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 SAfl O!!0FRE UtilTS 2 AND 3 g

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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2 vel! DOR DATA IlliOUEST FORM reu (Glo.Mit is s. ( fil TEST 0ATA TYPE AXIAL LA1LRAL DESIP.ED F0Ti!.1 i

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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Is InE00EnciES TABL'E l' g

TABLE DROP TEST

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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 For the forced vibration test program the fuel assembly was supported in 4

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 for guidance in approximating the true first mode shape.

Mode shapes 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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HID-2 Fuel A:.r.embly Axial 1.oad versus Axial Compression

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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 c- -

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15 TABLE 3-GRID _ IMPACT STlFFUESSES (HOT)

I*

One-Sided Thru (Internal Rod (External Grid

.to Grid Imp,et Impact StiffnessL Stiffness)

(#/in)

(#/in)

I HID-2 HID-1 j

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

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I 3.

Uniform Beam Models of Fuel (HOT) 2 El =

n -lb K

= Torsional Spring Representing i

upper Upper End Fitting p

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K

= Torsional Spring Representing.

i lower in/lb/ rad Lower Eno Fitting K

lower 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

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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.

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

Drop 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 I

'I less than 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 a

a 1

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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

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

[fiterial Description Center'of Gravity Type of Stiffness

_(i_nches)

Haterial and/or Preload Compon_eg Weight (1bs) i Fuci Rod

[ ]

flot Requested

' Clad & End Caps, Zr-4 flot Requested

• Plenum Spring, 302 SS A1 03

• Spacers:

2

• Fuel: Enriched U02

• l11D-1:( )]

flot Requested e lllD-1 : Zr-4 flot Requested Spacer Grid

• illD-2:

e lllD-2: Zr-4

• InconePu/o

• Inconel: Inconel 625 Skirt:

].

• Incone W Skirt:

}

Top End Box,

(

}

flot Requested

• Posts: 304 SS flot Requested 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 1.c., Lcwer End Type CF-8 Fitting Asser.bly fuel

[

]perRod flot Requested 002 flot Requested

] per 4,. bundle

~

Fuel Assembly, [

]

• End Fittings: 334 SS Not Requested i.e., Fuel

• Guide Tube: Zr-4 Bundle Assembly Iloiddown Spring [

l flot Requested Inconel X-750 Stiffness per.

per (5lloiddown-spri'ng 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

TIGURE 10 25

~~

Spacey Grid Inforraation

/dtt 79a E.S F. % ;

yn~m0 JWiS fg h _7

-+ Z re l

l

\\

i

=~~mf 4}.

Jf EC-1 Giruh l

q..:

A I

E

,i N

kH LO4 CnIos 7,

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i g

rz,

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l HTC 2L t

Is GRIO G Ap 14oi O.016" w

l

_41 b

lpr=

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3 i

.g.r..g,.

,t k

6 8

ru gtit.t g

-un >t

'{_11 dxe.ocL Gelo 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

j

-. a r -

-r._ -

m-

,%.,, y,

,,, m - my.,,

_F_I_GURE 12 0

Guide Tube / Lower End Fitting Connection _

27 e

e M

W e

eea e 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 b

1.1

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i

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I

+

a%

M Q.

4 e

4 de vL.

i L

. - _ _ -.c

FIGURE 15 29 f

Upper End fitting / fuel Alignment _ P, late Intef _ ace 9

i

/

/

/

/

/

~

~

[ M,

(,//

s M

[.. s4 da m

m.

e-a e

s o

e 4

6 b

h

~ _ -

-__..,._..z_.,..._.

FIGURE 16 O

30 1.ouer Grid /t.oaer End Fittinglntgface m

6 f

l I

1 1

j e

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 0

1 l-

=0 5--

-' TM-

- = y. MYge m - ws um m+4 4-ON -

m v

T M Mr--

- ' ' ' ~,

3ES^

,_ NW

.