| タイトル | Effect of variable-position inlet guide vanes and interstage bleed on compressor performance of a high-pressure-ratio turbojet engine |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930088889 |
| 著者（英） | Braithwaite, Willis M; Huntley, S C |
| 著者所属（英） | National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. |
| 発行日 | 1956-12-28 |
| 言語 | eng |
| 内容記述 | Increased guide-vane turning resulted in poorer overall performance, the decrease being greatest at the highest rotor speed. Rotating stall originating at the tips of the first stage correlated with the knee in the stall-limit line. Increasing guide-vane turning shifted the first-stage stall-free performance and the knee in the stall-limit line to a lower engine speed. Opening the interstage bleed reduced the minimum rotor speed at which stall-free performance of the first stage was possible and tended to eliminate the knee in the stall-limit line. |
| レポートNO | 93R18179
NACA-RM-E56E23a |
| 権利 | No Copyright |
