Numerical Calculations of the Viscous Flow in a Supersonic Compressor Cascade with Splitter Vanes.

摘要

A numerical method has been developed to solve the steady, three-dimensional Reynolds-averaged Navier-Stokes equations by iteration. The computer code which embodies the method was employed to calculate the viscous flow field about an axial compressor cascade at a freestream Mach number of 1.46 and a freestream Reynolds number based on chord of 1.36 million. The cascade geometry contained splitter vanes and contoured sidewalls to simulate the flow in the streamtube of an axial compressor rotor. A strong shock wave boundary layer interaction, with strong separation, was computed on the suction surface of the main cascade blade. This interaction region distorted the cascade flow field and resulted in high system losses. Measurements of static pressure on the main cascade blade and splitter vane compared favorably with corresponding computed static pressures. In addition measurements of the mass averaged static pressure and Mach number in the wake of the cascade agreed with corresponding computed mass averaged quantities. (Author)