A problem of engine surge occurred in the process of one aero engine bed test.In order to find out the reason of the engine surge

a mathematical model of the variable stator vanes angle control system of the aero engine high pressure compressor (AHPC) was established

and then joint-simulations were done.Theory analysis and simulation results show that dynamic response delay of a temperature sensor induces the engine surge.Then a dynamic calibration system of this temperature sensor was designed to solve the engine surge problem.The validation simulation results show that the calibration system presented can obviously improve the dynamic response of AHPC’s variable stator vanes

and it can effectively prevent the engine surge without affecting the working of the aero engine.The temperature sensor calibration algorithm presented has a good adaptability and a strong anti-interference capability

and it can provide an important reference to solve the engine surge problem exposed in the aero engine bed test.