The boundary layer equations with accounting for rotation and variation of stream filament thickness on the Sl stream surface of revolution in turbomachinery are derived in this paper. A method is presented for calculating laminar, turbulent and wake boundary layers by means of solving the integral momentum equation. The turbulent boundary layer with separation also can be calculated by use of present method.
The prediction of the boundary layer on the cascade blade of the DFVLR transonic axial compressor rotor was carried out in this paper. The effects of rotation and variation of stream filament thickness on the predicted behavior of the boundary layer are carefully investigated. It is shown that in certain cases their effects on the predicted results are significant.
