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H2O2 space shuttle APUA cryogenic H2-O2 auxiliary power unit (APU) was developed and successfully demonstrated. It has potential application as a minimum weight alternate to the space shuttle baseline APU because of its (1) low specific propellant consumption and (2) heat sink capabilities that reduce the amount of expendable evaporants. A reference system was designed with the necessary heat exchangers, combustor, turbine-gearbox, valves, and electronic controls to provide 400 shp to two aircraft hydraulic pumps. Development testing was carried out first on the combustor and control valves. This was followed by development of the control subsystem including the controller, the hydrogen and oxygen control valves, the combustor, and a turbine simulator. The complete APU system was hot tested for 10 hr with ambient and cryogenic propellants. Demonstrated at 95 percent of design power was 2.25 lb/hp-hr. At 10 percent design power, specific propellant consumption was 4 lb/hp-hr with space simulated exhaust and 5.2 lb/hp-hr with ambient exhaust. A 10 percent specific propellant consumption improvement is possible with some seal modifications. It was demonstrated that APU power levels could be changed by several hundred horsepower in less than 100 msec without exceeding allowable turbine inlet temperatures or turbine speed.
Document ID
19750022177
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Date Acquired
September 3, 2013
Publication Date
April 29, 1975
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIRESEARCH-75-11290
NASA-CR-134784
Accession Number
75N30250
Funding Number(s)
CONTRACT_GRANT: NAS3-15708
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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