Abstract
Experiments have been carried out to study flow characteristics of film cooling outflow in two-pass channel. The two-pass channel of a real turbine blade was simplified. Film bleed hole are distributed along the outlet section surface. Experimental data have been analyzed by dividing the outlet section into several typical cells with rib and film cooling. Experimental results indicate that the effective pressure distribution of the outlet section changes significantly compared with no film cooling outflow and that the flow friction of the whole section decreases due to the influence of film bleeding. The outflow rate of the film bleed hole is the largest at the back of a rib.
| Original language | English |
|---|---|
| Pages (from-to) | 827-830 |
| Number of pages | 4 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 20 |
| Issue number | 5 |
| State | Published - Oct 2005 |
Keywords
- Aerospace propulsion system
- Film cooling
- Flow characteristic
- Rib
- Two-pass channel
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