ML19341A190

Turbine Missile Rept (HP296-LP281-LP281).

ML19341A190
Person / Time
Site:	North Anna
Issue date:	08/31/1980
From:	WESTINGHOUSE ELECTRIC COMPANY, DIV OF CBS CORP.
To:
Shared Package
ML19341A188	List: ML19341A187 ML19341A190
References
CT-24821, CT-24821-R, CT-24821-R0, NUDOCS 8101220333
Download: ML19341A190 (26)

Text

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O STEAM TURBINE INFORMATION TURBINE MISSILE REPORT (HP296-LP281-LP281)

CT-24821 REVISION 0 AUGUST,1980 VIRGINIA ELECTRIC & POWER COMPANY NORTH ANNA STATION, UNIT NO.1 SERIAL NUMBERS 13 A3591-1, 23A3592-1, 23 A3593-1 9 .

WESTINGHOUSE ELECTRIC CORPORATION STEAM TURBINE GENERATOR DIVISION 20043 .

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NO WARRANTIES, EXPRESS OR IMPLIED, 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 will Westinghouse be responsible to the user in contract in tort (including negligence) or otherwise for any s,pecial, indirect, incidental or consequential damage or loss whatsoever 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 facilitire or claims against the user by its customers resulting from the use of the information and descriptions contained herein.

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WESTINGHOUSE ELECTRIC CORPORATION STEAM TURBINE INFORMATION CT-24821 AUGUST,1980 REVISION 0

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TURBINE MISSILE REPORT (HP296-LP281-LP281) 1 INTRODUC' DON

' Itis report suminarizes 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 '.he HP 294 and LP 281 turbine elements for Unit 1, North Anna Station, Vi:ginia Electric & Power Company, Serial Numbers 13 A3591-1, 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 ELEMENTS 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 cylinder. Steam from four control valves enters nozzle chambers at the center of i

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 f 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 23 to 59 20043 1 CT24821/0

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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 L approximately 620 square inches and the total free- !

length volume is approximately 31,500 cubic inches.

2.2 Low Pressure Turbine The LP turbines are of a double flow design similar to the double flow design shown in Figure 2. Each element consists of a double flow rotor assembly, an 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 oster cylinder where it flows to the inlet chamber of the inner cylinders. In the L.kt 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 qt:arters, the failure occurs in steps with the result that two fragments gain velocity and two lose velocity. The v*locities and energies given co for the higher velocity fragments.

2C043 3 CT24821/0

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3.1.2 In predicting the ability of the fragment to penetrate the turbine casing, test 1 i

results and analytical considerations indicate that the~translational kinetic energy l

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 equivedent areas are tabulated in TABLES I and 2.

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

2C043 . 5 CT24821/0

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• 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)

Blade Ring 1 52.1 25.8 4.9

,B' lade Ring 2 55.2 24.6 6.8 Cylinder 67.6, 27.9 7.4 l

2C043 6

_ CT24821/0

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 0 120 SEGMENT 4

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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 -

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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%

speed and destructive overspeed.

NOTES: (a) 100% speed

• l (b) 120% speed (c) Destructive overspeed 2C043 7 CT24821/0

3.2 High Pressure Turbine 3.2.1 For this report, it is assumed that the HP rotor falls as shown in Figrare 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- I

. 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 burrting 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 disc falls and fractures into several parts. Segments of 90, 120 and 180 degrees have been considered but only 90 and 120 degree segment

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properties are reported. Because of kinematic considerations, a 180 degree disc 1

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 2C043 8 CT24821/0 O

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HP MISSILE AREAS AND DIMENSIONS 10

TABLE 3 HP TURBINE ROTOR MISSILES - DIMENSIONS AND IMPACT AREAS (REFER TO FIGURE 5) l DIMENSIONS (ft) IMPACT AREAS (ft2)

L1 5.44 A1 16.83 L2 3.34 A2 11.48 W1 3.96 A3 4.08 W2 3.65 A4 10.88 D 0.75 -

A3 14.00 R1 2.80 A6 1.66 4

2C043 11 CT24821/0

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l 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 and tabulated in TABLES 4 and 5.

1he potential for distributed bore cracks and field experience indicate that an LP l

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

• degree segments are presented in this report, an assessment was made to l 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 disc 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 KSI. Upon failure of the initial disc, further acceleration is assumed to halt because of damage to the turbine. For purposes of calculating and reporting 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 fall on this unit.

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DIMENSIONS AMD IMPACT AREAS FOR 90 LP DISC FRAGMENTS (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 5 DIMENSIONS AND IMPACT AREAS FOR 1200 LP DISC FRAGMENTS (REFER TO FIGURE 6)

DISC NO. A1 A2 A4 W L

^3 2 2 2 2 (ft) (ft) (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 2C043 . 14 CT24821/0

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 Disc 5: 5 degrees to 25 degrees measured 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 given in TABLE 6, o HP Element Exit Missile Properties are given in TABLE 7, o LP Element Initial Dise Segment Properties are given in TABLE 8, o LP Element Exit Missile Properties are given in TABLES 9 through 13, and o LP Dise Indentification Information is given in TABLE 14.

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7 1 50 250 42 Vertical radial planes passing through all i I outer discs (i.e. those l I 50 /

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discs / rotor / element).

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i NOfE: Vertex of ejection angles located at the point of first contact between disc $

and stationary blade ring. k (A common practice is to p 9[/

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TABLE 6 . .-

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INITIAL ROTOR FRAGMENT PROPERTIES - HIGH PRESSURE TURBINE .

0 (90 ROTOR FRAGMENT) 100% SPEED 120% SPEED WEIGHT VELOCITY ENERGY VELOCITY ENERGY PRAGMENT l'

(Ib) (ft/sec) (106 ft-lb) (ft/sec)

. (108 ft-lb)

Initial 900Section 11830 307 17.30 371 25.27  !'

TABLE 7 EXIT MISSILE PROPERTIES - HIGII PRESSURE TURBINE 0

(90 ROTOR PRAGMENT) l 100% SPEED 120% SPEED i WEIGHT VELOCITY ENERGY VELOCITY ENERGY g FRAGMENT 6 (Ib) (ft/sec) (10 Ft-lb) (ft/sec) (106 ft-lb)

Initial 900Section 11830 Contained -

95 1.67 BLADE RING NO. I 1870 Contained -

95 0.26 BLADE RING NO. 2 2625 Contained -

95 0.37 CYLINDER 3960 Contained -

95 0.56 8

2CO43 CT24821/0 .

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, TABLE 8 INITIAL DISC SEGMENT PROPERTIES FOR LP DISCS NOS.* 1 THROUGH 5 (LP 1,2) 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED WEIGHT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY

_ (Ib ) (ft/sec) 106 ft-Ib) (ft/sec) (106 ft-lb) (ft/sec) (106 ft-Ib) 900 DISC SEGMENT DISC No.1 2700 558 13.04 674 19.03 1101 50.89 DISC No. 2 2965 581 15.52 702 22.72 1149 60.80 DISC No. 3 2775 543 12.70 657 18.59 1976 49.84

, DISC No. 4 3210 544 14.76 658 21.61 1077 57.85 DISC No. 5 3980 522 16.83 631 24.57 - -

DISC No. 5* 3710 - - - -

931 49.92 1200 DISC SEGMENT DISC No.1 3600 491 13.46 589 19.38 937 49.11 DISC No. 2 3955 511 16.04 613 23.08 976 58.48 DISC No. 3 3695 477 13.08 573 18.84 912 47.74 DISC No. 4 4285 479 15.24 575 21.95 914 55.80 DISC No. 5 5305 462 17.58 554 25.32 - -

DISC ho. 5* 4945 - - - -

799 48.98

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

2CO43 - " " ~

TABLE 9 EXIT MISSILE PROPERTIES FOR NO.1 LP DISC AND FRAGMEN'IB (LP 1,3) 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED WEIGHT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY (1b) (ft/sec) (106 ft-1b) (ft/sec) (106 ft-lb) (ft/see) (106 ft-Ib) 900 DISC BURST DISC No.1 2700 ConteIned i Contained 113 0.54 FRAGMENT No. 1.1 3470 Contalned Contained 113 0.69 FRAGMENT No. 1.2 2270 Contained Contained 113 0.45 FRAGMENT No. 1.3 1920 Contained Contained 113 0.38 U

1200 DISC BURST DISC No.1 Contained Contained Contained FRAGMENT No.1.1 Contained Contained Contained FRAGMENT No.1.2 Contained Contained Contained FRAGMENT No.1.3 Contained Contained Contained 20043 CT2 m 1in

TABLE 10 EXIT MISSILE PROPERTIES FOR NO. 2 LP DISC AND FRAGMEN'IB (LP 1,2) i 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED i WEIGHT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY (Ib) (ft/sec) (106 ft-lb) (ft/see) (106 ft-lb)

(ft/sec) (106 ft-Ib) 900 DISC BURST E

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

FRAGMENT No. 2.1 2895 184 1.52 239 2.57 441 8.73 l

FRAGMENT NO. 2.2 545 123 0.13 157 0.21 - - i-t FRAGMBNT NO. 2.2 130 - - - -

484 0.47 2

1200 DISC BURST -

DISC No. 2 3955 148 1.34 197 2.39 352 7.61 1

FRAGMENT Fo. 2.1 3915 148 1.33 1 97 2.36 352 7.53 .

FRAGMENT No. 2.2 725 108 0.13 138 0.22 239 0.64 2C043 "'

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TABLE 11

, EXIT MISSILE PROPERTIES FOR NO. 3 LP DISC AND FRAGMEN13 (LP 1,2) l' 100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED

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WEIGHT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENEROY j

(Ib) (ft/see) (106 ft-ib) (ft/see) (106 ft-lb) (ft/see) (106 ft-lb) 900 DISC BUR 3T i

DISC No. 3 2775 166 1.19 292 3.67 60f:' 15.54 FRAGMENT No. 3.1 1270 219 0.95 - - - -

• FRAGM' ENT No. 3.1 765 - -

377 1.09 710 6.00 FRAGMENT No. 3.2 970 177 0.47 310 1.46 639 6.17 5

1200 DISC BURST DISC No. 3 3695 82 0.39 148 1.26 471 12.75 FRAGMENT No. 3.1 1690 188 0.93 244 1.57 - -

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FRAGMENT No. 3.1 1920 - - - -

594 5.60 FRAGMENT No. 3.2 1295 89 0.16 159 0.51 507 5.17 l

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TABLE 12 I EXIT MISSILE PROPERTIES FOR NO. 4 LP DISC AND FRAGMENTS (LP 1,2) 100% SPEED 120% SPEED

• DESTRUCTIVE OVERSPEED i WEIGHT VELOCITY ENERGY VELOCITY ~ ENERGY VELOCITY ENERGY (Ib) (ft/see) (106 ft-Ib) (ft/see) (106 ft-lb) (ft/see (106 ft-Ib) '

900 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 FRAGMENT No. 4.2 2380 186 1.28 232 2.00 395 5.76 1200 DISC BURST M DISC No. 4 4285 31S 6.62 391 10.20 650 28.14 FRAGMENT No. 4.1 640 315 0.99 391 1.52 650 4.21 FRAGMENT No. 4.2 3175 196 1.89 243 2.91 404 9.03 2CO43 ~

CT24821/0

TABLE 13 '

, EXIT MISSILE PROPERTIES FOR NO. 5 LP DISC AND FRAGMENTS (LP 1,2) ' ,

100% SPEED 120% SPEED DESTRUCTIVE OVERSPEED WEIGHT VELOCITY ENERGY VELOCITY ENERGY VELOCITY ENERGY (Ib) (ft/sec) (106 ft-lb) (ft/sec) (106 ft-lb)

(ft/see) (106 ft-lb) 900 DISC BURST l

DISC No. 5 3980 408 10.29 498 15.35 - -

DISC No. 5* 3710 I

756 32.90 FRAGMENT No. 5.1 340 408 0.88 498 1.32 756 3.04 FRAGMENT No. 5.2 1290 193 0.74 235 1.11 358 2.56 0

1200DISC BURST

• DISC No. 5 5305 352 10.22 428 15.12 - -

DISC No. 5* 4945 - - - -

635 30.95 FRAGMENT No. 5.1 455 352 0.88 428 1.30 635 2.86 FRAGMENT No. 5.2 1720 1 98 1.04 240 1.54 357 3.41

• Weight change due to loss of bit. des prior to readhing destructive overspeed.

2CO43 CT24821/0

e TABLE 14 LP TUhBINE DISC 1DENTIFICATION INFORMATION LP-1 (23 A3592-1) DISC TEST NUMBERS DISC NO. GOVERNOR END GENER ATOR END 1 TN 1302 TN 1301 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 -

DISC' NO. _ GOVERNOR END GENERATOR END 1 TN 1306 TN 1659 2 TN 1366 TN 1629 3 TN 1368 TN 1367 4 TN 1231 TN 1233 5 TN 1307 TN 1308 2C043 24 CT24821/0

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