Transient state control of aero-engine based on active disturbance rejection control

A technique called active disturbance rejection control is proposed to realize the acceleration/deceleration process of aero-engine in a more flexible manner. According to the requirements of response time for acceleration/deceleration state, tracking differentiator is utilized to arrange the expected transition trajectories. An extended nonlinear state observer is introduced to estimate the rotor speed and its acceleration, as well as system disturbances. Based on this, a nonlinear PD controller is designed and added to the active disturbance rejection control algorithm, thus avoiding the integral saturation phenomenon. In addition, in order to ensure system safety and reliability, limit regulators are constructed with acceleration/deceleration schedule and values at steady state. Finally, comparisons between the proposed method and the traditional linear PI controller are conducted based on nonlinear model to show the effectiveness and flexibility of the proposed strategy. It is seen that our result can reduce the overshoot of turbine temperature and then extend its lifetime if fast response speed is not pursued.