Integrated through-flow and blade shape design of multi-stage axial flow compressor

The core of multi-stage axial flow compressor aerodynamic design are S2 through-flow and blade design. In order to reduce its time cost and improve design efficiency, research develops a method of integrated through-flow and blade design of multi-stage axial flow compressor. Integrated design for compressor aerodynamic flow field parameters, blade geometry and connect with three-dimensional numerical simulation by coupling S2 through-flow and blade design, which can achieve target of fast initial design. Besides, by using this method to conduct inversing design six stage axial flow compressor of E3, and its resulting error of flow and adiabatic efficiency are below 2.5% compare to experimental value of E3 compressor. Result shows it has good engineering accuracy thus verifies its validity and practicality.