Numerical investigations on effects of inlet boundary layer characteristics on aspirated compressor cascade

Effects of inlet boundary layer characteristics on aerodynamic performance of an aspirated compressor cascade are investigated by numerical simulation under the condition of low-speed. Schemes which has the characteristics of different boundary layer thicknesses are designed at various positive attack angles. Distribution of outlet aerodynamic parameters and three-dimensional flow field structures are comparatively analyzed. Meanwhile, under the condition of different inlet boundary layer characteristics, the effects of boundary layer suction on a compressor cascade are discussed. Numerical results indicate that the numerical simulation results and experimental results show a good consistency. An increase in boundary layer thickness could enhance the characteristic of three-dimensional in corner region and the change of the attack angle had a stronger influence on performance degradation. The transverse impact of secondary flow and an increase in the scope of corner region led boundary layer suction to a weakened effect. When the inlet flow boundary layer thickness increases, the increase of suction flow rate can effectively reduce the loss of strong aspirared compressor cascade. Thus, when the attack angle changes, the stability of cascade performance gets improved.