End phenomena at axial compressor designing

Main results obtained by researchers of "Gas-turbine and Non-traditional Power Plants" Department of the Bauman Moscow State Technical University at the investigation of axial compressors for gas turbine engines, are presented. It is proposed to calculate the lag angle value of the stream at the vane cascade outlet by means of integral equations with allowance for blade shape. It is shown that the flow passage length of multistage axial compressor strongly depends on the choice of its stages’ dimensionless parameters.