Weakening the conservativeness of the Min-Max control structure of aero-engine: a coordination function method based on safety margin

In order to solve the conservative problem of the existing Min-Max control structure, this paper proposes a coordination function method based on safety margin to give full play to the engine’s potential in output response. By defining the concept of safety margin, the coordination relationship between the performance and limit protection parameters in the transition process is analyzed, and the conservatism is described indirectly. Firstly, the concept of safety margin is given. Then, the influence of performance parameters on the safety margin of each limit protection parameter is analyzed. Finally, a coordination function method based on safety margin is designed and proposed. The basic idea of this method is to judge the safety margin of the engine limit protection parameters by improving the existing Min-Max control structure and using the coordination function to guide the linear controller of each limit protection parameter to change the control gain and control the current working state of the aero-engine. The simulation results show that this method can reduce the conservatism of the existing Min-Max control structure, improve the response speed of the fan speed, ensure that the aero-engine has a higher thrust response speed, and optimize the transition state performance of the aero-engine under the condition that the engine limit protection parameters are not exceeded.