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Space shuttle orbit maneuvering engine reusable thrust chamber: Adverse operating conditions test reportTest hardware, facilities, and procedures are described along with results of electrically heated tube and channel tests conducted to determine adverse operating condition limits for convectively cooled chambers typical of Space Shuttle Orbit Manuevering Engine designs. Hot-start tests were conducted with corrosion resistant steel and nickel tubes with both monomethylhydrazine and 50-50 coolants. Helium ingestion, in both bubble and froth form, was studied in tubular test sections. Helium bubble ingestion and burn-out limits in rectangular channels were also investigated.
Document ID
19740018134
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Tobin, R. D. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1974
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-134282
ASR-74-131
Accession Number
74N26247
Funding Number(s)
CONTRACT_GRANT: NAS9-12802
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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