| タイトル | Combustor technology for future aircraft |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910005036 |
| 著者（英） | Tacina, Robert R. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1990-01-01 |
| 言語 | eng |
| 内容記述 | The continuing improvement of aircraft gas turbine engine operating efficiencies involves increases in overall engine pressure ratio increases that will result in combustor inlet pressure and temperature increases, greater combustion temperature rises, and higher combustor exit temperatures. These conditions entail the development of fuel injectors generating uniform circumferential and radial temperature patterns, as well as combustor liner configurations and materials capable of withstanding increased thermal radiation even as the amount of cooling air is reduced. Low NO(x)-emitting combustor concepts are required which will employ staged combustion. The development status of component technologies answering these requirements are presently evaluated. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 91N14349
AIAA PAPER 90-2400
NASA-TM-103268
E-5707
NAS 1.15:103268 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/134933 |
