B-1 亜音速圧縮機動翼列流れの安定化に及ぼす前方スイープの効果(空力I,一般講演)

概要

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Compressor rotor flow modified by a forward sweep blade design is investigated at a blade Mach number of 0.35 through a rig experiment and an N-S analysis. The base radial blade is formed by a radial stacking of DCA profiles, and the stacking is shifted forward to form the swept blade with a 30 deg sweep angle at the tip. The throttle margin of 50% of the radial blade is increased to 65% by the sweep formation at a tip clearance of 0.5% of the blade chord. By increasing the clearance to 1%, the margin decreases by 7%. The numerical analysis reveals that an adverse pressure gradient caused by the sweep profile in the rear tip region of the suction surface interrupts radial surface flow to ascent toward the tip. Then, the main flow in the tip region is attached on the blade, and a stable flow is maintained even at the flow rate of radial blade stall. However, the interrupted surface flow forces to separate the main flow in the mid span range, so that the static pressurerise decreases toward the stall onset.
社団法人日本ガスタービン学会の論文
2004-10-01