遷音速軸流圧縮機動翼列における衝撃波を伴う乱流場のWall-Resolved LES解析

DOI

書誌事項

タイトル別名
  • Wall-Resolved LES Analysis of Turbulent Flow Field with Shock Wave in a Transonic Axial Compressor Rotor

抄録

<p>A large-scale Wall-Resolved Large Eddy Simulation（WRLES）has been conducted for a transonic axial compressor rotor, NASA Rotor 37. By using a very fine computational grid of 1.35 billion points for a single passage and a high resolution scheme based on a 6th-order compact interpolation, the fine scale eddies in the turbulent boundary layer were resolved, and the interaction between the shock wave and the blade boundary layer, and the boundary layer separation due to the shock wave interaction were clearly captured. The WRLES results of the total pressure distribution at the rotor exit was in good agreement with the experimental results, and the pressure deficit on the hub side was well captured in the WRLES results. The total pressure on the shroud side was slightly overestimated in the WRLES results, which is due to an underestimation of the tip leakage vortex and its associated flow loss.</p>

収録刊行物

  • ターボ機械

    ターボ機械 49 (3), 177-187, 2021

    一般社団法人 ターボ機械協会

キーワード

詳細情報 詳細情報について

  • CRID
    1390573242484703104
  • DOI
    10.11458/tsj.49.3_177
  • ISSN
    18802338
    03858839
  • 本文言語コード
    ja
  • データソース種別
    • JaLC
  • 抄録ライセンスフラグ
    使用不可

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