ML20086D191
| ML20086D191 | |
| Person / Time | |
|---|---|
| Site: | San Onofre  |
| Issue date: | 11/08/1991 |
| From: | SOUTHERN CALIFORNIA EDISON CO. |
| To: | |
| Shared Package | |
| ML13302A297 | List: |
| References | |
| M-DSC-250, NUDOCS 9111260010 | |
| Download: ML20086D191 (42) | |
Text
_ _ _ _ ._ _ - _ _ __. _ __ . _ _ _ . _ . _ _ _ _ _ _
e
. CALCULATION TITLE PAGE PRELIM. CCN NO. OF i
,, ,, PACE
~
4 CCN CONV(RSON Ceic. No M- DSC -2 50 Dep.MMP:FIDCNFCN No. & Rev. ccN e CCN-Sum.e, SYNSS GVALUATiohl of UN IT3 RCP FLYWHEEL. Sne., _I Cr* tem Numter i Pnmery Stat 6on System Des #gnetor / SONGS Unit 3 o-ci... E i
, 3 spec. Affecting? NO YES, Section No. Equipownt Tog No.
CONTROLLED @procRAu amocRAM CatABASE NAMEIS) VERSION RELE ASE NO.(S)
COMPUTER ALSO. LeTE D SELow DA M ASE PRocRAus DATABASE IN ACCORDANCE WiTH NLS&L 41 l t
{
RECORD OF ISSUES REV PREPARED APPROVED DISC. g gg (Print nemeinittel) (Signa ture) u mot._v- e-
/NII/Ab [33 N 42._ D n + PIC H / D K 7 -
n 1 l
"'T &a //Tc (92hxlu[ hP/9)
Q4hG Ca$ 0W Ag CM OATE QAlG. M OT R6 QM OATE 04sd M UT R( OM OAIk Space for RPE Stamp, identify use of en altemete calc., and notes es applicetwo.
l l
I l
Thee esse, was pw for sie teeniWed DCP'WWP. OCP semp6m6cn and tumover accepiawe to be vented of reuset of a memorandum onecteg DCN Conversoon upon seempt.une ease, repressess the es4ues eendHken. Meme seen by -
l l SCE 251211 REY Ertt I
?ii12/0010 2 dillOS U l *LR
[ ADOG MOO g 2 g r run
CALCULATION CROSS-INDEX ,CCN NO.,
PRELIG4. CCN NO. PAGE OF ,
~
CCN CONVERSION
^
Calculation No. ~b ~
Sheet No.' CCN NO. CCN-- -
' INPUTS OUTPUTS " ' " * *
- Calc rev. NN number and These interfaang rahdatons and /or Results arid cond;ssons of the subrect
- Identity output interface '
responsible docurnents provide input to the subsect "
calculaton ase used in tree intertaan9 calc / document CCN, DCN,
- supervisor calculation, and if revoed rney require innais and revision of the subsect caloidatert calculanons and/or documents ',%9 TCNtRev or FtDCN dam -------------------- ------------- --------
**--*-****---*-*---*7-**--*-~
Calc / Documord No. Rev.No. Calc 1 Document No. ' IRev.No.
YESINO ,
1 F
i O O Po Ar1ED ' 5:S h R , . (10 tTS 173-O M p gwk,ej Des /p Ray.vt ' l.
g %~.a nr- de AAos-000). t i
f
?
t i !
i 1 .
I i
?
m scs as424 My nei' g , ,
4 l
l
.. .. CALCb5A5$$dHEET _
- n , .
CC% CQNYiR$1CN Proje:t or DCP/MMP _10NGS 2&3 ' Calc No. M-DSC-230 CCh No. CCN .
Subject Jee Title Sheet _ Sheet No. 3 __ _ _ . ,
OtV ORIGINATOR DATE 1RE DAit REV 041GINAIQR DATE IR{ DAil.
o w, m, EL Arity U /o7/01 f, $ _ "h[f { l T -
TABLE OF CONTENTS Sheet Number CALCULATION TITLE SHEET . . . . . . . . . . . .. 1 CALCULATION CROSS INDEX . . . . . . .......2 TABLE OF CONTENTS . . . . . . . . . . . . . . . .. 3 1 PURPOSE . . ..................... 4 2 RESULTS/ CONCLUSIONS . . . . . . . . . . . . . . .. 5 3 ASSUMPTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . 6 4 METHODO LOGY . . . . . . . . . . . . . . . . . . . . . . . . . . 7 5 DESIGN INPUT . ....................... 14 6 REFERENCES . . .......................16 7 NOMENCLATURE . . . . . . . . . . . . . . . . . . . . . . . . 17 8 CALCULATIONS . . . . . . . . . . . . . . . . . . . . . . . . 19 SCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET ::n , . ,A,E ,,
CCN CChvfR51,N Project or DCP/MMP S0NGS 2&3 Calc No, M-DSC-250 c N ho. CCN -
Subject See Title Sheet sheet No.
DEV ORIGihATOR CATE 1RE DATE REV ORIGlkA10R DATE 1RE DATE O N. M. [L-AK!LY 11/07/91 f. 6, "[j/rf l 1 PURPOSE The purpose of this calculation is to parform a stress evaluation of the Reactor Coolant Pump (RCP) flywheel, Unit 3, for brittle fracture. The results of the analysis will be used to provide technical basis for a waiver of compliance from the requirements of Technical Specification (TS) Limiting Condition for Operation (LCO) 3.0.3 and 3.4.1.1 until February, 1992. These LCO's relate to the inspection schedule associated with the RCP motor flywheels per TS 4.4.9.
l l
I l
a GCE 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET =L ,a o, CCh CONvtR$10N ,
Project or DCP/M P SONGS 2&3 Calc No. M-DSC-250 cc= No. ccN - '
subject See Title Sheet Sheet No.
OEV ORIGlAA10R DATE 1RE DATE REV ORICIkATOR DATE IRE DATE O k. M. EL AKILY 11/07/91 7. hw c[
7 l
2 RESULTS/ CONCLUSIONS The stress intensity factor, K , was calculated for a crack depth of 0.6"representingthedepthokthekeywayplustwicethedepthof the largest nondetectable-crack. The flywheel loading combinations, included rotating disk stress, interference fit stress, key loading due to pump coast down deceleration, seismic loading and vibratory motion. All loads were calculated assuming overspeed condition; thus representing the most severe conditions. A safety factor (SF) was then calculated as follows:
SF- 4-7 ( b_ khb P) kr Where K 3e is the critical stress intensity for the flywheel material at the operating temperature (=220 ksi/in, Reference 1). It was concluded that the. case of pump rotor seizure and motor acceleration are enveloped by the pump overspeed conditions. It was also concluded that start-up stresses are enveloped by the pump overspeed conditions.
Total crack growth of 0.005" was calculated based on 100 pump stop and start cycles (the projected total number of c for the duration between 2/1/87 and 2/29/92 is less than 50)ycles .
Based on the abo ' results, it was concluded that continued operation until 2/29/1992 will not result in crack propagation resulting in loss of flywheel structural integrity.
l l
l SCE 26-426 NEW 4/90
NES&L DEPARTMENT l . ..
.. CALCULATION SHEET = = t se. ,m o, CCh C0hvfR5104 Project or DCP/MMP SONGS 2&3 Calc No. M-OSC-250 ccm h3. CCN -
Subject See Title Sheet Sheet No. d arvj onicinaten eart int eatt acv onicisaton cait int oait
', N. M. EL-AKILY 11/07/91 [h /[f,/) ;
3 ASSUMPTIONS 3.1 The dominant stress components in the flywheel are the tangential stress (o ) and the radial stress (o,). The axial jissmallsincetheloadsactingonthe stress flywheel component in the axi (a'al direction are significantly less than the loads in the plane of the flywheel. Specifically, the tangential stress due to vertical seismic acceleration (z-direction) is only 2.5V of the total targential stress.
3.2 The flywheel is keyed to the eight spider arms by two axial keys. However, it was conservatively assumed that the deceleration load due to coast down is supported by one key only.
3.3 The speed of pump is proportional to the rate of flow in the reactor coolant loop.
3.4 The tangential stress s of primary concern in the fracture mechanics calculation ince this stress component acts perpendicularly to th crack. Although shear stress (radial stress) which acts parallel to the crack represents a Mode II crack opening, this mechanism of failure rarely occurs and will not be considered r :e radial stress is smaller than the tangengial stress.
SCE 26-426 NEW 4'90
NES&L DEPARTMENT
." CALCULATION SHEET i::",:a;,,,. ,A , ,,
CCN CONVERSION Project or Dcr/ m r SONGS 2&3 cale No. H-DSC-250 cCn no. cCN -
s:bject See Title Sheet sh. t No. ~7 REV ORIG!hATOR DATE IRE DATE REV ORICibATOR DATE lRE Datt 0 N. M. EL AKILY 11/07/91 Jf, l 4 METHODOLOGY 4.1 Stress Evaluation _
The fracture mechanics evaluation of the flywheels at Units 2
& 3 is based on the methodology of the vendor's design report (Reference 1). Only Mode I edge cracks at the bore were considered, as explained in Section 3, since the maximum stress component is in the tangential direction Conservatively, the depth of the keyway was added to(ethe c cra)k depth.
A combination of static and dynamic loads act on the flywheel simultaneously during operation. The total stress, therefore, is equal to the sum of the individual components due to each type of loading. Specifically, the total load (or stress) is the sum of the following:
(a) Rotatina Disk Stresses The tanaential stress, as a function of the radius (~r), and the angular velocity (w), due to rotation if given by the following expression (Reference 1):
Q=f -+- Y-+ -
y,, n y -
w VJ 4Ere.
l cs. 5s "f r f q " (Reference t)
BCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET '=,:at.... ,A , ,,
CCN CONV!R$10N Project er Der /me SONGS 2&3 calc h. M-DSC-250 Cc= no. cCN -
subject See Title Sheet sheet h , 3 REY ORIGlWATOR DATE IRF DATE REV ORIGIhATOR DATE IRE DATE I
0 N. M. EL AKILY 11/07/91 f-(, tj ,
(b) Interference Fit Stresses (AR)
The stress in the flywheel is due to the interference fit between the flywheel and the spider arms. The stress is a function of the interface pressure P,, which is a function of W and the initial interference AR.
It was calculated in Reference 1 that I '3 3 4 P3 (a b ll ego rpm) 0.33 4 Pg ( A t I G D 0 'ff")
wkm (eema i7,
- 2. n c psl (a6 Ilsrc rpm)
$6%)=
250 p5/ ( cd Isw rp m)
(c) Key Loadina The torque (T ) due to the deceleration of the RCL pumpiscalcu$atedasfollows:
To =Cdj ) I r This torque is transmitted to the flywheel through ,the axial keys, which results in a tangential load acting on the flywheel at the axial key. This load (Fm) is calculated as follows:
Fgay = -
cc (3) where is assumed that one key is only transmitting the coast down deceleration torque to the flywheel. (See Sectisn 3).
SCE 26426 NEW 4%
NES&L DEPARTMENT CALCULATION SHEJT ;;;: n ... ,m o, CCN CONVER$10m Project er Dcr/NMP SONGS 2&3 cale No. M-DSC-250 CC= no. c N-s:bject See Title Sheet sheet No. i REY ORIGlWATOR DATE IRE DATE REV ORIGlhATOR DATE 1RE DATE W. M. EL AKILY 11/07/91 O
[.M [g/cy /
(d) Seismic Loadina Seismic loads were calculated based on the following acceleration components: (See Section 5)
A g = 2.5 3 h y = L 53 Tangential stress due to horizontal acceleration is given by: (Reference 1)
W T= p F_LmA 2 0 where A = T (a-b) .
Bending stress due to vertical acceleration is calculated as fc11ows:
total distributed load (w) =
7 62
)
m
.7(b % t h-s+(g .,2.)h .t JC v
maximum tangential stress occurs at the inner l dlaw ter; and it is given by: (Reference 2)
Otb4 (4.,) l $(k)t-cqha'(mw W )= 2 (h (6* o L) Y(4 )]
h*4 a4(u'. )-b 2 (4) where A J_ p
=v.Lz= 3 -33 Shear stress is negligible (it was calculated at 106 psi in Reference 1).
! SCE 2S 426 NEW 4/90
~
NES&L DEPARTMENT CALCULATION SHEET n::, % ,. ,Aa o, CCN CONVIR$10N Project or DCP/mP SONGS 2&3 cale No. M-DSC-250 Ccn no. CCN -
s:hject _ See Title Sheet sheet No. N WEV ORIClhAfDR DATE IRE DATE REV ORIGlhATOR DAff IRE DATE O N. M. EL AKILY 11/07/91 [{ "[ (f f
-(e) Stresses due to Yibratory Potion This analysis is based on the maximum allowed eccentricity in the orbit of the flywheel (Reference 5) . The radial force, F,, is given by:
F, = e* r, a This radial force results in tangential stress of:
Fr-r= E 2.(b -0 ) 6 Cs) as cyp \cdreck in Vs u rf Nl
- OP 50W k-1 4-4 m-
) Fr 1
's FF l w <_
k_
p_
C Figure 4.1 Stress due to Vibratory Hotion SCE 26426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET :: :oic ... ,Ax ,,
CCN C0hVER$10N Project or ocP/ mr - SONGS 2&3 cale no. M-DSC-U0 ccm No. CCN -
scbject See Title Sheet SheetNo,!k REV ORIG!hATOR DATE IRE DATE REv ORIGlhATOR DATE IRE DATE 6
D N. M. EL AKILY 11/07/91 J 6, qt The total tangential stress, s , is given by the i
sum of the components calculated in this Subsection, i.e.,
o (total) = e (rotating disk stress) +
e (interference fit stress) +
a (key loading stress) +
, o (seismic) +
e (vibratory motion) (6)
An additional evaluation was made assuming pump rotor seizure.
An upper bound key loading, corresponding to failure in the curvic coupling, was calculated and the total stress in this case was based on the normal speed condition. Details of this analysis can be found in Section 8 of this calculation SCE 26426 NEW 4,*90
,. -r-1 e -'
NES&L DEPARTMENT CALCULATION SHEET i::: n ,0. ,A. O, CCN CONVERSION Project or DCP/MMP _ SONGS 2&3 calc No. M-DSC-250 CCN No. CCN -
srbject See Title Sheet sh..t No. 1 REV ORIGlhATOR DATE IRE DATE REV ORIGlkATOR DATE IRE DATE O N. M. EL AKILY 11/07/91 J.( " */4 g 4.1 Crack Growth Evaluation A radial crack, of depth d, was postulated, and the model shown in Figure 4.2 was used to calculate the stress intensity factor versus crack depth.
N OV o y%
A'c r n,* / (i:a 0/4 , %;,
( _ _ ._ _ _ _
w ,d W-> ,
-> 2 <-
g b - ct m
l A. Postulated Crack B. Analysis Model Figure 4.2 Model for Brittle Fracture l
l SCE 26-426 NEW 4/90
. NES&L DEPARTMENT CALCULATION SHEET ::, L. ,Ax ,,
CCh C0%v[RSION Project or DCP/MMP SONGS 2&3 Calc No. M-DSC-250 CC4 NO. CCN -
Subject See Title Sheet sheet No. (
REV ORIGlhATOR CATE 1RE DATE REV ORIGINATOR CAtt IRE DATE 0 h. M. EL Atitt 11/07/91 [-6. U/ q The computer program PCCRACK was used to perform the analysis, and calculate the stress intensity factor (K3 ). Based on the calculated Kr , a comparison was made with the critical stress intensity factor of the flywheel material (K 3c) to calculate the safety factor.
A erack growth evaluation is made based on A K=K for one 3 cycles.
I i
l i
1 l
l SCE 26-426 NEW 4/90
NES&L DEPARTMENT
' CALCULATION SHEET ik,;%,. ,A. ,,
CCh CO*VER5tDN Project or DCP/ mr SONGS 2&3 cale h. M-DSC-250 CCN No. CCN -
scbject See Title Sheet sheet h. b REU ORIGlhATOR DATE IRE DATE REV ORIGlhATOR DATE IRE DATE O N. M. EL AKILY 11/07/91 Jf, //[p[f I
5 DESIGN INPUT
- Fivwheel
Description:
(Reference 1)
Figure 5.1 shows the assembly of the flywheel, the shaft and the eight spider arms. The flywheel has the fons of a disk with outside diameter of 82", inside diameter of 31" and thickness of 7.9". The flywheel is attached to the eight rotor shaft spider arms by a hetvy interference fit, and keyed by two axial keys and six circumferential keys.
- Material Properties: (Reference 1)
Material - ASTM A-543-72 GrB, Class I Young's Modu 1Ws (E) - 30X10' psi Poisson's Ratio (p) - 0.3 g$
ci debO A Y , ,[
L 3:
, ;f/ y-ve1 see dekc) A i o ns
v
(
] I m
y ~
7 M
_.4
'l , p f
u l
0 M
31 # //
< ;- --w 7.q --
g2 //
l
! Figure 5.1 Flywheel, Spider Arms and Shaft Assembly l
! SCf.26-426 NEW 4/90 i
I
. MES&L DEPARTMENT CALCULATION SHEET n;:,: L ,. ,A E o, CCN CONVER$10N Project or DCP/MMP SONGS 2&3 Calc No. M-DSC-250 cch h0. CCN -
subject See Title Sheet sheet No. !
N(v (>R I Gl h ATOR DATE IRE DATE REV ORIG!kATOR DATE 1RE DATE O N.M. EL AtiLY 11/07/91 J,d, //[g/c,f I
Hass density (p) -
0.000735 lb, sec8 /in' (490.8 lb,/f t ) 3 Yield Strength - 85 ksi Ultimate Strength - 105 ksi Critical Stress intensity factor (Kic ) - 220 ksi/in
- Rotational Speed (Reference 1)
Design Overspeed -
1500 rpm -
(w = 157.1 rad /sec.)
Normal Speed -
1180 rpm (1200 rpm used conservatively)
(w = 123.6 rad /sec.)
- Weicht (Reference 1)
Weight - 10,115 lb I
SCE 26-426 NEW 4/90
NES&L DEPARTMENT
... .. CALCULATION SHEET = n ho. ,m ,,
CCN C0hvfRSION Project or DCP/MMP SONGS 2&3 Calc No. M-OSC-250 CCN ho. CCN -
subject See-Title Sheet sheet No.
REV ORIGlhATOR DATE 1RE DATE REV ORIGlhATOR DATE 1RE DATE 0 N. M. EL AKILY 11/07/91 J-6, Ilhg j
/
6 REFERENCES
- 1. " Flywheel Design Report, Flywheels for Reactor Coolant Pump Motors for: Southern California Edison Company San Onofre Nuclear Generating Station, Units 2, and 3", Report No. 0501-4827, Revision 1 Allis-Chalmers Corporation, October 4,1978.
SCE number AA001-0001.
- 2. " Formulas for Stress and Strain", R.J. Roark, McGraw-Hill book Company, 4th Edition, 1965.
- 3. Letter from H. Stickel, Westir:ghouse Site Services Manager to S. Gosselin, SCE dated October 26, 1991.
Subject:
SONGS Unit 1 Flywheel Specifications.
- 4. Final Safety Analysis Report (FSAR), Units 2 & 3.
- 5. Document: SO 23-3-1.7, " Reactor Cooling Pump Operating Procedure, Unit 3."
- 6. ASME Boiler and Pressure Vessel Code, Olvision 1,Section XI;t977.
- 7. Document: 50 23-151-018, Revision 1, "CE, Ultrasonic Examination Procedure for Reactor Coolant Pumps, Flywheels and Balancing Devices."
- 8. Document: 50 23-922-35-2, Induction Motor Speed vs. Torque &
current curve.
- 9. Document: SO 23-922-36-4, Induction Motor Calculated Time vs.
current curve.
BCE 26-426 NEW 4/90
NES&L DEPARTMENT '
.. .. CALCULATION SHEET : : n ,,. ,
,A. O, CCN C0hvERSich
-Project or DCP/MMP SONGS 2&3 Calc No. M-DSC-250 Cc= no, cch -
subject See Title Sheet sheet No. l7 REV ORICthA10R DATE 1RE DATE REV ORIGlhATOR DATE IRE DATE O N. M. EL*AKitY 11/07/91 76, h[ tj [
7 NOMENCLATURE a = Inside radius, in A = Area, in' A, = Horizontal acceleration, g.
A, = Vertical acceleration, g.
b = Outside radius, in, d = Crack depth, in.
E = Young's modulus, psi F = Force, lb.
K3 = Stress intensity factor for Mode I cracks, ksi/in.
K 3e = Critical Stress intensity factor for Mode I cracks, ksi/in.
I, = Polar moment of inertia, lb, in'. -
m = Hass, lb,.
N = Number of cycles y = Poisson's ratto W = Angular velocity, rad /sec.
P, = Interference fit interface pressure, psi r = Radius, in.
p = density,lb/in 3 AR = Interference fit interference, in.
o, = Radial Stress, ksi, o, = Tangential Stress, ksi.
1 SCE 26426 NEW 4!90
NES&L DEPARTMENT CALCULATION SHEET '::::C,0
. ,Au ,,
CCN CONVER$10N Project or DCP/ M P SONGS 2&3 Calc No. H-DSC-250 CCn no. CCN -
s:bject , See Title Sheet sheet No. IN REW ORIGluAfoR DATE IRE DATE REV ORIGtkAtoR DATE IRE DATE s
0 N. M. EL AKILY 11/07/91 J. C u[ g, ,
~T.L ~
e, = Axial Stress, ksi.
T = Time, sec.
t = Th8 ckness, in.
SCE 26-426 NEW 4,40
NESAL DEPARTMENT CALCULATION SHEET '::!:L. ,Aa o, CCM CONVIRSION Project er ocP/mr SONGS 283 cele no. M-OSC-250 ccn no. cCN -
s:bject See Title Sheet _ sheet No. Ii REV ORIG!h4 TOR DATE ltE DATF REV ORIGlkATOR DATE Itf DATE O N. M. EL AKILY 11/07/91 [-6 I/h 7
/
8 CALCULATIONS l 8.1 Stress Evaluation i I
L o b*
4-N s:
n) (2) (3) M (g)
-j o --o o -o a 6575 0 x >
12.750 , _ _
I C1 .12 t> v m, 2E5"
, 7-.
Figure 8.1 Locations at which e, was evaluated SCE 26-424 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET :::" n ,.. ,m ,,
CCN CONVIR$10N Projact or ocP/ m r SONGS 2&3 calc No. M-DSC-250 CCn no, cCN -
J scbject See Title Sheet sheet No. 2.0 Rtv ORIGlkATOR DATE IRE DATE REV ORIGlhATOR DATE stE DATE o u. n. EL-Arity 11/07/91 T (, . */y/c,f
/
was evaluated at coaal intervals between r=a langential and r=b, asstress shown e,in Figure 8.1, usir.g equations 1 through 4, Section 4. These stress components were calc'alated for nonnal speed (1200 rps) and design overspeed (1500 rpm), as explained below.
(a) Rotatina Disk Stresses Equation (1), Section 4, was used to calculate the tangential stress due to disk rotation at normal speed (N=1200 rpe), and design averspeed (N=1500 rpe).
Results can be summarized as follows:
Location (Fig. 8.1) y,-nors (ksi) g,-overspeed (ksi)
(1) 16.0 25.9 (2) 11.5 18.6 (3) 9.1 14.7 (4) 7.3 11.'/
(5) 5.5 8.9 ACE 2s-426 NEW 4,90
NES&L uEPARTMENT CALCULATION SHEET =,:% ,, . ,x ,,
CCM CONVIR$10N Project or DcP/mr SONGS 2&3 cale No. M-OSC-250 Cc= no. ccN -
schjeet See Title Sheet Sheet No. b REV ORIGINATOR DATE IRE DATE REV ORIG 1hATOR DATE IRE DATE N. M. EL*AKILY D 11/07/91 J. 6 Uh p g 1
(b) Interference Fit Stresses Equation (2), Section 4, was used to calculate the tangential stress due to the traterference fit at the bore of the flywheel. This stress component is evaluated at normal speed (N=1200 rps) and overspeed (N=1500 rps). Results can be summarized as follows:
Lofation (Fla. 8.11 g,- nons (ksi) g,- overspeed (ksi)
(1) 3.9 1.1 (2) 2.2 0.6 (3) 1.5 0.4 (4) 1.2 0.3 (5) 1.0 0.3 SCE 26-424 NEW 4/oo
l NES&L DEPARTMENT
.. .. CALCULATION SHEET i:;n ,,. ,Aa ,, l Project or ocP/MHP .50NGS 2&3 Calc No. u, m, . , ,.... . n M 050-251_ ccm 6 ,
subjnt See Title Sheet $heet No, M
' itV ORIGlhA50R DAtg IR( Datt egy pat;lhAtog pagg ggg gagg
, O h. !
- L* AKILY 11/07/91 ] . (, #hi f .
i (c) Keyway Load _ing Per Reference 1, the keyway dimensions are:
Keyway Width = 0.750 in.
K:yway Depth a 0.470 in.
There are two keys 0.75"X0.75" 180' spaced.
In this subsection, the key loading due to flywheel
- inertia at the time of RCr trip from normal operating condition will be determined. This condition results in maximum rate of change in the pump speed vs. time.
Polar inertia moment of the flywheel, per Reference 2, Page D4, the sectional polar moment of inertia ist 12 77)
P:-
CifCeIe Y I C # "' ' I haf A W t
Multiplying by the rnass density [and flywheel thickness t, 3 2
I
,- o I.Ah) P 3 D = 11( 6 h b n -
1
)p T f # g b
$CE 26-426 NEW 490
. . _ _ . . - . ~ _ _ _ _ _ _ _ _ _ . . _ _ _ _ _ _ , . . . . . . _ , _ . _ . _ _ _ . _ . . _ - _ . . . . - - . . _ _ _ _ _ . . - -
WES&L DEPARTMENT
." ' CALCULATION SHEET :::1: % ,,. ,Au ,,
CCN (DhrtR$1DN Project er Dcr/mer SONGS 2A3 cele No. M-DSC-250 ccN no. cch -
scbject See Title Sheet , sheetNo.23 Rfy OplGINATC* DAlt Itt Daft itV CalGlhATOR DATF lit Daft 0 D. LAPICH 11/07/91 J. (, l'
<; g f
for wheel with a hole in the center, subtract inertia moment for8 the missing mass and using steel density y =
0.283 'b/in
.rP
=
8[b - A . -
0.223 3 yg . 7. cf
%, ,t b =tl r , p 17.5 "
-- 2 6 Il 3.5 lb I" NC' l%a s[
Toraue Due to Deceleration Using a generally known formula, i r (bM)^
Q- !? d&
w ke ,
jg hc Optr I Cr acc e le r A b ien d& U J
SCE 26426 NEW 4,40
NES&L DEPARTMENT c-CALCULATION SHEET = : L ,. , ,, ,,
f(N C0hVIR5104 Project or DcP/MMP SONG 5 2&3 talc No, M DSC-250 (cn ND. CCN -
subject See Title Sheet $heet No. 2-t(V 08101h4104 Call It! Daft 2(V 041Cthaft* OAll !#( DAtt 0 p. KAPitu 11/07/91 7. (,
8th g To calculatek, used is F re 3.1.2.1 from the updated FSAR, Reference 4. It is ,,sumed that the core flow is closely proportional to the pum) speed and therefore could be used to calculateW witi sufficient accuracy, dy ,
I iniHa\ 00 I YI*"d"'~ =
Ti~- lwe >
Ov3 75 Si 4 60 f' ).- 2. 7'1f Yo Ntoc ~
It follows that, 4 l = FC .79 fx 2. G il 3.T - 22O a90 e'nlb ,
Since at full pump speed the shrink pressure at the flywheel bore is very minimal, it is assumed that the entire inertia torque (T*) is being transmitted to the shaft via shaft key. One key is conservatively assumed .
to support the entire torque load, as shown in figure B.2. .
l I I
% o M7" o. 7t h a
/y n, I
figure 8.2 Key loading for one key l
sCE 26-426 NEW 4/90 ,
4
. -,--_;-,._.-.--,-.,-....-,_.-...--,--._-,-,-_m- .~.c.-_,_-,~,-,-_-.--.,m... , - , - . . . . . . - . . . . , _ , - , , . .
NESAL DEPARTMENT CALCULATION SHEET "?, ',"lc, . ..c., _ <, _ _ l Proret or DCPMMP bS Calc No
-2EO 7~Cc$4$
Subject $8I 7 / Ibb $NE67' Sheet No. A(
sii v i onomaton past ms oats nav rwicmaton oatt #Nt omir g
/NtJJL-AkM "h/4I Tt "lt/c, g 0 ,. 4 7\ 4 *)
F
~72 :
xR F fF =
h+
~
0375.
-lT.d7 in Fe9 = =-- lLy Dgl ll0
' R-F k ey we y avrfa to \oa0 hn one k<
cr
% a 6od . a,s2 ps; N+
~
y b 399J.9
.m,... .. . . .. o _,_..
\
NES&L DEPARTMENT CALCULATION SHEET ;;;1:%,,0. ,Am ,,
CCh ConVER$10N Pr: Ject or ott/ mr SONGS 2&3 -- cale no. H-OSC-250 ccm ho. CCN -
5:bject See Title Sheet sheet ko. 2b RfV OR I GlhA10R DATE let Daft REW ORIGlhATOR DAtt IRE Daft 0 N. M. EL AKILY 11/07/91 J-( #' eg (d) Seismic Loading Tangential stress due to DBE load was calculated using equation (4) which gives the maximum value at the bore due to vertical acce!eration A,. This maximum value was conservatively used at each of the five locations defined in Figure 8.1. The DBE stress, which was used in combination with other stress components under nonsal conditions, was assumed to be equal to one half of the DBE load. The full DBE load was used in the overspeed case.
Results can be summarized as follows:
- Normal conditions (N=1200 rps),
u, = 0.4 ksi
- Overspeed conditions (N=1500 rps),
e, = 0.8 ksi The tangential stress due to t$e horizontal component of acceleration (A,) was calculated in Reference 1 at 0.03 ksi; it was ignored in this analysis since it is very small compared with the other stress components calculated in this section.
scc 24424 NcW 430
NES&L DEPARTMENT
.. .. CALCULATION SHEET :*a , . ,Ac, ,,
C(4 CChWIRSID4 Project or DCP/MMP SONGS 2&3 Calc No, M-DSC-250 Cth ko. CCN . 1 Subject See Title Sheet Sheet No. b7 REV OAICIAATOR DAff 111 Daft AfV OR10thA10R Daft let Daft i 0 0. KAPICM 11/07/91 f. G , l (e) Vibratory Stres.3_dutto Synchronous Orbit l
1
. -s h /< FT e
% Fl wheeI y ceder ob .re v/b figure 8.3 Unit 3 RCP's, maximum allowed vibration " Peak to Peak" is 20 mils 2 (Reference 5) 1.e. r = 0.010 in.
4 Flywheel mass, g) =. I O Il d (b (Socl.w 5 )
m-
- 9H5 n . 2.
I6sec'/cn 8 3 s'6 SCE 26426 NEW 4f90
_ . _ . _ _ _ . . . . _ . . , - . _ _ _ _ . _ . . _ , . . - . . , _ _ _ . - . . . . _ , . _ _ . _ . . , , , _ . _ . _ _ . . . . . , _ . _ _ _ , , _ . . _ _ _ _ . . _ ~
NES&L DEPARTMENT CALCULATION SHEET ':::,: % ,,. ,Am ,,
CCN ((*VER$1Ce trej ut er ocr/ mr SONGS 283 cate me. M-050-250 CCm ho. CCN .
subject See Title Sheet sheet no. 2 4 try CalClh410R DATE IRI DAff R(V (ilGlhATOR DAff let Daft 0 D. LAPICM 11/07/91 J.( 't
/
Flywheel radial force, Assume design speed = 1500 rpa (O = 2 M 'YO? = l1 7.I n d /s oc..
6o
% = rn r as ' = as7 th og (h
++4 +t t l
I V FR figure 8.4 SCE M-4M NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET :n"!: % ,,. ,Am ,,
C(h (Oht[R$1DN Project or Dcr/mr SONGS 2&3 cele no. H-DSC-250 CCN h0. CCN -
5:bject See Title Sheet Sheet No. '7 t(V (alClkA10R DATI Itt CAit REV CalGlhA10R DAff Itt Daft 0 D. LAPICH 11/07/91 [.( ' _ /c, l Assume inner half is supported by the shaf t, while outer half tends to fly outward (Figure 8.4)
Stress due to synchronous orbit,
!=R 6467 Y= = - = lb psi a 2e. ; x v. y >c t 8 .2 " J
, il
,/ X
, I
- , , g
/ ,l, ,/
/ 7
,e .
lV Figure 8.5 SCE 26426 NEW 4/sc
. l NES&L DEPARTMENT l CALCULATlON SHEET =,:ai<,,,. ,,, ,,
I CCW CDhtlk$104 Project or otr/mr SONGS 283 cele no. M-DSC-250 Cth 40. CCN -
s m .et See Title Sheet 56..t u.. ? o REV CalGlhAf($ DAfl lt( DAf( R[V ORjG[hATOR DAl[ jg[ DAl[
0 W. M. (L Aritt 11/01/91 f.( U[,3 c,,
1 l
1 ThetotaltangentialstressisgivenbyequationI. !
It is sunnarized in Table 8.1 below:
Table 8.1 Total Tangential Stress Distribution Location Total Tangential Stress, e, (ksi)
(see Figure 8.1)
Normal Condition Overspeed Condition (N=120 rps) (N=1500 rps)
(1) 25.2 32.7 (2) 14.1 20.1 (3) 11.0 16.0 (4) 8.8 12.9 (5) 6.9 10.0 a
)
l
NES&L DEPARTMENT CALCULATlON SHEET
- in.... ,,o o, Cth C0ht!R5104 Project er ocr/Mur SONGS 283 cele No. H DSC-250 Ccn no. CcN .
Schject See Tit 1e Sheet sheetno.3I arv caicinatcm cast set oatt etv omisinatoe l cart iet oait 0 W. M. It AtiLY 11/07/91 J - [, "h .; e 8.2 Crack Growth Evaluation The computer program PC CRACK was used to perform linear elasticfracturemechanics(LEFN)analysisonthesingleedge crack plate shown in Figure 8.6.
3 2.7V s i O
Ve r.
7 s 1 Vs s ran g Mc,-
m,j
, \o V s
- c. n ;
4 ,- - >
d N _
Figure 8.6 LEFM Single Edge Crack Plate The figure shows the normal and overspeed stress distributions based on Table 8.1.
Analysis was performed for crack depth (d) up to 3". Results of the analysis, in the form of stress intensity factor (K r) versus crack depth (d), are plotted in Figure 8.7. These results are also listed in Table 8.2 SCE 26-426 NEW 4,90
- . - - - . - - . . - . - - . . . . - - . ~ - . - - , _ . - - . . . . . , . . . . - . . . . . . - - . - . . . - - . , . . - _ . . - . - - , - . .
NES&L DEPARTMENT
.' ' CALCULATION SHEET =l:L ,m o, CCN CDhWIR$10N Project er DCP/mt _ SONGS 2&3 cale no. M-DSC-?50 cca no. ccN -
s:bject See Title Sheet sh..t no. 3 2_.
AtV OtlClkATOR Daft itE Daft itV ORIGlhaf0R Daft Itt DAlt
- v. M. IL AtiLY D 0 11/07/91 f. (, h,9 8.3 JLumerical Results Stress intensity factors are given for different crack depths, 0<d5 3" in Table 8.2. Safety factors can be calculated based on the values of K (from Table 8.2) and the critical stress g
intensity factor K ,3c as follows:
SF =
W1 where K7c 22okri[n ((2e[emmlj Safety factors were calculated for 3 representative cases based on design overspeed condition:
(a) %" Crack This is larger than the smallest detectable crack
(% of the keyway depth) l 5P=2*i.41 = \0 3 l
l (b) Keyway deyth + 1/8" crath In this case, d = 0.47 + 0.125 = 0.595" 5.F = = 4.74 M5 l
l SCli 26-426 NEW 4/90
NES&L DEPARTMENT CALCULATION SHEET l:::n,,,. ,<, ,,
CCN C0ht(E5104 Project or otP/MMP SONGS 2&3 Calc No, M-DSC-250 ccm 60. CCN -
$sbject See Title Sheet Sheet No. 33 Riv ORlCthA104 DATE lAf CAff AtV OR I Clh ATOR CAff lit Daft 0 N. M. (L-AKILY 11/07/91 f-[ . "[j l
(c) Crack depth e.guals twice the keyway A pth In this case, d = 0.94" SC = _
.- 3 7E GC1 The crack growth rate is estimated using Reference 6. Maximum crack growth rate (for crack depth of 0.595") is 50X10 in/ Cycle.
Conservatively, 100 cycles are assumed total crack growth = 100x50x10
= 0.005" SCE 26-476 NEW 4%
. ,,..~.... -. ,. . .- -.-.- --._. - - ..- -.-...._.. .- . . _ . . . - . . . - , , . -
NES&L DEPARTMENT CALCULATION SHEET [~ lc,.
..c.,_,
GCN C(NYt 84 BON
< Project or DCPMMP GO% S-3 Ca6e No. M- D SC- 2.50 eneCCN.
Subject G' Gl= TI TL.E MlG E *T- snoot no 30
.m . . . . o.,. .. o.1, .m .. .... ,, ....
g foK u.m.EL- A k tLY lt/rl*\l 3. t. "l3l9 /f ~
b b t i O $
4 '\
1 4<
% t , m
% \ o
\ \ e a
W" wa
\
m
\.
\
m i
g ik 15 m s"N=. %x
% \
E 3 U 4 \
m a
Jh
- u. ,k
, y v
- i, e
n5 H a
b v2 u 3x k g u
\ \, ~
- j k,
t,,, \s ,
Q d b
'q k n '5 O
I b
h k k b b k k k $
(HONI 100H 3WYnOS ISM) IM
.e. .... . .. . . ..
Q .~ , . . .
NES&L DEPARTMENT s
CALCULATION SHEET "L ,
cv corn t um m., ,__
Project or DCP wp e b3 Calc No M-Of C 15 O ccm CCN-.
>c Subject GG5 7 i f~ C \4 F GL Sheet No. ">
HIV i DN IG S. A 1 CW D&fE INE DA TE R(V ($ 610sA T Odt Daf t j istg paTE L-M s LY \\My }.( _ "[fty , l'
/\ /N! ta O
pc-CRACK (C) COPYRIGHT 1984, 1988 STRUCTURAL INTEGRITY ASSOCIATES, INC.
SAN JOSE, CA (408)978-8200 VERSION 2.0 Date: 27-Oct-1991 Time: 9:55:57.64 LINEAR ELASTIC FRAC"IVRE MECMANICS EVALUATION NORMAL crack model: SINGLE EDGE CRACKED PLATE PLATE WIDTH (b)= 25.5000 STRESS COEFFICIENTS CASE ID CO C1 C2 C3 -
DESIGN 31.7330 -1.7403 0.0360 0.0000 NORMAL 24.2822 -1.SO96 0.033$ 0.0000 (2)
CRACK CASE -----STRESS
N INTENSITY FACTOR *----- W U) C c f 'c ti C SIZE CASEEL)
DESIGN NORMAL 5: 2E OCSIGN 9 t,M AL-0.0600 14.805 11.325 1.5600 74.708 56.761 0.1200 20.928 16.006 1.6200 76.098 S7.801 0.1800 25.621 19.589 1.6800 77.462 58.821 0.2400 29.573 22.605 59.820 0.3000 33.050 25.255 1.7400 78.799 27.647 1.8000 80.112 60.800 0.3600 36.190 1.8600 E1.402 61.762 0.4200 39.073 29.842 1.9200 82.669 62.706 0.4800 41.754 31.880 1.9800 83.914 63.633 0.5400 44.268 33.791 2.0400 85.140 64.545 0.6000 46.644 35.594 2.1000 86.346 65.441 0.6600 48.900 37.306 '. 2.1600 87.533 66.322 0.7200 51.053 38.938 2.2200 88.702 67.190 0.7800 S3.116 40.500 2.2800 89.854 68.044 0.8400 55.098 42.000 2.3400 90.989 68.884 0.9000 S7.005 43.444 2.4000 92.108 69.713 0.96.0 St.853 44.838 2.4600 93.212 70.529 1.0200 60.639 46.186 2.5200 94.301 71.333 1.0800 62.371 47.492 2.5800 95.531 72.244 1.1400 64.053 48.759 2.6400 96.905 73.265 1.2000 65.689 49.991 2.7000 98.273 74.281 1.2600 67.283 51.190 2.1600 99.635 75.292 1.3200 68.838 52.358 2.8200 100.990 76.297 1.3800 70.355 S3.498 2.8400 102.339 77.297 1.4400 71.038 S4.610 2.9400 103.683 78.291 1.5000 73.288 55.697 3.0000 105.020 79.283 (1 ) OvGY5 pe, cl c o = isoo r e-)
(7.) M m el ( b/ : 20 0 Y P " J T u ble IV 7 m ....,. . . . ..
o...-._._ l
NES&L DEPARTMENT
.. CALCULATION SHEET :: L : L ,. ,Ac, o, (Ch (0hyIR$tDh
- Project or DCP/MMP ,,,1Q1{95 2&3 cale No. M-DSC-250 cch 40. ccN -
subject See Title Sheet sheetNo.,)
Olv ORICibATCA CAtt ilt CAff WIV ORIC1haton DAtt ist CAtt D. t.APICH 11/07/91 0
f.{
l t ;
8.4 Postulated Pump _ Seizure i It is assumed that the p p impeller, or the 24" main pump
, bearing, seizes, resultin imost instant angular deceleration '
of the pump shaft.
^
As shown on figure 8.8, the pump shaf t is coupled to the motor shaf t via coupilny spacer, which is coupled to the pump shaf t via.curvic coupling.
Torsional Loads Compared is torsional load into the curvic coupling, with the torsionci load into the flywheel keys.
The load into the curvic coupling due to pump seizure consists of:
(a) Electric motor rotor inertia load, Ehl5, l-(b) Flywheel inertia load The load into the flywheel keys consist of:
(b) Flywheel inertia pnh Therefore, a conservative assumption would be to ignore the elettric motor rotor inertia, thus assuming equal torque for both, curvic and the flywheel attachments. .
Task Calculate torque required to fail the curvic teeth-and then L
calculate the stress level in flywheel keys at that point.
l t
SCE 26 426 NEW 4/90 l
L
NES&L DEPARTMENT CALCULATION SHEET nnv cew ra ca. . .c(._.
Propet of DCP MMP Canc No A1 - OIC- 250 7eCc$.I Subject SU Y!I b b bY Sheet No hty i onaceta t on 0418 i s4 Datt sel y cm omaton Datn mt Daf t
[o\ b. k ABCN Ml7/ A \ ] (, 'ff[q g [\ ,
~
. Y
- L _ Motor Stand Motot Half ry Loop Water ~
'%,.;._. ._ . '--., fd*b Couphng 1perature. ,
= ',
d Primary Loop Water i ; !! ~ ',
onent Cooieng Water +' i H 'l Couphng Spacer
,j '
- l l [ / *g/' vy c ' h
- f-;
j' .;{ sfn /0 4d, [j
_ ,4. e. z
. Egg .
, g M.cs.n.c.i sesi cartridge l ,/
- c.,..,.,w
.. . o y
- a,,w 3 3 (gi: kg j . . ca
_ ,l, i N - ;h 4,i mis - '~~ .----
ss.rt N gJ %
,jC i (N;h:'.N }
.f , .b-> NVs'Q Rl'Q'C;.'y?'MsNG s
f d: N's\ 'N:;;sN xNJ;J:N'Qs'CN' Pump Cover s N's\sN s xxN xx ss;s; s J .
NxN a. e: 9 '
i s\x s. m L p j' p kN' AsNN,N;'NN s xsl4' xNN 1
- ,;N\\ , j.=.m.d . QN xN'< NNN:y'
- , , e" ,
rm,
~>
. integrei Heat E.enenger I , ,.
- 'k id' syo, .t.t c bh
')
'Y,T,d,- ?: & //// B**na9
- 4. s // ,
q . i ,en.,
s y ,-
.. /
7/,/D , ~-
pf: ' ;' f,' ', & i
.(/
./ /
4-e// Pump Case t i'gnre 4
. . .. ... . . . .. g .., ,
NES&L DEPARTMENT '
CALCULATlON SHEET l:::!: % ,,. ,m c, !
CCN C04vtR$lth Project or DCP/>tiP SONGS 2&3 Calc No, M-D10-250 cCn no. CCN -
subject See Title She_f1 Sheet No.
RIV ORIGihATOR DATE 111 0Aff AIV ORIGihATOR Daft itt DAf(
0 D. KAPICH 11/07/91 76, '[j i
(urvic Dhensions TAFJ
~
, , - 1.T4%.75 -,,' , y g 'l ST A tl
- q.
t n-e., s F,,,is Total force Acting on Curvic Teeth.
About % of the curvic perimeter is occupied by teeth from each side.
M utcre S ide
(
\
I 1 p
/ ( TA tl
{ _
g< _.
l
\ I l
h e s de figure 8.10 Approximate crossectional sheer area of each teeth side, SCE 26-426 NEW 4!90
NES&L DEPARTMENT
.' CALCULATION SHEET = n ,,. ,A,, ,,
(CN (0hv[kS104
- Project or ocP/mP ,_SQ!$5 2&3 Calc No. M DSC-250 (Ch ht CCN -
subject See Title Sheet _ sheetNo.3Y 8tV (alGthAfC* DAff itt DAff at y ORIGlhaf04 Daft 161 CAlt 9 o, aArlen 11/07/91 ] (, "[
Total annulus area = )#: l 9 2- tY
\-----
f . 2. Y b 3pg
- I 41 i n 2-Per
Reference:
523-922-157 "RCP Pump Manual" Pump Side Material:
ASTM 351-Gr-Cf 3A Motor Side Material:
ASTM 182-Gr F6 Sn = 70 ksi Ultimate Shear Strength = 7V 0g9 fi Now, the f,,, can be calculated, at the point of curvic teeth failure.
f,,, = A ,
3 53 , = 9.105 35,000 fiAn = ll8.Jp0_ *.1)L Lorque at failure.
Ty = F,,,. Ri,, = 318,700 X 3.2125
= LQL5.693 in. Ib, ,
Now, apply the torque T , to the flywheel keys, the shear forces acting on 2 keys is, F,,N/2.Ry e _ loIS M 3
2.v U." . 6 i fsn
- 33642 llo SCE 26-426 NEW 4/90 -
NES&L DEPARTMENT
.' CALCULATION SHEET =:Mt,,0. , Aa !
cth cowiss!04 Project er DCP/ HHP JQ!{G1M3 Calc No. M-DSC-?,10__ CCh hp. CCN -
Subject See Title Shet} $heet No. 'I O Rfv 0#10thatoa catt lat l tatt sty cR i cIh Af on tAtt tat tatt
~
p orica ufor/91 ..J . (,
o
.--.s}TY L;(L, o Each flywheel key has shear area, As , = 0.75 X 7.90 = 5.925 13 '
Keys shear stress, s,,, 33 M , sf72 b's 5 .0f t 5 o' %4 L Hoop stress in the flywheci =
79<o.7% ,
= 11356 % f,S{
Assuming normal speed conditions, it follows that:
Maximum hoop stress at the bore = 11.356 + 16.0 + 3.9 =
31.3 ksi Where stresses due to rotation and interference fit have been included (seismic loads were excluded).
Since crack growth evaluation was performed for maximum stress of 32.7 ksi (see Table 8.1), this case is enveloped by the results of Subsection 8.3. There will not be crack growth under rotor seizure conditions.
l l
l l
l SCE 26 476 NEW 4/90
. . , _ . . _ - . . _ _ , _ .-. , -,. , . _ _ . _ , , , , . . - . ~ . ~ ~ . . . _ - _ , , _ . . . _ . - - _ _ - . . . ~ . - . . - - _ , . _ ~ _ - -
NES&L DEPARTMENT
/ CALCULATION SHEET mgai<,,,. m, ,,
CCN CONVIR$10N Project or ocP/MMP _ SONGS 2&3 cele no. M-DSC-250 CCh h0. CCN -
5 bject See Title Sheet Shut No. If I t!V ORICthA10R DAff let Daft sty CelClhATOR DAtt att DAlt 0 W. M. tL AKILY 11/07/91 J -(, *['[4 (
8.5 Key Loadina Due to Motor Start-Up The maximum angular acceleration during motor start up was calculated using the motor speed vs. time data Table 8.3.
(Table 8.3 is based on References 8 and 9)
Table 8.3 Time Speed (Seconds) (rpw) 0.5 200 4.8 590 6.0 790 7.0 932 8.0 1109 8.4 1132 The angular accelerat4* 41.9 rad /sec at T = 0.5 sec. 8
= 10.1 rad /sec' at T = 8 sec.
The corresponding key load can be calculate { based on the methodology descrf bed in Section 4, or by appiffd simple ratio to the results of Section 8.1.
Key Load = 22.6 ksi at t = 0.5 sec.
= 5.5 ksi at t = 8 sec.
SCE M-4M NEW 4,10
. _ _ _ . . . . _ __ _ _ , _ _ _ _ _ . - , . , _ . _ . _ . _ _ _ _ . ~ --._,_ .-
(
NES&L DEPARTMENT CALCULATION SHEET ';;:nh.. . ,m ,,
CCh CohvlRilon Project er ocr/m r SONGS 2&3 ceic no. M-DSC-250 (Ch h0. CCN -
5:bject See Title Sheet sheet No. O ttV CelClhATOR DAff Itt DAff tty Ca lGikalut DA!! til DAlt 0 m, u. EL AtlLY 11/07/91 f ff[gg
. A, - ~. .
Maximun ten;nMital stress is calculated based on the actual flywheel SNed utf^ng equation (4) as follows:
Tangentled stttsis due to interference fit
= 7.09 ksi at 100 rps
= 3.35 ksi at 1180 rps Rotating disk stress = 0.5 ksi at 200 rps
= 16. ksi at 1180 rpe Maximuu total tangential stress = 22.6 + 0.5 + 7.09
= 30.2 ksi, at 0.5 sec.
Maximum tottl tangential stress = 3.35 + 16 + 5.5
= 24.9 ksi, at 8 sec.
Both cases above are enveloped by the analyzed overspeed condition tilnce the maximum tangential stress in that case is 32.7 ksi.
- SCE 26426 NEW 4,90
_ ,._. __ _ , _ . _ . _ _ _ . -