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为了给各种压气机喘振主动控制器提供验证平台,提出了一个新的旋转失速及喘振模型.该模型在Moore-Greitzer轴流压气机过失速瞬态模型的基础上,考虑了转子动态及旋转失速高阶谐波对压气机气动稳定性的影响,并且在模型中增加了紧连阀作为执行机构.仿真结果表明:随着压气机转速的增加,压气机的失稳行为由旋转失速转为喘振;压气机转速的变化作为系统内部扰动,可能使压气机在节流阀开度较大时便进入气动失稳状态;虽然压气机初始扰动仅含有1阶谐波,但随着旋转失速的发展,高阶谐波强度不断增长而变得不可忽略.
In order to provide a verification platform for various active controllers of the surge compressor, a new model of rotating stall and surge is proposed. Based on the transient stall mode of Moore-Greitzer axial flow compressor, the rotor dynamic And rotating high order harmonics on the aerodynamic stability of the compressor, and in the model to increase the tight valve as the actuator.The simulation results show that: with the increase of the compressor speed, the compressor instability caused by the rotation stall To the surge; changes in compressor speed as a system disturbance, the compressor may enter the aerodynamic instability when the throttle opening is large; although the initial disturbance of the compressor contains only the first order harmonic, but with The development of rotational stall, the high-order harmonic intensity continues to grow and can not be ignored.