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Full-Scale GRCop-84 Combustion Chamber Liner Preform Fabricated SuccessfullyGRCop-84 (Cu-8 at.% Cr-4 at.% Nb) has been under development at the NASA Glenn Research Center for several years. The alloy possesses a unique combination of good thermal conductivity, high elevated temperature strength, long creep life, and long low-cycle- fatigue. The alloy is also more oxidation resistant than pure copper and most competitive alloys. The combination of properties has attracted attention from major rocket engine manufacturers who are interested in the alloy for the combustion chamber liner in their next generation of regeneratively cooled engines. Before GRCop-84 can be used in a main combustion chamber application, it must be demonstrated that the alloy can be made successfully to the large sizes and proper shape needed and that it retain useful properties. Recent efforts have successfully demonstrated the ability to fabricate a liner preform via metal spinning that retains the alloy s strength even in the welded sections.
Document ID
20050217183
Document Type
Other
Authors
Ellis, David L.
(NASA Glenn Research Center Cleveland, OH, United States)
Russell, Carolyn K.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Goudy, Rick
Date Acquired
September 7, 2013
Publication Date
June 1, 2005
Publication Information
Publication: Research and Technology 2004
Subject Category
Metals And Metallic Materials
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle20050228985Analytic PrimaryResearch and Technology 2004