上端壁流向槽抽吸对带导叶跨声速扇形扩压叶栅性能影响的数值研究

Numerical Study on the Effect of Streamwise Groove Suction on Upper Endwall on a Transonic Sectorial Compressor Cascade with Inlet Guide Vane

研究对象为跨声速压气机,探究附面层抽吸对跨声速压气机气动性能和流场结构的影响,利用数值模拟计算的方法对压气机进行了上端壁流向槽附面层抽吸的相关研究。对比原型静叶叶栅和各个抽吸方案可以发现:上端壁附面层抽吸对上角区分离的抑制具有显著效果,能够降低损失并提高扩压能力。当抽吸槽位置设置在靠近角区分离起始点附近时,其抽吸效果最佳,叶栅整体的总压损失降低15.82%。

The research object of this paper is transonic compressor.In order to explore the influence of the boundary layer suction on the aerodynamic performance and flow field structure of the transonic compressor,the numerical simulation method was used to study the upper endwall’s suction to the groove boundary layer of the compressor.Comparing the prototype stator blade cascade and each improvement of different suction schemes,it can be found that the upper endwall boundary layer suction has a significant effect on the suppression of the upper corner separation,which can reduce the loss and improve the pressure expansion capability.The suction effect is the best,with the suction groove position set near the separation start point of the corner zone,and the total pressure loss of the cascade is reduced by 15.82%.