軸流回転翼列のケーシング境界層に及ぼす翼先端すきまの影響

概要

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The casing boundary layer flows behind an isolated axial compressor rotor with various tip clearances were measured under design and off-design conditions. The velocity distributions inside the boundary layer, measured by a slow-response 5-hole pressure probe, are closely related to the phase-locked flow pattern of a leakage vortex measured by a fast-response slanted hot-wire. As the vortex is stronger, the local efficiency of a blade element becomes higher near the casing wall, and becomes lower at the inner side of the vortex center. The integral parameters of the casing boundary layer were calculated to clarify the effect of the tip clearance on the boundary layer development. blade-tip efficiency is introduced by use of these parameters. There is no significant difference in the variation of the blade-tip efficiency with tip clearance between the design and the off-design condition, except an incipient stall condition.
社団法人日本機械学会の論文
1986-12-25