Abstract
This paper presents a numerical study of a high-turning angle compressor stator with 51°. The main ideas and local modification to achieve better control of boundary layer flow in aircraft are applied to the contouring of bowed stator. The skin friction line of suction side and total pressure loss are discussed in the straight blade, bowed blade and local modified bowed blade. The results show that the local modified bowed blade can effectively control the boundary layer flow and it is applicable to the boundary conditions of high adverse pressure gradient, high-turning and high subsonic inlet velocity.
| Original language | English |
|---|---|
| Pages (from-to) | 465-470 |
| Number of pages | 6 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 22 |
| Issue number | 3 |
| State | Published - Mar 2007 |
| Externally published | Yes |
Keywords
- Aerospace propulsion system
- Bowed blade
- Compressor stator
- High-turning angle
- Local modification
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