Multi-Objective Aerodynamic Optimization Design Method of Compressor Rotor Based on Isight

Abstract

In order to achieving the multi-objective optimization of the compressor rotor blade, a hybrid optimization design algorithm was proposed. The algorithm included three parts: the design of experiment technology was applied to reduce the dimensions of the design variables; the response surface model was established according to the simulation data of the experiment design; the Non-Dominated Sorting in Genetic Algorithm was applied to acquire the multi-objective optimization solutions. In this study, NASA rotor37 was optimized for the maximization of the pressure ratio and adiabatic efficiency using the hybrid optimization algorithm. The result demonstrates that the optimization design method was effectively feasible.