关键词: 反问题设计方法；激波损失控制；载荷分布；反问题边界条件

Abstract: In order to reduce the shock wave loss of blade passage and improve the aerodynamic performance of transonic compressor，a compressor inverse design program is developed based on the three-dimensional viscous inverse design method theories，and some improvements are made to the inverse method boundary condition. The blade total tangential load remain unchanged during the computational process，and the strength of shock wave in the blade passage is reduced by adjusting the blade surface pressure loading distribution in the axial direction. The NASA Rotor 67 experiment data is used to validate the calculation results. The blade geometry is redesigned by using the modified load distribution based on the inverse design program. The numerical research shows that shock wave strength is reduced and better performance of compressor rotor is achieved. The mass flow and adiabatic efficiency increased by 0.5% and 1.0%，which demonstrates the effectiveness of this method.

Key words: Inverse method；Shock wave loss control；Load distribution；Inverse boundary condition