| タイトル | Optimization of engines for a commercial Mach 0.85 transport using advanced turbine cooling methods |
| 本文（外部サイト） | http://hdl.handle.net/2060/19730006302 |
| 著者（英） | Kraft, G. A. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1972-11-01 |
| 言語 | eng |
| 内容記述 | A parametric study was made of a group of separate-flow-turbofan engines for use in advanced technology airplanes designed for a cruise Mach number of 0.85 at 40,000 feet. The three-engined airplanes were sized to carry 200 passengers 3000 nautical miles. Supercritical aerodynamics were assumed. Film-cooled turbines were used and sea-level-static turbine-rotor-inlet temperature was always 2600 F. The optimum cycle depends on the noise goal assumed. Without a noise goal the best fan pressure ratio (FPR) is about 1.90. At noise goals of FAR 36, -10 EPNdb, and -20 EPNdb, the best FPR's are 1.85, 1.76, and 1.70, respectively, at cruise. The take-off FPR's are progressively less than the cruise value as the noise goal approaches -20 EPNdb. The penalties in take-off gross weight incurred were 8.5, 19, and 64 percent at goals of FAR 36, -10 EPNdb, and -20 EPNdb, respectively. |
| NASA分類 | AIRCRAFT |
| レポートNO | 73N15029
NASA-TM-X-68173
E-7212 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/201093 |
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