Abstract
A numerical simulation was performed to analyze the effect of bowed blade on the separation structures and the energy losses in the compressor cascades with different turning angles. The turning angles were 37°, 46°, 54°, respectively. The bowed angles were ±10°, ±20°, ±30°, and the incidence angles were ±5°, ±10°, respectively. The results show that the influence of positive bowed blade is different with the variation of the turning angles. If the turning angle is low, the secondary flow on the suction surface as well as the loss increases. If the turning angle is moderate, it restrains the corner separation, and changes the separation configuration. If the turning angle is high, a low positive bowed angle improves the performance. But the flow becomes worse again if the bowed angle exceeds 20°. The negative bowed blade results in the flow separation and the flow performance is reduced remarkably. The varieties at different incidences are similar. The tendency strengthens at positive incidence and weakens at negative incidence.
| Original language | English |
|---|---|
| Pages (from-to) | 362-366+387 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 28 |
| Issue number | 4 |
| State | Published - Aug 2007 |
| Externally published | Yes |
Keywords
- Air compressor
- Aircraft engine
- Blade
- Cascade
- Structure
- Turning angle
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