IGTC-59 Effect of Three-Dimensional Flow Field on Heat Transfer Problems of a Low Aspect Ratio Turbine Nozzle(Session B-5 BLADE HEAT TRANSFER AND HEAT EXCHANGER)

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概要

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• Heat Transfer distribution and film cooling effectiveness on the endwall, suction and pressure surfaces of an airfoil were studied by using a full annular, low aspect h/c=0.5 vane cascade. Film cooling effectiveness at airfoil midspan of annular cascade was compaired with previous two dimensional cascade test results. The predominant effect of horseshoe vortex and secondary flow on the heat transfer and the film cooling of the vane surface and the endwall were clearly demonstrated by the measured heat transfer and the film cooling distribution. In this paper discusses the effect of three dimensional flow on the heat transfer of the low aspect annular vane.

• 公益社団法人日本ガスタービン学会の論文

著者

• Sato T.

  Takasago Technical Institute, Mitsubishi Heavy Industries Co., Ltd.

• Matsuura M.

  Takasago Technical Institute, Mitsubishi Heavy Industries Co., Ltd.

• Aoki S.

  Takasago Technical Institute, Mitsubishi Heavy Industries, Ltd.

• Takeishi K.

  Takasago Research And Development Center Mitsubishi Heavy Industries Ltd.

• Matsuura M

  Yamaguchi Univ. Ube Jpn

関連論文

• IGTC-8 COOLING CHARACTERISTICS OF AIR COOLED RADIAL TURBINE BLADES
• IGTC-8 COOLING CHARACTERISTICS OF AIR COOLED RADIAL TURBINE BLADES(Session A-3 Heat Transfer III (Internal Surface))
• IGTC-87 DEVELOPMENT OF POWER TURBINE FOR VEHICULAR GAS TURBINE(Session C-1 Vehicular Gas Turbine I)
• IGTC-59 Effect of Three-Dimensional Flow Field on Heat Transfer Problems of a Low Aspect Ratio Turbine Nozzle(Session B-5 BLADE HEAT TRANSFER AND HEAT EXCHANGER)
• IGTC-42 Three Dimensional Inviscid and Viscous Flow Field Analysis of Low Solidity Annular Turbine Nozzle(Session A-13 COMPUTATIONAL AERODYNAMICS IV)

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