摘要
Numerical investigation was carried out to study the aerodynamics and cooling effects of trailing edge. For understanding deeply and gaining more details, an unsteady numerical model has been proposed based on steady model. The unsteady numerical simulation was conducted under different blowing ratios (0.5, 2.0) to show their effects on film cooling effectiveness. The computational results show that the turbulence intensity in downstream region of the outlet of trailing edge tends to be enhanced by the unsteady flow effect. Film cooling effectiveness of unsteady model is weaker than that obtained by the steady model. When the blowing ration is 0.5, the mixture and interaction of main flow and secondary flow are rapid and fierce; with the increase of blowing ratio up to 2.0, the secondary flow plays dominant role on the flow characteristics near the outlet of trailing edge. The mixture and interaction of main flow and secondary flow become smooth. The unsteady computational results agree better with the experiment results than that by steady computation.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 607-611 |
| 页数 | 5 |
| 期刊 | Tuijin Jishu/Journal of Propulsion Technology |
| 卷 | 28 |
| 期 | 6 |
| 出版状态 | 已出版 - 12月 2007 |