Boundary layer characteristics on rotor blades of transonic axial compressors

A detailed numerical investigation is undertaken to understand and quantify the development of boundary layer on rotor baldes of a transonic axial compressor. The theory is based on solution of the full Navier-Stokes equations for a viscous, compressible and unsteady flow, together with Reynolds stress turbulence modeling. Interaction of shock wave with boundary layer and the subsequent flow separation are simulated. Analeses are performed for different values of back pressures, incidences and freesteam turbulence intencities. Bounadry layer papremeters including displacement and momentum thicknesses, shape factor together with blockage and loss coefficients are calculated and discussed.