A-20 Numerical Analysis of Rectangular-to-Circular Transition S-shape Duct Flow

Bibliographic Information

Other Title
  • A-20 矩形-円形遷移S字ダクトにおける流れの数値解析(空力IV,一般講演)

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Description

The total pressure distortion of compressor inlet causes engine performance decrement or decreasing of surge margin. Because of the existence of secondary flow and flow separation, rectangular-to-circular transition S-shape duct was predicted to have distortion. Therefore designing method of a low distortion rectangular-to-circular transition S-shape duct is important. In this paper design parameter and design method of rectangular-to-circular transition S-shape duct was considered. Center line of top plane, bottom plane, side plane and cross-section area was selected as design parameter. And correlation between those parameter and distortion coefficient was gained from CFD of designed ducts. Flow separation leads low total pressure region. Therefor flow separation increase distortion. And supersonic flow causes total pressure loss. To decrease flow separation and supersonic flow region the curvature near the S-Duct exit should be small.

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Details 詳細情報について

  • CRID
    1573105976847776384
  • NII Article ID
    110008901589
  • NII Book ID
    AN10255898
  • ISSN
    09191941
  • Text Lang
    ja
  • Data Source
    • CiNii Articles

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