摘要
A cascade design method based on curvature optimization was introduced, which can reduce aerodynamic losses from non-smooth blade profile.14 design parameters are considered in this method. The parameters impacting aerodynamic cascade performance significantly include inlet and outlet geometry angle throat width, bending angle and so on. And the parameters having influence on blade strength evidently include radius of the leading, trailing edge, largest inscribed circle, etc. Either profile of pressure side or profile of suction side is composed of a few sections. The optimization of the largest inscribed circle angle is employed in order to guarantee the curvature continuity of profile. The results of cascade design show that the method developed in the work is suitable for cascade design.
| 源语言 | 英语 |
|---|---|
| 页(从-至) | 37-41 |
| 页数 | 5 |
| 期刊 | Tuijin Jishu/Journal of Propulsion Technology |
| 卷 | 34 |
| 期 | 1 |
| 出版状态 | 已出版 - 1月 2013 |
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