Numerical Analysis of Flow in Ultra Micro Centrifugal Compressor

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Other Title
  • 超小型遠心圧縮機内部流れの数値解析
  • 超小型遠心圧縮機内部流れの数値解析(子午面形状の影響)
  • チョウコガタ エンシン アッシュクキ ナイブ ナガレ ノ スウチ カイセキ シゴメンケイジョウ ノ エイキョウ
  • (Influence of Meridional Configuration)
  • (子午面形状の影響)

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Abstract

A single stage ultra micro centrifugal compressor constituting ultra micro gas turbine is required to operate at high rotational speed in order to achieve the pressure ratio which establishes the gas turbine cycle. As a consequence, the relative Mach number of the flow in the impeller passage increases and then the shock wave which causes the loss by the interaction with the boundary layer on the blade surface can be induced. In addition, the restriction of processing technology for the downsizing of impeller not only relatively enlarges the size of tip clearance but also makes it difficult to process the impeller with the three-dimensional blade. Therefore, it is important to establish the design technology for the impeller with two-dimensional blade which possesses the sufficient aerodynamic performance and enough strength to bear the centrifugal force caused by the high rotational speed. In this study, the flow in two types of impeller with the two-dimensional blade which have different meridional configuration was analyzed numerically. The computed results clarified the effects of the meridional configuration on the loss generation in the impeller passage.

Journal

  • Turbomachinery

    Turbomachinery 39 (6), 349-357, 2011

    Turbomachinery Society of Japan

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