Abstract: A Reynolds averaged Navier Stokes equation is solved for three dimensional flowfield inside a transonic compressor rotor,which has been experimentally investigated at the DFVLR.The numerical solution is based on implicit flux vector splitting scheme,and Baldwin Lomax turbulence model is used for the turbulence modeling.Based on the numerical results, the detailed flowfield structures,the secondary flows,and vortex development in the blade passage have been given.

Key words: three dimensional flow, turbulent models, flux vector splitting, compressor rotor transnic flow vortices