Based on artificial neural network and genetic algorithms

the aerodynamic optimization of stacking curve for a low-speed compressor rotor was implemented by controlling circumferential vorticity.The adiabatic efficiency under small flow rate condition was optimized.The numerical results show that the distribution of circumferential vorticity at the exit of rotor is improved

the adiabatic efficiency under small flow rate zone is enhanced

and the stall margin is greatly increased.The optimization approach have high efficiency

and can provide a ordered flow field for compressor.