关键词: 跨声速压气机;压气机叶栅;粘性流;数值计算

Abstract: A new numerical method for solving viscous inverse problem of transonic compressor cascades was developed.The calculation was performed directly on the physical plane by simplified Navier Stokes equations which were solved by time marching,finite volume method.This technique can be used to design the blade profile with prescribed dimensionless velocity distribution at the suction and pressure surface.Depending on comparing the aimed velocity distribution with the calculated velocity distribution,the new blade was obtained by modifying the blade profile shape.The turbulence eddy viscosity was simulated by B L model and region time steps with the multigrid techniques being used in the code in order to accelerate the convergence.Computed results of shock free supercritical cascade were presented

Key words: Transonic compressor;Compressor cascade;Viscous flow;Numerical calculation