Research on flow instability of transonic compressor rotor and boundary suction effect at low Reynolds number

The flow instability of NASA Rotor 37 transonic compressor rotor at low Reynolds number was investigated by numerical simulation.The result shows that the boundary layer radial vortex becomes an important factor for causing compressor flow instability.It's found that the compressor stability range is obviously enlarged by suction on the blade suction surface at different blade heights and axial chords.The influence of suction mass on the characteristic of the compressor was also compared.