(NASA-T_-lI0854) POSTTEST REPGRT

FOR THE ADVANCED SOLID ROCKET NOTCR

(ASRM) IGNITER OISCHARGE PORT FLOg

TEST (NASA. Marshal| Space Flight

Center) 39 F

N96-12963

Unclas

G3/20 0065143

NationalAeronauticsandSpaceAdministration

GeorgeC. MarshallSpaceFlightCenterMarshallSpaceFlightCent- _l&bama35812AC(205L544-'21:_l

.,._,NASA-TM-]. X0856 ',

_,_y to_,.or:E D 3 4- 3 5 - 9 3

I&IASA/'I' " " '"- 2 r>(

September 7, 1993

TO:

FROM:

SUBJECT:

REF:

Distribution

ED34/Anthony M. Springer

Posttest Report for the Advanced Solid Rocket Motor (ASRM) Igniter

Discharge Port Flow Test: SAF0006

Springer, Anthony M., "Pretest Report for the Advanced Solid Rocket Motor

(ASRM) Igniter Discharge Port Flow Test," ED34-22-93, July 28,1993

INTRODUCTION:

This memo documents the Advanced Solid Rocket Motor (ASRM) Igniter discharge port flow test,

SAF0006. run at the Solid Rocket Motor Air Flow Test Equipment (SRMAFTE) facility during

the week of August 9, 1993. The primary purpose of this test was to determine dischargecoefficients for both the center axial and radial 2:1 aspect ratio exhaust ports of the ASRM

multi-port igniter. In addition, both ports were tested with chamfered leading edge to assess

how much improvement in discharge coefficient could potentially be achieved.

FACILITY:

The SRMAFTE configuration is shown in figure 1. The air supply for the SRMAFTE is apressure

blowdown system discharging to atmosphere through the solid rocket model test section. The air

storage is comprised of eight storage tanks having acombined capacity of 9100ft 3. The storage

tanks are charged up to a maximum pressure of 1900 psig from a 3500 psig dry air supply

system. The inlet air is filtered through a bonded fiberglass filter with cylindrical canisters

that have a 0.3 micron filter rating. The Remote ©peration Valve (ROV) isolation valve is

downstream of the filter and is rated for a maximum pressure of 1960 psig. This valve can be

shut down at maximum speed in case of emergency. The actual test model inlet pressure iscontrolled by a quiet trim valve. The valve uses a hydraulic operator for actuation and will hold

the test model stagnation pressure constant at a set-point as the supply tank pressure decays.

Downstream of the quiet valve, a pilot operated safety relief valve is located to discharge 100%

of the flow operating at 1320 psia. The normal air weight flow range for system design is 20 to320 Ibm/sec which can be precisely metered by a sub-critical venturi which is located at a

minimum of 10 equivalent L/D's downstream of the control valve. In mode A of operation

metering nozzles are inserted upstream of the adapter chamber reducing the pressure seen bythe model.

The test configuration for this model makes use of the SRMAFTE facility checkout model, Model538. Model 538 consists of three model chamber spool pieces with a converging/divergingnozzle. The nozzle throat and exit diameters are scaled to 10% RSRM/ASRM size at motor

ignition. Normally, mass flow through the system is determined by sonic flow through the SRM

model nozzle. For this test neither the metering nozzles nor the SRMAFTE checkout model nozzlewere choked. A diffuser downstream of the checkout model enables the full scale booster nozzle

booster nozzle expansion ratio to be modeled without inducing flow separation. Air passesfrom the diffuser in to an exhaust duct whiciq leads to an 85db silencer which is locatedoutside of building 4777. Figure 2 describes the nomenclature used for specific modelcomponents while figure 3 describes the models axial stations and radial locations.

MODEL:

The model consisted of four test "plates" each with one of the test orifices in the center ofthe plate. The test orifices were the existing full scale ASRM igniter discharge ports with andwithout leading edge chamfer. The circular orifice is to be present at the center of the actualigniter while the elliptical orifices are spaced around the aft dome of the igniter. A circularorifice with a diameter of 2.55 in and an area of 5.11 in2, a chamfered circular orifice of the

same diameter and area, an ellipse with an area of 3.464 in2, a length of 2.786 in and a widthof 1.393 in, and a chamfered ellipse of the same dimensions as the previous ellipse. The termellipse is used to describe the 2:1 aspect ratio port. The test plates are shown in figure 4which correspond to the drawings in figures 5 through 7. Each of these small test plates wasmounted in the center of the larger test plate holder fixture, figure 8. The plates were .065inches thick which approximates the average thickness of the igniter chamber aft dome. Thisfixture was built to fit between spool piece 2 and 1 of the checkout model. A photograph ofthe model mounted in the facility is shown in figure 9. The fixture had the necessary gaskets,flanges, and bolt holes to accommodate it in the facility. The SAF0006 test models were builtaccording to the following NASA MSFC drawing numbers: 80M54212, test plate assembly;80M54213, test plate mount details; and 80M54214, test plate details. The modelcomponents are shown in figure 10. This photograph does not include the fixture sealinggasket, the plate holding screws, or the longer studs required to mount the fixture to thecheckout model.

TEST :

The test consisted of running each of the test plates for a range of predetermined operationpressures. The test conditions were based on bounding the current full scale Reynolds numberthe igniter orifices should see. The Reynolds number was based on the effective hydraulicdiameter for each orifice, 2.55 inches for the circles and 1.94 inches for the ellipses. Theoperating pressures were calculated from these full scale Reynolds numbers. Operatingpressures ranged from 250 psia to 25 psia in 25 psia increments. The flow was chokedthrough the orifices for all conditions except at the low pressure of 25 psia. The run scheduleis presented in table I. Initially, six frames of data were taken for each run, including allunchamfered circular orifice runs, runs 1 to 10. This was subsequently increased to 12frames of data for all further test orifices, runs 11 through 40.

INSTRUMENTATION:

The instrumentation and data acquisition for this test consisted of four pressure taps, twotemperature probes, and the facility mass flow calculation. Static pressure taps were locatedboth upstream and downstream of the test plate. Two taps were located in both spool piece1 and spool piece 3. A temperature probe was also located in each of these spool pieces. Themass flow calculation was based on facility instrumentation which consisted of venturiupstream and downstream pressure taps and a venturi temperature probe. These were therequired instrumentation for the test. Other parameters were measured during the test butwere not required for the analysis of the data and will not be mentioned. A list of parametersis located in the database along with their corresponding locations.

DATA:

All data from this test currentlyresideson the NASAMSFCAeroFluidsAnalysisSystem(AFAS)Vax in the databaseunder the SAF0006test heading. The relevantparametersweresubsequentlytransferredto the r,'lacJntoshfor data analysis. The data transferredfrom theVax to the Macintoshare in commaseparatedvariable, csv, format. The final data are in Excel4.0 format. All plots of the data were done in KaleidaGraph V2.0.

Discharge coefficient = measured mass flow/theoretical isentropic mass flow

Reynolds Number = (Density'Velocity'Diameter)/Viscosity

RESULTS:

The relevant data are presented in tables 2 through 5. Each table is for one of the fourconfigurations and is divided up by run number as shown in column 1. These tables contain theraw test data necessary to perform the data analysis and all subsequent data calculationsbased on these data. Pressure ratio, theoretical mass flow (based on 1-D isentropic flowequations), discharge coefficient, and Reynolds number were calculated. For each run, all theframes of data taken during that run are listed down the rows. The columns list theparameter that was measured or calculated. The nomenclature for the data tables ispresented in table 6.

Nomenclature DescriptionTAF-S30APS-S30GPS-S30U

Temperature in spool piece 3 at 0 degrees, upstream of plateStatic pressure in spool piece 3 at 90 degrees, upstream of plateStatic pressure in spool piece 3 at 90 degrees, upstream of plateAvera0e of Pressure Taps PS-S30G and PS-S30GPAVG

PS-Sl0G Static pressure in spool piece 1 at 90 degrees, downstream of plate ..PS-Sl0UPS-1 AVG

P1/P3 Pressure ratio of downstream to upstreamACTUAL M DOT

Static pressure in spool piece 1 at 90 degrees, downstream of plateAverage of Pressure Taps PS-Sl0G and PS-Sl0G

THEO M DOT

Cd Discharae CoefficientREYNOLDS #

Facility mass flowTheoretical mass flow usina isentropic 1-D calculations

Reynold.s number based on experimental information

Table 6' Test Nomenclature

Graphs of discharge coefficient verses Reynolds number are presented in figures 11 and 12.In each of these graphs the orifices with and without chamfer are compared. Figure 13presents discharge coefficient verses upstream to downstream pressure ratio for the fourdischarge ports.

CONCLUSIONS:

It can be seen from figures 11 and 12 that chamfer greatly improves the discharge coefficientof each orifice. It is also seen that the elJipse has a much better discharge coefficient thanthe circle. The effect of Reynolds number on discharge coefficient is seen to be almostnegligible for numbers greater than 4x106. It should be noted that the difference in

discharge coefficient at low Reynolds number, below 4X106, does not totally result fromReynolds number effects. Figure 13 shows the effect of pressure ratio on discharge

coefficientneglectingReynoldsnumbereffects. A pressureratio above .5283 signifies thatthe flow throughthe orifice is not choked.

Thedischargecoefficientmatchingthe full scale Reynoldsnumberfor the circle and ellipsealongwith the full scale Reynoldsnumberare shownin table7.

OrificeCircle

ReynoldsNumber6.22X106

DischargeCoefficient.873

ChamferedCircle 6.22X106 .938

Ellipse 4.72 X 106 .909

Chamfered Ellipse 4.72 X 106 .966

Table 7: Discharge Coefficient at Full Scale Reynolds Number

Based on repeated runs, the discharge coefficient is estimated to be accurate within 1.0%.

Questions concerning this report should be directed to the undersigned at (205) 544-1571.

Anthony M. S_ringer

APPROVED:

C

Chief, Fluid Dynamics Division

Distribution:ED01/J. BlairED31/D. AndrewsED34/C.DillED34/A. SpringerED34/D.BacchusED34/J.HengelED34/P.RamseyED34/FileED35/R.WalesED35/H.WalkerED35/G. McGriffED35/B. PepperED35/H.GwinED36/J.HeamanED36/M. NiedermeyerED36/R.NormanEE73/N.HundleyEP54/B.GoldbergEP54/C. Martin

ERC/H.WhitesidesAerojet/ASRM Div.Aerojet/ASRM Div.Aerojet/ASRM Div.APD/ Sacramento

S. SchlueterL. StockhamC. ClaytonL.McDaniel

722O720072602019A2/7210

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