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Full-scale grcop-84 combustion chamber liner preform fabricated successfully
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Russell, Carolyn K. Ellis, David L. |
| Copyright Year | 2005 |
| Description | GRCop-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. |
| File Size | 142191 |
| Page Count | 4 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050217183 |
| Archival Resource Key | ark:/13960/t6062ht1q |
| Language | English |
| Publisher Date | 2005-06-01 |
| Access Restriction | Open |
| Subject Keyword | Metals And Metallic Materials Fabrication Creep Properties Life Durability Metal Spinning Thermal Conductivity Metal Combustion High Temperature Combustion Chambers Copper Regenerative Cooling Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
