A-18 前方スイープ圧縮機動翼の亜音速流れ構造に及ぼす運転速度の影響(空力III,一般講演)

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The throttle margin of a forward swept blade rotor (swept blade) is considerably higher than that of a radially stacked blade (radial blade) in a low subsonic operation of M_<b,tip>≈0.3 at the rotating speed of 6000 rpm. Through a CFD study, tip leakage flow loss that is a major factor for rotating stall onset is found rather weak in compared with the loss in the radial blade. However in the blade mid span region, a significant loss is generated by a flow separation which is caused by retarded low energy hub flow streaming upward along the suction surface. Such increased mid span loss is particular to the forward sweep profile and leads a disadvantage of a static pressure decrease as the stall point is reached The CFD analysis is conducted for a high subsonic case of M_<b,tip>≈0.7 at the rotating speed of 13000 rpm. At the design flow operation, the hub flow extends closer to the tip region than the low speed hub flow, but interaction with the tip leakage vortex does not take place. Compatibly with the passage contraction, axial flow velocity becomes almost unchanged through the blade, and the pressure-rise exceedes over the low subsonic case. At a low flow operation of the radial blade rotor, interaction between the hub flow and intensified tip leakage vortex becomes significant inducing a high loss in the tip region. In case of the swept blade, the hub flow induces a heavy separation of the suction surface flow constituting a lateral vortex in the main flow. However, the tip leakage vortex is still disunited from the hub flow and the tip flow reversal still remains in a moderate level.
公益社団法人日本ガスタービン学会の論文
2006-10-01

A-18 前方スイープ圧縮機動翼の亜音速流れ構造に及ぼす運転速度の影響(空力III,一般講演)

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