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Small gas turbine combustor experimental study: compliant metal/ceramic liner and performance evaluation
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Acosta, W. A. Norgren, C. T. |
| Copyright Year | 1986 |
| Description | Combustor research relating to the development of fuel efficient small gas turbine engines capable of meeting future commercial and military aviation needs is currently underway at NASA Lewis. As part of this combustor research, a basic reverse-flow combustor has been used to investigate advanced liner wall cooling techniques. Liner temperature, performance, and exhaust emissions of the experimental combustor utilizing compliant metal/ceramic liners were determined and compared with three previously reported combustors that featured: (1) splash film-cooled liner walls; (2) transpiration cooled liner walls; and (3) counter-flow film cooled panels. |
| File Size | 14546865 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860022110 |
| Archival Resource Key | ark:/13960/t3mw79x52 |
| Language | English |
| Publisher Date | 1986-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Fuel Combustion Cooling Reversed Flow Metals Gas Turbine Engines Linings Modulus of Elasticity Ceramics Combustion Chambers Combustion Efficiency 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 |
