LES of turbulent channel flow with pressure gradient corresponding to turbomachinery conditions

Abstract

A converging–diverging channel flow with the geometry corresponding to the blade channel of axial compressor has been simulated using Large-Eddy- Simulation (LES) for the inlet Reynolds number based on the friction velocity equal to Reτ = 395. The channel geometry causes the existence of the adverse pressure gradient which induces the boundary separation. Both the influence of the mesh spacing and the subgrid scale models (SGS) have been investigated. Two SGS model have been considered: the Wall Adapting Local Eddy-Viscosity and the Smagorinsky with the dumping function.