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Low-cycle fatigue analysis of a cooled copper combustion chamberA three-dimensional finite element elastoplastic strain analysis was performed for the throat section of regeneratively cooled rocket engine combustion chamber. The analysis included thermal and pressure loads, and the effects of temperature dependent material properties, to determine the strain range corresponding to the engine operating cycle. The strain range was used in conjunction with OFHC copper isothermal fatigue test data to predict engine low-cycle fatigue life. The analysis was performed for chamber configuration and operating conditions corresponding to a hydrogen-oxygen chamber which was fatigue tested to failure at the NASA Lewis Research Center.
Document ID
19750026196
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Miller, R. W.
(Atkins and Merrill, Inc. Ashland, Mass., United States)
Date Acquired
August 8, 2013
Publication Date
October 1, 1974
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 74-1079
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference
Location: San Diego, CA
Start Date: October 21, 1974
End Date: October 23, 1974
Sponsors: American Institute of Aeronautics and Astronautics, Society of Automotive Engineers
Accession Number
75A10268
Funding Number(s)
CONTRACT_GRANT: NAS3-17807
Distribution Limits
Public
Copyright
Other

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