| タイトル | Internal flow characteristics of a multistage compressor with inlet pressure distortion |
| 本文（外部サイト） | http://hdl.handle.net/2060/19770010127 |
| 著者（英） | Debogdan, C. E.; Braithwaite, W. M.; Moss, J. E., Jr. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1977-02-01 |
| 言語 | eng |
| 内容記述 | The measured distribution of compressor interstage pressures and temperatures resulting from a 180 deg inlet-total-pressure distortion for a J85-13 turbojet engine is reported. Extensive inner stage instrumentation combined with stepwise rotation of the inlet distortion gave data of high circumferential resolution. The steady-state pressures and temperatures along with the amplitude, extent, and location of the distorted areas are given. Data for 80, 90, and 100 percent of rotor design speed are compared with clean (undistorted) inlet flow conditions to show pressure and temperature behavior within the compressor. Both overall and stagewise compressor performances vary only slightly when clean and distorted inlet conditions are compared. Total and static pressure distortions increase in amplitude in the first few stages of the compressor and then attenuate fairly uniformly to zero at the discharge. Total-temperature distortion induced by the pressure distortion reached a maximum amplitude by the first two stages and decayed only a little through the rest of the compressor. Distortion amplitude tended to peak in line with the screen edges, and, except for total and static pressure in the tip zone, there was little swirl in the axial direction. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 77N17070
NASA-TM-X-3446
E-8848 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/183267 |
