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Tensile Properties of GRCop-84This is a chapter in the final report on GRCop-84 for the Reusable Launch Vehicle (RLV) Second Generation/Project Constellation Program. It contains information on the tensile properties of GRCop-84. GRCop-84 (Cu-8 at.% Cr-4 at.% Nb) was produced by extrusion and Hot Isostatic Pressing (HIPing). Some of the extrusions were rolled to plate and sheet while other extrusions were drawn into tubing. The material was further subjected to various heat treatments corresponding to annealing, anticipated typical brazing conditions, an end-of-life condition and various elevated temperature exposures to attempt to improve creep resistance. As anticipated, cold work increased strength while decreasing ductility. Annealing at 600 C (1112 F) and higher temperatures was effective. An exposure for 100 h at 500 C (932 F) resulted in an increase in strength rather than the anticipated decrease. High temperature simulated-braze cycles and thermal exposures lowered the strength of GRCop-84, but the deceases were small compared to precipitation strengthened copper alloys. It was observed that the excess Cr could form large precipitates that lower the reduction in area though it appears a minimum amount is required. Overall, GRCop-84 exhibits good stability of its tensile properties, which makes it an excellent candidate for rocket engine liners and many other high temperature applications.
Document ID
20120008551
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Ellis, David L. (NASA Glenn Research Center Cleveland, OH, United States)
Loewenthal, William S. (Ohio Aerospace Inst. Brook Park, OH, United States)
Yun, Hee-Man (Cleveland State Univ. Cleveland, OH, United States)
Date Acquired
August 25, 2013
Publication Date
April 1, 2012
Subject Category
Metals And Metallic Materials
Report/Patent Number
E-17784
NASA/TM-2012-217108
Funding Number(s)
WBS: WBS 463169.04.03.04.03
Distribution Limits
Public
Copyright
Public Use Permitted.

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