摘要
Film cooling effectiveness of single row holes located at different sites on turbine blade surface were studied experimentally in a large-scale liner cascade. There were eight rows of film cooling holes on the surface of blade, two rows on the suction surface, three rows on the leading edge and three rows on the pressure surface. The Film cooling effectiveness on the blade surface were measured in the cases of mainstream Reynolds number from 250000 to 450000 and blowing ratio from 0.5 to 2.5. The influences of the location of film cooling holes on cooling effectiveness were described. The experimental results show that the film cooling effectiveness are mainly determined by blowing ratios.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 39-43 |
| 页数 | 5 |
| 期刊 | Tuijin Jishu/Journal of Propulsion Technology |
| 卷 | 25 |
| 期 | 1 |
| 出版状态 | 已出版 - 2月 2004 |