Compressor Cascade Flow with Strong Shock-Wave/Boundary-Layer Interaction

Abstract

A two-dimensional multiblock Navier ‐Stokes solver has been successfully applied to a supersonic compressor cascade e ow with strong shock-wave/boundary-layer interaction. The cascade model investigated is typical of a fan blade section with precompression design, low e ow turning, and a static pressure ratio around 2.0. Numerical calculations have been performed on a very e ne grid to guarantee sufe cient resolution of the supersonic/transonic e owe eldwithacomplexwavepatternandshock-inducedboundary-layerseparation.Highaccuracyandrobustness of the numerical scheme is achieved by the second-order Roe upwind ‐total variation diminishing scheme and a one-equation turbulence model. Investigations were performed for inlet Mach numbers from 1.28 to 1.53 and a Reynolds number of 2 :6 ££ 106. The results are compared with those of previous experiments in a supersonic cascade wind tunnel that provide proe le Mach number distributions, wake traverse data, and measured suction surface boundary-layer proe les throughout the strong interaction region. Furthermore, calculated discontinuities of Mach number and e ow direction across the shock system at blade passage entrance are compared with laser anemometer data. Finally the ine uence of inlet Mach number and axial stream tube thickness variation on the shock-wave/boundary-layer interaction mechanism and blade performance is presented.