ML20148E968

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Disk Velocity at Impact W/Seat for Line Break at Upstream Side of Size 14 Figure 607 Non-Return Valve
ML20148E968
Person / Time
Site: Yankee Rowe
Issue date: 08/13/1975
From: Milleville B, Pool E
ROCKWELL INTERNATIONAL CORP.
To:
Shared Package
ML20148E929 List:
References
2573-48, NUDOCS 8010310722
Download: ML20148E968 (6)
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Text

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Flow Con' trol Division -

Utility Products Group 400 North Lexington Avenue ,

Pinsburgh, Pennsylvania 15208 ROCkWe,ll Telex: 866241 Cablo: ROCKWL INT PGH Internat10nal TECHNICAL STUDY TITLE:

Disk Velocity at impact with Seat for Line Break at Upstream --t Side of Size 14 Fig. 607 Non-Return Volve ABSTRACT Steam pressure, disk position and velocity are computed for o postulatedl condition odiacent to the volve inlet. All significant influences on disk movement cre considered, including dynamic pressure distribution, pressure variations abo and below the disk, and disk-body friction. Contact with the seat occurs offer 0.009 seconds, at a velocity of 65.3 ft/sec. (19.9 m/sec).

APPROVED k 3 M AUTHOR: ""

E. B. Pool i TITLE: Supervising Research Engineer DATE: August 13, 1975 ,

.Y KEY WORDS Volves, Angle; Volves, Nuclear  !

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DISTRIBUTION _

DS W. Duffey/B J. Milleville  ;

i J. H. Loreton .

R. A. Seetholer R. W. Tortoglio e File 2573-48 i

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'(; F mrtmsnt 744-76XXX-645

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keport No. 2573-48 Pogs 2 OBJECTIVE .

This computation was pcrformed to provide velocity dato607 necessary for a companion Valve Body Seat report on the Energy Absorbing Copacity of the size 14 Fig.

and Disk. Studies of nuclear plant safety in the event of a postulated pipe break odiacent to the volve require determination of volve functional behavior and its consequences for conditions not previously analyzed.

RESULTS Velocity of disk at instant of contact with seat is 65.3 ft/sec. ( 19.9 m/sec).

Contact occurs .009 seconds offer line break.

ANALYSIS The volve configuration is shown in the accompanying illustration. The onelysis paral that of J. M. Gwinn of Stone and Webster (ASME Peper 74PVP51) as regards the inlet (overseat) pressure ofter the line becak. The pre,sure necessary to decelerate th flow and accelerate it to reverse critical nozzle flow reduces the original static pressure overseat to about half. The critical mass flow rote is determined by the equivalent nozzle creo of the volve and the upstreom conditions (no other flow restrictors are included). The critical area is at the cross section through the centrol guide rib so tha the undersect pressure is independent of the upstream pressure, but is depencknt on the back pressure created at the line break itself. This back pressure depends on the tross flow rate.

The other pressure which is vital to this analysis is the bonnet pressure (over the pisto The initial pressure is tropped in this cavity and expands on line break powering the initial occelerotion of the disk, since the pressure under the disk suddenly drops to less than half at line break. There is some flow initially out of the bonnet cavity through This is 'nventoried in the computer the Equalizer pipe and post the piston clearance.

program used to give the fluid mass at each timeAfter interval to calculate substantial change ino new bonne pressure based on the increase in bonnet cavity volume .

lift, the bonnet pressure becomes less than upstream and leakage flow reverses to incre the mass of steam in the cavity along with its pressure.- Meanwhile the continued ~

increose in cavity volume os the volve closes tends to reduce the cavity pressure.

As the critical nozzle arco decreases with lift, the flow decreases and the pressur-l above the volve seat moves back toward its initial value. The pressure under the disk  :

drops toward otmospheric as flo- is reduced. f Three experimentally determined coefficients are used in the analyais. The first rela  !

pressurc under the disk to inlet (overscot) pressure. The effective undersect p!

not necessarily the some as the discharge pressure at the. line break because of dynam i The sewnd coefficient relates guide rib effects which are included in the coefficient. l The third is the equivalent nozzle area. All of these bearing load to inlet pressure. l f

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(I' mrtmsnt 744-76XXX-645 R6 port No. 2573-48

, , Page 3 coefficients, os a function of lift, have been measured with load cells in on inclined .

bonnet globe volve under similar critical flow conditions on air.

This supply This Rockwell is exhausted facility contains a 300 cu.ft. tank for air storage to 1500 psi. ,

l ' through the 6" test volve while pressures and loads are recorded on a 4 chan; oscillograph. Since no similar dato is available for angle wives, it has been necessa  ;

to assume the coefficients to be the some for inclined bonnet globe and angle config uration. This is the more plausible because the overall flow coefficients of Rockwe It may be assumed ,

angle and Flite Flow wives are essentially equal in this vo necessary coefficients. These coefficients have been incorporated into the ,

equations .

l The force cousing disk acceleration is then the difference between bonnet and u 1 To this the disk weight is added and guide rib friction seat pressure times the disk area.is subtracted. In calculating the latte This retarding force is found to be a small fmetion because of the elevated temperature.

of the total force. i t

The residual unbolonced force is converted into acceleration which is numerically integrated with time to give disk velocity, which is again numerically integrate disk position. A separate onelysis will predict the consequences of this impa clostic plastic deformation of the sect-disk geometry.

The results are shown'in the attached computer printout. Only every 10th time ste printed.

Note that the wave front has troversed only 15.6 feet ( 4.8 m) before the volve is closed. Since this is less than twice the length of pipe, no pressure reflections wi -

offect the valve before it has impacted the seat.

1.1 lbs. ( 0.5 )kg.

The integrated reverse steam flow escoping before the volve closure is d

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