Abstract
Discharge coefficients of film cooling holes were investigated on the turbine blade surface with a large-scale low speed turbine cascade. Discharge coefficients with coolant injection were determined at different blowing ratio and Reynolds number. Results show that turbine blade surface film holes discharge coefficients are different greatly in different hole array position. The distribution of discharge coefficients is mainly determined by blowing ratio for same geometry.
| Original language | English |
|---|---|
| Pages (from-to) | 216-218+239 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 24 |
| Issue number | 3 |
| State | Published - Jun 2003 |
Keywords
- Experiment
- Film cooling
- Flow coefficient
- Gas hole
- Turbine blade