Investigation of shock wave control by suction in a supersonic cascade

The numerical simulation of suction control on a supersonic cascade is presented in this paper. The purpose of this study is to enhance the resistance backpressure characteristics of a flow field by suction control and demonstrate the evolution of shock structures and parameter distributions in the flow field controlled by suction. The study is based on the SAV21 supersonic cascade designed by the German Aerospace Centre and operated under an incoming Mach number of 2.4 and a flow turning angle of 45 degrees. The three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations in a Cartesian coordinate system are successfully applied to the cascade flow. The two-equation shear-stress transport (SST) k-omega turbulence model of Menter is employed to model the turbulent velocity profile. The results show that when the backpressure is greater than the critical backpressure, the shock train leading edge crosses the throat, causing a decrease in the mass-capturing coefficient and the occurrence of stall. To control supersonic cascade by suction, the most effective location is at the interaction of the shock train leading edge and the suction surface boundary layer. By applying suction control at the key position, the shock train is stabilized at the downstream boundary of the suction slot with a small loss of suction mass flow. At mild backpressure ratio range, the increased backpressure is compensated by the local enhanced barrier wave. By increasing the pressure gradient downstream of the barrier wave, the maximum backpressure is improved by suction control. By using the improved combined suction scheme with one spanwise slot on the suction surface and one streamwise slot on the endwall, the maximum backpressure can be improved by 20% under a suction mass flow of 8% of the capture mass. (C) 2020 Elsevier Masson SAS. All rights reserved.

Automated summary

The study presents a numerical simulation of suction control on a supersonic cascade to enhance resistance backpressure characteristics. The results show that implementing suction control at specific locations can stabilize shock waves and improve backpressure. Increasing pressure gradient downstream of the barrier wave can enhance maximum backpressure through suction control.