A-15 軸流圧縮機動翼列の内部流れ場に及ぼす後置静翼の影響に関する数値解析(空力III,一般講演)

概要

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The purpose of this study is to investigate the effect of downstream stator on a stall event in a ow-speed axial compressor. Unsteady RANS (Reynolds-Averaged Navier-Stokes) simulations were performed for the compressor with isolated rotor and stage conditions. The simulation showed that in the rotor passage a separate vortex from the tip leakage vortex occurred periodically near the casing wall prior to the stall and caused the unsteadiness of the tip clearance flow field. The flow in the vortex core rotated in the counter direction to that in the tip leakage vortex. That vortex has similar features to the "induced vortex", which was observed in the spike-type rotating stall inception. At near-stall condition, the boundary layer separation happened on the suction surface of the stator blade as well as the rotor blade, but that separation might not have much effect on the stall inception, because it was far away from the rotating stall started from the leading edge separation in the rotor.
2008-10-01