Redesign of axial compressor under multistage environment using inverse method

An inverse method for multistage axial compressor was researched based on the fully threedimensional viscous flow solution. The numerical method used was introduced, and the theory and procedure of inverse design method were described. In order to verify the effectiveness of present method, the initial design results of certain high pressure compressor at rear four stages were simulated and redesigned by using present inverse method. The specific method of tailoring the pressure loading distribution on the blade surfaces under multistage environment was developed based on the analysis of the numerical result. The redesigned result indicated that the whole aerodynamic performance of the fourstage compressor was enhanced after tailoring the pressure loading distribution on multi blade rows reasonably. The adiabatic efficiency of the whole compressor almost remained unchanged, while the pressure ratio was increased by 657% at the design point.