A-15 回転動翼プラットフォームにおけるフィルム冷却に関する研究(伝熱,一般講演)

書誌事項

タイトル別名
  • A-15 Study on Film Cooling for a Rotating Turbine Blade Platform

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Film cooling effectiveness on a rotating turbine blade platform have been studied by using a Low-Speed Research Turbine (LSRT) facility. The turbine model airfoils applied to LSRT were high loaded type suitable for next generation industrial gas turbines. The measurements of film cooling effectiveness on the platform have been conducted with pressure sensitive paint (PSP) technique. The horseshoe vortex, the passage vortex and the flow near the leading edge strongly influence film cooling around the inlet on the platform. They cause the decrease of film cooling effectiveness. Film cooling characteristic at the intermediate region is different from that around the outlet. Blowing ratio providing comparatively high performance is 1.0 in these two region. The useful information to attain high performance cooling design for high reliability turbine blades has been obtained.

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詳細情報

  • CRID
    1572824501872180608
  • NII論文ID
    110008901740
  • NII書誌ID
    AN10255898
  • ISSN
    09191941
  • 本文言語コード
    ja
  • データソース種別
    • CiNii Articles

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