高亚声速轴流压气机的优化叶型

Optimized profile of high subsonic axial flow compressor

基于计算流体动力学和数值优化算法,研究了一种压气机叶型优化设计方法.以入口马赫数为0.7的高亚声速轴流压气机叶型为研究对象,采用拉丁超立方实验法选取优化变量并构建了考虑攻角特性的目标函数,通过引入Gamma-Theta转捩模型,考虑了附面层转捩的影响,最终获得了可以有效改善攻角特性和降低总压损失的高亚声速轴流压气机优化叶型.计算结果表明：优化叶型可以显著降低入口马赫数为0.2-0.8时＋4°和-4°攻角的总压损失,使设计工况（入口马赫数为0.7）下的低损失攻角增加4°以上,优化叶型最佳稠度降低20%并改善低雷诺数时叶栅的流动特性.

An optimization design method of compressor profile was studied by combining computational fluid dynamics and numerical optimization algorithm.The profile of a high subsonic axial flow compressor was taken as the research object with inlet Mach number of 0.7.The optimization variables were selected by Latin hypercube sampling method and an objective function considering incidence performance was built.Boundary layer transition was also taken into account and the Gamma-Theta transition model was used in numerical simulation.An optimized profile of high subsonic axial flow compressor that can improve incidence performance and reduce total pressure loss was obtained.The results show that the optimized profile can significantly reduce total pressure loss at both incidences of-4degree and ＋4degree with inlet Mach number from 0.2to 0.8.It can increase the incidence of lower pressure loss by more than 4degree at the design point（inlet Mach number of 0.7）.In addition,the optimized profile can reduce the optimum consistency by 20% and improve the flow characteristics of cascade at low Reynolds numbers.