小型円環翼列による超高負荷軸流タービンの空力性能に関する実験的研究 : 翼端間隙高さと翼形状の影響

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タイトル別名
  • EXPERIMENTAL STUDY ON AERODYNAMIC PERFORMANCE OF ULTRA-HIGHLY LOADED AXIAL TURBINE BY USING SMALL SIZED ANNULAR CASCADE : EFFECTS OF TIP CLEARANCE SIZE AND BLADE PROFILE

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説明

Raising the turbine blade loading by the increase of the blade turning angle can improve the aerodynamic performance of axial turbine which is the main part of the gas turbines. However, the increase of the blade turning angle intensifies the passage vortex and leakage vortex, and deteriorates the aerodynamic performance of axial turbine. Therefore, in order to develop a highly loaded axial turbine cascade, it is necessary to clarify the influences of the intensifications of the passage vortex and the tip leakage flow on the aerodynamic performance of turbine cascade. In this study, the aerodynamic performances of two types of UHLTC, Up and Down, with the turning angle of 160 degree were measured by using the small-sized turbine cascade test rig. Furthermore, the tip clearance size was set to 2% and 3% of the passage height. The experimental results showed that the Up-blade possessed the higher efficiency than the Down-blade because of the higher torque performance in spite of the higher loss generation. The reduction of the tip clearance size was more effective to enhance the efficiency because it could reduce the loss generation in addition to the increase of the torque performance.

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詳細情報 詳細情報について

  • CRID
    1390853650462609792
  • NII論文ID
    120007119684
  • NII書誌ID
    AA12677220
  • DOI
    10.15002/00023891
  • HANDLE
    10114/00023891
  • ISSN
    21879923
  • 本文言語コード
    ja
  • データソース種別
    • JaLC
    • IRDB
    • CiNii Articles
  • 抄録ライセンスフラグ
    使用可

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