Numerical design optimization of compressor blade based on ADOP

An aerodynamic design optimization platform(ADOP) has been developed.The numerical optimization method is based on genetic algorithm(GA),Pareto ranking and fitness sharing technique.The platform was used for design optimization of the stator of an advanced transonic stage to seek high adiabatic efficiency.The compressor stage efficiency is increased by 0.502% at optimal point and the stall margin is enlarged by nearly 1.0% at design rotating speed.The flow fields of the transonic stage were simulated with FINE/Turbo software package.The optimization result indicates that the optimization platform is effective in 3D numerical design optimization problems.

An aerodynamic design optimization platform （ADOP） has been develolped. The numerical optimization method is based on genetic algorithm （GA）, Pareto ranking and fitness sharing technique. The platform was used for design optimization of the stator of an advanced transonic stage to seek high adiabatic efficiency. The compressor stage efficiency is increased by 0. 502% at optimal point and the stall margin is enlarged by nearly 1.0 % at design rotating speed. The flow fields of the transonic stage were simulated with FINE/Turbo software package. The optimization result indicates that the optimization platform is effective in 3D numerical design optimization problems.