Unsteady Behavior and Control of Diffuser Leading-Edge Vortex in a Centrifugal Compressor(Fluids Engineering)

  • GOTO Takashi
    Department of Applied Mechanics and Aerospace Engineering, Waseda University
  • OHTA Yutaka
    Department of Applied Mechanics and Aerospace Engineering, Waseda University
  • OUTA Eisuke
    早稲田大学

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Other Title
  • 遠心圧縮機ディフューザに発生する前縁渦の非定常挙動と制御(流体工学,流体機械)
  • 遠心圧縮機ディフューザに発生する前縁渦の非定常挙動と制御
  • エンシン アッシュクキ ディフューザ ニ ハッセイ スル ゼンエンウズ ノ ヒテイジョウ キョドウ ト セイギョ

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Abstract

The unsteady behavior of a vortex generated on the diffuser leading-edge, which is called the leading-edge vortex (LEV), is discussed through experiments and numerical simulation. The LEV is different from the separating vortex of the diffuser leading-edge and passage vortex of the diffuser, develops rapidly with a decrease in the compressor mass flow rate, and forms a flow blockage in diffuser passages. Therefore, the evolution of the LEV may become a cause of diffuser stall. Additionally, in one attempt to control the LEV, two types of tapered diffuser vanes, which are shroud- or hub-side tapered diffuser vanes, were adopted. Though the shroud-side tapered diffuser vane can effectively reduce the compressor noise level, the compressor performance deteriorates remarkably. On the other hand, the hub-side tapered diffuser vane not only reduces the compressor noise level but also improves the compressor performance. According to the visualization results of the oil-film methods and numerical simulations, the hub-side tapered diffuser vane can suppress the evolution of the LEV in the compressor low-flow-rate operation.

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