Abstract
The cooling effectiveness of cylindrical gas-film cooling holes was numerically investigated, which was determined at different radial angles, momentum ratio and turbulent intensity. The results show that: (1) with the increase of the momentum ratio, the area which is influenced by secondary airflow becomes larger, and the trace of the secondary airflow departures from the blade surface; (2) the deflective extent of secondary airflow trace increases with the increase of radial angle; (3) the cooling effectiveness decreases with the increase of distance x/d as a whole, at the condition of a fixed turbulence; (4) the cooling effectiveness increases firstly and then lessens when the turbulent intensity is risen; (5) the cooling effectiveness decreases with the increase of turbulent intensity at momentum ratio 1≤2; (6) the cooling effectiveness lessens with the radial angle of 0°~45°C.
| Original language | English |
|---|---|
| Pages (from-to) | 544-547 |
| Number of pages | 4 |
| Journal | Yingyong Lixue Xuebao/Chinese Journal of Applied Mechanics |
| Volume | 26 |
| Issue number | 3 |
| State | Published - Sep 2009 |
Keywords
- Cooling effectiveness
- Momentum ratio
- Radial angle
- Turbulence