| タイトル | Preliminary compressor design study for an advanced multistage axial flow compressor |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760025103 |
| 著者（英） | Marchant, R. D.; Marman, H. V. |
| 著者所属（英） | Pratt and Whitney Aircraft |
| 発行日 | 1976-09-01 |
| 言語 | eng |
| 内容記述 | An optimum, axial flow, high pressure ratio compressor for a turbofan engine was defined for commercial subsonic transport service starting in the late 1980's. Projected 1985 technologies were used and applied to compressors with an 18:1 pressure ratio having 6 to 12 stages. A matrix of 49 compressors was developed by statistical techniques. The compressors were evaluated by means of computer programs in terms of various airline economic figures of merit such as return on investment and direct-operating cost. The optimum configuration was determined to be a high speed, 8-stage compressor with an average blading aspect ratio of 1.15. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76N32191
PWA-5386
NASA-CR-135091 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184510 |
