摘要
Film cooling effectiveness of back-step three dimensional slots injection, which modeling the trailing edge cooling of turbine blade, was measured at the slot center line and rib center line. The effects of geometry of slot on film cooling effectiveness were studied. The ratio of slot width to rib width changed from 0.67 to 1.5 and ratio of lip height to slot height changed from 0.5 to 1.89. The experimental results show that the profile of film cooling effectiveness is different at the slot center line and rib center line. Both ratios of slot width to rib width and lip height to slot height have evident influence on the film cooling effectiveness. The sizes of three dimensional mixing flow region increases with the increase of both ratio of slot width to rib width and lip height to slot height.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 312-315+320 |
| 期刊 | Tuijin Jishu/Journal of Propulsion Technology |
| 卷 | 27 |
| 期 | 4 |
| 出版状态 | 已出版 - 8月 2006 |