| タイトル | Temperature distortion generator for turboshaft engine testing |
| 著者（英） | Barth, R. L.; Biesiadny, T. J.; Klann, G. A. |
| 著者所属（英） | NASA Lewis Research Center|Army Propulsion Lab. |
| 発行日 | 1984-01-01 |
| 言語 | eng |
| 内容記述 | The procedures and unique hardware used to conduct an experimental investigation into the response of a small-turboshaft-engine compression system to various hot gas ingestion patterns are presented. The temperature distortion generator described herein uses gaseous hydrogen to create both steady-state and time-variant, or transient, temperature distortion at the engine inlet. The range of transient temperature ramps produced by the distortion generator during the engine tests was from less than 111 deg K/sec (200 deg R/sec) to above 611 deg K/sec (1100 deg R/sec); instantaneous temperatures to 422 deg K (760 deg R) above ambient were generated. The distortion generator was used to document the maximum inlet temperatures and temperature rise rates that the compression system could tolerate before the onset of stall for various circumferential distortions as well as the compressor system response during stall. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 85A39065
SAE PAPER 841541 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/390796 |
