Application of genetic algorithm to multi-stage compressor aerodynamic optimization design

A multi-objective aerodynamic optimization method is developed using genetic algorithm and duct-flow code that employs streamline curvature approach. Velocity circulations at the trailing edges of each blade-row are optimized for overall maximization of total pressure ratio and isentropic efficiency. The test indicates that the optimization algorithms can auto-search for optimal result globally and efficiently. A five-stage high pressure compressor is redesigned by using this method and the performance is enhanced greatly.