Abstract
Film cooling effectiveness of single film row at different locations on turbine blade surface was studied experimentally. A three-blade linear cascade in a large-scale low-speed opening wind tunnel was used in the experiment. There were 15 rows of film cooling holes at the surface of middle blade which was made of high quality wood and three rows on the suction surface, six rows on the leading edge and six rows on the pressure surface. Film cooling effectiveness on the blade surface was measured for the cases with mainstream Reynolds number from 250000 to 450000 and blowing ratio from 0.5 to 2.5. The influences of Reynolds number, blowing ratio and the location of film cooling holes on film cooling effectiveness were described.
| Original language | English |
|---|---|
| Pages (from-to) | 528-531 |
| Number of pages | 4 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 24 |
| Issue number | 6 |
| State | Published - Dec 2003 |
Keywords
- Experimentation
- Film cooling
- Gas cooling
- Turbine blade