轴流压气机转子端壁造型多目标优化的数值研究  

Numerical Investigation on a Transonic Axia-flow Compressor Rotor with Multi-objective Endwall Profiling Optimization

作　　者：高翔[1] 晁晓亮 贾一哲[1] 

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《流体机械》2017年第3期26-32,共7页Fluid Machinery

摘　　要：针对NASA跨音速转子67,建立了可靠的数值计算模型,对3种不同的目标函数开展了非轴对称端壁造型的优化工作。3种优化方案均使得转子性能得到了不同程度改善,效率提升最大为0.41%。优化结果表明,由于相同流量的约束,转子通道中流量分布沿径向发生了改变,对于近轮毂的端壁区域来说,造型后静压梯度的方向对流场具有重要影响。不同造型结果中叶片尾缘三维角区分离的位置与范围也有所不同,当三维角区分离后移且沿径向发生迁移时,会使得效率得到的增益明显降低。Reliable numerical computation method was built on rotor67. Based on this numerical computation method,optimization of non-axisymmetric endwall contouring focusing on three different objective functions were conducted. The three optimal results all improved the performances of the rotor and the maximum improvement was 0. 41%. Because of the restriction of the mass flow rate during optimization,the flow fields in different span height changed to different extent. As for the regions near hub,validity of the gradient direction influences the flow field significantly. In different optimal results,the location and scope of the threedimensional corner separation near the trailing edge of the blade altered obviously,and the gain in efficiency drops when the separation region moves backward and migrates towards spanwise direction.

关 键 词：跨音速轴流压气机转子 非轴对称端壁造型 二次流 多目标优化 

分 类 号：TH41[机械工程—机械制造及自动化] V231.3[航空宇航科学与技术—航空宇航推进理论与工程]