Numerical simulation of the compressible transitional flow in a transonic compressor

This paper provides a numerical study of the flow through a transonic compressor cascade with transitional boundary layers, shock-induced separation and corner stall. The aim of the present work is to validate some state-of-the-art turbulence and transition models in complex flow configurations. The Reynolds-averaged Navier-Stokes equations for compressible flows, with an explicit algebraic stress model and k - ω turbulence closure, are solved. Such a turbulence model is combined with the Abu-Ghannam and Shaw transition model. The space discretization is based on a finite volume method with Roe's approximate Riemann solver and formally second-order-accurate MUSCL extrapolation with minmod limiter. Time integration is performed employing an explicit Runge- Kutta scheme with residual smoothing and multigrid acceleration. Numerical results are validated versus the experimental data available in the literature.