为研究某重型燃气轮机的压气机叶栅在振荡条件下的非定常响应特性，采用基于γ-Reθ转捩模型的雷诺时均方程对可控扩散叶型组成的振荡叶栅进行了数值计算，研究了折合频率、来流攻角和前缘造型对叶片气动性能及表面边界层发展的影响。结果表明：叶片吸力面发生分离前存在较大的压力波动,边界层转捩后叶片表面压力波动减小；叶片振动对可控扩散叶型的分离转捩特性影响较大，随着叶片振动折合频率的增大，叶片吸力面边界层分离转捩位置向叶片前缘移动；通过优化前缘曲率造型能抑制边界层转捩位置的前移，同时改善振动状态下的前缘压力波动特征。

To study the unsteady flow characteristics of a compressor cascade of a heavyduty gas turbine under oscillating conditions,a Reynolds averagedNavierStokes equation combining with the γ-Reθ transition model was used to numerically calculate an oscillating cascade with controlled diffusion airfoils (CDA).In allusion to the blades with torsional vibration,the effects of reduced frequency,incoming flow angle of attack and leading edge shape on aerodynamic performance and surface boundary layer development of the balde were studied.The results show that there is a large pressure fluctuation before the separation of the blade suction surface and the pressure fluctuation on the blade surface decreases after the transition of boundary layer.The blade vibration has a great influence on the seperation transition characteristics of the controlled diffusion airfoils.As reduced frequency of blade vibration increases,the boundary layer separation transition position on the suction surface of the blade moves forward to the blade leading edge.By optimizing the curvature shape of the leading edge,the forward movement of the transition position of the boundary layer can be suppressed,and the pressure fluctuation characteristics of the leading edge under the vibration state can be improved at the same time.

TK221

国家科技重大专项（2017-II-0007-0021）