Abstract
Heat transfer of rows on leading edge of turbine blade was studied experimentally. Minimum blowing rate with no ingress of gas into cavity, local heat transfer coefficients on the leading edge and the flat side-wall were measured. The influences of mainstream Reynolds number and blowing rate on heat transfer coefficients were described. The test parameters are the mainstream Reynolds number from 42 000 to 127 000 and blowing rate from 0. 8 to 2. 0.
| Original language | English |
|---|---|
| Pages (from-to) | 64-68 |
| Number of pages | 5 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 20 |
| Issue number | 2 |
| State | Published - Feb 1999 |
Keywords
- Film cooling
- Gas cooling
- Heat transfer
- Turbine blade