超音速燃焼飛行試験に用いる燃焼器流路形状の検討

機関リポジトリ

書誌事項

タイトル別名
  • Flow-path Design of a Combustor Model for a Supersonic-combustion Flight Experiment

抄録

第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京

51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan

A flight-ground test comparison program is undergoing at JAXA to reveal so-called facility effects on hypersonic aerodynamics and combustion phenomena. The flight test vehicle will mount a combustor duct along its centerline, with so-called alligator type inlet with side-spillage to attain good starting characteristics. In the present paper, parametric study on flow-path design of the combustor model was conducted by CFD to examine influences of the geometry parameters, such as configurations of fuel injector holes and geometry of a flame-holding cavity, on combustion characteristics and to settle the design guideline which could enhance so-called vitiation effects on combustion. A two-staged fuel injection scheme was adopted for the combustor model and the first-stage and second-stage injection holes were installed at upstream and downstream of the flame-holding cavity, respectively. The results showed that a distance between the first-stage injection hole and the flame-holding cavity as well as the number of the injector holes at each stage would have strong influence on the combustor flow-field and its characteristics while the depth of the flame-holding cavity would have little influence.

形態: カラー図版あり

Physical characteristics: Original contains color illustrations

資料番号: AA1930011013

レポート番号: JAXA-SP-19-007

収録刊行物

詳細情報 詳細情報について

  • CRID
    1050855511214937856
  • NII論文ID
    120006839154
  • ISSN
    24332232
  • Web Site
    http://id.nii.ac.jp/1696/00046343/
  • 本文言語コード
    ja
  • 資料種別
    conference paper
  • データソース種別
    • IRDB
    • CiNii Articles

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