为了研究压气机在不同工作转速下失稳形式的不同,进而研究不同失稳先兆的发生机理,针对一台跨声速压气机在不同转速下的失稳过程进行了实验研究。分别在转子叶尖机匣、静子出口布置了高频响动态压力探针对压气机失稳过程进行实时监测和实验数据采集,采用FFT(Fast Fourier Transform)、WFT(Window Fourier Transform)、滤波等数据处理方法对实验数据进行频域和时域分析,得到了压气机在不同转速下流动失稳的变化规律。实验结果表明:随着工作转速的升高,该压气机的失稳过程也会发生改变,在低转速(亚声速)下表现为经典Spike引起的旋转失速,如65%设计转速;而在高转速(跨声速)下则表现为一种新型的失稳过程,由一种发生在近轮毂区域的低频、轴对称、大幅值的扰动诱导了失稳,如88%设计转速。这种失稳先兆被称为局部喘振。两种失稳模态之间的相互转换存在一个临界转速(约为78%设计转速),在临界转速下,局部喘振几乎与旋转失速同时发生。 In order to study the different forms of instability of compressors under different operating speeds and to study the mechanism of different instability precursors, an experimental study on the instability process of a transonic compressor at different rotational speeds was carried out. The high-frequency dynamic pressure probe is arranged at the rotor tip casing and the stator exit, respectively. The instability process of the compressor is monitored in real time and the experimental data are collected. FFT (Fast Fourier Transform), WFT (Window Fourier Transform) Data Processing Method The experimental data were analyzed in frequency and time domain, and the variation of the flow instability of the compressor at different rotational speeds was obtained. The experimental results show that as the working speed increases, the instability process of the compressor will also change. At low speed (subsonic speed), the performance of the classic Spike rotation stall, such as 65% design speed; while in the high Rotational speed (transonic speed) shows a new type of destabilization process, which induces instability by a low-frequency, axisymmetric, large-amplitude disturbance occurring near the hub region, such as a design speed of 88%. This destabilizing aura is known as local surge. There is a critical speed (about 78% of the design speed) between the two destabilizing modes, at which point the local surge occurs almost simultaneously with the spinning stall.