扭转度误差对跨声速压气机叶片性能的影响

In the process of compressor blade machining，twist deformation is inevitable due to cutting force and other factors. To explore the effects of twist angle error on blade aerodynamic performance，the measured twist angle error of a compressor blade was applied to Rotor 37 to create the blades with error，and the performance parameters under the design rotating speed were obtained by numerical simulation. The results show that：compared with the original blade，the characteristic curve of under-deflection blades moves to the low-flow condition as a whole，which moves to the high-flow condition as the blades are over-deflection. And the aerodynamic performance of the corresponding blades of each twist scheme is qualified. Under the design condition，the total pressure ratio changes more significantly than the isentropic efficiency with twist angle error changing，and the total pressure ratio decreases when the blades are under-deflection whose maximum variation is 0.85%. Additionally，the stable working margin increases when the blades are under-deflection，whose maximum variation is 12.29% compared with the original blade. At the same time，the channel shock wave is delayed，the flow loss is reduced，and the range of low-speed area at the blade tip decreases as the blades are under-deflection. It indicates that the negative twist angle error within tolerance has a certain improvement effect on the flow condition.