| タイトル | Core compressor exit stage study. 1: Aerodynamic and mechanical design |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800010836 |
| 著者（英） | Burdsall, E. A.; Lyons, K. A.; Canal, E., Jr. |
| 著者所属（英） | Pratt and Whitney Aircraft Group |
| 発行日 | 1979-09-01 |
| 言語 | eng |
| 内容記述 | The effect of aspect ratio on the performance of core compressor exit stages was demonstrated using two three stage, highly loaded, core compressors. Aspect ratio was identified as having a strong influence on compressors endwall loss. Both compressors simulated the last three stages of an advanced eight stage core compressor and were designed with the same 0.915 hub/tip ratio, 4.30 kg/sec (9.47 1bm/sec) inlet corrected flow, and 167 m/sec (547 ft/sec) corrected mean wheel speed. The first compressor had an aspect ratio of 0.81 and an overall pressure ratio of 1.357 at a design adiabatic efficiency of 88.3% with an average diffusion factor or 0.529. The aspect ratio of the second compressor was 1.22 with an overall pressure ratio of 1.324 at a design adiabatic efficiency of 88.7% with an average diffusion factor of 0.491. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 80N19113
NASA-CR-159714
PWA-5561-55 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/173153 |
