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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
SverdrupTechnology, 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 TRANSPORTPROPERTIES

...... 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 GASPROPERTIES 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 fuelturbine. 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 gasproperty varlatlon of the SSME m ixture 1s q uantified.
Polynomial
Prandtl number,
turbine mixture
950 to 1140 K.
operation.

e xpressions, needed for future computer analysis, for v iscosity,
and thermal c onductivity are g iven for the H2/H20 SSME fuel
at a pressure of 305 atm over a range of temperatures from
These conditions are representative of the SSME turbine

Performance calculationsare presented for the space shuttle main engine
(SSME) fuel turbine. The c alculations use the air e quivalent concept. Progress
towards obtaining the c apability to e valuate the performance of the SSME fuel
turbine, with the H2/H20 m ixture, 1s d escribed.
INTRODUCTION

The SSME fuel turbopump operates with a m ixture of H2 and H20 at about
330 atm and 1105 K. These conditions are suchthat actual gas dynamic measurements 1n the turbine are d ifficult to obtain. One computational tool at NASA
Lewis for a nalyzing turbomachlnery 1s the combined computer programs of Katsanls
and M cNally (refs. 1 to 4). The program accepts constant thermodynamlc and
transport gas property data for each blade row. A current limitation of the
analysis 1s that the boundary layer program (ref. 2)requires the temperature
dependence of the transport properties to be Input as a polynomial function.
The program has thus far been limited to air properties.
The goals of the present study were:
(1) Determine the H2/H20 m ixture thermodynamlc and transport
properties v ariation
(2) C alculate the air e quivalent performance

(3) C urve fit the v ariation of y, Cp, and Pr with temperatureat the
appropriate pressure
(4) C alculate the H2/H20 m ixture performance accounting for property
varatlons from b lade row to b lade row
(5) M odify the K atsanls and M cNally computer programs to account for real
gas effects.
The f irst three goals are addressed herein.
NOMENCLATURE

sound speed

2
act
22
C
Id/Cact
CP
c

actual sound speed squared, c
Ideal/actual sound...
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