纳秒脉冲等离子体激励控制低雷诺数压气机叶栅激波/附面层干扰探索研究

In order to reveal the control mechanism of shock wave/boundary layer interaction in the supersonic compressor cascade at low Reynolds number using plasma actuation, large eddy simulation (LES) is used to study the effects of nanosecond pulse plasma actuation on the boundary layer flow of the supersonic compressor airfoil at low Reynolds number. Flow characteristics of the supersonic compressor airfoil and shock wave systems of the cascade passage under low Reynolds number are studied firstly, then two kinds of plasma actuation layouts are designed. It is found that the plasma actuation imposed in front of the boundary layer separation point of the blade suction surface and pressure surface both can induce the distorted flow structure. The distorted flow structure can trigger the K-H instability of the separated shear layer and induce the spanwise large vortex structure, which can suppress flow separation through promoting the mixing between the main flow and the low-energy fluid in the separation zone. Meanwhile, the shock wave system has been changed due to plasma actuation. It has been found that the shape of separation zones is associated with the position of passage shock waves, which causes various changes of the ratio of boundary layer viscous loss and shock loss.