ML19316A230

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Acceptance Criteria for Measured Vibrations of Core Support Shield During Hot Functional Testing. Submitted as Amend 28 to License Application on 710806
ML19316A230
Person / Time
Site: Oconee  Duke Energy icon.png
Issue date: 04/30/1971
From:
BABCOCK & WILCOX CO.
To:
References
PROC-710430, NUDOCS 7912030346
Download: ML19316A230 (9)


Text

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RtGU'.A70RY E20!:.H F!!E COPY f* +,

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DUKE PCRER COMPANY .97

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AUG 9 1971 * $l OCONEE NUCLEAR STATION

, ul Mt*C CGET UNITS 1, 2, and 3 g 5j?,?37 '

LICENSE APPLICATION m *s. tan

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DOC E NOS. 50-269, -270, and -287 /q c:

ACCEPTANCE CRITERIA FOR THE MEASURED' VIBRATIONS ""

, OF THE ""'d "'" "*

CORE SUPPORT SHIELD DURING HOT FUNCTIONAL TISTING l APRIL, 1971

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Prepared By: )

BABCOCK & WILCOX ,

Power Generation Division Nuclear Power Generation Department P. O. Box 1260 Lynchburg,. Virginia 24505 Submitted as Adendment No. 28 Au6ust 6, 1971

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llEGULA10RY 000KET FILE COPY 7912030 3f8#

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ACCEPTANCE CRITERIA FOR THE MEASURED VIBRATIOr.3 0F THE CORE SUPPORT

SHIELD DURING HOT FUNCTIONI.L TESTING

.
ACCEPTANCE CRITERIA -

The upper bounds of the displacement and the acceleration are as follevs:

- Acceptable displacement of the shield cylinder shall be limited to +

'

15 mils between frequencies of 0 to 120 H .

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- Above 120 H acceptable acceleration of the shield cylinder shall be limited to an acceleration which shall correspond to + 15 mils at 120 H or 22 g's.

BASES FCR THE CRITERIA -

Core Support Shield Frecuencies i

A vibration survey was performed on a set of Duke type reactor internals to determine the vibration characteristics of plenum cylinder, thermal shield and

,

l the core support structure.

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i Characteristic frequencies were determined from escillograph record *, of the core 4

i support shield response to both impact and steady state forced excitation. The steady state force was generated by an electrodynamic shaker. Resenant frequencies

,

determined from the test data are. tabulated in Table 1. The resonant frequency 2

of 118 H, is identified with the hth order mode which has the lowest frequency.

J j Ctherfrequencies are associated with higher order modes. It'is expected that the shield vill respond principally at the lowest frequency with some additional response in the 120 to 225 Hzfrequency range. l l

i l I Core Sunnert ' Shield Distlacement

.To arrive at _ the anticipated flev induced response of 15 mils it was assumed that - j at least. 0.5.T of the flov energy around the shield is absorbed as structural

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vibratory energy. Such a substantial transfer.of energy to the shield is judged to yield a very conservative prediction fo.r the upper limit' of displacement.

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Stresses Correspondine to the Acceptance Criteria Limits Actual ficv induced vibrations are expected to result in small cyclic stresses.

However, to determine the magnitude of the strees for the conservative upper limits of displacer--ts previcusly discussed, a mathematical model of the core suppcrt structure was used in conjunction with a computer program called GEUSH.

A distributed load va applied to the cutside of the shell which resulted in a configuration equivalent to cne of the mode shapes with a displacement of 10 mils.

A constant 10 mils displacement was used for each of the several different con-figurations. The resulting stresses are shcvn in Figures 1, 2, 3, and h.

As stated previously, the response frc the higher r. odes are expected to be acnsiderably less than the response far the icwest frequency r. ode. However, even if it is assumed that four modes each contribute a 10 mil displacement, the ras cyclic stresses for the modes at the highest stress location is cnly 5,100 psi.

An rms stress was computed because the modal maxima do not occur simultaneously.

Adding this stress to the normal operating stress shown in Figure 5 results in a total stress of only 6,300 psi which is considerably below the endurance limit stress of 26,000 psi.

The main points with regard to the acceptance criteria are:

1. The acceptance limits for both the measured vibratory responses, i.e. ,

acceleraticns and/or displacements and the corresponding stresses are conservative.

2. The acceptance criteria limits can be conservatively increased withcut exceeding the endurance limits.

2-

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PEPSORMMICE CAPA3ILITI 0F TE INSTRLMUTATICH -

'21e specially designed instrumentaticn for measuring the core support shield accelerations has a flat frequency response over a range of 2 to 300 H, and can sense vibratory accelerations up to 30 g's. Sese design specifications for the sensors are, of course, conpatible with the acceptance limits established for the

=easured accelerations.

Table 1 Resonant Frequencies of the Core Support Shield - H, 118 H,

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133 lo9 225 1

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82"R  ;'

I d a Pt+PB = 8 68 P SI --+ , +- - -1437 PSI Pu = 285 PSI 2 . 2 5 " -. .-

CORE Py = 352 PSI N -

SUPPORT SHIELD I

P,+PB i *'766 PSI,, w __ __ 9 7, p g g 74.125 R ---e4 114" Pg = 102 PSI

' PL ANE OF SYMMETRY PL+PB = 463 PSI --* e - 259 PSI

-

4 V 4

J a i RADygx = .010" T

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  • REF. SURFACE 2 " --* +

MODE SHAPE CONFIGURATl0N  :

170" l 71.5"R  ::

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g l

-* CORE SUPPORT STRUCTURE

%3a GENSH MODEL & STRESS iNTENSITI ES FIGURE I

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- -. .- - - - , - - -

.-..

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82"R 4 d Pt + Pg = 1094 , e -

1811 PSI

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Pg = 350 PSI

2. 2 5, -= .-

CORE PM = 281 PSI , SUPPORT SHIELD 1 Pt + Pg = 1463 PSI N e- - - 2024 PSI 74.125,R ---e e 114"

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Pg = 163 PSI l

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Pt+P8 = 536 PSI - e -

208 PSI PLANE OF SYMMETRY

% II - a R40mgx = .010"

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- REF. SURF ACE li 2 " --ei e- i MODE SHAPE CONFIGURATION 170" 71.5"R  ::

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-* CORE SUPPORT STRUCTURE l*-3a GENSH MODEL & STRESS INTENSITIES FIGURE 2 ^

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--

82" R l

a n Pt+PB = 1149 PSI" , e -

- 1901 PSI Pg = 376 PSI 2 25' -. +

CORE Pg = 206 PSI N - SUPPORT SHIELD 1

Pt+PB = 2281 PSI N *-- - - 2E92 PS,.

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74.125 R --ee 114" t

Py = 187 PSI

--* '

e -

- 203 PSI PLANE OF SYMMETRY PL+PB = 577 PSI 4 U a R ADMAX = .010" y

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REF. SURFACE 2" % +

MODE SHAPE CONFIGURATION ,

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170"

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71.5"R  ::

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-* CORE SUPPORT STRUCTURE I

%3a GENSH MODEL & STRESS INTENSITIES

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FIGURE 3

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a 82" R c' I

il d Pt + Pg = 1162 PSI ~ -

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- 1903 PSI Pg = 370 PSI 2 . 2 5 " --. .-

CORE Pg = 147 PSI

, SUPPORT SHIELD l

Pt+PB = 3211 PSl% _ _

p 74.125 R -----ee 114" Pg = 182 PSl

'

---*' *-- -

- 217 PSI -

PLANE OF SYMMETRY Pt+PB = 581 PSI

( 4 J < b 4 RADMAX = .010"

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, r J

'" ' REF. SURFACE

[

i 2 " ---e e-

. 170" MODE SHAPE CONFIGURATION 71.5'R  ::

1 1

4

1

-* l*-3= CORE SUPPORT STRUCTURE GENSH MODEL & STRESS INTENSITI ES FIGURE 14 i

w- w

_ - _ _ _ - - _ _ _ _ _ - _ - _ _ _ _ _ _ _

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82'R r I

il ib 569 PSI - , .-- -

-Pt+PB = 953 PSI Py = 652 PSI

2. 2 5' -= .-

U N - SUP ORT SHIELD I Pg, + PB = 1872 PSI N i *--

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- 1215 PSI 74.125"R --e e 114" Py = 1008 PSI 1148 PSI  % '

  • -- -

Pt+PB* '

972 psi y PLANE OF SYMMETRY v v

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2 < >

l r

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/' REF. SURFACE 2 " --* *-

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M H H ON 170" 71.5"R  ::

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-* CORE SUPPORT STRUCTURE

}*-3" GENSH 90 DEL & STRESS INTENSITI ES 1

FIGURE 5

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