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Space Shuttle Orbiter engine main combustion chamber cooling and lifeA reusable life requirement of 100 missions is met by controlling the combustion chamber hot-gas wall temperature and strain levels. Maximum life, maximum performance, and minimum engine weight are attained through a descriptive parametric assessment of the regenerative cooling circuit, combustor length, contraction area ratio, and coolant passage geometry. Life is categorized by low-cycle fatigue and creep-stress rupture. Relationships are developed to determine the impact of heat transfer rate, thermal strain level, and geometric influence parameters on life. It is empirically shown that a throat heat flux of 100 Btu/sq in./sec can be accommodated.
Document ID
19740030200
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cook, R. T.
Coffey, G. A.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, Calif., United States)
Date Acquired
August 7, 2013
Publication Date
November 1, 1973
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 73-1310
Meeting Information
Meeting: Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: November 5, 1973
End Date: November 7, 1973
Sponsors: Society of Automotive Engineers, American Institute of Aeronautics and Astronautics
Accession Number
74A12950
Funding Number(s)
CONTRACT_GRANT: NAS8-27980
Distribution Limits
Public
Copyright
Other

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