ML20137Z810

Vol 6, Vibration Aging Procedure, to Qualification Plan for Qualification of Edgs 64546 for Application in Comm Ed LaSalle County Station Div 3. Actual Procedure Number: 02-6073-011-QP-(2)-V6-(2)

ML20137Z810
Person / Time
Site:	LaSalle, 05000000
Issue date:	03/31/1982
From:	SOUTHWEST RESEARCH INSTITUTE
To:
Shared Package
ML20137Z802	List: ML20137Z795 ML20137Z810 ML20137Z816 ML20137Z827
References
02-6073-011-QP, 2-6073-11-QP, NUDOCS 8512110412
Download: ML20137Z810 (7)

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02-6073-011-QP-(2)-V6-(2) (

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QUALIFICATION PLAN FOR THE QUALIFICATION OF t

{ EDCS No. 64546 FOR APPLICATION IN THE s

COMMONWEALTH EDISON COMPANY (

LA SALLE COUNTY STATION DIVISION 3 l

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t Volume 6 - Vibration Aging Procedure I

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March 1982 l i

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j STEWART AND STEVENSON SERVICES 4516 Harrisburg ,

- Houston, Texas 77001 l

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(713) 923-2161 t i

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- SOUTHWEST RESEARCH INSTITUTE 6220 Culebra Road '

~ San Antonio, Texas 78284 -

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($12) 684-5111  !

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1.0 INTRODUCTION

1.1 Purpose of Vibration Aging

] The purpose of vibration aging of components of the EDGS is to simulate aging conditions and fatigue resulting from significant non-seismic vibration environments which components may see over the 40-year service life of the system. This is in accordance with the requirement " equipment subject to non-seismic vibration during normal and abnormal use shall be subjected to such typical vibration following the aging and seismic procedures" (323, 6.3.5). Accordingly, each mechanical or electromechanical component in the EDCS which could be subject to wear as a result of non-seismic vibrations during the service life of the EDCS will be exposed to an equivalent fatigue environment in the laboratory to simulate this wear.

1.2 Non-Seismic Vibration Environment of the EDCS y

Typically, non-seismic vibration environments for a component in d a nuclear plant are a result of transmission of dynamic loads through the plant piping system, or the proximity of the component to rotating machinery.

The EDCS is not affected by loads transmitted through the plant piping system.

J Furthermore, the major subsystems, the CT/PT, the CC, and AS should not, in general, be exposed to vibration environments caused by rotating machinery, since these subsystems are physically separate from the NC and are floor-mounted. Components of the HC other than the CEX and DE will be exposed to the non-seismic vibration environment created by operation of the DC over its service lifetime for a total of 11,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br /> maximum. The DE and CEX are designed and maintained to withstand the vibration environment created by their normal operation.

~ Since the major source of non-seismic vibrations is the LE, a preliminary investigation has been nade to obtain data on the power spectral density of the vibratory energy emitted by the DE during operation. These data reveal, as might be expected, that most of the energy is contained in narrow band frequency intervals equal to the rotation frequency of the engine

~ and harmonics of this frequency. For the EDCS considered, these base f requencies are 15 and 30 Hz for the 900 and 1800 rpm engines, respectively.

The data indicate that the maximum ras acceleration value over the range of frequencies emitted by the DE in operation is 0.5 g's or less.

Accordingly, the following vibration environment is postulated.

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1. Over a period of operation of 1000 hours0.0116 days <br />0.278 hours <br />0.00165 weeks <br />3.805e-4 months <br /> with a major vibration frequency of 30 Hz, couponents seeing the DE vibration

. environnent would receive 1.08 x 108 fatigue cycles.

~ 2. Since the total broadband ras value of acceleration is 0.5 s's, this is a conservative maximum for single frequency sinusoidal excitation sinulating the DE vibration environment.

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3. An amplitude exaggeration factor of tw duration for equivalent fatigue by 10~g,will reduceonly requiring the time 1.08 i x 106 fatigue cycles at 1.0 g nss for equivalent fatigue.

i If a 300 Ha sinusoidal excita

! the fatigue cycles,1.08 x 10gion signal cycles is used would be obtained to provide in 1 i

hour. (

i l 4. The maximum number of hours of operttion of the DE is OC member [

j s pecific . One hour of test at 1.0 g and 300 Hz will be run j for each 1000 hours0.0116 days <br />0.278 hours <br />0.00165 weeks <br />3.805e-4 months <br /> of operation of the DE for the worst case l j .

number of hours of operation for the pertinent OG members '

i involved. The current maximum is 11,000 hours0 days <br />0 hours <br />0 weeks <br />0 months <br />. ,

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2.0 QUALIFICATION, PROCEDURE 2.1 Pr,ercquisite Components to be vibrationally aged will have successfully conpleted thermal radiation and operational aging where required. This will be demonstrated by a functional check (V2) showing that each component to be vibrationally aged meets its EPR.

2.2 Analysis As previously discussed, some of the major subsystem components 3 of the EDGS vill not be exposed to significant non-seismic vibrations during their 40-year service life.

In particular, the components of the CT/PT, the CC and the AS, which are the majority of the electromechanical components, need not be exposed to a non-seismic vibration environment unless information on special cases showing otherwise is provided by the OG. Components of the CEX and DE are part of the design and are maintained such that they

] will be essentially unaffected by the vibration environment produced by the equipment of which they are a part. Other components which may be on the MG skid that are not components of the CEX or DE should not have component resonances at the base frequency or any of the harmonic frequencies of the DE while in operation. If this were so, these components would be particularly susceptible to damage due to the non-seismic vibration environment and would constitute an improper design. Any components of d this type which may be discovered during the resonant search which is part of the process described in Section 2.3 below, should be reviewed for possibio

" elimination fecm the EDCS and replacement with components whose mechanical characteristics are nore suitable to the design. We do not contemplate components of this type will be found.

2.3 Type Test Based on our conservative value for number of fatigue cycles and acceleration level given in Section 1.2, the following type testing will

' be perfor aed on MG skid components other than subcomponents of the DE and GEX in order to produce the appropriate non-seisnic vibration aging.

1. The component will be exposed to I hour of uniaxial sinusoidal

' excitation in each of its three principal axes per 1000 hours0.0116 days <br />0.278 hours <br />0.00165 weeks <br />3.805e-4 months <br /> of DE operation as stated in the CFMA.

2. Tests will be performed at 300 Hz in cach axis.

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The rms acceleration level of the excitation will be 1.0 g's.

Prior to vibration aging, each component will be exposed to

~ sinusoidal excitation in the frequency range 10 to 200 Itz. Excitation will be at .1 g or less uniaxially in each of the three principal axes of the a

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02-6073-011-QP-(2)-V6-(2)-4 component. The sweep rate will be 2 octaves per minute or less. The

' components will be monitored with an accelerometer in a manner sufficient to determine that no resonances occur at multiples of 15 or 30 Hz. Components  !

which have resonances at these frequencies will be reviewed for possible  !

, elimination from the EDCS.

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.. , A f tdC bm et1 Y O DATA SUPPLEMENT "I'o Response of an EMD'645' Engine and Selected Accessories to Impulsive and Steady State Loads by '

James F. Unruh The steady-state data, test numbers 19 through 46, of the subject investi-gation were analyzed-for overall RMS acceleration levels in the frequency range from.1-200 Hz. While'the data were considered to be steady state engine ex-citation sample averaging over a 128-second interval (64 sample averages) were used to establish the RMS values listed in Table 1. Typical 1.0 second accel-eration time history and Fourier amplitude spectra in units of g's are given

, on the following data plots. These data were generated using a sample rate of 1,000 samples /second. As can be seen by the overall average RMS amplitudes given in Table 1 and the peak spectrum values that some nonstationarity in the data was present.

Insofar as using these data for evaluating the level of operational loads due to engine vibration it is recommended that an equivalent static load approach be used rather than the specific time history events for the following reasons.

1) In a majority of the cases the peak vibratory input is above the seismic region of excitation. Spectra peaks are on the order of 75 Hz and above for the larger excitation levels.

2) In those cases where vibration energy is present at the _

engine first two harmonics -(15.or 30 Hz) the base level of vibration is less than 0.2 g's (less than 0.008 inch de-flection).

Based on the RMS summary data given in Table 1 it is suggested that the following (mean + 1 std. dev) peak static gravity loads be used to conserva-tively assess the operational vibratory loads of EDGS.

Direction Level.(g's)

X O.95 Y 0.85 Z 1.00 e

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TABLE 1. RMS mpli tude 'Sumary Measurement -Response

• RMS File Data .

Directions Location (g) -

Name Record No.

Ch. 1 Ch. 2 Ch. 1 Ch. 2 1 X ,Z 0.13 0.078 SSXZ01 1,2 Y t- Z 0.064 0.066 SSYZ01 3,4 2 X Z 0.100 0.087 SSXZO2 5,6 Y Z 0.114 0.162 SSYZO2 7,8 3 X Z 0.450 0.182 SSXZ03 9,10 .

Y Z 0.613 0.560 SSYZO3 11,12 4 X, - Z 0.998' O.748 SSXZO4 13,14 5 X Z 0.769 0.603 SSXZ05 15,16 6 X Z 0.497 0.675 SSXZ06 17,18 Y Z 0.511 0.652 SSYZ06 19,20 7 X Z 0.458 1.020 SSXZ07 21,22 Y

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Z l.00 0.554 SSYZ07 23,24 8 X Z 0.732 0.847 SSXZO8 25,26 Y Z 0.347 0.374 SSYZ08 27,28 9 X Z 0.469 0.477 SSXZ09 29,30 Y Z 0.414 0.469 SSYZO9 31,32 10 X Z 0.378 0.296~ SSXZ10 33,34 Y Z 0.169 0.421 SSYZ10 35,36 11 X Z 0.305 0.281 SSXZ11 37,38 Y Z 0.078 0.267 SSYZll 39,40 12 X Z 0.374 0.198 SSXZ12 41,42 13 X Z 0.349 0.299 SSXZ13 43,44 Y Z 0.344 0.501 SSYZ13 45,46 14 X Z 0.185

,Y 0.211 SSXZ14 47,48 Z OL255 0.601 SSYZ14 49,50 15 X Z 0.'26 1 0.100 SSXZ15 51,52 Y Z 0.142 0.111 SSYZ15 53,54 16 X Z 0.344 0.818 SSXZ16 55,56 Y Z 0.214 0.771 SSYZl6 57,58 RMS

SUMMARY

(g's)

X Y Z Mean 0.416 0.328 0.429' '

Std. Dev. 0.248 0.263 0.268 Variance 0.057 0.064 0.069

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Based on 128 sec of sample averaging, 1-200 Hz window. -

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APPENDIX A 7

TEST PROCEDURES I

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