.27 . Shipping Cask Lid 1154,2 34.34 Total Package 7458,3 19.0 /

X: Center of gravity measured from base of RTG,
- 5 : Center of gravity measured from truck bed.

TES-3205 1-3 . -~...

In operation, heat given up by the decay of the radioactive fuel, is transmitted to the shield assembly and then directed by thermal insulation upwards through the ( thermoelectric module where a portion of the heat is converted directly to electrical J energy. A series of special alloy steel Belleville washers positioned between hardened bearing plates are employed to provide a pre-load on the shield assembly. Pre-loading ^ of componeds is equired to withstand the shock and vibration environments imposed on the R'IG by the user. 1.2.1.2.1 Fuel. The fuel used in the Sentinel SS RTG is Strontium-00 fluor-ide processed and encapsulated at the Waste Encapsulation and Storage Facility (WESF) l in Hanford, Washington. Biel from the WESF capsule is removed, hot pressed into pellets, and encapsulated at the Oak Ridge National Laboratory under contract to Teledyne Energy Systems in new encapsulation hardware. The thermal inventory specified in each Sentinel SS capsule is nominally 185 watts or about 27,600 curies. Where relevant, the evaluation of the package presented herein is based on a maximum fuel loading of 210 watts or 31,400 C1. The solid, pelletized, Strontium-90 fluoride is encapsulated to meet "special } form" criteria. 'Ihe fuel is not a fissile material. The fluoride form of Strontium-90 has been successfully used in the Sentinel 8S and Sentinel IS RTG models produced by } Teledyne Energy Systems, i i 1.2.1.2.2 Heat Source Assembly (Biel Capsule Assembly). The completed j heat source assembly consists of a sealed, thick-walled outer capsule or strength member containing a sealed inner capsule or liner assembly with the liner assembly containing two hot pressed Sr-90 fuel pellets. The heat source assembly is shown in i Figure 1.4 and is designed to provide double encapsulation of the Sr-90 fuel. The heat i source is designed to meet the requirements of ' Guide to the Safe Design, Construction i and Use of Radioisotopic Power Generators for Certain Iand and Sea Applications," International Atomic Energy Agency Safety Series 33,1970 Edition (see Section 2,8). l The liner assembly consists of a tubular housing with two welded end caps. One of the end caps is welded and tested for leak tight integrity and weld quality prior to any hot cell operations. After the fuel pellets are inserted into the liner, the final j weld closure is done in a hot cell by a remote, automatic TIG process using weld parameters established in a development program. The liner provides none of the structural integrity of the heat source but serves only to protect the strength member from chemical attack by impurities in the fuel and to provide a convenient means to decontaminate the fueled package prior to its subsequent encapsulation in an outer cap-sule or strength member. The strength member or outer capsule consists of a tubular housing with an integral solid end and one threaded end into which an end cap is screwed and subse-quently welded. Final weld closure of the end cap, following the insertion of the clean (decontaminated) liner assembly Mo the strength member, is an automatic plasma- - I arc type weld performed using weld parameters established in a development program. .The strength member or outer capsule is designed to provide the necessary structural integrity of the heat source assembly. I!O TES-3205 1._- a -~.. i

1.2.1.2.3 Shield Assembly. The shield assembly consists of a shield plug attached to a shield body with 3 steel bolts to form the container for the fuel capsule (q assembly. The plug is designed with a " stepped" lower end which fits into a mating y cavity in the body. This arrangement serves as a guide for the plug as it is lowered into position in a hot cell following the fueling operation. The shield assembly and constmetion details are shown in Figures 1. 5,1. 6 and 1. 7. An alloy of depleted uranium with. 75% titanium was selected as the shield material for the Sentinel SS RTG because RTG weight was a primary consideration. This alloy has a minimum bulk density of 18.45 g/cc. Each component is fabricated by rough casting and machining and each component is clad in a thin stainless steel can to preclude oxidation. The shielding thicknesses are sized so that the RTG, in its shipping codainer, will not produce radiation levels which exceed the limits specified in 49 CFR 173 and 10 CFR 71. Additionalinformation on shield components and the complete radiation analysis is given in Section 5, ' Shielding Evaluation. " 1.2.2 Operational Features Them are no special operational features of the package which could affect the safety of the unit. That is, there am no cooling systems, pressure relief valves or moderating materials employed in the package design. Once the RTG is fueled and installed in its shipping container, no special pm-paration is mquired for transport.

1. 2. 3 Contents of Packaging The contents of the Sentinel SS package could be as much as 31,400 curies (capacity of liner) of Strontium-90 as fluoride in the hot pressed pellet form. The thermal inventory of the radionuclide is nominally 185 watts. The fuel does not re-lease helium during its decay process, thus, there is no internal pressure buildup.

For purposes of evaluation for this license application, the maximum liner loading of 210 thermal watts or 31,400 Ci is assumed. O TES-3205 1-5 t i y c

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/% f i U V V e f I [ e i [ l l e e a ~" W==e; ~ e em 9 3 4 10 2b 1. Heat Smrom Assembly a. Liner - Hastelloy C-276 b. Strength Memher - HasteUoy C-276 +j g e c. Mael - Sr F2 N -.p 2. thield Assembly g( a. thield plug ) Depleted uranium .75 titanium b. Shield body j ' Canned'in Type 321 stainless steel I O c. Shield plug attaching Ixalts - alloy steel 6e g p 3. IJd Assembly - W 6061-14 Alumimm AUoy 5 00UdhIddOOO W 4. Nrmoelectric Module f4 l ab ..3 /~~ ~' g g g g, steel bellows using Viton 'O' rtass. >3 Ns \\ 5. Housing Aasemtly - Type 6061-76 Aluminum Alloy 5m 4 f Q \\ \\ + 6. Nrmal Insulation gg \\ a. Min-K 1E 1800 tc - \\\\. yMy,.J@X \\ f b. Standard Microtherm block c. Min-K TE 1400 3" 7. Preload Componente le 1 a. lead bearing plate - Type SAE 01 tool steel )\\ l '," ' -- - r] b. Belleville washers $21sc springs) - alloy steel - AMS 6455 x ,p, 77 gpl c. Oulde plate - Type SAE 01 tool steel s-# 8. hl Access Cover - Type 6061-T6 Aluminum ADoy \\ 9. Pre-Imd Support Ring 'Macor' Machineable Glass Ceramic rw 1 _ ' _ _. b l - CQ 80. R*C'588CI8 Mr Output) .f _ qg... - _ - - f. _. g Tinned-mild steel shen - bermetically sealed connector s - e -- ' soldered to stainless steel adapter-scaled to housing with [ 2n Viton 'O' rings. 6 11. Cetter Ring - porous sintered sincontum-vanadium-tron aDoy 7, ,g g 3:1 J_. l 22in.M- -

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2 STRUCTURAL EVALUATION This chapter provides the identification, description and analytical data m-quired to evaluate the structural integrity of the packaging components important to safety and to compliance with the performance requimments of 10 CFR Part 71 and IAEA Safety Series No. 6. 2.1 Structural Design 2.1.1 Discussion There are four principal structural members affecting the safety of the Sentinel SS package. Dese components include the fuel capsule assembly, the shield assembly, RTG housing and the shipping cask. Details of constmettonof these components is given in Chapter 1. The shipping cask is the primary structure for lifting and handling for transpod. It provides additional radiation shielding and protects the package under the normal conditions of transport. For evaluation of the package under the hypothetical accident conditions, no credit is taken for the structuralintegrity of the cask given the 30 foot drop. The R1T) housing is sufficiently strong to survive this drop to the extent that is provides p protection for the subsequent puncture environment. The shield assembly / fuel capsule Essembly are shown hemin to survive the total accident sequence. This subassembly provides for fuel containment and radiation pro-tection consistent with the requirements. - The fuel capsule assembly consists of an outer strength member containing a liner which contains the fuel. The strength member i s the primary fuel contalmnent member. The strength member is designed to msist hydrostatic pressure. 2.1.2 Design Criteria l The design criteria used in this chapter to demonstrate compliance to the vari-ous requirements of 10 CFR Part 71 and IAEA Safety Series No. 6 are in general as itemized below. For ductile materials the established criteria is as follows: a. Tension and Compression - For these applications the distration energy theory of Von Mises is used where the equivalent uniaxial stmas is limited to 2/3 of ultimate strength or 90% of the yield strength, whichever is less. Membrane stmases in shells have the same limits whereas primary plus ! n secondary stresses including discontinuity effects am limited to 90% of the QJ yield strength. TES-3205 j 2-1 1 t

b. Shear - Shear stresses shall not exceed 2/3 of the material's ultimate shear strength at the temperature of interest. c. Elastic Stability - Members are evaluated at 1.5 times the anticipated load and am demonstrated not to buclkle. For brittle materials the maximum pricicpal stresses are limited to 2/3 of the ma-terial's ultimate strength.

2. 2 Weights and Center of Gravity The weight and balance statement for the components associated with the RTG and shipping cask is given in Table 1.1.

The total weight of the package is 7458 lbs, whereas the RTG is only 276.2 lbs of the total weight. The center of gravity of the package is 19. O inches measured from the truck bed and is as indicated on Figure 2.1.

2. 3 Mechanical Properties of Materials The cask body is fabricated of ASTM-A-181 Grade 2 carbon steel, whereas the lid is made from A-36 steel. The RTG hmising is fabricated fmm 6061-T6 aluminum alloy and the shield is uranium - 3/4% titanium. Structural pmperties for these ma-terials is provided below. Structural properties of other materials are presented where applicable in the appropriate sections.

A-181 A -36 6061-TG U - 3/4 Ti Ult. Tensile Strength, psi 79,000 70,000 42,000 110,000 Yield Strength, psi 45,000 36,000 35,000 45,000 0 6 0 0 Modulus, psi 30 x 10 30 x 10 10 x 10 26 x 10 Elongation, 90 31 18 8-10 5-15 3 Density, lbs/in .286 .286 .098 .672 2.4 General Standards for All Packages The general standards for all packaging, as specified in 71. 43 and 71.45 are complied with, as demonstrated in the following paragraphs.

2. 4.1 Chemical and Galvanic Readions l

The shipping cask consists of a body fabricated from a forged steel alloy billet q and a lid, made from hat rolled steel plate. The integral pallel assembly and lid hardware are also fabricated from steel alloys. There are no dissimilar metals I utilized in the cask assembly. In addition, the entire unit is painted inside and out with f% a coat of zinc chromate wash primer and all exterior surfaces painted with 4 coats of I l V epoxy paint. The RTG electrical cables terminate in hermetically sealed connectors. l TES-3205 2-2 i

Lift Lifting Ring & Eye Bolt t Y 18.2 inches 17 inches /.h., j s' ./ ,/

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o' ./ * - h'k;;/ - e. 4, / - o O / g i / / / / 7 / f;... -/f-shi,,in,ca.h Integral Pallet ' FIGURE 2,1 ORIENTATION OF SENTINEL SS RTG SHIPPING CASK HANGING FREELY FROM A SINGLE LIFTING RING TES-3205 2-3

4 l 1 i + G i i i I r 4 t I i 1 t 1, i i i 1 l This page intentionally blank. lO i 1 l 4 i l t i i, l I O TES-3205 2-4

Each connector is mounted to a stainless steel plate. The plate is bolted to the exterior of the cask and sealed with a silicone rubber gasket. \\ The RIG inside the cask is an epoxy painted aluminum alloy. The areas of the RTG in contad with the cask are the housing lower cover and the tips of the three RTG centering fins. The housing lower cover is machined with a lip or ring extending below the fuel access cover such that the actual bottom of the RTG would sit about 1/8 inch off of the cask. The fins are bolted on to welded studs and are used only during transporta'- tion. Wen the cask to be completely filled with an electrolyte, such as salt water, the galvanic series grouping and the similar anodic and cathodic areas indicate that there would be no strong tendency to produce galvanic corrosion on each other. Excepting the internal gaps of the fuel capsule assembly, spaces within the RTG housing contain inert gases. Gaps between the depleted uranium shielding and its protective stainless steel clad are filled with helium. All other spaces exterior to the fuel capsule assembly are filled with argon. Prior to outgassing of the RTG and backfill with argon, the insulation is baked out to remove absorbed water vapor. The materials which comprise the RTG were selected to preclude chemical reaction at the nominal RTG shipping and operational temperatures in this inert gas environ-ment. No galvanic reactions can occur because of the absence of an electrolyte. 2.4.2 Positive Closure, Seal The cask lid is bolted to the cask body with twelve 3/4 - 10 UNC square head steel bolts which go through the lid into tapped holes in the cask body. The square head O bolts are recessed 3/4 inch below the top surface in a hole whose diameter preclude use of a standard socket wrench. Not onlymust standarti tooling be machined to fit over the square head bolts, but one of the bolt heads is wired through a hole in the lid and sealed with a metal seal. These measures assum that the package cannot be intentionally opened and a broken seal would provide evidence of tampering by unauthorized persons. 2.4.3 Lifting Devices l The shipping cask is designed to be handled either by forklift truck or by a three ( legged sling system. The three lifting rings located on the cask lid are required to be ( capable of supporting three times the weight of the loaded cask without generating stress j in any material of the system in excess of its yield strength. To be conservative, this l requirement is applied to only one ring. The load in that one ring is: (3) (7458 lb )== l 22,374 lb, l The lifting ring and eye bolt, supplied by Davis Aircraft Products Co., Inc., are rated for a load of 25,000 lb. (Purchased according to Martin Standard 26A12 - refer to l Figure 2-10-1. ) The capability of the ring is invarient with the orientation of the package during lifting, however, the stresses in the stud of the eyebolt are a fLmetion of orientation. The following analysis will further illustrate that the stud capability exceeds the 3g requirement for handling the RTG in the shipping cask. i O ~ TES-3205 2-5

A single ring supporting a free hanging shipping cask is shown in Figure 2,1. Under the 3 g loading, the force directed along the path between the center of gravity m and the lifting ring is 22,374 lbs. This can be divided into a shear and a tensile force for the lifting eye bolt. P (22,374) cos O = 15,259 lbs = s P,g, (22,374) sin O 16,355 lbs = = These loads create a tensile stress and shear stress in the eye bolt (minimum area for stress shown in Figure 2.2). I '3 = P,3,/ area = 21,807 psi Tensile Stress e = 75 P / area Shear Stress 7 = = 20,345 psi = 3 5 From Mohr's Circle the maximum principal stress is, 2 e/2 + (e/2)2,7 e* = 32,830 psi e* = It is unlikely that the system would assume an orientation other than that shown in Figure 2.4-1, but for completeness the pure shear and pure tensile cases will be examinei These cases are presented in Figure 2.3. Under the 3 g loading the stress under pure shear is, load 22,374 T 29,832 = = = area . 70 and the stress under pure tension is, 1 ad 5 = _ 22,374 29,832 psi = area .75 The lifting bolt is 4130 steel heat treated to an ultimate stress of 160,000 to 180,000 psi and a yield stress of 135,000 psi per MIL-H-6875 'Iherefore, the bolt will easily carry the 3 g load without yielding. Bending stress was neglected because the eye of the eye bolt is flush with the lid of the shipping cask and too stubby to accommodate bending. 2.4.4 Tie-Down Devices Shipping pallet tie-downs have I aen supplied in the four corners of the pallet structure. Each tie-down consists of a 2.5 inch diameter hole through the top side of .the rectangular tube forming the pal'.et. There will always be at least two of the tie-downs holding the shipping cask at any one time. This system is capable of withstand-c ing a static force applied to the conter of gravity of the complete system having a vertical component of 2 g's, a horizontal componert along the direction in which the vehicle travels of 10 g's, and a horizortal component in the transverse direction of l 5 g's, o TES-3205 i 2-6 I

- 1. O '" .563" - ~

N

. 75 in. . 75 in. g %d SECTION A-A SECTION B-B Area =. 75 sq. in Area = (2)(. 422) =. 844 sq. in. (minimum area) Lifting Ring-Eye Bolt O 1 B B i l A A 1-1/8 - 12 UNF Thread i i e ( FIGURE 2.2 CROSS SECTIONS OF THE EYE BOLT FOR LIFTING RING TES-3205 2-7 i -,,n-.- a. sw -- - - -- -- m . --w - --~ - - ,,----~e r-- - - - - - - - - - - - - -

i Lift Lift i. i IIq G .i 6 ll ' l.! - .;l; i i Force of 'll j Gravity i l 1 ? i o Y' I 1.

1

. l[ [b_il '!t l: PURE TENSION ORIENTATION PURE SHEAR ORIENTATION i i f ) i i FIGURE 2.3 i EXTREME ORIENTATIONS FOR SINGLE RING LIFTING OF R'IU IN SHIPPING CASK l TES-3205 2-8 l l _ ,.-,,-,-..-,--.----,..--,-,,,---w~e, n v - - - - - - - --- - - - -

The resultant g-loading can be determined as: 1. U o o (10 g's) + (5 g's)" + (2 g's)~ = (Resultant g's) = 10 Resultant g-loading = 11.4 g's 5 he force due to this loading is: (11.4 g's) (7458 lb) = 85,000 lbs ne minimum tear-out material for one tie-down is shown in Figure 2.4. n (

6 Vs.o "

m.. ~.5 " FIGURE 2.4. MINIMUM TEAR OUT MATERIAL FOR PALLET DIE-DOWN O TES-3205 2-9 L

2 Minimum Material Sheared = (2 faces) (. 5" x 1. 25") = 1. 25 in, b De conservative assumption that two tie-downs hold the system means the total area V to be sheared is 2.5 in2 Werefore shear stress equals, load 85,000lb = 34,000 psi area

2. 5 The allowable shear stress = e E 0. 6 e

=. 6 (58,000) su tu 34,800 psi r = su The same resultart of force of 85,000 pounds could be applied to the welds between pallet and cask. To be conservative, only the welds between the cask and one of the 6" x 4" rectangular tubes will be examined. This assumes that the other 6" x 4" rec-tangular tube and the two flat plates which make up the rest of the pallet would break away with the cask. A cross section of a typical weld is shown in Figure 2.5. O e SHEAR PLANE. .50 " / v c __,0,,- l l FIGURE 2.5. CROSS SECTION OF PALLET WELD l TES-3205 l 2-10 l l

The shear plane area is A,. A, depth x length = depth x (length of upper circular weld +1ength of lower straight weld) = A, = (. 353555) (29. 461 + 39. 5) 2 A, 24.38 in = ne resulting shear stress is = I "d 85,000 m = 2 24,38 in 3486 psi = which indicates the cask will not break away from the pallet under this load #:ondition. Examining the bending stmss developed in the stmetural members of the pallet due to the same loading, it will be assumed that the 6" x 0. 5" flat steel platt s do not contribute and only the 6" x 4" rectangular steel tubes make up the pallet. 3e worst loading on the pallets is experienced when the complete system is oriented as shown in Figure 2.6 and the highc st loads will be experienced at Point B. The moment equations am as follows: For 10 g: (17. 0) (10) (7458) (33.5) (2) (P ) = 3 18,923 lbs P = For 5 g: (17. 0) (5) (7458) (34. 5) (P ) (2) = 2 9,187 lbs P = 2 For 2 g: 7458 (2) 4P = 3 3729 Bs P = 3 Totalload on point B is P = P1+P2+P3 31,839 lbs P = ne end of the 6" x 4" rectangular tube can be considered a cantilever beam of length of 3-9. 5". The maximum stress created by this load is, MC max 1 6 (4)3 5 (3) 4

where, I

= 20,75 in = ,2 and C= 2" (31,839 lbs) (9. 5 in. ) (2 in. ) = 29,154 psi 4

20. 75 in Yield stress of the ASTMA-500 material = 46,000 psi.

TES-3205 2-11

D C" Point B Q l-I I I 8 1 1 I I log = 34.5" 2g I I t. 1 O O 33.5" = =- i i l Sg O 28 4 i 1 ' ', j i: 10g - 4-t Sg 17.0 19.0" l c i s u i I where appropriate FIGURE 2,6 10g, Sg, & 2g ORTHOGONAL LOADINGS ON SHIPPING CASK AND PALLET l TES-3205 2-12 lj i _,,_.,__.------.-_.,..,-n.--.-_.,

i This indicates the rectangular tube will carry the desired loading. The G" x . 05" flat steel plate which was neglected does not need to carry any loads in the local vicinity of the pallet tie downs and the rigidity of the tube limits the plate deflection. 4 It was assumed that the load P = 31,839 lbs was applied to the welds connecting i one corner of the cask and one end of a rectangular tube. To simulate the prying effect caused by the loading being generated at the pallet tie downs, a triangular loading will be assumed as shown in Figure 2. 7. i i 5 1 65678 IIPS. N N J PEAK OF 2(31839) = 69678 O FIGURE 2. 7. LOADING ON PALLET / CASK WELDS j ne length of weld involved is equal to the weld around the cask on top of the tube and under the cask on the side of the tube. L

14. 73 in. + 12. 75 in. = 37. 48 in.

= j ne depth of the weld to be sheared is. 35 inch. He shear plane area is A

s A, = depth x length j

A, = (. 35) (37. 48) A, = 13.25 square inches The resulting shear stress = 1 ad 1{ = 4806 psi which indicates the cask ,ya i will not break away from the pallet under this load condition. I i lO 1 l TES-3205 r 2-13

2.4.5 Package External Surface Temperature Para. 71.43 (g) requires that, for a package designed for non-exclusive use shipment, the accessible surface temperatum should not exceed 122* F under conditions of ambled still air at 100*F and shade. Thermal analysis presented in Table 3. G projects an average cask surface temperature of 114*F. Owing to the high thermal conductivity of the steel of the cask body and lid, variations in temperature over the external surface of the cask should be small. IIence, the above mquirement for non-exclusive use shipment is met.

2. 5 Standards for Type B Packaging The standards for Type B packing are addressed in the following paragraphs to show compliance to each item.

2. 5.1 Load Resistance In this analysis the cask is mgarded as a simple beam supported at its ends along its longest axis with a uniformly distrButed load equal to five times the weight of the loaded unit. The loading diagram is shown below.

W = ual = 5(7458) = 57,290 Les. e o o o e o e o o J.b Ab 39 3" r The maximum bending moment M occurs at the mid point and is equal to, 1/8 W1 at 1 = 19. 75" max M = .125 (37,290) (19,75) = 92,060 inch lbs = (/ I TES-3205 2-14

'Ibe cross sectional area of the cask at its mid-point, neglecting the pallet members is shown. J ~26. /" = \\\\\\\\\\\\\\\\ f \\ \\ SE.2 ' 21.7 " i' D b N x ANNM NNN

-- 17.95

= 5 A (32. 2) (37. 53) - (26.1) (21, 7) = G42.1 in. = 4 The maximum stress developed is e = M/Z ; Z = I/C, 1 = 74,604 in and C = 18. 765 in. ..r 23.2 psi (negligible) = = 397 2.5.2 External Pressure i Analysis to show that the cask will suffer no loss of contents when subjected to an external pressure of 25 psig indicates negligible stresses. For a Ap of 25 psi the maximum stress in the cask would be the result of flexure of the 44nch thick lid. For a uniformly loaded circular plate with an edge constrained from rotation, the maximum moment occurs at the edge where, pa max 8 where "a"is the cask inner radius = 13.055 inch ( I = 532.6 in-lbs/in. I. M nm 8 O TES-3205 2-15

The resulting bending stress becomes, 6 ( I = 200 psi (negligible) cr = (4)2 2 t

2. 6 Normal Conditions of Transport This section demonstrates that the package, when subjected to the Normal Con-ditions of Transport specified in 71.71, meets the standards specified in 71.51 (a) (1) for Type B packages.

The package is assessed against each condition that is applicable and a deter-mination is made that the performance requirements specified in 71.51(a)(1) have been satisfied. 2.6.1 Heat Detailed temperature distributions are provided in Section 3.4 for the package under conditions of still ambient air at 100*F and insolation (as derived from the insola-tion data of 71. 71 (c) (1)) for the generator on short circuit. The RTG on short circuit is the normal condition for transport. The derived temperatures for the innermost componer1s of the RTG (shield and fuel capsule assembly) are lower than for an RTG operating on load and deployed as per the design ope-ating conditions. As a point of reference, the T/E module hot junction temperature under the above stated shipping condition is about 75*F lower than the RTG operational condition given the same fuel ) inventory. Thus temperatures, pressures, thermal expansions and the resulting stresses / under the transport conditions are within the design operating conditions for the RTG. 2.6.2 Cold The ambient steady state envrionment of -40*F air and shade on the package pro-duces no adverse effects. MIL Handbook 5 shows that ultimate and yield strengths and tensile and compressive modulus of the cask are actually higher than at room tempera-ture. Although the cask does not mquire a seal to meet any of the delsgn criteria, the lid to cask gasket is silicone rubber which is rated serviceable to -80*F. At an ambient temperatum of -40*F lt is estimated that the average cask temperature would be -18'F. Under the same ambient connition, the average RTG housing surface temperature would be about 47*F. - RTG internal temperatures am well within allowable operating tempera-ture ranges for the materials of its construction. R is concluded that no adverse effects could occur as a msults of the cold en.riron-ment. 2.6.3 Pressure It should be readily apparent that a reduction in the external atmospheric pressure to to 3.5 psia would have no deleterious effect on the massive, thick walled, steel cask ( or the sealed RTG within. The effects of increased pressure (20 psia) are negligible (see Seetion 2. 5,2). l TFS-3205 2-16 L_.

C 2.6.4 Vibration Except for the tie-down provisions examined in Section 2.4. 4, normal trans-V portation vibration effects on the shipping cask are negligible. Although there is no analytical data supporting this conclusion, the shipping cask casks, (there are 4 in existence)as part of the Sentinel 8S and 1S packages, have been shipped overseas by combinations of motor vehicle and ocean vessel numerous times with no adverse effects. These casks were originally shipped by authority of DOT Special Permit #5862 and more recently by Certificates of Compliance No. 9085 and No. 9153. 2.6.5 Water Spray Except for the protrusion of two RTG connectors which are shipped with potted shorting plugs in place, the entire exterior surface of the shipping cask is steel. It should be obvious that the unit would be unaffected by a water spray that simulates exposure of rainfall as per 71. 71 (c) (6). 2.6.6 Free Drop The steel cask with very thick walls relative to its overall dimensions will not exhibit any permanent deformation as a result of a 1.2 meter drop (approximately 4 feet) to a non-yielding surface. Assuming linear elasticity the maximum stress de-veloped as a result of the impact is related to the velocity at impact, y and the speed of sound through the steel, C.o Ee E e = = C* / gl 2 gh where: I o I 6 [ 2 (386) (48)] 1/2 30 x 10

28,710 psi y

'30 x 106 (386) ~ 286 Thus, the assumption that the yleid stress will not be exceeded is justified. 2.6.7 Corner Drop NOT APPLICABLE. This test applies only to packages which are constructed primarily of wood or fiberglass and do not exceed 110 lbs gross weight. l l-h) l TES-3205 2-17 l

2.6.8 Penetration From the geometry and materials of construction, it is obvious that the pack-age cannot be penetrated by a 3.2 cm diameter, 6 kg, bar dropped through one morter. 2.6.9 Compmssion For packages not more than 11,000 pounds in weight, a compressive load applied uniformly to the top and bottom of the backage equal to either 5 times the pack-age weight or 1.85 pounds per squam inch multiplied by the maximum vertically pro-jected area of the package (whichever is greater) shall not reduce the effectiveness of the packaging. Weight = 7458 (5) = 37,290 lbs. In section 2.5.1 the maximum cross section was shown to be 642.1 in.

1. 85 lbs/in x 642.1 in = 1,188 lbs

2. 7 Hypothetical Accident Conditions The package, when subjected to the hypothetical accident conditions as specified in 71.73 of 10 CFR Part 71, meets the standards specified in 71.51 (b) of 10 CFR Part 71 as demonstrated in the following paragraghs. With respect to these standards, the critical member of the package is the fuel capsule assembly installed within the O

shield assembly (clad shield body with attached clad shield plug). Analysis is provided V to s':ow that the result of the hypothetical accident sequence would be (at least) an intact shield / fuel capsule assembly with no breech of the fuel containment capability of the stangth member (primary containment member). This configuration, the, would re-tain the radioactive material within the fuel capsule and, by design, exhibit an external -dose rate of less than one rem per hour at one meter from its external surface (see Chapter 5). Hence, the standards (71.51 (b)) are met. The acci' dent sequence consists of the following test conditions to be sequentially ~ applied to the package: free drop followed by puncture followed by thermal. Ambient air temperatures before and after the tests must be assumed constant at a value between -20*F and 100*F which is most unfavorable for the feature under consideration. Damage caused by each test is cumulative. The evaluation of the ability of the package to withstand any one test must consider the damage resulting from the previous tests. The residual configuration from a test becomes the initial configuration for the next test in the series. The configuration for the first test (free drop) is the nominal package: RTG installed within the shipping cask. Because of the nil-ductitility problem with the structure steel of the cask at low temperatures, no credit it taken for the structural integrity of the cask for the fme drop. Aralysis is provided to examine the effect of the drop on both the RTG housing and the shield assembly.. Although some fin damage may i occur, it is concluded that the housing is intact after the drop and that the shield assem-i bly remains intact and within the housing. From the shield drop analysis presented herein and from consideration of the IAEA Safety Series 33 drop test performed on the

q fuel capsule assembly (Section 2.8)it is concluded that there will be no loss of fuel Q

containment capability and no loss of shield integrity, i TES-3205 2-18 l

The configuration for the punctum test is an RTG containing the shield / fuel capsule assembly. 'Ihe puncture test acting on the housing constitutes a relatively j mild environment due to the mlative thickness of the housing and/or the pmtection i afforded by the fin slabs. Puncture of the housing is not expected. The nominal configuration for the thermal environment is an RTG housing j w/ fins containing the shield /fnel capsule assembly. Thermal analysis (Chapter 3) demonstrates that this environment would qu12kly (within a few minutes) effect melting of the aluminum fins and housing with little transfer of heat to the internals. This results in the release of the shield / fuel capsule assembly such that it is exposed directly to the radiation envimnment. Subsequent analysis assumed the shield / fuel capsule assembly was exposed directly to the fuell (30 minute) ineironment. Maximum tem-peratures in the fuel capsule and liner occur in the post fire period. The maximum temperaturev are well below the critical (melt) temperatures for these components. 1 Maximum thermal stresses in the shield occur during the post-fire cooling period. The stresses are far below the yield stress for the shield material (see Section 2. 7.3.2). t Detailed analyses follow. I

2. 7.1 Free Drop l

For the hypothetical 30 ft drop and impact against a nonyielding surface the l analysis to follow examines the msponse of two major components of the RTG:its i housing and the shield. The housing is locally deformed, but not breeched. The basic shell will remain to asist penetration as delineated in the next section of this mport. It will also be shown that the shield will not be breeched. g For the evaluation of both components the orientation of the RTG relative to l the impacting surface at the moment of impact is most important. For completeness one must examine an impact on a side, either end (top and bottom) and on a corner, j Although credit is not taken with respect to the stress levels generated in the cask i (Figure 1.2) at the moment of impact, its extremely high rigidity implies that its geometric envelop will be maintained. That is, there will be no gross deformations analogous to denting, bending, etc. Further, this implies that any potential damage to the RTG housing is from a direct impact state against the cask; tractions onthe housing i cannot be due to deformation of the cask. Hence, a corner impact orientation may be considered as a combination of the side and end impacts. l l 2.7.1.1 Shield Impact Response. For an impact on the top surface the shield is support by the T/E module and the Macor preload support ring. Although these com-ponents have finite moduli, the interface does approach a rigid surface. All other im-pact orientations include the shield / fuel capsule assembly compressing some. compliant insulation such as Min-K TE1400, MIN-K1800 or a combination of the two. Min-K a rigid fibrous insulation, is an effective energy absorber as has been demonstrated by testing. It will be shown that the insulation absorbs, through strain energy of compaction, a significant percentage of the total available energy where the available l energy is, l E, Wh = 180 (30) (12) = 64,800 in-lbs. = For the hard impact of the shield on the upper surface, the effective decelera-l ) tion of the shield / fuel capsule assembly can be approximated by the following equation - l (Ref. 2.1), TES-3205 2-19 i- ~ ., _,_ _ -.,,, _.- ~.. -, _..

i f gh G = O where G = acceleration in g's, t is the shock rise time in msec and h is the drop i height in inches. Since the shock rise time for steel impacting concrete is between 1 and 2 msec, t = 1 msee will be conservatively used hem. Therefore, i i 1 70 y30 (12) = 1366 g.'s G = This magnitude should be considered an upper bound. Not only was the mini-mum shock rise time selected, but the other materials when crushed will absorb some energy and attenuate the shock duration. The shield, canned with stainless steel, is fabricated from uranium - 3/4% l titanium having the following structural properties (Ref. 2.2). Ultimate strength 110,000 - 145,000 psi = Yield strength 45,000 - 55,000 psi = Elongation 5 - 15 % = 0 Elastic Modulus 26 x 10 psi = j The maximum stress for the top impact occurs at the upper surface of the shield where ~ f the cross sectional area is a minimum. The normal stress becomes O . = 1366 (180) = 13,150 psi = f(4.80) I This stress is far below the yielI capability of the material. Plastic deforma-j tion will not occur. To illustrate the less sevem impact for the side impact orientation, it can be shown that the insulation will absorb a significant portion if not all of the a*/allable i energy. This is also very important when evaluating the RTG housing structural cap-ability during impact. As an example, consider the side-on impact orientation where the shield / fuel capsule assembly will crush Min-K 1800 insulation. Recently, com - pression tests were conducted on three coupons of Min-K 1800 (2.5" diameter; 1.5" thick) where the coupons were not laterally constrained. The results were nearly I identical for all three coupons where the typicalload-displacement curve is shown in l Figure 2.8. The tests were terminated at or near the 5000 lbs level. The area under a stress-strain curve repmsents the material's strain energy capability per unit volume of effective material. From Figure 2,8, the area under the curve is 233. 9 in-3 l lbs/in.. The shield / fuel capsule assembly can be geometrically represented by conical l frustrums and cylinders. The cmshable volume via projection os a typical section is shown in the sketch below. O TES-3205 2 t

FtG U R_E. Z. 6 TYPtCAL COMPRE93cto LOAD - Di :P./CLM?.g, r DATA foe' UNCbtuSTFA NED MIN - K 19 >O AT ROOM W P. i l 500C f / TEST TERA nNI.TEC-ECCC / i F) / C / 3t0C / ( q[C(. I 1000 O 1 0 .E 4 .6 .S 1.0 IN. DisPLACEM ENT ~ SPECIMEN 5 DtA = 2 5 't2. TM IC <.tC ESS =- i. :.. !. l TES-3205 2-21

I b' s I w%ip / (l. &* ' MAtM>drP MR C405YMh!? ~ s u f9*h:n e r I MES7Alf U U A A <<<//////r/,, ,/< <<< /,,, CAsX LIO l TES-3205 l 2-28 l

2.7.2 Puncture O The second environment in the hypothetical accident sequence is a free drop of the package through a distance of 40 inches onto a stationary and vertical mild steel bar or rod of 6 inch diameter with its top edge rounded to a radius of not more than 1/4 inch. Following the 30 foot drop and impact against a non yielding surface, the result-ing conSguration is the intact RTG. Potential penetration of the RTG housing, fabricated from 6061-TG aluminum alloy, is examined. From Ref. 2.3 the minimum thickness of the housing to resist penetration is given by the empirical equation, f#\\ t = P \\rui where W is the RTG weight of 276 lbs and e represents the ultimate tensile strength u of the aluminum which is 42,000 psi (minimum). Substituting in the above equation, t =. 028 inch. The minimum thickness of the housing is th9 cylindrical housing shell at 0. 23G inch. However, with the radial cooling fins it is impossible for the 6" diameter pin to contact the cylindrical surface. Themfore, the only vulnerable surface is the lower closure where its minimum thicknessis' O.500 inch, much thicker than that derived from the penetration equation.

2. 7. 3 Thermal O'
The nominal configuration for the thermal environment is an intact RTG housing containing the shield / fuel capsule assembly. '1he initial effect of the thermal environment 'is to quickly melt the aluminum housing which reduces the configuration to the intact shield / fuel capsule assembly. The thermal emironment was assumed applied to this configuration for the full 30 minute period. The post thernal period was analyzed to a point in time for which steady state condt-tions had been attained. Details of the thermal analysis are presented in Section 3. The following section present the major findings of the thermal analysis and analyses of pressures, differential thermal expansion and thermal stresses occurring over the thermal and post thermal periods. 2.7.3.1 Summary of Pressures and Temneratures. Maximum temperatures of individual components occurring as a result of the thermal environment are pre-sented in Table 3.10. Maximum temperatures of the shield body and plug, shield clad, strength member and liner are well below their respective material melt temperatures. Internal pressures which may result within the primary fuel containment mem-ber (strength member) are insignificant when compared to the capability of this unit. .The strength member was tested to an external pressure of 1000 bars -see Section 2.8, IAEA Special Form Testing, q I TES-3205 2-29 l l
Internal pressures which may develop within the shield body and shield plug (gas gaps between shield and shield clad) are addressed in Section 2. 7. 3. 3. (V) 2.7.3.2 Differential Thermal Expansion The effects of diffemntial thermal expansion in the clad shield member are addressed in Section 2. 7. 3. 3 below. 2.7.3.3 Stress, Pressure and Thermal Expansion Analysis. The biological shield with the fuel capsule has been thermally analyzed for the fire emironment. The maximum thermal stresses occur at 0,05 hours after the initial exposure to the fire, at the time when maximum thermal gradients are achieved. To perform the thernal stress analysis, the shield body, fabricated from U -3/4 Ti, was subdivided into 152 finite elements for a solution utilizing the ANSYS program (Figure 2.11). Each finite element is a ring with r, O and Z displacement degrees of freedom at each node required to define the element. Figure 2,12 presents the isothermals resulting from the thermal analysis. The gradients are not severe due to the high conductivity of the shield material. The minimum and maximum temperatures are 997 and 1123*F respectively. The thermal stresses are a function of both clastic modulus and the enefficient of thermal expansion. For U - 3/4 Ti, E = 20 x 100 psi and a = G. 4 x 10-0 n/in
F.
i The solution indicates a maximum equivalent stress (Mises) of 7250 psi at node 110 (see Figure 2.13). This stress intensity is far below the yield stress. 7 ( ) The shield also includes a. 025 inch thick stainless steel clad (Type 321). '~ The thermal expansion coefficients of the clad and shield am different, 0.3 x 10-G in/in *F for the former and 6.4 x 10-G in/in *F for the latter. Following the impacts, two possible conditions can exist (1) the internal proload, or a portion of the preload, exists where the top and bottom faces of the clad are compmssed against the rigid shield, or (2) no preload exists and the clad is free to expand away from the shlald with no induced stress. The more critical environment is the first. The inner clad shell is 4.822 inches in length where its maximum average temperature in the fire becomes 1075*F. The change in length of the clad is. V AL = 9. 3 x 10-6 (4.822) (1075-70) 04507 inch = 4.821 " I For the identical length of shield, AL, = 6. 4 x 10 (4.822) (1075-70) g = 03102 inch. // /j/ o m v TES-3205 2-30
i l i i 1 1 .9. /88 t 2.454 - l l' /. 7/0 ---- d.Sd6 i72 i?> { l i X /j9 I$B I?*3 l l i i l T j l l I II\\ j 4.5l6 I st, 4 i i 3 no iI!i J.3//, g 'er -l l l l 1 l /.984 5** I i l' ,o i i j [( n e t t,. 17 j ,!/* e => ' sc su. -- i i 2 S 4 I I sm. o 2.$9/ ~ 3.6l2 ? J 1 l dimensions in inches FIGURE 2.11 i 4 I SHIELD FINITE ELEMENT MODEL 4 t {' TES-3205 i 2-31 I
J. /88 2.656 /. 2/O = 8 3G8 llZ3 Q'o iti il 7,39 L iiw 1 _L wool ik l . _L_ _weeU-k I i; \\ j 0010 \\ i !7 N stubo - SS%. i i Yhh 5* \\i$ \\ \\ _L
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\\ > o N..i. 3.. /. - i v \\,; $~ E~ 4 e t-i / i \\a6 / i g. [. I s! / era. O y, \\ 2 39/ ~ s.rd2 i t I dimensions in inches i 1 i All Temperature in 'F FIGURE 2.12 SilIELD ISOTilERMS O TES-3205 2-32 l l
l l [ Vl1 ANSTS 85/ 7/10 N 11.5306 [g-g PLOT H0. 1 POST 1 STEP =1 I ITER =1 ~ STRESS' PLOT I b! ! !,,!k SIGE ORIG SCALING l l [ ZU:1 DIST=4.6 ll XF=1.82 YF=4.18 NoOF-ll DMAX=.0555 DSCA=8.29 iso N l l A MX=7248 MH=133 r 9 il IHC=500 1}i% lli O i i r ..=. =,=,=w I 1 I I I I I t/ l 1 1 1 1 t/ i 'l 5 S SHIELD THE N SS*IT FTRE FIGURE 2.13 SilIELD ISOSTRESSES O TES-3205 2-33
Therefore, the differential expansion is. 04507 . 03102 or. 01405 inch. This is equivalent to a strain of.01405 (100)/4.822 or 0.291%. This implies a very small O plastic strain since the yield strength is defined at 0.2%. Geometrically, this also implies an extremely small buckle pattern as shown in the preceeding sketch. It is important to note that the elongation of Type 321 stainless at 1100*F is nominally 30%. A similar condition exists in the circumferential direction. At room tempera-ture there is a nominal five mil gap between the inner clad shell and the shield ma-terial. As a result of the Bre environment, the interference is approximately.001 inch implying an insignincant strain of 0. 052%. Failure at a weld is also impossible since a relative displacement cannot develop at either shell-closure interface. The same argument is applicable with respect to the external shell of clad. In addition to clad / shield interfaces the differential thermal expansions of the capsule strength member mlative to the shield wem investigated. 'Ihe design provides gaps between these members and the majority of the gap dimensions are preserved during the fire environment. That is, no interferences are developed. Another possible concern is the membrane stress in the outer clad shell from gas expansion between the clad and the shield. During assembly assume that the helium at atmospheric pressure is at approximately 70*F. At an average temperature of about 1100*F the air expands where the pressure becomes, 1100 + 460 14.7 = 43.3 psi p = ( 70 + 460 j Therefore, the dliferential pressure becomes 28.G psi. The maximum radius of the outer shell is 3.642 inch. The circumferential membrane stress becomes, pR 28.6 (3.642) "O " t .023 4529 psi = At 1100*F, the yield strength for this material is 18,000 - 20,000 psi. 2.7.4 Immersion - Fissile Material Not applicable. The package does not contain fissile material. 2.7.5 Immersion - All Packages Para. 71.73 (c) (5) states that a separate, undamaged specimen must be sub-jpcted to water pressure equivalent to immersion under a head of water of at least 15 m for a period of not less than eight hours. The equivalent external water pressure ( for this environment is 21 psig. As per the definition, the package to be considered is the nominal shipping con-figuration - an RTO installed in the shipping cask. The effects of the external water pressure on the cask structure would be nil. TES-3205 2-34
J De cask would allow relatively slow ingress of water into its interior. The silicon rubber seal between the cask lid and bocty and the rubber gaskets between the j cask body and the ste.inless steel exterior receptacle / connector mounting plates are r i A capable of preventing water ingress under b 21 psig pressure. However, the attach-ment poid for the receptacles to the stainless steel plates (two per cask) are not i sealed. (The configuration for other RTG units shipped in this cask did include an O-ring seal at the receptacle attachment point. For this package, the O-ring seal is omitted -the receptacles are bolted to the plate; metal to metal contact). These two } points will, then, allow for the ingress of water. The rate of ingress is unknown: i ^ j Assume that the interior of the cask is completely filled with water. 1 3 Even given sudden immersion of an RTG in water, detrimental effects on the RTG from brmal shock would be insignificant. All seal points in the RTG are cap-able of withstanding the 21 psig water pressure. Here would be no ingress of water l to the interior of the RTG. I At worst, then, the effect of this environment would be a lowering of RTG housing and fin temperatums effecting lower temperatures throughout the interior of j the RTG. RTG temperatums would, at any point within or on the surface be higher than the water temperature (unspecified - assume 40*F). RTG temperatures would l then be between those previously discussed under normal conditions of transport - see Section 2. 6. I and 2.6.2. i Thus, it is concluded that no adverse effects would occur given the immersion 1 environment. l 2.7.6 Summary of Damage The end result of the hypothetical accident sequence (drup, puncture, thermal) I i-is an intact shield / fuel capsule assembly. The fuel containment capability of the pri-mary containment member (strength raember) has not been comprumised. There will i be no release of the radioactive fuel which is contained within the stangth member. External radiation dose rates for this configuration am (by design) less than one rem / i ] hour at one meter from the surface of the configuration. l The consequences of b immersion environment (for all packages) are less i severe than those for h accident sequence. [ l Hence, the requirements of 71.51 (a) (2) have been met.
2. S Special Form i
1 The contents of this package qualify as "special form" by virtue of the fact that the fuel is doubly encapsulated in a heat source assembly that has been tested to cri-4 teria that meet or exceed the test requirements for special form material as specified in Para.10 CFR 71.77. l The actual tests applied to a sample heat source assembly containing fbel l simulant are shown in Figure 2.14. Of these tests only the impact test, percussion test and brmal test am requimd by 10 CFR Part 71. (Note that the bending test of 10 CFR d O oes not apply since the heat source length to diameter ratio is less than 10. ) The i TES-3205 I 2-35 i 1 i
FIGl'RE 2. I4 (APPEND'X 1. IAEA SAFETY SERIES 33) HEAT SOURCE QUA1JFICAT10N TEST REQUIREMENTS 1.0 CENERAL
2. 2 percussian test 1.1 De teste desertbed in paragraphs 2.1 - 2.6 saclusive shall be applied he capsule shall be pieced on a sheet of lead widch le opported to semples or preeotypes of capsules constmeted as for use in a generator except by a smooth solid surface and striack by the flat face of a steel billet so as to that their radioective content may be olmulated by inactive material of the same produce an impact equivalent to that resultig imm the free fall of 7 kilograms or etztler asture. His implies that, subsequent to satisfactory conclusion of thinugh 1 meter. The flat face of the billet shall be 2.5 centimeters in diameter the tests. Ast! laspection will be carried out during the production of capsule for with the edges rounded off to a redlue of not less than 3 millimeters. He leed, operstlomst use to ensure that the standartie schieved by the samples or proto-of hardness number 3.5 to 4.5 on the Brinell scele and not more than 25 milli-types are malataleed.
meters thick, shall cover en eres greater then that covered by the espoule, ^ I" to adottion, every loaded capsule shall be subjected to t:e leakage test ladicated ha paragraph 2.6 prlor to tastallation in a generator. 2.3 'Nrmal het 1.2 De capoule shall be subjected to each of the tests indicated in q Section 2 below, anch.dans those for corrosion and vibration where appropriate ne capsule shall be heated to e temperature of 800*C and it aball grg for the particular opplicotton. be held at that temperature for a period of 30 minutes before betg allowed to
cong, M
i c.) d3 1.3 I the teste de not regnire to be carried out at a particular tempers-2.4 hermal shock test C3 ro ture, then they should be done et the operatig temperature if this is practicable. 8 1.4 De testo shall be carried out in such a way se to ensure that the "the capsule shall be heeted to its maximum operating temperature sample capsule sidfere maximum damage, and then phanged in water et zero temperature where it aball be left for 10 minutes. 1.5 After each of the toets, the capsule shall be shown to have retained 2.5 Pressure teet its original leak-tigtenese within the securacy of the chosen method. 1.6 A efferent semple or prototype espoule may Le used for eed. W the of 1000 bars .e 08 N re m r, testa encept in the case of that ladicated in paragraph 2.6.
2. 0 TEST METHODS 2.I knuset test nts test relates to the requirements of paragraph 1.5 Any commonly accepted leakage test may be used, provided it is of a senettivity comparable with e
in fles a n ofI em acc. If thie & gree of leakage can k he capsule shell fall ce to the target from a belght of 9 meters. De
*** '*9"I " "*"I* * "" * * " " * *

target shall be a flat, hortaontal surface of such a character that any increase in Its resistmace to displacement or deformation upon impoet by the capsule would 2.7 Other testa not significantly increase the damage to the capsule.
For certain applications, corrosion, vibration, irradiation and creep testa may be specified by the competent authority.
T j i l tests to which the bed source was subjected am those prescribed in the Internatior.al Atomic Energy Agency's Safety Series 33, "A Guide to the Safa Design, Constructicu L and Use of Radioisotopic Power Generators for Certain Land and Sea Applications. " { j SpeciScally, the tests are as speci$ed in Appendix I of that document, reproduced t herein as Figure 2.14. Summary test maults are as stated in the Certification Docu-i ment provided by the Test Facility, Oak Ridge National Imb, and reproduced hemin as Figure 2.15. i i
2. 8.1 Descrintion h strontium fluoride was processed at the Waste Encapsulation and Storage Facility (WESF) at Hanford, Washington. Basically the fluoride conversion process is as follows: A volume of aqueous feed solution containing strontium is neutralized to ph 8-9 with sodium hydroxide solution. Solid sodium Duoride is added to the solu-4 tion to pacipitate SrF. h resulting slurry is digested at approximately 80*C for 2
t one hour with air sparging and is then Sitered. & Siter cake is washed with water and Sred at approximately 1100*C in argon for several hours. ARer cooling, the SrF2 is pulverized and loaded into the WESF capsules by impact consolidation, which is essentially a cold step-pressing operation. Complete properties of the fuel can be found in Ref. 2.4. i 90 h fuel to be used the Sentinel SS heat source is SrF which has been en-2 j capsulated at WESF. N rF2 fuel within the WESF capsules is extracted as sin-tered agglomerates, pulverized to smaller pieces and hot pressed in a graphite die to l a " puck" or pellet about 2. 56 inches in diameter and 1.16 inches thick. Hot pressing i and reencapsulation of the fuel is accomplished at the Oak Ridge National Laboratory. h liner assembly consists of a tubular housing with two welded end caps. O One of the end caps is welded and tested for leak tight integrity and weld quality prior l to any hot cell operations. Details of the liner assembly and internal shims are pro-i- vided in Figures 2.16 and 2.17. After the fuel pucks are inseded into the liner the Baal weld closure is done in a hat cell by a remote, automatic TIG process using weld parameters established in a development program, r I h stungth member or outer capsule consists of a deep bored cylinder with I one end integral and the open end machined to accommodate a threaded and welded end cap. Final weld closure of the end cap, following the insertion of the clean (decon- = taminated) liner assembly into the strength member, is an automatic plasma-arc type weld performed using weld parameters established in a development program. A stainless steel handling knob is threaded into the end cap to facilitate transfer of the assembly between adjoining hot cells and to permit lowering of the heat source into the RTG, The knob is removed aRer capsule installation, Details of the strength member and handling knob are shown in Figures 1.4, 2.18 and 2.19 & stungth member is designed to meet the test requirements of IAEA Safety Series 33 previously described in Figum 2.14. 1 l Paragranha 2. 8. 2 thmush 2. 8. 5 These sections of the Regulatory Guide 7.9 pertain specifically to the special form testing as pascribed in 10 CPR 71. As previously stated, the acutal testing performed is as per Appendix I of IAEA Safety Series 33 (reproduced herein as l Figure 2.14). Summary results of this testing are provided in Figum 2.15 lO TES-3205 2-37 i
" 52 0"" K RIDGE NATIONAL LABORATORY Smero av uAarn umstra ENEmov sysTrus ac. Can RfDGE TENNESSEE 3'831 September 26, 1985 Mr. John F. Vogt Project Manager Teledyne Energy Systems 110 West Timonium Road Timonium. Maryland 21093-3163
Dear John:
Certification of IAEA Testing of the sentinel SS Heat Source Capsule for the 180 Wattit) Strontium-90 Generator During the period of September 4 to September 12, 1985 the heat source cap-sule for the Sentinel SS strontium-90 generator was tested by the methods laid out in the IAEA publication Safety Series No. 33 (Guide to the Safe Design. Construction, and Use of Radioisotopic Power Generators for Certain 7s ( ) Land and Sea Applications. IAEA. Vienna, 1970). The exact date, test con-x' ditions, and leak rates before and after each test are given in Table 1. Table 1. IAEA Testing Date Test Conditions Befor fter 9-04-85 Drop Test 9.0 m 2.0 x 10-9 1.4 x 10-8 9-05-85 Percussion 1.4 Kg x 5 m 1.4 x 10-8 1,4 x to-a 9-09-85 Thermal 800*C for 30 min. 1.4 x 10-8 1.8 x 10-8 9-11-85 Thermal Shock 800'C - 0'C 1.8 x 10-8 2.4 x 10-4 9-12-85 Pressure 1000 bars (15 Kpsi) 2.4 x 10-8 2.8 x 10-8 As can be seen from the leak rate data, the highest leak rate measured with our helium leak rate detector was 2.8 x 10-8 std. cc/sec. Since this is much less than the 1 x 10-4 std. cc sec required by the IAEA test. I cer- \\ tify that this capsule has successfully met all test requirements. FIG 07tE 2.15 IAEA TEST CERTIFICATION l TES-3205 - 2-38
. - - -. _ _. ~.. - . - - - ~.. - -. -. - -. - i i Mr. John F. Vogt, Project Manager September 26 1985 ) i 4 i i j Attached you will find a copy of the technician's logbook entries photo-i graphs, and leak rate testing data for the IAEA testing. l 1 I Very truly yours. P .'. 0 m. J., /. A. Tompkins J Radioisotope Development and Technology Operations Division L JAT:drw I I Enclosures { I cc: H. L. Adair l J. R. DeVore ~ K. W Haff I L. J. Mezga C. L. Ottinger i W. E. Pasko. DOE'ORO i W. C. Remini. DUE HQ l 3 T. H. Row l I J. A. Setaro i i i t f i i I ( l I i l l i FEURE 2.15 (Cont'd. ) a TE8-3206 ~ j 249 I t ~
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>r9 l With regard to the pressum test (test 2.8 of Figure 2.12), additional analysis is provided below in Section 2. 8. 6. The summary statement mquired by Regulatory Guide 7. 9 is pmvided in Section 2. 8. 7. 2.8.6 External Pressure on Strength Member l The fuel capsule stength member, fabricated from Hastelloy C-276 is a cylin-drical shell of 0. 384 inch (min. ) thickness with end closures. The end closums, one i of which is threaded and seal welded, are 0. 744 inch in thickness. The inside and out-side radii am 1.476 and 1.860 inches mspectively. i' The environment of interest is an external pressure of 14,500 psi per IAEA Series 33 representing deep submergence. A prototype heat source assembly has been hydrostatically tested to this level where the test specimen includes a ibel simulant of lava. The fuelis an attribute in that it provides a rigid foundation to restrain any j large plastic deformation or collapse (instability). The structural properties for Hastelloy C-276 at room temperature am tabu-lated below. Minimum Values per ASTM 8574-83a Typical Values Ult, tensile stungth, psi 100,000 115,000 Yield strength, psi 41,000 52,000 Elongation, % 40 59 0 Elastic Modulus, psi
29. 8 x 10 i
The minimum values will be used in the analysis to follow. I An estimate of the strength member capability can be obtained from the classi-cal thick wall cylindrical shell equations where the maximum stress occurs at the in-i side surface. 'Ihe circinnflerential and meridian stresses of interest am, 2 -2 p b Sg" 2 2 (Eq. 1) j b-a i "O x 2 (Eq. 2) l i f i TES-3305 2-44
where: b outside radius = 1. 860 = inside radius
1.476 a
Since Hastelloy C-276 is a very ductile material, an equh'alent stress rather than a maximum principal stress can be compared with the yield strength to determine insiplent plasticity. From the energy of distortion or von Mises yield state, the equivalent stress is given by, (T -7 3) + (7 -T ) + (# -# o) (Eq. 3) e = x r r g o Substituting Eq. I and 2 into Eq. 3 with e = o at the inside surface, the pressure re-quired to achieve initiation of yielding is," e, (b -a) p = Y
1. 732 b'
_ 41000 [(1.860) -(1.476) ) o 1.732 (1.800)*" 8765 psi = An estimate of ultimate capability can be made by Ictting e represent the ultimate strength of 100,000 psi in Eq. 3. 'Ihe associated pressure becomes 21,380 psi. However, there is concern for more than the cylindrical shell such as the end 3 closures, seal weld and the closure-cylinder transitions. To evaluate the strength member in detail the ANSYS finite element program was utilized to obtain an clastic-plastic solution. Figure 2.20 illustrates the applied finite element model where the ele:nents are axisymmetric 2D isoparametric solid elements defined by four nodes per element and two degrees of freedom (displacements) at each node. The material model input is identical to the linear strain hardenir4; stress-strain curve for Hastelloy C-276 as shown below, o; pc too,000 - 4 0C0 -- E - r?. 9 - 10^ T S ( 6 E$- .00.7 s .w O TES-3205 2-45 L
I.596 F.oso meto f
ii,,
h v. a --....u o = _..- M I' 't 1.476 l l.i i l..,ll 4.4:e iI!, >!r,i O .in !! !l
ra u _.
- Q +4 ii l l Ni, ~ l 1 ! ;1_ i ~M1 e 1.860 dimensions in inches Mat'l: Hastelloy C-270 FIGURE 2.20 c FUEL CAPSULE STRENG'III MEMBER FINITE ELEMENT MODEL TES-3205 2-46 ... _.. - ~
The results of the elastic-plastic analysis is as follows: O Equiv. Stmss, Equiv. Strain, 3 psi Threaded closure - outside center 41,316 0.41 Thmaded closure - inside center 41,905 0.81 Weld 24,765 < 0.2 Thmaded closure - shell iderface 64,G97 16.19 i Cylindrical wall - outside* 41,927
0. 83 Cylindrical wall - inside*
41,884 0.80 Lower closure transition 58,153 11,77 Lower closure - outside center 41,260 0.38 Lower closure - inside center 35,450 < 0.2 The total axial displacement at the center hne is. 011 inch Ob
Remote imm the end closures; approximately mid length.
2.8.7 Summary A single heat source assembly was subjected to all of the tests shown in Figure 2.14 and exhibited a leak rate of less than 1 x 10-0 (STP) cm3/see helium as showm in the certification given as Figure 2.15.
2. 9 Fuel Rods Not applicable.
2.10 ppendix 2.~ 10.1 References -Chapter 2 2.1 " Design for Shock Resistance," by R. Magner, Product Engineering, ( 1962. 2.2 Nuclear Metals Inc. -Private Communication l TES-3205 2-47 l L
e f i. I i
2. 3 ORNL-NSIC-68, " Cask Designers Guide," L. Shappert, Feb.1970.
i .i 2.4 PNL-3846, " Strontium-90 Fluoride Data Sheet," Battelle-Pacific Northwestern Laboratories, June 1981. i 4 l r f [ l l i t I f l i I i t ) i l } [ t 9 i i 1 l i s i 1 I l 5 i I b l l i O TES-3205 2-48 -. _.. _ _ _ _ _. _ _ _ _.. _ _ _ _ _ _ _ _ _ _ _ _. _, ~,.. _ _ _. _,. _ _. _ _ _ _.... _ - _ _. _ _ _
. =. i 1 l l' 3. THERMAL EVALUATION 3.1 Discussion j %e Sedinel SS RTG thermally consists of a cylindrical heat source containing,- nominally,185 thermal watts of heat energy. %e heat source, however, is physically i capable of containing up to 210 watts of thermal energy of the curmntly available fuel form. Themfore, for purposes of these transportation safety analysis, a thermal in-vedory of 210 watts is assumed for conservatism. De thermal energy is created by the decay of the radioisotope Sr-90 and its daughter product Y-90 in the SrF fuel form. 2 l The fuelis encapsulated and shielded as described in other chapters of this report. Excepting the thermoelectric (T/E) module contact area above the shield, the shield is surrounded by a high purity, low conductivity, high temperature, molded fibrous insulation called " Min-K" which is made by the Johns-Manville Company of Denver, . Colorado. His insulation serves to direct the majority (about 60%) of the heat output from the fuel through the T/E module which is located at the top of the shield. A l small amount of the heat (8 to 9%) which passes through the T/E module is converted to electrical power for use in an external resistive load. The remainder of the heat passing through the module and the heat losses through the insulation must be rejected ' by the generator housing and fins to the ambient. Therefom 95 to 96% of the heat source energy must be rejected during normal generator operations and/or normal transport conditions. i De generator is, for the most part, filled with inert gasses. The single ex-t ception to this are spaces within the fuel capsule assembly. Construction of this assembly is performed in air. Gaps internal to the clad on the shield body and plug g cladding are purged and backfilled with helium. All other spaces within the generator are purged and backfilled with pure argon. Internally, a bellows seal exists between the T/E module assembly and the insulation spaces. A consequence of the loss of seal to the insulation spaces would be the gradual replacement of argon with air which i j would result in higher heat losses. The increased heat losses would result in Icwer internal RTG temperatures; an inherently safer condition. The T/E material used for this generator would be adversely affected by air. The effect would be a nct de-crease in the efficiency of the module to conduct heat which would tend to increase internal temperatures. This event is readily detectable as a substadial decrease in i the generator output electrical failure. Sentinel operating experience infers a low probability of the occurrence of this event (leakage of air to the module region). There j have been no known occurrence of this for the many Sentinel type generators produced l by TES over the past 29 years. e For all power tests and transport the SS generator is installed within a 7000 lb i steel shipping cask. The cask has a large oder surface area to reject the relatively small fuel heat energy. This cask was originally designed to transport the Sentinel 8S unit which codains over twice the fuel thermal inventory. For transport, the gen-erstor is placed on short circuit - a condition which produces lower internal temper-atures than those for which the unit was designed to operate, t As will be noted in subsequed sections,'the analyses reported herein is con-servative. Conservative assumptions include the assumption of maximum possible fuel loading and the assumption that the thermal environmed of the hypothetical accided sequence is applied directly to the shield and enclosed fuel capsule. That is, no credit is taken for the cask, generator housing or thermal insulation. O %e analysis summarized herein shows that the package'is capable of with-standing the various thermal extremes associated with the normal conditions of g TES-3205 ~ l 3-1 t i- ___..,,._,,_,._._,..._.____._._.__.._..a__m.._~-__
transport. Analysis is preseded which predicts the detailed temperature distributions for the package for operation on short circuit in 100*F ambient air and with a solar load (as specified in 10 CFR 71) on the cask. He bam shield / fuel capsule assembly is capable of surviving the 30 minute thermalenvironment of the hypothetical accident sequence. The shield and capsule will not exceed their melt temperatures during or after the fire. Fael containment and external radiation levels within specifications am assurred for an indefinite period beyond the end of the fim. The predicted maximum temperatures for the fire event are compared to critical (melt) temperatures in Table 3.1. TABLE 3.1 COMPARISON OF CRITICAL AND PREDICTED MAXIMUM TEMPERATURES (FIRE ACCIDENT) Predicted Critical Maximum Temperature Temperature Component (*F) (*F) Liner, Hastelloy C-276 2320 1510 Capsule, Hastelloy C-276 2320 1390 . Shield, DU- 0. 75% Ti 2075 1383 Shield Clad, (321 Stainless 2550 1402 Steel
3. 2 Summary of Thermal Properties of Materials i
nermal properties of the various RTG component materials are listed in Tables 3.2 through 3.5. Temperature depended properties such as thermal conduc-tivities are provided as coefficients for function fits of polynomial form of order N i _ (N 5 4) as: N' I F (T) 'C T = g i=o I where F is the property and T is the temperatum in 'F. The highest number coeffi-cied provided in the tables indicates the degree of the fit for that particular property j and material. Coefficleds were obtained by least squares analyses of available pro-perty data which spanned the range of temperatures indicated in the tables. Absence l of coefficieds indicates that the property was assumed constad with respect to tem-perature. O TES-3205 3,2
m A r TADI.E 3. 2 111FHMAL CONDUCTIVITY 4 g)4 K (T) = CO+CgF)+C2 g) +C F) +C 3 Temperature Range Material Components Coluluctivity: K (11tu/11r-In
F)
(* F) Ref. No. 1 - llastelloy C-276 Liner, Strength C 0.44705, C *4*404 =. 69E-F IM-2000
3. 5 0
l 2 Memler, Pellet Shims C = 4. 9895E-II, C = - 2.1538 E-14 3 4 2 Argon (15 psia) Fuel Capsulo Gaps, C
7. 7702E-4, C = 1. IGSE-6, C2 = - 1. 5059E-10 100-1200
3. 3 o
g ShieldClad Gap (15 pala) 2 l 5 3 Depleted Uranium Shield C = 1. 08. C, = 9. 4807E-4, C2 0 = -4.1958E-7 IM-12M 3.8, 3.10 C = 1. 2835E-10 3 4 SrF Fuel C I"4 '4' U2 = 1. 2094E-7 70-1562
3. I 2
0" M c4 g C = -2.1433E-Il 3 too CJi 5 Min-K 1800 Insulation Low (K ): C = 8. 583E4, C, = 5.523 E-7 70-700
3. 7 l
p liigh (K ): C = 1. 062GE-3, C, = 9. 75E4 g 6 Min-K 1400 Insulation C .4 -4, C = 7. 52E-7, C =1.3977 M 0 IM-12M
3. 7
= O g 2 C =1. G E-13 3 7 Aluminum IIousing Fins C, = 8. 4 38, C = 7. 254 E-5, C = -7. 622 E-7 70-1000
3. 3 g
2 l (G 0GI-TG) J 8 Stainless Steel Malule llot-P' ate. C = 0.C0943. C = 4. 8302E-4 C
4. 882E-8 138-2118
3. 9 j
(ASTM-347) Dellows 0 1 2 r j C = -1. N E-12 3 4 9 Cart)on Steel Belleville Washers, C a 3. 155, C = -4. 865GE-3. C = 2. 6903E-G 86-1472
3. 3 O
g 2 Load IIcaring Plate. S j Gukle Plate C . 5312E -10 3 1 4 J f
TABLE 3.2 (Cont'ef. ) h Material Components Temperature Range Cormfuctivityr K (Itu/1Ir-La *F) (*F) Ref. No. 10 Macor Pre-Imd Support C, = 0. OG 172, C, = 6. 363 E-6, C2 = - 2. 201E-8 70-1112
3. 0 Ring C = 3. 7 Nil, C = - 1.1394E-14 3
4 11 Cold End llart! ware Temp. (*F): 800 900 931 1000 K: 2.2353 2.7794 2.9855 3.3235 t 12 Dellows Cavity K= 0.00455 190-950 d t'1 13 T/E Malule i, Co 02 (a) O en Circult: l gg Temp. (*F): 800 900 331 1000 to K
0. 01537 0.01G42 0.01690 0.01721 (b) Short Circuit:
T'emp. (* F): 250-919 K 0.02157 i i l 4 I
m TABTE 3.3 SPECI11C 11 EAT C (T) = Co + c, (T) + C2 (T)2 + C3(T)8 Temlernice Range q aN Material Components Spact fle IIcat: C. (TWu/Ih
F)
(' F) Ref. No. I llastelloy C-276 1,lner Strength C, = 0.135 70-2000
3. 5 l
Memler, Pellet Shims 2 Argon (15 psia) Fuel Capsule Gaps, C = 0.1245 o 70-2000
3. 3 Shield / Clad Gap 4
3 Depleted Uranium Shield C = 0,0262, C = 8. 455 E 4, C = 7. 921 E-9, 80-1161 3.3, 3.10 O 3 2 C = - 1. Ol E-12 3 4 SrF I el
C
0. 2431. C, = - 3. 588 E-4, C2 = 3. 787E-7, 116-1800 3.1 2
O C = - 1. W2 10 C
1.343E-14 3
4 5 Min-K 1800 Insulation C
O 4 M-1600
3. 7 1
4m 6'- Min-K 1400 Insulation C = 0. 265 MC/2 0 400-1600
3. 7 k
7 Aluminum Ilousing/ Fins C = 0. 2130, C3 = 5,509E4, C - 7. 622E-7 80-1220
3. 3 to (60Gi-T6)
O 2 e <n 8 Stainless Steel Module llot Plate, C = 0.1025, C, = 8. 355M, C = .625E-8, 80-18 M
3. 3, 3. 9 OSTM-347).
Bellows 0 2 C = 2. 9mE-!I 3 i 9' Carbon Steel Belleville Washers, CO" 3 IM- 00
3. 3, 3. 9 load Bearing Plate, 4
Guide Plate a 10 Macor Pre-Load Support C .0 M -4, C 0" I 2 ~
U
= ~~ Ring i 11 6061-T6 Aluminum Coli End liartfware C = 0. 223 100-200
3. 9 J
12 Argon / Stainless Bellows Cavity C = 0.135 Steel 100-200 3.3 13 T/E Moilule C = 0.6481; (Average of 'C'salues for 70-1200 3.12 T/E elements and Min-K) 4 I n
..m._ TA HLE 3. 4 4 MASS DENSITY p (T) = CO + Cg (T) + C2 (T)2 + C3( ) +C4(T) 4 3 Temperature Range h Material Components ik nsity: 9, (the /In,
g. pg g,g, go, i
I llastelloy C-276 Liner, Sturgth C = 0. 312 g 70-1000
3. 5 Member, Pellot i
Shims i 2 Argon (15 pala) Rael Capsule Gaps. CO = 6. 4 5 E-5 300-1000
3. 3 1
l Shield / Clad Gap 3 Depleted Uranium Shield CO = 0. G901, C, * -1. 747 E-5, C2 = 2.312E-10, 80-1251 3.3, 3.10 C * -3. 2M E-12 3 4 SrF niel '4 C,= 0.1358 2 100-1472 3.1 to tv] 5 Min-K 1800 Insulation C = 0. 0116 a Cl2 0 70-700
3. 7 c's 6
Min-K 1400 Insulation C = 0,0116 i to O 70-700
3. 7 7
Aluminum llousing, Fins C = 0.10 (6061-T6) O 70-200
3. 9 1
8 Stainless Steel Module Ilot Plate, C a 0. 2v.4, C = -8.M43E-6, C = -4.079 E-10, 200-1800
3. 9, 3. 3 T
(ASTM-347) Bc!!ows O 3 2 C3= .136E-14 9 Carbon Steel Delleville Washers. C e 0. 24 D 70-200
3. 3 Load Bearing Plate, Guide Plate i
10 Macor Pm-Load Support Ring C = 0,0908 t o 70-200 I -11 6061-T6 Al with Cold End liardware Cg + 0. 095 A Pistons. Pidon 1 Ifoles, Springs, etc. 12 Bellows Cavity C = G. 45E-5 i O 300-1000
3. 3 I
13 T/E Mmlule C3 = 0. 0155 I 200-950
3. 13 (Average of ' A' values for T/E elements and Min-K) i L
s 4 ,, _ _ - _.,. ~ n 4
O O O TABLE 3,5 EMISSIVITY Temperatum Range No. Material Components Emissivity: e (*F) Ref. No. 1 Ilastelloy C-276 Liner, Strength
0. 2 100-1400

3. 3 Member 2
SrF Fuel
0. 4 70-1800 3.1 2
3 Depleted Uranium Shield
0. G 100-1000 3.3, 3.10 4
Stainless Steel Shield Clackling 0.2 and O.9 70-1500
3. 3, 3. 9 d
(ASTM-347) (2
w44, s
a e
Thermal conductivities for the T/E module were derived from detailed thermo-electric analyses which considers the effects of production of electricity and its O associated internal heat guaeration effects. The conductivities simulate the stated operating condition which vary from generator on short circuit to generator on open i circuit. Their use produces the correct differential temperature across the module. The term " cold end hardware" is defined to mean that portion of the lid / module assembly which codains the imbedded springs and pistons which act to form the thermal contact with the T/E module. IIere again, the thermal conductivity simu-lates the results of analysis using a detailed thermal model of this region. For refer-ence, the detailed modelling yielded a temperature drop of 15'F from the module interface to the exterior surface of the lid. Thermal properties not included in this section are provided in the section describing the analysis, i
3. 3 Technical Specifications of Components Three types of insulation are used in the RTG: Min-K 1400, Min-K 1800 and Microtherm. Min-K is made by the Johns-Manville Corporation of Denver, Colorado (Ref. 3. 7). The material is composed of submicron silica and several t}T;es of silica fibers. Dependent on the form, Min-K may exhibit bidirectional thermal conductivity.
Microtherm, produced by Micropore International, Ltd., is of similar material com-position and may also exhibit a bidirectional thermal conductivity. O Min-K 1800 is produced in two forms: pressed sheet or molded. The thermal conductivities provided in Table 3.2 (Item 5, low and high) are for the bidirectional sheet form. The molded form, used for the SS, has an isotropic conductivity equiva-lent to the low values stated in the table. Conductivity measurements performed at TES and elsewhere on the Micro-therm material used in the generator indicate that this material is essentially equiva-lent to the bidirectional Min-K 1800 as given in Table 3.2 (measurements for the two materials agree to within ten percent for temperatures from 200* to 1200*F). Min-K 1400 is used between the shield plug and the pressure plate. This ma-terial is bidirectional with the high thermal conductivity in the radial direction (as i placed in the RTG). However, since most of the heat transfer occurs in the axial di ection, the material was assumed isotropic with a conductivity equivalent to that which exists in the " low" direction (as given for Item 6, Table 3.2). Figure 3.1 indicates the placement of the various materials. Microtherm is ~ placed such that the high conductivity is in the radial direction of this figum; the low condudivity in the axial direction. Min-K insulation has been used in the many Sentinel type and other generators i designed and constructed by TES. Numerous tests and millions of operating hours have proven the stability of Min-K and its compatibility with interior components. i During normal transportation conditions and design operating conditions, insulation j temperatures are far below the maximum temperature limits (1400*F for Min-K 1400 and 1800*F for Min-K 1800). Although Microtherm has not been used in previous designs, its material composition is very similar to Min-K. l TES-3205 3-8
_ - = - 1 l I
3. 4 hermal Evaluation for Normal Conditions of Transport i O

3. 4.1 nermal Models and Results Thermal analysis included herein assesses package temperatures wer the j
various thermal states mlated to the normal conditions of transport. Detailed des-criptions of the models developed for and employed in the analysis are prwided along with results of the analyses. 3.4.1.1 Shipping Cask and RTG Surface Temperatures. Two thermal models were developed to relate the shipping cask temperatum and the RTG surface tempera-ture to external ambient conditons: a. Cask temperatum. His model predicts the shipping cask surface tem-perature given the internal heat source Q (210 watts or 717 Istu/hr) and l the external ambient air temperature and external insolation heat input I (if present). Details of the model and thermal properties used are pro-l vided in Appendix 3.6.2. For subsequert analysis, the cask is assumed to be of uniform temperature. (He high thermal conductivity of the cask material precludes the establishment of any significant temperature 3 j gradierts in the cask. The temperature differential through the thickness i at any point is est1'nated to be less than a few degrees F). b. RTG surface and head temperatures. His model computes the average RTG housing and fin surface temperature given the cask temperature and the internal heat source Q. It embodies both convective and radiative heat i transfer links from the inner cask surfaces to the housing and fin surfaces. Details of the model and thermal properties am provided in Appendix l 3.6.3. The RTG head temperature is, then,10*F hotter than the average i surface temperature (based onthe results of detailed thermal analysis of the RTG and internals). Both models (a) and (b) are in the form of heat balance equations which are readily solved by an iterative technique, i Cask and RTG surface temperatures derived using these models are provided in Table 3.6. Case 1 of this table prwides (in part) the boundary condition for the detailed RTG thermal model described below. It relates to 71. 71, (c) (1) " Heat. " The insola-tion heat, Q was derived as explained in Appendix 3.6.2 from the Insolation Data . of 71. 71 (c) h(,also IAEA Series 6, Table III). Case 2 addresses 71. 71 (c) (2) " Cold. "- Case 3 of Table 3.6, package in still, ambient 100*F air and in shade was eval-i uated for compliance with the requirements of 10 CFR 71.43 (g), (IAEA Series 6, 230. (b)) for non-exclusive use shipment (non-fullload shipment). He package external surface temperature, according to the requirements, shall not exceed 122*F for the abwe stated conditions. The calculated average cask temperature of 114*F demon-str~ates compliance with the requirements. 3.4.1.2 Detailed Model for Assessing RTG Temperatures. Detailed thermal analysis for the RTG was performed using a thermal model developed for the ANSYS program. ANSYS (Ref. 3.4) is a finite element computer program which has been used extensively for structural and thermal analyses. TES-3205 3-9 , - _ _ _ _ _ _ _ _. _ _ _ _ _ _ _ _ _.. ~. _.. _.. _ _ _ _. _ _ _ _
O O O i TABLE 3. 6 TEMPERATURES: CASK SURFACE, RTG SURFACE AND RTG IIEAD (*F) (NORMAL TRANSPORTATION -RTG IN CASK) Temperatures (*F) Case Cask (T ) RTG Surface (T ) RTG IIcad (T ) [ No. Boundan Condition _ c h yg 1 Still Ambient Air at 100*F, 175 222 232 ) Q = 717 RuAir (210 watts) RTG j QSOL. = 4190 Btu /IIr 8 2 Still Ambient Air at - 40*F, -18 47 57 i } 'Eh Q RTG i 8 j Q = 0 MuMr (sWe) SOL i 3 Still Ambient Air at 100*F, 114 1G7 177 QRTG" ] QSOL "
I8 8 ")
i i l a i i i i l l 3 i -4 m
i l A two-dimensional vedical section of the RTG assembly in R-Z coordinates, was used to create an axisymmetric finite element model for the analyses. The vari-(~ ous components of the RTG were represented by finite elements with corresponding material thermal and other properties. Mgures 3.1 through 3. 7 show the arrange-ment of elements and the dimensions of the analysis model. In the Figures, encircled numbers are the finite elements; the other numbers designate the nodes. Temperatures am computed at the node points. Material desig-l nations are provided for elements as per the companion figures which show components. 2 The component material designations are provided in the propedy tables of Section 3. 2 Fuel thermal inventory was represented by internal heat generation rates in j the fuel elements on a volumetric basis. The heat generated is one of the boundary con-ditions. Analyses of the RTG under operating conditions using this model with a fixed ambient temperature (not reported herein) established a relative temperature pro-file at the surface of RTG housing. For the analysis reported herein, the R'1B head temperature was used to scale these previously derived surface temperatums forming the second boundary condition. Specifically, an RTG head temperature of 232 F (av-erage) was assumed corresponding to Case 1, Table 3.6. Thus, temperatures gener-ated using the model are for the " hot" condition of the normal conditions of transport. l Complete thermal contact for conduction was assumed at all the component boundaries, except at the radial gaps between the fuel, the liner and the strength mem-i ber of the heat source assembly, as well as between the 25 mil thick stainless steel cladding and the uranium shield. Radiation across these gaps was included along with the conduction through the argon gas fill in the gaps. ) 'Ihe thermal resistances at various contact surfaces were modelled as con-vective conductance links between corresponding nodes. The following four interfaces 2 l were included in the model (Figure 3.3)with appropriate conductance values (Blu/hr-ft _p) 4 Strength member end cap to stainless steel cladding; h = 570 Ref. 3.10, 3.11 Liner end cap to strength member end cap; h = 300 Ref. 3.10, 3.11 I Fuel pellet-shim to liner end cap; h = 300 Ref 3.10, 3.11 \\ Threads across the end cap and the wall of the strength member; i h = 1000 Ref. 3.10 l Stainless steel cladding on the shield body to the stainless steel weld l plate under the T/E module (Figure 3.7); h = 600 Ref. 3.10 l 'Ihe values of 'h' were interpolated from ranges indicated in the published i materials referenced and modified with results of various in house tests conducted. j For this analysis, the T/E module was assigned the " shod circuit" conductivity of Table 3.2 corresponding to the normal transport condition. TES-3205 3-11
^ .Z 0 _ L_ l _ g _ _. O COLD - EN D-K g .. HARDWARE o 1 f 5 .~. gj g, c $ >U u Z T/E. MobutE < P-a / E E Yb HOT PLATE. h T a 10 u) S H \\ E. L D o e .2 WI O d I D v cAPautE O Z AsseMety e g 5 al Z x FUEL M a 5 9 e i I o SHlf.LD Pluc, O MIN-K. 1400 I C LOAD Pt.ATY l Gu1DE PL. & WAtl4ERS M ousiN0 'R FIGURE 3.1 l COMPONENTS OF THE FINITE-ELEMENT MODEL: SENTINEL SS RTG O ~ TES-3205 3-12
13 06._E ~ ,_is.co" ma e, n i me ma na ia m @ 38 '@- '@- u.g _ 6_ O b 6 a.ts" =
t na M
M 12.64s_ g " 88 - R a M - 8* m

~ g g staiL*_ =m
11. 1 5 "
ma M ten enom m M E 5" = w a se O 0 8 ges* m g s.ssi_ m = 0 6 8 9 es#5 9 m si sa is34"., 9 9 3;77*
3. 50*_
\\ an " N )NW z.ss'. = si as . sa s. as O O O 9 O g 1.7(_._ ma en 'as ~ ~ as m n' n s.56 - @ 2 e rr ei 6 g e g or 6 ii O @.D s s l 7 i 4 5
s's a
d n 4, FIGURE 3.2 NODAL MODEL OF THE RTG SECTION: NORMAL TRANSPORTATION CONDITION TES-3205 3-13
o 1 END CAP A RCrO N GAP END CAP W ARGON GAP ~ u) .l D a E d C a S FUEL C 2 e PELLETS d O 2 El l-6 O O W/5HIMS g
a 2
a m e < a d D 4 INTERFAC.E g g J coNouc. TANG o U PELL.ET SHIM EMD CAP 4l 4I EN D CAP ce I z i FIGURE 3.3 i COMPONENTS OF THE CAPSULE ASSEMBLY 1 TES-3205 3-14
i s.ss2 " du %. S51"', ggy [g'G y b m2 [f g s.s s a,'. 4. as "7 1.24t" (9 6e) w 7 O ej 7 484" 67 4 681) fog)/ 7.40g*,5-7, a p ( 7.257's d at y 7.206" a so nW g g 6 8 s.e34-55 N 55 E 57 si aW W e ~ s
a 9
1 8 4.fo92" o 6 @ ei y$g 4.f42' y2 49 g g 'd5 v 4.5M" k) zoF l b f 3.77" t do OE M I.Sto" ,g ~ ~ jgg i R 7 l.326" f,4748 -^ n.m n >> l 97 I, Sl5" l l t,33o*' 4
1. M 3 FIGURE 3.4 f)
NODAL MODEL OF THE CAPSULE ASSEMBLY, v NORMAL TRANSPORTATION CONDITION TES-3205 \\ 3-15
t i I l L 1. D l 2 CO L D - END-0 2 C - M ARbWARE O 6 d g 2 g S. S. P L AT E ~ W E A dW d I h F 0 V ! !! O w scoute I W/ MtCA E g) I 10 6. S. P L A T E. 1 FIGURE 3,5 COMPONENTS OF THE LID ASSEMBLY TES-3205 3-16
b) V m 16 00* r39 14 0 14 i 14 2 roa es w.so~ iu i, m im im ~ ~ g 4 r2s 13.1 5" i29 iso ini 152 I S, (e O " 12 S r24 i2s 124. tz7 iso 92. O .3 ne iz.e w ii, im i2i m h ~I I O "8 9 .I d ...Q 11 3 12.0 5" it4 its it in -- Q n-. - Q @,. Q .. Q \\* \\ ' . s s-ie, ie i,1 ,es i' 3 IS4 19 5.. l FIGURE 3.G NODAL MODEL OF THE LID ASSEMBL Y: SENTINEL SS RTG TES-3205 3-17
S.$. P LATE. y M.e ;- tv7 6 t. 5 3 4", ccmangtAw.E I. O O j_& 5' g SMrst ) 34 S H 1 E. L D o 2 4 a.ssi " " g-@ m n p .N!J 4 u, d d = O 4 0 ug is2 so e 5.934" 53 CAPSQLE ASS 6NBLE Y rrr 4.72" rm \\ rrs H \\@ 4.ro" B e O.s ,a .t s.77 44 g FIGURE 3. 7 l NODAL MODEL OF THE SHIELD AND CLAD: ) NORMAL TRANSPORTATION CONDITIONS O TES-3205 3-18
Results of the analysis are given in Table 3.7. In this table, the node numbers (' correspond to the node points as shown in Figums 3. 2, 3. 4, 3. 6 and 3. 7. Temperatures I are in units of "F As previously discussed, the boundary conditions for this analysis correspond to the ' heat" conditions of 71.71 (c) (1) of the normal conditions of trans-port: 100*F ambient air with insolation. Analysis assumes the maximum possible fuel loading of 210 watts thermal. A comparison of temperatures for this transportation conditions with those for the RM in its design operating concucion indicates that temperatures of the shield / fuel capsule assembly are mostly lower than those for the operating condition. R M head, T/E cold junction and housing temperatures are higher, however. This is due to the higher head and housing temperatures applied as the boundary condition tothe analysis. As a point of reference, the module hot junction temperature is estimated to be about 75'F lower given the same fuel inventory. 3.4.2 Maximum Temperatures Maximum temperatures for the normal conditions of transport occur under the " heat" condition (71. 71 (c) (1)). Maximum (or average) temperatures for the major components of the package are presented in Table 3. 8. These values were extracted from the detailed analysis presented in 3.4.1. As previously stated, temperatures for the shield / fuel capsule assembly are lower than those occurring for the RTG in its design operating condition. / TABLE 3. 8 MAXIMUM COMPONENT TEMPERATURES (Normal Transportation Conditions) Component Temperature ("F) Housing 222* j Converter Hot Plate 941 Shield Cladding 1106 Shield 1070 Strength Member 1143 Liner 1321 Fuel 1544 Hot Junction 908* Cold Junction 250* Shipping Cask 175* RTG Head 232* NOTE: For ambient air at 100*F and specified insolation on the shipping cask at 4190 Btu /hr, RTG thermal invoentory at 717 Btu /hr (210 W (t)). 1 O
Average temperature.
b TES-3205 3-19
O O v TABLE 3. 7 RTG TEMPERATURES FOR T11E IIEAT CONDITION (NORMAL CONDITIONS OF TRANSPORT) SFNTINFL 5-5 RTG 1 NCRMAL TRANSPORTATION CohDITION ffRANCSS). ..... TLMPEF ATURE SOLUTION..... TIME = 0. teaC STEPz 1 ITfRATION: 10 CUM. ITIR.: 8 N00L T[ *P N00E TE MP NODr if Mr NODE TEMP N00E TEMP 1 210.00 2 210.00 3 210.00 4 210.00 5 210.00 6 210.00 7 210.00 8 210.2P 9 210.13 10 210.00 11 210.01 12 210.00 13 210.69 14 211.00 15 210.29 16 211.74 17 213.58 IN 35 5.f P 19 270.78 20 211 0R 21 211 00 22 210.36 23 211.42 24 213.ft 25 417.95 26 284.66 27 211.00 28 211.00 29 1064.8 30 1047.6 31 1043.0 32 N05.23 33 331.46 34 211.02 35 211.00 36 1066.8 37 1046.3 3r 1042.7 39 1026 5 40 1122.0 41 1106.3 42 1107.1 43 1102.1 44 1044 3 45 1162.8 46 1156.4 47 1128.3 48 1160.7 49 1170.4 50 1169.8 51 1185.3 52 1193.5 b5 1544.2 54 1428.7 55 1268.6 56 1265.8 57 1154.8 58 1155.0 59 1014.0 60 1503.2 F3 61 1443.2 62 1321 2 63 1290.5 64 1318.9 65 1289.9 L3 M 66 1289.9 67 1143.3 6A 1142.0 69 1142.9 70 1139.8 [3 71 1135.5 72 1138.5 75 9P3.56 74 987.22 75 989.06 c) ba 76 1020.2 77 1107.0 TH 1130.8 80 998.84 gg R1 442 18 82 213.00 F3 213.00 P4 977.75 85 437.25 H6 214 04 87 214.00 R8 919.2P A9 354.27 90 216.96 91 217.00 92 224.54 93 278.26 94 217.01 95 217.00 96 224.25 97 256.82 98 216.M0 99 217.00 100 223.3P 101 221.12 102 218.12 103 217.00 104 223.00 105 221.00 106 220.00 107 219.00 108 935.10 109 940.52 110 993.59 111 929.08 112 924.02 113 931.35 114 935.86 115 927.71 116 927.30 117 924.21 IIM 245.90 119 253.30 120 544.a2 121 550.22 122 645.92 123 241.10 124 241.55 125 341.u4 126 339.48 127 225.58 128 259.53 129 238.57 130 303.59 131 303.95 132 224.92 133 236.28 134 230.15 135 228.43 136 227 91 137 225.72 138 234 00 139 230.00 140 22A.00 141 227.00 192 226.00 145 1069.8 146 1052.2 147 1052.0 148 1047.5 149 1045.5 150 1044.8 111 1044.7 152 1105.7 153 1090.3 154 Inet.2 155 1070.9 156 in50.4 157 1048.4 158 1044.6 159 1048.0 160 1047.a 161 1033.H 162 1033.8 163 9P4.79 I f.4 989.46 165 989.68 166 9P9.58 167 989.43 I f. R 9A4.T4 169 989.3R 170 9P9.64 171 9P9.60 172 989 24 173 9Ha.90 174 98R.95 175 1042.7 176 1042.7 177 In26.h 178 1026.5 179 1022.5 1MO 1020.2 181 999.29 182 998.85 183 977.01 1P4 977.70 1h5 952.h7 186 948 14 187 947.96 188 944 13 190 224.9e 191 919.22 193 943.60 194 447.42 195 947.98 196 1105.9 197 1090.R 198 10H4.9 199 1071.9 200 1141.2 201 1152.0 202 11h4.9 203 1191.7 max 14UM TEMPERATURf: 1544.2 AT NODL 53 MINIMUM TEMPERATURE: 210.00 AT N00F 12
3.4.3 Minimum Temperatures n() Under conditions of still, ambient air at -40*F and shade, the average shipping cask temperature is about -18'F and the average RTG surface temperature is about 47'F for a fuel loading of 210 watts. Given the nominal fuel loading of 185 watts the temperatures would be somewhat lower. Temperatures are well within design limits given this environment. 3.4.4 Maximum Internal Pressure The RTG is charged with argon gas at BOL under one atmospherie pressure. Viton O-rings in the housing end covers and around the electrical connector assembly provide positive seal and cause internal gas pressure buildup. Under the normal conditions of transport, this increase would not be more than 5 psi. For this shipment, the cask is not sealed. Hence, there would be no pressure buildup within the cask cavity. 3.4.5 Maximum Thermal Stresses The small temperature gradients, especially in the shield, of about 15*F do not cause any significant amount of thermal stresses. 3.4.6 Evaluation of Package Performance for Normal Conditions of Transport A review of all component tempe. itures of the package computed for the " heat" condition and those temperatures inferred for the " cold" condition indicates that tem-peratures are well within acceptable values for the component materials. He RTG housing can withstand a hydrostatic pressure of 25 psig. Internal pressures which may be created by the heat condition are well below this value. There are no significant thermal stresses generated in any component.
3. 5 Hypothetical Accident %ermal Evaluation In this section, the effects of the hypothetical accident thermal environment are evaluated and discussed. The environment is as specified in 71.73 (c) (3).
Specifically, the configuration resultant from the free drop and puncture environments is to be subjected to a heat flux not less than that of a radiation environment of 1475*F with an emissivity coefficient of at least 0.9 for a time period of not less than 30 minutes. For purposes of calculation, the surface absorptivity of the configuration must be either that value which the package is expected to possess if exposed to a fire or 0.8, whichever is greater. As previously discussed (see Section 2. 7), the initial configuration for the thermal environment is assumed to be an RTG oontaining the shield / fuel capsule as-sembly. The evaluation provided herein first shows that the initial effects of the thermal environment would be to quickly effect complete melting of housing components /] which allows the exposure of the shield / fuel capsule assembly. Subsequent analysis, 'V then, examines the effects of the " fire" applied directly to shield / fuel capsule l TES-3205 l 3-31 l
assembly. Post fire cooling is examined for a period of 24 hours after the fire. Dur-ing this period all temperatures attain their " steady state" values for the assumed O post fire ambient air condition of 100*F.
3. 5.1 Thermal Models Temperature evaluation was performed using two ANSYS thermal models and the ANSYS program. The first model examined the effects of the thermal environment on the RTG to the point of exposure of the shield / fuel capsule assembly. The second examines the full 30 minute environment and the cooling period on the shield /fael capsule assembly.
3.5.1.1 RTG Model. He ANSYS model used for thermal evaluation for normal conditons of transport as described in Section 3.4.1 and shown in Figures 3. I through 3. 7 was modified as follows: a. He housing side thickness was increased by an amount equivalent to the weight of detachable top and bottom fins, fin stubs and mating flanges; similar thickness addition was done to the RTG head to accommodate fin stubs on the top cover. He calculated weight to area ratio for the fins was used on a per radian basis in the model (see Appendix 3.G.4). The resulting additional housing thickness is as shown on Figure 3.8. Node points and finite element numbering in this figure and the revised model are as per the previous model (Figure 3. 2), b. The thermal conductivity for the T/E module was changed from those for short circuit condition to the open circuit condition. Here it is assumed that the 30 ft drop and/or puncture would cause an open circuit in the T/E module or external electric circuitry, c. De external node (node 205, Figure 3.8) was held at a constant temperatum of 1475'F and radiatively linked to the external surface nodes of the RTG. He effective emissivity for the radiation links was as per requirements, [(1/C RTG) + II!' fire) -1] = 0. 735 'eff = where, (RTG = 0.8 (aluminum housing) and e = 0. 9 (specified) fire Initial temperatures for the transient analysis were the steady state tempera-tures reported in Section 3.5.1 corresponding to an RTG which hrs been released from the cask after ambient conditions of 100*F air, insolation and the maximum 210 watt . fuel loading, c This model is applicable up to the point where the critical housing elements reach their melt temperature (1080*F for the strudural aluminum). At this point, a supplementary calculation was performed to estimate the time required for these critic,al elements to absorb the required latent heat of fusion for melt. This calcula-O tion is provided in Appendix 3.6.5. TES-3205 3-22
Eh 15.221 15.2 21" ma tal ' Ma
Ma 24 vs w,
se7 @ 38 'O-6 6 3 ,,, g ..i 6 S O S _!1.ss"
w w
,M, M @,_n.gio " .c e 2.644,_ O O 8 s2a - N tem 160 tillis M M 5" - ~ ll, { { O 0 9 e . s. ~ O 8.553L_ = 0 g g g _us - to si sa u ' os O es>4 -- a 9 [AMBRT. N O D E. AT coNiT. g g g TEMP 3 x, g l ~ e @ s.so __ z.ss" N /N = so si = . n se u 6 9 0 0 0 i.7c = n 'm = m. e n is6--- O 6 CE 2 m a rr a e ao ai 6 8 0.M" L M a ti f1 IS 4 0 @.O - g 7 i a 4 a 4 n fg FIGURE 3.8 RTG NODAL MODEL: 30-MIN. FIRE CONDITION TES-3205 3-23
3. 5.1. 2 Shield / Fuel Capsule Assembly Model.
This model is similar to the applicable portions of the RTG model described above. The finite element and node '~/N numbering system is diffemnt. He model is as shown on Mgures 3. 9, 3.10 and 3.11. ' V Figure 3.9 shows the bottom portion of the shield, shield plug assembly; 3.10 the details of fuel capsule assembly; 3.11 the sides and top of the clad shield. Individual componerts of these figures may be identified by examination of Figures 3.1, 3.3 and
3. 7.
An external node, node 135 in Figure 3.11, provides the link to the radiative thermal environment or to ambient air for the post fim cooling period. For the 30 minute fire, the radiative linkage to the shield clad surface nodes is similar to item (c) of 3. 5.1.1 above. IIere, however, the effective emissivity is 0. 818 since the emissivity for the oxidized stainless steel clad is assumed to be 0. 9. For the post fire period this node was radiatively and convectively linked to the surface nodes with a fixed temperature of 100*F mpmsenting 100*F ambient air. He convective film coefficients for the top, bottom and side were assumed to depend on the surface geometry and the temperature difference between the surface and the ambient air and were of the form, c (AT/L)*, b = where: e and m are constants and L is the charactoristic dimension. s L diameter D (ft) for top and bottom surfaces = L height, H (it) for the side surface = /' For this analysis, c = 0. 281 and m = 0.25 (Laminar flow). The characteristic dimensions are: Surface L (ft) Top 0.542 Side 0.742 Bottom 0.542 Temperatures of all nodes at the end of the 30 minute fire input transient mn were applied as the starting temperatures for the cool down run. he emissivity of the chdding was assumed to be 0.9 for heavily oxidized stainless steel, t l The gap dimensions between the capsule components and shield-shield clad l remained constant for fire and post fire analyses. This adds conservatism to the results since thermal expansion would, in reality, tend to close the gaps and enhance heat transfer. Initial temperatures for the 30 minute fire phase are those for the steady state ' heat" condition as discussed above. (The RTG housing melt analysis msulted in very little heat transfer to the interior portions). TES-3205 3-24 u
O CAPSULE j, ASSEMBLEY 102. .10 5 10 4 IM lof, 101 96 2 4 O D ./ $ 4 de d J S H1E LD GI 4 u M qw hw '9 h k its I.770" g so ae e N ic, #b i.7w 'O D I' IFF lat um 12 es so g h 9 9 es as 57 55 bl n M 40 15 0 si M N N N O ARGONM G A
H 69 M @ M
=g c g g c LA D ei az es e SH tkLn O O 5' PLUG 52 55 57 SHIE L D as @ @ 8 e ri 22 2s 34 mm 27 P Ltr G 2s 2s 3e 64 E (@ H @ [t A RGoNM) GAP [t it 20 u iz is u is r. n is 0 8 $ @ @ cLA@o @is@ [ i z 3 4 s c, y a3 io i i l l l FIGURE 3.9 NODAL MODEL DETAILS OF SHIELD AND CLAD ) O TES-3205 3-25
O) 'w. .ae m y,*
5. m
,7 se w 9 EB,io r io .M M / 5.2si w so my ' ~ ' ' ' ' 4.524 A& 27 m 09 60 / 4.445 33 sg 4.k$7 _ Al N c .o' e a 4.=.- o 9 8 g (h g .() .2.974 To 71 72 m u 7s ar. m 73 . O g O k) h I.732 H ES O ( g,@ B 11 3 05
4 g,7g r.7 L5R _
p ....__. l 65 6.11a M 108 1.Sto .i 57 M' WM' W g 1.32to t.474 '" f,371 l.BlE t.M11a l.ett FIGURE 3.10 CAPSULE ASSEMBLY DETAILS: ( 30-MIN. FIRE AND COOLDOWN CONDITIONS O TES-3205 3-26
6,,, -~ -- 12 9 8.900 - @ E.ERS O ISI 12 1 60 a.mno ei 13 0 It'T = 6se 134 - 25 O a. ._. S H.1 E L D. s g4, e2 = los os q q s i33 '03 M M d (AMST. ~ ~ ~ h N0D$ gg 7 ] s g i/Djl22 12 3 'j U - y.. CAPSULE-b . ASSEMI5LEf 11 5 11 8 bilG U 11 9 U 11 7 120 1.75 l Q 3 $ 5 N \\@ 6f. A FIGURE 3.11 SHIELD AND CLAD DETAILS: 30-MIN. FIRE AND COOLDOWN CONDITIONS TES-3205 3-27 t
i l For conservatism, the full 30 minute fire period was analyzed. (No credit was taken for the time required to melt the RTG housing. ) 3.5.1.3 Test Model. The assessment of the package is made by analysis in lieu of testing. + 3.5.2 Package Conditions and Environment As previously discussed, the drop and puncture environment are assumed to release an essentially irtact RTG with some minor fin or housing damage but no punc-ture of theRTG. This is adjudged to be the worst case initial condition for the thermal analysis. Fudhermore, initial temperature conditions for the transient thernal analysis correspond to the highest temperatures that the RTG will experience under the { various possible states of the normal conditions of transport. 3.5.3 Package Temperatures i 3.5.3.1 Fire Input (30 Minute Thermal Environment). The first transient analysis with the full RTG section exposed to 1475'F fire, indicated the housing and i fins reaching the melt temperature (about 1080*F for 6061-T6 aluminum) in slightly _ ore than one minute into the fire. Detailed temperature distributions from the m ANSYS run are provided in Appendix 3.6.6. Another 2. 5 minutes were estimated to add the necessary heat of fusion to melt the side of housing and bolted fins away. Since most of the heat from the fire is absorbed in melting away the housing and fins, the increase in temperatures of the internal components is insignificant. I Exposure of the bare shield to the full 30 minutes of fire raises the component temperatures. Maximum temperatures reached for each of the components are listed in Table 3.9. Detailed temperature distributions from the ANSYS model are provided i in Appendix 3. 6. 7. 3.5.3.2 Post Fire Cooling. During the initial period of cooling, the' shield and the cladding lose heat at fast rate. The fuel and liner, however, continue to i rise in temperatures due to the time laginvolved. The temperatures reach peak values of 1845'F and 1510fF, respectively for the fuel and theliner in the first half hour of cooling. In the next seven hours of cooling, temperatures of all the component fall considerably and reach steady state values asymptotically. At the end of the 24 hour cooling, total heat rejected equals the fuel thermal inventory, indicating that the heat input through the fire is dissipated completely. Detailed temperature distribu-tions are provided in Appendix 3.6.7. 4 l O TES-3205 3-28 I L
1 i TABLE 3. 9
A jQ MAXIMUh! COh1PONENT TEMPERATURES (Fire Input on the Bare Shield)
Componed Temperature (*F) Shield Clad 1402 Shield 1374 Strength Member 1390 i Liner 1466 Fuel 1779 NOTE: The bare shield with cladding exposed to 1475*F fire for full 30 minutes. Table 3.10 summarizes the maximum temperatums reached by each of the i componerts through the post-fire cool down period. Figure 3.12 shows the tempera-ture time history of significant nodes for every component. Detailed temperatum distributions from the ANSYS model are provided in Appendix 3. 6. 7. Maximum temperatures attained by the liner and the strength member, remain considerably below the solidus temperature of the materialinvolved, namely, Hastelloy C-276. A similar conclusion can be drawn for the shield material, the depleted uranium. Thus, the resulting temperatures do not cause any breach of containment or loss of shield integrity, i ) TABLE 3.10 i MAXIMUM COMPONENT TEMPERATURES: POST-FIRE COOLD0%T Component Temperature (*F) Shield Clad 1402 Shield 1383 Strength Member 1390 i Liner 1510 Fuel 1845 L ( NOTE: The solidus melt temperature for Hastelloy C-276 (the strength member and the liner), is 2435*F. (Ref. 3. 5). lO TES-3205 3-29
O ...e_ =hw-a v vy - 48 85/ 7/ 8 -. a n.- 19.7375 PLOT ll0. 3 TEP P FOST26
na CPIC SCALI!4G 2u=1 DIST=1.1 i n.u 1,*
i ib,a i a w 70 TEIP FuE L , s \\ 91 TEN )
1. t N E R.
o i \\ ,,,l 62 TEN ) ST R. M ER., l w s! pt SHLD/ CLAD no 0 2.5 S.0 i.51(l.012.515.0 ti.5 2(1.0 22.5 25.0 SENTIHEL 5-S RTG : POST-FIRE C00LDOWN (COOLSSC) ~ l FIGURE 3.12 MAXIMUM COMPONENT TEMPERATURES: POST-FIRE COOLDOWN O TES-3205 3-30 -.. ~
3.5.4 Maximum Internal Pressures t Relevant considerations here are pressures which may develop within the stangth member (primary fuel containment member) and within the cladding of the shield. With aspect to the former, the fuel caps 11e assembly has been tested to an external pressure of 1000 bars without loss of containment capability (Section 2. 8, IAEA testing). Pmssums which may develop within the shield components (shield-clad gap) have been discussed in Chapter 2 of this report. 3.5.5 Maximum Thermal Stresses The maximum thermal stresses in the shield would result from the largest thermal gradient across the shield. De thermal transient analyses for the 30 minute fire input and the post-fire cooldown were reviewed to obtain the largest temperature gradients, which occurred at O. 05 hours (3 minutes) into the fire input stage. Results of the detailed finite element stress analysis performed are reported in Chapter 2. Rese stmsses were computed on the basis of the temperature profile of the shield at 3 minute into the fire. The temperatums at the various locations in the shield and capsule components are shown in Figum 2.10. 3.5.6 Evaluation of the Package Performance for the Hypothetical Accident hermal Conditions ne thermal environment, when imposed on the RTG results in an intact shield / fuel capsule assembly with no breech of containment and no loss in shield integrity. Hence, there will be nc release of the radioactive material within the primary con-tainment member (strength member). Furthermom, the analysis presented in this h chapter infers no breech of the inner liner which contains the fuel. Hence, the double d containment system is intact. Maximum temperature in critical components occurring once the fire and/or post fire cooling period are reported and compared to critical (melt) temperatures in Table 3.1. Here it is seen that the maximums are well below the critical temperatures. By design, the shield / fuel capsule assembly provides sufficient radiation shielding to meet the radiation requirements of 71.51 (a) (2) (see Chapter 5). Hence, there is no breech of containment or loss of shielding. Information provided in this chapter for use in other chapters have been noted in the applicable sections of this chapter.
3. 6 Appendix 3.6.1 References (Chapter 3) 3.1
" Strontium-00 Fluoride Data Sheet,"H. T. Fullam, Battelle Pacific Northwest Laboratory, PNL-3846, Richland, Washington, June 1981. 3(G TES-3205 3-31
3. 3
"%ermo-Physical Properties of Matter," TPRC Data Series, Purdue University, Lafayette, Indiana. 3.4 "ANSYS Engineering Analysis System," Swanson Analysis Systems, Inc., Houston, Pennsylvania, Rev. 4.1E.
3. 5 Brochures from the Stellite Division of Cabot Corporation, Kokomo, Indiana.

3. 6 Brochure from Corning Glass Works.

3. 7 Johns-Manville Product Information Data Book (and in-house tests).

3. 8 "he Use of Uranium as a shielding Material," E. F. Blasch, G. L. Stukenbroeker, et.al., Nuclear Engineering and Design, No. 13, 1970.

3. 9
" Aerospace Stmetural Metals Handbook, " Belfour Stulen, Inc. 3.10 "hermal Iderface Conductance of TEG Hardware,"J. Hargodon, Martin Marrietta Corporation, July 30,1965 3.11 " Simplified Method for Calculating Thermal Conductance of Rough, Nominally Mat Surfaces in High Vacuum," D. McKinzie, Jr., Lewis Research Center, Cleveland, Ohio, NASA Techrdeal. Note: TN-D-5627. O 3.12 " Thermal Conductivity of lead Telluride" - R. Taylor & H. Groot, Properties Research Laboratory, W. Lafayette, Indiana.
3. 6.2 Cask Temperatum For the transportation condition, the RTG is installed in the shipping cask.
The average cask temperature was determined through a solution of the heat balance equation which includes the internal heat source,~ specified insolation rate, ambient air temperature and convection and radiation between the cask surface and the ambient air. To determine the insolation rate, Q the surfre areas assumed were the full areas of the surfaces (as opposed to thb,re realistle projected area). A surface absorptivity of 0. 8 was assumed. His value is twice the absorptivity for the white egoxy paint on the casks exterior surface. De factor of two was applied for con-servatism and to account for some degradation of the paint surface.. Hence, Q T^T + S^S SOL where: R.and R are the top and side heating rates and T g A,A are e top and side surface areas, res-T g j pectively, (ft ). 2 Here, R[m=2 246 Btu /ft -hr, is the average rate corresponding to the specified value of 800 cal / on a flat surface for a 12 hour day, transported horizontally; TES-3205 3-32
2 R = 123 Btu /ft -hr is the average rate corresponding to the specified value g of 400 cal /cm2 on a curved surface for a 12 hour day. Thus,
0. 8 [246 (7. 72) + 123 (27. 2)]
Q = SOL = 4190 BtuAir The heat balance equation is, (QRTG+ 9 SOL) = {(n A (T -O) C +bA g + h A ) (TC ~ 0) l 2 T where: QRTG RTG reject heat = maximum thermalloading of = the heat source (210 w(t)). QSOL specified insolation input to the cask (Btu / hrs). = ~1 Stephan-Boltzman constant, (1. 714 x 10 e = 2 4 Btu /hr-it _.R ) E Cask outer surface emittance = 0. 8s (cpoxy paint) = A total surface area = Ag+AT, (34. 9 ft ) = Ag cask lateral area (cylindrical surface), 27. 2 ft ) = AT cask top area (flat surface), (7. 7 ft ) = TC unknown cask temperature, (*h) = O ambient air temperatum, (560*R) = h,h natural convection coefficients for the cask = y 2 cylindrical surfacgand the top surface, respec-l tively. (Blu/hr-ft *F) I/4
further, fT -e 0.281 ( C h
f r the side and = 3 1 H /T -O C h 0.281 f r the top = 2 D j with H cask height, (2. 77 ft) = l D cask diameter, (3.13 ft) = i-1 i O TES-3205 3-33
.J.+- a J --+a -w-.4.* 4 A -an. i-f 3.6.3 RTG Surface and Head Temperatums ' \\ A heat balance equation is used to determine the RTG surface temperature for the RTG in the cask. The average cask temperature is computed according to the method and data of 3.6.2, along with the RTG internal heat source inventory as the input boundary conditions. The equation provides for convective and radiative links between the RM surface (housing) and the cask internal surface. (The temperature drop through the thick wall of the stainless steel cask is neglected. ) The heat balance equation is, ORTG* eff b ^ fin /hsg + Astring) I h c -T} U e i where: Q and T are as defined earlier in 3.6.2. RTG c n = effective fin efficiency for the entire RTG, 0. 9. gfg A areas of fins and housing. n d sg A +A +A = j top bottom housing i fins fins side + top
17. 84 ft
= i 2 A = lateral envelope area = 9.2 ft, E h natural nvection coefficiert for the enclosed = e space between the cask and the RTG. l h is of the form, e
0. 0732 E (G r)
/S M S , Ruhr-R - F h = e r i i where: K thermal conductivity of the air film over the tem- = perature range of the system. -2.6956 x 10~4 + 3. 2603 x 10 T 'Ihus, K = film ~0 + 7. 2433 x 10 Tgg,, (Btu /hr-A *F) fil m = 1/2 (Th+ c)' ( ) T L, S charactoristic length of the RM and the average = spacing between RTG and the cask. L = 1. 521 ft, S = 0. 504 R. f The product of the Grashoff-Prandt1 numbers, N - Pr '8 Gr evaluated from a function fit: OV TES-3205 3-34 l l .. ~.
~ ~ R (NG r' Pr _S (T -T) - h c -0
19. 8567 - 0. 01395 Tfh + 6. 516 x 10 T
= gg 7 h is evaluated for N range of 2 x 10 to 2 x 10. Gr Pr j Further, h = equivalent heat transfer coefficient for radiation between the RTG g l and the cask. 4 7 E (T -T 4) h Btu /hr-ft
F R
(T -T ) h c j i where: _/ 1 / 1 _1 1 l l +l -1 E = \\ ' cask ( RTG with ceask = 0.6 (cask inside coated with chromate conversion coating) CRTG 0.9 (epoxy paint on the RW nousing and fins) = 1 An iterative solution of the above equation yields the average RTG housing temperature. Detailed analyses of the RTG thermal models under the design, full load condi-tions have established that, over the range of interest, the RM head temperatum would be 10*F higher than the average housing temperature. 'Ihus, { Thead = (Th + 10),
F.
t j 3.6.4 Fin Weight as Extra Housing Thickness There are three kinds of fins on the generator: Welded stubs of 2. 90" x 4.3" x 0,25",12 in number on the top cover. a. j b. Nine, 6.88" x 4. 08"x 0.25" top fins bolted on the stubs, i c. Three 6. 88" x 6. 00" x 0. 25" top fins. d. Nine, 9. 94" x 4. 08" x 0. 25" bottom fins bolted on the stubs below the
flanges, e.
Ihree, 9. 94 " x 6. 00" x 0. 25" bottom fins. f. Twelve bolting stubs: 6. 88 x 0. 75 x 0. 25" (top) I g. Twelve bolting stubs: 9. 44 x 0. 75 x 0,25" (bottom) TES-3205 3-35 i. 7 _., - -,,.... _, - - -.,,,, ~ ~,,.. _ -
l h. Mating flanges between the top assembly and the lower housing: R
7. 625 ", R 6. 625", H = 1. 00".
= g g Areas for Radiation Top fin stubs: (2. 9 x 4. 3 x 2) (12) = 299. 28 in A = Top, bolted fins: A (6. 88 x 4. 08 x 2 x 9) + (6. 88 x 6.00 x 2 x 3) = (505. 267 + 247.68) = 752. 947 in = Bottom, bolted fins: A (9.44 x 4. 08 x 2 x 9) + (9.44 x 6. O x 2 x 3) = (693. 274 + 339,840) = o 1033.114 in" = Bare housing between fins: f(2 x) (6.875) (15) - (12) (9. 94 + 6,88) (O. 25 ) A = 597. 49 in = Total radiation area 2682. 83 in =
18. 63 ft
= Fin Weights Top fin stubs: (2. 9 x 4. 3 x 0. 25 x 12) v =
37. 410 in
= Top bolted fins: V = (6. 88 x 4. 08 x 0.25 x 9) + (6.88 x 6. O x 0. 25 x 3) (63.158 + 30. 960) = 3 94.118 in = O TES-3205 3-36 1
i 1. t Bottom bolted fins: (9. 94 x 4. 08 x 0. 25 x 9) + (9. 94 x 6. O x 0.25 x 3) v = ) (91. 249 + 44. 730) = if 3 135. 979 in = 2 i Bolting stubs (top and bottom): I (6. 88 + 9. 94) (O. 75) (0,25) (12) v = 1 3 i
37. 845 in
= Mating flanges: I ] r (7. 625 - 6.625 ) (1. 00) v =
44. 768 in
= j Extra housing wall thickness (side): Total volume to be added j (94,118 + 135. 979 + 37. 845 + 44. 768) = 3 V 312, 71 in = s { Weight = (312,71) (0,10) = 31. 27 lbs 1 r (R,2 2 and, V, -Rg ) (H) = i j .. 312. 71 = r(R,2 -(6. 875)2 ) (15. 0) ., R, =
7. 342 in.
.,textra
@o -6. 875) = 0. 467" j Extra top cover thickness: Volume added = (a) = 37.41 in j 37.41 ..t= 4' r(7. 342)2 l'
0. 221 in.
= I j . Maximum height of the housing, Z = 15, 221 " m,x i i TES-3205 3-37 i i* - -.., - -, __. _ _.. _.._-,. _ -,. _._, _ _ _ _.._ _ -- - _. _. --.. -.._ ---- _ _ _. _ _ _ _ _ _ _. _.
3.6.5 Housing / Fin Melt Time Total weight of the housing side with extra thickness of 0.467": Total wt. = (p) [( x ) (R -Rg ) (H)] g (O.10) (( x ) (7.342) - (6. 625) f (15. 0)] = ' 47,19 lbs = At 170 Btu /lb of lated heat of fusion for 6061-TG aluminum, total heat of fusion, Q (170)(47,19) = g 2. 8022 Btu Assuming housing / fin surfaces to be an average temperature of 1080*F (melt temper-ature of 6061-T6 aluminum), the heat rate due to " fire" environment, rI A (0)4 - (T )4 , where the terms are as defined earlier. Q = h -8) (O. 818) (16. 55) {(1475 + 460)4 - (1080 + 460) (0,1714 x 10 = 194815 Btu /hr = .. time mquired to melt the housing side, 8 = 0. 041 hr T = 394 5 = 2.46 min 3.6.6 Temperature Distributions -Hypothetical Accident thermal Environment on RTG The data sheets included in this appendix (six sheets) provide the detailed tem-perature distributions for the transient thermal analysis (ANSYS model) which ex-amined the effects of the thermal environment on the RTG (as reported in Section 3.5.3.1). Node numbers on the sheets correspond to the nodal numbering system of Figure 3. 4, 3. 6, 3. 7 and 3. 8. Temperatures are in units of 'F. Each sheet corre-sponds to a specified time (in hours) relative to the beginning of the fim. The first sheet gives the initial conditions for the run (time = 0). Data carries through that period required for the critical nodes mpresenting the aluminum to reach, or go be-yond, melt temperatures. I i ( l O TES-3205 3-38
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O O O SENTINEL 5-S RTG1 HOUSING MELT (TRAN5SM) 23.5764 85/ 8/15 CP: 9.482 ..... TEMPERATURE SOLU 1 ION..... T!*[ r .50000F-02 LOAD SirP: 2 ITERATION: 1 CUM. ITER.= 2 h00[ TEMP h000 TEMP N000 TEMP NODE TEMP NODE IIMP 1 227.32 2 243.43 3 243.62 4 265.08 5 365.26 6 514 59 7 798.21 8 225.17 9 231 97 10 245.33 11 261.25 12 354.42 13 549.71 14 684.53 15 217.58 16 216.05 17 214.60 18 354.23 19 271.57 20 575.45 21 707.87 22 216.77 23 215.41 24 214.91 25 418.00 26 285.29 27 560.36 28 679.85 29 1065.0 30 1047.8 31 1043.0 32 805.00 33 331.22 34 432 36 35 465.86 36 1067.0 37 1046.2 38 1042.e 39 1026.9 40 1122.8 41 1106.3 42 1107.1 43 1102.2 44 1044 1 45 1166 1 46 1156 1 47 1128.1 48 1163.3 49 1170.4 50 1169.7 51 1187.2 52 1193.4 53 1546 1 54 1428.3 55 1268.8 56 1266.0 57 1154.8 58 1152.5 59 1014.3 60 1505.1 61 1442.3 62 1321.2 63 1290.8 64 1319.0 65 1290.1 66 1290.1 67 1143.0 68 1141.9 69 1142.8 70 1139.9 71 1135.0 72 1131.0 73 983.84 74 987.09 75 988.95 76 1020.2 77 1107.0 78 1130.6 80 998.93 81 442 16 82 368.38 83 402.00 84 977.91 85 437.16 ,g pq 86 379.49 87 415.57 88 919.00 89 358.24 90 428.31 L3 03 91 463.63 92 277.47 93 278.42 94 531.14 95 610.53 l j, d, 96 332.78 97 2t8.01 98 539.81 99 653.50 100 379.74 c> bo 101 465.60 102 550.94 103 662.56 104 408.35 105 489.33 106 568.24 107 658.86 108 936.67 109 941.28 110 934.15 111 929.48 112 924.01 113 932.8% 114 936.99 115 928.68 116 927.74 117 924.15 118 266.35 119 265.44 120 545.95 121 550.68 122 648.38 123 308.60 124 284.58 125 341.46 126 339.88 127 307.65 128 348.48 129 306.49 130 309.26 131 310.00 132 340.05 133 555.27 134 408.88 135 412 58 136 409.68 137 375.54 138 801.46 139 480.15 140 442 67 j 141 439.02 142 476.27 145 1070.0 146 1052.2 147 1052.0 148 1047.4 149 1045.3 150 1044.6 151 1044.5 152 1106.5 153 1090.4 154 1085.2 155 1073.0 156 1054.9 157 1053.2 158 1044.4 159 1052.9 160 1052.7 161 1024.3 162 1024.1 163 985.47 164 988.86 165 991.81 166 991.76 167 989.14 168 985.40 169 988.80 170 991.69 171 991.64 1 72 988.97 173 988.89 174 988.94 175 1042.8 176 1042.8 177 1027.0 178 1026.9 179 1022.9 180 1020.2 ] 181 999.06 182 998.95 183 977.02 184 977.87 185 953.05 166 948.46 187 948.09 188 944.63 190 292.20 i 191 918.98 193 944.32 194 947.78 195 948.30 1 196 1106.4 197 1090.8 198 1084.9 199 1073.9 200 1147.6 201 1131.8 202 1186.9 203 1191.6 205 1975.0 MAXIPUM TEMPERATURE: 1546 1 AT N0DE 53 MINIMUM TEMPERATURE: 214.60 AT NODE 17 f 3
_ _ = \\ J v v 4 SENTINEL 5-S RTG1 HOUSING MELT (TNAAS$M1 23.5783 85/ 8/15 CP: 10.937 i' ..... TFMPERATURf SOLUTION..... TIMF : .10000E-01 LOAD STfP= 2 ITERATION: 2 CUM. ITER.: 3 NODE TIMP NODE TF MP NODE TEMP NODE TEMP N00E TEMP 1 253.80 2 292.66 3 315.24 4 360.82 5 589.75 j 6 621.H3 7 1125.2 8 250.94 9 276.19 10 317.55 11 357.34 12 575.75 13 P70.12 14 1022.8 15 237.74 16 227.99 17 217.49 18 354.91 19 273.17 20 921 48 21 1045.7 22 235.80 23 225.75 24 218.41 25 418.01 26 286.07 27 901.20 2H 1016.9 29 1065.0 30 1047.7 31 1043.0 32 805.00 33 311.88 34 710.66 35 743.94 36 1067.0 37 1046.2 38 1042.7 39 1026.8 40 1123.2 ,I 41 1106.5 42 1107.3 43 1102.4 44 1044.2 45 1166.8 46 1156.1 47 1128 1 48 1164.9 49 1170.2 50 1169.5 ] 51 1189.8 52 1192.7 53 1548.9 54 1427.4 55 1268.6 56 1265.9 57 1154.4 58 1152.0 59 1014.5 60 1507.9 61 1941.5 62 1321.4 63 1290.6 64 1319.1 65 1290.0 66 1290.0 67 1143.1 68 1141.8 69 1142.6 70 1139.9 71 1135.0 72 1131.0 73 983.71 74 987.17 75 988.97 76 1020.4 77 1107.2 78 1130.6 80 998.87 >3 81 442.69 82 575.12 83 611.73 84 977.82 85 437.69 bq 86 599.55 87 637.87 88 919.01 89 358.97 90 693.09 L3 U2 91 729.23 92 402.75 93 279.52 94 865.13 95 942.99 l j.b 96 507.78 97 260.83 98 877.42 99 986.86 100 583.43 >a h3 101 750.99 102 885.60 103 1002.4 104 616.69 105 772.98 h*. 106 898.18 107 999.66 108 938.07 109 941.99 110 934.77 111 930.11 112 924.25 113 934.85 114 938.01 115 929.53 116 928.46 117 924.40 118 324.90 119 302.11 120 547.75 121 552.10 122 655.97 123 439.84 124 372.95 125 343.64 i 126 342.27 127 469.54 128 516.P2 129 421.22 130 322.06 I 131 323.16 132 521 80 133 844.00 134 610.77 135 617.68 136 614 17 137 570.89 138 1101.4 139 699.06 140 656.53 l 141 651.86 142 689.77 145 1070.0 146 1052.3 147 1052.0 148 1047.4 149 1045.4 150 1044.6 151 1044.5 152 1106.6 153 1090.5 154 1085.5 155 1074.0 l 156 1056.8 157 1055.1 158 1044.4 159 1054.8 160 1054.7 161 1021 4 162 1021 3 163 985.64 164 988.67 165 992.92 166 992.87 167 989.16 168 965.56 169 988.62 170 992.76 1 171 992.70 172 988.98 173 988.91 174 988.96 175 1042.7 176 1042.7 177 1027.0 178 1026.8 179 1022.9 lbD 1020.4 181 999.14 182 998.87 183 977.04 184 977.78 185 953.20 186 948.77 187 948.31 188 945.33 190 438.42 191 919.06 193 945.05 194 948 14 195 948.62 196 1106.8 197 1090.9 196 1085.1 199 1074.9 200 1145 6 201 1131.8 202 11P9.3 203 1191.0 205 1975.0 MAXIMUM TEMPERATURE: 1548.9 AT NODE 53 MINIMUM TEMPERATURE: 217.49 AT NODE 17 i
rA= m e-at+4 ...e_+_ __4s_ o __w .4-4,, .= = + 4 -e -e -k-e._ e -4 +-,-4 a4--*J4.-- -4 -4 O O O SENT1hEL 5-S RTG:Hous1NG MELT ITHAN%SM) 23.5808 85/ 8/15 CPz 12.385 ..... TEMPERATURE SOLUTION ***.* Timi * .15000E-01 LOAD STEP: 2 ITERATION 3 CUM. ITE8. 4 N000 TEMP NODE TrMP NODE TEMP N0DE TEMP N00E TEMP 1 293.81 2 361 46 3 413.37 4 481 54 5 803.19 6 1046.6 7 1294.9 8 288.71 9 341.35 10 416.06 11 477.80 12 790.18 13 1093.1 14 1227.0 15 272.60 16 249.47 17 224.52 18 356.21 19 275.90 20 1158.2 21 1248.7 22 269.50 23 245.01 24 226.28 25 418.04 26 287.33 27 1140.5 28 1227.5 29 1065.0 30 1047.6 31 1043.0 32 805.01 33 333.07 34 958.74 35 986.85 36 1067.0 37 1046.2 38 1042.7 39 1026.8 40 1123.4 41 1106.7 42 1107.5 43 1102.F 44 1044.2 45 1166.8 46 1156.0 47 1128.1 48 1165.7 49 1169.9 50 1169.3 51 1191 9 52 1192 2 53 1551 9 54 1426.6 55 1268.4 56 1265.6 57 1153.9 58 1151.5 59 1014.6 60 1510.7 l 61 1940.7 62 1321.6 63 1290.4 64 1319.3 65 1289.9 66 1289.9 67 1143.1 68 1141.7 69 1142.4 70 1139.8 71 113*.9 72 1133.9 73 983.67 74 987.24 75 989.01 76 1020.4 77 1107 3 78 1130.6 80 998.84 >g 81 443.71 82 776.98 83 813.51 84 977.76 85 438.72 bc 86 814.40 87 846.82 88 919.an 89 360.26 90 931.89 L3 03 91 964.59 92 578.50 93 281.33 94 1117.6 95 1176.5 j d3 96 695.84 97 265.63 98 1129.2 99 1212.1 100 782.80 4 b4 M 101 991.46 102 1132.1 103 1226.2 104 817.18 105 1009.2 h$ 106 1140.2 107 1224.3 In8 939.62 109 942.79 110 935.51 111 930.83 112 924.67 115 936.91 114 939.00 115 930.50 116 929.24 !!7 924.79 118 421 37 119 364.9R 120 550.70 121 554.49 122 670.16 123 592.17 124 485.22 125 348.22 i 126 346.93 127 662.81 128 684.C4 129 550.46 130 341.96 131 342.84 132 713.42 133 1027.2 134 787.92 135 800.65 136 798.62 137 760.17 138 1244 6 139 882.26 140 840.51 141 836 19 142 872.42 145 1070.0 146 1052.3 147 1052 1 148 1047.4 149 1045.4 150 1044.7 151 1044.5 152 1106 8 153 1090.6 154 1085.4 155 1074.3 156 1057.1 157 1055.4 158 1044.4 159 1055 1 160 1055.0 1 161 1021.2 162 1021 2 163 985.66 164 988.68 165 993.14 166 993.09 167 9n9.20 168 985.58 169 988.63 170 992.97 171 992.91 172 989.02 173 988.95 174 989.00 175 1042.6 176 1042.6 177 1027.0 178 1026.8 179 1022.9 180 1020.4 181 999.21 182 998.84 183 977.08 184 977 72 185 953.44 186 949.16 187 948.66 188 946.18 190 626.47 191 919.27 195 945.93 194 948.59 195 949.31 } 196 1107.0 197 1091.0 198 1985.2 199 1075.1 200 1144.6 201 1131 8 202 1191 3 203 1190.6 205 1475.0 Max!PUM TEMPERATURE: 1551.9 AT N00E 53 MINIMUM TEMPERATURE: 224.52 AT NODE 17 6
O O O SENTINEL 5-5 RTG1H00EING MELT (TRAN5SP) 23.5831 85/ 8/15 CP: 13.825 ..... TEPPERATURE SOLUTION..... TIPF z .20000r-01 LOAD STEP: 2 ITERATION: 4 CUM. ITER.= 5 NODE TEMP hODE TEMP N0DL TEMP NODE TEMP NODE TEMP 1 348.53 2 44f.08 3 523.18 4 607.67 5 971.61 6 1189.3 7 1372.4 8 340.27 9 422.88 to 526.38 11 603.16 12 960.92 13 1228.6 14 1333.3 15 321.77 16 280.55 17 237 13 18 358 17 19 279.60 20 1296.4 21 1353.5 22 317.48 23 273.61 24 239.84 25 418.10 26 288.99 27 1284.8 28 1342.0 29 1065 1 30 1047.6 - 31 1043.0 32 805.02 33 334.75 34 1149.2 35 1170.8 l 36 1067.1 37 1046.2 38 1042.7 39 1026.8 40 1123.4 41 1106.7 42 1107.6 43 1102.9 44 1044.2 45 1167.0 46 1155.9 47 1128.1 48 1166.4 49 1169.6 50 1169.0 51 1193.6 52 1191 7 53 1554.9 54 1425.7 55 1268.0 56 1265.2 57 1153.4 58 1151 0 59 1014.7 60 1513.5 61 1439.8 62 1321.9 63 1290.2 64 1319.5 65 1289.7 66 1289.7 67 1143 1 68 1141.6 69 1142.2 73 1139.7 71 1134.9 72 1130.9 73 9R3.69 74 987.31 75 989.06 76 1020.5 77 1107.4 78 1130.6 80 998.84 81 445.25 82 960.52 83 992.36 84 977.72 85 440.26 h 86 1001.8 87 1031.3 88 919.16 89 362 10 90 1120.0 CJ 91 1148.0 92 766.86 93 2m3.75 94 1279.4 95 1317.2 U2 d6 96 869.93 97 272.16 98 1287.9 99 1341 5 100 956.36 G3 I'$ 101 1166.5 102 1286.7 103 1351 1 104 989.55 105 1179.6 @{ 106 1291 1 107 1349.7 108 941.30 109 943.66 110 936.35 til 931.68 112 925.25 115 939.18 114 940.05 115 931.63 116 930.17 117 925.32 118 547.75 119 451.34 120 555.20 121 558.17 122 690.48 123 752 13 124 615.90 125 355.62 126 354.36 127 846.60 128 850.24 129 699.24 130 367.56 131 367.57 132 687.19 133 1114.1 114 928.55 135 950.50 136 ?51.49 137 924.78 138 1303.2 139 1025.4 140 989.29 141 986.72 142 1023.0 145 1070.1 146 1052.3 147 1052.1 148 1047.5 149 1045.4 150 1044.7 151 1044.5 152 1106.8 153 1090.7 154 1085.4 155 1074.4 156 1057.0 157 1055.4 158 1044.4 159 1055.1 160 1055.0 161 1021.4 162 1021.4 163 985.67 164 988.75 165 993.le 166 993.09 167 989.25 168 985.59 169 988.70 170 992.97 171 992.91 172 989.07 173 989.00 174 989.05 175 1042.6 176 1042.6 177 1027.0 178 1026.8 179 1022.9 180 1020.5 4 181 999.27 182 99h.84 183 977.14 184 977.68 185 953.78 186 949.63 187 949 14 188 947.17 190 814.18 191 919.60 193 946.94 194 999.12 195 949.48 196 1107.0 197 1091 1 19H 1085.2 199 1075.2 200 1144.3 201 1131.8 202 1192.8 203 1190.2 205 1975.0 i MAXIMUM TEMPERATURE: 1554.9 AT N0DE 53 MINIMUM TEMPERATURE: 237.13 AT h0DE 17 t I i
F) C. n v $[NTINEL 5-S kTG1 HOUSING MELT tTRAN5SM) 23.5881 85/ 8/15 CP: 15.826 ..... TEMPERATURE SOLUTION..... TIPE : .30000E-01 LOAD SirP: 3 ITERATION: 1 CUM. ITER.: 6 NODE TLMP NODE TEMP N00E TLPP NODE TEMP NODE TEMP 1 th7.29 2 626.32 3 729.29 4 824.97 5 1179.9 6 1333.6 7 1932.4 8 472.97 9 600.45 10 733.20 11 819.55 12 1173.5 13 1359.3 14 1919.4 15 448.16 16 363.01 17 280.25 18 363.83 19 268.97 20 1418.3 21 1436.1 22 441 85 23 351 49 24 284.70 25 418.37 26 293.0R 27 1416.3 28 1936.3 29 1065.1 30 1047.7 31 1043.0 32 805.05 33 339.25 34 1367.9 35 1375.3 36 1067 1 37 1046.3 38 1042.7 39 1026.8 40 1123.4 41 1106.9 42 1107 7 43 1103.2 44 1044.2 43 1167.7 46 1155.7 47 1128.0 48 1167.7 49 1169.1 50 1168.6 51 1196.0 52 1191.1 53 1560.5 54 1424.2 55 1267.2 j 56 1264.4 57 1152.6 58 1150.2 59 1014.8 60 1518.7 61 1438.4 62 1322 6 63 12R9.7 64 1320 1 65 1289.2 66 12h9.2 67 1143.1 68 1141.3 69 1141 8 70 1139.6 71 1134.7 72 1130.8 73 9R3.86 74 987.46 75 989.18 76 1020.6 77 1107.5 78 1130.5 80 998.91 >3 81 449.54 82 1223.9 81 1246.9 84 977.72 85 444.63 P2 86 1262.2 87 1279.6 88 919.66 89 367.02 90 1345.6 ca T3 91 1360.5 92 1973.7 93 2R9.75 94 1428.3 95 1437.7 8 L3 96 1153.4 97 288.57 98 1431.2 99 1445.6 100 1199.9 $[$3 101 1357.4 102 1425.9 103 1448.6 104 1224.8 105 1362.4 cn 106 1925.7 107 1447.9 108 945.34 109 945.80 110 938.50 111 933.88 112 926.89 113 944.61 114 942.56 115 934.54 116 932.60 117 926.84 118 828.96 119 665.01 120 569.78 121 570.41 122 741.23 123 1005.5 124 867.34 125 378.96 126 377.66 127 1122.0 128 1057.3 129 932.01 130 427.59 131 426.02 132 1144.2 133 1216.4 134 1136.9 135 1165.5 136 1170.0 137 1163.5 138 1360.9 139 1216.8 140 1195.9 141 1196.5 142 1228.5 145 1070.1 146 1052.3 147 1052 1 148 1047.5 149 1045.4 150 1044.7 151 1044.6 152 1106.8 153 1090.8 154 1085.5 155 1074.5 156 1057.1 157 1055.4 158 1044.5 159 1055.1 160 1055.0 161 1021.6 162 1021 5 163 9H5.82 164 9RR.91 165 993.22 166 993.17 167 989.37 168 9AS.74 169 988.86 170 993.05 171 992.99 172 989.20 173 9H9.13 174 989.18 175 1042.7 176 1042.7 177 1027.1 178 1026.n 179 1023.0 180 1020.6 IP1 999.38 182 998.91 183 977.33 184 977.68 185 954.74 186 950.89 187 950.51 1R8 949.66 190 1103.6 191 920.62 193 949.49 194 950.52 195 950.75 196 1106.9 197 1991.2 198 10P5.5 199 1075.3 200 1144.5 201 1131.7 202 1195.0 203 1189.6 205 1475.0 MA31 MUM TEMPERATURE: 1560.5 AT N0DE 53 MINIMUM TEMPERATUNE: 280.25 AT N000 17 l i 1
i )
3. G. 7 Temperature Distributions -Hypothetical Accident Thermal Environment on Shield /Fael Capsule Assembly The data sheets included in this appendix provides the detailed temperature j
distributions as a result of the transielt thermal ana'ysis (ANSYS model) for tne 30 l minute fire and the post fire cooldown period for the shield / fuel capsule configuration (as reported in Section 3. 5. 3.2 ). 4 Sheets labeled " Sentinel SS % 30 minute fire on bare shield" are for the 30 minute fire period. Times (in hours) on these sheets are relative to the beginning of the 30 minute period. Sheets labeled " Sentinel SS RTG: Post-Fire Cooldown" are for the post fire periods. Times (in hours) are relative to the beginning of the cooldown period. Node numbers on the sheets correspond to the node numbers of Figures 3. 9, 3.10 and 3.11. Temperatures are in units of *F. Node number 135 represents the fire (fixed at 1475'F for the 30 minute period) l or ambient condition for the post fire period (fixed at 100*F. ) I O } 1 l I l l !O TES-3205 l 3-45
. _ - -.. ~. -. . _. _~ -..,. ~. N 1 SENT1hEL 5-S RTG % 30-MIN. FIRE ON fARL SHIELD-SARP (FIRf5SFD 18.6P03 85/ 7/ 2 CP: 6.608 3 ..... TEMPERATURE SOLUTION * *** TIMr = .50060E-u? LOAD STEP: 2 ITERATION: 1 CUM. ITER.: 2 h00E TIMP NODE TEMP N00E TfND N000 TFMP NODE TEMP 1 1092.8 2 1091.6 3 1105 7 4 1090.0 5 10A6 2 6 1085.6 7 10A5.6 H 1117.6 9 1124.9 10 1132.4 11 1092.2 12 1091.6 13 1104.4 14 1090.0 15 1086.0 16 1085.3 17 I L I.S.2 18 1117.4 19 1119.7 20 1125 0 21 1070.0 22 1057.2 23 1057 1 24 1054.4 25 1054 2 26 1054.2 27 1054.2 2e 1053.1 29 1052.9 30 1052.6 31 1069.5 32 10t5.3 33 1055.0 34 1050.3 35 1049.9 36 1849.8 37 1049.8 38 1051.6 39 1052.1 40 1052.6 41 1071.9 42 1055.9 43 1055.8 44 1049 1 45 1047.7 46 1047.1 47 1047.0 48 1112.8 49 1096.3 50 1092.5 51 1070.6 52 1050.9 53 1046.9 54 1046.9 55 1112.9 56 1096.6 57 1092.2 58 1071.4 59 1048.8 64 1048.7 61 1046.6 62 1141.5 63 1132.0 64 1127.9 65 1161.6 66 1171.1 67 1170.6 68 11M6.8 69 1143.6 70 1546.2 71 1929.2 72 1268.1 73 1265.7 74 1154.6 75 1152 8 "3 76 1024.2 77 1024.1 78 1015.1 79 1506.0 80 1444.0 h! 81 1320.1 82 1290.3 83 1318.2 84 1290.C 85 1290 1 63 e 86 1192.6 87 1141 6 88 1142.5 89 1139.( 90 1134.9 d6 $$ 91 1131.1 92 992.33 93 995.62 94 993.19 95 993.12 C3 ca 96 989.83 97 992.26 98 995.54 99 993 16 100 993.10 C' 101 989.64 102 983.95 103 987.02 104 989.49 105 989.57 106 989.58 107 1123.8 108 1107.4 109 1107.9 110 1102.9 111 1163.2 112 1157.6 113 1186.3 114 1191.9 115 1030.6 116 1078.0 117 1078.0 118 1031 2 119 1073.7 120 1074.2 121 1903.6 122 1053.9 123 1054.4 124 9A2.49 125 1022.9 126 1023.3 127 959.54 128 970.55 129 971.08 130 950.58 131 999.74 132 950.06 133 1107.9 134 1130.9 135 1475.0 MAXIMUM TEMPERATURE: 1546.2 AT NODE 70 MINIMUM TEMPERATURE: 949.74 AT N0DE 131 l
O t O i ] SENTINEL 5-5 RTG % 30-MIN. FIFE ON EART SHirLU-SAMP (F IRf 5%F ) 1H.6819 85/ 7/ 2 CP: 7.496 i ..... T[mFERATURE SOLUTION Tier .30000F-01 LOAN STCP: 2 ITERATION: 2 CUM. ITIR.: 3 NODE TFMP NODE TE*P ADDE TFFP N000 TEMP NCOE TEPP 1 1105.8 2 1111.4 3 1125.0 4 1106.9 5 1103.2 6 1102.6 7 1102.6 H 1148.7 9 1155.5 10 1162.4 11 1103.2 12 1111.3 13 1123.7 14 1106.9 15 1103.0 16 1102.3 17 1102.1 18 114P.5 19 1150.6 20 1155.4 21 1076.3 22 1064.6 23 1064.6 24 1064.1 25 1064.2 26 1064 3 27 1064.3 28 1066.4 29 1066.2 30 1066.0 31 1074.6 32 1059.9 33 1054.8 34 1056.6 35 1056.4 36 1056.4 37 1056.4 38 1061.5 39 1061.9 40 1062.5 41 107b.1 42 1061.0 43 1060.9 44 1054.6 45 1053.3 46 1052.6 47 1052.6 48 1135.4 49 1899.1 50 1095.7 51 1074 1 52 1056 1 53 1052.5 54 1052.5 55 1116.0 56 1099.4 57 1095.5 58 1074.8 59 1n54 2 60 1054 1 61 1052.2 62 1142.5 63 1152.4 64 112R.2 65 1103.0 66 1171.9 67 1171.4 68 1189.0 69 1193.5 70 1549.0 71 1929.6 72 1267.5 73 1265.1 74 1154.2 75 1152.5 hf 76 1023.3 77 1023.2 7M 1017.6 79 1510.0 80 1495 2 c3 U2 61 1319.3 82 12H9.8 e5 1317.3 84 1289.6 85 1289.8 86 1142.0 87 1141.2 88 1142.1 89 1139.1 90 1134.7 g $$ 91 1131.1 92 994.10 93 998.2R 94 996.24 95 996.16 C) 96 991.39 97 994.03 98 998 19 99 996.19 100 996 11 101 991.17 102 984.35 103 987.96 104 990.97 105 991.08 106 991.10 107 1126.0 108 1104.1 109 1109.4 110 1104.2 4 1 111 1164.1 112 1158.7 113 1188.3 114 1191.9 115 1037.1 116 1100.4 117 1100.4 118 1042.5 119 1098.5 120 1099 1 121 1010.7 122 1075.4 123 1075.9 124 990.68 125 1041.5 126 1041.9 127 968.4R 128 979.84 129 980.36 130 954.33 131 953.28 132 953.62 133 1109.6 134 1131 3 135 1975.0 i MAX 1PUM TEMPERATURE: 1549.0 AT NODE 70 MINIMUM TEMPERATURE: 953.28 AT NODE 131 i s 1 3 l l )
~ - -, -..-. - N SENTIhEL 5-5 RTG 1 30-MIN. FIRL OR FARF SHI( LD - SAPP (F IRE 5SF) 18.6R33 R5/ 7/ 2 CP: 8.380 ....* TEMPERATURL SOLUTION..... TIME z .15000E-01 LOAD STEP: 2 ITERATION: 3 [UM. ITER.= 4 NCOE TEMP N00E Tr*P NODE Tr*F N000 TEPP NOCE TEMP 1 1107.9 2 1120.3 3 1153.7 4 1115.5 5 till.P 6 1111 2 7 1111.2 8 1160.4 9 1167.1 10 1174.1 11 1107.4 12 1120.2 13 1132.4 14 1115.5 15 1111.6 16 1110.9 17 1110.7 le 1160.2 19 1162.3 20 1167 1 21 1082.4 22 1072.4 23 1072.5 24 1072.9 25 1073.1 26 1073.2 27 1073.2 28 1077.2 29 1077.0 30 1076.9 31 1080.7 32 1066.8 33 1066.7 34 1064.4 35 1064.4 36 1064.4 57 1069.4 38 1970.h 39 1071 2 40 1071 6 41 1082.0 42 1067.6 43 1967.5 44 1062.1 45 1060.8 46 1060.3 47 1060.2 48 1118.9 49 1101.8 50 1098.7 51 1079.0 52 1063 1 53 1060.0 54 1060.0 55 1119.0 56 1102 1 57 1098.5 58 1079.6 59 1061 4 60 1061 4 61 1059.7 62 1144.0 63 1153.2 64 1129.0 65 1164.7 66 1172.4 67 1171.9 68 1191.1 69 1193.5 70 1552.0 71 1929.9 72 1267.0 73 1264.6 74 1153.9 75 1152 1 76 1026.6 77 1026.5 78 In21.4 79 1514.1 80 1446.4 81 1318.6 82 1289.4 83 1316.6 84 1289.3 85 1289.4 86 1141.5 87 1140 8 88 114I.R 89 1138.6 90 1134.6 ,g pq 91 1131 1 92 994.84 93 999.94 94 998.64 95 998.77 La u) 96 993.87 97 994.77 98 999.86 99 998.79 100 998.71 j, da 101 993.63 102 985.36 103 9P9.86 104 993.38 105 993.52 a, b3 106 993.55 107 1128.5 108 1111.0 109 1111.2 110 1106.0 ES 111 1165 6 112 1159.4 113 1190.3 114 1192.1 115 1044.7 116 1109.6 117 1109.6 118 1053.0 119 1109.8 120 1110.5 121 1918.0 122 1083.6 123 1084.1 124 999.09 125 1050.3 126 1050.7 127 977.76 128 988.50 129 989.00 130 958.75 131 958.10 132 95R.45 133 1111.5 134 1132.1 135 1475.0 MARIMUM TEMPERATURE: 1552.0 AT NODE 70 MIh! MUM TEMPERATURE: 958.10 AT h00L 131 t r e
_ _. = ~ - - - - -... - . -. - _ ~. _. -. - ~. ~ O O SENTINEL 5-5 R TG % 30-4tN. FIRE
f. N Papr shirtL-SARP tFIpr.srs 18.6850 85/ 7/ 2 CPz 9.266
..... T(MPLPATUNE SOLUTIGN..... TIPE = .20000[-01 LCAD STEPr 2 ITFRATION: 4 CUM. ITER.= 5 NOCE TEMP N00[ TEMP NODE TIMP NODE TEMP NODE TEMP 1 1112.9 2 1127.1 3 1140.4 4 1122.7 5 1119.1 1 b 1118.5 7 111M.5 8 1167.6 9 1174.2 10 1181.2 11 1112.4 12 1127.0 13 1139.1 14 1122.7 15 111R.9 4 16 111e.2 17 111R.0 18 1167.4 19 1169.4 20 1174.2 21 1088.4 22 10ho.2 23 1080.3 24 1081.0 25 10h1.2 26 1001.3 27 10Mt.3 28 1086.1 29 In85.9 30 1965.7 i 31 1087.1 32 tc74.4 33 1074.3 34 1072.5 35 1072.5 36 1072.5 37 1072.5 3R 1079.4 39 1079.8 to 1080 2 41 1068.2 42 1074.9 43 1074.9 44 1070.1 45 1068.9 46 1068.4 47 1068.3 48 1122.1 49 1104.9 50 1102 3 51 1084.4 52 1070.7 53 1068.1 54 106P.1 55 1122 2 56 1105.1 57 1101 9 58 10P4.9 59 1069.3 60 1069.2 61 1067.8 62 1145.M 63 1134.2 64 1130.0 65 1166.6 66 1172.9 67 1172.4 68 1193.1 69 1193.8 70 1555.1 71 1430.2 72 1266.6 73 1264.2 74 1153.7 75 1151.R 76 1031.3 77 1031.2 78 1026.2 79 1518.1 80 1447.6 81 1318.1 R2 12e9.1 P3 1316.1 R4 1289.0 85 1289.1 >g 86 1141.1 A7 1140.5 88 1191 5 89 1138.1 90 1134.4 g3 bc 91 1131 0 92 996.30 93 1002 2 94 1001 8 95 1001 7 U2 96 997.13 97 996.23 98 1002.1 99 1001.n 100 1001 7 i j, d as *a 101 996.87 102 987.07 103 992.57 104 996 59 105 996.75 lu6 996.79 107 1130.6 108 1113.0 109 1113.2 110 1108.2 i b! 111 1167.3 112 1160.1 113 1192.3 114 1192.3 115 1052.4 116 1116.1 117 1116.2 118 1061 3 119 1117.6 120 1118.2 121 1025.0 122 1089.5 123 1090.0 124 1007.0 125 1057.2 126 1057.6 127 986.76 128 997.33 129 997.84 150 963.57 4 131 963.04 132 963.40 133 1113.5 134 1153.1 135 1975.0 l l MARIMUM TEMPERATURE: 1555.1 AT N0Dr 70 [ MINIMUM TEMPER A TURE : 963.04 AT NODE 131 I I l 1 i I l i i
C O gggyIgLt 5 5 RTC % 3 0
1 '>. FIRf (N F APF 5H1f LD. S AMP (F IRif fII
..... 7 FPER ATUpt SOLUT1oN..... T1*r - .50000E-01 LOAD ST[": 3 ITERATION: t F* 1 re 6 000 TfPp NODE TI MP hn F t,, 0l
0 5
1133 0 e 3 l llIJj? w lins.s 10 1195 0 1 19 3 13 11e1,9 14 1136 4 15 1132.8 l l;f if 185d 0 la 1179.7 19 11st.7 20 1186.3 b 21 110.~ 9 22 1095 1 23 1995.2 24 1096.2 25 1096.4 26 1096 5 27 1640.5 28 1101 6 29 1101.4 30 1101.2 31 1099.5 32 1069 4 13 10t9.7 34 1088.0 35 1088.0 36 106R.C 37 10PR.0 34 1094.9 39 1095.3 40 1095.7 41 1100.5 42 1089.5 43 1089.5 44 1985.5 45 1084.3 4b ICs3.9 47 10 :. 3.h 48 112P.R 49 1111.5 50 1109.4
1 1095.3 52 1065.4 53 1083 6 54 1083.7 55 112e.8 56 1111.7 57 1109.3 SR 1n9%.6 59 1084.3 60 1064.3 (1
10a3.3 62 1149.9 63 1156.M 64 1132.7 65 1170.7 '66 1174.3 A7 1173.9 68 1147.1 69 1194.7 70 1561.1 71 1930.9 72 1266.3 73 1265.M 74 1153.6 75 1151.6 76 Icel.M 77 1041 7 78 1037 2 79 1525.9 80 1449.9 M1 1117.7 62 1269.8 83 1315.7 R4 1<88.6 85 1288.7 P6 1140.3 P7 1140.0 88 1141.2 89 1137.3 90 1134.2 g, 91 1131.0 52 1001.3 93 1008.6 94 1009.4 95 1009.3 e g 96 1005.2 97 1001.2 98 1008.6 99 1009 3 100 1009.2 jg a; 101 1004.9 102 992.47 1n3 999.61 104 1004.6 105 1004.6 I$ 106 1004.8 107 1135.6 1C8 1117.8 109 1117.9 110 1113.4 CD . D' 111 1171.0 112 lift.A 113 1196.2 114 1193.3 115 1067.0 116 1128.6 117 112M.7 118 1076.4 119 1130.5 120 1131.1 121 1037.7 122 1100.4 123 1100.9 124 102).O 125 1c69.9 126 1070.3 127 1CO3.4 128 1013.7 129 In14.2 130 974 07 131 973.60 132 973.97 153 111P.2 134 1135.7 135 1475.0 MAX 1mUp TEMPERATURC: 1561.1 AT NODE 70 MINIPUM TLPPERATURE: 973.60 AT NGOL 131 . f\\ -n
[ [ rh l O Y SENTINCL 5-s gir. t 5t "IN. F1Rt GN FARE SelfLC-SA*P (f IF ['!I l IM.fF81 A5/ 7/ ? CF: 11.415 Time = 400C00-11 LnAO sitt= 3 ITEkATION: ? CUM. ITER.: 7 ..... TfmprnaTUFE TrLU11rN NOEE TEMP Nbor fr*P NOCE TFwP MODr TF*p N000 ifMP 1 113%.7 ? 11S?.6 3 1165.1 4 1149.2 5 1145.9 6 1145.3 7 1145.4 8 1891 0 9 1157.2 10 1203.7 l 11 1136.2 12 1152.* 13 11h'.9 14 1149.? 15 1145.7 16 1145.1 17 1144.9 18 1190.e 19 1192.7 20 1197.? ?! 1115.2 22 11u9.1 23 110".? 24 1110.7 25 1110.4 26 1110.5 27 1110.5 28 111'. 4 29 1115.2 30 1115.1 31 1111 7 32 1163.4 33 1103.? .i t 1102.1 35 1102.1 36 1102.2 37 1102.2 3h 1109.0 39 1109.3 40 1109.7 41 1112 4 42 1103.? 43 1105.; 44 1099.6 45 1096.5 46 105h.C 47 1097.9 4R 1835.5 49 11th.6 50 1117.0 51 110%.M S2 1098.9 53 Id97.P S4 1047.R 55 1135.6 56 1114.7 57 1116.9
8 1105.1 59 109P.1 60 1098.1 61 1L97.5 67 1154.6 63 1140.1 64 1136.1 65 1175.1 66 1176.4 67 1175.9 68 1201.?
69 1196.2 70 1567.0 71 1431.5 72 12f6.4 73 1263.9 74 1154.0 75 1151 9 i T f. 10*2.9 77 10%2.9 78 Inte.h 79 1533.0 80 1451.9 >3 81 131N.n 82 1218.7 (3 131*.9 84 1288.6 M5 1288.6 D1 86 1139.n H7 1139.H MR 1141.1 A9 1136.M 90 1134.1 j3 y2 91 1131.2 92 100M.3 43 1016.7 94 101P.2 95 101R.2 C] ca 96 1614.5 97 10C8.2 98 1n16.7 99 101H.? 10C In18.1 b3 101 1014.2 102 gag,9e 103 1000.5 104 1013.R 105 1014.1 [$ 106 1014.1 107 1140.9 108 1173.2 109 1123.2 110 1119.4 111 1175.1 112 1164.? 113 1200.2 114 1194.9 115 1080.4 116 1140.1 117 1140.2 11H 10P9.0 119 1141.6 120 1142.? 121 1049.5 122 1110.6 123 1111 1 124 10 5 3.F. 125 1CA1.4 126 1081.H 127 1018.5 12h 102M.5 179 1029.0 130 9P5.28 131 984.kB 137 985.26 133 1123.6 134 1139.1 135 1975.0 MAXIMUM ILPPERATURL: 1567.0 AT NODE 79 Mlo!PUM TEMrERATUAL-984.96 AT N000 131 l f a M.
-. ~ _~_ $j \\ ( i g ~ ,,/ SENTIP;EL-S-S RTG 2 St-91N. F1GL O P. PART SH1[LC-SARP 8FIRIfI IU*6h?4 H5/ 7/ 2 CP= 12.296 e' a f s ITrRAT1oN= 5-CUP. 11EP.: 8 e n 2 3 33 4, t t >PIR $ Ti[C SELuficre..... TIPr = .S(On0E-01 LOAD STIF: k00C'~ jgg ;{ ,y littsp 1 117h.3 4 1161.1 ICMP 400( TIMP A0DE TEPp NODE TFMP f NODE TEPP g 5 1157.8 6 ll4 g4 f ligf,$ 8 1r01 4 9 1207.3 /- 10 1213.6 11 1147 6 12 1164.2 15 117%.1 14 1161.0 15 1157.7 16 1157 1 17 1156.9 le 1201.2 19 1203.n 20 1207.4 21 1125.0 22 1121.9 23 1122.0 24 1123.1 25 1123.3 / 2h 1123 4 27 1123 4 28 1128.2 29 1128.0 30 1127.8 31 1123.3 32 t i li.. I 33 1116.1 34 1135.1 35 1115 1 ^ y 36 1115 1 37 1115.1 3h 1121.P 39 1122.2 to 1122.6 41 1123.R 42 1115.* 43 1115.9 44 1112.4 45 1111.* 46 1110.9 47 1110.9 48 1142.4 49 1125.8 50 1124.7 51 1115 9 52 1111 3 53 1110.6 54~ 1110.7 55 1142.4 56 1125.9 57 1124.6 58 1116.1 59 1110.7 60 1110.7 61 1110.4 62 1159 7 65 1143.9 64 1140.1 65 1179.8 66 1179.0 67 11FP.6 6A 1205.4 69 1198.3 70 1572.6 71 1432 2 72 126F.9 73 1264.4 74 1154.9 75 1152.7 76 1064 1 77 1064.1 76 1062.4 79 1539.7 80 1453.7 81 1318.6 82 12bH.H 83 1316.5 h4 1288.6 85 1288.8 h 86 1139.6 87 1139.9 M8 1141.3 A9 1136.6 90 1134.4 La U2 91 1131 5 92 1016.7 93 1025.H 94 1027.8 95 1027.8 8 96 1024.5 97 1016.6 98 In25.7 99 1027.R 100 1027.8 l$ I! 101 1024.2 102 1008.9 103 101P.4 104 1023.R 105 1024.1 - gj 106 1024 1 107 1146.5 108 1129.1 109 1129 1 110 1125.7 111 1179.5 112 1167.2 113 1204.5 114 1197.0 115 1092.7 116 1151.0 117 1151 1 118 1100.8 119 1151.9 120 1152.5 121 1060.2 122 1120.3 123 1120.8 124 1045.2 125 1092.1 126 1092 4 127 1032.2 128 1042.1 129 1042.6 130 996.a8 131 996.51 132 996.88 133 1129.S 134 1143.0 135 1475.0 Pax 1pum TEMPERATURE: 1572.6 AT A00E 70 M141 MUM TEMPER A f t:RF: 99E.51 AT N00r 131 1 h
- - - - ' - - ' - ~ S EP.T I AF L 5-5 R T s *. 3 n-M i t., r t R L c t, IAhr ShifLL-SAEP triptr$rt 18.t914 e5/ 7/ 2 CPz 13.599 TEMPLR470kr SOLUT10N.*... Tirt = .1060fE+20 LOAD STEF: 4 ITTPATION: 1 CUP. ITER.= 9 AOCE T[*P NOUE Tt *P 600[ TrPP NnDF TFPP NnDE , TEMP 1 1195 3 2 1210.6 5 1221.0 4 1208.3 5 1205.6 6 1205 2 7 120%.2 8 1242.6 9 1247.7 10 1253.1 11 1194 8 12 1210.6 13 122c.D 14 120P.3 15 1205.4 16 1204.9 17 1204.F 18 1242.4 19 1244.0 20 1247.7 21 1174.8 22 1174.2 23 1174 3 24 1175.4 25 1175 6 26 1175.7 27 1175.7 2h 1190.0 29 1179.8 30 1179.6 31 1172.7 32 lif8.7 33 1168.6 34 1167.9 35 1168.0 36 1168.0 37 1158.0 38 1174 2 39 1174.5 40 1174.8 41 1172 5 42 1167.8 43 1167.h 44 1165 2 45 1164.2 46 1163 9 47 1163.8 48 1175.P 49 1161.4 50 1161.7 51 1160.6 52 11(2.7 53 1163.6 54 11f3.7 55 1175.9 56 1161'.4 57 1161.F 58 1150 5 59 1162.9 60 1162.9 61 1163.5 62 1187.7 (3 11A7.7 64 1164.0 65 1206.0 66 1197.6 67 1197.3 68 122%.b 69 1215.1 70 1598.9 71 1437.5 72 1274.u 73 1271 4 74 1165.2 75 1162.9 76 1115.2 77 1115.1 78 1113.3 79 1567 5 PO 1962.3 81 1325.2 F2 1293.2 P3 1323.3 84 1292.9 85 1792.9 86 1142.3 87 114 4. f. P8 114 f. 9 R9 1140.1 90 1139.5 h 91 1137.0 92 1063.P 93 1973.3 94 1076.9 95 1076.9 ja U2 96 1075.3 97 1063.7 98 1079.2 99 1076.9 100 1076.9 cm 8 101 1075.0 102 1858.9 103 1069.2 104 1974.6 105 1074.9 O' 106 1074.9 107 1175.P IL6 1160.5 109 1160.4 110 1158.9 $j til 1204.9 112 1187.6 113 1228.9 114 1214.0 115 1145.4 l' 116 1196.2 117 1156.3 11R 1152.0 119 1196.2 120 1196.7 121 1110.4 122 1163.H 123 1164.? 124 1057.7 125 1139.1 126 1139.4 127 1090.3 12H In99.0 129 1099.4 130 1053.8 131 1t53.5 132 1053.H 133 1160.6 134 1166.8 135 1975.0 MANIMUM liMPERATbRE: 1598.9 AT N300 in MINIMUM TEMPERATUNE: 1053.5 AT NODE 131 -~
O SENT1hEL 5-S RTG % 30-MIN. FINE ON bAR[ SHIELD = SARP EFIPI55FI IP.6928 P5/ 7/ 2 CP: 14.4R4 ..... TEMPERATURE SOLUTION..... TIPE : .I'000 LOAD STIP: 4 lir#ATION: 2 EUM. ITER.: 10 NODE Tf"P NODE f t PP NOEE Tr"P NODE TFMP NODE TEMP 1 1231 5 2 124t.4 3 1254.5 4 1243.7 5 1241.5 h 1241.0 7 1241.0 8 1273.5 9 1277.9 10 12P2 6 11 1231.1 12 1248.4 13 1253.6 14 1243.7 15 1241.2 16 1240.P 17 1240.7 IP 1273.3 19 1274.7 20 1277.9 21 1213.2 22 1213.6 23 1213.7 24 1214.P 25 1215.0 Pb 1215 1 27 1213.1 28 121H.9 29 1218.P 30 1218.6 31 1211.1 32 1200.5 33 120N.4 34 1200.0 35 120H.1 36 120H.1 37 12C8.1 38 1213.8 39 1214.1 40 1214.3 41 1210.6 42 1207.4 43 1207.4 44 1205.5 45 1204.7 46 1204.3 47 1204.2 48 1207.2 49 1194 6 50 1195.5 51 1198.0 52 1202.7 53 1204.0 54 1204.1 55 1207.2 56 1194.5 57 1195.6 Se 1197.6 59 1203 1 60 12C3 1 61 1203.H 62 1217 1 63 1194.6 64 1191 0 65 1234.5 66 1221.6 67 1221.1 68 1257.0 69 1237.9 70 1623.1 71 1446.1 72 12A7.0 73 12P4.5 74 1182.5 75 1180.2 76 1158.8 77 1158.8 78 115M.1 79 1589 0 80 1971.1 81 1335.5 82 1302.5 H3 1333.3 P4 1302 1 85 1301 8 86 1151.4 87 1155.6 N8 1158.9 89 1150.0 90 1150.0
3 91 1148.3 92 1110.5 93 111P.P 94 1123 2 95 1123.1 33 h!
96 1122.8 97 1110.4 98 111M.h 99 1123.1 100 1123.1 i 101 1122.5 102 1107.9 103 1117.2 104 1122.2 105 1122.4 gg $$ 106 1122.4 107 1205.4 102 1191 9 109 1191 8 110 1191 3 111 1232.7 112 1212.6 111 1250.1 114 1236.9 115 1187.6 116 1232.2 117 1232.3 11H 1193.5 119 1252 1 120 1232.6 121 1154.6 122 1201.8 123 1202.2 124 1143.2 125 1179.9 126 1180.2 127 1137.8 128 1145.5 129 1145.8 130 1105.2 131 1105.0 132 1105.3 133 1192 2 134 1193.7 135 1975.0 MAXIPUM TEMPERATURE: 1623.1 AT N000 70 MINIMUM TEMPERATURE: 1105.0 AT NODE 131 A
O SLNT1hEL 5-5 RTG t 30-MIN. F IRE ON 6ARr SHIFLD-5ARP GFIRf5SF) 18.6942 85/ 7/ 2 CP: 15.375 .... TEMPERATURE SOLUTION..... TIME : .20000 LOAD STEP: 4 ITEPATION: 3 CUM. ITER.= 11 60DE TEMP WODE TEMP AOLE TEMP NODE Tr*P N000 TEMP 1 1261.6 2 1274.3 3 1282.4 4 1273.0 5 1271.0 6 1270.7 7 1270.7 R 1249.2 9 1303.2 10 1307.4 11 1261.3 12 1274 2 13 1201.6 14 1271.0 15 1270.8 16 1270.5 17 1270.4 18 1299.1 19 1300.3 20 1303.2 21 1245.0 22 1245.9 23 1245.9 24 1247.0 25 1247.2 26 1247.3 27 1247.5 2A 1250.6 29 1250.7 30 1250.6 31 1242.h 32 1241.2 33 1241.1 34 1241.0 35 1241.0 36 1241.1 37 1241 1 38 1246.3 39 1246.6 40 1246.8 41 1242.3 42 1240.0 43 1240.0 44 1238.6 45 1238.0 46 123F.7 47 1237.6 48 1236.7 49 1225.2 Sn 1226.3 51 1230.4 52 1235.9 53 1237.4 54 1237.5 55 1236.7 56 1225.1 57 1226.4 58 1230.2 59 1236.4 60 1236.5 61 1237.3 62 1246.1 63 1222 2 64 121R.5 65 1263.1 66 1247.2 67 1246.H 68 I?>4.9 69 1263.2 70 1646.0 71 145H.0 72 1303.9 73 1301 5 74 1203.9 75 1201.8 76 1196.8 77 1196.8 78 1196.8 79 1607.0 80 1481.5 el 1348.7 82 1315.8 P3 1346.6 84 1315.3 85 1314.8 Ab 116b.0 87 1171.8 88 1176.0 89 1165.3 90 1167.1 pg 91 1164.4 92 1153.1 93 1160.5 94 1164.9 95 1164.9 pq 96 1165.4 97 1153.1 98 1160.3 99 1164.9 100 1164.9 j' 03 101 1165.2 102 11'2.2 103 1160.4 104 1164.9 105 1165.1 ci da 106 1165.1 107 1234.3 108 1221.8 109 1221.7 110 1221.8 b' 111 1260.9 112 1239.1 113 12H4 1 114 1262 2 115 1723 1 b 116 1263.C 117 1263.1 118 1228.5 119 1263.0 120 1263.* 121 1193.8 122 1236.1 123 1236.5 124 1183.8 125 1216.R ) 126 1217.0 127 1179.2 128 1186.2 129 1186.5 130 1150.8 131 1150.6 132 1150.9 133 1222 1 ,134 1221.3 135 1475.0 MARIMUM TEMPERATURr= 1646.0 AT NODE 70 MINIPUM IEMPERATURE: 1150.6 AT NODE 131 n-
.. _ ~ -. -. O ( t SE AT INFL* S-S P TG t 30-h1A. FIPL O f4 F APr SHlf L9-SARP (Fthr'9F) 18.7000 RS/ 7/ 2 CP: 18.936 ..... IFFFERATUer SCLui10N..... TIME : .40000 LOAD STFf: 4 ITERATIOh: 7 Cit M. 1Tra.= 15 h0DI T[FP N0ct frMP NODE TIPP N000 Tf rP N000 TEMP 1 1350.1 2 135.7.6 3 13 f.2. 6 4 1357.2 5 1356.0 6 13 f.5. 8 7 13 5 5. t-H 1372.7 9 1375.2 13 1377.7 11 1349.9 12 13t7.6 13 1962 1 14 1357.2 15 1355.9 16 1355.7 17 13'.S.6 In 1372.7 19 1373.4 20 1375 2 21 1339.4 .22 1340.1 ?3 1340.2 24 1340.9 25 1341 1 26 1341.1 27 1341.1 28 1.*43.3 29 1343.3 30 1343.2 31 133H.1 32 1337.1 33 1337.1 34 1337.1 35 1337 2 J6 1337.2 37 1337.2 38 1340.7 39 1340.8 40 1341 0 41 1337.8 42 1336.4 43 1336.4 44 1335.7 45 1355.4 46 1355.2 47 1335.2 4R 1336.7 49 1326.4 50 1327 3 51 1330.6 52 1334.1 53 113f.0 54 1335 1 55 1336.7 56 1326.4 57 1327.3 58 1330.5 59 1334.4 60 1334.5 61 1334.9 62 134P.0 63 1323.7 64 1320.0 65 1365 2 66 1346.5 67 1346.0 66 1 3 P(.. ? 69 1362 3 70 1734.3 71 152H.0 72 1368.7 73 13P6.6 74 1301.3 75 1299.6 76 1309.8 77 1309.9 78 1310.5 79 1674.0 80 1541.9 81 1422.5 e2 1392.5 83 1420.6 84 1391.6 65 1390.7 86 1254.P H7 1263.1 NH 126H.3 89 1255.3 90 1258 7 91 1255.7 92 12H2.3 93 1286.6 94 1290.6 95 1290.6 "3 96 1292.4 97 12F2.3 98 12h6.6 99 1290 6 100 1290.6 d,h! to 101 1292.2 102 1283.9 103 12P9.2 104 1292 1 105 1292 2 g 106 1292.2 107 1335 5 108 1324.2 109 1324 2 110 1324 6 C) no 111 1362.2 112 1339.7 113 1385.5 114 1361.4 11b 1326 7 o 116 1351.5 117 1351.6 11H 133b.2 119 1351.5 120 1351.7 121 1310.0 122 1336.4 123 15 3f.6 124 1304.9 125 1325.6 126 1325.7 127 1302.9 128 1307.4 129 1307.6 130 1285 2 131 1285.2 132 1285.4 133 1324.5 134 1322.R 135 1475 9 MAF1PUM TEPPERATURE: 1734.3 AT NODE 70 M1ft1 MUM TEMPERATURE: 1254.8 AT NODE 86
_m. --...._m. A s \\ i l SENi ttiLL S-S RTG % 30-MIN. FIR [ n f. 6ARE %HITLD-SADP (FIRf5SF3 18.7017 PL/ 7/ 2 CP: 19.831 ..... TLMPLPATURE SOLUTION..... ilmf : .45000 LOAD STFP: 4 ITERATION = H r im. ITER.: 16 kont TE*P NODE TEPP h00E TfhP hCOE TEPF N C r?. TEMP 1 1367.0 2 1375.2 3 13F7.6 4 1372.8 1371 7 6 1371.6 7 1371.6 8 13Pf.3 9 13HH.4 10 1390.6 11 1366.8 12 1373.1 13 1377.1 14 1372.R it 1371 7 16 1371.5 17 1371.4 18 13P6.2 19 13H6.8 20 138R.4 21 1357.6 22 1357.9 23 1357.9 24 1358.5 25 13 S A. 6_,. 26 155h.7 27 135R.7 28 1360.6 29 1360.5 30 1360.4 31 1356.5 32 1355.3 33 1355.3 34 1395.2 35 1355.2 36 1355.3 37 1355.3 Se 1356.2 39 135e.4 40 1358.5 41 1356.4 42 1354.7 43 1354.7 44 1354 0 45 1353.6 46 1353.5 47 1353.4 en 1357.6 49 1347.4 50 1347.9 51 1350.3 52 13S2.6 53 1353.5 54 13S3.4 5S 1357.7 56 1347.3 57 1348.0 58 1350.2 59 1352.9 60 1352.9 61 1353.2 62 13t9.8 63 1346.0 64 1342.3 65 1387.2 66 1369.0 67 136H.4 68 1408.3 69 1384.9 70 1756.4 f 71 1$48.2 72 1910.9 73 1408.R 14 1324.9 75 1323.3 ji 76 1330.9 77 1330.9 78 1331.4 79 1692.1 80 1569.3 J 81 1443.8 82 1914.0 83 1442.0 84 1413.4 85 1412.4 >3 86 1279.6 87 12F7.7 68 1292.8 89 1280.1 90 1283.5 os bd 91 1280 5 92 1306.4 93 1310 2 94 1313..s 95 1313.P f, T3 S6 1315.4 97 1306.4 98 1310.2 99 1313.8 106 1313.8 -a G3 101 1315.3 102 1308.0 103 1312 6 104 1315.2 105 1315.3 106 1315.3 107 1357.1 108 1345.P' 109 1345.H 110 1346.0 j i ca 111 1384.2 112 1362.2 113 1907.6 114 13P3.9 115 1345.8 4 116 1367.6 117 1367.6 118 1348.H 119 1367.5 120 1367.7 l 121 1331.0 122 1354.5 123 13$4.5 124 1326.7 125 1344.9 126 1345.1 127 13?5.1 128 1329.1 129 1329.3 130 1309.5 131 1309.5 132 1309.6 133 1346.1 134 1345 1 135 1475.0 MAXIMUM TEM PE 8 4 TURE: 1756.4 AT NODF 70 MINIMUM TLMPERATURE: 1279.6 AT NODE B6 l l i
m. O h 7 k, SENTINEL
-S RTG 1 3h-MIN. F IRE 06 FARL SHITLD-SARP (FINE!5F) 18.7031 85/ 7/ 2 EP=
20.716 ..... T E MP E R t. T UR L S 6LtlT I O N..... TIPE = .50000 LOAD !TIP= 4 ITERATION: 9 EUM. ITER.= 17 60CE TE MP N000 TINP NODE TE4P N00E TE MP NODE TEMP 1 13h2.2 2 1317.1 3 1391.0 4 13A6.M 5 1385.A 6 1385.7 7 1385.7 8 139H.4 9 1900.2 10 1902.2 11 13P2.0 12 13H7.1 13 1390.6 14 19R6.H 15 1385.8 16 1385.6 17 1385.6 1H 1*98.3 19 139P.9 20 1400.2 21 1374.0 22 13F3.h 23 1373.9 24 1374.3 25 1374.4 26 1374.4 27 1374.4 28 1376.0 29 1376 0 30 1375 9" 31 1373.2 32 1371.6 33 1371.6 34 1371.4 35 1371.4 36 1371.4 37 1371.5 38 1374.0 39 1374 1 40 1374 2 41 1373.3 42 1371.2 43 1371.2 44 1370.3 45 1370.0 46 1369.8 47 1369.8 48 1377.1 49 1366 7 50 1367.0 51 136M.1 52 1364.3 53 1369.7 54 1369 8 55 1377 2 56 1366.7 57 13#7.0 58 136h.1 59 1369.4 60 1369.4 El 1369.f 62 1390.2 63 1367.0 64 1363 5 65 1407.8 06 1390.3 67 13F9.8 68 1929.1 69 1406.4 70 1778.5 71 156H.5 72 1932.7 73 1430.7 74 1347.6 75 1346.0 in 1349.6 77 1349.6 78 1349.9 79 1710.A 80 1579 3 81 1965.5 82 1435.8 H3 1463.7 84 1435 1 PS 1434 2 P6 1304.1 87 1311.P P8 191(.P A9 1304.5 90 1307.7 "3 91 1304.7 92 1327.8 93 1351.2 94 1334.3 95 1334.3 f,h! 63 96 1335.8 97 1327.9 98 1331.2 99 1334.3 100 1334 3 f, 101 1335.7 102 1329.3 103 1333.4 104 1335.6 105 1335.7 op ha 106 1335.7 107 1377.3 108 1365.9 109 1365.9 110 1365.9 111 1404.9 112 1363.5 113 142h.4 114 1405.4 115 1362.0 116 1381.9 117 13P1.9 118 1365.3 119 1381 7 120 1381.9 121 1349.5 122 1370.1 123 1370.2 124 1345.8 125 1361 9 126 1362.0 127 1344.6 128 1348,1 129 1348 5 130 1330.8 131 1330.8 132 1330.9 133 1366.5 134 1366.1 135 1475.0 max 1 MUM TEMPERATURE: 1778.5 AT NOCE 70 MINIMUM TEMPERATURE = 1304.1 AT NODE 66 e h
. = - _ -.. l SENTIAEL 5-S RTG'1 POST-FIRE C00LDowN (E00LSSc3 19.6550 85/ 7/ 8 CP: 5.923 .e... TEPPERATUhE SOLUTION...*. TINF : O. LOAD Sifr= 1 ITERATION: 1 CUP. ITER.: 1 N00[ TEMP t'0 0 L Tl 4P ADDE TEFP NODE TEMP NODE TFMP 1 13P3.0 2 13 P. 7. 0 3 1341.n 4 13P7.0 5 1385 0 6 1366.0 7 13F6.0 8 1 3 ') P. 0 9 1400.0 10 1402.0 11 1302.0 12 13h7.0 13 1391.0 14 1387.0 15 1386 0 16 1386.0 17 138(.0 18 1396.0 19 1399.0 20 1900.0 21 1174.0 22 1374.0 23 1374.0 24 1374.0 25 1374.0 26 1374.0 27 1374.0 28 1376.0 29 1376.0 30 1376.0 31 1373.0 32 1372.0 33 1372.n 34 1371.0 35 1371.0 36 1371.0 37 1372.0 38 1374.0 39 1374.0 to 1374 0 41 1373.0 42 1371.0 43 1371.0 44 1370.0 45 1370.0 46 1370.0 47 1370.0 48 1377.0 49 1367.0 50 1367.0 j 51 1368.0 52 1369.0 53 1370.0 54 1370.0 55 1377.0 56 1367.0 57 1367.0 58 13#4 0 59 1369.0 60 1369.0 61 1370.0 62 1390.0
f. 3 1367.0 64 1364 0 65 1408 0 66 1390.0 67 1390.0 68 1429.0 69 1406.0 70 1779.0 71 1569.0 72 1453.0 73 1431.0 74 1348.0 75 1346.0 76 1350.0 77 1350.0 78 13%0.0 79 1711.0 80 1579.0 81 1966.0 82 1436 0 83 1464.0 84 1935.0 85 1455.0 86 1304.0 H7 1312.0 88 1317.0 89 1309.0 90 1308.0 F3 91 1305.0 92 1320.0 93 1331 0 94 1334.0 95 1334.0 DU 96 1356.0 97 1328.0 98 1331.0 99 1334.0 100 1334.0 f
101 1336.0 102 1329.0 103 1333 0 104 1330.0 105 1336.0 L8 Es gj 106 1536.0 107 1377 0 108 13F6.0 109 1366.0 110 1366.0 43 o 111 1405.0 112 1366.0 113 192P.0 114 1405.0 115 1363.0 C" 116 1382.0 117 13P2.0 118 1365.0 119 1382.0 120 1382.0 121 1350.0 122 1370.0 123 1370.0 124 1346.0 125 1362.0 126 1362.0 127 1345.0 128 1348.0 129 1348.0 130 1331.0 131 1331 0 132 1331.0 133 1366.0 134 1366.0 135 100.00 MANIMUM TEMPERATURE: 1779.0 AT NODE 70 MINIMUM TEMPERATURE: 100.00 AT NODE 135 i i
7___________________________ lL) U (J SENTINil 5-5 FIG : POST-Flpt C00LOOWA (C00L5SC) 19.6575 RS/ 7/ 8 EP= 7 2}] ..... TLMPrd7TUR(. SCLUTION..... TIME = .100u00 00 LOAD STrf= ? ITERATION: 1 CUM. ITER.= 2 ACDE T[*P NOCL f t wP ADDE TEMP N000 TrMP
000 TEMP 1
1240.1 2 1198.5 3 1182.1 4 1200.3 5 1204.5 6 1205.1 7 1205.1 H 1135.1 9 1126.5 10 1117.4 11 1240.P 12 1198.( 13 1163.7 14 1200 3 15 1204.7 16 1205.5 17 12ns.7 18 1135.4 19 1132.R 20 1126.5 21 1271.5 22 1254 5 23 1254 2 24 1248.9 25 1248 1 26 1247.H 27 1247.8 28 1237.6 29 1237.8 30 1237.9 31 127h.0 32 1263.R 33 1263.6 34 1257.8 35 1257 1 16 1256.9 37 1256.8 38 1244.3 39 1243.9 40 1243 5 41 1241.4 42 1267 2 43 1267.0 44 1260 1 45 1259 3 46 1259.0 47 1259.0 48 133a.0 49 1322 6 50 1317 5 51 1290.9 52 1265 2 53 1259.1 54 1259.0 55 1339.1 56 1323.0 SF 1317.2 58 1291.9 59 1262.7 60 1262.5 61 1259.1 62 1376 1 63 1355.1 64 1350 3 65 1400 1 66 13PH.4 67 1387.A t,8 1926.7 69 1408.4 70 1803.6 71 15H9.4 72 1947.6 73 1445.5 74 1353.5 75 1352 4 76 1273 1 77 1273.1 7H 126h.7 79 1734.3 80 1601.2 81 14HR.6 N2 1456.2 P3 1486.5 P4 1955.7 85 1454.9 pg H6 1323.2 87 1327.8 P8 1331.1 89 1322.A 90 1322.7 p3 91 1319.0 92 1287.8 93 12P4.0 94 127P.7 95 1278.7 63 02 96 1276.H 97 12 8 7.R 98 12P4.0 99 1278.7 100 1278 7 f3 d3 101 1276.9 102 12A5.7 103 1280.3 104 1277.1 105 1276.9 c) h3 106 1276.9 107 1355.3 108 1338.7 109 1339.3 110 1335 3 El 111 1397.4 112 1379 0 113 1425.R 114 1407.1 115 1251.8 116 1170 1 117 1170.0 119 1234.0 119 1160.4 120 1159.5 121 1250.3 122 1872 8 123 1172.2 124 1246.R 125 1189 5 126 1188.9 127 1248.5 128 1236.3 129 1235.7 130 1274.4 131 1275.4 132 1275.0 133 1339.5 134 1353.9 135 100.00 MAXIMUM TEMPERATURE: 1803.6 AT NODE 70 MINIMUM TEMPERATURE: 100.00 AT NODE 135 ^-
i r\\ ] SEATINEL 5-5 R1G 1 POST-F1RE COUL006M (EOUL5SC) 19.6594 95/ 7/ 8 CP= H.127 j ..... T[ MPE R ATilR E 90LUT10N *.*.. T I ME = .200u0 LOAD SifP= 2 liEFATION= 2 CUM. ITER.= 3 NOUE TrwP NOCE TfMP fl0DE TEPP NODE TI MP NODE TE9A 1 1154.9 2 1123.0 3 1110.5 4 1117.5 5 1119.8 6 1119.9 7 1119.8 8 10H2.4 9 1076.4 10 1070.2 11 1155.5 12 1123.1 13 1111.7 14 1117.6 15 1120.0 4 16 1120.2 17 1120.3 1R 1082.5 19 IGRO.R 20 1076.4 21 1185.2 22 1162.1 23 11F1.R 24 1156.0 25 1155.2 ?6 115d.0 27 1154.9 2A 1 14 f>. 6 29 1146.7 30 1146.9 31 1192.8 32 1170.5 33 1170.2 34 1163.2 35 1162.5 i 36 1162.3 37 1162.2 in 1150.1 39 1149.7 40 1149.4 41 1197.7 42 1175.3 43 1175.0 44 1165.6 45 1164.4 i j 46 1164.0 47 1163.9 4R 12A9.6 49 1267.1 50 1259.0 51 1216.2 52 1173.9 53 1164.0 54 1163.9 55 1289.9 56 1267.8 57 1258.5 58 1217.8 59 1169.6 60 1169.3 01 1163.9 62 1340.2
f. 3 1321.9 64 1316.4 65 1369.2 66 1365.4 67 13 e,4. 9 68 1401.1 69 1389.0 70 1828.5 71 I f. 0 3. h 72 1450.0 73 1447.8 74 1341.5 75 1340.7 76 1184.7 77 1184.6 78 117f.5 79 1759.1 80 1620.7 81 1506.4 H2 1968.7 b3 1505.9 64 1468.5 85 1968.2 kg 86 132R.7 67 1329.1 88
!?30.4 89 1325.8 90 1323.2 b1 91 1319.2 92 1213.3 93 1207.' 94 1197.5 95 1197.4 j3 U2 96 1191.9 97 1213.2 98 1207.2 99 1197.5 100 1197.4 05 d3 101 1192.0 102 1206 1 103 1197 1 104 1192.3 105 1192.1 106 1192.1 107 1314.7 108 1292.2 109 1292.9 110 1285 6 b 111 1367.5 112 1352.9 113 1400.0 114 1387.6 115 1157.4 116 1095.0 117 1094.9 118 1142.7 119 10H8.2 120 10R7.6 121 1161.6 7 22 1101.5 123 1101.0 124 1158.6 125 1113.2 126 1112.H .t 2 7 1155.8 128 1145.6 129 1145.1 130 1190.4 131 1190.8 1 52 1190.4 133 1292.9 1 34 1320.4 135 100.00 MAXIMUM TEMPERATURE: 1828.5 AT NODE 70 4 MINIMUM TLMPERATURE: 100.00 AT N000 135 i t 4 r i ___m_
O O O SENTIAEL 5-S NTG 1 POST-FIRI C00LDukN (COOLSSC) 19.6614 85/ 7/ R CP: 9.054 e.*** TLkPERATURE SCLUTION **... TIPE : .30000 LOAD STFP: 2 ITERATION: 3 CUM. ITER.: 4 ADDE T!*P Norf TFMP NODE TFPP N0nr Tr=P N000 TE1P 1 1096.6 2 1061.0 3 10%0.7 4 1057.7 5 1059.7 6 l 'J 6 0. 0 7 1059.9 H 1021.1 9 1016.2 to 1010.9 11 1097.0 12 1061.0 13 1051.6 14 1057.7 15 10%9.9 16 1060.2 17 106D.3 18 1021.3 19 1019.7 20 1016 1 21 1120.7 22 1094 6 23 1094.3 24 10H8.3 25 1087.6 26 1087.3 27 10e7 3 2P 1079.0 29 1079 1 30 1079 2 ] 31 1128.4 32 1102.4 33 1102.1 34 1094.3 35 1093.6 1 36 1n93.3 37 1093 2 38 1082.2 39 1081.9 to 1081 7 '{ 41 1134.0 42 1107.6 43 1107.? 44 1096.4 45 1094.9 46 1094.4 47 1094.3 48 1240.7 49 1214.5 50 1205.2 i 51 1155.0 52 1105.8 53 1094.4 54 1094.3 55 1241.0 56 1215.2 57 1204 6 58 1156.9 59 1100.A 60 1100.4 1 61 1094.2 62 1246.2 63 1280.0 64 1274.3 65 1327.3 66 1330.1 67 1329.6 (6 1362.2 69 1355.5 70 1M43.2 71 1604.1 72 1437 2 73 1934.7 74 1314.8 75 1313.8 76 110R.5 77 110A.4 7A I f'9 7.9 79 1775.1 80 1628 1 81 1510.3 62 14(.6 2 N3 1507.4 P4 1466.2 85 1966.3 86 1315.h 67 1312.6 ha 1312.2 89 1311.3 90 1306 1 "3 91 1302.0 92 1134.7 93 1130.0 94 1118.3 95 1118 1 h! 1 96 1110.0 97 1134.7 98 112a.9 99 111R.2 100 111R.1 g3 e 101 1110.1 102 1123 1 103 1114.P 104 1110.3 105 1110 2 i Ej $$ 106 1110.1 107 126A.9 108 1?42.7 109 1243.4 110 1234 1 111 1326.7 112 1315.1 113 1361.0 114 1353.9 115 10R4.0 116 1030.5 117 1030.5 118 1070.4 119 1023.8 120 1023.3 121 1084.2 122 1033.0 123 1032.6 124 1081.0 125 1042.5 126 1G42.2 127 1077.4 128 1069.1 129 1068.7 130 1107.2 i l 131 1107.2 132 1106.9 133 1243.4 134 1278.5 135 100.00 4 MAXIMUM TEMPERATURE: 1H43.2 AT NODE 70 PINIMUM TEMPERATURE: 100.00 AT NODE 135 t 4 e
O% O O i l SEN11NEL 5-S NTG 1 PCST-F14E C00LD09N tc00L5cc) 19.6631 P5/ 7/ R CP: 9.9R0 1 4 1 ..*.* TEPPERATURL SOLUTION..... TIME : 40000 LOAD STFI': 2 I TE R A T 106= 4 CtlM. ITfR.: 5 i 6CDE TEMP N O C f. TL"P NODE TFFF NonE TEPP h0DE TEMP 1 1999.1 2 1013.6 3 1004.6 4 1009.9 5 1011.6 j 6 1011.h 7 1011.7 8 977.13 9 972.83 10 968.23 j 11 1049.9 12 1013.7 13 1005 4 14 1009.9 15 1011 7 lb 1r12.0 17 1012.0 1H 977.27 19 975.41 20 972.7P 21 1070.4 22 1042.F 23 1042 4 24 1036.4 25 1035.7 j 26 1035.4 27 1035.3 28 1027.4 29 1027.5 30 1027.6 31 1078.0 32 1050.0 33 1049.6 34 1041.4 35 1040.6 36 1040.3 37 1040.2 38 102a.h 39 1029.6 40 1029.4 41 10e3.7 42 1U55.3 43 1054.9 44 1043 1 45 1041.3 46 1040.F 47 1040.6 48 1195.7 49 1167.5 50 1157.9 1 51 1104.5 52 1052.6 53 1040.7 54 1040.6 55 1196.0 56 116R.3 57 1157.2 58 1106.5 59 1047.2 60 1046.9 61 1040.4 62 1252.6 63 1237.5 64 1231.8 65 1284.5 i 66 1291.1 67 1290.6 68 1320.4 69 1317 3 70 1P44.9 71 1591.3 72 1413.7 73 1411.0 74 1280.4 75 1279.2 76 1046.1 77 1046.0 78 1054.3 79 1778.7 80 1622.4 81 1500.4 P2 1950.4 83 1997.1 84 1450.6 85 1451.2 86 1289.2 87 12P3.8 88 1282.5 89 1283.5 90 1276.8 H 91 1272.9 92 1065.6 93 1062.4 44 1050.0 95 1949 8 M g, 96 1040.2 97 1065.5 9H 1062.3 99 1049.9 100 1049.8 Co 4 i 101 1040.2 102 1051.2 103 1044.2 104 1040.4 105 1040.2 [ E) $3 106 1040.2 107 1224.7 108 1196.4 109 1197.1 110 1186.9 $3 111 1284 5 112 1274.6 113 1319.5 114 1315.7 115 1026 1 4 On 116 979 13 117 979.09 118 1012.R 119 971.66 120 971.19 2 121 1019.4 122 975.07 123 974.72 124 1014.8 125 981.58 i 126 981 31 127 1011.0 128 1003.9 129 1005.6 130 1035.0 131 1935.1 132 1034.9 133 1197.2 134 1236.0 135 100.00 3 MAXIMUM TEMPERATURf: 1H44.9 AT NOOL 70 MINIMUM TEMPERATURE: 100.00 AT NODE 133 9 i 1 ? 4 4 i e i
- _ _ _ _ -. ~.. - - - - - ~ ~/ ] i SENT1hEL 5-S RTG : POST-rIRf C00LOOVN (C00L5SC) 19.6650 RS/ 7/ P CP: 10.915 i } ..... TEMPEH 7TURE SOLUTICH..... TIME : .50000 LOAD siffa ? ITERATION: 5 CUM. ITER.: 6 .j NCD[ 7EMP NODE TCPP NODE TEMP NonE-TEMP NODE TEMP j 1 100H.2 2 974.4H 3 9f5.iH 4 969.66 5 971 14 ] 6 971.?6 7 971.24 8 939.24 9 935.40 10 931.P9 11 1009.2 12 973.49 13 466.13 14 964.6A 15 971.25 16 971 44 17 971.51 le 939.37 19 938.15 20 935.36 21 1027.9 22 999.42 23 999 13 24
93.05 25 992 31 26 992.0A 27 992.00 PR 984.26 29 9H4.35 30 984.40 31 1035.3 32 1006.1 33 1005.h 14 997.22 35 996.38 J
3h 996.12 17 996.07 38 9H6.07 39 985.M7 40 985.76 41 1041.0 42 1011.4 43 1011.1 44 998.61 45 996.66 46 995.97 47 995.e4 4e 1154.H 49 1125.6 50 1115.R 51 1061.2 52 100R.0 53 995.90 54 995.80 55 1155.1 56 1126.3 57 1115.2 5A 1063.2 59 1002.5 60 1002.2 61 995.Sh 62 1212.1 63 1197.? 64 1191.3 65 1244.3 66 1252.6 67 1252.1 68 12A1.% 69 1279 1 70 1R34.9 1 71 1569.6 72 13F4.2 73 1381.4 74 1243 5 75 1242.1 76 994.26 77 994.16 78 981 94 79 1770.8 80 1606.6 3 81 1483.3 82 1426.1 P3 1976.7 84 1926.4 85 1427.1 pg 86 1255.2 87 124R.9 P8 1247.? A9 124R.9 90 1241.5 4 as by 91 1237.5 92 1067.5 93 1005.4 94 997.87 95 992.69 I D2 96 982.27 97 1007.4 98 1005 2 99 992.79 100 992.60 32d3 101 962 27 102 991.51 103 965.70 104 9AP.42 105 9P2.30 h3 106 982 27 107 1183.8 108 1154.4 109 1155.1 110 1144.3 t l 111 1244.7 112 1235.1 113 1280.1 114 1277.5 115 978.13 116 936.02 117 936.00 118 965.1P 119 928.06 120 927.64 121 965.62 122 976.47 123 926.17 124 959.19 125 930 01 126 929.77 127 954.M7 128 948.73 129 948.41 130 974.7A 131 -974.96 132 974.76 135 1155.? ,134 1195.6 135 100.00 pax!PUM TEMPERATURE: IR34.9 AT NODE 70 MINIMUM TEMPLRATURE= 100.00 AT NODE 135 ) i 1 4 i i ?- 1 I i l t
. - ~. w/ 'd D I SE P!T INE L 5-5 hiG 1 POST-FIRE LobLDOLN (C00L5SE1 19.6669 85/ 7/ 6 CP= 11 845 ..... TL MPIR ATUR E - SOLUTION...*. Tirr = .00000 LO AP Sif r= 2 ITfkATION: 6 CUM. ITIR.= 7 NODE Tt MP NODI TFrP N 0(, E Tr"P NODE TFMP A00E TEMP 1 972.99 2 937.99 3 930.04 4 934.11 5 935.42 6 935.53 7 935.4H 8 905.71 9 902.24 10 898.50 11 973.31 12 a3P.00 13 931 32 14 934.13 1% 935.51 16 935.67 17 935.75 18 9 05.P 3 19 904.71 20 902.19 21 990.27 22 9h1.46 23 961.17 24 955.11 25 954.39 26 954.13 27 954.0P 2h 946.56 29 946.64 30 946.67 31 997.48 32 967.77 33 967.39 54 958.67 35 957.H3 30 98,7.57 37 957.52 38 947.93 39 947.75 40 947.67 41 1003.2 42 972.98 43 972.62 44 959.82 45 957.76 46 957.03 47 956.6N 9P 1117.6 49 10M7.5 50 1077.8 51 1022.9 52 909.13 53 956 93 54 956.84 55 1117.9 b6 1088.3 57 1077.2 58 1024.9 59 963.60 60 963.25 61 956.58 62 1115.0 L3 1159.4 64 1153.4 65 1207.4 66 1215.h 67 1215.3 68 1245.1 69 1242.6 70 1815.7 71 1S42.8 72 1352.3 73 1349 4 74 1206.7 75 1205.2 i 76 950 14 77 950.04 7H 937 66 79 1754.1 80 1584.6 bl 1454.1 82 1397.1 83 1450.3 84 1397.5 85 1398.3 kg 86 121H.5 87 1212 0 BB 1210.3 R9 1211.9 90 1204.4 2 bc 91 1200.3 92 958.b7 93 957.15 94 944.R2 95 944.64 1 96 933.95 97 956.45 98 956.98 99 944.75 103 944.55 g, U2 101 '933.93 102 941 83 103 936.P7 104 934.04 105 933 94 $j[da 3 106 933.92 107 1146.2 108 1115.9 109 1116.6 110 1105.6 I cn 111 1207.9 112 1197.7 113 1243.E 114 1240.9 115 937.06 116 898.70 117 896.69 118 924.46 119 890.49 120 890.11 a 121 920.39 122 68'.22 123 884.95 124 912.45 125 886.?6 126 886 15 127 907.54 128 902 11 129 901.R1 130 924.57 131 924.77 132 924.60 133 1116.7 134 1157.8 135 100.00 MAXIMUM TEMPERATURE: 1815.7 AT N000 70 MININUM TEMPERATURE: 100.00 AT NODE 135 h 1 i w
O 3 j 1 SENTINFL 5-5 RTG 1 POST-FIRL C00tD6EN (C60L5 SCI 19.0736 85/ 7/ 8 CP: 15.555 ..... T L MPt'R A T UR F SOLUTION....* TIMr : 1.0000 LOAD Sifr: ? ITERATIO6: 10 CUM. ITfR.: 11 h0DE Tr"P NODE Tr*p A0rr Trur N0nf TfPP NODE TEMP I 859.44 2 h?6.H5 3 821 4N 4 F23.05 5 P23 90 i 6 n23.96 7 H23.92 H BUO.46 9 797.93 10 795.20 11 859.66 12 826.H6 13 621.97 14 H23.06 15 P23.97 I f. o24.06 17 024.10 la 800.55 19 799.72 20 797.P9 21 671.97 22 843 95 23 M43.6A 24 837.99 25 837.33 26 837.10 27 837.05 28 830.43 29 830.4P 30 830 4R 31 678.41 32 e49.06 33 e48.68 34 R40.15 35 R39.35 96 639.09 37 H39.05 38 e30.82 39 830.70 40 830.68 41 883.78 42 853.83 43 853.47 44 840.77 45 838.60 46 837.h2 47 R37.66 48 995.94 49 964.32 50 955.24 51 902.57 52 849.63 53 H37.67 54 837.60 55 996 25 56 965.08 57 954.57 SR 904.56 59 844.17 60 843.H2 61 837.29 62 1052.4 63 1032.8 64 1026.7 65 1085.1 66 1089.4 67 1088.8 68 1123.1 69 1116.7 70 1697.2 71 1929.1 72 1229.4 73 122(. 5 74 1077.1 75 1075.6 76 821.07 77 820.98 FR HC9.24 79 1653 0 80 14H1.1 8! 1335.6 HP 1277.0 P3 1331.H 8* 1277.4 85 127R.3 >3 H6 10Hk.6 87 1077.5 68 1076 6 89 1076.2 90 1069.6 P1 91 1065.3 92 819.98 93 F19.76 94 H0H.91 95 80H.75 g3 U2 96 798.57 97 N19.86 98 A19.59 99 808.P3 100 808.65 e 101 798.50 102 803 36 103 800.31 104 798.55 105 798.49 $$fj 106 798.48 107 1022.0 108 990.04 109 990.65 110 979.52 g 111 1084.9 112 1070.5 113 1121.6 114 1114.9 115 814.86 116 785.91 117 765 92 118 F03.00 119 777.75 120 777.48 121 791.54 122 765.72 125 765.53 124 781.21 125 762 27 126 762.11 127 775 38 12e 771.51 129 771.30 130 786.23 131 786.43 132 786.32 133 990.e6 134 1031.1 135 100.00 MAX 1"UM TEMPERATURE: 1697.2 AT NODE 7n MINIMUM TEMPERATUNE: 100.00 AT NODE 135 1 1 5 4 4
. -.. = l f f V b d i SENTINEL 5-F R1G 1 POST-FIRE C60LOOWN ( C O O L'.SC ) 14.6006 85/ 7/ P CP= 19.691 ..... TE MPER ATURE SOLUTION..... TIME = 2.0000 LOAD STIP: 3 ITERATION = 4 CUM. ITER.= 15 NOOL TEMP N000 TINP NODE TEPP NODE TEMP NODE TEMP 1 6P7.64 2 660.13 3 656.78 4 656.64 5 657.06 6 657.06 7 h57.03 8 640.08 9 639.31 10 637.61 11 6e7.9e 12 660.14 13 657.08 14 656.65 15 657.10 16 657 12 17 657 14 18 640.93 19 640.41 20 639.28 21 695.66 22 670.h4 23 670.60 24 665.75 25 665.19 26 66b.00 27 664.96 28 659.f6 29 659.69 30 659.67 31 700.98 32 674.59 33 674.25 34 6ff.70 35 666.00 36 665.79 37 665.75 38 659.27 39 659.20 40 659.23 41 705.71 42 67e.58 43 67H.25 44 666.91 45 664.88 46 664.15 47 664.00 48 810.83 49 777.79 50 769.93 51 724.00 52 675 02 53 663.99 54 663.93 55 811.11 Sh 778.46 57 765.28 58 725.H6 59 669.95 60 669.63 61 663.61 62 865.0H 63 837.98 64 A31.75 65 897.63 66 892 05 67 M91 26 68 939.01 69 919.71 70 1943.4 71 1229.9 72 1025.9 75 1023 1 74 872.63 75 871.47 76 642.02 77 641.95 78 632.01 79 1442.0 80 1291.3 81 1823.4 82 1073.3 e5 1119.9 P4 1070.6 85 1071.3 pg 66 866.51 87 Bf4.3H 88 864.95 89 P61 26 90 856.64 g3 N3 91 652 00 92 634 83 93 635.22 94 626.P2 95 626.67 a U2 96 618.22 97 634.72 98 635.0H 99 626.75 100 626.60 C) d3 101 618.13 102 620.45 103 618.58 104 618.14 105 618.11 h3 106 618.11 107 832 41 108 75P.f 2 109 799.16 110 788.50 111 895.73 112 872 90 113 9?3.41 114 917.62 115 641.44 116 622.08 117 622 10 118 632.23 119 614.R9 120 614.72 121 616.21 122 599 31 123 599.19 124 605.62 125 593 30 126 593.20 127 600.00 128 597.51 129 597.38 130 605.86 131 606.01 132 605.95 133 799.47 134 836.08 135 100.00 MAxlMUM 1EMPERATURE: 1443.4 AT NODE 70 MINIMUM TEMPERATURE: 100.00 AT NODE 135 O _.O
R O S E P. T I N E L 5-S RTG 1 PCST-FIRE CLOLO06N (C00L5 SCI 19.7P03 85/ 7/ P CP: 27.052 ..... TEMPERATURE SCLUTION..... TIME = 4.0000 LO AD STF r= 3 ITERAfl0N: 12 CUM. ITER.= 23 NCDE TEMP NODE TEMP NODE TFMP NODE TEMF NODE TEMP 1 553.24 2 529.16 3 527.03 4 525.87 5 526.02 f. 525.98 7 525.96 8 514.*' 9 513.5P to 512.51 11 553.32 12 52'8.17 13 527.21 14 525.R7 15 526.04 16 526.02 17 526.02 18 514.00 19 514.27 20 513.56 21 55R.32 22 53A.00 23 535.P0 24 531.54 25 531.06 26 530.89 27 530.H6 28 526.45 29 526.46 30 526.44 31 562.91 32 538.92 33 53H.62 34 531.85 35 531.24 36 531 05 37 531.02 3R 525.67 39 525.63 40 525.67 41 567.1P 42 542.37 43 542.06 44 531.87 45 529.99 46 529.31 47 529.17 4H 667.32 49 632.A9 50 625.96 51 bh5.15 52 359.44 53 5?9.15 54 529.10 55 667.60 56 633.49 57 625.34 SH SH6.R9 59 534.70 60 534.41 61 526.79 62 720.63 63 886.F5 64 6R0.36 65 753.56 66-739.11 67 736.09 68 790.53 69 767.30 70 1244.5 71 1073.2 72 A65 94 73 P63.30 74 712.35 75 711.49 76 505.06 77 505.01 78 496.54 79 1271.9 80 1142.2 81 953.91 82 906 47 83 950.74 84 906.60 85 907.05 86 (95.94 87 696.41 A8 098.29 89 691.74 90 688.78 >3 91 663.P3 92 494.84 93 4"S.48 94 488.93 95 488.R1 bd 96 4H1.78 97 494 74 48 495.37 99 488.88 100 4P6.75 os 8 U3 101 4H1.66 102 482.54 103 481.97 104 481.66 105 481.65 $$fj 106 461.65 107 685.77 108 650.37 109 650.89 110 640.69 111 750.06 112 719.76 113 788.90 114 764.97 115 507.62 gg 116 494.41 117 494.44 118 499.87 119 4RP.07 120 487.96 121 482.47 122 471.18 123 471 10 124 472.22 125 464.02 126 463.95 127 466.98 128 465.34 129 465.25 130 470.05 131 470.17 132 470.13 133 b51.26 134 684.68 135 100.00 MAXIMUM TEMPE R A TURE: 1271.9 AT N000 79 MINIMUM TEMFERATURE: 100.00 AT NODE 135 A
. ~. 's [ ~ SENilArt 5-5 R1G : Post-F1RE ConLDO.N (COOLESCI 19.7039 85/ 7/ H CP= 29 321 I ..... TLFPERATURL SOLUTION *.... TIME : P.0000 LOAP STft-= 4 I TE R A TION: 2 CUM. ITER.: 25 NOOL TEMP N000 TFMP NODE TEMP N000 ffMP N00f TEPP 1 4th.27 2 462.43 3 4(0.71 4 459 14 5 459.le i t. 459.13 7 459.11 8 449.4% 9 448.(,8 to 447.H4 11 465.33 12 462.43 13 4 8,0. P r. 14 459 14 15 459.20 16 459.16 17 459.16 18 449.48 19 449.?2 20 448.67 21 489.54 22 467.94 23 467.79 24 463.66 25 463.21 26. 463.05 27 463.01 2H 45H.40 29 458.91-30 458.h8 31 493.93 32 470.59 33 470.30 34 465.77 35 463.19 36 463.01 37 462.97 38 457.97 39 457.94 40 457.98 41 99P.10 42 473.87 43 473.57 44 463.75 45 461.90 46 461 23 47 461 10 46 599.57 49 565.03 50 556.34 51 517.14 52 471.39 53 461.0A 54 461.03 55 599.P4 56 503.62 57 555.71 58 51P.H8 59 466.65 60 466.35 61 460.72 62 654.07 65 615.07 64 608.47 65 687.87 (6 667.49 67 666.29 68 72S.12 69 696.61 70 1147.9 71 1b01.1 72 791 12 73 789.60 74 656.39 75 635.79 i 76 435.93 77
35.88 78 4?7.82 79 1189 3 80 1074.0
( HI 676 15 82 H31.04 H3 873.12 M4 831.06 H5 831.37 86 614.75 87 616.45 A8 619.01 R9 610.97 90 608.65 "3 91 603.37 92 424.24 93 425.0F 94 419 18 95 419.06 I' $ 96 412.47 97 424.15 98 424.96 99 419 13 100 419.01 c) 101 412.37 102 412.62 103 412.43 104 412.34 105 412.34 I "' I$ 106 412.34 107 616.79 108 '79 16 109 579.69 110 569.32 o 111 683.25 112 647.53 113' 723.46 114 694.03 115 439.75 U' 116 428.96 117 429.00 118 432.51 119 422.92 120 422.P4 a 121 414 33 122 405.33 123 405.2P 124 404.09 125 397.59 126 397.53 127 398.95 128 397.65 129 397.5A 130 400.H5 131 400.95 132 400.92 133 580.10 134 612.64 135 100.00 i MAXIMUM TEMPERATURI: 1189.3 AT NODF 79 MINIMUM TEMPERATURE: 100.00 AT NODE 135 4 1 1 s 1 1 i
m_. i 2 SENTINEL 5-S hTG 1 POST-FIRE C00LD0m6 (COOLSSC) 19.7075 85/ 7/ 8 CP: 31.136 ..... T[HptkATURL SOLUTION...*. T i r'E : 12.000 LOAD STIF: 4 ITENATION: 4 CUM. ITER.: 27 ^ P.00E TEMP NODE TEPP NnOf IEur NODE TrMP N000 TEMP l 1 477.44 2 454.95 3 453.29 4 451.66 5 451.69 6 451.64 7 451.62 8 442.30 9 441.t7 10 440.77 11 477.50 12 454.93 13 '453.45 14 4 51.f 6 15 451.71 1 16 451.67 17 451 67 le 442.33 19 442.08 20 441.55 21 481.49 22 460.16 23 459.97 24 455.94 25 455.49 26 455.34 27 455.30 28 451.26 29 451.27 30 451.24 1 31 4FS.81 32 462.75 33 462.46 34 456.n2 35 455.44 36 455.26 37 455 23 38 450.31 39 450.2H 40 450.33 1 41 409.92 42 465.99 43 465.69 44 455.96 45 454.15 1 46 453.49 47 453.35 48 589.57 49 5 5 3. f.6 50 547.07 51 508.32 52 463.44 53 453.33 54 453.2R 55 589.84 1 56 554.24 57 546.46 58 510.03 59 458.79 60 458.50 61 452.98 (2 643.41 63 605.07 64 598.52 65 676.95 06 657.11 67 655.94 68 715.97 69 6HS.96 70 1140.4 71 990.24 72 78u.94 73 778.40 74 625.99 75 625.35 76 4 2H.29 77 42F.24 78 420.34 79 1180.6 en 1063.4 l R1 864.33 82 M19.50 83 P61.32 A4 819.53 85 819.H4 gg 86 6C4.11 of 605.91 88 608.49 P9 600.42 90 598.21 g3 pq e U2 91 592.99 92 41F.58 93 417.3h 94 411.64 95 411.52
! da 96
05.07 97 416.50 98 417.24 99 411.59 100 411.47 b3 101 404.97 102 405.16 103 405.01 104 404.94 105 404.94 lS 106 404.94 107 606.68 108 E69.69 109 570.22 110 56E.0R 111 672.43 112 637 39 113 712.31 114 6A3.43 115 432.21 116 421.84 117 421.87 118 425.10 119 415.R9 120 415.81 121 407.01 122 398.34 123 398.29 124 396.P5 125 390.59 j
126 390.53 127 391.74 12R 390.50 129 390.43 130 393.54 j. 131 393.63 132 393.61 133 570.62 134 602.86 135 100.00 s MAPIMUM TEMPERATURE: 1160.6 AT NODE 79 4 l MINIMUM TEMFERATURE: 100.00 AT NODE 135 a i 4 4 l }
--. -. _ ~ _-.. /~N SEr.TI6CL 5-5 kTG 1 POST-FIRE C00100bN (C00L%SC) 19.711, 65/ 7/ d CP= 32.938 TE MPF. A A T UR E SOLUTIOW..... TIME = IP.000 LOAD SitP= 4 ITfpATION: 7 CUM. IffR.: 29 NODE. TEMP NODE TfMP N0f L TEMP NODE TEMP NODr TfPP 1 477.43 2 454.95 3 453.32 4 951.70 5 451.75 6 4 % 1. t.8 7 451.65 8 442.35 9 441.62 10 440.62 11 477.49 12 454.96 13 4 5 3. 4 f. 14 451.70 15 451.75 16 451.71 17 451.70 la 442.5P 19 442.13 20 441.60 21 4H1 47 22 460.17 23 459.98 24 455.96 25 455.51 2 (. 455.36 27 455.33 2R 451.29 79 451.30 30 451.27 31 485.77 32 46?.76 33 4(2.47 34 456 04 35 455.46 36 455.2R 37 455.25 38 450.35 39 450.32 40 450.36 41 489.87 42 465.99 43 465.70 44 455.5A 45 954.17 46 453.51 47 453 3H 44 569.19 49 553.4? 50 546.A5 51 508.15 52 463.43 53 453.36 54 453.31 55 SP9.46 56 553.99 57 540.23 58 809.85 59 45H.79 60 458.50 61 453.00 62 642.89 63 604.73 64 598.20 65 676.34 66 656.71 67 655.54 6A 713.34 69 685.50 70 1140.7 71 9h9.71 72 7R6.47 73 777.P8 74 625.64 75-624.9R 76 42H.57 77 428.32 78 4?O.45 79 1180.5 80 1062.8 el 663.77 82 618.94 H3 P60.76 84 818.97 85 819.28 M6 603.79 87 605.58 P8 608.16 89 600.10 90 597.91 gg , pq 91 592.70 92 416.70 93 417.49 94 411.76 95 411.65 4 e u) 96 405.21 97 416.62 98 417.39 99 411.71 100 411.60 -3 d3 101 405.12 102 405.37 103 405.16 104 405.08 105 405.09 b3 106 405.09 101 606.29 108 569.45 109 569.97 110 559.67 [?: 111 671.e8 112 637.03 113 711.6a 114 6A2.98 115 432.2A 116 421.92 117 421.95 118 425.1P 119 415.9h 120 415.90 121 407.14 122 39A.4A 123 398.42 124 397.00 125 390.75 126 190.69 127 391.91 128 390.66 129 390.59 130 393.72 131 393.81 132 393 79 133 570.37 134 602.54 135 100.00 M4MIPUM TEMPERATURE: 1180.5 AT N00f 19 MINIMUM TEMPERATURE: 100.00 AT NODE 135 i f 1 1
.~. i t G G SENTIhEL 5-S RTG 1 6 0ST-F IRE C00LCOWN (C00LS$09 19.7125 H5/ 7/ R CP: 33.854 ...*. TEMPIRATURE SOLU 110N..... TIPT = 24.000 LOAD SirF: 4 ITERATTON: 10 CUP. ITER.: 30 AOCE TEMP NODE TfwP 400[ Tr"D NODE TEMP N00E TEMP 1 477.59 2 455.11 3 453.4h 4 451.R5 5 451.89 6 451.H3 7 451.P1 8 442 51 9 441.77 10 440.*7 11 477.65 12 455.11 13 453.61 14 451.H6 15 451.90 16 451.H6 17 451.86 1H 442.53 19 442.28 20 441.76 21 4M1.63 22 460.33 23 460.14 24 456.12 25 455.67 26 455.52. 27 455.49 2P 451 44 29 451.46 30 451.43 2 31 465.93 32 462.92 33 4(2.63 34-456.20 35 455.62 36 455.44 37 455.41 38 450.51 39 45n.48 40 450.52 41 490.03 42 466.15 43 465.P6 44 450.14 45 454.33 46 453.67 47 453.54 48 569.29 49 5 'a t. 5 5 50 546.98 51 50P.29 52 463.5H 53 453.52 54 453.47 55 589.56 56 554 13 57 546.37 58 509.99 59 458.95 60 458.66 61 453.17 62 642.96 63 604.66 64 598.33 65 676.39 i 66 656.83 67 655.66 68 713.3H E9 685.60 70 1141.0 71 949.78 72 760.51 79 777.98 74 625.79 75 625.14 76 424.54 77 42P.49 7e 420.62 79 1180.7 80 1062.9 al 863.88 H2 R19.05 83 860.87 84 819.08 85 819.39 86 603.98 87 605.76 M8 60e.34 89 600.29 90 598.09 "3 91 592.HH 92 416.88 93 417.67 94 411.94 95 411.82 h! 96 405.38 97 416.79 98 417.57 99 411.99 100 411.77 os 8 a 101 405.29 102 405.49 103 405.3', 104 405.25 105 405.26 [! h$ 106 405.26 107 606 40 Ina 569 59 109 570.11 110 560.02 CD 111 671.95 112 637.16 113 711.75 114 663.08 115 432.44 116 422.08 117 422.11 11H 425.35 119 416.14 120 416.06 121 407.30 122 398.64 123 598.58 124 397.17 125 390.91 12b 390.d5 127 392.0M 12P 390.b3 129 390.76 130 393.69 i 131 393.98 132 393.96 133 570.51 134 602.67 135 100.00 MAX 1PUM TEPPERATURL: 1160.7 AT NODE 79 MINIMUM TEMPERATURE: 100.00 AT N00E 135 j l e
-_ ~ l 4. CONTAINMENT i For normal conditions of transport and for the hypothetical accident conditions, the stangth member of the fuel capsule assembly is the primary containment. The fuel capsule assembly includes a seal welded liner assembly am! ao! tilly provides double encapsulation of the radioactive material. I 4.1 Containment Boundary he containment boundary is the envelope of the outer capsule or strength member assembly. This containment volume is identified in Figure 1.4. Additional details are provided in Figures 2.1G through 2.19. 4.1.1 Containment Vessel l The design specifications for the Sentinel SS strength member are summarized below: i a. He strength member is, designed to meet all requirements of IAEA Safety Series 33, Appendix I, entitled " Capsule Tests. " nese requirements are defined in Figure 2.12, herein. b. The material used in the strength member housing and end cap is Hastelloy C-276 bar, procured in the solution heat treated condition, meeting the i chemical and physical requirements of ASTM B-574 specification, Machined details of the strength member housings and end caps are sub-c. jected to radiography in accordance with MIL-STD-271D, to detect ma-terial flaws such as voids, cracks or inclusions. i d. Specifications governing the fuel chemistry, fuel quantity, weld quality, weld penetration, surface contamination and leak testing exe defined in TES Drawing 015-800000, " Heat Source Specification -Sentinel SS RTG. " his document is provided as Appendix 4.4.1 of this section. ] I 4.1. 2 Containment Penetrations i I There are no penetrations in either the strength member housing or end cap. i i 4.1.3 Seals and Welds There are two seal welds in the fuel capsule assembly, one to seal the liner l end cap in place after the fbel is installed, and the other is the final seal weld made I on the fuel capsule's, threaded end cap. Both welds are performed by programmed automatic remote welding equipment in a " hot cell" at the Oak Ridge National Labora- . tory. The specification requirements for these welds are identified in the Teledyne Energy System Drawing No. 015-600000 entitled " Heat Source Specification - Sentinel SS " (Appendix 4. 4.1). i l0 i j TES-3205 j 4-1 ,~ ,r, --e.., .,-r + --.-,,--n.,. wn.v-,., ,w.,. ,.,.n --vm~,---,
4.1.4 Closure The closure for the fuel capsule assembly is a seal weld described Jn Section
4. 2 Requirements for Normal Conditions of Transport

4. 2.1 Release of Radioactive Material A heat source assembly identical in every aspect to a fueled Sentinel SS heat source, except that it used a fuel simulant, has been subjected to the tests defined in Figure 2.12 herein. These tests either meet or exceed the environments defined for both normal transport conditions and the hypothetical accident conditions. The tests also meet or exceed "special form" requirments defined in 10 CFR Part 71. The test results (see Figure 2.13) clearly demonstrate radioactive material containment.
One parameter that has not been specifically addressed is the effects of seawater corrosion. If a conservative seawater corrosion rate of 0. 0001 inch per year is used, the . 090 inch minimum weld thickness will provide a capsule seal for approximately 900 years. 'Ibe maximum activity of the capsule, 31,375 curies will decay to a 1cvel of one curie in approximately 430 years. The corrosion resistance of Hastelloy C-276 in seawater is addressed in Appendix 4.4.2 Hydrostatic pressure analysis is provided in Section 2. 8. 6. l 4.2.2 Pressurization of Containment Vessel Not applicable. 4.2.3 Coolant Contamination l Not applicable - there is no coolant in the fuel capsule. 4.2.4 Coolant Loss Not applicable - there is no coolant in the fuel capsule.
4. 3 Containment Requirements for the Hypothetical Accident Conditions See discussion under 4.2

4. 3.1 Fission Gas Products l
Not applicable - no fission gas products available in the containment vessel. !O TES-3205 4-2
4 4.3.2 Release of Contents There will be no release of radioactive material following the hypothetical accident conditions. See Discussion under 4.2.1.
4. 4 Appendix This appendix includes supporting information for Chapter 4.
4.4.1 Dwg 015-800000, " Heat Source Specification, Sentinel SS. " (Bookform draw-ing -18 sheets. ) 4.4.2 Corrosion resistance of Hastelloy alloy C-276 in seawater. l 4 i i l i l I I TES-3205 4-3 l
.~.. -..- V + Q SECURITY UNCL. CONF. SECRET l Rtvislows: su surf arv tivtt REVIEW Di RD GP.12 3 4 IMis
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sun $gy CL ASStFIE R + ?$*.?). kr3 r D .Y f TABLE OF CONTENTS Title Page 1 Revisions 2 Change I.: dex 3 Procedure Index 4 Procedure 5 g %O q'M k l l ~)., ' ' +'; ' NOTE: This drawing releases no parts. Gt >y..
i.s i!5
,3y, ,73y IO-j mm umY um a itsi oAsn yuenvg o,, sb mumste N? APPticAfim OTY Mdb '"'*l E u n 7 W ar SPTELEDYNE ENERGY SYSTEMS """ 8' " *"_ e ; ', W O' '., m #.t..,,:l' c'Jb.. cwacain ,44_ sist ausfi HEAT SOURCE SPECIFICATION univsing/.f.,,/.f). U - SENTINEL 5S RTG suaury % g/ L. 7- $f .u..w s. o- .r A 30s56 OlF-ROODDD esen c 18 w r o w e dsfo %,1-sf-4-scAI dco-851-0Ml surf 1 I or a TES -3205 j 4-4 I f
I newmous $YM PAGE wN DATE APMtOVED i I 1 l l c 30856 A a's-'"aa 2 TES-3205 4-5
v INDEX ggp Qi D@: SHEET REV. SHEET REV. SHEET REV. 5 ett Y s:x.w A l l h k ~s \\
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I 4 5}M ': SIZE CODEIDENT.NO. g Ol-A 30s56 on-s**C REv. ~ SCALE l SHEET 3 m e. a rs ) (J 1 l TES-0205 4-6 l
1 .s_......._._..__...... + l::...
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INDFJ: J:': P_gg_ 1.0 Scope 5 1.1 General 5
j * :.
1.2 Description 5 2.0 Applicable Doceness 6 l 2.1 SpeciScations and *=ndards 6 2.2 Drawings 6 2.3 Fueling Facility Docunents 6 ~
3.0 Requirements 7
3.1 Fuel 7 3.2 Heat Source Components 7 3.3 Heat Source Assembly 8
/
3.4 Welding 10 3.5 Heat Source QualiScation Testing 12 4.0 Quality Assurance Provisions 13 4 4.1 Quality Assurance Program Plan 13 4.2 Testing 14 D 4.3 Non-Compliance Rems 15 4.4 Deliverable Data 15 , ~ *. Appendix A 16 Appendix B - Heat Source Qualineation Test Requirements 17 + SIZE CODE IDENT NO. 055 015-800000 ^- REV 5:::!9 SCALE ' SHEET 4 I ES-211 J k v' TES-3205 4 'T
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1.o 8 COPE
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1.1 General This specification establishes the requirements for the radioisotope fuel and its encapsulation in a heat source assembly for application
,:::::.:l in a SENTINEL 5S thermoelearic generator.
l- .0. :::: 1.2 Descrintion
p*,
The completed heat source assembly consists of the fuelin the form
.; :::(
of hot pressed cylindrical discs sealed within an inner capsule or liner assembly;in turn, sealed within an oder capsule or strength member assembly. The inner capsule or liar serves only as a L;:::0*- compatible lintnr for the fuel and facilitates cosamination control L:...:* sor the subsequem assembly. The outer capsule or strength member I:::: provides the structural integrity and oxidation and corrosion resistance to preved release of the isotope in cpecified accident conditions.
i
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.

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SIZE CODE IDENT NO. i :::: A 30856 ois-sooooo REV SCALE l$HEET 5 is-211 J L I s d TE S-3P C., 4-S 1 l l
..... ~ - -... -. 2.0 APPLICABLE DOCUnfENTS !*.d
(: -
The following doctanents, of the exact issue shown, form a part of this specincation to the extent spec 15ed herein. In the event of
(:,<
oonflict between this speciScation and the documents referenced herein, the requirements of this specincation shall govern. 2.1 Specineations and mamiards - of the issue in effed on the date of . j-{ this speciScation. !!.l. ANIM-B574-83A Stamtard SpeciScation - Inw Carbon Nickel-Molybdenum-Chromitan Alloy Rod Rev. A-1983. IAEA Safety Series No. 33, 'Unide to the Safe Design, Cowtruction and Use of Radioisotopic Power Generators for Certain land and Sea Applications." 1970. MIL-STD-271D, " Nondestructive Testing Requiremeds for Metals." 10/1/63. ,I' 2.2 Drawings - (Teledyne Energy Systems) of the latest issue in effect at time of fuel encapsulation. 015-200000 Heat Source Assembly 015-200001 Ilner Assembly 4 015-200002 Ilner and Shim Detalls 015-200003 Strength Member Detalls I. ': 015-200004 Capsule Handling Knob s 015-200005 Ilner Weld Test Specimens ( 015-200006 Strength Member Weld Test Specimens
f 2.3 Fueling Facility Documents
-( Quality Assurance Program Plan. t i
i:.
c:::.:.:. < SIZE CODE IDENT NO. i:i.:::'i A 30856 013-800000 IIEV .0::* * - SCALE l$HEET 6 is-2n J 6 i 1 m) TES-3205 4-0
/~T U + ' ~.. * -
.;l 3.0 REQUIREMENTS
'N!!.. Each heat source assembly and its componess shall meet the requiremens of this sedion. 3.1 Fuel The basic fuel, for purposes of this specincation, shall be the radioisotope strosium-90. l 3.1.1 Chemleal Form - The fuel shall be in the fluoride form ( SrF I* 2 . I.' 3.1.2 Fuel Composition - The fuel composition, for purposes of this specincation, shall be "SrF as synthesized and stored at the Waste 2 Encapsulatig and Storage Facility (WESF) in Richland, Washington. The WESF SrF is precipitated and subsequently processed from a 2 feed solmion whose composition is given in Appendix A. Fuel from the f, WESF capsules is further densined by hot pressing at the Oak Ridge National laboratory (ORNL) but its composition is unaltered. 3.1.3 Fuel Quantity - The fuelis to be hot pressed into discs with a nominal diameter of 2.577 inches and a density in range of 3.7 ,4.0 g/cc. These discs are loaded into liners to a nominal thermal inventory of 185 watts 15% with the desired loading in the 185-190 watt range. ( The thermal inventory of each liner is to be measured by a calorimeter f ,-l with an accuracy of13% (representing 3 a of a normal distribution). ( ,f - 3.2 Heat Source Components 3.2.1 Liner Components - The liner consists of a tubular housing with an end esp welded on each end. Dda!!s of the liner components are shown on TES Dwg. No. 015-200002. The housing and end caps of the liner are fabricated from 'llastelloy C-276' bar stock procured in the solution .: *l' heat treated condition and certined to AFDi-B574-83A specification. Shim details shown on the drawing are used only to hot press the fuel deses. with one shim on each side of the fuel to prevent the fuel from adhering to the graphite press rams. The shims are fabricated fr'm Hastelloy C-276 sheet to be compatible with the fuel. t SIZE CDDE IDENT ND. it:i::. A 30856 015-800000 nEv SCALE l SHEET 7 c ES-211 J b v TES-3005 4-10
O ':::.( One of the end caps is welded in place at TES prior to shipping the components to the fueling facility. The weld joint is leak tested at
(:::,
ambient temperature and radiographed prior to shipment. The maximum acceptable leak rate is 1 x 10-8 cc/sec-helium at STP. The weld joint is also radiographed in accordance with MIL-STD-271D .f.l 8edion 3 to assure th11 weld fusion. Radiographic quality level specified is 2-27. A matching serialized and cap is provided which .f * : ORNL will weld. 3.2.2 Strength Member Components - The strength member consists of ,*l a thick walled titular housing with one end closure of solid material
( ::,
amehlud as an integral part of the housing and the open end threaded to accept an end cap which is installed and subsequently welded in place at ORNL. Details of the strength member components are shown on TES Dwg. No. 015-200003. The housing and end cap are fabricated from Hastelloy C-276 bar stock procured in the solution best treated condition and certified to ASTM-B574-83A specification. ~ Each housing and end cap are serialized as matched sets. 3.3 Heat Source Assembly The heat source assembly, shown on TES Dwg. No. 015-200000 consists of a sealed liner assembly inserted and sealed within a strength member assembly. Only one such heat source assembly is required for the SENTINEL SS radioisotope thern.oelectric ( generator (RIG). (V designed to contain a thermal inventory of 185 watts (t) at a power l 3.3.1 I1ner Assembly - The internal volume of the liner assembly is density of -0.91 w/cc. This number was derived by taking the average specific power of 0.246 w/g hot pressed to the minimnm expecta! fuel density of 3.7 g/cc. The liner assembly is shown on TES .Dwg. No. 015-200001. i Two hot pressed fuel discs will be inserted into each liner prior to welding the final and cap in place. The thermal inventory of each fuel disc w!!!be determiwd by the fueling facility. Adjustments are to be made Letween fuel discs to arrive at the required heat source inventory. The completed liner assembly is to be
-l subjected to calorimetry measurement to determiw the actual fuel thermal invesory.
After the two fuel discs are inserted in the liner, the end cap is to be installed and welded in place. .: l ElZE CODE IDENT ND. iiiiii::' A 30356 025-8* *o p(::.:. AEV q 6::..- SCALE l$idif 8 ES-211 J b Ov TES-3203 l 4-11 l x-
D + V
.: ( *-
N M E: Each liner and end cap are serialized as " matched sets" and should be used in that manner. The end cap is designed
0:
to ' seat' on a lip machined in the housing to achieve proper

f: <
weld lip mating. The end cap is to Ise ' seated' and tack
:.". (<
welded if required to prevd cocking. There will be a gap between the top fuel dise and the aderside of the end cap in all cases. The exad amount of this gap will depend both onTe total thermal inventory and the actual power density ch*=laad. No shimming is required in this gap. g Welang of the end cap is to be done in accordance with the criteria of Section 3.4. 3.3.2 Strength Member Assembly
Ihe internal volume of h strength member is designed to comain the liner assembly with allowances for tolerances and brmal expansions.
After & liner assembly is insersed in the strength member, the and cap is threaded in place a=4 welded. NME: Each strength me.cl a and end cap are serialized as " matched sets" ana.Muld be used in that manner. The end cap is designed to " seat" on a lip machined in b housing to give the proper weld lip joint. No shimming is required in the gap between the liner top and the end cap underside. Welding is to be done in accordance with ( the criteria of Section 3.4. Each end cap of the heat source assembly is provided with ...:( a 1/4-20 UNC tapped hole, to facilitate transfer of the assembly between hot cells and for general handling purposes. For RTG loading a handling knot, willbe threaded into the end cap to permit lowering of the heat source into h RTG. This knob must be removed after feeling. The handlina knob is shown on TES Dwg. No. ?.- 015-200004. j Removable radioactive contamination from the exterior surfaces of the completed heat source assembly shallbe as low as reasonably achievable. The fueling facility shall submit its proposed limits and
l.,,
test method to TES for approval. Each of the strength member end caps of the completed beat source assembly are to be identified by a serial number, mique to each l heat source, applied in a permanent manner (electro-chemical etch, metal stamp or vibro-stch). The TES serial number is acceptable. SIZE CODE IDENT NO. ' i:i...: A 30856 Dis-800000 l nEv l .::. :(. l SCALE l$NEET g ES-2n J 6 TES-3205 4-12 1 .._.._._,_..___..,1
io g~ s $[a
3. 4 Welding
%g ' The nethod of welding the heat source assembly componess, that is, the Hastelloy C-276 liner assemblies and strength member assemblies shall be at the disention of the fueling facility provided sufficient weld penetration, the degree of leak tightness and the additional requirement 5 i cf this section are satisfled.
3. 4.1 Weld Develorment - A weld development program is to be planned by the fueling facility based on the use of weld test arecimens furnished by TES. Uner weld test specimens are shown on TES Dwg. No. 015-200005. Strength member weld test specimens are y
shown on TES Dwg. No. 015-200006. The weld test specimens provide full sized joints of. exact configuration and tolerances as the fueling componess but in shorter length units. The weld parameters such as start-up current, weld curant, tail-off current, overlap and rotational speeds are to be established tr; the fueling facility through a plawd weld development program. This program, as a minimum, shallinclude the weldtrg and subsequent testing of sufficies numbers of full sized joint configurations to verify that the welds meet the acceptance criteria listed be ein and are fully reproducable. It is recommanded that a minimum of two specimens each of line s and strength members be welded to establish each set of parameters. 4 ) The weld development program is also intended to establish and/or verify the helium leak test and netallographic inspection procedures v to be used for weld testing. Inspection of weld joints to detect flaws such as voids, inclusions sud discontinuities shall be performed by dye penetrant and metallographic examination techniques. Magnified photomicrographs shall be used to determine weld penetration. 3.4.2 Production Welding 3.4.2.1 Liners, Strength Members and Associated Weld Test Specimens - Production linerr., strength members and their associated weld test specimens are to be welded in batches of not more than five (5) fueled piece s. Uke componess la any one batch shall be welded using the same equipment, ftxtures and welding procedure established for that component in the weld development program (3.4). ( l wr I s I l SIZE C00EIDENT NO. I A 30856 015-s000
REV c
SCALE l l SHEET 10 C\\ U TES-3205 4-13 1
N
9' ARer the equipment has been setup, and the appropriate parameters

(
established by weld development, a minimum of one test weld shall be f.:::.: made prior to vielding each batch of fueled Eners and/or strength (::*:. members. De test welds shall be subjected to dye penetrant tests,
9..(
leak tests and metallographic ewamination. The tests shall be performed and evaluated grior to welding any production liners
((-
and/or strength members. .9 In the eyed that a test specimen does not meet the requiremert s of i paragraphs 3.4.3.3.1, an mMitional specimen (or specimens) shall be welded and tested aRer apy necessary corrections are made to the welding equipmed or setup. Evaluation of Aaeled liner and /or strength member welds shall be nude in accordance with para. 3.4.3.3.2. ARer a satisfactory weld test specimen has been prodmed (meeting all requiremeds of para. 3.4.3.3.1) the weld run may proceed. The first piece welded is to be a fueledliner and/or strength member, followed by a weld test specimen, etc. The sequence is to codinue in this manner such that each fueled component is both preceded and followed by a weld test sample. .- l < ne last weld test sample shall be subjected to dye penetrant test, leak -l test and metdlographic examinatinn prior to acceptance of the production batch. In the event this sample has defects exceeding those allowed by para. 3.4.3.3.1, the production liner and/or strength member g ~* welded immediately prior to the weld sample shall be discartled and the next weld test sample analyzed (evn1nated). Should this weld also n prove defective, the production liner and/or strength member welded U immadiately prict shall be discarded and the next welded immadiately prior shall be. discarded and the next weld test sample examinad. If necessary, the sequence of weld test sample testing shall be carried backward (in order of welding) from the last sample to the next to last, to the third from last sample, etc., until a satisfactory sample is found or stilthe edire batch has been rejected. All weld samples are to be Photograt s of the examinations t retained for a minimum period of 5 years. are not required provided certifled reports of the tests are furnished. l l f::.:..'< SIZE CODE IDENT NO. '5 " ii:.:::/ A 30856 REV ~ [ SHEET 11 c {${f.- SCALE l
s-m J 6 t
lO v TES-3205 4-14
~. _ l i j l O j l
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3. 4. 3 Weld Testtag

3. 4. 3.1 Weld Test Specimens - WeM test specimens, as required herein, am to j
4 be subjeded to the tests =p=daad in para. 4. 2. 2, 4. 2. 3, and 4. 2. 4. U( ~:;: 3.4.3.2 Production IJaers and Strensth Members - Production fueled liners
Ol and strength members are to be subjected to the tests speciSed in para. 4.2.3.
l:{- 3.4.3.3 WoM Acceptance Criteria l (.. :: 3.4.3.3.1 Weld Test SpecinE us - Weld test specimens, when tested in accedance 'j with para. 4.2.2, 4.2.3, and 4.2.4 herein, shall meet the following criteria: , y' a. Cracks - There shall be no visible surface cracks in the weld or adjaoed base metal when inspected by dye penetrad in accordance with para. 4.2.2 b. Ie - De leak rate of tested samples shall not exceed 1 x 10. soc e see atm when tested in accordance with para. 4.2.3. c. Penetration - h weld penetration shall be equal e greater than l ~ that speciSed by the appropriate TES drawings when eramt=d Ma"Wcally in accordanne with para. 4.2.4. N., ' d. Aggregde Thear De'ects - ne sum of the lengths of all root 4 cracks, voids and inclusions (aggregate linear defects) along ag one straight line on the surface of a metallographic section (see - (.: para. 4.3.4) shall not exceed 0.015 inch. 3.4.3.3.2 Production IAners and Strength Members l
~;
a. Isakage - The leak rate of production liners and weld test =p=d'a== shall not exceed 1 x 10-6 sec He/sec atm when tested
(.
in accordance with para. 4.2.3.
3. 5 Heat Source QualiScation Testing

) *-
Prior to use in an RTG, one beat source assembly is to be subjected to the capsule tests prescribed in IAEA Safety Series 33. These tests i are shown in Appendix B. De best source assembly used in the tests shall be a production unit in every aspect except the radioactive fuel may be simulded by ir. active material of the same or similar nature. The beling faciljty is to provide a written renort to eqmmarize test Ms. He report should incorporate the actual test Irocedures used and the leak test rate results following each test. :.. p < .. :. l 882E CODE IDENT NO. A 30856 '25-800'00
.r nEv
, ' {* ' SCALE g jsMEET 12 es-2n 9 l TES-3205 t 1 4-15 l l l l
+
(
4.0 QUAIITY ASSURANCE PROVISIONS 4.1 Quality Assurance Program Plan The fueling facility is to establish and maintain a Quality Assurance Plan, which, in general chall comply with the applicable DOE QA requirements. The Quality Program Plan must incorporate the necessary quality coro' measures to assure that the weld parameters and test procedures diliLed for the heat source qual 15 cation hardware are malmained during the fabrication and testing of production heat source assemblies. The Quality Assurance Program Plan shallinclude codrols over current engineering drawings and specifications; written operating and test procedures; qualineation of competent personnel, and a system of quality controlinspections and documentstion to verify compliance with the requirements of this speciscation. A copy of this plan is to be provided to TES, unless previously submitted. Certinestion The Fueling Facility shall prmride certiSed test results of the following items: a. Fuel Chemistry - The fuel contained in the completed heat source assemblies has been processed from feed solution that complies with the composition shown in Appendix A. 4 b. Fuel Quantity - The quantity of fuelin each liner assembly C) and heat source assembly in thermal watts and in curies, the associsted errors, and the date(s) of measurement (s). I c. 11ner Weld Quality - Ilner weld joint shall comply with the l requirements of para. 3.4.3.3.2 as established by testing in accordance with para. 4.2.3. d. Strength Member Weld Quality - Strength member weld joint shall comply with the requirements of para. 3.4.3.3.2 as established by testing in accordance with para. 4.2.3. e. Strength Member ar liner Weld Test Specimen Weld Penetration - Weld test specimens welded with production components in accordance with para. 3.4.2 shall comply with alrequirements of para. 3.4.3.3. I as established by testing in accordance with gara. 4. 2. 2, 4. 2. 3 and 4. 2. 4. t f. Surface Contamination - The amount of codamination on each l heat source assembly, establiahed by testing in accordance with pars, 4. 2. 2. SIZE CODE IDENT NO. '2 5-8"" A 30856 REV SCALE ( l$NEET 13 Es-211 JL v TES-3205 4-1C ) ~.
) + J
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4. 2 Testing Tests performed by the Feeling Facility to verify conformance with the requimments specified herein shall be as follows:
4.2.1 Radioactive Cantamination - Remorable codarnination on the exterior surface of the completed bed source assembly shallbe evaluated by a p:.: pmposed method by the Fueling Facility and approved by TES. 4.2.2 Dye Penetrant Test - Dye penetrant testing to disclose sur' ace cracks mhall be performed in accordance with aprocedure selected or generated
f..
by the fbeling facil1*.y and sutmitted to Teledyne Energy Systems for information, if not previously provided. The procedure shallcomply with the ided of ASTM standard E165-60T. (Applies to test welds only.) 4.2.3 Isak Test - Testing of weld test specimens and production beat source assemblies and liners shall be performed in accordance with a procedure prepared by the fuelin,1 facility and furnished to Teledyne Energy Systems for inbrmation, if not previously provided. The l:..: procedure shall be based on the use of Helium Mass Speetrometer, Krypton 85 or a residual gas analyzer. In the event helium is not used, the fueling facility shall provide analysis to show equivalency between the selected g::.*. test and helium tests. Minimum sensitivity of 2.emeasuring equipmed shall be 10-8 STD cc He/sec. 4.2.4 Metallographic Examination - Metallographic examination of weld 4 test samples shall be performed as follows: s r*: a. Each weld test sample (specimen) shall be sectioned in four ) s_./ places, 90'
10' spart with one of the sections taken through the point where the weld beads overlap.
b. Each section abs 11 be polished and etched as req 11 red, and examinad under 75X magnification to determine weld penetration and aggregrate linear defects. M*. 4.2.5 Source Calorimetry - The thermalinventory of each completed beat scuroe shall be determinad in accordance with a procedure prepand by the fueling facility and submmd to Teledyne Energy Systems for I:* :', information, if not previously provided. l ..c SIZE CODE IDENT NO. l .t. : A 30856 015-8 *
o REV f
i SCALE l$HEET 14 l
5-2 n J k r3 N
TES-3205 4-17 l l -~- ~ -, - ~
l [s -.~. l \\,, 4 [:* :
4. 3 Non-Comnitence Eems
[:*:, Arg stem which does not comply with the requiremess or Quality Assurance provisions of this documerit or the appropriste Teled w 3 Energy Systems drawing shall be properly documented and submitted to Teledyne Energy Systems for disposition. A Corrective Action Board (CAB) will review these discrepent itema to determina the cause of event, to propose corrective action to prevent reoccurrence, and to determine the disposition of affected hardware. The operation of this review board is covered by the SENTINELQuality Assurance Plan. g t
4. 4 Deliverable Data h following data items shall be delivered by the Ibeling Facility to Teledyne Energy Systems covering all heat sources used in the SENTINEL SS RTG:
s. N1 chemistry cert 1Scation (4. la) b. hl questity certincation (4. lb) e. Results of helium leak tests 4.1c & d) d. Results of metallographic ern-nination (4. le) e. Results of radioactive codamination tests (4.2.1) ( ] In addition to the deliverable data pertinent to each individualle at source listed above, the following documentation shall be delivered to Teledyne Energy Systems for information/ review and/or comment: s. Results of hest source qualineation tests (3.5) Appendix B. b. The proposed limit for removable surface contamination on the completed heat source assemblies and the proposed test nethod (3. 3. 2 sad 4. 2.1). Pheling Facility Q. 'A. Plan, Dye Penetrant Test Procedure, Imak ~*' c. Test Procedure and Calorimetry Procedure. These documents need not be submitted if previously provided and no revisions have been made subsequent to document submission. SIZE CODE 10ENT NO. {'{': :.. A 30856 015-8 *
o REV c
SCALE l$ MEET 15 ES-211 J g \\ ] TES-3205 4-18
,.s.. -- +- - ~ apporprx A w same. . muss m ra m me nammmamar rnatons! att aarr
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w. n. mammets Seie4*e teerty Systes 110 he i Tiemate Reed
.a.
1toonte msrpiend 21893 I: :.,, esforense r Letter. October it.1977. J. E. beecker to W. A. k9maald. eene setject P...*. Smar nr. hatenstd: Strentle fleeride We onderstead poo need to here tafemettea over end ebeve that ohtch ses provided to the ettedument to reference letter. Tats is provided t.eles. Cuneesttfea of feed to Stectfe facepsviettoa foafte mette* .,.0 jg1 Total Trf vetent tettens (Fe. tr. E. A1) e7 I 10 s i Total of me. Se. Ce Cettens ,4.13 4 ~ Pb p I 10** .3 g ig e g4 el I 10** - 0 Oh SDo" Q E 10** og, e M5r d.66 ~
5r Reage 45 31 Perseet a811 emelstitel date reprted as e *less then' eelse erill be considered sere.
,-l Sers trols poors. f I i ~.- I l 1 'lN.teetter l Iregras Rensger Weste manegment 3RAll/ha W. C. Johnson. Jr. 00f-8L i et: ....u. l SIZE CODE IDENT NO. i:.. A 30856 .ois-sooooo nEv C 16 SCALE l [5HEET a TES-320.3 4-19
T + J i.. :. APPENDIX B ),,- HEAT SOURCE QUAIlFICATION TEST REQUIREMENTS
O-5 2...
I:!$..!. L0 GENERAL The tests described in paragraphs 2.1 - 2.6 inclusive shall be applied [9 - l L1 to samples or prototypes of capsules constructed as for use in a generator except that their radioactive content may be simulated by inactive material 0 This implies that, subsequent to satisfactort of the same or similar nature. 0 9*: conclusion of the tests, full inspection will be carried out during the 's.- production of capsule for operational use to ensure that the standards achieved by the samples or prototypes are maintained. The lasst material or Anel almulag used in the test capsule shall be j*,*,, documented and furnished by TES. The capsule shallbe subjected to each of the tests indicated in Section 2 L2 m., If the tests are not required to be carried out at a particular teJaperature. then 1 L3 they should be done at the RTG operating temperature if this is practical. The tests shall be carried out in such a way as to ensure that the sample 4 L4 r capsule suffers maximum damage. Aft 2r each of the tests, the capsule shall be shown to have retained its L5 \\ origina11eak-tightness within.the accuracy of the chosen method. l* L6 A different sample or prototype espsule may be used for each of the tests except in the case of that indicated in paragraph 2.6. [*..
2. 0 TEST METHODS 2.1 Impact Test The capenle shall fall on to the target from a height of 9 meters. Tbc target shall be a flat, horizontal surface of such a character that any increase in its resistance to displacement or deformation upon impact 4
by the capsule would not sign 1 Scantly increase the damaqre to the espoule. l-SIZE CODE IDENT NO. I 015-800000 !!:j.j:: A 30856 AEV 17 SCALE j$HEET i $+:: 1 l d TES-3205 4-20
..w. ._-----.=r.----=-a...m c S .$.(. h.
2. 2 Percussion Test The capsule shall be placed on a sheet of lead which is supported by a smooth solid surfmoe and struck by the Dat face of a steel billet so as
~$:'
to produce en impact equivalent to that resulting from the free fall of .-(* 7 kilograms through 1 meter, ne flat face of the billet shall be 2.5 cenNmeters in diameter with the edges rounded off to a radius of not less than 3 millimeters. De lead, of hartiness number 3.5 to 4.5 on the Brinell scale and not more than 25 millimeters thick, shall cover an ana gnater than that covered by the capsule. A fresh surface of lead shall be need in each test. ~$~
2. 3 nermal Test The capsule shall be heated in air to a temperature of 800*C and it shall be held at that temperatum for a period of 30 mimtfes before being allowed to cool.

2. 4 Thermal Shock Test
.f$(- The capsule shall be heated to its maximum operating temperature and then plunged in water at zero temgrature where it shall be left for 10 minutes.
!f
2. 5 Pressun Test
(- The caspule shall bg shown to be able to resist an external pressure of ~ 1000 bars, i.e.,10 Newtons per square meter. .f..
2. 6 Imakage Teet
...(: This test relates to the requirements of' paragraph 1.5. The minimum sensitivity of the leak test system and the pass / fail criteria for the test l are spelled out in the basic specification.
2. 7 Other Tests
[*[.' For certain applications, corrosion, vibration, irradiation and creep tests 9 may be specified by the competent authority. No additional tests are required for this application. .0:
p l
t SIZE CODE IDENT NO. ii.' A 30856 ois. oooo REV
!j SCALE I
IsHEET 18 i TES-3205 j 4-21
i O 4.4.2 Corrosion Resistance of Hastelloy Alloy C-276 in Seawater CONCLUSIONS: Hastelloy C, Haste 11oy C-276 and Uniloy HC are all suitable capsule materials for seawater service. The modified Hastelloy alloy C, desig-nated Hastelloy alloy C-276, retains all of the essential constituents which impart the remarkable corrosion resistance to the original alloy. Carefully controlled silicon and carbon content in alloy C-276 prevents grain boundary precipitates in the heat-affected zo'ne, which normally occur during welding of Hastelloy C, thus eliminates the need for a desirable heat treatment step that is frequently imprac,ticable. The modification is of s'uch a nature that an a priori assumption of superior corrosion resistance in the as-welded condition of the two materials and equivalent corrosion resistance when Hastelloy C has received a post-weld solution heat treatment is valid. Uniloy HC is precisely the same formulation as Hastelloy C; therefore, an a priori assumption of its corrosion resistance as compared to the latter alloy is valid also. . Like Hastelloy C, Uniloy HC should receive a post-weld solution heat treat for maximum corrosion resistance if the exposure media is severe. It has recently beca determined that NRDL has done corrosion tests on Hastelloy C-276. The 200 day tests show a corrosion rate of 2 X 10-6 mpy. Receipt of this information confirms the conclusions presented previously. DISCUSSION: Union Carbide Corporation announced in 1968 that they would phase out production, therefore availability, of Hastelloy alloy C. The replace-ment alloy, Hastelloy alloy C-276, is a very minor modification of alloy C. The modification consists of lowering the already low silicon and carbon, content fr.om 1. 00% and 0.08% maximum, respc.ctively, to " low as' pos sible, " (LAP). It is important to note that all of the constituents that impart the remarkable corrosion resistance to Hastelloy C are un-changed in alloy C-276. The 1mprovement of Hastelloy C was required [ TES-0205 ( 4-22
to eliminate the need to heat treat vessels (usually chemical vats, the almost exclusive use for Hastelloy C) after fabrication to' redissolve O the grain boundary precipitates in the heat-affected zone, thereby achieve maximum corrosion resistance for the intended service. The elimination of th heat treatment step represents a significant advancement. It was achieved by carefully controlling the concentratio of silicon and carbon which form compounds (silicides and carbides) that have low solid solution solubilities. Therefore, in the Hastelloy C formu-lation these compounds precipitate at the grain boundaries during welding and ultimately increase the susceptibility to attach by several media which aye otherwise innocuous. The absence of grain boundary precipitates in as-welded or as-fabricated conditions of alloy C-276 is of a decided ad-vantage for two reasons: (1) it precludes the heat treatment step as mentioned previously, and (2) it indicates that overaging of the alloy in high temperature service is not a problem. In view of the fact that a solution heat treatment of a fueled and seal-welded Haste 11oy C capsule to enhance its corrosion resistance is im-practicable, it is reassuring to know that no grain boundary precipitates are present in the replacement alloy after fabrication. This is the greatest advantage of Hastelloy alloy C-276. Hastelloy C always had some precipitates present as-fabricated and it is well know that in certain media the corrosion rate is increased. Corrosion generally O. manifests itself as a grain boundary attack. However, the seawater corrosion resistance of as-welded Hastelloy C easily rneets all require-ments of the prescribed safety standards. The heat treatment is of real significance in cases where the service, condition of the material is severe, such as exposure to a strong oxidizing or reducing media. Unikoy HC has a composition which very nearly duplicates that of Hastelloy C, therefore can be substituted directly for Haste 11oy C. It too should be solution heat treated after welding to dissolve grain boundary precipitates and restore the full potential of corrosion resistance. Some specimens of Haste 11oy C-27.6 are on test in seawater at INCO's Harbor Island Test Station. These tests are perhaps two years in duration and at the last inspection nothing unusual was noted. The tests are continuing. ) The writer contacted NRDL to determine their experience with Uniloy HC , and Hastelloy C-276. NRDL has conducted several tests by several methods over the past few years on many materials of interest as fuel capst...:s. i t They have duplicated the results of corrosio$ tests of Hastelloy C conducted by the writer several years ago. The accomplishment of interest is that O TES-3205 4-23
NRDL applies the classic anodic and/or cathodic polarizafion curve method to determine the propensity of a material to corrode. The advantage of this test method is that accurate and reliable Igng term corrosion predictions can be made from very short term tests. NRDL is interested in assisting us by making any measurements'we want if a the proper arrangements can be made; however, NRDL is being phased out currently. NRDL has done no work at all on Uniloy HC, but some corrosion studies on Hastelloy alloy C-276 are reported in NRDL-TR-68-109. Three kgnds of tests are described, hot seawater vapor, high hydrostatic pres-sure and ionizing radiation. The polarization method was not usad. However, " baseline" tests were conducted similar to a method used by INSD several years ago, viz, irradiated specimens were exposed to sea-water for an extended period and aliquots of the seawater were " counted" periodically for certain dissolved radioactive constituents. The corrosion rate of the C-276 alloy (improperly identified throughout the report as Hastelloy C) at 20 C is 2 X 10-6 mpy after 200 days and decreasing with time. This rate is considerably lower than the corrosion rate of Hastelloy C measured earlier at INSD, 5 X 10-4 mpy at 65 C in 180(?) day tests. For comparative purposes, a corrosion rate of 8. 3 X 10-4 mpy, for Hastelloy C ( (or C-276 or Uniloy HC) is a corrocton rate of one mil per twelve centuries' nt /fs> J. W. McGrew, Teledyne Energy Systems c l TES-3205 4-24 v
5. SHIELDING EVALUATION 7 This chapter identifies, describes and analyzes the principal shielding design of the package. Dose rate analyses for the Sentinel SS unit as packaged for shipment under normal transport conditions and as a result of the hypothetical accident condi-tions (Para. 71. 73) are presented. The analyses are evidence of compliance with the requirements of the external radiation standards for non-exclusive use package of 71.47 and the additional radiation requirements for Type B packages of 71. 51 (a) (2). 5.1 Discussion and Results The Sentinel SS RTG design includes a stainless steel clad shield assembly (body and plug constructed of depleted uranium (DU)) which encloses the fuel c.apsule assembly. The combination of radiation attenuation within the fuel capsule assembly i (including the SrF2 fuel form), the shield assembly and the steel shipping cask serves to mduce dose rates to permissible levels during transport. Specifically, as required for non-exclusive shipment, dose rates at the surface of the package are everywhere less than 200 mrem / hour. Dose rates at one meter from the external surface of the package are less than 10 mrem / hour. By design, the configuration consisting of the RTG shield assembly containing the fuelcapsule assembly has external dose rates less ti an one rem / hour st one meter from its external surface consistent with the require.nent for Type B packages sub-jected to the hypothetical accident sequence. This configuration is postulated to be the Q (minimum) oonfiguration resultant from the accident sequence (see Chapters 2 and 3). V Dose rate analysis provided herein is based on the maximum possible fuel in-ventory at time of fueling 31,400 C1 (210 thennal watts) of the Sr00 fuel. A summary of the maximum dese rates under normal condition of transport and for the configuration resulting from the hypothetical accident sequcnce is provided in Table 5.1.
5. 2 Source Specification

5. 2.1 Gamma Source
'Ibe radioactive source consists of up to 31,400 Ci of Sr-90 in the SrF fuel 2 form. Sr-90 and its relatively short lived daughter product Y-90 am considered, for all practical purposes, pure beta emitters. External radiation consists of Bremsstrahlung radiation (hereafter referred to herein as gamma radiation) which is produced by the betas emitted in the decay process. Energy dependent gamma source distributions am derived using the theory and computational technique of Evans (Ref. 5.1) for external Bremsstrahlung. Source stmngth distributions derived for the SrTIO 0 fuel form, using this method, were verified by comparison of computed dose rates with measured values beyond varying thicknesses of lead shielding (Ref. 5.2). l TES-3205 5-1
TABLE 5.1
SUMMARY
OF MAXIMUM DOSE RATES (mremAir) One Meter from Package Surface Serface of Package Side Top Ik>ttom Side Top Bottom Normal Conditions 19. O.32 40.
2. 0

0. 03

2. 7 Hypothetical Accident Corrlitions(")
1.3 x 10 710 5 g en 5 ah 8 .10 CFR Part 71 Limit 1000 1000 1000 I"IMaximum dose rates to side and top of unit not computed for this case. Dose rates will be lower than values given for bottom. Bottom is ama where shield thickness is minimum. g
The volumetric gamma source strength is based on an active fuel volume of 224 cm3, a power density of 0.9375 watts /cm3 and 149.4 curies / watt for Sr-90, Y-90. A multiplying factor of 1.16 is included to account for increased Bremsstrahlung production in SrF2 over the SrTIO fuel form. Total gamma source strengths for a 3 31,400 Ci source are given in Table 5.2. l 5.2.2 Neutron Source Not applicable. No neutrons am produced by the SrF source material. 2 TA BLE 5. 2 ') TOTAL GAMMA SOURCE STRENGTHS Production Rate S ES Energy _E in SrTIO3 Sr-90, Y-90 Range Photons MeV GIeV) GleV) (Photons / Disintegration) see sec 1 1 0-0.22 0,11
6. 37 x 10~

8. 58 x 10 9.44 x 10
-3 0,22-0.44 . 33
5. 72 x 10

7. 70 x 10 2.54 x 10
-3 1 1 0.44-0.66 .55 2.22 x 10
2. 99 x 10

1. 64 x 10 1
-3 1 12 0.66-0.88 .77
1. 03 x 10

1. 39 x 10

1. 07 x 10 11 11 0.88-1,10
.99
4. 00 x 10

6. 60 x 10 6.53 x 10
-4 11 11 1.10-1.32 1.21 2.18 x 10
2. 94 x 10 3.55 x 10
-5 11 11 1.32-1.54 1.43
9. 00 x 10

1. 21 x 10

1. 73 x 10
-5 10 10 1.54-1.76 1.65
2. 97 x 10

4. 00 x 10 6.60 x 10 1
-6 0 10 1.76-1.98 1.87 6.80 x 10 9.16 x 10
1. 71 x 10 f
~7 8 0 >1.98 2.09 7.32 x 10
9. 06 x 10

2. 06 x 10 i
5.3 Model Specificatig i I Thir section presents the details of the models used for shielding evaluation. T
5. 3.1 P7gst,nal Description of the Shielding Configuration M:,&ds Shieltiing calculations are performed by computer pmgram SPEND written by Teledyne Erargy Systems. The code has been used extensively over the past 25 years I
for dose rece radiation ant. lysis for nuclear mactors, spent fuel shipping casks, and TES-3205 5-3 l l
RTG shiehi design and evaluation. RTG applications include other members of the l Sedinel Ikoduct Line. The program employs a point kernel technique to numerically integrate over the cylindrical or cylindrical annulus source regions (s). Space is apportioned into axial zoms with boundary planes perpendicular to the symmetry axis. Within ea :h axial zone, several radial regions may be specified. In the course of the integration a geomety routine determines the distance and path lengths through the intervening media alcag the path from source point to dose point. 1 The gamma kernel determines the attenuation along the path for each of several er.ergy groups. The effects of scattered radiation are incorporated into the calculations by the use of buildup factors in Taylor-exponential form. Configuration geometry and material specficiation, energy depended gamma absorption coefficients, buildup constants and flux to dose conversion factors are provided as input to the code. J 'Ihe SPEND geometry routine allows for an esseitially exact reporduction of i the actual physical geometry of the various components which comprise the configura-tion under study. One exception is the " tapered" region of the shield body. For analysis, the tapered portion was approximated by division into multiple axial zones + { which were stepped (varying radli) to closely approximate the actual geometry. 5.3.1.1 Model for Nominal Transport Condition. For dose rate analysis l under normal conditions of transport (the nominal transport package of the RTG in-stalled in the shipping cask), the SPEND shield modelincluded the fuel region (two fuel pucks), the liner and strengh member, the DU shield body and plug (less clad) and the shipping cask. The above mentioned RM components were positioned with the axis of the fuel capsule assembly as the axis of symmetry. This configuration
O was such that the center of the fuel region is about 6.15 inches above the radial planc which defines the inner surface of the bottom of the cask.
I Radiation attenuation was considered only in the above described regions. For conservatism, all RM components exterior to the exterior surface of the shield assembly (e.g., insulation, housing, head / module assembly, preload components) were not_ included (considered void space) in the radiation analysis model. Also, the preload component for the RTG within the cask was omitted. The model source / shield geometry, then, is essentially as the elevation view of Figure 1. I would be if it in-cluded only the shield / heat source assembly suspended at its proper elevation within the shipping cask. 5.3.1.2 Model for Hypothetical Accident Condition. As discussed and ana-lyzed in Chapters 2 and 3, the (minimum) configuration resulting from the hypothetical l accident sequence is the intact shield / fuel capsule assembly. The geometrical model for mdiation analysis is that for the nominal transport condition (5.3.1.1)less the details which represent the shipping cask. As is obvious from the peculiar shield geometry, dose _ rates are a maximum along the axis of symmetry off the bottom of the unit (shield plug portion).' i ( j TES-3205 5-4 i _,.. - _ l
5.3.2 Shield Region Densities Gamma absorption coefficients for the materials of the models were computed ~ from the elemental data of NSRDS-NBS29 (Ref. 5.3). Interpolations of the elemental 4 data for the missing elements were performed according to the procedures recom-mended in the mport. To generate the linear absorption coefficients for the regions i of concern, the elemental composition and the weight fractions were used. i This information is provided in Table 5. 3 for all materials included in the shielding model. Excepting the fuel, densities are nominal values for the material. The density of the Sr-F2 fuel material, as pressed and loaded in the fuel capsule may range from 1
3. 7 to 4. O g/cm3 with an expected value of 3. 9 g/cm3 or better.
For conservatism, the shield analysis assumes the minimum fuel density. As previously stated, all materials excluded from the configuration were considered void (null absorption) in-l cluding air space.
l TABLE 5. 3 i l h1ATERIAL COh1 POSITION AND DENSITY Afaterial _ Density Composition 3 (g/cm ) Element Wt. Fraction 4 1.
Fuel, 3.70 Sr 0.698

SrF, F
0.3 02 2. Hastelloy C-27G(1) 8.88 Fe 0.8025 i AIo 0.1600 W 0.0375 3. Depleted Uranium, 18,45 U 0.9925 O. 75% Ti (by wt) Ti 0.0075 1 1 4. Steel Shipping Cask
7. 8 Fe 1.000 t
I Actual composition (by wt): Cr (.155), AIn (. 01 max. ), Co (. 025), Ni (. 554), V (. 0035), Fe (. 055). These elements have atomic number near Fe (Z = 26); l assumed to be Fe (.8025) for computation of absorption coefficients. i i I
Fuel density information from ORNL, the facility that prepams and loads the fuel packs.
l TES-3205 5-5 _ _ _ _ ~,. _ __. _ _ _., . -, _ _ ~. _ _.
5. 4 Shielding Evaluation This section completes the description of the radiation analysis technique, provides the remaining input information and presents the results of the analyses for the nominal transport package and for the configuration msulting from the hypothetical accident sequence.

5. 4.1 Computer Code Input The radiation analysis technique, embodied in the SPEND computer program has been described in Section 5. 3.1. Specific geometrical models used for analysis of the SS are described in 5. 3.1.1 and 5. 3.1. 2.
The code considers ten energy groups which span the source energies. For each dose point (specified as input) the code integrates over the source and sums the individual contributions from each energy group to determine the total dose rate. Energy dependent source stengths input to the code are provided in Table 5.2 Linear gamma energy absorption coefficients computed as previously described are provided in Table 5.4. Buildup factors are provided in Taylor exponential form. TABLE 5.4 LINEAR GAMMA ABSORPTION COEFFICIENTS O k(cm-1) Attenuation Depleted ~ SrF Energy 2 Hastelloy Uranium Steel (MeV) (3.7 g/ce) (8.88 g/cc). (18.45 g/cc) (7. 8 g/cc) 0.11 1.83 4.56 33.7 2.36 0.33 .396 .986 7.49 . 798 0.55 .288 .720 2.96 .620 0.77 .242 . 6 05 1.87 .529
0. 99
. 2 12 .530 1.41 .467 1.21 .193 .484 1.21 .427 1.43 .177 .442 1.04 .391 i 1.65 .165 . 4 13 .953 .365 1.87 .155 .390 .898 .343 l 2.09 .148 .319 .800 .327 l o TES-3205 5-6
I i \\ The constants for the buildup factor were generated from the buildup data of Goldstein (Ref. 5.4) by interpolation and function fit and are as given in Table 5.5. Specifically, 1 l these constants are for a dose buildup factor, point isotropic source, infinite medium. The SPEND kernel applies a M input buildup factor, over the total number of mean free paths from source to dose point regardless of the mix of materials actually comprising that path. For the nominal transport package model, the buildup factor for iron is used. For the shield / fuel capsule assembly model, the buildup factor for uranium is used. Generally, the application of a single medium buildup factor over a path length comprised of various materials (Iow to high atomic number, Z) may produce a non i conservative result. Supplemental calculations were performed to quantify the possible i error produced by the use of the uranium buildup factor for the shield / fuel capsule i assembly configuration. These calculations used an empirical model developed by Kalos (see Goldstein, Ref. 5.4, p. 225-227) from measurements performed on a low Z material (water) followed by a high Z material (lead). The analysis produced a r l TABLE 5. 5 ) CONSTANTS FOR BUILDUP FACTORS (Point Isotropic Source, Infinite Medium) i f-a x f-a2* B (E, x) = A exp + D - A ) exp g 1 1 1 where x = number of mean fme paths Source
Uranium Iron E
A OfeV) 1 ai a A 2 1 1 "2 0.55 1.44 .0321 .435
10. 0
.0945 .0125 O.77 1.67 .0377 .338 9.15 .0915 .0215 0.99 1.86 .0433 .278
8. 6
.088 .0280 1.21 1.98 .0490 .239
8. 2
.0845 .0335 I t 1.43 2.04 .0525 .218 7.65 .0810 .0385 5 i 1.65 2.07 .0568 .198 7.25 .0770 . 0430 1.87 2,08 . 0650 .181 6.85 . 0750 .0465 l 2.09
2. 06
.0640 .171 6.50 . 0730 .0505 e
For source energies below 0.5 MeV, bullup factor for Iron at 0.55 MeV used; for Uranium unity assum' d, i.e., B = 1. 0 (A = 1. O, a
=a'" )* 1 1 2 j TES-3205 5-7 1
mas cornction factor of 1. 07 to be applied to the SPEND derived dose rates for the region where the depleted uranium shield is thinnest (shield plug). For conservatism, this factor was applied to all external dose rates generated by the SPEND model. For the nominal transport model, the use of the medium Z (Fe) buildup factor for path lengths comprised of medium Z (fuel, Hastelloy, steel) and high Z (uranium) materials pro-duces a mnservative result (no correction factor needed). Gamma flux to dose rate conversion factors, adopted from ANSI-ANS standards, are given in Table 5.6. i TABLE 5. 6 o FLUX TO DOSE CONVERSION FACTORS C Source Energy 2 (MeV) (mrem /hr)/ photon /cm -sec) 0.11 0,000298 .33 .000382 .55 .00127 .77 .00164 .99 .00196 1.21 .00227 1.43 .00255 1.65 .00281 1.87 .00307 2.09 .00330 5.4.2 Results of Analyses Prinicpal msults of the Analyses are presented in Table 5.1. For the nominal transport package, maximum external dose rates occur along the axial center line of the configuration and below the cask. The maximum dose rate at the surface of the cask is 40 mrem / hour and at one meter from the surface is 2.7 mrem / hour. E is expected that, when verified by measurement, the actual transport index for the package will be 3 (or less). As can be seen by the maximum recorded in Table 5.1, exterior dose rates are expected to be well within the limits imposed by 71.47 for non-exclusive use shipment (transport index not to exceed 10, surface dose rates not to exceed 200 mrem / hour). The low dose rates result, mainly, be-cause the shipping cask was originally designed for another unit (Sentinel 8S) which has a higher fuel inventory. For the post hypothetical accident configuratloa, maximum dose rates occur along the axis of symmetry of the configuration adjacent to the region where the shield is thinnest (shield plug). The shield plug was designed, such that the maximum dose TES-3205 5-8
3 e 1 4 i* 6. CRITICALITY EVALUATION O This chapter is Not Applicable. 'Ihe radioactive source material does not emit neutrons. I I i i I I P i k s l L i i i I f f i i i t l t i t l-E o l i f I t O I TES-3205 f 6-1 i- ? t i I
7. OPERATING PROCEDURES A \\ \\ v' This chapter describes the operating procedums used in the loading and un-loading of the Sentinel SS pac' ige. These procedures are intended to assure that oc-cupational radiation exposure' am maintained as low as is reasonably achievable. 7.1 Procedures for Loading the Package Prior to shipping the units to the fueling facility each generator is completely assembled (except for the heat source) and leak tested. The assembly includes the precise sizing of the internal components required to properly pre-load the shield. Each head / module assembly installed on a generator is first tested on an electrically heated body to assure pmper performance. The assembled generator is installed in an individual shipping cask and the RTG pre-load assembly sized to give the proper RTG pre-load for shipment. The units are then transported as an unfueled package to the fueling facility. Toledyne Energy Systems requires the fueling facility, Oak Ridge National Laboratory (ORNL) to follow a complete, detailed, procedure covering pre-fueling inspections and checks of the RTG and fuel capsule assembly; installation of the cap-sule into the RTG and closure of the RTG, Most of these operations are performed in a " hot cell"by the fueling facility operators, with Teledyne personnel present to mon-itor the operations. (O) by Teledyne personnel at the fueling facility, and is an easy and straight forward pro-The actualloading or installation of an RTG into its shipping cask, is performed cedure. This procedure is briefly discussed in the following paragraphs. Prior to moving an RTG into a hot cell for the fuel capsule installation, the shipping cask (s) have been prepared in the following manner. The internal surfaces of the cask and cask lid are inspected for cleanliness and the gaskets inspected for damage. The lid attaching hardware, RTG pre-laad hardware, with spares; RTG out-gassing fixtures and electrical monitoring equipment are collected in an area to facili-tate an expeditous RTG loading operation. All personnel involved in the package loading operations am equipped with in-dividual monitoring devices. The devices consist of both TLD badges and pocket dost-meters and, where applicable, additional pocket chambers and ring chambers are used. Radiation dose levels received by operating personnel are limited to the standard es-tablished in 10 CFR 20.101. When the RTG is removed from the hot cell, wipe tests are performed by ORNL Health Physics to detect exterior residual surface cortamination on the RTG housing. The RTG is immediately set into the shipping cask and the immediate vicinity of the cask is evacuated of personnel pending Health Physics approval. The level of surface contamination must be less than 6600 DPM (corrected) as picked up over a 300 cm2 c area. This is in accordance with the requirements of 71. 87 (1) (1) for non-exclusive use shipments (less than 22 DPM/cm2 for beta gamma emitting radionuclide). If surface contamination exceeds the level specified, the RTG is removed from the cask Q and scoured with water and detergent. When it has been determined that tie surface t Q contamination is at an acceptable level the procedure may be continued. TES-3205 7-1
At this point in the initial RTG load procedure, the RTG cables are routed through the two cask openings, and the RTG outgassing plumbing attached to the RTG (Vg) head. This plumbing is made up so that it exits radially from the cask just above the cask body and is mated to the RTG with a single pipe thread fitting. The cask lid is set in place on spacer blocks to allow passage of the outgassing line. This arrange-ment provides good shielding for personnel in the area and permits conditioning of the RTG environment (evacuation, leak check and backfill) and electrical performance monitoring without impairing work from proceeding on other units. When the RTG is fully conditioned, plumbing is removed and the outgassing port sealed with a Teflon wrapped pipe plug. The hold down assembly is then posi-tioned and the cask lid is immediately installed, bolts torqued and a security seal run through one of the bolt heads and lid. The sealed shipping cask is wiped tested for surface contamination as described for the RTG. Radiation dose rates are measured at the cask surface and at I meter from the surface to assure compliance to 71.47 for non-exclusive use shipment and to 49 CFR Part 173.939. The cask is properly hbeled with Category III yellow labels and is ready to deliver to a carrier.
7. 2 Procedures for Unloading the Package The procedures for removal of the RTG from its shipping cask are discussed in the following paragraphs.
Q] All personnel involved in the receipt and/or unloading of the Sentinel SS package ( are to be equipped with appropriate ionizing radiation monitoring devices. Upon receipt of the package, radiation dose rates should be immediately mea-sured. These dose rates should be less than 200 mrem / hour at the surface and less than 10 mrem / hour at one meter from the surface. Wipe tests to determine the sur-face contamination should also be performed and should be less than 22 dpm/cm2 (corrected count) or 9. 9 x 104 HCi/cm, 2 Assuming that the cask is received in the expected condition, and after the Health Physics verification has been performed; the unloading operation can proceed. All of the tools, socket wrench extensions and special handling equipment should be amassed to prevent unnecessary delays in the RTG removal. The cask lid can then be removed and set aside. The hold down assembly can now be removed since it is merely " clamped"in position. Prior to removing the RTG, the connector plugs must be removed from their mounting plate and the cables pushed into the cask. The cable shorting plug should be reinstalled after pushing the cables into the cask. The RTG can now be easily removed (there is no attachment hardware). The RTG removal should be planned to occur after preparations have been made either for immediate installation at the users site or for temporary storage in an adequately shielded facility. (Q O TES-3205 7-2
I Teledyne Energy Systems furnishes an operating and instruction manual to ac-company each Sentinel package. This manual will contain a radiation dose rate map of ( the RTG both as a bare unit and as installed in its cask. A sample of the radiological safety contents of the manual is enclosed in Appendix 7.4. The sample enclosed per-tains to the Sentinel 8S model.
7. 3 Pmparation of an Empty Package for Transport i
A package having contained radioactive materials must be cleaned internally (usually a detergent and water is sufficient) and visually inspected to assum that the 4 gaskets and hardware am in good condition. All external markings and labels required by 10 CFR Part 20 must be covemd so as not to be visible. Cask lid hardwam is to be torqued to their normal values (90-110 ft-lbs). The cask can then be delivered to a carrier for transport. v I r e 4 i i lO 1 TES-3205 7-3
_m.. 4
7. 4 APPENDIX t
4 RADIOLOGICAL SAFETY 4 1 e e This appendix provides a sample of the radiological safety information which is part of the operating and i astruction marfbal supplied with each Sentinel model. This sample is spec'fic to the Sentinel SS, i i A I l 1 i 3 i ? i d 1 l i l { l l 6 l i t i i i l 1 i d l 1 i i i 1 i i I I r TES-3205 7-4 L ,--,n-,,------ -.a ---e,,,.,
A. CHARACTERISTIC DOSE RATES 1. RTG in Air The special design requiremed oflow overall weight for the RTG's result in MmHnn levels adjaced to the unit. Dose rate measuremeds wem performed on one of the four units, assumed to be typical because of the similar fuelinventory. Mea-suremens were taken at poids shown in Figure A-1 whem points 1 through 9 were taken at one inch from the housing surface and points 11 through 18 at one meter from the housing surface. Table A-1 gives the measured dose rates at each poid for the RTG unit. The RTG pasents a highly non-uniform dose rate with inhered measurement un-certaigies. Uncertainty in or enchancement of measured dose rates are mainly due to the three items listed below: a. Instrument Uncertainty - The standard error (95 percent confidence limits) quoted for the instruments used in the radiation survey is
10 percent. Hence, the actual dose rate for a nominal reading of 700 mrem /
hour may be somewhere between 630 to 770 mrem / hour. b. Position Uncertainty - As can be seen from the data of Table A-1, large variations in the dose rate occur over short physical distances. Hence, a small uncertainty in the actual positioning of the radiation detector could lead to a significant apparent difference when compared to calculated values. Some evidence of the presence of positioning uncertainty was present in the measured data. OU TES-3205 7-5 l
TABLE A-1 MEASURED DOSE RATES - SENTINEL 8S RTG TYPICAL MR SERIAL NOS. 017, 018, 019 AND 020* Measured Dose Rate Point No._ (mrem /hr) 1 1,200 2 1,200 3 1,500 4 9,500 5 10,000 6 7,500 7 6,000 8 20,000** 9 70,000** 10 65 11 65 12 75 O 13 175 14 400 15 300 16 300 17 550 18 2, 000** See Figum A-1 for location of dose rates
Measurements actually performed on RTG Serial No. 020.
These measurements are believed to be higher than actual. The RTG was raised and suspended directly over cask during measurements and the readings at the RTG bottom were probably subjected to high scatter from the cask.
O TES-3205 7-6
.,m_r_se m ~ >. ~, w_.-.... FIGURE A - 1 LOCATION OF MEASURED DOSE RATES Points 1 - 9 ara 1" from RTG Surfeca Points 10 - 18 are 1 meter from RTG Surface o o,_ ,J b .e. i. 1 Oe l. h O 1 } d i2 . w E %_~ .3 ./1. m@ _ - ~.... .c %~. - ~ a...-
f..
N &a...q~. j i W K.. 4 \\ u,,,. 4 - 'I s -O sb N . 6 i~ ~ y-.:- \\ .~ i. ,. / fg$$/ / /./ L ~- ~ ~ ~ s 4 / r
At' 84% f," it' g..-
4 / $s(s., / t, / .c s ./ / / /- / .'[ " " /$. ' /. r- /, O I, , e g,,/ s M lA .-. =.. s. /' f m\\ y ", ' *. _ * *. ~. / 4 u. N.. N
=.. _ -/
1./ . t. / .~ ~ t / / / 4 .<*to-f, />',, s 7 s . s. ' ?-:. 2 :::- "' _~ ,/ t ... c.,-
-. l-l5 t.
y ~,; : - - ~ .. ~....... -.. ,// e 1, . - ~. na........ - . ~ ~,. s 4-l f.*:p....,p.- 7 . W,.: b3 p ( ,l } W* s en -O d a g \\Q e \\ r ~ l TES-3205 7-7 l 'o yg is Q
J c. Cell Wall Scattering - Radiation measurements wer performed in a con-crete willed test cell. Cell walls were 6 to 10 feet away from the unit, but space limitations required the unit to be closer to the floor. Scatter-ing imm the cell walls and floor may have significantly increased the dose rate below the unit. 2. RTG in the Shippiu Cask with Shipping Cask Head Removed The shipping cask body in close proximity to the unit presents an extensive scatterig region. Dose rates above the unit will be increased (over the dose rates for the unit in air) by scattering from the inner walls of the shipping cask body. I Measurements were made with the unit in the shipping cask body at location shown on Figure A-2. Point 1 is 30 cm from the RTG housing surface (approximately 52 cm from source center) and Point 2 is 130 cm from the surface (approximately 152 cm fmm the center). Maximum measured dose rates are tabulated below. Dose Rate Point (mrem / hour) j S/N 020 1 400 2 40 Off to the sides of the cask (out of the cone) the dose rates will decrease to near the levels of the sealed cask (less than 200 mrem / hour at the exterior cask surface and less than 10 mrem / hour at one meter from the center of the source), c ( l TES-3205 j 7-8 l l [
LOCATION Ol' DOSE POINTS FOR RADIATION 5 MEASUREMI;NTS Y.1Til ItTG IN Ol EN SH11' PING CASK l .? l N z/ \\ g N- / \\ l / / i K ./ / N l, ss N / \\ 2-ye s y / g 'i r / \\ / \\f/ WShoppeaq Or,L t" f W'Ccvare,n. oc s~u ct. j . hf>bult. C / t .i O 6 p l 4 l e e NOT. TO SCALG I TES-3205 4 l 70 o g j h g g g y--. .m_~.--y--.,.,_, ---.-.,,-m.we-. 8
(G 3. RTG in the Scaled Shipping Cask The shipping cask is designed to meet applicable international standards. Whenloaded with the intact RTG, dose rates at the exterior surface do not exceed 200 mrem / hour and dose rates at one meter from the center of the source (fuel cap-sule) do not exceed 10 mrem / hour. B. EXPOSURE OF PERSONNEL IN VICINITY OF TIIE RTG Personnel exposure time is limited by the health physics restrictions imposed. Given a set of restrictions, the dose rates given in Section A may be used to estimate permissible working times. For example, the U.S. restrictions for monitored personnel require that ex-posure be controlled so that dose rates are maintained as low as reasonably achievable (n) (ALARA) not to exceed the following levels: a. Whole body; head and trunk ; active blood forming organ; lens of eyes; or gonads ---- 1-1/4 rem / calendar quarter, b. Ilands and forearms; feet and ankles ---- 18-1/4 rem / calendar quarter. c. Skin of whole body ---- 7-1/2 rem / calendar quarter. (A monitored person is anyone equipped with an appropriate ionizing radiation moni-toring device (s) ) Dose rates reported in Section A are subject to the uncertainties and effects discussed therein. Actual working time limits should be verified by checks with field survey instruments, where possible, i n v TES-3205 7-10 l i L
8. ACCEPTANCE TESTS AND MAINTENANCE PROGRAM (n) kJ The Sentinel SS RTG, like other Sentinel models, is designed to operate un-attended, and maintenance free for a minimum period of five years. These units are usually sited in remote and relatively inaccessible areas. This chapter will, therefom, address the acceptance tests of the package and maintenance of the shipping cask only. 8.1 Accertance Tests Although the shipping cask has been used numerous times as part of the Sentinel IS and 8S packages, it has never been employed to ship the Sentinel SS RTG, The following paragraphs discuss those tests to be performed prior to the use of the Settinel SS package. 8.1.1 Visual Inspeetion The safety related components of the Sentinel SS package undergo rigid dimen-sionalinspection to assure proper fits, clearances and thicknesses. These safety re-lated components are the fuel capsule assembly, which inaludes the capsule housing and end cap and the liner assembly, liner housing and liner end cap; the shield assem-bly consisting of the shield body and shield plug; and the shipping cask which includes the cask body and cask lid. The shipping cask (s) were dimensionally inspected many years ago and for p) their muse, are memly gone over to assure that the gaskets and hardware are in (, good condition, and that no damage has occurred to reduce the effectiveness of the structural or shield properties of the body and lid, in addition to the dimensional inspections required on the fuel capsule compo-nents, material certifications, including chemical compositions and material heat number, is required. This certification is required to assure that the capsule and liner weld test specimens are identical to the actual encapsulation hardwam materials. Material certification is also required on the shield and shield canning components. The control of inspection, measuring equipment and non-conforming materials, and components is addressed in detail in Tcledyne Document TES-3134 " Sentinel Pro-duct Line Quality Assurance Program Plan," doci t number 71-0307 (see Appendix A of this report). Other tests performed on the capsule assembly and shield assembly components are described under Section 8.1.4. 8.1.2 Structural and Pressure Tests Structural tests have been performed on the fuel capsule assembly (contalmnent vessel). One fuel capsule assembly has been subjected to the complete set of testa prescribed in IAEA Safety Series 33 (see Section 2.8). Following the tests, the test leakage rate less than 1 x 10 gequired of the fueled hardware, that is, it must have a specimen passed the leak test cc/sec, I ( ) l RJ TES-3205 8-1
i 8.1. 3 Leak Tests Both the liner assembly and the capsule assembly are subjected to leak tests i \\ at the fbeling facility, ne test procedure is to be submitted to Teledyne Energy Systems by Oak Ridge National Laboratory. Leak testing of encapsulated fuel is rou-tine at ORNL using a radioactive Krypton gas and a pmssurized chamber. The require-ments of the test and acceptance criteria are specified in Tcledyne Energy Systems drawing, No. 015-8000, " Heat Source Specification - Sertinel SS," included in this re-port as Appendix 4.4.1. Failure of either the liner assembly or the capsule assembly to meet the leak test criteria can sometimes be remedied by setting up the unit and remnning the programmed weld or by the addition of filler wire to the suspect weld area. If attempts to repair the leak also fail, the unit is rejected. The capsule or liner is cut open and the fuel mencapsulated in new hardwam after determining that the equipment is functioning satisfactorily as determined by the use of weld test sam-ples. The RTG assembly, scaled with dual Viton O-rings is also leak tested after { fueling although not considered to affect the safety of the package. 8.1. 4 Component Tests In addition to the tests previously described, the capsule and liner hardware are also subjected to radiography as specified in MIL-STD-271D Section 3. This is a non-destmetive test used to detect flaws, such as volds, cracks or inclusions in the finished fabricated parts, no snield components are subjected to dimensional and weight checks to verify that the proper material density has been obtained, ne sealed stainless steel can surrounding the uranium alloy components am also leak tested. This test is to assure m a scaled component with the can merely used as an oxidation barrier. a 8.1. 4.1 Valves, Rupture Discs and Fluid Transport Devices. Not applicable, j The Sentinel IS package contains none of these units. 8.1. 4. 2 Gaskets. Even though the shipping cask is equipped with a gasket between the body and lid and between the connector mourting plate arx! cask lxxty the gaskets are not required to achieve any of the safety criteria specific iin 10 CFR Part
71. The welded fuel capsule assembly remains as the containmert, therefore, no tests are performed on the gaskets.
8.1. 4. 3 Miscellaneous. Dere are no components, other than the fuel cap-l sule assembly, shield assembly and shipping cask previously discussed, whose failure l would impair the effectiveness of the package. 8.1.5 Tests for Shielding Integrity The shield integrity of the package is not subjected to testing prior to fueling, but s verified by the !!ealth Physics personnel at OHNL using calibrated radiation measuring instruments. Dose rates both at the cask surface arul at one meter from the surface are expected to be far less than the allowable limits of 200 mrem / hour and 10 mrem / hour respectively (see Chapter 5). Failure to meet this criteria will prevent delivery of the package to a common , y, carrier. The package would then require a cylirwirical tube of undetermined thickness l TES-3205 8-2
f to be fitted inside the shipping cask bo@. Such measures would be evaluated when the dose rate data became available. Until corrective measures could be taken the package i would be stored in an appropriate area of the ORNL complex. 8.1. 6 Thermal Acceptance Tests No thermal acceptance tests are planned to verify the thermal analysis shown in Chapter 3. l i
8. 2 Maintenance Program j
1 Not appilcable - see discussion under Chapter 8 heading. I i t I i f f I 1 1 4 P i i i l I .i i r i r i i l l l l i l I l TES-3205 i 8-3 1
APPENDIX A ( l QUALITY ASSURANCE 'o This appendix provides the quality assurance information required by 10 CFR 71.37. A.1 Quality Assurance Program The qualtiy assurance program for the Sentinel SS RTG is as defined in the " Sentinel Product Line Quality Assurance Program Plan," Report No. TES-3143, Revision B. An approved copy of this plan is on file with the Transportation Certifica-tion Branch of the U.S. Nuclear Regulatory Conunission under Docket Number 71-0397. Teledyne Energy Systems recently received a five year extension of the approval period for the plan as shown in Exhibit A of this appendix. A.2 Leak Testinc Procedures Leak testing procedures applicable to components of the transport package have been identified and described in preceeding chapters of this report: Procedure See Section a. Leak testing of the encapsulated 8.1. 3 and Appendix 4. 4. I fuel b. Leak testing of the stainless 8.1. 4 0 stcol cladding on the shield body and shield plug c. Wipe testing for removable 7.1 radioactive contamination on the RTG housing and shipping cask i s (v) TES-3205 A-1
r [ EXHIBIT A +* ,'C, UNITED STATES [' i NUCLEAR REGULATORY COMMISSION g j waswiecTow, p. c. zosse 0
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FCTC: LLC JAll 2 8 E 71-0397 Teledyne Eneray Systems AT1W: H.A. Mcdonald 110 West Timonium Road Timonium MD 21093 Gentlemen: Enclosed is Quality Assurance Proaram Approval for radioactive materi, packaoes No. 0397, Revision No. 2. Please note the conditions included in the approval. Sincerely, b) Ch ef Transportation Certification B: Division of Fuel Cycle and Material Safety, NMSS
Enclosure:
As stated l TES-3203 A2 i i i
. -m _ - _ weia _ma - a a A1 e - - _ _2 2 m _,_. m _ t gygy em j ,e,,,,,,, n wmm mmme mesa tm CUALITY ASSURANCE PROGRAM APPR2 VAL lp j! FOR RADIOACTIVE MATERIAL PACKAGES RE W CN UVBER e g ( l! em s i ( ) Pursuant to the Atornic Energy Act of 1954.as amended,the Energy Reorganization Act of 1974. as amended and Title 10. Code of Feoeral I p' 2, the Ouality Assurance Program identified in item 5 is hereby approved This approval as issued to satisfy tne requirements of Section Regulations. Chapter 1. Part 71 and in reliance on statements and representations heretofore made in item 5 by the person named in stem I 4 I q 71.101 of to CFR Part 71 This approvalis subject to allapphcable rules, regulations.and orders of the Nuclear Regulatory Commission I g now or nereafter in effect and to any conditions specified bese. I 4 I in 4 2 NAuE 3 EXPIRATION DATE g 4-Teledyne Energy Systems I i January 31, 1990 sTmEET AcoaEss jy j 110 West Timonium Road j a ooc =ET NuveEn ( CITY STATE ZIP CODE 4 Timonium MD 21093 71-0397 j i 5 OVAtiTV AsSVRANCE PROGRAW APPLICATION CATEisi jg October 18, 1979 and December 10, 1984 !) j e COumONs 4 i 4 g Ig 3 Activities conducted under applicable Criteria of Subpart H of 10 CFR lIl j Part 71 to be executed with regard to transportation packages for I !j radioactive material in special fonn. i I f I !g I I i I lI J !D il 1 'I !I i i 'I I I i I l e I !I I I! I i g, 4 I 4 g 1 I I I I I 4 I 1 TES-3205 I g A -3 g II c I / 6% THE u.s NUCLEAR REQULATORY COMMillioN I l i f JAN28 M l i Charles E. MAC00nald j' l CMlEF. TRANsPO4T Afl0N CERTIFICAf TON BRANCH DATE i olvis ON OF FutL CYCLE ANo MATERIAL SAFETY g i OFFICE OF NUCLEAR MATERIAL &AFETY AND SAFEGUARDS g sLFwViiii~ Mis ins fi#miadM wk w w whyh*gy gmgp3 gggv_ww mgar w w ww,,,,,, w,,,,,,,,, g ,}}

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