摘要
在某次某型航空发动机的地面台架试车中,该航空发动机发生了喘振.为查证导致发动机喘振的原因,构建了该型航空发动机高压压气机可调静子叶片转角控制系统的数学模型,完成了联合仿真.理论分析及仿真研究证明了:温度传感器动态响应特性滞后是导致发动机喘振的主要原因.为解决喘振问题,设计了该传感器的动态性能校正系统.验证仿真表明:所采用的校正方案可在不影响系统正常工作的前提下,明显改善该高压压气机可调静子叶片角度的动态响应特性,并有效地防止发动机喘振.该温度传感器校正算法具有适应性良好,抗干扰能力强等突出优点,可为解决试车过程中暴露的发动机喘振问题提供重要参考.
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 sta- tor vanes angle control system of the aero engine high pressure compressor （AHPC） was es- tablished, 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 effec- tively prevent the engine surge without affecting the working of the aero engine. The tem- perature sensor calibration algorithm presented has a good adaptability and a strong anti-in- terference capability, and it can provide an important reference to solve the engine surge problem exposed in the aero engine bed test.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第3期707-714,共8页
Journal of Aerospace Power
