Numerical simulation of the flow in the NASA low-speed centrifugal compressor

摘要

The performance of different low-Reynolds number turbulence models applied to the simulation of a flow in the NASA low-speed compressor is described. The flow solver utilizes a structured multiblock grid with Cartesian velocity components in a rotating coordinate system. The inviscid fluxes are calculated using Roe's scheme. An implicit solution method is applied and a multigrid cycling is used in order to accelerate the convergence. In this study the Baldwin-Lomax model, Chien's k - ε model and a full Reynolds-stress closure by Speziale et al. are applied. A detailed comparison between the experimental and computational velocity fields and pressure distributions is made.