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Advanced liner-cooling techniques for gas turbine combustors
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Riddlebaugh, S. M. Norgren, C. T. |
| Copyright Year | 1985 |
| Description | Component research for advanced small gas turbine engines is currently underway at the NASA Lewis Research Center. As part of this program, a basic reverse-flow combustor geometry was being maintained while different advanced liner wall cooling techniques were investigated. Performance and liner cooling effectiveness of the experimental combustor configuration featuring counter-flow film-cooled panels is presented and compared with two previously reported combustors featuring: splash film-cooled liner walls; and transpiration cooled liner walls (Lamilloy). |
| File Size | 8268358 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850012805 |
| Archival Resource Key | ark:/13960/t50g8jd8w |
| Language | English |
| Publisher Date | 1985-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Wall Temperature Temperature Distribution Stress Analysis Reversed Flow Gas Turbine Engines Linings Sweat Cooling Film Cooling Combustion Chambers Combustion Efficiency Thermal Stresses Heat Transfer Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |