The performance recovery control system of an aircraft engine was designed for deterioration compensation due to aging.The system switched among the conventional speed control mode

steady state performance recovery control mode and acceleration performance recovery control modes

based on the engine operation condition and healthy condition.Steady-state performance recovery control mode is an outer control loop added on the conventional speed control mode to recover the deteriorated engine performance through adaptive adjust engine compressor speed command at steady state.Acceleration of recovery control modes ensures the air stability of the engine and fully taps the potential of the engine by integrating conventional speed control and surge margin control.Simulation results of different states under different components deterioratation show the validity of the proposed system.