周方向単一溝型ケーシングトリートメントが遷音速圧縮機に及ぼす影響 : 第2報:翼端流れ場の変化と失速抑制効果のメカニズム

概要

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The effect of circumferential single grooved casing treatment on the stability enhancement of NASA Rotor 37 has been examined with CFD analysis. Based on the assumption that the onset of stall in Rotor 37 is initiated by accumulation of blockage flow in the tip region, the effect of circumferential groove on near tip flow field was observed in detail. The reduction of local blade loading and the radial transportation of passage fluid were the primary effects of the groove, which lead to the change in momentum and flow angle of the tip leakage flow. The extent of these changes showed a clear correlation with the groove depth and the local blade loading at the groove location. The result of parametric study on the location and the depth of the groove showed that the stall margin can be improved most effectively by placing the groove 20% axial chord width down stream from the leading edge. This was due to the deflection of tip leakage vortex trajectory caused by attenuation of leakage flow.
公益社団法人日本ガスタービン学会の論文
2014-05-20