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NASA Contractor Report 175066

Characterization of Real Gas Properties for Space Shuttle Main Engine Fuel
Turbine and Performance Calculations
(NASA-CR-175066)
CHARACTERIZATION OF REAL
GAS PEOPEETIES FOE SPACE SHUTTLE M AIN E NGINE
FUEL TURBINE A ND P EBFOBMANCE CALCULATIONS
Final R eport {Sverdrup Technology, Inc.),
97 p BC A05/MF AQ 1
CSCL 21H G3/20

Gary J. Harloff
Sverdrup Technology, Inc.
Lewis Research Center
Cleveland, Ohio

June 1986

Prepared for
Lewis Research Center
Under Contract NAS 3-24105

NASA

National Aeronautics and
• Space Administration

N86-27418
Unclas
43234

TABLE OF CONTENTS

Page
SUMMARY

1

INTRODUCTION

1

NOMENCLATURE

2

THERMODYNAMIC PROPERTIES

3

MIXING R ULE

3

H 2 T HERMODYNAMIC A ND TRANSPORT PROPERTIES

...... 5

H20 THERMODYNAMIC AND TRANSPORT PROPERTIES

5

H2/H20 T HERMODYNAMIC AND TRANSPORT PROPERTIES

5

AIR T HERMODYNAMIC A ND TRANSPORT PROPERTIES
MIXTURE PROPERTIES

. ..

.........

7

AIR E QUIVALENT CONDITIONS
SSME FUEL TURBINE P ERFORMANCE CALCULATION
SUMMARY O F RESULTS
REFERENCES

7

8
.

9

........ 9
10

C HARACTERIZATION OF R EAL GAS PROPERTIES FOR SPACE SHUTTLE M AIN E NGINE
FUEL T URBINE AND P ERFORMANCE CALCULATIONS

Gary J. Harloff
Sverdrup Technology, Inc.
Lewis Research Center
Cleveland, O hio 44135
SUMMARY

Real thermodynamVc and transport properties of hydrogen, steam, the SSME mixture, and air are developed. The SSME mixture properties are needed for the a nalysis of the space shuttle main engine fuel turbine. The m ixture conditions for the gases, except air, are presented graphically over a temperature range from 800 to 1200 K, and a pressure range from 1 to 500 atm. A1r properties are g iven over a temperature range of 320 to 500 K, which are w ithin the bounds of the thermodynamics programs used, 1n order to p rovide mixture data which 1s more easily checked (than H2/H20) . The real gas