Effect of the bionic chamber position on the aerodynamic performance in a transonic compressor cascade

Abstract

A bionic chamber structure has been investigated in a linear compressor cascade to suppress corner separation of suction side, reduce flow loss, and improve cascade performance. Effects of the bionic chamber at various positions on flow field structures and aerodynamic performance have been studied by numerical simulation. The investigation illustrates that the bionic chamber can increase turbulence kinetic energy near the endwall. Additionally, corner separation along the pitchwise direction is suppressed, and an interaction of concentrated shedding vortex and passage vortex is weakened. Meanwhile, the existence of the bionic chamber is able to diminish the flow loss and enhance the diffusion ability. With the increase of the number of the bionic chamber from the leading edge to the trailing edge, the range of low-energy fluid shrinks more in the pitchwise direction and expands more apparently in the spanwise direction. The bionic chamber arranged in the range of 25% to 50% chord length produces the best effect, which can reduce total pressure loss coefficient by 9.43% and increase static pressure coefficient by 8.35%.