G607 軸流圧縮機動翼列の旋回失速発生時におけるはく離流れの非定常三次元挙動(2)(GS-6-2 翼干渉,フィン,境界層,一般セッション)

概要

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Recently, it had been clarified that the flow field in an axial flow compressor rotor at rotating stall consists of a tornado-type separation vortex linking from the blade suction surface to the casing wall. In the present work, unsteady three dimensional flow behavior of separated flow at rotating stall has been investigated by large-scale unsteady RANS (Reynolds-averaged Navier-Stokes) simulations. The results show clearly the rotating stall propagation process, which is different from the guess in the past experimental work that a similar separation vortex must revolve stably in the rotor. It has been found that the separation vortex causes a leading edge separation at following blade due to the large blockage effect and the new separation vortex propagates at the blade passage again.
2006-10-28