| タイトル | Optimization of engines for a commercial Mach 0.98 transport using advanced turbine cooling methods |
| 本文（外部サイト） | http://hdl.handle.net/2060/19720014166 |
| 著者（英） | Whitlow, J. B., Jr.; Kraft, G. A. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1972-03-01 |
| 言語 | eng |
| 内容記述 | A study was made of an advanced technology airplane using supercritical aerodynamics. Cruise Mach number was 0.98 at 40,000 feet altitude with a payload of 60,000 pounds and a range of 3000 nautical miles. Separate-flow turbofans were examined parametrically to determine the effect of sea-level-static design turbine-inlet-temperature and noise on takeoff gross weight (TOGW) assuming full-film turbine cooling. The optimum turbine inlet temperature was 2650 F. Two-stage-fan engines, with cruise fan pressure ratio of 2.25, achieved a noise goal of 103.5 EPNdB with todays noise technology while one-stage-fan engines, achieved a noise goal of 98 EPNdB. The take-off gross weight penalty to use the one-stage fan was 6.2 percent. |
| NASA分類 | PROPULSION SYSTEMS |
| レポートNO | 72N21816
E-6848
NASA-TM-X-68031 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/203698 |
