Multi-objective optimization of three-dimensional blade shape for an axial compressor rotor in transonic stage

Abstract

A three-dimensional (3D) blade design method for an axial compressor transonic stage to optimize the aerodynamic performance is presented in this paper. The blade is defined by three profiles and a radial stacking line. Each profile is a multi circular arc (MCA), and the stacking line is defined as a B-spline curve with six design parameters. To ensure the off-design performance, a multi-objective genetic algorithm (MOGA) is applied. The objective functions are the efficiency, shock position and leading edge pressure difference at the design point. Because shock position and leading edge pressure difference can evaluate the potential for stalling, the method can generate blades with a wide operating range with just one performance prediction. This method is applied in a transonic blade design. The result shows that the efficiency of the optimized blade at the design point is increased and the operation range is expanded compared with the original blade. Copyright © 2013 Gas Turbine Society of Japan.