A control scheme of satisfying different inlet distortions was proposed for turbofan engine. The turbofan-engine performance was improved by increasing the pressure ratio under low inlet distortion conditions

and the pressure ratio was reduced with addition of guide vane adjustment to provide additional stall protection at high inlet distortion. By using the differential evolution algorithm with border buffer zone(DEBZ)

the control scheme of the turbofan engine pressure ratio and variable guide vanes in envelope was optimized and obtained according to the requirements of stall margin with different inlet distortions. The simulation over full envelope was accomplished with the model

control algorithm and control scheme. Using the proposed control scheme

the simulation results show that thrust performance of turbofan engine can be improved more than 8% when the distortion index is 2

and the stall margin requirements can be satisfied when the distortion index is 8 with more than 1% thrust performance improvement.