Application of 3D blading and non-axisymmetric endwall in a transonic compressor

In order to improve the aerodynamic performance of a transonic compressor rotor, based on three dimensional numerical simulation optimization platform, 3D blading and non-axisymmetric endwall contouring has been carried out successively on this rotor and changes of performance and flow field were compared and analyzed. The results show that both 3D blading and non-axisymmetric endwall contouring can improve the aerodynamic performance of the transonic compressor. On near design point, the isentropic efficiency increased by 0.75% after 3D blading optimization and further increased by 0.3% after non-axisymmetric endwall contouring optimization, meanwhile the off-design performance of the compressor has also been improved. 3D blading changes the position of shock wave in the blade channel, adjusts the load distribution along the radial span, and finally increases the isentropic efficiency of the compressor. Through changing the static pressure distribution at the hub, non-axisymmetric endwall weakens the intensity of shock wave near the hub, and makes it move backward, and thereby reduces the intensity of transverse secondary flow in the endwall region.