Research of manufacturing errors on aerodynamic performance uncertainty of compressor rotor

To investigate the impact of manufacturing errors on the stability of the compressor operation, a geometric uncertainty reduced order model is developed by generating the normal manufacturing error of blade profile and considering the correlation of blade profile. The stability margin improvement of the compressor was then calculated by using the computational fluid dynamics (CFD), and the neural network was used to predict the relationship between the uncertainty input variables and the stability margin improvement. Finally, a large number of samples were generated by using the Quasi-Monte Carlo method, and Sobol sensitivity analysis was performed. The results show that although the average value of the stability margin under the impact of manufacturing errors is almost equal to the design value, manufacturing errors can reduce the stability margin by about 3% in the limiting case. The parameters that have the greatest impact on the stability of the compressor are the blade chord length of the hub section and the maximum thickness of the tip section and they affect the blade tip blockage by influencing spanwise secondary flow on the suction surface. Furthermore, the results also demonstrate that the decrease in maximum thickness at the tip section affects the separation of the boundary layers on the suction surface, resulting in additional effects.