进口导叶角对叶根失稳压气机流动失稳的影响

A high-speed aero-compressor with different instability precursors was taken as the research object. The inlet guide vane was installed to manipulate the compressor inlet pre-swirl angle. Several dynamic pressure transducers were arranged to measure the whole instability evolutions. The instability precursor and the evolutions were observed under different inlet guide vane angles. The results showed that at negative inlet guide vane angle， the compressor instability was caused by the spike in the rotor tip region. At zero inlet guide vane angle and small positive inlet guide vane angle， the instability was induced by the partial surge in the stator hub region. Under the condition of large positive inlet guide vane angle， local instability occurred at stator hub first in the process of throttling， and led to complete compressor instability with further throttling in form of rotating stall cells at the tip. The analysis showed that the increase of the inlet guide vane angle adjusted the load distribution between the rotor and the stator by reducing the degree of reaction， thus causing the instability precursors to change from “spike at rotor-partial surge at stator-local instability at stator” as described above.