IGTC-122 Effect of Tip Clearance in Three-Dimensional Cascade Flow Analysis(Organized Session III TIP CLEARANCE FLOW)

  • Nozaki O.
    Thermofluid Dynamics Division, National Aerospace Laboratory
  • Kikuchi K.
    Thermofluid Dynamics Division, National Aerospace Laboratory
  • Tamura A.
    Thermofluid Dynamics Division, National Aerospace Laboratory
  • Shimizu K.
    Engine and Control Equipment Department, Mitsubishi Heavy Industries, Ltd.
  • Miyake Y.
    Engine and Control Equipment Department, Mitsubishi Heavy Industries, Ltd.
  • Watanabe T.
    Department of Aeronautics and Astronautics, University of Tokyo

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抄録

The three-dimensional transonic flow fields of a turbine stage have been analyzed by computational solutions of Navier-Stokes equations employing an implicit finite deference method with high accuracy upwind scheme. Numerical solutions were compared for different approaches to deal with tip clearance flow. Experimental data were also introduced for verifying the computation. The turbine stage model under consideration consists of inlet guide vanes and rotor blades. Two approaches were examined for dealing with the flow through tip clearance. These approaches have been applied to the turbine for a certain flow condition to evaluate the advantages of them. In this paper the numerical approaches are illustrated and discussed, comparing the resultant flow fields as well as over-all characteristics with experimental data.

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詳細情報 詳細情報について

  • CRID
    1573387452121914496
  • NII論文ID
    110006692056
  • NII書誌ID
    AA12007658
  • 本文言語コード
    en
  • データソース種別
    • CiNii Articles

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