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Slides Depicting Structural Analysis Methods Testing, Properties & Analysis & Test Results for C-E 16X16 Fuel Assembly.From 781214 Presentation to NRC
	ML19263C069
Person / Time
Site:	San Onofre
Issue date:	12/14/1978
From:	; ABB COMBUSTION ENGINEERING NUCLEAR FUEL (FORMERLY
To:	;
Shared Package
ML19263C070	List: ML19263C069;
References
	NUDOCS 7902020269
	Download: ML19263C069 (31)
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SAN Orl0FRE UtlITS 2 AllD 3 DOCKETS 50-361 Afl0 362 SLIDES DEPICTIflG STRUCTURAL AtlALYSIS ftETHODS TESTIflG, PROPERTIES AllD AliALYSIS AtlD TEST RESULTS FOR THE C-E 16X16 FUEL ASSEMBLY FOR SAfl Ofl0FRE UtlITS 2 AtlD 3. fl0N-PROPRIETARY VERSI0ft PRESENTATI0ft T0 flRC Ofl DECEftBER 14, 1978. COMBUSTI0ft EtiGIflEERIllG, IllC. flVCLEAR POWER SYSTEftS POWER SYSTEMS GROUP tilflDSOR, C0ftflECTICUT RECEIVED DEC 2 61978 790202 c}69 LDMfGO

i t = t e LEGAL !!0TICE ~ This report was prepared as an account of work ~ sponsored by Cc7.bustion Engineering, Inc. !!either Combustion Engineering ncr any person acting on its behalf: a. Makes sny warrar,ty'or representation, express .Q or ' implied inclucing the warranties of fitness for a particuler purpcse or cerchantability, uith respect ~ to the accuracy, ccmoleteness, or usefulness of the ' informatica contained in this report, or that the use of any infomaticn, apcaratus, tethod, or process dis-closed in this report cay not infringe privately owned rights; or .s b. Assuces any liabilities with respect to the~ Use of, or for da:Eges resulting frca the use of, any ' infomation, appartus, method or process disclosed in this report. ~ e e 9 =-

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1 ~ I. IrlTRODUCTI0tl IIe IECH!!ICAL P R E S E fl T A T I O fl A. D E S I G il DESCRIPTI0ft B ', ArlALYSIS C ',' TEST . D ', D E S I G il EVALUATIOff ~ III ',' D I S c u S S 1 0 rl \\ ~ ~t / . s w s

~ g FUEL SEISMIC DESIGN PROCES8 ~. ~ FUEL ASSEMBLY DESIGN I l L FUE L ASSEMBLY PROPERTIES DYNAMIC SEISMIC ANALYSIS rM ~q SEISMIC EXCITATION I I FORCES, ETC. LOADS,lMPACT 1 I1 DESIGN EVALUATION = I e I li GRID STRENGTH' TESTING GRID 3TRENGTH \\ l l / l. STRESS LIMITS: l ~ s

- - i 60!!GS-II FUEL ASSLf'! LY l I ,p SEIS!!!C l>ESIG:1 FEATUI:ES i \\ ~. 2 .s, s.- l .M M M. l I I i

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STRESS-RELIEF AllNEALED y isisiticiaisicis GUIDE TUBES O e: _;_n b, s.ai a.s s i s i s i s i s i.,s,t .c -g .s ~ - is;risisisitar

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.I,. .: g CESHOCK .!~ .o-s l I

DYNAMIC RESPON-E OF MULTI-SPRINGIMASS SYSTEMS '

i

AXIAULATERAL MODEL CAPABILITIES r
PRELOADS, TENSION-AND COMPRESSION-ONLY SPRINGS, AND i,

l NONLINEAR SPRINGS

GAPS, IMPACT, COEFFICIENT OF RESTITUTION

'l e a - S DAMPING

HYDRODYNAMIC MASS MATRIX i.

i i

ARBITRARY TIME DEPENDENT EXTERNAL LOADS
NUMERICAL INTEGRATION TECHNIQUES: RUNGE-KUTTA-GILL AND NEWMARK
0UTPUT: DISPLACEMENT, VELOCITY, ACCELERATION, FORCE, SHEAR, IMPACT LOAD AND M0 MENT TIME HISTORIES i

1

'\\.. i S JMMARY OF THE METHODS EMPLOYED TO VERIFY THE CESHOCK CODE TYPE OF CESH0CK PROBLEM METHOD OF VERIFICATION I. NONLINEAR, DAMPED PULSE EXCITED SYSTEM ' PUBLISHED CLASSICAL SOLUTION A. DEGREE OF NONLINEARITY VARIED ..c.,. 'C' (DUFFING OSCILLATOR) . ;i,;

8. lYPE OF PULSE VARIED

+ II. MULTI-DEGREE OF FRE-' 'i BASE EXCITED INDEPENDENT COMPUTER CODE LATERAL SYSTEM WITH FRICTION, GAPS, AND DAMPING A. WIll10UT HYDRODYNAMIC MASS B. WITH HYDRODYNAMIC MASS .? III. FRICTION ELEMENT WITH STATIC AND ANALYTICAL SOLUTION DYNAMIC COEFFICIENTS OF FRICTION A. COEFFICIENT OF FRICTION VELOCITY NON-DEPENDENT B. COEFFICIENT OF FRICTION VELOCITY DEPENDENT IV. IMPACT El.EMENT WITH COEFFICIENT OF ANALYfICAL' SOLUTION RESTITUTION V. HYSTERESIS ELEMENT: INDEPENDENT COMPUTER CODE i TWO DOF SYSTEM WITH SPRING AND GAP ELEMENTS i

NONLINEAR, D AM PE D P U L'S E ' EXCITED SYSTEM I DUFFING OSCILLATOR K(x) dg. 0.6 s M ~ F(t) o q 9 } [ C 0.4 MR + Ci + K(x) = F(t) 2 z.-. 0.2 ' M + 0.1x + x(1 + x ).cos2t ' ' 4: 3 0 1 21 3 5 8 9 Id 11 i o 13 TIME, SEC 5 o_ $-0.2 -0.4 -ANALYSIS -0.6 o o CESH0.CK

.......__u._____..- IMPACT ELEldENT WITH COEFFICIENT 0F RESTITUTION 10 SPRINGIMASS MODEL K M O= !! $ M 8 1 2 - V = 10 INISEC o 6 e=1.0 \\ 4 COEFFICIENT OF RESTITUTION 8 e=0.0 2 m 'z -e=0.5 l ~ 0 e=0.0I z u. O 7 b o e=0.5 9W4 e = 1. 0 4 -8 -10 0 20 40 60 80 100 120 TIME, MILLISECONDS

!r t l ', TWO DEGREE OF FREEDOM HYSTERESIS PROBLEM WITH GAPS r i i i i 300 t r $J 2 1 K13 APPLIED. FORCE a t . 200 s. -{ W M'3 = w E f P 2 H23 f K23 [ j FORCE = F12+F23 +F 100 3 2 DISPLACEMENT = DISP. N0DE 3 23 0.1 0.2 0.3 H .3 -0I2 -0.1 b SPLACEMENT, INCHES F RCE 'O X /. DISPL .y..r ^ -100 FORCING FUNCTION { ~ = m +250

CESH0CK

-200 ur 0 N

ANSYS O

-250 1 2 3 p TIME, SEC -- -300 ~ j s, f

BASE EXCITATION PROBLEM INCLUDES, DAMPING, GAPS II. HYDRODYNAMIC MASS \\ 500 BASE ' ' ACCELERATION TIME HISTORY ~ 0 10 20 MSEC 8 400 LUMPED SPRINGIMASS MODEL 948 a 10 c 7 l 11 c'6 17 ,,5 5' .13 f 4 " 300 t 14 - e 3 5 15.-.w-2 E nA m ".1 BASE I ACCELERATION m 9 25 x m 200 wm cn o'CESH0CK 100 0ANSYS g 0 0 5 10 15 20 TIME MILLISECONDS gun. 4

. m _. - REL TESTIfra STATIC LD@ - IElICTIQ1 e.e. FORED VIEPATI0fl s' RfRE IFFACT s. ERIZDtiTAL ~ VERTICAL SPAER GRID IFPACT PBOULLH DROP PLIIK / 4

SCE - C0'RE INTERNALS MODEL o 29 10 r//AV///////// 28 ff v / / / / /.v / / / / / / " 19 / UGS u /F 9 CSB% RPV [ o 27 // I / FAP CORE . o 18. 4 8 / 26 SHROUD / SHROUD d b*-~\\/ / " ' / / =d b/ / CORE / 25 >-{ bw-o 34 0 39 cH H 25 0 17 [ 7 M / 43 / 24 o-l!=m 33 38 <H }-o 24 o 16 f 6 / 42 / o 15 4 5 23 <HH 32 > 37 <H H 23 / 41 / 22 >.{ H 31 36 o-w.-{ 1-30 o 35 <H p,21 o 13 [ 3 / f f20 / / /V /// / / '/ / / / / / / / / / CSP 12 \\ l}- 2 -PERIPHERY FUEL )Sb 1 R0W 3 11 f 1 \\ SNUBBERS ,e e e

, [ CORE SHROUh GUIDE LUG FUEL 2 l hw/www/wwwme/wmms/mmimms wh]H {f'M d [ ELE 13 18 23 28 33 38 43 48 53 58 63 68 73 78 83 7 h-{ HH } $ >-{ H H H >-{ H >-{ H >-{ }-o-l H >-{ H >-{ H >-{ h >-{ H H H >-{ H >-l H >-{ H 7 12 17 22 27 32 37 12 47 52 57 62 67 72 77 82 6 <>-lHHH:-lH>-lH>-lHHH>-ll y-lHHHHHHHHHHHHHHHHH> 6 i 11 16 21 26 31 36 41 46 51 56 61 66 71 76 81 5 o-lH>-1}-y-l}-c-{H>-i} 'H H +-l}-o-i H >-lH >-{ H >-lHHH>-iH>-lH -lHHH'S ~ CORE SHROUD 10 15 20 25 30 35 40 45 50 55 60 65 70 75 80 4 >-lHHH -lH>-lHH}-e-lb -lHS-l}-o-l}-o-lH>-lHHHHH:- HHH'- H 4 FUEL ASSEMBLY 9 14' 19 24 29 34 39 44 49 54 59 64 59 74 79 (TYP) 3 u-l H >-{ }-H H -l b >-l }-o-J H :-{ H H H >-{ }-o-l H >-l h >-l H >-l H >-{ H >-l H>-{ H, 3 f 1 '//////////////////////////x:////////////////////////////, A"fe """ "' S N CORE I I 6 I6 I II I II II 6 6 SHROUD R 3-3 . DETAILED HORIZONTAL CORE SEISMIC MODEL 7 6

y. SCE HORIZONTAL COUPLED CORE INTERNALS _. 0 C A. MODEL I g F . UGS CYoupCR y c2 ,c; v2-Sc .gg ,co ,SS 57 , gg-CSA "48' "49 S1 SL 5] 51 50 v v l 'fW*" U S /r 47 3<-lWil' ,4g ,42. ,44 .,g9 45 4a c v te3y ,m 35 37 "3e go yg e e -' "4 27 .17 J z. j" ' {o_ si 33 2.1 19 <4w{F y 16 FAPJ }}-MWl25 7c56 14<-ji4W 72. " S 2-

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."!gg(:.=DEtAllED 'CdRE SNISMIg N0DEFNESULT.S-O ons now or .t7. FUEL ASSEMBLt ES 1 h e 0 I h O e t b q f am e 4
S.CE. ; DETAILED ' CORE . SEISMIC MODEL RESULTS ~
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ONE R'OW OF 17 FUEL ASSEMBLt ES meWW 4 1 1 f J G 6 4 g. T emu j t
S.C.E. DE' TAILED "CORb MODEL' O CA R ESidL T25. n '. ONE Row OF
17. FUEL ASSEMBLIES
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+ V Z,3 I I l COMPARIS0N OF TYPItat L0aD_ DEFLECTION CilAP.f.CTERISTICS-
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SSE GUIDE TUBE STRESS CALCULATION STRUCTURAL ANALYSIS INPUT 1. HORIZONTAL SSE DEFLECTED SHAPE FUEL ASSEMBLY SSE STRESS 2. VERTICAL SSE ) LOADS STRESS ANALYSIS INTENSITIES 3. NORMAL OPERATING LOADS . ~ - G e 0
OUTLET _BitEAK GUIDE TUBE _ STRESS CALCULATION STRUCTURAL ANALYSIS IflPUT 1. LOCA OUTLET BREAK - DEFLECTED SHAPES ^ 2. LOCA OUTLET BREAK m STRESS ANALYSIS STRESS INTEfiSITIES VERTICAL LOADS 3. NORftAL OPERATING ~ LOADS e
S e t COMBINED SSE/LOCA GUIDE TUBE STRESS CALCULATION 4 FUEL ASSEMBLY STRESS AtlALYSIS e 1. LOCA INLET BREAK e STRESS INTENSITIES COMBINED SSE/LOCA SRSS AT COMMON 2. SSE STRESS 3_ y GUIDE TUBE STRESS INTENSITIES ASSEMBLY LOCATIONS INTENSITIES 3. LOCA OUTLET BREAK STRESS INTENSITIES e o e
1 .\\ e e. ./ .g .c. l i ~,i Faulted condition Criteria Sum.arv .l ..,l s /s 3 Component Statement of Criteria Numerical Limit m 2.4 S 1. End Fitting P a
Castings, mF x 2.4 S Pb+P s
m 2. Upper End P,< 2.4 S, P 9 Fitting \\ osts mF x 2.4 S i Pb+P s a L 3. Upper End Calculated Shear Stress Fitting Not to Exceed Minimum Springs Yield Stress in Shear 3,4$ 4. Guide Tubes Pm .7 5 w-- u mF .7 5 i P+P b s u F = 1.39 g 5. Spacer Grids Impact ' Load Less Than Tested Grid Strength at Temperature ,') ~ . f.' ~ 6. Fuel Rods ,PmS y aFs. x S b+P P y F = 1.36 s _m... .~. e .L-
I I e .M M M. l l 1 l .i.. l i jl J 3 -same=rr=s SPAll 11-NC .=.:.==, ~ /Gh.__-sisisisiisu u = \\',:) s :: - - .=, HID-1 SPACER GRID (6) /s v. . m : -s_ SPNI 10 4 - a ' st:tCt:t*tattf3tl _;_- w ) ? I { Spg 9 . - fm:9 naurainen: : g. _ _4sma +p o s g u n s"m sN --:'f A ~ ~ SPAff 8 3 c .i s .i SPA!{ 7 ,e. 5-::': g a --L-n e u. n : e n. n). a. -o -- HID-2 SPACER-GRID (4) M... e SPAll 6 5 t ~ ~p u n :ss ienici ~ s' g. SPAft 5 ur.4 :- c o 18303:I*131:1313 g - ^:a m /.mst SPAft 4 m grengs;<;t:igiar)- . :.g .y_:., m m SPAft 3 n::uia::tcu)a 2 - a ;..; /^ ^ =m SPM 2 nennunno i 1
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e - ~' -" s. t t ~ '. ; ,f s r 1 s. + ~ l . GUIDE TUBE STRESS (PSI) ~ l y 1 DBE . t. s. .I ". ~ ' CALCULATED - ' ALLOWABLE 9 6500F 1 . u '1 P b,3)5 E o P+P' a b i. +- Q \\- ~: 7' LOCA ~4:V a.. 3 CALCULATED ALLOWABLE 9 650 F a e ~_ p a r Sjh5' ~ P+P .a b t t. ..s, e.. ~.u. .,.. ~ .g g; ~. i C0 MINED DBE AND LOCA t 4 .6 =! ,~ ' f n CALCULATED ALLOWABLE 9 650 F .r, u V ^ G m
3. 9,,f P+P
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~
ALLOWASLE ALLOWABLE CALCULATED 0 6000F CALCULATED 9 6000F hY t. v r. LOCA / f ~ HID-1 HID-2 . ~ ' ALLOWABLE ALLOWABLE . CALCULATED 0 6000F CALCULATED 0 6000F e m> c ~ .s l M g
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ML19263C069

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