高負荷軸流圧縮機翼背面/壁面コーナー流れに対する翼端隙間の効果(流体工学,流体機械)

概要

論文の詳細を見る
Strong adverse flows tend to occur in the suction surface/wall corner of high-load blade cascades of axial compressors. In a two-dimensional cascade wind tunnel test, effects of tip clearances on the cascade pressure coefficient Cp and flow structures in the corner were surveyed. Addition of a tip clearance was found to alter the flow conditions in the suction corner of axial compressor blade cascade. Tip clearance of 0.4mm for the test blade of chord length of 100mm in a typical high-load stator blade cascade increased the pressure coefficient Cp and lessened the corner loss coefficient compared with the cases with no clearance or with wider clearance. The issuing jet through the tip clearance of 0.4mm was found to have eliminated strong vortices in the corner zone. It suggests a very useful means of improving the axial compressor performances.
社団法人日本機械学会の論文
2004-10-25