进口附面层厚度对弯叶片扩压叶栅损失的影响

THE EFFECTS OF INLET BOUNDARY LAYER THICKNESS ON THE LOSS OF CURVED BLADE COMPRESSOR CASCADE

本文通过人工加厚叶栅进口附面层厚度，考察了叶搬进口附面层厚度对弯叶片扩压叶栅损失的影响．实验结果表明，进口附面层厚度增加时，叶栅两端区二次流增强，叶栅损失增大．采用正弯曲叶片在参考进口附面层状态和人工加厚附面层时均未得到叶栅损失的降低，而反弯曲叶栅损失的降低出现在参考进口附面层状态下．

The effects of inlet boundary layer thickness on the secondary flow and the vortices of the curved blade compressor cascade are studied in this paper. The experimental results show that with the thickening of the inlet boundary layer the secondary loss increases and the movements of vortices enhance. No beneficial effects are gained under the condition of the positive curved blade in the reference and artificial thickened inlet boundary layers. A remarkable improvement for the negative curved blade is obtained with the reference inlet boundary layer.