| Citation: | MAO Xiaochen, JIAO Yingchen, YANG Zonghao. Effect of inlet boundary layer condition on the flow characteristics at endwall region of a compressor tandem cascade[J]. Journal of Aerospace Power, 2025, 40（3）：20220668 doi: 10.13224/j.cnki.jasp.20220668
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Inlet boundary layer (IBL) condition can make a significant effect on the flow condition in the compressors. In order to explore the effect of IBL condition on the flow characteristics at the endwall region of the highly loaded compressor tandem cascade, a steady numerical method was used to calculate the flow field of a high subsonic tandem cascade, and comparatively analyze the effects of different IBL conditions, including thickness and form (normal and skewed), on the corner separation and tip leakage flow characteristics. The results showed that: without tip clearance, increasing the IBL thickness could increase the three-dimensional corner separation range from the front blade and the circumferential range of the rear blade. The skewed IBL weakened the secondary flow in the front blade passage but enhanced the secondary flow in the rear blade passage, the total pressure loss decreased and the effect of the skewed IBL on corner flow was weakened with the increase of IBL thickness. With 1% blade height clearance, increasing the IBL thickness could increase the scale of the leakage vortex in spanwise direction and the skewed IBL could enhance the leakage vortex of the front blade but weaken the leakage vortex of the rear blade, the total pressure loss decreased but the effect of the skewed IBL on tip flow was enhanced with the increase of IBL thickness.
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