Effect of Segment Endwall Boundary Layer Suction on Compressor 3D Corner Separation

Abstract

Due to the strong secondary flow behavior in the compressor endwall/blade suction-side corner region, a large three-dimensional corner separation will usually be formed with large amounts of compressor aerodynamic loss. In this paper, a linear high-speed compressor cascade, with five NACA 65-K48 stator profiles, is numerically simulated to understand the state of this phenomenon. Based on the experiment, the base flow is validated for the numerical result. Active control of 3D corner separation was investigated by using segment endwall boundary layer suction, which is located along the pressure-side leg of leading-edge horse-shoe vortex during its development in the frontal part of the blade passage. The influence of suction flow ratio was investigated in an effort to quantify the improvements of compressor cascade performance. The results show the optimal suction flow ratio is not the largest, but a critical value, which is 0.83% of inflow mass flow rate. Taking all performance parameters’ changes into consideration, the best is with 1% suction flow ratio. The total-pressure loss is eventually reduced by 11.2% with the optimal suction flow ratio compared to the design condition, and an increase of 9.84% is obtained for the static-pressure ratio.