A-13 遠心圧縮機におけるディフューザ前縁渦の挙動と非定常流れ構造(空力III,一般講演)

概要

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Behavior of diffuser leading-edge vortex in a centrifugal compressor is investigated by both experiments and computational analyses. In centrifugal compressor with vaned diffuser, while high pressure-rise characteristics can be obtained, radiated noise level becomes larger and steady operating range becomes narrower. Therefore, understanding the complicated unsteady flow structure within diffuser passage is important not only for the noise reduction but for the compressor performance improvement. The leading-edge vortex exists stationary at the front part of the diffuser passage, and its scale becomes larger when the mass flow rate is decreased. Finally, enough grew-up vortex covers the diffuser inlet passage to form a passage blockage. This phenomenon may be one of the undiscovered incipient pattern of the diffuser rotating stall. The hub side tapered diffuser vane can disturb the growth of the leading-edge vortex and also can improve the surge margin of the compressor.
2008-10-01