ML19341A358

Turbine Missile Rept (HP296-LP281-LP281), CT-24821 Revision O.Related Correspondence

ML19341A358
Person / Time
Site:	North Anna
Issue date:	08/31/1980
From:	WESTINGHOUSE ELECTRIC COMPANY, DIV OF CBS CORP.
To:
Shared Package
ML19341A357	List: ML19341A356 ML19341A358
References
HP296-LP281-LP2, HP296-LP281-LP281, NUDOCS 8101230109
Download: ML19341A358 (26)

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TURBINE MISSILE REPORT

. (HP296-LP281-LP281)

CT-24821 REVISION 0 AUGUST,1980 VIRGINIA ELECTRIC & POWER COMPANY .

NORTH ANNA STAT!ON, UNIT NO.1 SERIAL NUMBERS 13A3591-1, 23 A3592-1, 23 A3593-1 l

1 WESTINGHOUSE ELECTRIC CORPORATION 8i01230/07' STEAM TURBINE GENERATOR DIVISION

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NO WARRANTIES, EXPRESS OR DIPLIED, INCLUD-ING WARRANTIES OF FITNESS FOR A PARTICULAR PURPOSE, OF MERCHANTABILITY OR WAR-RANTIES ARISING FROM COURSE OF DEALING OR

. USAGE OF TRADE, ARE MADE REGARDING THE INFORMATION AND DESCRIPTIONS CONTAINED HEREIN. In no event wfR Westinghouse be responsible to the user in contract, in tort (including negligence) -

or othcrwise for any special, Indirect, incidental or consequential damage or loss what.oever including but not limited to damage to or loss of use of equipment, plant or power system, cost of capital, loss of profits ,

or revenues, cost of replacement power, additional ex-penses in the use of existing power facilities, or claims against the user by its customers resulting from the j use of the information and descriptions contained j herein.

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WESTINGHOUSE ELECTRIC CORPORATION STEAM TURB1NE INFORMATION

- CT-24821 AUGUST,1980 REVISION 0 TURB1NE MISSILE REPORT (HP296-LP281-LPM: 8 1 INTRODUCTION This report summarizes Westinghouse's evaluation of potential turbine missiles ,

above the turbine deck from the high pressure (HP) rotor and the low pressure (LP) rotor discs of the HP 296 and LP 281 turbine elements for Unit 1, North Anna Station, Virginia Electric & Power Company, Serial Numbers 13A3591-1, 23A3592-1, and 23A3593-1. The contents of this report supersede any previously issued information for this unit on turbine missile energies.

2 DESCRIPTION OF TURBINE ELEMEN'IS  !

l 2.1 High Pressure Turbine The HP element is a double flow design similar to the HP double flow design -

shown in Figure 1, and consists of a forged single-piece double flow rotor, a cast steel outer cylinder, and four cast steel blade rings supported inside the outer l l eylinder. Steam from four control valves enters nozzle chambers at the center of l the turbine element through four inlet pipes (two in the cylinder base and two in the cylinder cover). In these chambers, the steam is distributed equally to both halves of the rotor and flows axially through the blading to the exhaust chambers at each end of the HP cylinder. The HP cylinder cover and base are held together at the horizontal joint by studs and stud-bolts have lengths ranging from 28 to 59

CYLINDER x ,- - ,- re - -,

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BLADE RINGS c l

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• FIGURE 1 4& .

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HP DOUBLE-FLOW TURBINE

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inches and diameters ranging from 2.50 to 3.50 inches. The total cross-sectional area of the studs and bolts is approximately 620 square inches and the total free-length volume is approximately 31,500 cubic inches.

2.2 Low Pressure Turbine i

The LP turbines are of a double flow design similar to the double flow design. i shown in Pigure 2. Each element consists of a double flow rotor assembly, an l

outer cylinder, two inner cylinders, and blade rings. The rotor assembly consists of a shaft with 10 shrunk-on discs made of low alloy steel and two shrunk-on couplings. Steam enters at the top of each outer cylinder where it flows to the inlet chamber of the inner cylinders. In the inlet chamber, the steam is distri-buted equally to both halves of the rotor and flows through the blading to the condenser. LP turbines are numbered from the HP element to the generator. The LP-1 element is next to the HP element, the highest numbered LP element is next to the generator.

3 COMMENTS AND ASSUMPTIONS 3.1 High Pressure / Low Pressure Turbines 3.1.1 When a disc or rotor fails in quarters, the failure occurs in steps with the result that two fragments gain velocity and two lose velocity. The velocities and energies given are for the higher velocity fragments.

OUTER CYLINDER INNER CYLINDER

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h FIGURE 2 LP DOUBLE-FLOW TURBINE

3.1.2 In predicting the ability of the fragment to penetrate the, turbine casing, test results and analytical considerations indicate that the translational kinetic energy of a fragment is of much greater importance than the rotational kinetic energy.

Rotational kinetic energy tends to be dissipated as a result of friction forces developed between the surface of the disc or rotor fragment and the stationary part; therefore, rotational kinetic energy was not considered in the penetration calculations.

3.1.3 The analysis considers the energy absorbed by the inner and outer cylinders, blade rings, and cylinder rings where appropriate. The results of R&D tests, including the 1979 non-symmetrical tests, are incorporated into the analysis.

3.1.4 When missile energies exiting the turbine are less than 100,000 ft-lb, they are not reported in the Analysis Results section of this report.

3.1.5 Blade ring and cylinder exiting fragments vary significantly in shape. Fragments of equivalent area are reported rather than furnishing separate tables and sketches for the numerous possible configurations (refer to Figure 3). HP/LP turbine cylinder and blade ring fragment equivalent areas are tabulated in ,

)

l TABLES 1 and 2.

3.1.6 Minimum ultimate strength was used to establish the dynamic strength of the cylinders and blade rings for the missile penetration calculations.

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- FIGURE 3 ,

HP &,LP CYLINDER & BLADE RING FRAGMENTS

- TABLE 1 HP CYLINDER AND BLADE RING FRAGMENT DIMENSIONS (REFER TO FIGURE 3)

L (in) B (in) H (in) j Blade Ring 1 52.1 25.8 4.9

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55.2 24.6 6.8

,B,'Inde Ring 2

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Cylinder 67.6, 27.9 7.4

TABLE 2

. LP CYLINDER AND BLADE RING FRAGMENT DIMENSIONS (REFER TO FIGURE 3)

FRAGMENT L (in) L (in) B (in) H (in) NOTES NUMBER 900 SEGMENT 1200 SEGMENT 1.1

• 87.9 - 18.1 7.7 (c) 1.2 103.7 - 8.5 9.1 (c) 1.3 117.1 - 3.0 19.3 (c) 2.1 95.8 129.5 12.0 8.9 2.2 36.7 - 9.5 5.5 (a,b) 2.2 - 48.9 9.5 5.5 2.2 36.7 - 1.9 6.6 (c)

~3.1 86.7 115.6 9.4 5.5 (a) 3.1 85.3 - 6.1 ~ 5.2 (b,e) 3.1 - 115.6 9.4 5.5 (b) 3.1 - 113.7 6.1 5.2 (c) 3.2 87.6 116.8 4.0 ,

9.8 4.1 81.8 108.9 4.5 4.6 4.2 91.0 121.3 18.5 5.0 5.1 73.2 97.9 2.5 6.6 5.2 74.0 98.7 14.0 4.4

• Except as indicated by the following notes, dimensions apply to 100 and 120%

l speed and destructive overspeed.

i NOTES: (a) 100% speed .

(b) 120% speed (c) Destructive overspeed i

wne 7 CT24821/0 l

3.2 High Pressure Turbine 3.2.1 For this report, it is assumed that the HP rotor fails as shown in Figure 4. Failure such as that illustrated will generate eight fragments that may become missiles; -

note that the two end sections of the rotor are assumed not to become missiles.

HP turbine missile impact areas and dimensions are given in Figure 5 and tabula-

• ted in TABLE 3. .

3.2.2 It is not necessary to calculate missiles at the ductile bursting speed of the HP rotor since this bursting speed is higher than the theoretical terminal speed of the unit. -

3.2.3 The ejection angle of the HP rotor fragments is assumed to be + 5 degrees mea-sured from the vertical radial plane perpendicular to the rotor's longitudinal axis.

3.3 Low Pressure Turbine -

3.3.1 In evaluating the capability of LP turbine structures to contain fragments, it is assumed that a single dise fails and fractures into several parts. Segments of 90, 120 and 180 degrees have been considered but only 90 and 120 degree segment properties are reported. Because of kinematic considerations, a 180 degree disc segment will have a lower initial translational energy and more of the energy is absorbed by the internal structures. As a result, the likelihood of generating O

Radial Cracking Transverse Cracking 1

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End initial cracking of one-piece rotor  %

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• STEP 3 STEP 2 ,

Each quarter section cracks Rotor splits into six pieces:

as shown above four "quarker" sections asuf two end sections

!' End 1

Section 1 1

" Eighth" _ +

l Section '; Isometric half view of fractured actor '

STEP 4 t Quarter sections split; rotor now in ten peaces:

eight " eighth" sections (these beconw missiles) and two end sections .

o FIGURE 4 HP ROTOR FRACTURE SEQUENCE

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JL JL AREA A3 VIEW C-C PROJECTED W3 W2 AREA AS NO AREA A6 VIEW E E DEVELOPED Y .

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C, E C i i VIEW A.A PROJECTED AREA A4 l SECTION 0 0 B 6-M I '

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, - AREA A SECTION 3 BB FIGURE 5 HP MISSILE AREAS AND DIMENSIONS 10

TABLE 3 HP TURBINE ROTOR MISSILES.- DIMENSIONS'AND IMPACT AREAS (REFER TO FIGURE 5)

DIMENSIONS (ft) ,

IMPACT AREAS (ft2)

Lt 5.44 At 16.83 L2 3.34 A2 11.48 l

Wt 3.26 A3 4.08 W2 3.65 A4 10.88 D 0.75 A5 14.00 Rt 2.80 A6 1.66 G

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missiles is less than for the other segments, and exit energies will be lower. LP turbine missile impact areas and dimensions are given in Figure 6 an'd tabulated in TABLES 4 and 5.  ;

The potential for distributed bore cracks and field experience indicate that an LP '

disc burst may result in major segments (hub to rim fractures) varying in size from approximately 30 to 200 degrees. Although missile data for only 90 and 120

• degree segments are present' e d in this report, an assessment was made to determine if smaller, larger, or intermediate size disc segments could exit with higher energies. The results of this assessment indicate that 90 and 120 degree segments are reasonable approximations for the highest exiting energy disc segment.

3.3.2 The bursting speed of each shrunk-on disc is calculated. The criterion used is that the dise will fail when the average tangential stress equals the maximum temperature corrected tensile strength of the disc material. The maximum value was taken as the minimum specification value plus 20 KSL Upon failure of the initial disc, further acceleration is assumed to halt because of damage to the turbins. For purposes of calculating and reportJng the energies of missiles, all other discs are assumed to fail at the same speed as the initial disc.

3.3.3 The calculated value of destructive overspeed for this unit is 191% of rated speed. This is the speed at which the initial LP dise fails. The No. 2 disc is the initial disc to fail on this unit.

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LP DISC MISSILES (See tables 4 & 5) 13

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TABLE 4

. DIMENSIONS AND IMPACT AREAS FOR 908 LP DISC PRAGMENTS (REFER TO FIGURE 6)

DISC NO. A1 A2 A3 A4 W L 2 2 2 2' (ft) (ft) (ft) (ft) (ft) (ft) -

1 4.94 2.40 3.33 1.27 6.08 2.64 2 4.28 2.23 3.09 1.26 6.08 2.72

• 3 2.03 1.77 3.09 1.28 6.08 2.80 4 2.45 2.03 3.33 1.46 5.88 2.74 5 3.10 2.60 4.00 1.89 5.32 2.43 TABLE 5i 0

DIMENSIONS AND IMPACT AREAS FOR 120 LP DISC FRAGMENTS (REFER TO FIGURE 6)

DISC NO. At A2 A3 A4 W L -

2 2 (ft2) (ft) 2 (ft) (ft) (ft) (ft)'

1 6.05 3.12 4.61 1.27 7.45 2.64 2 5.24 2.84 4.34 1.26 7.45 2.72 3 2.48 2.11 4.35 1.28 7.44 2.80 4 3.00 2.40 4.74 1.46 7.20 2.74 -

5 3.80 3.03 5.92 1.89 6.51 2.43 l

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3.3.4 The ejection angles of the disc missiles are given by the following guidelines (refer to Figure 7):

o Discs 1, 2, 3, and 4: + 5 degrees measured from the vertical radial plane passing through the disc. -

o Dise 5: 5 degrees to 25 degrees mecsured from the vertical radial plane passing through the disc. Fragments from this dise will eject only towards the cylinder end wall.

ANALYSIS RESULTS This section gives the weights, velocities, and translational kinetic energy for the potential HP and LP missiles described in this report. The data for this section is presented in tabular form; the following is a breakdown of these tables:

o HP Element Initial Rotor Fragment Properties are hven in TABLE 6, o HP Element Exit Missile Properties are given in TABLE 7, o LP Element Initial Disc Segment Properties are given in TABLE 8, .

o LP Element Exit Missile Properties are given in TABLES 9 through 13, and o LP Disc Indentification Information is given in TABLE 14.

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2C043 15 CT24821/0

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$1 Vertical radial planes 1 r

a / Cylinder passmg through all end wall 1

inner discs y .

50 1 250

$2 Vertical radial silanes l Rassing through all i 8 # l outer discs (i.e. those l I 50 f/ '

discs closest to the rotor i /

f ends; there are two outer I

~ ( 1 discs / rotor / element). l

.  :. l NOTE: Vertex of ejection angles locatedr' t the point of first contact between disc fh and stationary blade ring.

(A common practice is to locate these vertaxes at the ll l-s l

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p point of insection between /

LP rotor the radial plane and the rotor's centerline.)

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l FIGURE 7 l EJECTION ANGLES FOR LP MISSILES 16 I

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. TABLE 6 a-INITIAL ROTOR FR AGMENT PROPERTIES - 111011 PRESSURE TURBlNE (900ROTOR FRAGMENT) 120% SPEED 100% SPEED ENERGY VELOCITY ENERGY , l WElGitT VELOCITY (10 8 ft-lb)

FRAGMENT (Ib) (ft/see) (106 ft-lb) (ft/see) 371 25.27 307 17.30 Initial 900Seetion 11830 TABLE 7 U

EXIT MISSILE PROPERTIES - 111011 PRESSURE TURBINE 0 ,

(90 ROTOR FRAGMENT) 120% SPEED 100% SPEED ENERGY VELOCITY EhZ"CY WElGitT VELOCITY (106 F1-lb) (ft/see) (108 ft-lb)

FilAGMENT (ib) (ft/sce) _ ,

- 95 1.67 Initial 900Section 11830 Contained

- 95 0.26 BLADE IllNG HO. I 1870 Contained

- 95 0.37 HLADE RING NO. 2 2625 Contained

- 95 0.56 CYLINDER 3960 Contained

• CT24821/0 20043

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TABLE 8 INITIAL DISC SEGMENT PROPERTIES FOR I.P DISCS NOS.*1 TIIROUGH 5 (LP 1,2) 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED I

VELOCITY ENERGY VELOCITY ENEROY WEIGilT VELOCITY ENERGY 106 ft-lb) (ft/sec) (10 6 ft-lb) (ft/sec) (106 fi-lb)

(Ib ) (ft/see) 908DISC SEGMENT 13.04 674 19.03 1101 50.89, DISC No.1 2700 558 ,

702 22.72 1149 60.80 2965 581 15.52 DISC No. 2 657 18.59 1076 49.84 2775 543 12.70 DISC No. 3 14.76 658 21.61 1077 57.85 DISC No. 4 3210 544 on ~

24.57 - -

3980 522 16.83 631 DISC No. 5

- - - 931 49.92 DISC No. 5* 3710 -

f 0 i 120 DISC SEGMENT 13.46 589 19.38 937 49.11 DISC No.1 3600 491 613 23.08 976 58.48 i DISC No. 2 3955 511 16.04 13.08 573 18.84 912 47.74 DISC No. 3 3695 477 i 575 21.95 914 55.60 DISC No. 4 4285 479 15.24 5305 462 17.58 554 25.32 -

DISC No. 5

- - - 799 48.98 DISC No. 5* 4945 -

• Weight change due to loss of blades prior to reaching destructive overspeed.

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CT24821/0

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TABLE 9 EXIT MISSILE PROPERTIES FOR NO.1 LP DISC AND FRAGMENTS (LP 1,2) 100% SPEED 120% SPEED DESTRUC11VE OVERSPEED i WEIGitT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY (Ib) (ft/see) (106 ft-lb) (ft/see) (10 6 ft-Ib) (ft/see) (108 ft-Ib) 900DISC BURST 2700 Contained Contained 113 0.54 DISC No.1 FRAGMENT No.1.1 3470 Contained Contained 113 0.69 FRAGMENT No. 1.2 2270 Contained .

Contained 113 0.45 FRAGMENT No. 1.3 1920 Contained Contained 113 0.38 5

1200 DISC BURST ,

DISC No.1 Contained Contained Contained FR AGMENT Ho.1.1 Contained Contained Contained FR AGMENT No.1.2 Contained Contained Contained FRAGMENT No. 's.3 Contained Contained Contained 2C043 .

CT24821/0

6.

4 TEST TARGET (MT-3) i 1.0 i#EMEM

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TEST TARGET (MT-3) 4 l.0 MIL 4 EM E!E E l-l E ea

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,8 1.25 IA I.6 i < 6" 5% + /4

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TABLE 10 EXIT MISSILE PROPERTIES FOR NO. 2 LP DISC AND FRAGMENTS (LP 1,2) .

100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED WEIGilT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY (Ib) (ft/sec) (108 ft-lb) (ft/sec) (106 ft-lb) (ft/sec) (108 ft-lb) 8 908DISC HURST ,

DISC No. 2 2965 184 1.56 239 2.64 441 '8.94 .

184 1.52 239 2.57 441 8.73 FR AGMENT No. 2.1 2895 FRAGMENT NO. 2.2 545 123 0.13 157 0.21 - -

FR AGMENT NO. 2.2 130 - - - -

484 0.47 E

1208 DISC DURST 3955 148 1.34 197 2.39 352 7.61 DISC No. 2 148 1.33 1 97 2.36 352 7.53 FR AGMENT No. 2.1 3915 ,

108 0.13 138 0.22 239 0.64 FRAGMENT No. 2.2 725 O

' ~ - - CT24821/0

TABLE 11 EXIT MISSILE PROPERTIES FOR NO. 3 LP DISC AND FRAGMENTS (LP 1,2) 100% SPEED 120% SPEED DESTRUC11VE OVERSPEED WEIGHT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY 6

(Ib) (ft/sec) (10 ft-lb) (ft/sec) (106 ft-lb) (ft/see) (104 ft-lb) 900DISC BURST .

DISC No. 3 2775 166 1.19 292 3.67 600 15.54

. FR AGMENT No. 3.1 1270 219 0.95 - - - -

FRAGMENT No. 3.1 765 - -

377 1.69 710 6.00 FRAGMENT No. 3.2 970 177 0.47 310 1.46 439 6.,17 M

1208 DISC BURST DISC No. 3 3695 82 0.39 148 1.26 , 471 12.75 FR AGMENT No. 3.1 1890 188 0.93 244 1.57 - -

FRAGMENT No. 3.1 1020 - - - -

594 5.60 FR AGMENT No. 3.2 1295 89 0.18 159 0.51 507 5.17 20043 .'

CT24821/0

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l TABLE 12 EXIT MISSILE PROPERTIES FOR NO. 4 LP DISC AND FRilGMENTS (LP 1,2) 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED '

WEIGHT VELOCITY ENERGY ~ VELOCITY ' ENERGY YELOCITY ENERGY (Ib) (ft/see) (106 ft-lb) -(ft/sec) (106 ft-lb) (ft/see (108 ft-lb) 9 908 DISC BURST DISC No. 4 3210 369 6.78 460 10.54 781 30.44 FRAGMENT No. 4.1 480 369 1.01 460 1.58 '781 4.55 FR AGMENT No. 4.2 2380 186 1.28 232 2.00 395 5.76 1200 DISO BURST U DISC No. 4 4285 315 6.62 391 10.20 650 28.14 FR AGMENT No. 4.1 640 315 0.99 391 1.52 650 4.21 FR AGMENT No. 4.2 3175 196 1.89 243 2.91 404 8.03 1

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2CO43 CT24821/0

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TABLE 13 EXIT MISSILE PROPERTIES FOR NO. 5 LP DISC AND FRAGMENTS (LP 1,2) 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED WEIGilT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERCf (Ib) (ft/sec) (100 ft-lb) (ft/sec) (10 0 ft-lb) (ft/sec) (100 ft-lb) 90" DISC BURST i 3980 408 10.29 498 15.35 - -

DISC No. 5 3710 - - -

756 32.90 DISC No. 5*

408 0.88 498 1,32 756 3.04 FR AGMENT No. 5.1 340 193 0.74 235 1.11 358 2.56 FR AGMENT No. 5.2 1290 0

1200DISC BURST 5305 352 10.22 428 15.12 - -

DISC No. 5 4945 - - - - 635 30.95 DISC No. 5*

455 352 0.88 428 1.30 635 2.86 FRAGMENT No. 5.1 198 1.04 240 1.54 357 3.41 FR AGMENT No. 5.2 1720

• Weight change due to loss of blades prior to reaching destructive overspeed.

a CT24821/0 2C043

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' TABLE 14 LN TURBINE DISC IDENTIFICATION INFORMATION LP-1 (23 A3592-1) DISC TEST NUMBERS ,

DISC NO. GOVERNOR END GENERATOR END 1 1 TN 1302 TN 1301 i 2 TN 1362 TN 1361 3 ,

TN 1364 TN 1363 4 TN 1240 TN 1241 5 TN 1303 TN 1304 ,

LP-2 (23 A3593-1) DISC TEST NUMBERS r DISC NO. GOVERNOR END GENERATOR END 1 TN 1316 TN 1659 2 TN 1366 TN 1629 .

3 TN 1368 TN 1367 4 TN 1231 TN 1233 5 TN 1307 TN 1308 l .

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l 2C043 24 CT24821/0 l

_ _ _ _ . _ _ . _ _ _ _ . _ _ _ _ _ _ _