关键词: 反问题设计方法；轴流压气机；反问题边界条件；静压分布

Abstract: A new three dimensional viscous inverse design method，which is based on a new inverse boundary condition，is developed for axial compressor blade. The blade surface static pressure distribution is used as design input and the both the blade pressure and suction side profile is the design object. The conservation of Riemann invariant on the blade surface is applied to establish the relationship between the prescribed aerodynamic parameters and the blade geometry variation. The blade geometry keeps changing during the design procession，the dynamic mesh technique is used for updating the computational mesh. In order to validate the effectiveness of present method，the NASA Rotor 37 is chosen as the test case. The blade recovery test is carried out first. Then，the blade surface static pressure distribution is modified reasonably，and a new blade geometry is designed by the inverse method. The design results show the prescribed static pressure distribution is achieved by the inverse design and the design intent is reflected correctly. The adverse pressure gradient on the blade suction surface of modified blade geometry is reduced. The flow separation is controlled and mass flow，total pressure ratio and adiabatic efficiency of compressor is improved by 0.7%，2.2% and 1.0%，respectively，which demonstrated the effectiveness and accuracy of present inverse design method.

Key words: Inverse design method；Axial compressor；Inverse boundary condition；Pressure distribution