B-15 圧縮機翼列の失速特性に及ぼす壁面コンターリングの効果(空力III,一般講演)

概要

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In order to investigate the mechanism of casing treatment effect, numerical study was carried out on a transonic compressor rotor with different configurations of circumferentially grooved (contoured) endwalls. The result showed the wall contouring above the blade leading edge had stall margin improvement effect with insignificant efficiency deterioration. By applying the second invariant Q, two major vortex structures were observed near the stall conditions. One was tip leakage vortex and the other was, probably, rotating instability vortex. The rotating instability vortex seemed to be generated by the interaction between the inflow and the reverse flow induced by shock - leakage vortex interaction near the endwall. In the case with wall contouring, enlarged clearance gap enhanced the tip clearance flow and relieved the interaction that caused the rotating instability vortex. The rotating stall onset was thereby delayed.
公益社団法人日本ガスタービン学会の論文
2007-09-01