小尺寸多级轴流压气机级间干扰现象试验

The dynamic pressure signals were measured and analyzed by the Kulite transducers and the fast response pressure probes to investigate the rotor-stator interaction phenomenon in small multistage axial compressor. Results indicated that, at higher rotor speed, the 1st rotor tip flow-field agreed well with the typical supersonic-cascade flow features, and only the flow-field at the 1st rotor trailing-edge was disturbed by the rotor-stator interactions. However, at lower rotor speed, the rotor-stator interaction obviously increased in intensity and appeared at the 1st rotor leading-edge with the compressor throttling. Modal analysis was carried out for these frequency components of rotor-stator interactions, and then the propagation speed and modal number were obtained finally.