(NASA-CR- 178828) FEASIBILITY S10DY AND

VERIFIED DESIGH CONCEPT FOE NEH IHPROVED HOT

GflS FACILITY Final Eeport (Lockheed

Hissiles and Space Co.) 111 p BC A06/MF A01

LMSC-HEC TR D065122

N86-24719

Duclas

CSCL 14B G3/14 H2S3Q

FEASIBILITY STUDY

AND VERIFIED DESIGN CONCEPT

FOR NEW IMPROVED HOT GAS FACILITY

- FINAL REPORT

7 February 1986

Contract NAS8-36304

Prepared for

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

MARSHALL SPACE FLIGHT CENTER, AL 35812

by

Missiles & Space Company, Inc

Huntsville Engineering Center

4800 Bradford Drive, Huntsville. AL 35807
LMSC-HEC TR

FOREWORD

This document was prepared by personnel of the Systems Analysis

Section of Lockheed's Huntsville Engineering Center for NASA-Marshall

Space Flight Center under Contract NAS8-363U4. The NASA-MSFC

Contracting Officer's Representative for this study was Mr. R.E.

Tepool, ET62.

ii

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR DO65122

CONTENTS

Section Page

FOREWORD 11

1 BACKGROUND AND INTRODUCTION 1

2 TECHNICAL DISCUSSION 3

2.1 Hardware Design Fabrication, Delivery 3

2.2 Test Plan 3

2.3 On-Site Monitoring 3

2.4 Data Analysis b

2.5 Interface Drawings and Detailed Sketches 7

3 CONCLUSION 6

REFERENCE 9

Appendix

A DD-250 Form Showing Delivery of all Hardware

B Dimensioned Sketches of Redesigned HGF Diffuser

C Rough Stress Notes for Beef-Up of Structure to Increase

Chamber Pressure from 150 to 300 psia (by Mike Tilley, LMSCHuntsville)

D Typical Set of Calibration Run Data (for Run Number 30)

E Listing of Computer Program to Determine HGF Set Pressures,

Chamber Pressures and Temperatures

F Listing of NASA-MSFC Static Measuring Program for HGF CAL Runs

G Calibration Panel Instrumentation Locations

H HGF GH2 and Air Venturi Calibration Data

I HGF Interface Drawing and Detailed Sketches of HGF

Hardware/Components

iii

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D06J>122

1. BACKGROUND AND INTRODUCTION

The MSFC Hot Gas Facility (HGF) was fabricated in 1975 as a temporary

facility to provide immediate turnaround testing to support the SRb and ET

TPS development. This facility proved to be very useful and was used to

make more than 1300 runs, far more than ever intended in the original

design. Therefore, it was in need of constant repair and needed to be

replaced with a new improved design to support the continuing SRtt/ET TPS

product Improvement and/or removal efforts. MSFC contracted with

Lockheed-Huntsvllle to work on this improved design through Contract

NAS8-36304 "Feasibility Study and Verified Design Concept for the New

Improved Hot Gas Facility." Figure 1 shows—a-photograpti-of this new

facili-tyt This •f-i-naA-reptn.'t summailzes;^he results of Lockheed-Huntsville's

effortsjunder this contract which were to;

• Design and fabricate three Cal panels (10 thermocouple locations,

one calorimeter location (GFE), four static pressures, one total

pressure).

• Design and fabricate four dummy panels.

• Design and fabricate one ramped panel fixture.

• Design and fabricate 18 panel spacers (three each £ 1/16, 1/tt, 3/lb,

1/4, 3/8, and 1/2 in. thickness).

• Make facility drawings (see list below).

• Write, present, and revise a Test Plan.

• Monitor Cal runs on-site.

• Reduce and analyze data.

• Write final report.

• Fabricate 60 aluminum, TPS substrate panels.

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TK DU6M22

List of Drawings To Be Furnished

I. Interface Drawings

• Nozzle

• Test Section

• Diffuser

II. Detailed Shop Drawings

Flat Cal Panel

Ramped Cal Panel

Dummy Panel

Ramped Panel Fixture

Window Frame

Panel Support Frame

New IPS Ramped Panel Substrate.

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR DO65122

2. TECHNICAL DISCUSSION

2.1 HARDWARE DESIGN FABRICATION, DELIVERY

The design and fabrication of all deliverable hardware was completed

and delivered to NASA oil schedule. Copies of the signed DD-250 forms are

attached as Appendix A.

2.2 TEST PLAN

A test plan (Ref. 1) was prepared and delivered to MSFC.

2.3 ON-SITE MONITORING

Calibration runs were monitored on-site and the data were analyzed.

Table 1 presents a run log from these runs.

When the calibration runs were first begun, the diffuser did not pump.

Various combustor chamber conditions were tried to get the ditfuser to

"start" such as higher chamber pressure, different oxidizer-to-fuel (0/F;

ratios, etc. However we were never able to get the diffuser to pump.

Therefore, the diffuser design was changed to provide a larger second throat

area. Sketches of this redesigned diffuser are shown in Appendix B. Tnis

redesigned configuration was rectangular rather than round. It was made

from mild steel and was cooled by "spray bars" rather than by a

double-walled cooling jacket as on the original. It was designed by

Lockheed and built by MSFC in-house and was a "stop gap" measure to see if

pumping could be attained. The second throat area was increased from

o 2 approximately 298 in to approximately 414 in . The second throat

section length was also increased and an exit cone was added.

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR DU65122

In connection witli this diffuser redesign it was decided to increase the

combustion chamber pressure from the original design allowable value ot 150

psia to 3UO psia to assist in starting the diffuser. In order to do this,

additional structural strength was required. Lockheed designed the required

"beefed-up" members and these were fabricated and installed by MSFC. Appendix

C presents the detailed stress analysis/design of these structural changes.

After installing this new rectangular diffuser and raising the chamber

pressure limit to SOU psia, additional calibration runs were made. It was

found that the diffuser would now pump. It required a "start" pressure of

approximately 280 psia and a "run" pressure of approximately 220 psia. Test

9 section pressures showed the facility to be operating at a Mach number of

approximately 4.7 as compared to the Mach 5 value originally planned. This

was attributed to the slightly oversized throat. Heating rates in the test

2

section varied from approximately 1 to 6 Btu/ft sec.

After installing the new diffuser, another problem was encountered. i)ue

to delayed ignition on run No. 16 the test section and diffuser were

apparently filled with a combustable GH^/air mixture and when ignition

occurred, a simultaneous explosion ruptured the diffuser and knocked out all

windows and calibration panels from the test section (see Figs. 2, 3, 4, and

5). This ignition delay was apparently due to the increased propellent mass

flow rates at the higher chamber pressures. In order to alleviate these

ignition problems, Lockheed made the following recommendations:

0 Increase all igniter chamber pressures to 375 psia.

• Add water cooling to igniter bodies.

9 Add a GH2 detector to sample air from top of test section during

countdown.

• Refurbish GH2 main valve to prevent leakage.

9 Add high response dynamic pressure measurement to main chamber to

watch for detonation during start transients.

• Add two igniters to top of combustion chamber.

• Increase voltage to Igniter spark plugs from 10,000 to 50,000 volts.

• "Soften" the attachment of the four test panels to the test section

walls so they can serve as "blow out" ports.

• Bleed the igniter GH2 feed lines through the vent stacks rather

than through the main chamber.

• Put redline on Pc to shutdown if not up to 150 psia at 400

milliseconds after start of opening of oxidizer valve.

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR DO b 512 2

Several of these "fixes" were added, and a series of runs was made, without

the diffuser attached to the test section to check out the new Ignition

sequence/procedure. In the meantime a replacement diffuser was fabricated to

the same dimensions as the one which ruptured.

After the new ignition sequence was developed and checked out, tnen tne

replacement diffuser was attached to the test section. Additional runs were

made and it was found that the diffuser would "start" and pump at a combustion

chamber pressure of approximately 280 psia, and would continue to "run" down

to a chamber pressure to approximately 220 psia. A "two-stage" start sequence

procedure was developed to start the diffuser at 280 psia and then immediately

ramp down to 220 psia for tne duration of the run. This was necessary in

order to reduce mass flow rates and, hence, increase the total run time.

After working out these procedures, additional calibration runs were

conducted until a water leak occurred in the throat area (see Figs, b, 7, and

8). The leak was caused by additional thermal stress in the rectangular

tubing joints adjacent to the welds. This was a result of running the

facility at the chamber pressure of up to 300 psia whereas the throat section

was orginally designed to operate at conditions produced by a chamber pressure

of 150 psia. This caused the throat heating rates to increase by a factor of

approximately 1.75 times the original values. Also, because of this increase

in gas-side pressures, the internal cooling water pressure had to be increased

accordingly to prevent inward "dimpling" of the tube walls. The result was an

over stressing of the tube walls, their fatigue life was drastically reduced

and hence they failed after approximately 60 cycles as opposed to 1000 cycles

which was the original design requirement.

Lockheed has offered to repair the welds and find a subcontractor who

would be able to apply a thermal coating to the inside of the throat such as

"Rock-Hide," MgO, or A1203. However, at the time of this writing, MSFC

is considering replacing this throat section with a water-cooled copper

section which would be designed to the higher pressure and heating rates.

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

2.4 DATA ANALYSIS

Table 1 shows the run log of the calibration runs made to date. A

typical set of calibration run data is shown in Appendix D. The ramped,

two-stage "start" procedure is seen in the first plot (page D-l), showing

the chamber pressure versus time, measurements P0713 and PU714.

Analyses of the calibration runs showed that after the dlffuser started

pumping that the test section Mach number was approximately 4.7 as compared

to the design Mach number of 5.0. This was attributed to the sligntly

oversized throat and to a thicker than anticpated boundary layer in the test

section. The actual throat height was approximately 0.045 in. oversized in

the center on both top and bottom halves of the nozzle as compared to a

design value of 1.0 in. This difference was due to manufacturing tolerances

which is not bad for a welded, unmachined structure. The throat height at

the sides (i.e., next to the flanges) was right on 1.0 in.

The heating rates in the test section varied from approximately 1 to b

o

Bt/ft -sec depending of the chamber conditions and on the location in the

test section. The test section static pressures varied from 0.5 to 2.0

psia, depending on chamber conditions and position in the test section.

During the process of these calibration runs, chamber conditions were

selected to yield three distinct enthalpy levels as shown in Table 2.

Table 2 HYDROGEN AND AIR SET PRESSURES REQUIRED

FOR THREE ENTHALPY LEVELS

Enthalpy Level

Low

Medium

High

Set Pressure (psia)

GH2

900

945

1010

Air

1020

945

8«0

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

One "endurance" run was made (Run No. 53) to see how long the

propellant feed supply would hold the required chamber pressure. This

resulted in a ruu time of 71.14 sec. The original run time requirement of

180 sec was not met because of the increased chamber pressure psia required

to keep the larger diffuser running (220 versus 150 psia).

Appendix E presents a listing of a computer program for the IBM PC

which was used to choose set pressures for the GH,. and air regulators to

yield a required combustion chamber pressure. This program is written in

BASIC language.

Appendix F presents the Static Measurements Program Listing which was

used during our data analysis efforts.

The calibration panel instrumentation locations are shown in Appendix

G. A complete set of all calibration data plots is available from Dick

Baker ET62, NASA-MSFC.

Appendix H presents the HGF air and GH~ Venturi Calibration Data.

2.5 INTERFACE DRAWINGS AND DETAILED SKETCHES

Appendix I contains interface details and sketches of the hardware discussed

in the Background and Introduction section. These are presented in lieu of

the "detailed shop drawings" as originally planned. This substitution was

agreed upon by the NASA Technical Contracting Officer's Representative.

Also shown are additional sketches of instrumentation locations, nozzle

dimensions, etc., which may be useful in the future, although not originally

required by the contract.

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

3. CONCLUSION

In conclusion, all requirements of the subject contract have now been

completed.

8

LOCKHEEIKHUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR

REFERENCE

1. Karu, Z.S., "Test Plan for Initial Check Out/Troubleshooting and

Calibration of the New NASA. Hot Gas Facility," LMSC-HREC TN IWSlbUO,

Lockheed Missiles & Space Company, Huntsville, Ala., 14 January 1985.

LOCKHEED-HUNTSV1LLE ENGINEERING CENTER
LMSC-HEC TR D005122

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LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

ORIGINAL PAGE IS

OF POOR QUALITY

Fig. 1 Overall View of Assembled MSFC

Hot Gas Facility (Lower Foreground)

12

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

ORIGINAL PAGE IS

OF POOR QUALITY

Fig. 2 MSFC Hot Gas Facility Showing Damage Caused

by Overpressure Due to Delayed Ignition

13

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

Fig. 3 MSFC Hot Gas Facility Rectangular Diffuser Top Showing

Damage Caused by Operpressure Due to Delayed Ignition

14

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TK D065122

ORIGINAL

OF

Fig. 4 MSFC Hot Gas Facility Test Section Showing Damage

Caused by Overpressure Due to Delayed Ignition

15

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TK D065122

Fig. 5 MSFC Hot Gas Facility Rectangular Diffuser Bottom Showing

Rupture Due to Overpressure Caused by Delayed Ignition

16

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

ORIGINAL PAGE IS

OF POOR QUALITY

*fc

•< i **-** -j

Fig. 6 Thermal Stress Cracks in Upper Half of MSFC

Hot Gas Facility Nozzle/Combustor

17

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

Fig. 7 Thermal Stress Cracks in Lower Half of MSFC

Hot Gas Facility Nozzle/Combustor

18

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

ORIGINAL PAGE IS

OF POOR QUALITY

Fig. 8 Thermal Stress Cracks in Upper Half of MSFC

Hot Gas Facility Nozzle/Combustor

19

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
LMSC-HEC TR D065122

Appendix A

DD-250 FORMS SHOWING DELIVERY OF ALL HARDWARE

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
MATERIAL INSPECTION

AND

RECEIVING REPORT

»»OC INSTRUMENT IDCNlCOMTtACTl

NAS8-36304

•QROCR1NO « INVOICE

NO

DAT E 1/21/85

' PACE OF

1 1

I ACCEPTANC E POINT

D

1 SHIPMENT NO

RC00002

] DATE SNIPPED

1/21/85

• B/L

TCN

HREC/2875

9 DISCOUNT TERMS

Net 30

PRIME CON TRAC T OB COOE

Lockheed Missiles & Space Co., Inc

P. 0. Box 1103

Huntsville, AL 35807

0 ADMINISTERED BY CODE

DCASMA-Birmingham

2121 8th Avenue, N.

Room 104

Birmingham, AL 35203-2376

II SHIPPED FROM II oin., flton 91 COOfl

Same as Block 9

FOB 17 PAYMENT *ILL BE MADE BY COOf

Financial Management Office

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

13 SHIPPED TO COOE

Transportation Officer, Bldg. 4471

National Aeronautics & Space Administration

Geroge C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

14 MARKED FOR

Richard Baker

ET65

COOE

IT[ M

NO

001

STOCK'PART NO DESCRIPTION

1

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OF POOR

17 MS

QUANTITY

SHIP/REC'O

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PROCUREMENT QUALITY ASSURANCE RECEIVER'S USE

A OO.G.N

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DATE RECEIVED

TYPED NAME

AND OFFICE

OF AUTM GOVT RE P

DATE

TYPEONAM E

AND TITLE

SIGNATURE OF AUTH GOVT REP

• II 0wontifr rac*i«rd by rha Covtrnmani <t fto io«« at

'•rani tflfar oeiwo' gwcni«i|r fcctota1 6a/o» owant-rir

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To be picked up by NASA from Lockheed's Bldg. 401

A-l

nO«-ORM?50 I NOV 68 REPLACES COITION OF 1 AUC 67 WHICH MAY 9E USED
MATERIAL INSPECTION

AND

RECEIVING REPORT

3 SHIPMENT NO

HRC00003

) OATf SHIPPED

1/30/85

1 PROC INSTRUMENT lOCMICONTftACT)

NAS8-36304

«• B/L

TCM

HREC/2884

9 »RIM( CONTRACTOR CODE

Lockheed Missiles & Space Co., Inc.

P.O. Box 1103

Huntsville, AL 35807

(ORDERING

J DISCOUNT

• INVOICE

NO

DATE 1/30/85

' PACE 1 or

1 1

a ACCEPTANCE POINT

0

TERMS

Net 30

((.ADMINISTERED BY CODE

DCASMA-Birmingham

2121 8th Avenue, N.

Room 104

Birmingham, AL 35203-2376

I I SHIPPED FROM III oik., ikon 91 COOf |

Same as Block 9

FOB II PAYMENT WILL BE MADE BY COOf I

Financial Management Office

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

13 SMIPPEO TO CODE

Transportation Officer, Bldg. 4471

National Aeronautics & Space Administration

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

U MARKED FOR

Richard Baker

ET65

CODE

ITEM

NO

001

STOCK'PARTNO DESCRIPTION

flndicof* number of shipping conlomlrl typ» of

conlomtr eonfoimn nurnWr I

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OF POOR QUALITY

QUANTITY

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UNIT

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DATE RCCEIVED

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rtfil onror octwa/ ovanlifr racoivad bafo*

1) CONTR.lTOR USC ONLY

To be picked up by NASA from Lockheed's Bldg. 401.

A-2

OOrr>RM?SO I NOV •• NEPLACCS EDITION OF 1 AUG 67 WHICH MAY BE USED
MATERIAL INSPECTION

AND

RECEIVING REPORT

I MOC iNJTHUlrtwT lOCNlCONTBACTi

NAS8-36304

(OBOER'NO 6 INVOICE

NO

DATE 3/7/85

! PAGE

1

I ACCEPTANCE POINT

D

I SHIPMENT NO

HRC00004

i OAK SHIPPED

3/8/85

B/L

ICN

HREC/2930

S DISCOUNT TEAMS

Net 30

' PRIME CONTRACTOR CODE

Lockheed Missiles & Space Co., Inc.

P.O. Box 1103

Huntsville, AL 35807

0 ADMINISTERED BT COOE

DCASMA-Birmingham

2121 8th Avenue, N.

Room 104

Birmingham, AL 35203-2376

u SHIPPED FROM ill oihxfko.fl CODE)

Same as Block 9

foe 12 PAYMEN T WILL BE MADE BT CODE I

Financial Management Office

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

1) SHIPPED TO COOf I

Transportation Officer, Bldg. 4471

National Aeronautics & Space Administration

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

U MARKED FOR

Richard Baker

ET65

CODE

ITEM

NO

001

16 STOCK'PART NO DESCRIPTION

ftWicor* numb*' al shipping eontointri type of

container container number )

Hot Gas Test Section TPS Panel

Substrates

ORIGSNAL PAGE IS

OF POOR QUALTfY

QUANTITY

SHIP/REC'D1

60

UNIT

Ea

UNIT PRICE

NA

AMOUN T

NA

PROCUREMENT QUALITY ASSURANCE

A ORIGIN

t-CEPTANCEof lilUd .'••"» hoi b..n modi

t>c«o* 01 *o**d h«f«in or on tuoaof'tng document!

O«I E

•tP|0 NAME

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SIGNATURE or AUTH COVT REP

__ __ B DESTINATION ,

I I PQA I I ACCEPTANCE ol t.l'.d .'.-. Ko> b..« "Ode

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RECEIVERS uiE

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DATE

TYPED NAME

AND TlTUE

DATE (ECEIVEO SIGNATURE OF AUTH GOVT REP

TYPED NAME

AND OFFICE

SIGNATURE OF AUTH GOVT REP

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«nxt.ir

ftronf «f.t«r octwo' 4w

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fh« Co«»

.1 J.I

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To be delivered to NASA at Bldg. 4707

A-3

OD'riRM 7so t NOV ee REPLACES EDITION OF 1 AUC 67 WHICH MAY BE USED
MATERIAL INSPECTION

AND

RECEIVING REPORT

1 SHIPMENT NO

RC00005

3 DATE SHIPPED

3/8/85

1 P*OC (MtTMUMCNT r0e*(CONTB*CT1

NAS8-36304

4 e/i

TCM

 HREC/2930A

V PRIME CONTRACTOR CODE

Lockheed Missiles & Space Co., Inc.

P.O. Box 1103

Huntsville, AL 35807

(OBOfHINO a INVOICE

NO

DATE 3/7/85

' PACE I 0'

1 1

I ACCEPTANCE POINT

D

5 DISCOUNT TEAMS

NET 30

0. ADMINISTERED BY CODE

DCASMA-Binningham

2121 8th Avenue, N

Room 104

Birmingham, AL 3S203-2376

II SHIPPED FROM

Same as Block 9

COOf rot 12 PAYMENT WILL BE MADE BY COOf

Financial Management Office

George C. Marshall Space Flight Center

Marshall Space Flgiht Center, AL 35812

U SHIPPED TO CODE] '« MARKED FOR CODE)

Transportation Officer, Bldg, 4471

National Aeronautics & Space Administration Richard Baker

George C. Marshall Space Flight Center ET 65

Marshall Space Flight Center, AL 35812

15

ITEM

NO

001

16 STOCK/PART NO DESCRIPTION

ffWicofo numbvr of shipping containers • rjrp* of

container container numoer )

RAMPED PANEL FIXTURE

QUANTITY

SHIP/REC'O •

1

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| . ___ A ORIGIN __. ._. B DESTINATION

1_JPOA [__UcCEPTANCEoll,If.d .t.rr,, hot b«.n mod. 1 1 PQA 1 1 ACCEPTANCE »l l.tt.d .t«~l ho. b.»n mod.

• •c«pt Qt noted K«««in o* 9n supporting document! «Re«»1 at no»«d h«r«in v on •upftrting document!

DATE SIGNATURE OF AUTH COVT REP DATE SIGNATURE OF AUTM COVT REP

TYPED NAME TYPED NAME

AND OFFICE AND TITLE

u

UNIT

ea

19

UNIT PRICE

NA

20

AMOUNT

NA

22 RECEIVER'S USE

opporcnf good condition ••opt ot no)*d

DATE RECEIVED 2-^tlNATuHE OF AUTM GOVT REP

TYPED NAME

AND OFFICE

* II ouonrify r«c«'V«dBr rh« Cov«irwMnf it fm> SOMO Ol

quantity sntppW indieoto oy ' «^ / mark >1 d>t

f*r*nf, »nf«r ocruof 0woririr)r r«c«i.*d »*fov ouottiijr

inipptd ond •rtcircf*

23 CONTRACTOR USE ONLY

To be delviered to NASA at Bldg. 4707

A-4

DO FORM 250 I NOV 66 REPLACES COITION OF 1 AUG 87 WHICH MAY BE USED
MATERIAL INSPECTION

AND

RECEIVING REPORT

2. SHIPMENT MO

"C00001

). 0»T| SNIPPED

12/19/84

i.r«OC M»l*Uttt«T tO«MCO*TI*CTt

NAS8-36304

4.1/1

TC" HREC/2856

* P«IME CON Tit AC TO* COOt

Lockheed Missiles & Space Co., Inc.

P.O. Box 1103

Huntsville, AL 35807

tO«0««\MO 4.IMVQICI

NO

OATI 12/19/84

t PAOI I or

I 1

1 ACCEPTANCE POINT

D

J. DISCOUNT TERMS

Net 30

0. ADMINISTERED it COOC

DCASMA-Birmlngham

2121 8th Avenue, N. ,

Room 104

Birmingham, AL 35203-2376

11. SHIPPED FROM II'•rfWrlkM f)

Same as Block 9

coo* | II PAYMENT WILL BE MADE BY cooc I

Financial Management Office

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

IL SHIPPED TO C00E

Transportation Officer, Bldg. 4471

National Aeronautics & Space Administration

George C. Marshall Space Flight Center

Marshall Space Flight Center, AL 35812

14 MARKED FOR

Richard Baker

ET 65

cooc

ITEM

NO

001

r

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(Im/icot* muntu, ol i/iippinf eenioiiwf • >rP» d

centouwr • content*, avmbtr 1

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mftf-r SS

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OF POOR QUM-1^

QUANTITY

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1 JPQfc 1 Let

tor «• 9 vf«4«r My

A ORIGIN

w*«rvifti«n VfW tk«y conlflTM '• c«ntf«ct.

DATE SIGNATURE OF AUTH COVT REP

•VPEO NAME

ANO OFFICE

__ ___ B DESTINATION

1 1 POA 1 1 ACCEPTANCE d l.t'.d .ix» •>.« b>«« ix>d.

DATE SIGNATURE OF AUTH GOVT REP

TYPED NAME

AND TITLE

II

UNIT

Ea

IV

UNIT PRICE

NA

20

AMOUNT

NA

22. RECEIVER'S USE

DATE RECEIVED ' JolSfrfATURE OF AUTH GOVT REP

TYPED NAME

AND OFFICE

fl.-n.ty tA.>wrf, «4<m kr ' ^ '•»» •H*

2) CONTRACTOR USE ONLY

To be picked up by NASA from Lockheed's Bldg. 401.

A-5

DO *ORM 250 i NOV «• REPLACES COITION OF 1 AUG 67 WHICH MAY BE USCO
LMSC-HEC TR D065122

Appendix B

DIMENSIONED SKETCHES OF REDESIGNED HGF DIFFUSER

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
U

Ju.

li.

u. oopoUJo-J

CD «f

* — — *^ '

oo "c;

ORIGINAL PAGE IS

OF POOR QUALITY

T1

o ^ • TW

(NJ &

<N s

UJ

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oO— oIIXatB-l
ORIGINAL PAGE IS

OF POOR QUALITY

— <N

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B5
LMSC-HEC TR D065122

Appendix C

ROUGH STRESS NOTES FOR BEEF-UP

OF STRUCTURE TO INCREASE CHAMBER PRESSURE

FROM 150 TO 300 PSIA (BY MIKE TILLEY, DdSC-HUNTSVILLE)
Pr«por«d by. Dot*

LOCKHEED MISSILES ft SPACE COMPANY. INC.

Po«.

Ch.clc.d by. Dot* TitU Mod*!

Approved by , Dot. Report No.

X 13

x

UlUO)

c-i

Z 37$ > v,

-TWO ?A£U~ztit>

o

o
3

r*por*d by. Dot*

LOCKHEED MISSILES ft SPACE COMPANY. INC.

Pag* T«mp.

z_

Ch*ck*d by: Dot* Tltl. Model

Approved by .Dot*

ORIGINAL PAGE tS

OF POOR QUALITY Report No.

6 >L 13

\

/

/

/

/

C-2

.7«
'lepoted by:

••""••

 7 i Dot*

LOCKHEED MISSILES ft SPACE COMPANY. INC.

Poo* I""*-

Checked by.

Approved by.

Dot* TltU

Date

Model

Report No.

l(.>

?Z. i^) TLATi A^TSAS

C-3
Pr«por»d by. I Dot*

LOCKHEED MISSILES 4 SPACE COMPANY. INC

Pag* T.~

Ch.ek.d by. .Dot* TltU

Approved by Dot*

ORIGINAL PAGE IS

OF POOR QUALTTY

Model

Report No.

"EAR 1

r

~LO.2\t~ 'M.

/AJ

Z7.

*i

LtITi CW*'* OUWit. ,.'[—

-B

! \

-fc

\ X
>r«par«d by- Dot*

LOCKHEED MISSILES & SPACE COMPANY. INC.

Pog. T.-P.

Ch.ek.d by. Dot* TitU Mod.I

Approved by. Dot* Report No.

FfrK. TSAR 3

Z.// 0

2 /. //Jb(A 2

C-5
'r»por»d by: Dot*

LOCKHEED MISSILES ft SPACE COMPANY. INC.

Poo. '«•».

Ch.ek.d by

Approved by.

Dot* TitU

i Dot*

Mod»l

Report No.

r

37S

I I

CUT cur 7?4is

T5/A/1A
Prepored by: I Dot*

LOCKHEED MISSILES ft SPACE COMPANY. INC.

Pog*

Checked by Dot* Title Model

by Dote Report No.

o v / • «t— j

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A^J

T5

1,0

i

C-7
'repored by: Dot*

LOCKHEED MISSILES » SPACE COMPANY. INC.

Pap*

Cheeked by

Approved by

Dot* Till.

Date

Model

Report No.

4.1

C-8
LMSC-HEC TR D065122

Appendix D

TYPICAL SET OP CALIBRATION

RUN DATA (POR RUN NUMBER 38)

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
o

CM

oo

i-H

10

1°

IAJ

J !____ _

ORIGINAL PAGE IS

j Of| POOR QUAlifTX

1.: ! i L_o_

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LMSC-HEC TR DO65122

Appendix E

LISTING OF COMPUTER PROGRAM

TO DETERMINE HGF SET PRESSURES,

CHAMBER PRESSURES AND TEMPERATURES

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
ORIGINAL PAGE ?S

OF POOR QUALITY

JO REM PROGRAM 70 DETERMINE HBP OPERATIONAL PARAMETERS SUCH AS

'4<'i KEI1 02 PRESSURES, H2 PRESSURES, AND Tc TEMPERATURES.

50 REN

60 REM **** INITIALIZE PROGRAM ****

70 REM PRINT CHR*(27);CHRS(43): PRINT

30 PRINT

rff) PRINT

ilOO PRINT "THE PURPOSE OF THIS PROGRAM IS TO ACT AS A TOOL IN CALCULATING"

110-PRINT "FOR ANY TWO OF THE FOUR VARIABLE HGF TEST REQUIREMENTS.": FPINT

120 PRINT TAB(5);"ASSIGNED DESIGNATORS FOR EACH VARIABLE ARE AS FOLLOWS:": PRINT

(13O PRINT TAB(5> ; "OXIDIZER CONTROLLER PRESSURE 'Pa' "

|140 PRINT TAB (5) ; "HYDROGEN CONTROLLER PRESSURE ' Ph ' "

150 PRINT TAB (5) ; "COMBUSTION CHAMBER PRESSURE ' Pc ' "

•160 PRINT TAB(5);"COMBUSTION CHAMBER TEMPERATURE 'Tc' "

SELSCT DESIRED FUNCTION FROM THE FOLLOWING:":PRINT

(1) FOR Pc IF Pa V Ph ARE KNOWN"

(2) FOR Tc IF Pa '.< Ph ARE KNOWN"

(3) FOR Pa IF Pc !' Ph ARE KNOWN"

(4) FOR Pa IF Tc !< Ph ARE KNOWN"

(5) FOR Pa IF Pc & Tc ARE KNOWN"

(6) FOR Ph IF Pc & Tc ARE KNOWN"

(7) TO QUIT THIS PROGRAM AND EXIT TO CF/M."

170 PRINT TABU5)

180 PRINT TAB(25)

190 PRINT TAB(25)

20O PRINT TAB(25)

210 PRINT TAB(25)

220 PRINT TAB(25)

£30 PRINT TAB(25)

E40 PRINT TAB(25)

250 PRINT: PRINT

C60 INPUT "ENTER NUMBER 1-7 FROM THE ABOVE MENU"5E*

270 IF E*="l" GOTO 1000

280 IF E*="2" GOTO 20OO

290 IF ES="3" GOTO 3OOO

3'>O IF E$="4" GOTO 4000

310 IF ES="5" GOTO 5OQ<>

32'"> IF E$="6" GOTO 6OOO

33<.i IF E*="7" GOTO 50O

3£ O IF E*-"7" GOTO 60

50O PRINT CHR*<27);CHR*(43)

51O SYSTEM

52U END

100O PRINT CHR*(27);CHR*<43> : PRINT:PRINT:PRINT

1010 PRINT "SUBROUTINE FOR DETERMINING PC IF Pa AND Ph PRESSURES ARE KNOWN"

1020 PRINT

1030 INPUT "ENTER PRESSURE (PSIG) VALUE FOR 'Pa' "; XV.

1040 PRINT

1050 INPUT "ENTER PRESSURE (PSIG) VALUE FOR 'Ph' "; Y7.

1070 ANS1= 17.72 + .1115 * (XV. + Y7.)

1080 PRINT "COMBUSTION CHAMBER PRESSURE (Pc) IS ";ANSI;"PSIG.": PRINT

1090 INPUT "ENTER 1 TO RETURN TO MENU OR 2 TO EXIT TO CP/M.";Gt

1100 IF G1i="l" GOTO 6O

ill 10 IF G*="2" GOTO 500

Ill2u IF G$>"2" GOTO 1O90

poOO PRINT CHR«(27);CHR*(43>: PRINT:PR INT:PRINT

E010 PRINT "SUBROUTINE FOR DETERMINING Tc IF Pa AND Ph PRESSURES ARE KNOWN"

2O20 PRINT

Z030 INPUT

-Pa' X7.

•Ph' Y7.

"ENTER PRESSURE (PSIG) VALUE FOR

C040 PRINT

[2050 INPUT "ENTER PRESSURE (PSIG) VALUE FOR

P060 REM

(2070 ANS2= 4704 - 3116 * <XV. / Y7.)

'COMBUSTION CHAMBER PRESSURE (Pc) IS ";ANSZ "DEG.F":PRINT

"ENTER 1 TO RETURN TO MENU OR 2 TO EXIT TO CP/M."; GS

ioao PRINT

7090 INPUT

2100 IF G$="l" GOTO 6O

2110 IF G$="2" GOTO 5OO

2120 IF G$>"2" GOTO 2090

:000 PRINT CHRS(27);CHRS(43): PRINT:PRINT:PRINT

3O10 PRINT "SUBROUTINE FOR DETERMINING OXIDATION CONTROLLER PRESSURES (Pa)

3020 PRINT "IF Pc ?< Ph PRESSURES ARE KNOWN.":PRINT:PRINT

:030 INPUT "ENTER PRESSURE 'PSIG) VALUE FOR 'Pc' ": XV.

E-l
3040

.3050

3O70

3090

3100

5110

El 20

»000

4010

4O20

4030

4040

4050

4O70

4080

4090

41OO

'4110

J4120

5000

,5010

5020

J5030

15040

J5050

5070

5080

5090

5100

pllO

SI 20

'6000

60 1 0

6020

6030

6040

6050

6070

6080

6090

6100

6110

6120

PRINT

INPUT "ENTER PRESSURE (PSIG) VALUE FOR ' Ph' "; F/i

ANS3= (( X7. -17.72) / .1115) - F7.

PRINT "COMBUSTION CHAMBER PRESSURE (Pc) IS "; .WS3:"P<3IG."iPRINT

INPUT "ENTER 1 TO RETURN TO MENU OR 2 TO EXIT TO CP/M."; G*

IF G*="l" GOTO 60

IF G*="2" GOTO 500

IF GS>"2" GOTO 3090

PRINT CHR*<27>;CHR*(43): PRINT:PRINT:PRINT

PRINT "SUBROUTINE FOR DETERMINING OXIDIZER CONTROLLER PRESSURES (Pa)1

IF Tc TEMPERATURE 8- Ph PRESSURES IS KNOWN.":PRINT:PRINT

ENTER TEMPERATURE (DEG.F) VALUE FOR 'Tc' "; T7.

PRINT

INPUT

PRINT

INPUT

ANS4=

PRINT

"ENTER PRESSURE (PSIG) VALUE FOR 'Ph'. "; F7.

((4704 - T7.) / 3116) * F7.

"OXIDATION CONTROL PRESSURE (Pa) SETTING IS ";ANS4;"PSIG.":PRINT

INPUT "ENTER 1 TO RETURN TO MENU OR 2 TO EXIT TO CP/M."; GS

IF GS="1" GOTO 60

IF GS="2" GOTO 500

IF G*>"2" GOTO 4090

PRINT CHR*(27>;CHR*(43): PRINT:PRINT:PRINT

PRINT "SUBROUTINE FOR DETERMINING OXIDATION CONTROL PRESSURES (Pa)"

PRINT "IF PC PRESSURE & Tc TEMPERATURE ARE KNOWN.":PRINT:PRINT

INPUT "ENTER PRESSURE (PSIG) VALUE FOR 'Pc' "; C7.

PRINT

INPUT "ENTER TEMPERATURE (DEG.F) VALUE FOR 'Pc' "; T7.

ANS5= (( 4704 - T7.) / 3116) * ( 27946.2 * ( C7. - 17.72» / ( 7B20 - T7.)

PRINT "OXIDATION CONTROL PRESSURE (Pa) SETTING IS ";ANS5;"PSIG.":PRINT

INPUT "ENTER 1 TO RETURN TO MENU OR 2 TO EXIT TO CP/M.";G*

IF G$="l" GOTO 60

IF G*="2" GOTO 500

IF G*>"2" GOTO 5090

PRINT CHR*(27>:CHR*(43>: PRINT:PRINT:PRINT

"SUBROUTINE FOR DETERMINING HYDROGEN(FUEL) CONTROLLER PRESSURES(Ph)'

" IF Pc PRESSURE ?< Tc TEMPERATURE ARE KNOWN.": PRINT: PRINT

"ENTER PRESSURE (PSIG) VALUE FOR ' Pc' . "; X7.

PRINT

PRINT

INPUT

PRINT

INPUT

ANS6=

PRINT

INPUT

IF G*="l"

IF G$="2"

"ENTER TEMPERATURE (DEG.F) VALUE FOR ' Pc' . ": Y7.

(( X7. - 17.72) / .115) /(!+( ( 4704 - T7.) / 3116))

"HYDROGEN CONTROLLER PRESSURE (Ph) SETTING IS ";ANS6?"PSIG.":PRINT

"ENTER 1 TO RETURN TO MENU OR 2 TO EXIT TO CP/M.";G*

GOTO 60

GOTO 500

GOTO 6090

E-2
LMSC-HEC TR D065122

Appendix F

LISTING OF NASA-MSFC STATIC

MEASURING PROGRAM FOR HGF CAL RUNS

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
IMSC-HEC TR D065122

J3-257G STATIC MEASURING PROGRAM

R. SMITH ET64

HOT GAS FACILITY IA

P092-0017 FORWARD

8/13/85

GEORGE C. MARSHALL SPACE FLIGHT CENTER

TEST LABORATORY

HUNTSVILLE. AL

F-ii
mSC-HEC TR D065122

STATIC

NO.

I 1

T 2

T 3

T 4

T 5

T 6

T 7

T 8

r 9

T 10

T 11

T 12

T 13

I 14

T 15

T 16

T 17

T 18

T 19

T 20

T 21

T 22

SIU

R/C

0500

0501

0502

0503

0504

0505

0506

0507

0508

0509

0510

0511

0512

0513

0514

0515

0516

0517

0518

0519

0520

0521

MEASUREMENT

DESCRIPTION

TOP TEST PANEL T/C 11

TOP TEST PANEL T/C *2

TOP TEST PANEL T/C *3

TOP TEST PANEL T/C *4

TOP TEST PANEL I/C *5

TOP TEST PANEL I/C *6

TOP TEST PANEL T/C *7

TOP TEST PANEL T/C *8

TOP TEST PANEL I/C 49

TOP TEST PANEL T/C *10

TOP TEST PANEL I/C HI

TOP TEST PANEL I/C *12

TOP TEST PANEL T/C *13

TOP TEST PANEL T/C 114

TOP TEST PANEL I/C 115

TOP TEST PANEL T/C *16

TOP TEST PANEL T/C *17

TOP TEST PANEL T/C *18

TOP TEST PANEL T/C *19

TOP TEST PANEL T/C *20

WEST TEST PANEL T/C *1

WEST TEST PANEL I/C 42

TRANSDUCER

NAME

TC CR/A

1C CR/A

1C CR/A

1C CR/A

TC CR/A

TC CR/A

TC CR/A

TC CR/A

1C CR/A

TC CR/A

1C CR/A

1C CR/A

TC CR/A

TC CR/A

1C CR/A

TC CR/A

1C CR/A

TC CR/A

1C CR/A

1C CR/A

TC CR/A

rc CR/A

CALIB.

RANGE REMARKS

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

F-l
IWSC-HEC TR D065122

STATIC

NO.

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

T

23

24

25

26

27

28

29

30

31

32

33

34

35

36

37

38

39

40

41

42

43

SIU

R/C

0522

0523

0524

0525

0526

0527

0528

0529

0530

0531

OGOO

0601

0602

0603

0604

0605

0606

0607

0608

0609

0610

MEASUREMENT

DESCRIPTION

UEST

WEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

UEST

EAST

EAST

EAST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

T/C

T/C

T/C

T/C

T/C

T/C

T/C

T/C

I/C

T/C

I/C

I/C

I/C

T/C

I/C

I/C

T/C

T/C

T/C

T/C

T/C

*3

*4

*5

*6

#7

*8

*9

*10

til

#12

#13

*14

415

*16

*17

*18

*19

*20

*1

*2

#3

TRANSDUCER

NAME

1C

1C

1C

TC

TC

TC

TC

TC

1C

TC

1C

TC

1C

1C

1C

1C

TC

TC

1C

TC

TC

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CALIB.

RANGE REMARKS '

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000E

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

F-2
—rtJCA, in. IAJOJJ.AA

STATIC

NO.

T 44

T 45

T 46

T 47

T 48

T 49

T 50

T 51

T 52

T 53

T 54

T 55

T 56

I 57

T 58

T 59

T 60

T 61

T 62

T 63

T 64

T 65

SIU

R/C

0611

0612

0613

0614

0615

0616

0617

0618

0619

0620

0707

0708

0709

0710

0711

0712

0713

0714

0715

0716

0717

0718

MEASUREMENT

DESCRIPTION

EAST TEST PANEL T/C *4

EAST TEST PANEL T/C *5

EAST TEST PANEL T/C *6

EAST TEST PANEL T/C *7

EAST TEST PANEL T/C *8

EAST TEST PANEL T/C *9

EAST TEST PANEL T/C *10

EAST TEST PANEL T/C #11

EAST TEST PANEL T/C 112

EAST TEST PANEL T/C *13

EAST TEST PANEL I/C *14

EAST TEST PANEL T/C *15

EAST TEST PANEL I/C *16

EAST TEST PANEL T/C *17

EAST TEST PANEL T/C *18

EAST TEST PANEL I/C *19

EAST TEST PANEL T/C *20

BOTTOM TEST PANEL T/C *1

BOTTOM TEST PANEL I/C *2

BOTTOM TEST PANEL T/C *3

BOTTOM TEST PANEL T/C *4

BOTTOM TEST PANEL T/C #5

TRANSDUCER

NAME

TC CR/A

1C CR/A '

TC CR/A

TC CR/A

TC CR/A

TC CR/A

TC CR/A

1C CR/A

TC CR/A

1C CR/A

TC CR/A

TC CR/A

1C CR/A

TC CR/A

1C CR/A

1C CR/A

TC CR/A

1C CR/A

1C CR/A

1C CR/A

1C CR/A

1C CR/A

CALIB.

RANGE REMARKS

0/1000E

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000E

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

F-3
LMSC-HEC TR D065122

STATIC

NO.

T

T

T

T

T

T

T

T

T

T

T

I

T

T

T

T

T

T

T

T

T

66

67

68

69

70

71

72

73

74

75

76

77

78

79

80

101

102

103

104

105

106

SIU

R/C

0719

0720

0721

0722

0723

0724

0725

0212

0213

0214

0215

0216

0217

0218

0219

0621

0622

0623

0624

0625

0626

MEASUREMENT

DESCRIPTION

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

BOTTOM

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

TEST

AIR BOTTLE

AIR BOTTLE

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

PANEL

TEMP

PROBE

OXIDIZER IGN NOZ

T/C

T/C

T/C

T/C

T/C

T/C

T/C

T/C

T/C

T/C

T/C

T/C

I/C

I/C

I/C

TEMP

W

#6

#7

*8

#9

#10

#11

*12

*13

*14

*15

#16

*17

*18

#19

#20

GH2 IGN NOZZLE U

OXIDIZER ORIFICE

GH^ lin.TTI r»

IN

TRANSDUCER

NAME

TC

1C

TC

TC

TC

TC

TC

TC

TC

TC

TC

TC

TC

TC

TC

TC

TC

1C

1C

TC

mr*

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

CR/A

r»r» / A

CALI6.

RANGE REMARKS

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/1000F

0/150F

0/150F

0/150F

0/150F

-150/150F

A 1 1 ^ ** r*

F-4
LMSC-HEC TR D065122

STATIC

NO.

T 110

T 113

T 114

T 115

T 116

T 117

T 118

T 119

T 120

T 121

T 122

T 123

T 124

SIU

R/C

0630

0631

0627

0628

0629

0705

0706 ,

0700

0701

0702

0703

0704

0714

MEASUREMENT

DESCRIPTION

AMBIENT TC CHECK

MAIN CHAMBER *1 TC

MAIN CHAMBER *2 TC

MAIN CHAMBER 43 TC

MAIN CHAMBER 44 TC

MAIN CHAMBER 15 TC

MAIN CHAMBER 46 TC

INLET WATER TEMP.

NOZZLE 41 OUTLET UATER TEMP.

NOZZLE 42 OUTLET UATER TEMP.

DIFFUSER DUCT T/C 41 TEMP.

DIFFUSER DUCT T/C 42 TEMP.

DIFFUSER DUCT T/C 43 TEMP.

TRANSDUCER

NAME

TC CR/A

TC CR/A

TC CR/A

TC CR/A

TC CR/A

TC CR/A

TC CR/A

T/C CR-A

T/C CR-A

T/C CR-A

T/C CR-A

T/C CR-A

T/C CR-A

CALIB.

RANGE REMARKS

0/150F

0/2000F

0/2000E

0/2000F

0/2000F

0/2000F

0/2000F

0/1000F

0/1000F

0/1000F

0/2000F

0/2000F

0/2000F

PRESSURES

P 701

P 702

PU702

P 703

PU703

0300

0301

0328

0302

0329

GH2 IGN REG

GH

GH2 IGN NOZ E

UPSTREAM ORIFICE

GH2 IGN NOZ U

GH2 IGN NOZ W

UPSTREAM ORIFICE

mm

HiJW

TABER

751794

mm*

TABER

850505

2000 PSIS

1000 PSIS

1000 PSIA

1000 PSIS

1000 PSIA

F-5
IMSC-HEC TR D065122

STATIC

NO.

P 704

P 705

P 706

P 707

PU707

P 708

PU 708

P 709

P 710

P 711

P 712

P 713

PQ713

P 714

P 715

SIU

R/C

0000

0001

0303

0304

0330

0305

0331

0306

0307

0308

0309

0028

0324

0003

0325

MEASUREMENT

DESCRIPTION

IGN CHAMBER E

IGN CHAMBER U

OXIDIZER IGN REG

OXIDIZER IGN NOZ E

DOUNSTREAN ORIFICE

OXIDIZER IGN NOZ E

UPSTREAM ORIFICE

OXIDIZER IGN NOZ U

DOUNSTREAM ORIFICE

OXIDIZER IGN NOZ U

UPSTREAM ORIFICE

OX FLOW CON REG PR.

OX INJ PR.

GH2 FLO CON REG PR.

RH

2 INJECTOR

MAIN CHAMBER PC

MAIN CHAMBER PC CLOSED-COUPLE

MAIN CHAMBER (BACKUP) PC

OXIDIZER VALVE MANIFOLD

TRANSDUCER

NAME

DATA SENSORS

191

SG-AL

751791

G-DYN

35616

SG-DYN

28341

TABER

850506

SG-DYN

27673

TABER

761760

TABER

802028

SG-AL

43776

9H5W*

mm

SG-AL

41794

DYNISCO

27167

ALINCO

41582

DYNISCO

27686

CALIB.

RANGE REMARKS

1000 PSIA 150 LOU 375 HIGH

1 SEC DELAY

1000 PSIA 150 LOU 375 HIGH

1 SEC DELAY

1000 PSIS

1000 PSIS

1000 PSIA

1000 PSIS

1000 PSIA

(PSIG ADJ)

3000 PSIS

300 PSIS

5000 PSIS

500 PSIS

200 PSIA 75 LOW 150 HIGH

(PSIS) 1.5 SEC DELAY

500 PSIA ANALOG BAY 29 * 14

(PSIG-ADJ)

200 PSIA 75 LOU 150 HIGH

(PSIS) 1.5 SEC DELAY

1500 PSIS

F-6
LMSC-HEC TR D065122

STATIC

NO.

P 716

P 719

P 722

P 723

P 724

P 725

P 726

P 753

P 754

P 781

P 782

P 783

P 790

P 791

SIU

R/C

0326

0310

0311

0319

0320

0321

0322

0312

0313

0314

0315

0316

0323

0004

MEASUREMENT

DESCRIPTION

GH2 VALVE MANIFOLD

HYDRAULIC SUPPLY

COMB CHAMBER H20 INLET PRESS

NOZZLE H20 INLET PRESS

NOZZLE H20 INLET PRESS BACKUP

DIFFUSER SUPPLY

COOLANT SYSTEM

DIFFUSER SUPPLY

COOLANT SYSTEM

DP GH2 INJ/CMBR #1

DP GH2 INJ/CMBR *2

DP MAIN OXID ORF

GH2 TRAILER PRESSURE

AIR SUPPLY

AIR BOTTLE PRESS.

PITOT TUBE PRESS

TRANSDUCER

NAME

TABER

811887

TABER

761490

SG-SI.C

6704

ALINCO

41315

STANDARD

6691

ALLEGANY

22133

TABER

781313

HHb

HHk

SG-DYN

29636

SG-TABR

781385

DYNISCO

25225

DYNISCO

25622

SG-TABR

830715

CALIB.

RANGE

2500 PSIG

5000 PSIG

200 PSIG

200 PSIG

200 PSIG

50 PSIG

0-50 PSI6

100 PSID

100 PSID

2500 PSID

5000 PSIG

5000 PSIG

3000 PSIG

50 PSIA

REMARKS

CUTOFF 100 PSIA HIGH

75 PSIA LOU

CUTOFF 100 PSIA HIGH

1.00 VDC = 100 PSI

75 PSIA LOU

CUTOFF 30 PSIA LOU

47.2 PSIA HIGH

1.00 VDC = 30 PSI

CUTOFF 30 PSIA LOU

47.2 PSIA HIGH

5 LOU 1.5 SEC DELAY

5 LOU 1.5 SEC DELAY

F-7
IMSC-HEC TR D065122

STATIC

NO.

P 1

P 2

P 3

P 4

P 5

P 6

P 7

P 8

P 9

P 10

P 11

P 12

P 13

P 14

SIU

R/C

0005

0006

0007

0027

0009

0010

0011

0012

0013

0014

0015

0016

0017

0018

MEASUREMENT

DESCRIPTION

STATIC #1

STATIC #2

STATIC *3

STATIC *4

STATIC #5

STATIC *6

STATIC *7

STATIC *8

STATIC *9

STATIC *10

STATIC *11

STATIC *12

STATIC *13

STATIC *14

TRANSDUCER

NAME

SG-TABR

752295

SG-TABR

752302

SG-TABR

752273

SG-TABR

752268

SG-TABR

752306

SG-TABR

752279

SG-TABR

840713

SG-TABR

840711

SG-TABR

840712

SG-TABR

752294

SG-TABR

752306

TABER

752298

TABER

840708

TABER

840714

CALIB.

RANGE REMARKS

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

F-8
IflSC-HEC TR D065122

STATIC

NO.

P 15

P 16

P 17

P 18

P 19

P 20

P 21

P 22

P 26

P 27

P 28

P 29

P 30

P 31

P 32

P 33

P 34

P 35

SIU

R/C

0019

0100

0101

0102

0103

0104

0105

0106

0110

0111

0112

0113

0114

0115

0116

0117

0118

0119

MEASUREMENT

DESCRIPTION

STATIC *15

STATIC *16

STATIC *17

STATIC t!8

STATIC #19

STATIC *20

STATIC *21

STATIC *22

DIFFUSER *1

DIFFUSES *2

DIFFUSER *3

DIFFUSER *4

DIFFUSER *5

DIFFUSER *6

DIFFUSER *7

DIFFUSER *B

DIFFUSER 19

DIFFUSER *10

TRANSDUCER

NAME

TA6ER

840716

TABER

752303

TABER

752287

TABER

840715

TABER

752286

TABER

752281

TABER

752284

TABER

840710

CEC 2848

CEC 2823

CEC 1573

CEC 2844

CEC 2820

CEC 2825

CEC 2826

CEC 2828

CEC 2831

CEC 2834

CALIB.

RANGE REMARKS

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

25 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

0-10 PSIA

F-9
LMSC-HEC TR D065122

STATIC

NO.

P 36

P 37

P 38

P 39

P 40

P 41

P 42

P 43

P 44

P 45

P 46

P 47

P 48

H 1

H 2

SIU

R/C

0120

0121

0122

0123

0124

0125

0126

0127

0128

0129

0130

0131

0200

0020

0021

MEASUREMENT

DESCRIPTION

DIFFUSER *11

DIFFUSER *12

DIFFUSER *13

DIFFUSER *14

PITOT DIFFUSER PRES.

TEST SECTION *1 (TOP)

TEST SECTION *2 (BOTTOM)

TEST SECTION *3 (WEST SIDE)

TEST SECTION *4 (EAST SIDE)

NOZZLE *1

NOZZLE *2

NOZZLE *3

NOZZLE 44

HEAT FLUX 1 TEST SECTION-TOP.

HEAT FLUX 2 TEST SECTION-BOT.

TRANSDUCER

NAME

TABER

830710

CEC 2839

CEC 2843

TABER

820718

STANDARD

6671

CEC 2842

TABER

752272

TABER

ALINCO

47199

TABER

830709

TABER

830712

TABER

820714

TABER

820716

MEDTHERM

7248417

MEDTHERM

7248437

CALIB.

RANGE REMARKS

0-15 PSIA

0-10 PSIA

0-10 PSIA

0-30 PSIA

100 PSIG

0-20 PSIA

0-25 PSIA

0-25 PSIA

0-20 PSIA

0-15 PSIA

0-15 PSIA

0-15 PSIA

0-15 PSIA

0-40 BTU

0-40 BIU

F-10
LMSC-HEC TR D065122

STATIC

NO.

H 3

H 4

H 5

H 6

SID

R/C

0022

0023

0024

0025

H 7 0026

FLOUMETERS

F l" 0202

F 2

F 3

F 4

F 5

POSITION

Dl" ~

02

0207

0208

0209

0210

INDICATOR

0030

0031

MEASUREMENT

DESCRIPTION

HEAT FLUX 3 TEST SECIIONWEST SIDE

HEAT FLUX 4 TEST SECTIONEAST SIDE

TOP TEST PANEL HEAT FLUX

WEST TEST PANEL HEAT FULX

SPARE CALORIMETER

FLOW COHBUSTER COOL

INLET COMBUSTION CHAMBER *1

OUTLET COMBUSTION CHAMBER *2

OUTLET COMBUSTION CHAMBER *1

INLET COMBUSTION CHAMBER *2

HYDROGEN VALVE POSITION

OXIDIZER VALVE POSITION

TRANSDUCER

NAME

MEDTHERM

7248422 '

MEDTHERM

7248438

MEDTHERM

98837

MEDTHERM

98838

MEDTHERM

7248433

POTTER

RAA 235

POTTER

346

POTTER

317

POTTER

335

POTTER

357

CALIB.

RANGE

0-40 BTU

0-40 BTU

0-40BTU

0-40BIU

0-40BTU

100 GPM

190HZ=5.00

V=250GPM

0-10 GPM

400HZ=4.00V

10.4 GPM

400HZ=2.5V

=10.75 GPM

400HZ=2.5V

10.2 GPM

400HZ=2.5V

=10.2GPM

o-iooz

0-100Z

REMARKS

CUTOFF 85 GPM MINIMI

CUTOFF 2.0 GPM LOU

CUTOFF 2.0 GPM LOU

CUTOFF 2.0 GPM LOU

CUTOFF 2.0 GPM LOU

F-ll
IMSC-HEC TR D065122

STATIC SIU MEASUREMENT TRANSDUCER CALIB.

NO... R/C DESCRJPTJtON NAME RANGE REMARKS

H Y D RO G EN_ DE T EC T.IOJL SENSORS.

GHI 0428 IGNITER" 0-100% LEL

GH2 0429 H2 VALVE 0-100% LEL

GH3 0430 MAIN GH2 VALVE 0-100% LEL

GH4 0431 DIFFUSER DUCT SENSOR 0-100% LEL

CONTROL TRANSDUCERS

C 1 GH2 SUPPLY CONTROL TRANSDUCER TABER 0-2000 PSIG

751787

C 2 GH2 CONTROL TRANSDUCER PACE 0-1500 PSIG MODEL P2G-1500 PSI

9874

F-12
LMSC-HEC TR D065122

Appendix G

CALIBRATION PANEL INSTRUMENTATION LOCATIONS

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
CO

B

o

•H

CO

B

CU

B

B

•H

01 0) Hi

B T>

P-, C/i

<T >»

mm:

ao

noir

W

O

Ca

W

Pi

W

H

HHHHHHHHWHHE-iUUHWE-iHHUCJ H

O

W

O O

HH

O O

HH

O O

HH

OO

HH

V^

a HHHHHr-iHH

OOOOOOOP^OOOOOOO O

HHHHHHHHHHHHHHH H

HHHHHQQHHHHHH H

w w td u

P

1

" H H M

8 S gg

33

CJ CJ

01

4J

01

B 4-1

•H to

M Ol

to a)

o j=

4) -O

0)

01

.c

w

iH •

<u c

C O

a -H

o. u

u

rH <U

<a tn

co

cu

4J

o

S5

3 r-t

o n

U 4J •

0 co B

6

C O

•H -H

01 4J

ft rH O

4J 0> 01

B CO

01 O, 4-1

B to

co .n o>

D, 4J 4J

•H

B 3 0)

O .B

tH CO U

•U B

(fl O <w

l-l -H O

J3 4J

•iH RJ 4)

rH CJ T3

10 O -rl

I 10

(II U)

JS 0)

J2 IM

4J O

-H

S 6

O

(U 4-1

T3 4-<

CB O

(U VJ

1-1 O

01

[0

cfl

at

1

UJ

;$

D.

i

CJ

u.

LQ

cr

UJ

UJ

»o /• \ i* s-\

n ( 1 n vo

^ LJ g£

<

o

8H O V y ^_ ^^

n 01 co CM cs CM

H H H M tH H

•C«O r I • 1^

^ Vl/

sO

E01 /^~x

O

aO

OJ -< o

OJ * Ol o» * H F-i (-<

«O

•0

S

o

M

Bw

i os

G-l
01

d .-I

O CO

•i-l U C

0) f-l

<a 4J i-i

C

o

a -H

o w

H O

oj

*J

05

<u

c H

CO

<r -T

c*"» n ;

\o

t*>

U]

td

H

Ci CS

U U

H H

.

HHHHHHHHHWHHHUUHWHHHO O

ooo

HHH

HUl

oo

HH

oo

HH

oo

HH

oooooooooopp p

HHHHHHHHHHHH H

U U3

u

r. O

-i O

H W

O O

H H

v0 r-»

H H

OH

g

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G-2
LMSC-HEC TR D065122

Appendix H

HGF GH2 AND AIR VENTURI CALIBRATION DATA

LOCKHEED-HUNTSVILLE ENGINEERING CENTER
HGF GH2 VENTURI

CONTROL FLOW

PRESSURE RATE

(psig) (Ibm/sec)

CONTROL FLOW

PRESSURE RATE

(psig) (Ibm/sec)

CONTROL FLOW

PRESSURE RATE

(psig) (Ibm/sec)

CONTROL FLOW

PRESSURE RATE

(psig) (Ibm/sec)

500

505

510

515

520

525

530

535

540

545

550

555

560

565

570

575

580

585

590

595

600

605

610

615

620

625

630

635

640

645

650

655

660

665

670

675

680

685

690

695

700

705

710

715

720

725

730

735

740

745

0.355

0.358

0.362

0.366

0.369

0.373

0.376

0.380

0.383

0.387

0.390

0.394

0.397

0.401

0.405

0.408

0.412

0.415

0.419

0.422

0.426

0.429

0.433

0.436

0.440

0.444

0.447

0.451

0.454

0.458

0,461

0.465

0.468

0.472

0.476

0.479

0.483

0.486

0.490

0.493

0.497

0.500

0.504

0.507

0.511

0.515

0.518

0.522

0.525

0.529

750

755

760

765

770

775

780

785

790

795

800

805

810

815

820

825

830

835

840

845

850

855

860

865

870

875

880

885

890

895

900

905

910

915

920

925

930

935

940

945

950

955

960

965

970

975

980

985

990

995

0.532

0.536

0.539

0.543

0.546

0.550

0.554

0.557

0.561

0.564

0.568

0.571

0.575

0.578

0.582

0.586

0.589

0.593

0.596

0.600

0.603

0.607

0.610

0.614

0.617

0.621

0.625

0.628

0.632

0.635

0.639

0.642

0.646

0.649

0.653

0.656

0.660

0.664

0.667

0.671

0.674

0.678

0.681

0.685

0.688

0.692

0.696

0.699

0.703

0.706

1000

1005

1010

1015

1020

1025

1030

1035

1040

1045

1050

1055

1060

1065

1070

1075

1080

1085

1090

1095

1100

1105

1110

1115

1120

1125

1130

1135

1140

1145

1150

1155

1160

1165

1170

1175

1180

1185

1190

1195

1200

1205

1210

1215

1220

1225

1230

1235

1240

1245

0.710

0.713

0.717

0.720

0.724

0.727

0.731

0.735

0.738

0.742

0.745

0.749

0.752

0.756

0.759

0.763

0.767

0.770

0.774

0.777

0.781

0.784

0.788

0.791

0.795

0.798

0.802

0.806

0.809

0.813

0.816

0.820

0.823

0.827

0.830

0.834

0.837

0.841

0.845

0.848

0.852

0.855

0.859

0.862

0.866

0.869

0.873

0.877

0.880

0.884

1250

1255

1260

1265

1270

1275

1280

1285

1290

1295

1300

1305

1310

1315

1320

1325

1330

1335

1340

1345

1350

1355

1360

1365

1370

1375

1380

1385

1390

1395

1400

0.887

0.891

0.894

0.898

0.901

0.905

0.908

0.912

0.916

0.919

0.923

0.926

0.930

0.933

0.937

0.940

0.944

0.947

0.951

0.955

0.958

0.962

0.965

0.969

0.972

0.976

0.979

0.983

0.987

0.990

0.994

H-l
HGF Aik VENTURI

CONTROL FLOW CONTROL FLOW CONTROL FLOW CONTROL FLOW

PRESSURE RATE PRESSURE KAIE PRESSURE RATE PRESSURE RAft

(PSIG) (LBM/SEC) (PSIG) (LBM/SEC) (PSIG) (LBN/SEC) <PSI(3) (LBM/SEC)

500

501

502

503

504

505

506

507

508

50V

510

511

512

513

514

515

516

517

518

519

520

521

522

523

524

525

526

527

528

529

530

531

24.115

24.162

24 . 208

24.255

24.302

24.349

24.396

24.443

24.4V0

24.536

24.583

24.630

24.677

24.724

24.771

24.818

24.864

24.911

24.958

25.005

25.052

25.099

25.146

25.192

25.239

25.286

25.333

25.380

25.427

25.473

25.520

25.567

531

532

533

534

535

536

537

538

539

540

541

542

543

544

545

546

547

548

549

550

551

552

553

554

555

556

557

558

559

560

561

562

25.567

25.614

25.661

25.708

25.755

25.801

25.848

25.895

25.942

25.989

26.036

26.083

26.129

26.176

26.223

26 . 270

26.317

26.364

26.411

26.457

26.504

26.551

26.5V8

26.645

26.692

26.739

26.785

26.832

26.879

26 . 926

26.973

27.020

562

563

564

565

566

567

568

569

570

571

572

573

574

575

576

577

578

579

580

581

582

583

584

585

586

587

588

589

590

591

592

593

H-2

27.020

27.066

27.113

27.160

27.207

27.254

27.301

27.348

27.394

27.441

27.488

27.535

27.582

27.629

27.676

27.722

27.769

27.816

27.863

27.910

27.957

28.004

28.050

28.097

28.144

28.191

28 . 238

28.285

28.331

28.378

28.425

28 . 472

593

594

595

596

597

598

599

600

601

602

603

604

605

606

607

608

609

610

611

612

613

614

615

616

617

618

619

620

621

622

623

624

28.472

28.519

28.566

28.613

28.659

28.706

28.753

28.800

28.847

28.894

28.941

28.987

29.034

29.081

29.128

29.175

29.222

29.269

29.315

29.362

29.409

29.456

29.503

29.550

29.596

29.643

29.690

29.737

29 . 784

29.831

29.878

29.924
HUF AIR VENFURI

CONTROL FLOW CONTROL FLOW CONTROL FLOW CONTROL FLOW

PRESSURE RATE PRESSURE RATE PRESSURE RATE PRESSURE RATE

(PSIG) (LBM/SEC) (PSIG) (LBN/SEC) (PSIG) (LBfl/SEC) (PSIG) (LBM/SEC)

625

626

627

628

629

630

631

632

633

634

635

636

637

638

639

640

641

642

643

644

645

646

647

648

649

650

651

652

653

654

655

656

29.971

30.018

30.065

30.112

30.159

30.206

30.252

30.299

30.346

30.393

30.440

30 . 487

30.534

30.580

30.627

30.674

30.721

30.768

30.815

30.861

30.908

30.955

31.002

31.049

31.096

31.143

31.189

31.236

31.283

31.330

31.377

31.424

656

657

658

659

660

661

662

663

664

665

666

667

668

669

670

671

672

673

674

67b

676

677

678

679

680

681

682

683

684

685

686

687

31.424

31.471

31.517

31.564

31.611

31.658

31.705

31.752

31.799

31.845

31.892

31.939

31.986

32.033

32.080

32.127

32.173

32.220

32.267

32.314

32.361

32.408

32.454

32.501

32.548

32.595

32.642

32.689

32.736

32 . 782

32.829

32.876

687

688

689

690

691

692

693

694

695

696

697

698

699

700

701

702

703

704

705

706

707

708

709

710

711

712

713

714

715

716

717

718

32.876

32.923

32.970

33.017

33.064

33.110

33.157

33.204

33.251

33.298

33.345

33.392

33.438

33.485

33.532

33.579

33.626

33.673

33.719

33.766

33.813

33.860

33.907

33.954

34.001

34.047

34.094

34.141

34.188

34.235

34.282

34.329

718

719

720

721

722

723

724

725

726

727

728

729

730

731

732

733

734

735

736

737

738

739

740

741

742

743

744

745

746

747

748

749

34.329

34.375

34.422

34.469

34.516

34.563

34.610

34.657

34.703

34.750

34 . 797

34.844

34.891

34.938

34.984

35.031

3b.078

35.125

35.172

35.219

35.266

35.312

35.359

35.406

35.453

35.500

35.547

35.594

35.640

35.687

35.734

35.781

H-3
HGF AIR VENFURI

CONTROL FLOW CONTROL FLOW CONTROL FLOW CONTROL FLOW

FREbSORE RATE PRESSURE RATE PRESSURE RATE PRESSURE RATE

(PSIG) (LBn/SEC) <PSIG) (LBfl/SEC) (PSIG) (LBM/SEC) (PSIG) (LBN/SEC)

750 35.828

751 35.875

752 35.922

753 35.968

754 36.015

755 36.062

756 36.109

757 36.156

758 36.203

759 36.249

760 36.296

761 36.343

762 36.390

763 36.437

764 36.484

765 36.531

766 36.577

767 36.624

768 36.671

769 36.718

770 36.765

771 36.812

772 36.859

773 36.905

774 36.952

775 36.999

776 37.046

777 37.093

778 37.140

779 37.187

780 37.233

781 37.280

H-4

781

782

783

784

785

786

787

788

789

790

791

792

793

794

795

796

797

798

79V

800

801

802

803

804

805

806

807

808

809

810

811

812

37.280

37.327

37.374

37.421

37.468

37.514

37.561

37.608

37.655

37.702

37.749

37.796

37.842

37.889

37.936

37.983

38.030

38.077

38.124

38.170

38.217

38.264

38.311

38.358

38.405

38.452

38.498

38.545

38.592

38.639

38.686

38.733

812

813

814

815

816

817

818

819

820

821

822

823

824

825

826

827

828

829

830

831

832

833

834

835

836

837

838

839

840

841

842

843

38.733

38.780

38.826

38.873

38.920

38.967

39.014

39.061

39.107

39.154

39.201

39.248

39.295

39.342

39.389

39.435

39.482

39.529

39.576

39.623

39.670

39.717

39.763

39.810

39.857

39.904

39.951

39.998

40.045

40.091

40.138

40.185

843

844

845

846

847

848

849

850

851

852

853

854

855

856

857

858

859

860

861

862

863

864

865

866

867

868

869

870

871

872

873

874

40.185

40.232

40.279

40.326

40.372

40.419

40.466

40.513

40.560

40.607

40.654

40.700

40.747

40.794

40.841

40.888

40.935

40.982

41.028

41.075

41.122

41.169

41.216

41.263

41.310

41.356

41.403

41.450

41. 49/

41.544

41.591

41.637
HGF AIR VENTDRI

CONTROL FLOW CONTROL FLOW CONTROL FLOW CONTROL FLOW

PRESSURE RATE PRESSURE RATE PRESSURE RATE PRESSURE RATE

(PSIG) (LBN/SEC) (PSIG) (LBPI/SEC) (PSIG) (LBN/SEC) (PSIG) (LBN/SEC)

875 41.684

876 41.731

877 41.778

878 41.825

879 41.872

880 41.919

881 41.965

882 42.012

883 42.059

884 42.106

885 42.153

886 42.200

887 42.247

888 42.293

889 42.340

890 42.387

891 42.434

892 42.481

893 42.528

894 42.575

895 42.621

896 42.668

897 42.715

898 42.762

899 42.809

900 42.856

901 42.902

902 42.949

903 42.996

904 43.043

905 43.090

906 43.137

H-5

906

907

908

909

910

911

912

913

914

915

916

917

918

919

920

921

922

923

924

925

926

927

928

929

930

931

932

933

934

935

936

937

43.137

43.184

43.230

43.277

43.324

43.371

43.418

43.465

43.512

43.558

43.605

43.652

43.699

43.746

43.793

43.840

43.886

43.933

43.980

44.027

44.074

44.121

44.167

44.214

44.261

44.308

44.355

44 . 402

44.449

44.495

44.542

44.589

937

938

939

940

941

942

943

944

945

946

947

948

949

950

951

952

953

954

955

956

957

958

959

960

961

962

963

964

965

966

967

968

44.589

44.636

44.683

44.730

44.777

44.823

44.870

44.917

44.964

45.011

45.058

45.105

45.151

45.198

45.245

45.292

45.339

45.386

45.433

45.479

45.526

45.573

45.620

45.667

45.714

45.760

45.807

45.854

45.901

45.948

45.995

46.042

968

969

970

971

972

973

974

975

976

977

978

979

980

981

982

983

984

985

986

987

988

989

990

991

992

993

994

995

996

997

998

999

46.042

46.088

46.135

46.182

46.229

46.276

46.323

46.370

46.416

46.463

46.510

46.557

46.604

46.651

46.698

46.744

46.791

46.838

46.885

46.932

46.979

47.025

47.072

47.119

47.166

47.213

47.260

47.307

47.353

47.400

47.447

47.494
AIR VEN1UR1

CONTROL FLOW

PRESSURE RATE

(PSIG) (LBN/SEC)

CONTROL FLOW

PRESSURE RATE

(PSIG) (LBN/SEC)

CONTROL FLOW

PRESSURE RATE

(PSIG) (LBN/SEC)

CONTROL FLOW

PRESSURE RATE

(PSIG) (LBN/SEC)

1000

1001

1002

1003

1004

1005

1006

1007

1008

1009

1010

1011

1012

1013

1014

1015

1016

101/

1018

1019

1020

1021

1022

1023

1024

1025

1026

1027

1028

1029

1030

1031

47.541

4/.b88

47.635

4/.681

47. /28

4/.77S

47.822

47.869

47.916

4/.963

48.009

48.056

48.103

48.150

48.197

48.244

48.290

48.337

48.384

48.431

48.478

48.525

48.572

48.618

48.665

48.712

48.759

48.806

48.853

48.900

48.946

48.993

1031

1032

1033

1034

1035

1036

1037

1038

1039

1040

1041

1042

1043

1044

1045

1046

1047

1048

1049

1050

1051

1052

1053

1054

1055

1056

1057

1058

1059

1060

1061

1062

48.993

49.040

49.087

49.134

49.181

49.228

49.274

49.321

49.368

49.415

49.462

49.509

49.55b

49.602

49.649

49.696

49.743

49.790

49.837

49.883

49.930

49.977

50.024

50.071

50.118

50.165

50.211

50.258

50.305

50.352

50.399

50.446

1062

1063

1064

1065

1066

1067

1068

1069

1070

1071

1072

1073

1074

1075

10/6

1077

1078

1079

1080

1081

1082

1083

1084

1085

1086

1087

1088

1089

1090

1091

1092

1093

50.446

50.493

50.539

50.586

50.633

50.680

50. /2/

50.7/4

50 . 820

50.867

50.914

50.961

51.008

51.055

51.102

51.148

51.195

51.242

51.289

51.336

51.383

51.430

51.476

51.523

51.5/0

51.617

51.664

51.711

51.758

51.804

51.851

51.898

1093

1094

1095

1096

1097

1098

1099

1100

1101

1102

1103

1104

1105

1106

110/

1108

1109

1110

1111

1112

1113

1114

1115

1116

1117

1118

1119

1120

1121

1122

1123

1124

51.898

51.945

51.992

52.039

52.086

52.132

52.179

52.226

52.2/3

52.320

52.367

52.413

52.460

52.507

52.554

52.601

52.648

52.695

52.741

52.788

52.835

52.882

52.929

52.9/6

53.023

53.069

53.116

53.163

53.210

53.257

53.304

53.351

H-6
HGF AIR VENTURI

CONTROL FLOW

PRESSURE RATE

(PS10) (LBM/SEC)

CONTROL FLOW

PRESSURE RATE

(PSIG) (LBM/SEC)

CONTROL FLOW CONTROL FLOW

PRESSURE RATE PRESSURE RATE

(PSIG) (LBM/SEC) (PSIG) (LBN/SEC)

1125

1126

1127

1128

1129

1130

1131

1132

1133

1134

1135

1136

1137

1138

1139

1140

1141

1142

1143

1144

1145

1146

1147

1148

1149

1150

1151

1152

1153

1154

1155

1156

53.397

53.444

53.491

53.538

53.585

53.632

53.678

53.725

53.772

53.819

53.866

53.913

53.960

54.006

54.053

54.100

54.147

54.194

54.241

54.288

54.334

54.381

54.428

54.475

54.522

54.569

54.616

54.662

54.709

54.756

54.803

54.850

1156

1157

1158

1159

1160

1161

1162

1163

1164

1165

1166

1167

1168

1169

1170

1171

1172

1173

1174

1175

1176

1177

1178

1179

1180

1181

1182

1183

1184

1185

1186

1187

54.850

54.897

54.943

54.990

55.037

55.084

55.131

55.178

55.225

55.271

55.318

55.365

55.412

55.459

55.506

55.553

55.599

55.646

55.693

55.740

55.787

55.834

55.881

55.927

55.974

56.021

56.068

56.115

56.162

56.208

56.255

56.302

1187

1188

1189

1190

1191

1192

1193

1194

1195

1196

1197

1198

1199

1200

1201

1202

1203

1204

1205

1206

1207

1208

1209

1210

1211

1212

1213

1214

1215

1216

1217

1218

56.302

56.349

56.396

56.443

56.490

56.536

56.583

56.630

56.677

56.724

56.771

56.818

56.864

56.911

56.958

57.005

57.052

57.099

57.146

57.192

57.239

57.286

57.333

57.380

57.427

57.473

57.520

5/.S67

57.614

57.661

57.708

5/. 755

1218

1219

1220

1221

1222

1223

1224

1225

1226

1227

1228

1229

1230

1231

1232

1233

1234

1235

1236

1237

1238

1239

1240

1241

1242

1243

1244

1245

1246

1247

1248

1249

57.755

57.801

57.848

57.895

57.942

57.989

58.036

58.083

58.129

58.1/6

58.223

58.270

58.317

58.364

58.411

58.457

58.504

58.551

58.598

58.645

58.692

58.739

58.785

58.832

58.8/9

58.926

58.973

59.020

59.066

59.113

59.160

59 . 207

H-7
HGF AIR VEfNTURI

CUN1ROI FLOW CONTROL FLOW CONTROL FLOW CONTROL FLOW

PRESSURE RAFE PRESSURE RA'FE PRESSURE RATE PRESSURE RATE

(PSIG) <LBfl/SEC> (PSIG) (LBN/SEC) (PSIG) (LBN/SEC) (PSIG) (LBd/SEC)

1250

1251

1252

1253

1254

1255

1256

125/

1258

1259

1260

1261

1262

1263

1264

126b

1266

1267

1268

1269

1270

1271

1272

1273

1274

I27b

1276

1277

1278

1279

1280

1281

59.254

59.301

59. .548

59.394

59.441

59.488

59.535

59.582

59.629

59.676

59.722

59.769

59.816

59.863

59.910

59.957

60.004

60.050

60.097

60.144

60.191

60.238

60.285

60.331

60.378

60.425

60.472

60.519

60.566

60.613

60.659

60.706

1281

1282

1283

1284

1285

1286

1287

1288

1289

1290

1291

1292

1293

1294

1295

1296

1297

1298

1299

1300

1301

1302

1303

1304

1305

1306

1307

1308

1309

1310

1311

1312

60.706

60.753

60.800

60.847

60.894

60.941

60.987

61.034

61.081

61.128

61.175

61.222

61.269

61.315

61.362

61.409

61.456

61.503

61.550

61.596

61.643

61.690

61.737

61.784

61.831

61.878

61.924

61.971

62.018

62.065

62.112

62.159

1312

1313

1314

1315

1316

1317

1318

1319

1320

1321

1322

1323

1324

1325

1326

1327

1328

1329

1330

1331

1332

1333

1334

1335

1336

1337

1338

1339

1340

1341

1342

1343

62.159

62.206

62.252

62.299

62.346

62.393

62.440

62 . 487

62.534

62.580

62.627

62.674

62.721

62.768

62.815

62.861

62.908

62.955

63.002

63.049

63.096

63.143

63.189

63.236

63.283

63.330

63.377

63.424

63.471

63.517

63.564

63.611

1343

1344

1345

1346

1347

1348

1349

1350

1351

1352

1353

1354

1355

1356

1357

1358

1359

1360

1361

1362

1363

1364

1365

1366

136/

1368

1369

1370

1371

1372

1373

1374

63.611

63.658

63.705

63.7b2

63.799

63.845

63.892

63.939

63.986

64.033

64.080

64.126

64.173

64.220

64.267

64.314

64.361

64.408

64.454

64.501

64.548

64.595

64.642

64.689

64.736

64.782

64.829

64.876

64.923

64.970

65.017

65.064

H-8
HGF AIR VEINTURI

CONTROL FLOW

PRESSURE RATE

(HS1G) (LBM/SEC)

1375

1376

1377

1378

u;y

1380

1381

1382

1383

1384

1385

1386

1387

1388

1389

1390

1391

1392

1393

1394

1395

1396

1397

1398

1399

1400

65.110

65. 15/

65.204

65.251

65.298

65.345

65.392

65.438

65.485

65.532

65.579

65.626

65.673

65.719

65.766

65.813

65.860

65.907

65.954

66.001

66.047

66.094

66.141

66.188

66.235

66.282

H-9
LMSC-HEC TR D065122

Appendix I

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