叶片单一与耦合误差对轴流压气机性能的影响

Due to the limitation of processing technology and other factors，there is always a small error between the theoretical blade profile and the actual blade profile in the actual processing. For transonic compressor Rotor 37，the influences of axial position and stagger angle errors on the uncertainty of compressor aerodynamic performance were studied by numerical simulation and NIPC (non-intrusive polynomial chaos method). The conclusion indicated that，for machining errors with zero mean standard normal distribution of axial position and stagger angle，the sensitivity of rotor aerodynamic performance was approximately the same when they changed singly or in coupling，only individual parameters were different. The correlation between the aerodynamic performance of axial flow compressor and each error was strong or weak，and attention shall be paid to the performance parameters with strong correlation during processing. The influence of blade coupling error on compressor lied in the superposition of the influences of blade axial position error and stagger angle error.