叶片破损对压气机性能的影响OA北大核心CSTPCD

The change rule and mechanism of the aerodynamic performance of transonic compressor blades with damage are studied to investigate the effect of blade damage on compressor performance.The accuracy of the calcu-lation method is verified by the results of the NASA rotor 37 experiment.The influence rule of blade breakage on compressed air performance is investigated through numerical simulation.The flow field structure before and after blade breakage under two typical working conditions is then compared and analyzed to explore the specific causes for performance changes.The results show that the pressure ratio and adiabatic efficiency of the compressor de-crease by 0.663 1%and 0.787 7%,respectively,and that the stability margin of the compressor decreases more obviously.The tip damage mainly affects the structure of the tip flow field and enhances the leakage flow in the tip area.When it interacts with shock waves,flow blockage and flow loss occur in the channel.The findings of this study can provide a theoretical reference for the performance evaluation of aircraft engines in actual service.