| タイトル | Energy Efficient Engine: High-pressure compressor test hardware detailed design report |
| 本文（外部サイト） | http://hdl.handle.net/2060/19900019254 |
| 著者（英） | Howe, David C.; Marchant, R. D. |
| 著者所属（英） | Pratt and Whitney Aircraft |
| 発行日 | 1988-03-01 |
| 言語 | eng |
| 内容記述 | The objective of the NASA Energy Efficient Engine program is to identify and verify the technology required to achieve significant reductions in fuel consumption and operating cost for future commercial gas turbine engines. The design and analysis is documented of the high pressure compressor which was tested as part of the Pratt and Whitney effort under the Energy Efficient Engine program. This compressor was designed to produce a 14:1 pressure ratio in ten stages with an adiabatic efficiency of 88.2 percent in the flight propulsion system. The corresponding expected efficiency for the compressor component test rig is 86.5 percent. Other performance goals are a surge margin of 20 percent, a corrected flow rate of 35.2 kg/sec (77.5 lb/sec), and a life of 20,000 missions and 30,000 hours. Low loss, highly loaded airfoils are used to increase efficiency while reducing the parts count. Active clearance control and case trenches in abradable strips over the blade tips are included in the compressor component design to further increase the efficiency potential. The test rig incorporates variable geometry stator vanes in all stages to permit maximum flexibility in developing stage-to-stage matching. This provision precluded active clearance control on the rear case of the test rig. Both the component and rig designs meet or exceed design requirements with the exception of life goals, which will be achievable with planned advances in materials technology. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 90N28570
NASA-CR-180850
NAS 1.26:180850
PWA-5594-287 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/136335 |
