タービン周方向翼力に及ぼす境界層フェンスの効果

概要

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Boundary layer fences were attached to end walls of a linear turbine rotor cascade, in order to increase the circumferential component of the aerodynamic blade force. Measurements were taken of the static pressure distribution on the channel-confining surface, for different heights and pitchwise locations of the fences. The pressure distribution correlated well with the secondary flow pattern visualized by the surface oil flow method. The fences diminished effectively the crossflow-induced local pressure rise in the tip region of the blade suction surface, but decreased the passage-vortex-induced local pressure drop also on the suction surface. The fences were most effective if they were 1/3 of the inlet boundary layer thickness high from the end wall and located half a pitch away from the blades, reducing the thickness of the force defect at the blade tip by 40 percent.
社団法人日本機械学会の論文
1989-08-25