高压压气机出口级叶型加工偏差影响的相关性分析

In order to investigate the coupled effect law of the deviations in different positions on the blade surface, the blade mid-span profile of a high-pressure compressor rotor is studied with the crosscorrelation sensitivity analysis method. The objective is to provide the necessary theoretical basis for rapidly evaluating the blade aerodynamic performance when geometric deviations exist on the blade surface. In this paper, the Hicks-Henne function was used to model the geometric deviations of the blade profile, and the Monte Carlo Simulation and the Surrogate Model method was used during calculating the blade aerodynamic performance under the effect of geometric deviations. By analyzing the calculation results, the correlation law of the deviations in different positions on the blade surface on the non-linear aerodynamic effect was obtained, and the deviation criterion was further optimized by considering the processing cost and the aerodynamic performance. The results show that the sensitivity of the local geometric deviation on aerodynamic performance is affected by the relative size of the deviation and the thickness of the upstream boundary layer in the deviation position. The change of the boundary layer thickness caused by the local geometric deviations is the main factor which affects the correlation of the deviations between different positions.