吸附式压气机叶型和抽吸方案优化设计  

Optimization design for aspirated compressor airfoil and aspiration plan

作　　者：李俊[1] 刘波[1] 杨小东[1] 史磊[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2014年第8期1871-1877,共7页Journal of Aerospace Power

基　　金：国家自然科学基金重点资助项目(51236006)

摘　　要：将智能优化算法与准三维叶栅计算程序相结合,对某吸附式压气机叶型进行了优化设计,对优化设计前后的流场进行了详细分析.优化设计之后叶型总压损失下降40%,静压升提高0.6%.优化得到最佳抽吸位置位于分离区起始点上游,优化叶型具有更均匀的负荷分布,并且优化后叶型的性能在全攻角范围内均得到了提升.结果表明:更均匀的负荷分布会提高叶型的性能,减小叶型分离,降低抽吸所需要的能量.对于在尾缘处存在轻微分离的叶型其最优抽吸位置位于分离区上游.A method was developed by combining intelligent optimization algorithm and quasi-three dimensional cascade calculation programme, and an aspirated compressor airfoil was optimized using this method. And there was a detailed analysis of changes in the original and optimized flow fields. Optimized airfoil can make the total pressure loss reduce by 40 % and the static pressure ratio increase by 0.6 %. The best suction position locates in upstream the start position of the separation region, and the optimized airfoil has more uniform load distribution. In addition, the performance of optimized airfoil has a great improvement with- in the whole incidence angle range. The results show that more uniform load distribution can improve the airfoil performance, decrease the separation region and reduce the energy output on suction. For the airfoil with a small separation region in trailing edge, the best suction lo- cation is located upstream the start position of the separation region.

关 键 词：吸附式压气机 叶型优化 抽吸量 抽吸位置 智能优化 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]