ML20002A591

Nonproprietary Version of CEN-140(S)-NP, Data Transmittal for Southern CA Edison Fuel Audit Analysis.

ML20002A591
Person / Time
Site:	San Onofre
Issue date:	10/10/1980
From:	ABB COMBUSTION ENGINEERING NUCLEAR FUEL (FORMERLY
To:
Shared Package
ML13308B785	List: ML13308B784 ML20002A591
References
CEN-140(S)-NP, NUDOCS 8011200207
Download: ML20002A591 (33)

Text

t g SAfl O!!0FRE UtilTS 2 AND 3 DOCKETS 50-361 AND 50-362 CEN-140(S)-NP DATA TRANSMITTAL FOR SCE FUEL AUDIT 'aALYSIS OCTOBER 10, 1980 s

COMBUSTION EilGINEERIllG, IllC.

NUCLEAR POWER SYSTEMS P0'r,'ER SYSTEMS GROUP WINDSOR, CONNECTICUT 06095 THIS DOCUMENT CONTAINS POOR QUAUTY PAGES 801y20oD7

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reu (Glo.Mit vel! DOR DATA IlliOUEST FORM

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i TYPE AXIAL LA1LRAL DESIP.ED F0Ti!.1 FORCE DEfLCCil0n '

FIGURE 4 FIGURE 3 '

(STA1!C)

FLOTS N4PLITUDE AT GRIDS lst 5 FIGURE 1 (AODE Sl! APES LATERAL- PLOTS

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InE00EnciES Is TABL'E l' g TABLE .

DROP TEST FIGURES 5,6 TORCE 11.tE

+ DROP I!EIGHT FLOTS

!!!iEnt!AL E0310 GR:D I?.1PACI Silif t:ESS / TABLE 3' TABLE iXTER'it.L GR!3 7- -/71

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DISCL'SSiON TABLEOP.FLOTS m onoo IRlCIION TABLE 4 TABLE

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. 3 DISCllSS10

10F LATERAL LRECT10il TEST -DATA 1 .-

I In the information that follows, spacer grid elevations are always given i

. with respect to the bottom of the lower end fitting. Most of the tests were run in air ~ at room temperature (70 F). Some information is provided in

{

-water at room temperature.

i 4 For the forced vibration test program the fuel assembly was supported in special fixturing which simulated reactor end support conditions. The fuel assembly was preloaded in the axial direction by compressing the holddown L springs 3/8 inch. Sinusoidal excitation was applied from a hydraulic shaker by a rod link to the simulated core support plate which was resting on rollers.

The simulated fuel alignment plate remained fixed during the test program.

For the water environment tests, a cylinder with a 30 inch .I.D. was installed over the fuel assembly. The water level was held above the simulated fuel

alignment plate during the in-water test program. The lateral displacement i

of the assembly was monitored at every spacer grid.

1 ~

In Table 1, the first five fuel assembly natural frequencies and associated critical damping ratios are 1isted. These values were taken from a forced j vibration test. The assembly was in a simulated "end of life" condition during this test series. The values are for=.the largest double amplitude input i

used in each mode.

. Fuel- assembly mode shape data are given in Table 2. Plots of this data are provided in Figure 1 (a) (e). This data provides an envelope of the peak

[ response of the fuel assembly at each resonant frequency and not a true mode shape. The envelope of peak response is the maximum response of each grid i withoat regard to the phase between the response and the input. The divn-ience l'

4 from a true mode shape is particularly evident near the lower end fitting where the input excitation is applied. liowever, these data are the best available. Refer to the static lateral deflection shape discussed below Mode shapes for guidance in approximating the true first mode shape.

are not used directly in our modelling effort and therefore we iave never attempted to determine exact mode shapes.

The static lateral displacement shape of a fuel assembly with a load applied to the central grid is given in Figure 2. This figure is based on many sets of displacement shape data with central grid displacements of 0.4 inches to 1.6 inches.

The lateral load-deflection characteristics of a fuel assembly are shown in Figure 3. The lateral load was ipplied to the central grid (grid #6) and the deflection of that grid was nanitored.

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. I c 0 STRAIGHT FUEL BUNDLE o 0.5 INCH BOW v 1.0 INCH BOW t

I i0 0.25 0.50 0.75 1.00

. NOMINAL DROP HEIGHT, IN.

MAXIMUM IMPACT LOAD vs Db OP HEIGHT

- TEST CONDITION B WITH HOLDDOWN SPRINGS .

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I* One-Sided Thru (Internal Rod (External Grid

.to Grid Imp,et Impact StiffnessL Stiffness)

(#/in) (#/in)

I HID-2 HID-1 j .

t

2. Coefficient of Restitution =[ [(in place of impact damping)

~

I

3. Uniform Beam Models of Fuel (HOT) i El = n2 -lb K upper

= Torsional Spring Representing

. p Upper End Fitting K

upper ". J i n/lb/ rad K = Torsional Spring Representing.

i lower Lower Eno Fitting K

lower in/lb/ rad i TABLE 4 GRID-ROD FRICTION

'T BOL (HOT) Force Per Rod Per Grid (All Grids Same) 20L (H0T) Force Per Rod at Top Zircaloy Grid Force Per Rod at Lcwer Inconel Grid

Remaining Grids-ASSUME STATIC FRICTION FORCE EQUALS DYNS4IC FRICTION FORCE ,

4 i

,, -- .- , . ... _v . .4

' 16 TABLE 5_

Spacer Grid Crush Strength (to be supplied following completion of production testing) 1

DEN! colin't RESULTS

- The. following data gives the results of a . test program designed to determine the dynamic response characteristics of a bowed 16 x 16 fuel assembly (see Fig.7) sub-jected to axial' impact loadings. The experiments were performed in air with simulated reactor end conditions. The fuel assembly was incrementally deflected .

Land raised, then released, and allowed to strike a rigid impact base. For each, drop cycle the impact load, the_ displacement, the velocity and acceleration characteristics _ at the lower end fitting location were to be monitored as a function of time. In' addition, time history traces of the lateral deflection

~

behavior at three-spacer grid locations were developed. A tabular summary of the lateral amplitude excursions as measured from the LVDT traces is presented in Table 6.

Drop Figure 8 summarizes the effect of axial impact on lateral deficction.

height versus the percentage increase of lateral deflection from the fuel assem-- ,

blics initial bow are presented for a 1.0" bow (at midspan). Tnree spacer grid elevations are considered Fuel assembly hysteresis and friction effects tend to mask the effects of axial loads on lateral deformation for initial bows of less than I

'I .

L J .

Further test data corroboration-of the minimal effect of axial loads on the lateral deformation of a fuel assembly is shown in Figure S Figure 9 indicates

$ . , , y a less than increase in lateral deformation due to a .

lb. axial load 1

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a a statically applied to an initially _ deformed (0.5") 16 x 16 fuel assembly.

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18 TABLE 6 Spacer Drop fleight Bow Grid fio. 0.25" 0.5" 0.75" Lateral /.mplitude Excursions (in.)

0.5" 3

1.0" 0.5" 6

1.0" 0.5" 9

1.0" B

9 Q

I Hopw 7 19 1LST S[ TUP 10 x 10 FUEL A S S L f.i l! L Y D il O P TESTS I

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.Ibf]cction at Grid No. 6 ---

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=

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.=. .. L. . .. .. .. .. . . .

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m . =. ,i

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re

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. _F.ig.u.rc 9 Fuel lituulle. IM]ection at 7..ero anu at ,Lbs.

- J Axial-rorce for 0.5 luch lateral 'lusplacciaent p

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23-San Onofre' Unit 2 - Vendor Data Request form

[fiterial Description Center'of Gravity Type of Stiffness Compon_eg Weight (1bs) i

_(i_nches) Haterial and/or Preload Fuci Rod [ ] flot Requested ' Clad & End Caps, Zr-4

• Plenum Spring, 302 SS flot Requested

• Spacers: A1203

• Fuel: Enriched U02 Spacer Grid flot Requested e lllD-1 : Zr-4 flot Requested

• l11D-1:( )]

• illD-2: e lllD-2: Zr-4

• Inconel: Inconel 625

• InconePu/o Skirt: ].

• Incone W Skirt: }

flot Requested

• Posts: 304 SS flot Requested Top End Box, i.e . Upper ( } 'liolddown Plate &

> End Fitting Flow Plate: 304 SS Assenbly Casting Type CF-8 elloiddown Springs:

Inconel X-7SO

)

Botton End Box, Not Requested 304 SS Casting flot Requested Type CF-8 1.c., Lcwer End ,

Fitting Asser.bly

]perRod flot Requested flot Requested fuel [ 002 4,

] per

. bundle ,

~

Fuel Assembly, i.e., Fuel

[ ] '-

• End Fittings: 334 SS

• Guide Tube: Zr-4 Not Requested

Bundle Assembly Stiffness per.

Iloiddown Spring (5lloiddown-

[spri'ng l per flot Requested Inconel X-750 Spriqq: .,

Springs per Cold , ,

Ib/in Bundle) llot Ib/in

• Prelo~ad BG. I:ot=

[. ,]lbs per spring 1

(

a 499 g .

24 Miscellaneous Information Requested at September 9,1980 Meeting

1. Spacer grid axial spacing, .outside dimensions, and assembly to assembly gap - Figure 10

2. Guide tube / upper end fitting connection - Figure 11

3. Guide tube / lower end fitting connection - Figure 12

4. Guide tube / spacer grid connection - Figure 13

5. Fuel rod / spacer grid interface - Figure 14

6. Upper end fitting / fuel alignment plate interface - Figure 15 ,

7. Lower grid / lower end fitting connection - Figure 16

8. Guide tube details - Figure 17

9. Fuel rod details - Figure 18 l

l l

• TIGURE~~ 10 25 Spacey Grid Inforraation

/dtt yn~m0 79a E.S F. % ;

J WiS fg h '

_7 .

. -+ Z re . ,

l l

i "

=~~mf Jf EC-1 Giruh

\

- 4}.

q. .: _ _ .

l A

I E

. ,i .

N kH LO4 CnIos 7,

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rz, ,

9 HTC ~/ll?C. Gr:.En 4e 21CC w l 2L t Is GRIO G Ap 14oi O.016" l

_41 -

b .

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.g.r . .g,. . .

,t 8

• k 6 ru gt it.t g -un >t dxe.ocL Gelo

'{_11 t.oto u. G J F. O .1 e

i

FICllitE 11 0

5 Guide Tube /lfpper End Fitting Connection 26 e

e W

9 f

l l

l l

l l

j l

l

-. a r - . _ _ - -r ._ - m- .. , _. ,% . ,, y, ,,, m - my., , .__

_F_I_GURE

-- 12 0

Guide Tube / Lower End Fitting Connection _ 27 l l

1 e

e M

_ e eea e W I

. . - . . .. ~. ._.  :. . . ,_. = .: -- --

' ' - -' ~ ~

FIGURE'13-

-- buide Tube / Spacer Grid _ Connection 28 i

FIGURE 14 Fuel Rod / Spacer Grid Interface f

e a- --.- m.

p L 's .., . . . .

\}

,/ ...- I ,s.v. . .:.: .: - \,.

v

.v..,... b

. 1.1 .. i

.* **, ,\, . d '

I

+

a% M Q.

4 e

4 de v

L.

L - .... _._.

. - _ _ - .c i

FIGURE 15 29 Upper End fitting / fuel Alignment _ P, late Intef _ face 9

/ / - '

/

/ ,

i

/ ~ ~

[ M , ( ,// s M [.. s4 da a m -

e s m. e-o e

. 4 6

b '

h

~ _ - -__..,._..z_.,..._. , . . . - . . . . . , . _ . . . . . _ _ . . _ . . _ , _ . . . . . . _ . . _ . , _ . . _ . . ;

O FIGURE 16 -

30 1.ouer Grid /t.oaer End Fittinglntgface

• m 6

f l

I l 1 .

1

! e j

l l I i W~ ~ - - -- - - _ . _ ._ - - .. -. __ _. ;_,,,_ _ _;_-_._._,___,,_..g

FIGURE 17

. , 1

, 3) -

- Guide Tube Details ,

~

, Center Guide Tube Outer Guide Tubc_

_]

FIGURE 18_

Fuel Rod Details 32 b

/

[\

e b

W N N 9

l50 000

- M,a FJ Lu;fk

~ ,331 -

s VC O b

\ I .f7/

\. l 01 l-

% =0

- = y . MYge m - ws um m+4 4- ON - T M Mr-- - ' ' ' ~, 3ES^

,_ NW -

5-- -' TM- ,- -

m v .