来流附面层对吸附式压气机叶栅影响的数值研究

数值研究低速条件下来流附面层特性对吸附式压气机叶栅气动性能的影响，在不同正冲角时，设计不同方案的附面层厚度分布，对比分析叶栅出口气动参数的分布以及叶栅内的三维流场结构，讨论不同来流附面层情况下在压气机叶栅中采用附面层吸除的效果。结果表明，数值模拟结果与试验数据有较好的一致性;附面层厚度的增加导致角区流动三维性增强，且变冲角性能下降，二次流横向作用和角区范围的增加使得附面层抽吸效果减弱;当来流附面层厚度增加时，通过增加抽吸量可以有效降低强吸附式压气机叶栅的损失，变冲角性能得到改善。

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.