Assessment of Aerodynamic Performance of Ultra-Highly Loaded Axial Turbine by Using Small Sized Wind Tunnel for Annular Cascade

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Other Title
  • 小型円環翼列風洞による超高負荷軸流タービンの空力性能評価
  • 小型円環翼列風洞による超高負荷軸流タービンの空力性能評価 : 翼端間隙高さの影響
  • コガタエンカンヨクレツ フウドウ ニ ヨル チョウコウフカジクリュウ タービン ノ クウリキ セイノウ ヒョウカ : ヨク タン カンゲキ タカサ ノ エイキョウ
  • (Effects of Tip Clearance Size)
  • (翼端間隙高さの影響)

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Description

<p>The increase of turbine blade loading by increasing turning angle is one of the effective methods to improve the aerodynamic performance of gas turbine, which makes it possible to reduce the number of blades and stages. As a consequence, the decreases of both the weights and the costs for manufacturing and for maintenance can be realized. However, the secondary losses caused by the passage and the tip leakage vortices are inevitably increased due to the increase of the pitchwise pressure gradient.</p><p>This study aims to investigate the effects of tip clearance size on the aerodynamic performance of an ultra-highly loaded turbine cascade (UHLTC) with the turning angle of 160 degrees by using a small sized wind tunnel for annular cascades. The experimental results showed that the decrease of the size of tip clearance resulted in the enhancement of the turbine efficiency due to the reduction of aerodynamic loss.</p>

Journal

  • Turbomachinery

    Turbomachinery 48 (6), 345-351, 2020

    Turbomachinery Society of Japan

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