JAERI-Tech--97-038

JAERI-Tech 97-038

JP9709036

1997 3E9E
Japan Atomic Energy Research Institute

(T319-11

This report is issued irregularly. Inquiries about availability of the reports should be addressed to Research Information Division, Department of Intellectual Resources, Japan Atomic Energy Research Institute, Tokai-mura, Naka-gun, Ibaraki-ken 319-11, Japan. Japan Atomic Energy Research Institute, 1997

? 8 $ i t itLLi

(1997^ 7 ^ 15 B
(JRR-2, JMTR) tf o X % tzo i tz (i, IEAf6:^ltfk7i7^ h / v ^ f ^ t - f h#i7- + >^ Jlft, B^, EU, T ^ 'J *
Properties of Low Activation Ferritic Steel F82H IEA Heat Interim Report of IEA Round-robin Tests (1) Kiyoyuki SHIBA, Akimichi HISHINUMA, Akira TOHYAMA* and Katsumi MASAMURA* Department of Materials Science and Engineering Tokai-Research Establishment Japan Atomic Energy Research Institute Tokai-mura, Naka-gun, Ibaraki-ken (Received July 15, 1997)
F82H has been developed by JAERI and NKK Co.Ltd. as a low activation ferritic steel for a nuclear fusion reactor, such as prototype reactor and beyond. We have evaluated the properties of this material including the neutron irradiation effects using JAERI reactors (JRR-2, JMTR) and HFIR at ORNL. F82H also had been chosen as a reference material for the round-robin testing planned by the IEA workshop on the low activation ferritic/martensitic steels. These round-robin tests are conducted by several research groups in Japan, European Union,and the United States. The results for the Japanese share of IEA round-robin tests have been obtained, and are summarized in this report. Several properties, such as microstructure, mechanical properties, and physical properties have been obtained. The results are important for the estimation of the possible availability as a fusion reactor material and for the improvement of this material. Data accumulation and the preparation of the database are quite important for the reactor design activity. Keywords : Low Activation Ferritic Steel, Physical Properties, Mechanical Properties, IEA Round-Robin Tests, Microstructure, Vacuum Properties, Corrosion Resistance
NKK Co.Ltd. Central Research Center
1. 1 ZtbK 2 2. | | f t : o v > t (F82HlIEAt-^*&*>LJI#) 3. IW& 3. 1 &ffiUM 3.2 t>3Jf#14 3.3 t t K # t t 3.4 K ^ ^ t t 3.5 g&&!}f14 4. i^^lg^jo J: (f%m 4. 1 :ffiij 4. 2 t/SM^tt 4. 3 WttfLMftft.

* ^ H 4

4. 5 J&!fttt 5. i bib

Contents

1. Introduction 2. Material(F82H IEA Heat Standard Heat Treatment) 3. Experimental Procedure 3.1 Metallography Test 3.2 Physical Properties 3.3 Mechanical Properties 3.4 Vacuum Properties 3.5 Corrosion Resistance 4. Results and Discussion 4.1 Metallurgical Tests 4.2 Physical Properties 4.3 Mechanical Properties 4.4 Vacuum Properties 4.5 Corrosion Resistance 5. Summary Acknowledgments References Appendix A Tensile Test Charts Appendix B Fatigue Test Stress-strain Hysteresis Curves
F82H m\tWmt NKK 2, JMTR)-*H ORNL (D HFIR

Itttblz

Fig. 1 ic 2030
, Fig. 2 ( c ^ f *9f= ^ S B * - E U fc
Time Schedule of F82H Development for Fusion Device
1995 ITER/Prototype/Demo Reactor IFMIF (1)Material Development
- Standard/Control Properties - Basic Irradiation Properties -Compositional Optimization
i i i (ITER) Design/ponstructic)n
^Prototype) CDA EDAiConstruction (C&R) lEA'Collaboration/Round Robin Tests HFIR Phased

i_ AF?P _ Design

Construction (DEMO)
Operation Design/Construction

Operation

(2)Making/Fabrication Technologies
- Large Heat Melting - Welding/Joining - Component Fabrication
iTiq/EB/HIP Blanket Module, etc. Fission Reactor (HFIRVPhenix/JOYO) Irradiation IFMIF Irradiation
(3)Properties under Fusion Neutrons
- Heavy Irradiation - 14MeV Neutron Irradiation - Fission & Fusion Correlation
Model Simulation Fracture Mechanism esign Code JFT-2M Coating, etc. Module Tesjt using ITER JOYO/IFMIF Irradiation
(4)Utilization Technologies for
- Quasi-Brittle Materials - Ferromagnetic Materials - Fusion Environment
(5)Data Accumulation for Designing & ^ Construction
Fig. 1 Time Schedule of F82H development for fusion devices

fc IEA t - h t t J

K P tf

(1994-1999)

EU CEA-Saclay CIEMAT-Madrid ECN-Petten ENEA-Casaccia EPFL-Villigen FZK-Karlsruhe NFR-Nykoping PSI-Villigen

NKK(|)

ORNL-Oak Ridge PNL-Richland UC-Santa Barbara

Fig. 2

Participant of IEA round-robin testing on low activation ferritic steels

IEA 9741, 9753), t 9753

IEA fc0CD 5ton fc 9741 OM>=fyhfrbl* 7.5mm H i : 15mm Wa>fl*t, t 15mm W-t 25mm J i ^ i W ^ t l ^ t l U H t U i o Fig. 3

IEA t -

F82H i^ IEA t Table2 lz

Table 1 Ic

Fig. 4 fccfctf Fig. 5 ( c ^ f 0
Melting Casting Blooming Grinding Slab cutting Hot rolling Normarizing Tempering Plate cutting
5ton VIF | top:350 x 1410, bottom:250 x 1350, height:2000 mm temp: 1250 C slab size: 1310 x 3820 x 115t mm slab size: 1310 x 3820 x 107t mm Powder cutting Reversible rolling mill: reduce to 7.5t, 15t, 25t mm temp: 1250C temp: 1040C 750C x 60 min Plasma cutting: 7.5t, 15t, 25t mm plates Fig. 3 F82H IEA heat production flow

Rolling direction

Ingot Top

A o o o

RB801-1

RB801-3

RB801-5

RB801 -7

RB801-2

'RB801-4

RB801-6

RB801-8

F 1B801-X Y(X=1-8 , Y=1-21), RB802-X-Y(X=1-4, Y=1-21).--> RB802-1 RB802-3.__ 320

X-2 X-3

X-4 X-5 X-6

X-7 X-8 X-9

X-10 X-11 X-12

X-13 X-14 X-15

X-16 X-17 X-18

X-19 X-20 X-21

Ingot Bottom

RB802-2

RB802-4

(Unit: mm)

Fig. 4
F82H IEA heat (Heat No. 9741)

5500 A o

^ 4000 \ V A

RB820-1

RB819-1

RB820-2 RB819-1

RB820-1,2 (25t); y=31 or 41 yW-1 yW-14 yW-27 yW-13 yW-26 yW-39 xW-1 xW-10 xW-19
RB819-1,2(15t); x=1 or 2 xW-9 xW-18 xW-27

Fig. 5

F82H IEA heat (Heat No. 9753)

JAERI-Tech 97-( Table 1

Heat No.
Chemical compositions Of F82H IEA heat (wt%) Roll No.
Ladle RB801-1 RB801-8 RB802-1 RB801-4 Ladle KG819-2 KG819-1 KG 820-2 KG 820-1 Roll No. Ladle RB801-1 RB801-8 RB802-1 RB801-4 Ladle KG819-2 KG819-1 KG820-2 KG820-1 C 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 0.09 Si 0.11 0.11 0.11 0.11 0.11 0.08 0.07 0.07 0.07 0.07 Mn 0.16 0.16 0.16 0.16 0.16 0.1 0.1 0.1 0.1 0.1 P 0.002 0.002 0.002 0.002 0.002 0.003 0.003 0.003 0.003 0.003 To.N 0.005 0.006 0.008 0.006 0.008 0.006 0.006 0.007 0.007 0.007 S 0.002 0.002 0.001 0.002 0.002 0.001 0.001 0.001 0.001 0.001 Sol.AI 0.001 0.003 0.003 0.003 0.003 0.001 0.001 0.001 0.001 0.001 Cu <0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 Co <0.01 0.005 0.005 0.005 0.005 0.003 0.003 0.003 0.003 0.002 Ni 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 0.02 Cr 7.66 7.70 7.64 7.71 7.70 7.89 7.87 7.87 7.84 7.82 Mo <0.01 0.003 0.003 0.003 0.003 0.003 0.003 0.003 0.003 0.003
0.16 0.16 0.16 0.16 0.16 0.19 0.19 0.19 0.19 0.19
<0.01 0.0001 0.0001 0.0001 0.0001 0.0002 0.0002 0.0002 0.0002 0.0002
0.0002 0.0002 0.0002 0.0002 0.0002 0.0002 0.0002 0.0002 0.0002 0.0002

0.01 0.01 0.01 0.01 0.01 0.004 0.004 0.004 0.004 0.004
0.02 0.02 0.02 0.02 0.02 0.02 0.04 0.03 0.04 0.04
2.00 1.94 1.97 1.95 1.95 1.99 1.98 1.98 1.98 1.98
Table 2 Heat treatment conditions of F82H IEA heat Heat No. Thickness Normarizing _j Tempering 15 mm 750Cx60min 1040Cx38min mm 750C x 60 min 1040Cx40min 7.5 mm 1040Cx37min 750Cx60min 7941

1040Cx38min

750C x 60 min

F82H m IEA fc-

3. 1. 3.1.1. 7.5, 15s 25mm <D&fa 5-14, 2W-23, 42W-18 fcy% 50 x 30 x t (O

3. 1. 2.

5 i ^ ( S ] ^ W g L , JIS G &Jte<*:tf ASTM E45-87 Tstandard Practice for Determining the Inclusion Content of Steelj0 A

3. 1. 3.

WLM 7.5, 15, 25mm (D&fflWL 5-16, 2W-23, 42W-18 cfcy, 30 x 10 x t
3. 2. 3. 2. 1. 15mm (DMfi 2W-10 J:y,j>16xiOLmm

3. 2. 2.

15mm 0)WSL

SH-3000 Fig. 6 AG

S*;ffl5

SSSlB 1 *

Fig. 6 Specific heat measuring system (isothermal method)

3. 2. 3 m

12L (c DL-7000

0.4C/min

3. 2. 4.
15mm (Oflffi 2W-10 <fcy, J

Fig. 7 [c

3.2.2 -e

oc= 1.37-LVt 1/2. a: L:

$* ; a S ATmCD 1/2 (DS

Fig. 7

Schematic diagram of the thermal conductivity measurement

3. 2.5.

Fig. 8 lz JIUiF^LTI*, z 1 ~ioMHz
E: Young's modulus G: Modulus of rigidity v : Poisson ratio Vc: Sonic speed of longitudinal wave Vs: Sonic speed of transverse wave p: Density

Fig. 8

Schematic diagram of Young's modulus and modulus of rigidity measurement using super sonic method

3. 2. 6.

200,300.

Fig. 9 Ic

3000Oe *-efcfci; 15000Oe

xtf-a-

Fig. 9 schematic diagram of the magnetic properties measurement

3. 3. 3. 3. 1. s JIS Z

10kgf(9.8N),
3. 3. 2. a mm 15mm <*)& 2W-10 KUJIS G K K * f r o f c 0 K e ( = l i A * a ^ h ^ 7 IS-10T ;. 50, 100. 200, 300, 400, 450, 500, 550, 600, 650, 7 OC fc O <) Fig. 10 Iz

R3 (|)6.20.02

cb -e-

oo -e-

Fig. 10
Dimension of the tensile test specimen

3. 3. 3. 15mm

1 O m m ) U JIS Z2242 M-50-ICA S ^ c, -20, -50, SEM JSM-T330 \z<>)fem 200 {SfcJ:t; 2000

s Fig.

Fig. 11
Positions of the SEM observation of fracture surface after Charpy test

3. 3. 4. ^ ' J -

15mm (Dm 2W-10

Table 3 I c ^

Table 3 Creep test conditions Test temp. Applied stress ID (MPa) (C) 2W101 2W160 2W103 2W150 2W105 2W75
Expected rupture time (h) 3000

3. 3. 5. 25mm 42W-18

EMF-EB3

& Table 4 Iz,

^ S Fig. 12 fz

Table 4

Fatigue test conditions Gauge length Test temp. ID (mm) 9 7
Total strain range 1.0 0.6

Fig. 12

Dimension of the fatigue test specimen

3. 4. 15 x 15 xO.4t mm

2000 #<7)X>'J ffi-ePfift, 0.05urn AQA-100MPX ::l, -b<=i: Model
STP-300 S-7tf^tf>?($suJ:0.34 m /s:N2)<t ULVAC TypeOMT-050(StiSJt:0.06 m3/s), -ettlcfl|i/K>^tL Model 929-9119 ^ > ^ r ^ 7 K > ^ * f f i f f l U I'J^B#(7)^ J r>/'v-*(DE^Ii 12 x 10"5 Pa -Cfcofco H 5 t a 0 ) l f i i a * Fig. 13 d

ft, 10

0.08, 0.17, 0.33, 0.55, 0.83 deg/s m/e=1 - 4 5

f:QMS>JfS

Orifice Window

(1Omm<|>)

,MIG Transfer Rod

Sample

Valve Ti Getter Pump Manipulator

Fig. 13

Schematic diagram of the released gas analysis system (TDS method)
3. 5. F82H (is F82H z F82H MIc o Table 5 \z HT-9 HT-9 43wx20Lx6t mm
Table 5 Chemical comjposition of HT-9 steel (wt%) P Ni Cr Mo V Sol.AI W S Ta T.O. I C Si Mn 0.19 0.22 0.48 0.018 0.001 0.59 12.0 1.00 0.29 <0.0005 0.02 0.51 0.002||

Fig. 15 ic -[cr* 6

K*4(TP1 ~

o Table 6

Table 6
Estimated test temperature of each specimen position (in the case of 280C operation) Thermocouple Test piece (calculated) (measured) TC2 TP1 TP2 L TP3 TP4 TP5 ^ 6 TC1 Distance from top (mm) Temp (C) 250 220

0.8 ppm

920C),Ci\ AI203sNH4CI

unmmvtD cr

. HCI 2. 3. 4. 5. Cr
NH4CI <-> NH3 + HCI (2NH3 Cr + 2HCI CrCI2 + H2 CrCI 2 +Me CrCI2 + H2 Cr + 2HCI Cr+MeCI 2

N2 + 3H2)

Fig. 14
High-temperature water circulation system for corrosion teset

220 200

TP1 TP2 TP3 TP4 TP5 TP6

/\ z _

Fig. 15 Alignment of corrosion test pieces and estimated temperature

4. 1. 4.1.1.

photo 1 fc<m* Photo 2 ic
ASTM (7) ASTM & J t 7.5 c Ta Ta
4. 1. 2. Table 7 (c JIS JilZ , tz Table 8 Iz ASTM ; Photo 3 Photo 4 izJF

Table 7

Non-metallic inclusion analysis result of F82H IEA heat(JIS method) Type of inclusion (%) Thickness Roll No. Plate ID (mm) Btype A type Ctype L_Total 0.004 5-14 7.5 0.02 0.02 0.05 RB801-5 0.02 KG819-0 0.02 2W-25 0.004 0.04 ^ 0.04 KG819-2 42W-18 0

Table 8

Non-metallic inclusion analysis result of F82H IEA heat(ASTM method) Type of nclusion Thicckness Dt>/pe Roll No. Plate ID Btype Ctype A t i /pe (mm) T H T T H H T H 5-14 7.RB801-5 1.1.5 0.1.0 0.5 KG819-2 2W-1.0 1.0 1.5 0.5 KG819-2 42W-0 1.0 1.0 0.5 5

4. 1. 3.

Photo 5-7 lcs
Photo 1 Macroscopic structure of F82H IEA heat (x5); (a) 5-14, (b) 2W-23

JAERI-Tech 97-C

Photo 2
Macroscopic structure of F82H IEA heat (x5); (42W-18)

ASTM method

JIS method

A type

B type

-:"

D type

C type

*The largest inclusion in the scope was photographed Photo 3 Non-metallic inclusion in F82H IEA heat (5-14)

I 25|im I

x1OO 2W-23

42W-18

x100 42W-18

D type C type

*The largest inclusion in the scope was photographed Photo 4 Non-metallic inclusion in F82H IEA heat (2W-23, 42W-18)

* / :

' '"?
"*.:&& "

"

I 25nm I

Photo 5

Microstructure of F82H IEA heat (5-16); (a) x100, (b) x400

i f - ' "

.&.

Ui ' * * * >

' ' > / '
Photo 6 Microstructure of F82H IEA heat (2W-23); (a) x100, (b) x400

A"

yr'-J *?

*',*" ''&* ^.

*.* : ' , *:-.

*>,

/ " ,

I25nmi

Photo 7 Microstructure of F82H IEA heat (42W-18); (a) x100, (b) x400

4. 2. 4. 2. 1.

fc F82H 7.87 g/cm3

4. 2. 2.

Fig. 16 (z

C 5 h>;t D

Table 9 Specific heat of F82H IEA heat Test temp. Test temp. Specific heat (J/kg-K) (K) (K) 586
Specific heat (J/kg-K) 803

4. 2. 3. Table

5 h>i

Fig. 17 iz

Ehrlich

Table 10

Results of thermal expansion measurement of F82H IEA heat Thermal expansion Thermal Test temp. Temp, range expansion (%) coefficient (1/K) (K) (K) Heating | Cooling^ Heating ^Cooling* -0.137 293-373 10.8 x 10"' 11.5 x 10"' 373 6.086 -0.045 293-473 11.0x10"' 11.9x10"' 473 0.077 293-573 11.2x10"' 6.198 ii.9xi6" 0.313 0.195 293-673 11.7x10"' 12.0x10"' 12.0 X10" 6.443 0.317 293-773 12.1 x i o 6.578 0.445 293-873 12.5x10"' 12.3x10"' 873 0.716 0.586 293-973 12.8x10"' 12.5x10"' 973 0.848 0.730 293-1073 11.7x10"' 12.6x10"' 0.984 0.772 293-10.8x10"' 10.0x10"' 1173 0.876 0.813 293-1273 10.7x10"' 12.1 x10"1.048 1.049

'Coefficient during cooling was calculated with the room temperature after cooling (293K).

4. 2. 4. mmmm

Table 11 iz C 5 D

Table 11 ( z ^

Table 11 Thermal properties of F82H IEA heat Test Thermal diffusion Specific Thermal coefficient heat conductivity temp. (cm2/s) (J/kg-K) (W/m-K) (K) 293 0.31.477 0.0865 33.511 33.1 6.573 0.0785 33.0.33.644 0.0656 33.0.33.0.32.0.30.1
Calibrated thermal conductivity (W/m-K) 31.3 32.5 32.9 33.4 33.0 32.7 32.3 31.9 29.2

1200 1000

-"Pre-IEAheat|

Test Temperature (K)

Fig. 16 Specific heat of F82H IEA heat X10- 6 13

CD O +

O c 10 o
--Pre-IEAheatl -o-IEAheat i

800 1000

1200 1400

03 CL X LJJ

"cc
Fig. 17 Thermal expansion coefficient of F82H IEA heat

o c o O

-- Pre-1 EAh

--IEAheat

' at S

600 800

Fig. 18 Thermal conductivity of F82H IEA heat
JAERI-Tech 97-038 4. 2. 5. Table 12 I Z

Table 12 <D

*fc--<DISJIi Fig. 19 ic
Table 12 Elastic modulus and modulus of rigidity^ of F82H IEA heat Elastic Test Sonic speed of Sonic speed of Modulus of Poisson temp. longitudinal transverse rigidity modulus ratio (K) wavejm/s) wavejm/s) (GPa) (GPa) 3270 0.29 84.0.29 83.3 (83.3) 215(215) 3240 0.29 82.4 (82.3) 213(213) 81.1 (81.0) 210(210) 6.29 80.4 (80.2) 207 (207) 473 6.79.6 (79.4) 205 (204) 523 0.0.87.1 (77.8) 202(201) 5790 0.29 77.3 (77.0) 200(199) 197(196) 3110 0.29 76.1 (75.8) 195(194) 3090 0.29 75.4 (75.0) 73.1 (72.7) 773 0.29 189(188) 183(182) 2990 0.30 70.5 (70.6) 178(177) 0.30 68.4 (67.9) 2870 64.9 (64.4) 923 0.31 170(169) 0.31 61.4(60.9) (1601
4. 2. 6. Table 13~Table 21 j^to Fig. S f c t X x ' J v X f f i l f Fig. 21 -Fig. 28 ( 210 210

(a) Elastic modules

180 160

(b) Modules of ricjidity

(C) Poisson ratio

"S 0.35 c

Table 15 F82H#UEAfcOersted Gauss Oersted Gauss Oersted -45 -425.1 -12000 -50 -497.3 -19440 -55 -565.5 -19330 -60 -637.7 -3000 -65 -707.9 -18490 -70 -780 -1900 -75 -852.2 -18370 -80 -922.4 -18210 -85 -992.6 -17780 -90 -1063 -1500 -95 -1133 -17450 -100 -1205 -16390 -200 -2623 -1200 -300 -4029 -15630 -400 -5439 -14740 -500 -6839 -12580 -600 -8229 -800 -700 -9598 -11320 -800 -10940 -10000 -900 -12230 -8643 -1000 -13420 -7262 -1100 -14500 -5868 -1200 -15440 -4456 --1300 -1622 -1400 -16890 --1500 -10 347.-3000 -5 -4500 -0 200.9 -6000 -5 138.-10 68.25 -7500 -19400 -15 -3.9 -9000 -25 -20 -70.2 -10500 --25 -142.4 -12000 --30 -214.5 -13500 -19430 -35 -284.7 -15000 -45 -40 -354.9 -15000 -19430
-19440 -19400 -19330 -19040 -18490 -18370 -18210 -18030 -17780 -17450 -17000 -16390
, RTC) Oersted Gauss 50 497.565.637.707.9

100 200

852.2 922.4 992.6

19430 19430

-15630 -14740 -13720 -12580 -11320 -10000 -8643 -7262 -5868 -4456 -3038 -1622 -347.1 -275 -200.9 -138.5 -68.25
70.2 142.4 214.5 284.7 354.9 425.1
Table 16 F82HSHIEAL Oersted Gauss Oersted -18950 -18900 -18830 -18630 -18300 -18230 -18140 -18020 -17870 -17680 -17410 -17060 -16520 -15770 -14820 -13710 -12430 -11040 -9568 -500 -400 -300 -3365 -1783 -362.5 -288.3 -208 -4500 -5 133.9 -6000 -10 59.72 -7500 -15 -20.59 -9000 -20 -96.79 -10500 -25 -175 -12000 -30 -255.4 -13500 -35 -331.6 -15000 -40 -416 -15000
-490.1 -570.5 -644.6 -724.9 -805.2 -881.4 -959.7 -1040 -1118 -1197 -1277 -1355 -2931 -4494 -6057 -7607 -9133 -10640 -12080 -13410 -14590 -15590 -16400 -16970 -17350 -17630 -18670 -18830 -18890 -18930 -18950 -18970 -18960 -18940 -18940 -18940
Oersted -12000 -9000 -6000 -3000 -2000 -1900 -1800 -1700 -1600 -1500 -1400 -1300 -1200 -1100 -1000 -900 -800 -700 -600 -500 -400 -300 -200 -100 -10 -45
-18950 -18900 -18830 -18630 -18300 -18230 -18140 -18020 -17870 -17680 -17410 -17060 -16520 -15770 -14820 -13710 -12430 -11040 -9568 -8048 -6504 -4934 -3365 -1783 -362.5 -288.3 -208 -133.9 -59.72 20.59 96.255.4 331.490.1
,200L) Oersted Gauss 50 570.644.724.805.881.959.18940
!5E$PH(4"73K, 200C1) Table 17 F82H IIEAfch Oersted Gauss Oersted Gauss Oersted Gauss Oersted Gauss 509 -45 -438.8 -12000 --50 -509 -9000 -579.18590 -55 -579.2 -6000 -18520 649.725.4 -60 -649.4 -3000 --65 -725.4 -2000 -795.17880 865.8 -70 -795.6 -1900 --75 -865.8 -1800 -17680 -1700 -17530 -80 -17530 -85 -1006 -1600 -17360 -90 -1080 -1500 -17110 -95 -1153 -1400 --100 -1223 -1300 --1200 --200 --300 -4062 -1100 -14720 -400 -5476 -1000 -13710 -900 --500 -12570 -600 -8272 -800 --700 -9647 -700 -1002(10020 -600 -12270 -800 -8653 -500 -13450 -900 -7278 -1000 -13450 -400 -5880 -1100 -14510 -300 -300 -1200 -15430 -200 -200 -1300 -16170 -100 -1619 -1400 -16700 -10 -339.339.3 -1500 -17050 -5 -263.263.3 -3000 --193.193.1 -4500 --128.18600 -5 128.7 -6000 -18600 -58.11.7 -10 58.5 -7500 --11.7 -15 81.9 -9000 --20 152.1 -81.9 -10500 --25 -152.1 -12000 -222.d -30 -222.3 -13500 -292.5 -35 -292.5 -15000 -366.6J -40 -366.6 -15000 -438.8|

400 300

0 -5 -10 -15 -20 -25 -30 -35 -40
Table 21 F82H$IIEA fc-hTOratt14JWJE*S*(673K, 400C) Oersted Gauss Oersted Gauss Oersted Gauss Oersted Gauss 50 538.2 -45 -468 -12000 -612.17260 -50 -538.2 -9000 -684.17210 -55 -612.3 -6000 -754.17130 -3000 -16930 -60 -684.830.7 -65 -754.7 -2000 -900.16620 -70 -830.7 -1900 -971.16560 -75 -900.9 -1800 -16470 -1700 -16380 -80 -971.16380 -85 -1041 -1600 --1500 --90 -1258 -95 -1188 -1400 -15930 -100 -1258 -1300 -4119 -200 -2693 -1200 --1100 --300 -14610 -400 -5552 -1000 --900 --500 -700 -600 -8366 -800 -11340 -700 -9747 -700 -10030 -12360 -800 -11090 -8676 -900 -12360 -500 -7295 -400 -14500 -1000 ---1100 -14500 -300 -15590 -1200 -15180 -3038 -100 -15870 -1300 -16070 -1400 -15870 -10 -310.310.1 -5 -239.16920 -1500 -239.-169.17060 -3000 -169.7 -4500 --101.17130 -5 101.4 -6000 --29.17180 -10 29.-7500 --15 -39 111.2 -9000 --20 -111.2 -10500 -17240 181.-25 -181.4 -12000 -255.5 -30 -255.5 -13500 -327.17260 -35 -327.6 -15000 -397.8 -40 -397.8 -15000 -468
F82H IEA heat (300K, RTL) 20000

-15000 -20000 -15000

-10000

0 H (Oersted)

"ST

II // // /

m -200 -400 -600 -800.mnn -400

/, // //

H (Oersted)
Fig. 21 Hysteresis curve of F82H IEA heat (300K, RTL)
JAERI-Tech 97-038 F82H IEA heat (300K, RTC) 0 -5000 -10000 -15000F -20000 -15000

, 1 " ^

-u>

C -200 D

-400 -600

I ! I / /

Fig. 22 Hysteresis curve of F82H IEA heat (300K, RTC)
JAERI-Tech 97-038 F82H IEA heat (473K, 200L)

10000 5000

0 -5000 -10000 -15000

-15000

600 400
-200 -400-600 -800 -1000 -400 -300 -200 -100 H (Oersted) 400

Fig. 23

Hysteresis curve of F82H IEA heat (473K, 200L)

J AERI-Tech 97-038

F82H IEA heat (473K, 200C1)

10000^

-5000 -10000 -15000 -20000 -15000

/ / / / / / / /

w CD 0 -200 -400 -600 -800 innn -400

i i i /

1/ l '1

Fig. 24

Hysteresis curve of F82H IEA heat (473K, 200C1)
F82H IEA heat (573K, 300L)
-10000 -H (Oersted) 15000 /

400 (Gauss) 200 0

m -200

-400 -600 -800

// // // / /
H (Oersted) Fig. 25 Hysteresis curve of F82H IEA heat (573K, 300L)
F82H IEA heat (573K, 300C)
0 -5000 -10000 -15000 -20000 -15000

400 CO

i i i / / i i i

-400 -300 -200 -100

Fig. 26
Hysteresis curve of F82H IEA heat (573K, 300C)
F82H IEA heat (673K, 400L) 5000

| c o C D

I I I I

m -200 -400 -600

-800 h

Fig. 27

Hysteresis curve of F82H IEA heat (673K, 400L)
F82H IEA heat (673K, 400C) 20000
-10000 -15000 -20000 -15000
400 (Gauss) -200 -400 -600 -800 mnn -400

II / I

// // / l/
Fig. 28 Hysteresis curve of F82H IEA heat (673K, 400C)

JAERI-Tech 97-

4. 3. 4. 3. 1. Table 22 Ic Hv222 Hv217 25mm Hv213

Table 22

Results of Vickers' hardness Thickness Roll No. Plate ID (mm) 5-14 7.5 RB801-5 KG819-2W-23 KG819-42W-18
measurement of F82H IEA heat Hardness: HV2 Ave. 215
4. 3. 2. Table 23 fcJ:tf Fig. 29 [z s Fig. 29 fwl

Fig. 30

Table 23
Tensile properties of F82H IEA heat Reduction Break Total Test 0.2% offset Ultimate tensile yield stress stress elongation of area position temp. ID YS UTS Et Temp RA (MPaJ (MPa) (JIS) (%) (K) (%) 21.7 A 78 2W-10-A 2W-10-20.A 2W-10-20.2W-10-4 18.7 A A 2W-10-17.2W-10-6 (517 A 16.2W-10-15.7 B 493 17.A 2W-10-A 2W-10-21.2W-10-296 A 368 25.23.7 A 91 2W-10-2W-10-26.A
700 - Nt^tlltimate tensile stress 600 500
100 \1 Reduction of area "*"

a. 400

^_ 0.2% offset yield stress

100 Total elongation-* 0

i i 1 i

Test temperature (K)

Fig. 29 Tensile properties of F82H IEA heat

O o O o

o oo o o o o o 1000

11 i i i

o o o o
0.001 0.002 0.003 0.004 0.005 0.006 Test Temperature 1/T (K 1 )
Temperature dependence of yield stress of F82H

n I* Fig. 31

n=(W/m) k: ^ ou:

(W/mK) (Pa) (Pa)

200 Fig. 31

400 Temperature (C)

Thermal stress factor of F82H IEA heat

4. 3. 3.

S/-WUtf-SKB SKB<D*S!ll Table 24 Iz, , L5, L6)lz-Dl^X(D SEM H ig. 32 ( c ^ Photo 8~Photo 10

Fig. 32

, DBTT
Table 24 Charpy impact test results of F82H IEA heat ID L6 L3 L9 L2 L8 L5 L7 L4

316L Amount of desorption (1020molec./m2) 14.5 0.97 ' 0.62 0.34 [ 0.086 16.5 Flux in total desorption (%) 4

0.5 100

4000 Time (sec)

Fig. 42

TDS spectrum of F82H IEA heat (p = 0.17 K/s)

F82HSS 316LSS

Temperature (K) Fig. 43 x10 TDS spectrum of H2 gas from F82H IEA heat (p = 0.17 K/s)
Temperature (K) Fig. 44 TDS spectrum of H2O gas from F82H IEA heat (p = 0.17 K/s)
X101' 6 o A F82HSS |c 316LSS
Temperature (K) Fig. 45 TDS spectrum of CO gas from F82H IEA heat (p = 0.17 K/s)
Temperature (K) Fig. 46 TDS spectrum of CO2 gas from F82H IEA heat (P = 0.17 K/s)

x12 o F82HSS 316LSS

Temperature (K) Fig. 47 TDS spectrum of CH4 gas from F82H IEA heat (p = 0.17 K/s)
JAERI-Tech 97-038 , F82H ffllcfe CO > H2O > H2 > CO2 H2O t CO

Fig. 48 frb Fig. 52 iz

v2: a0: 1/TP, 53 A^b Fig. 57 I c ^ f 0 Table 29 I z j ^ Fig.

Table 29 Gas

H2 H2O CO
Activation energy of desorption Activation energy (eV) Desorption peak F82H ^ 316L 1st peak 0.840.07 0.560.18 2nd peak I 0.670.34 0.620.08 3rd peak 0.700.st peak 0.170.05 nd 2 peak 0.480.12 speak 3.47 0.500.58 2nd peak 0.380.13 3rd peak 0.400.st peak 1.23 0.240.25 2nd peak 0.500.24 1.17 1st peak 0.180.28 2nd peak 0.440.10 3rd peak 0.51 0.20

E d "o

eo 1 CO
Temperature (K) Fig. 48 TDS spectrum of H2 gas from F82H IEA heat with heating rate variation (p = 0.17-0.83 K/s) x1017 io

.E d 6

c 4 _ o
Temperature (K) variation (P = 0.17-0.83 K/s)
Fig 49 TDS spectrum of H2O gas from F82H IEA heat with heating rate
Temperature (K) Fig. 50 TDS spectrum of CO gas from F82H IEA heat with heating rate variation (p = 0.17~0.83 K/s)
Fig. 51 TDS spectrum of CO2 gas from F82H IEA heat with heating rate variation (p = 0.17-0.83 K/s)

d o E S c g

3 "

|3=O.83(K/s) 0.5 0.33

Temperature (K) Fig. 52 TDS spectrum of CH4 gas from F82H IEA heat with heating rate variation ((5 = 0.17~0.83 K/s)

13.5 -,

x10"
Fig. 53 The relationship between disorption peak temperature of H2 and heating rate p.

_).::^".::L:rj

jZT-:pz:

E^:h:^-f::: tffej^^r^]

i "

' ^'._(' 2J

-:|::::

:^fe=t:~

:!:;::

Fig. A-7
Load-Displacement diagram of tensile test at 500C (2W-10-8)

Fig. A-8

Load-Displacement diagram of tensile test at 550C (2W-10-9)

Fig. A-9

Load-Displacement diagram of tensile test at 600C (2W-10-10)

Fig. A-10

Load-Displacement diagram of tensile test at 650C (2W-10-11)
Fig. A-11 Load-Displacement diagram of tensile test at 700C (2W-10-12)

BSlftg.

. _. i

/ : ;.

- 50 - 50

- 0. 5

Fig. B-1
Stress-Strain hysteresis diagram of fatigue test at room temperature

Fig. B-2

(Specimen ID:6, Total strain range: 1.0%, Cycle number: 1-10)
(Specimen ID:6, Total strain range: 1.0%, Cycle number 20)

I -\ S 0

R T 1.0%

: ' L.--pi^i".;

'.' _ ; :

,.| j.--_

1 -_ \ p

fgfgi? : Sit^ :

-rr-^L-

_. L__:;t-Tir

-;jr~;l ''-

._-. r-^i- h

i::-.:f--r:rrrf:

___. j. _.

".". 7 : _ - - L.

: I ::_-.

J^^ii".

Fig. B-3

Fig. B-4
(Specimen ID:6, Total strain range: 1.0%, Cycle number: 30)
(Specimen ID:6, Total strain range: 1.0%, Cycle number: 50)

- i ---r--|-:.-|-n::

. :: -.

l L - -. ;

SSK&8E

~|ausia

I loo ^ ^

IRT 1.0% 500

. |. - j -..

. f _ "~

:.:. "rrp~'L""" " "'r.- "~ i

! i '

- -+ -

r # (X)

Fig. B-6 Stress-Strain hysteresis diagram of fatigue test at room temperature (Specimen ID:6, Total strain range: 1.0%, Cycle number: 500)
Fig. B-5 Stress-Strain hysteresis diagram of fatigue test at room temperature (Specimen ID:6, Total strain range: 1.0%, Cycle number: 100)

r a s us

H T 1.0% 1000

: T i - i

::. - -

[ -- r

5 O -.

-.:.-.-

i-. [ - :

- : - - - : ~

i i~io
r r " " : "ir :;
i=bzt=nz^feferf-3^.j.- -' M - ^ pmfzrr:

.r.L-i:

r-r--4- :fe

ii.r-i.jrr

-tru-t-r:; ^ [ ^

- 5 I) ~r

h- ( ) %
Fig. B-7 Stress-Strain hysteresis diagram of fatigue test at room temperature (Specimen ID:6, Total strain range: 1.0%, Cycle number: 1000)
Fig. B-8 Stress-Strain hysteresis diagram of fatigue test at room temperature (Specimen ID:7, Total strain range: 0.6%, Cycle number. MO)

.IT 0-6%

0.6% i_

i as-ua

"""-i.jTzir:.

.X -.;-

: ".

_L_. _:_..

- _ :. _. _ _. ;

"A-

\~'.A~"~r I -l//F/

-. I -"-.I.

. /. - A

rzrr"'X.-;

-I-/i/tr

1 r 1-IT

E=z^-b-!^ELtz
(Specimen ID:7, Total strain range: 0.6%, Cycle number: 20)
(Specimen ID:7, Total strain range: 0.6%, Cycle number: 30)

50 lasts

IRT io.6%

~r>

-7? 4__t.!.z^;.:

i3~_ZZTl

.-i.! (:-:-

.^ ~ l"

- I -

; ! ! i ! ! :

- 5 (1 J L 1. L J

t ft- (%)

Fig. B-11

Fig. B-12

(Specimen ID:7, Total strain range: 0.6%, Cycle number: 50)
(Specimen ID:7, Total strain range: 0.6%, Cycle number: 100)

R T 0.5% ! IOOO

. _ sssiesjs **LSS

R T 0.5% 500

.j '.

l *gLS

~~iqij-

i- --J

_. ! I

"I-A!' -i

- -j ( -

m& S-n

~r=i-jrp-.

=4:^4^1

)-.-;;

- 8. 5

i II. 5

1 - 0. 5

Fig. B-13

Fig. B-14

(Specimen ID:7, Total strain range: 0.6%, Cycle number 500)
(Specimen ID:7, Total strain range: 0.6%, Cycle number: 1000)

SSkSS.

O-rB 1 0.6% absua |97oo

:. : | _. i.

. -j.% r ~: [/. ---prrprrnzr-/ i -/i

-_-- - I I

^ : -. | :

- 5 I)

>-I--r

0. 5 - J. 5

Fig. B-15
Fig. B-16 Stress-Strain hysteresis diagram of fatigue test at room temperature (Specimen ID:7, Total strain range: 0.6%, Cycle number: 9700)
(Specimen ID:7, Total strain range: 0.6%, Cycle number: 7000)

ft ft 1

-: f *' 7

m L. ~! t' -r T

ft * S3

. B. f>

10"
10" 10" 10' 101 10' 10' 10-

A K mol

E P T G

M k h da d c m n P f a

^ >.

ft (* ft

1 eV=I.602I8xlO-"J 1 u= 1.66054x10" kg

io-' io-'

io10'* 10" 10"' 1 10""

t"

;7. x*/u-+-, f t *. *

'<

r. * * a . a *(>!. 3Ki, &^ /J +

. ft W *

RADHEAT-V4:A Code System to Generate Multigroup Constants and Analyze Radiation Transport for Shielding Safety Evaluation

8C ? # flf ft i?r

Japan Atomic Energy Research Institute
I +:l(i ) Simfirtjfifft*ilUtflfc. SUli u III 7C

'. <i"l")U

fsk IM
.'is : (imresn) im (wffiaj)

rtnr. (jT-6ntsii)

A# fill'Itlll fclll

itl.* (Illif-

Japan Atomic Energy Research Institute Board of Editors Masaji Yoshikawa (Chief Editor)
Kazuyoshi Bingo Takeo Fujino Katsuichi Ikawa Yoshihiko Kaneko Keizo Makuuchi Shigeru Moriuchi Eiji Shirai Toshiaki Tobioka Shigeru Yasukawa Yukio Ebinuma Toshio Fujishiro Yukio Ishiguro Ikuro Kondo Yoshiaki Miyamoto Yohta Nakai Enzo Tachikawa Jikei Yamaki Takeyoshi Yokomura Hideo Ezure Akimasa Funahashi Tadao Iwata Hiroshi Kudo Teijiro Miyata Shinzo Saito Tatsuoki Takeda Akira Yamamoto Hiroyuki Yoshida

JAERI u.t;- Hi.

a >) $ t o
JAERI reports are reviewed by the Board of Editors and issued irregularly. Inquiries about availability of the reports should be addressed to Information Division Department of Technical Information, Japan Atomic Energy Research Institute, Tokai-mura, Naka-gun, Ibaraki-ken 319-11, Japan.
Japan Atomic Energy Research Institute, 1989

*f5fc*ii

a * n f)} m %. ft

<> ts L, # En a m

JAERI 1316
RADHEAT-V4: A Code System to Generate Multigroup Constants and Analyze Radiation Transport for Shielding Safety Evaluation
Naoki Yamano*, Kazuyoshi Minami", Kinji Koyama and Yoshitaka Naito
Department Fuel Safety Research Tokai Research Establishmcni Japan Atomic Energy Research Institute Tokai-mura, Naka-gun, Ibaraki-kcn (Received May 13, 1987) Abstract
A modular code system RADHEAT-V4 lias been developed for performing precisely neutron and photon transport analyses, and shielding safety evaluations. The system consists of the functional modules for producing coupled multi-group neutron and photon cross section sets, for analyzing the neutron and photon transport, and for calculating the atom displacement and the energy deposition due to radiations in a nuclear reactor or shielding material. A precise method named Direct Angular Representation (DAR) has been developed for eliminating an error associated with the method of the finite Legendre expansion in evaluating angular distributions of cross sections and radiation fluxes. The DAR method implemented in the code system has been described in detail. To evaluate the accuracy and applicability of the code system, some test calculations on strong anisotropy problems have been performed. From the results, it has been concluded that RADHEAT-V4 is successfully applicable to evaluating shielding problems accurately for fission and fusion reactors and radiation sources. The method employed in the code system is very effective in eliminating negative values and oscillations of angular fluxes in a medium having an anisotropic source or strong streaming. Definitions of the input data required in various options of the code system and the sample problems are also presented. Keywords: Modular Code system, RADHEAT-V4, Neutron and Photon Transport, Radiation Shielding, Angular Distribution, Anisotropy Problem, Computer Code Manual, Transport Equation, Secondary Gamma-Ray Yield, Atomic Displacement Cross Section, Energy Deposition Factor.
Sumitomo Atomic Energy Industries, Ltd. Fujitsu Ltd.

RADHEAT-V4:

(19871:-5M 13
^1>df fflifc t CK't'fl; f - i RADHEAT-V4 *|fflS6$<!/: *> x r A(i^ifl; f - ) t

uY:&'l~

, RADHEAT-V4 l t"ICii
Program Abstract in NEA DATA BANK Format
1. Name: RADHEAT-V4 2. Computer for which tl program is designed and others upon which it is possible: FACOM- M38O 3. Nature of physical problem solved: Multi-group cross sections for neutron and photon are generated by using the evaluated nuclear data, ENDF/B, JENDL and DLC 15 for transport, heal generation and radiation damage calculations in nuclear reactors and shields. The secondary gamma ray production cross section by the neutron induced reaction and the Bremsstrahlung effect is also generated. The radiation transport problems for shielding designs and safety analyses of fusion and fission reactors are solved. 4. Method of solution: A point-wise processing technique and the Bondarenkn type resonance self shielding factors are adopted to generate multi-group cross sections. One and iwo dimensional SN transport methods and three-dimensional Monte Carlo method are used for shielding calculation. 5. Restrictions on the complexity of the problem: The maximum number of neutron and photon fine group arc 200 and 50, respectively. The maximum number of angular meshes in the macroscopic TOSS section are 64. The energy ranges from 2.' eV lo 16.74 MeV for nculron and those from 1 keV to 20 MeV for photon are available. 6. Typical running time: (a) FAIR-CROSS: At step I. an iron run with 100 neutron groups takes about 3 minutes. At step 2, a preparation of the macroscopic cross section of wulcr takes about 2 minutes. At step 3, the generation of P5 cross section takes about 5 seconds for a material. IMTWOWAY: For a uranium run with 20 photon groups it takes about 1 minute. H I FDEM: For the production of few " -group cross section of a material it takes about 10 seconds, (d) BREM: For the production of Bremsstrahlung data of a material it takes about 20 seconds. lc| DIAC: For a problem of coupled neutron and photon (lOOn + 20/) with 32 angular meshes and 50 spatial intervals it takes 30 seconds for a material, (f) ESPRIT: For a problem of coupled neutron and photon (I5n + 5?) with 48 angular meshes and 50x50 spatial intervals it takes 2 minutes for a material. (Kl MCACE: The time estimation strongly depends on the particular problem, (h) VISUAL: For the production of a graph it takes less than 1 second. (i) POOL: For the operation with a command it takes mainly about less than 1 second. 7. Unusual features of the program: The angular distribution of the group cross section is expressed by the form of Direct Angular Representation instead of finite Legendre expansion. 8. Related and auxiliary programs: RADHAT V4 can produce also the cross sections compatible with the ANFSN, DOT, MORSE codes by using the FAIR-CROSS step 3. 9. Status: 10. References: "RADHEAT-V4: A Code System to Generate Multigroup Constants and Analyze Radiation Transport for Shielding Safety Evaluation", to be published as the JAERI report (1989). "JSD1000: Multi-Group Cross Section Sets for Shielding Materials", JAERI M84-O38 (1984). 11. Machine requirement: Requires about 1 Mbytes of core storage in addition to the usual complement of tapes and the large-size direct access devices. 12. Programming language used: FACOM M-380 FORTRAN-77. Some ASSEMBLER routine are included. 13. Operating System or monitor under which the program is executed: FACOM MST 14. Any other programming or operating information or restrictions: The program is approximately 76000 source cards. Overlay structures are employed. 15. Name and establishment of author: N. Yamano et al., JAERI Tokai Research Establishment, Tokai -mura, Ibaraki-ken, 319-11, Japan. 16. Material available:

ii)For^EBND(.E 8.),

(Region 2) (2.61)
Si) For E B N D ( g ) < < E B N D ( 8 -. ; ) , (Region 1 and 2)

Hmin=Min

(2. 62)
5) Calculation of the cross section from Eq. (2.45) or (2.54) at S angular points which divide the range of the scattering angle into four. (In Fig. 2.6, cross sections denoted from aa to o, are calculated at the cosine of scattering angles from fi0 to //.,, respectively.) 6) Calculation of approximate integral of a' over the scattering angle by using the 4-th order Newton -Cotes formula:
45 where m is the interval of the angular mesh. 7) Test of whether a linear interpolation can be applied between // and //,

(2. 63)

nm--{na+nx)n.

(2. 64a) (2. 64b)

i.e., i ) test of relative error, (condition 1)
ii > test of integral error, (condition 2)

(2. 65a)

(2. 65b)
where is a permissible tolerance specified by the user. The condition 2 becomes severe for a peak of the cross section and loose for the part of small value. Therefore, this condition is useful to decrease the number of the angular mesh in the part of small value. 8) When either condition is satisfied, no additional points are required between fi0 and fi,. Otherwise the angular point jum is added and the step (7) is repeated for the two intervals of (fig, fim) and (ftm, (i,). This iteration is executed until the either condition is satisfied. 9) For other intervals (ji,, Ui), (M* Us) a n d (/"* P < ). t h e same process is executed.

K3 >

Fig. 2.6 Algorithm to determine the optimum angular mesh
The reaction types to be processed are shown in Table 2.4. The scattering matrices are summed up with respect to three reaction types, elastic, inelastic and (n, 2n) scattering reactions, and are normalized to the total scattering cross sections, respectively. The cross section to the scattering to the energy below the lowest energy group is added to the cross section of the lowest energy group. Owing to the DAR method, the angular distributions of cross sections do not take any negative value for all directions. The FAIR-CROSS step 1 can take into account of the up-scattering component of the thermal scattering cross section by using the S(a, /S, T) function as follows:

dQdE where Mn :

(2.66)
number of the n-th type atoms in the molecule, T: moderator temperature (K), k -. Boltzmann constant (cV/K), 0 : energy transfer (E,-Es)/kT, a : momentum transfer (,+ Et- 2fi/EiE/AokT), An : mass of the n-th type atom, An is the mass of the principal scattering atom in the molecule, a h n : bound atom scattering cross section of the n-th lype atom,

where ' and E are the energies of the photon before and after the scattering, /i is the direction cosine of scattering angle. The units of energy and cross sections are the rest mass energy of an electron {mj?) and the Thomson unit (STt/ii^/m^c1)2- 0.6656), respectively. The group to group transfer cross section from group g' to group g by the direction cosine n of scattering angle is given as follows:

f O r l +

I " IT T

-0 where

otherwise, 7'^ Min(E^ 7),
(2. 114) (2.115a) (2.115b)

i8'= *#<(. ,8),

'= l - ^ i - g )

<2"

(2. USd) = , and 0() is the weighting function. To compute Eq. (2.114), the direction cosine ft is divided into 96 points used in the Gauss-Legendre integration. The weighting procedure is performed by assuming the weighting function to be constant or linear. In the case of the constant weight (KON=0 in the 17$ array), the numerator of Eq. (2.114) becomes

JAERi 1316

, {1+(1 , )} ,
] I' The other cross sections are averaged as follows:

(2- 116)

(2.117)
where the integration is performed analytically based on the interpolation scheme for y{E) defined in the DLC-15 library. In the case of the linear weight ( K O N - 1 in the 17$ array), the numerator of Eq. (2.114) becomes

, ^ 1 , ^

f(l-,u)NV-2)ln
where 0(")-a,E'+ 6, for ,. , < '<E f The other cross sect'ons are averaged as follows: (2. 119)

j ^ AE)y(E)dE

(2. 120)
, = ,. , + ( i - 1) ^*~^A-

(2. 121)

N : number of meshes in an energy group (N in the 17$ array), /?,) : interpolated value of the weighting function at y(Et) : interpolated value of the DLC-15 library at ,. The energy deposition factor is also calculated in the form of KERMA factor as follows: /!,= 1.6X10" (}ia/p)Ee (2.122)
where hg is the KERMA factor for energy group g, ilim/p) indicates the energy-absorption coefficient and { shows the mean energy of energy group g. The unit of the KERMA factor is (barn watt sec).
Compton Scoitenng component Lead
Calculated by Klein-Nlthlno rormulo 0LC-I5 MT-5O1 (Bound electron!

Pholon Energy ( M p V )

Fig. 2.7 Comparison of Compton scattering cross sections produced by the Klein-Nishina formula and DLC- 15 library

31. IB4 32. ISC

33. IZ3

34. M07

35. M06

36. IZ1

37. IZ2 38. IBS

39. IB6

: Distributed source input. 0, 1, 2, 3, and 4, the same as for N07 except for the array is designated by the 17* 5 = source on the logical unit NBSO : Radial interior boundary source input. 0= no effect N - source for radial boundary 1 < N < I M entered on cards (15*) N=source for radial boundary ] < N < I M entered on the logical unit NBSO : Axial interior boundary source input. 0, N, N, the same as for IZ1 except for axial boundary 1< N < J M. : Radial interior boundary ar.gular flux output. 0 = no effect N = write angular fluxes for angles with positive mu's at the radial boundary N on the logical unit NBFT N = write angular fluxes for angles with negtative mu's at the radial boundary N on the logical unit NBFT : Axial interior boundary angular flux output. 0 = no effect N=write angular fluxes for angles with positive eta's at the axial boundary N on the logical unit NBFT N = write angular fluxes for angles with negative eta's at the axial boundary N on the logical unit NBFT

40. IZ4

41. IB2
Final total scattering source output. 0 no effect N - final total scattering source is written on the logical unit N Cross section and scalar flux print. n - no effect ! no cross section print 2 - no scalar flux print 3 - both ! and 2 Activity calculation, (see Note 6) N - calculate N zone and point activities - N calculate N zonewize activities Zone balance tables. 0 - n o effect N number of zones specified in the 30$ array for which zone balance tables are desired Fission density output. 0 - n o effect 1 fission distribution is outputted on the logical unit FT07F001 Angular flux output. 0 = no angular flux output 1 = angular fluxes are outputted on the logical unit NAFT 2 = angular fluxes are printed 3 = both 1 and 2

42. M05

45. IB1

44. 1P3

45. IAFT

46. IP4

47. IS2 48. IS3 49. IZ5
(if DATA-POOL output is assigned, IAFT> 1 is required) Angular flux output. 0 = no effect 1 = output angular flux without doing extra outer iteration (used with 1-iteration problems) Not used. Not used. Lower iteration limit for the WWESOL subroutine which solves for the spacepoint scaling factors, (if 0, default = 8) Upper iteration limit for the WWESOL subroutine, (if 0, default =100) Number of inner iterations before a space-point rescaling which is performed in the WWESOL subroutine. (IMG = 2 is recommended) Number of inner iterations between successive the space-point rescalings. (IP2=1 is recommended) Damping constant for the space-point rescalings. (IB3 = 4 is recommended) Not used. Flux guess preparation control. 0 = no effect INN = prepare a flux guess from the logical unit NN as specified by I, write on NFLUX1

cosr/U X

y>n

(3.37)

When the axial direction of the cylinder is parallel to the x or y axis of the system coordinates, the following transformation of coordinate system is performed, a) In the case of parallel to the x-axis: x-z yx zy b) In the case of parallel to the ,y-axis: xy yz z-*x In the case of plane geometry, the coordinates (* yp z,) in Fig. 3.12 satisfy the following equations: x, - x, + ut, (3. 39) (3. 38)

(3.40)

, (y,-yo) From the above equations, we obtain (3.41) The solution for ( exists under the following conditions: t>0, and *>) +(*(-%) ^ ' 2. (3.42b) (3. 42a)
where r, and r2 means the inner and the outer radii of the detector surface, as shown in Fig. 3.12. Then
RADHEAT V4: A Code System to Generate Multigroup Constants and Analyze Radiation Transport for Shielding Sufcty Hvalualion

JAF.RI U l h

we obtain the flux density by using the following equations:
0--WATE>exp j - J V d r l / {x cos 6 (r: r,)\.
where cosf? is the direction cosine to the normal vector given as
COS 8 UU, + VV, + H>M>|,

(3.43)

(3. 44)
and the other notations are the same as those for the point detector. The estimators mentioned above are defined as the expected estimators called the next event surface crossing estimators. We can also use the real crossing estimation. The judgment whether the event is the real crossing or not, is made by te following conditions: t< ft no real crossing, l ft real crossing, O f t real crossing if T> I. (see Fig. 3.13) The computation of the real crossing is perfonned by using the value of the expected crossing at the point A inFig. 3.13. Note that the number of the crossing counts is twice when the estimation geometry is sphere or cylinder, (see Fig. 3.14) (u,v,w)

Surface

Fig. 3.12 Surface crossing estimation scheme for plane geometry in MCACE

(xo.Vo.Zo)

Fig. 3.13 Condition of real crossing estimation in MCACE
surface cresting point Fig. 3.14 Schematic representation of surface crossing in MCACE
The values for flux density, leakage current and angular flux are computed by using the following equations: a) expected crossing ( i ) flux density _ F 1 v 1 WATE , (.,;,, Z | CXP < J / * 1 I

8. TCUT 9. VELTH

CARD Cl 1. IBOOT
CARDD 1. XSTRT 2. YSTRT 3. 4. 5. 6. ZSTRT AGSTRT: UINP VINP
7. WINP Source data on Cards C and D will be overridden by any changes in the subroutine SOURCE. CARD El Format (7EI0.4) [Omit if ISOUR on Card C >0 or if IBOOT - I or if ISOUR - N G P F S - 0 ]
NGPFS values of FS, where FS is equal to the unnormalized fraction of source particles in each group. CARD E2 Format (7EI0.4) [Omit if ISOUR > 0 or if IBOOT - 1 or if ISOUR < 0 and ISBIAS - 0 ] If ISBIAS >0, NGPFS values of BFS, the relative importance of a source in group I, are required. Format (315, E10.3, 15) [Omit if IBOOT-0] : selection of boundary source. if JTYPE= 1 , plane (R, 6) source from MCACE, ( / + = real/expected surface crossing) JTYPE= 2 , plane (X, Y) source from MCACE, (/+ = real/expected surface crossing) JTYPE = 3, axial boundary source from DOT/ESPRIT, JTYPE=4, radial boundary source from DOT/ESPRIT. 2. IDIST : spatial distribution function of total flux for JTYPE^1 or 2. if IDIST=0, read from tape, IDIST = 1, assume constant, IDIST=2, assume cosine disribution,

CARD E3 1. JTYPE

3. JDIST

4. FNORM 5. NSURF

IDIST-3, assume (cosine)2 distribution. : angular distribution function for JTYPE- I or 2. if JDIST = 0, read from tape, JDIST = 1, assume constant, JDIST = 2, assume cosine distribution, JDIST 3, assume (cosine)2 distribution. : normalization factor (n/sec); if zero is set, the value is normalized to the total leakage current. : plane identification number (stored in the bootstrap tape) to be connected. ( J T Y P E - 1 , 2) Format (6E1O.3) [IBOOT- 1 and JTYPE- 1 , 2] center coordinates of a bootstrap surface,
CARD E4 1. XOO 2. Y00 3. ZOO 4. UOO
5. VOO 6. ZOO CARD E5 1. Ull 2. VII
3. Zll CARD E6 1. R00 2. THMIN 3. THMAX
direction cosines of a normal vector to the bootstrap surface.

Formal (3E1O3) [IBOOT

1 and JTYPE

* I, 2]

direction cosines of the R or.tfaxis at the bootstrap surface to X, Kand Z axes.
Format (3E1O.3) [IBOOT- 1 and JTYPE-4] radius of the surface , range of angle. (-n<6^
means on the line of X axis.
CARD F Format (7E10.4) NMTG values of ENER, the energies (in eV) at the upper edge of the energy group boundaries. NOTE: The lower energies of groups NMGP and NMTG were read on Card C. CARD G Format (215, 5X, 3611, 5X, 1311) [Omit if NCOLTP on Card B < 0 ] NHISTR : logical tape number for the first collision tape. NHISMX : the highest logical unit number that a collision tape is assigned. NBIND(J) : J 1, 36 - an index to indicate the collision parameters to be written on tape. NCOI.LS(J): J^= 1, 13 - an index to indicate the types of collisions to be put on tape.

Arbitrary Polyhedron

Face Descriptions (see note below) Termination of Body Input Data END
NOTE: Card 5 of the arbitrary polyhedron input contains a four-digit number for each of the six faces of an ARB body. The forma! is 6D10.3, beginning in column 11. See the ARB write-up in Section 4.7 of Reference 27 for an example.
RADHEAT-V4: A Code System to Generate Multigroup Constants and Analyze Radiation Transport for Shielding Safety Evaluation Table 3.6(a) Variables to be written on tape ( N B I N D ) J IS 18 VariableNCOLL NAME IG U V J Variable* WTBC ETAUSD ETA AGE OLDAGE NREG NMED NAMEX WATEF BLZNT BLZON VEL (IG) VEL (IGO) TS1G PNAB NXTRA EXTRA1 EXTRA2
X Y Z WATE IGO UOLD VOLD WOLD XOLD YOLD ZOLD OLDWT
These variable* are defined in Table 3.6(C).
Tabla 3.6(b) BANKR arguments (NCOLLS) BANKR argument -1 -2 -3 -Called from MORSF MORSE MORSE MORSE MSOUR TESTW FPROB GSTORE MORSE MORSE NXTCOL NXTCOL MORSE MORSE TESTW TESTW GSTORE Location of call in Walk After call to INPUT-to set parameters for new problem At the beginning of each batch of NSTRT particles At the end or each batch of NSTRT particles At the end of each set of NITS batches-a new problem is about lo begin After a source event After a splitting has occurred-commented in column 1 After a fission has occurred After a secondary particle has been generated After a real collision has occurred-post-collision parameters are available After an albedo collision has occurred-post-collision parameters are available After a boundary crossing occurs (the track has encountered a new geometry medium other than the albedo or void media) After an escape occurs (the gemetry has encountered medium zero) After the post-collision energy group exceeds the maximum desired commented in column I After the maximum chronological age has been exceeded-commented in column 1 After a Russian roulette kill occurs-commented in column I After a Russian roulette survival occurs-commented in column 1 After a secondary particle has been generated but no room in the bank is available-commented in column I
Table 3.6(c) Definition of variables described in Table 3.6(a) Variable name NCOLL A type of event: (1) (2) (3) (4) (S) (6) (7) (S) (9) (10) (11) (12) (13) NAME IQ U, V, W X, W, Z WATE sources generated splittings occurring fissions occurring gamma-rays generated real collisions albedo scatterings boundary crossings escapes energy cutoffs time cutoffs Russian roulette kills Russian roulette survivals gamma-rays not generated because bank was full Definition

DATE 84-01-20 INF0(4) 0

!NF0K(5) 0
DATE 84-01-20 INF0NC4) 0 DATE 84-01-20 INF0NC4) 0 DATE 84-01-20 INF0MC4) 0 DATE 84-01-30 INFOMU) 0
INF0N(5) 0 INF0MC5) 0 INF0N<5) 3 INF0H(5) 0

DATE 84-01-24 INF0M(4) 2

INF0MC5) 48
BATE 84-01-24 INFOMU) 0 DATE 84-01-24 INFOMU) 48

INF0M(5) 0 1NF0NC5)

*** INDEX = 8 *** NODE NAME = HA92 ADDRESS FOR THE UPPER NODE DIRECTORY = = 3 NUMBER OF THE LOWER NODE NADAT NDASET NODE NRECS NADWN NO. SELF INF0N(3) 1NF0HC1) 1NF0MC2) 0 NADAT NDASET NO. NODE NRECS NADWN 2 FX11 INF0M(3) INFOM(l) INF0M(2) 0 NADAT NDASET NO. NADWN NODE NRECS 1010 ! 1 INFOM(l) INF0NC2) 1NF0NC2) INF6N(3) INDEX = 9 *** NODE NAME = SELF ADDRESS FOR THE UPPER NODE DIRECTORY = B NUMBER OF THE LOWER NODE = 0 INDEX = 10 * NODE NAME = //// ADDRESS FOR THE UPPER NODE DIRECTORY = 9 NUMBER OF THE LOWER NODE = 2
DATE 84-01-26 INFOMU) 0 DATE 84-01-26 INF0NC4) 0 DATE 84-01-26 IKFOMU) 2

1NFUHC5) 0

INF0KC5) 0

INF0M(5) 16

4. Module Tor Data Base Management
NODE NRECS NADWN NADAT NDASET DATE 1 84-01-26 INFONU) INFOM(l) INFON(3) INF0NC2) FEENO. NODE NRECS NADWN NADAT NDASET DATE 84-01-26 INF0K(3) INFON(I) INF0MC2) INF0MC4) FF.E* INDEX = 11 * NODE NANE = FX16 ADDRESS FOR THE UPPER NODE DIRECTORY = 8 = 1 NUMBER OF THE LOWER NODE NO. NODE NRECS NADWN NADAT NOASET DATE FEE- - 2 6
INF0NC3) INFOM(l) INF0NC2) 4 FEE4 INDEX = 12 * * * NODE NANE = 1010 ADDRESS FOR THE UPPER NODE DIRECTORY = 8 NUMBER OF THE LOWER NODE = I NO. NODE NRECS NADWN NADAT NDASET I SFXO I I INFOM(l) INF0KC2) INF0MC3) 0 !NF0N(4) 95

1NF0KC5) 0 INFON(S) 0

INF0M(5) 0

DATE 84-01-26

INFONU) 0

INF0NC5) 0

f) LIST Command Th LIST command displays the record information for the node name specified by the user. A sample follows as
ENTER COMMAND NAME ===> LIST
ENTER DSN OF DATA POOL ===> J3678i.TESTOO.DATA ENTER NODE NANE OOSGO 1 NAGE.lNFX.1276 RECORI) INFORMATION FOR NODE NAME NAGE.INFX.I276 ITEM CONTENTS 1 NODE NAME 2 TOTAL LENG. OF DATA I>ET = 3 ADDRESS OF A LOWER NODE = ADDRESS OF A DATA SE5 NO. OF SUB-DATA SETS 1 =84-01-DATE OF CREATION 8 DATA I = DATA 2 = DATA 3 = I DATA 4 = I DATA 5 2

4HEGRP 28 S 4HSB32 I I 4R0 T 6RI 4R2 3R3 3R4 2RS 3R8 3RT 2R8 S 3RI0 3RI1 3RI2 3RI3 3RI4 3R15 3R1E 3R17 2RI8 3R19 5R20 BR2I 6R22 6R23 5R24 3R25 2R26 9R27 2R5R1 5R2 SR3 4R5 4HE6RP 4H 777 4HSFX0 I U 4HE6RP 4HFX10 4HIR0N 4HAIR0 I2 T CLFE IRON (ENDF/B-IV) COLLAPSED BY ZONE 1 FLUX OF DIAC CAIR AIR (ENDF/B-IV) COLLAPSED BY ZONE 2 FLUX OF DIAC END OF FILE
5.5 Sampl* Problem for ESPRIT A sample problem for ESPRIT is a gamma-ray skyshine problem. The gamma-ray cross sections for air and concrete used in the calculation are generated by FAIR CROSS step 2. The flux-to-dose conversion factor is also produced by FDEM. The job control cards and the input data are shown below. At the first, the generations of the gumma -ray cross sections for air and concrete are described. The second is the production of the flux-to-dose conversion factor. The last is the skyshine calculation by ESPRIT. The results of compuutions for each procedure are shown in Appendix D. The result of the cross section production for concrete is omitted because the output form of the concrete is the same as that of air. MEMBER NAME > 8:EMCROS.TXT LINE NO:.!. 2. //JCLG JOB 1 // EXEC JCLG 2 //SYSIN DD DATA.OLM'-"' 3 // JUSER *t*tt##*/tt.***#**,##.** 4 T.2 1.3 P.O.2 C.4 SRP S OPTP PASSW0RDtt*tS*** 6 // EXEC LMG0.LM'JI446.FCSTEP2X' 7 //FTOSFOOI 00 DUMMY S //FTI1FO0I 00 DSNiF1,UNITWK10.SPACE(TRK,(50.20)). 9 // DCB-CLRECl-19064.BLKSI2E-iaO68,RECFM"VBS) 10 //FTI3FO0I 00 DSN>UF3.UNITWKI0.SPACE*(TRK. (50.20)). II // DCB*(LRECL*I6804,ELKSIZE'lB804.RECFM-F) 12 //FT14F00I 0D DSNMF4.UNIT-WKI0.SPACE-(TRK.<50,20>). 13 // DCB'(LRECL-19064.BLKSIZE-19088.RECFM-VBS) 14 //FTI8F00I 00 DSN*MF6,UNIT>WK10.SPACE*(TRK,(30,20)>. 15 // DCB(LRECL>l9064.BLKSIZE*19068.RECFM>VBS) 16 //FT17FOOI DD DSN*UF7.UNIT*WK10.SPACE*(TRK. (50.20)). 17 // DC3(LRECL'19064.BLKSIZE1906S.RECFM'VBS> 18 //FTI8FO0! 00 OSNF,UNIT(KtO.SPACE<TRK. (50.20)). 19 // DCB-(LRECLI9OB4.BLKSIZE-19O6.RECFM-V6S> 20 //FT2IF00I DO 0SN>UFA.UNIT'IIK10.SPACE*(TRK. (50.20)). 21 /' DCB-(LRECL-l9064.BLKSIZE-19068.RECFMVBS> 22 //FT22F001 DO 0SN-MFB.UN 1T-WK10.SPACE-(TRK. (50.20)). 23 // DCB*(LRECLI9O64.BLKSIZE-I9O6.RECFMVBS> 24 //FT23FOO1 DD DSNUFC.UNITWK10.SPACE<TRK. (50.20)). 25 // DCB(LRECLI9O64.BLKSIZEI9OBB.RECFMVSS> 28 //FT9IF001 DD 0SNJ1446.P00L87.0ATA.0ISPSHR.LABEL-(., OUT) 27 //SYSIN DD * 28 FAIR-CROSS STEP-2 FOR GAMMA-RAY SKYSHINE PROBLEM 29 (UNIT FXSN-91 <ENO 16 4HG09 I 1 T 31 3** 1.S60E+6 I.330E+6 1.0S0EB 0.800E*B 0.600E6 0.400EB 32 0.300E+8 0.200E+8 0.100Efi 0.050E*6 T 33 AIR CROSS SECTION BY EMPIRICAL FORMULA 4HAIR 0 3B PAGE

FEM : self-shielding factor for the elastic cross section FFM : self-shielding factor for the fission cross section FCM. self-shielding factor for the capture cross section k) SFX0/SFX1 Data Form level 1 node : EGRP information same as the SMT data form ditto data level 2 node : id. name information data where IGE IGE, IM, JM, IZM, MM PREAD4 (N, NCOM, I M + 1 , R, JM+1, Z, IM, MA, IZM, MZ) identification for the geometrical configuration 1-slab 2-cylinder one-dimensional configuration 3-sphere 4-(X-Y) 5-(R-Z) two-dimensional configuration IM JM IZM number of interval meshes for X or R axis number of interval mesbes for Y, Z or 6 axis (for the case of one-dimension, JM= 1) number of zones number of angular quadratures logical unit number of DATA-POOL comment of the node (20 worjs) spatial interval meshes for X or R axis (cm) spatial interval meshes for Y, Z or 6 axis (cm) zone numbers by interval material numbers by interval

N NCOM R Z MA MZ

level 3 node : SFX0/SFX1 SFX0 shows forward scalar flux and SFXl means adjoint scalar flux for the one-dimensional configuration.
Appendix C Record Format of Dt Stored in DATA-POOL
information ING, IGG, ITH, 0, 0 data PREAD1 (N, NCOM, IM XIGM, FLX) where ITH : solution indicator (0: forward, 1: adjoint) FLX : scalar fluxes 1) SFX2/SFX3 Data Form level 1 node : EGRP information same as the SFXO/SFXI data form data ditto level 2 node : id. name information same as the SFXO/SFXI data form data PREAD4 (N, NCOM, IM+1, R, JM + 1 , Z, IM x JM, MA, IZM, MZ) where notations are the same as those of the SFXO/SFXI data form. level 3 node : SFX2/SFX3 SFX2 shows forward scalar flux and SFX3 means adjoint scalar flux for the two-dimensional configuration. information same as the SFXO/SFXI data form data DO 10 1=1, IGM 10 PREADI (N, NCOM, IMXJM, FLX) where notations are the same as those of the SFXO/SFXI data form. m) AFX0/AFX1 Data Form level 1 node : EGRP information same as the SMT data form data ditto level 2 node : id. name information same as the SFXO/SFXI data form data ditto level 3 node : AFXO/AFXl AFXO shows forward angular flux and AFXl means adjoint angular flux for the one-dimensional configuration. information data ING, IGG, ITH, MM, IPMESH PREAD3 (N, NCOM, MM, W, MM, DSN, IPMESH, NOANLL) DO 1 1=1, IGM 1 PREADI (N, NCOM, MM X IPMESH, AFX) solution indicator (0: forward, I: adjoint) number of angular quadratures number of spatial intervals angular quadrature weights angular quadrature cosines spatial interval numbers angular fluxes

.0.0.0.0. 0.

9$ 99 00
0.0 .0 0.0 0.0 0.0 0.0 0.0 0.0
0.o 0, 0 ft. 0 0. 0 0.0 Q.0
3.7<*2E.*00 3.74*71*00 3.7301C*0B 3.7504E*O 3.75ME*OO 3.75MC*O0 3.730*1*00 3.7311**00 3.7521t*Oa 3.75r.OC 3.74SSt*M 3.7474E*M 3.7737C***

<.0.0.0 i.0

0.0 C.0 0.0 0.0 o.0 0.0 0.0 0.0 0. 0 0.0
3.74aze*o 3.Y4BXE*O* 3.74BZC*OO S.>411|.00 3.74Blt*OO S.7411tOO 3.?4Blt*00 3.74Blt*OO
Appendii D Simple Output Lists of RADHEAT-V4
0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
3.S4MC-02 4.I27IE-I2 4.2O3E-02 S.0>79E-0>
t.S47t-02 L2tllE-tl 1.4M01-0I 1.07111-01 1.UH1-I1 1.20101-02 I.IS7M-II >.74111-02 t.MME-*2 0.33321-02 3.31011-02 I.7I30E-03 I.1USE-I4 1.33I1E-0I 1.7SI4E-M
1.1I10E-02 I.401IE-02.472*E-I3 t.tltlE-OS

O.I O.I O.I

.0 .0 .0
O.I O.I 0.0 O.I O.I I.I O.I O.I 0.0 0.0
1.0 B.O 1.0 1.0 1.0 1.0 1.0 1. 0 1. 0 C.0 C.0 t.0 (. <. <.0 i.0 0.0
0.0 0.0 0.0 0.0 0.0 0.0 0.0 - 0.0 0.0 0.0 - .0 0.0 0.0

0.0 0.0 0.0 0.0 0.0 0.0

o.o o.o
0.0 0.0 0.0 0.0 0.0 0.0 0.0
AFTER M W 17 1AM AIOVE At H i Illusion CHOII 9ECTIMI <MMTH I I H I SECTIM) HEM OUTPUT T A l>t P O i O OL N M >EMP-llirK-t27- VM AE
m i l no. SEl HANI F WIITTCN MC0MS at Mcoiot
i - J1444.POQLI7.IATA t 1U4S
IME R N t-lM-l274- FT! UE ' larOMATIOH 0l M M y l A I I LOtlCAL HIIIT HO. | l > l i IET ADE J144t.P0OLI7.IAT*

MIDI MC0MI

no. of mi mil m m i

. ItlM

0 O.ttl 7 o.tttt O.ttl > O.ttt 1.tt? O.t71l O.MSO O.tSS4 O.tlfe2 O.t2OO O.t204 O.IIOt O.ttIS O.tOI 1 O.tttl o.tst r.t47 *.t41.t!3.to? 0.C40 O.tS7 l.tll.MOI l.Mtl.ttt ulSl
1.0 l.tttZ o.tttt O.tttl l.tMS o.ttl? O.MSI O.tIM O.t77t O.tAtO O.t4|l 0.0417 O.fl?2 O.ttti O.tllS O.ttM

><-

o.ttto LM0 O.tttl O.ttt2 O.ttM o.ttu O.tM2 O.ttit l.MM l.MM I.MM .MM LOOM.tM? .MM O.tttl .MM .ttM.Mt *.M7I .MM l.MM l.Mtl .MM.ttM .ttM .MM .MM .MM 0.MU.tttl I.MM l.MM l.OMO l.MM LMM l.M0 i.ttts l.Mtl I.MM l.tttl 1.MI4 1.M0S l.OMO l.OMI LOOM.M01 I.Mtt I.MM.Ml L.MI I.Mt7 1. M M

4-H* 5 CO 9.41941C-43 * 0.0 3.104S7I-OS 0.0 4.941491-43 I.l2*t-l
!> I " 9. % 0-K* 4 0.0 0.0 0.0J 0.0 JUKI 9 THUy AMftL 9 M I AMVI 7.S24171-0S 4.124131-04 ?.*0444t-44 1.I9721E-43 MI4L 11 TtMU *NftL 17 S M I * t AMVt t - *4K4VP M.

SKILL SOKCC 4L 1

t-n* i 4.*

%mm* 2.

a*o i

4.4 I7E-02

A 4 HL 2 TMII MI4L 9 *ftHt At A 4 E 0W 1.M7WI-O2 f , S * 4 S - 2.93I7OC-O2 t.1401t>

0.0 3.O97O4E-T'

4-1* + 1 C*H* 0.0 0.0. 4).4 L 2 1WII1 MM4L 9 *KHC At AOOVt 2.3*1371-02 2.2SI44I-02 2.1ZB41I-O2 l.*9S02C02
net 1 rmu M I L SAHI At AOOVC

1.01X091-02

1.*L41*I-31

1.4t434t-O2

l.S3207t-l
- 1 CO* Z ? t>N* 4 4*0* S 0.0 0.0 0.0 0.0 0.O AML 2 IHRU ANIL 9 tAW At AMVI 1.I777IE-02 l.O3t*2t-O2 0.99*441-03 7.790401-03 4.7*44-OS AML 11 TMM AML 17 tME At A0BVI 4>0M0W M. N- * 1 0.0 1.7*2441-03 0.0 I.SO74K-O3

4.tl9ME-0>

4.194391-0*
0,0 0.0 0.0 0.0 AML 2 1MB AML 9 SAM At H 4 V I 3.3429BE-03 X.M29BI-O* 2.S4O10E-01 2.14)141-03 AML 11 TH4U AML t 7 SAW A AOOVt S

0.0 t.U*90t-03

SHELL sevtce 0.0

10 > 1

C H M O W no.

SHI 0.0 0.0 0.0 0.0

4kL 2 7Nttt AML 9 S*W AS AMVB 4.94911E-04 *.I3S34E-O4 4.03O42E-04 4.2433M-04 ANAL THAN A M L 17 SAW A t AOOVC 2 - MOW*1 M. 0.40 < 0.0 4
SKILL t O M I C I III INlfkVAl AML 1 0.0 I

2 IMAM AML

S 2 0.0

17 SAW At A M V I

*N 0.0

SHELL SOWRCt IN IMTEBVAL

Z - A-4M#f M.

S4 0.0

AML 4-Ht I I 3 S I M 1 0.0 0.0 O.O O. AML 2 TMU AWL 17 SAW AS AMVI
RADHEAT-V4: A Code System lo Generate Multigroup Constants and
l.43ll-l 0.0 1.744t2E-43 3.323726-43 4.43047E-43 2.7SO7tE-42 2.*.443tE~Q2 2.34S2IE-42 3.71422I-O2 3.2394E-4Z s.sazttE-42
ABSOtMKM 1.34*741-43 7.I2144E-I9 1.2S324E-44 2.444791-44 J.119471-44 1*2Z3tSE-43 3.4tt4U-43 3.U31IE-43 l.taittE-BJ i.teitai-42 2.32t27E-8J

aap. I I 1.I04IN-I t.4 i.lPtlltH l.llltil-l 4,4 4.4 4.4 4.4 4.4 4.4 4.4 t!t4tlll-l n.t.> a.t a.c t.t a.* a.t a.t
1.4llBtE-4* 0.4 4.7ll-44 l^tt*l*l-tl 4.4 4.4 4.4 4.4 4,4 4.4 4.4 4.4 4.0 4.0 4.4 I.7t4ll-t* 4.4

7.*1I4II-I

I.1U77I 4.4 0.4 0.4.IU0t!S.7JI*Jf4.4 4.4

i t titan <

CUP. 1 *

3 I M t A1 AMWt

4B.P. 17
4.704.I3E-04 4.43Q7W-44 1.470 31E-K t.O 0.0 CO 0.0 0.0 4.4 0.4 4.t o.a o.o 0.0 0.4 1.4 t.4 4.4 4.4 4.4 4.4 O.t
4.113*71-04 3. * t ) t * U - M t. l t * K - t * 0.0 t.t t.t
4. 74at B-t4 3.97**31-04.X3740E-t9

t.t t.t t.t t.t ot.

U P. IS

t a p. a

4. 7tl*H-44 4.A1441E-44 1.4M43B-44

L.tlltlt-O*

M P. 3* MP. H 1. 0 U t f - 0 * 1,74 3*31H t.t Ot. s.maii-** 1.1013M-IS *. M l l t l - 4 * 1.4713SI-t9 I. U l 011-4* >.tlK-H

i.nnti'ir

.11074E-4T
4.4 4.4 4.4 1.4 a.t 4.4 0.4 4.4

!t7tltE-M

.17MI-M.4XI1H-**
4.UMM-M 4.1M14I-M 1.41MU-M 0.434M-t 4.mSl!-Bf 1.1474f-tt 1.9 M i l t-t>
1.3t37H-lt r.lSlfflt-Sl l.t17E-11 1.411UI-11 X.147911-11
t.t t.t t.t t.t t.t t.t t.t

1.4 1.4 4.4.

o.a alo a.o

o.t t.t t.t t.t o.t t.t

*!* a.t 4.0 4.4 t.t 4.4 t.t 1.3tl*4K-lt 4.4 l.t l.t

t.t t.t t.t t.t

a. 4 E - t l 4.4.M14H-M 4.iu-ia 4.41S7SE-11 4.B ,mM-tt l.lSMMfl-14 4. l l * l t E > l l 4.4 t7ttH-*t 1.1U4-11 2.4J444C-11 . * i.*trtu-ia o.a._ 7.4744K-I1 4.4 ,9I4*3-** 3.11*411-11 7.M*t4K-ll t.t.1104M-44 l.OMU-ll S.Mri-II.t

4I19H-1*

4. M M - M 4.147ffll-ll a.ttirte ? >. M I H I - I I

9.4V741E-M 1.41J3M-*?

4.4 4.4 t.t

O.t O.t t.t

3.fl7S3E-*4
7 t M I Ptl. LOfilCM. tMtl M. *

1 * SAM AS MOVE t l

H4. 4f MITttH atCORQt HMIM MtMII

a m SET ki

Ji44*.Pt.t?.4iiTk

Tt *10

RADHEAT-V4: A Code System to Generate Multigroup Cnnsunts and Anclyze Radittion Transport for Shielding Safety Evaluation
D.7 Sample Problem for ESPRIT
MEMBER NAME > B:EMCROS.TXT LINE NO: 3 I //JCLG JOB 2 // EXEC JCLG 3 //SYSIN DO DATA.DLM-1**4 // JUSER SfSSttSi.SS.ttftit.ittS.tS S T.2 1.3 P.O W.2 C.4 SRP