端壁合成射流激励参数变化对跨声速轴流压气机性能的影响

To improve the aerodynamic performance of high-load axial compressor, an active flow control method with synthetic jet applied on the endwall was proposed. A transonic axial flow compressor NASA Rotor35 was taken as the research object. On the basis of fixed endwall excitation at the core of blade tip blockage, the influences of three excitation frequencies and three jet peak velocities on the aerodynamic performance of the compressor were numerically simulated, and the influencing rules of the endwall synthetic jet excitation parameters were obtained. The results show that the excitation frequency has little influence on the near stall flow of the compressor, but has great influence on the total pressure ratio and isentropic efficiency. It is also found that there is a threshold of excitation frequency, and only when the excitation frequency is greater than the threshold, can the total pressure ratio and isentropic efficiency be higher than those of the prototype compressor. The effect of jet peak velocity on the performance of compressor is inferior to the excitation frequency. Under the action of the endwall synthetic jet exceeding the excitation frequency threshold, the compressor can obtain higher flow margin, total pressure ratio and isentropic efficiency than the prototype compressor even if the peak velocity of the jet is small, and the performance of the compressor can be further improved with the increase of the jet peak velocity.