Numerical experiments of scramjet combustion with boundary-layer bleeding

Toshinori Kouchi, Tohru Mitani, Masatoshi Kodera, Goro Masuya

研究成果: Conference contribution

5 被引用数 (Scopus)

抄録

Airframe-integrated scramjet engines swallow the boundary-layer which develops on the airframe of space planes. The scramjet engine easily falls into engine stall (engine unstart) due to the boundary-layer separation resulting from combustion. In this study, to investigate the unstart characteristics, numerical simulations of a scramjet engine with boundary-layer bleeding were performed using a reacting flow code which includes a one-equation turbulence model. This computation is calibrated by the experimental wall pressure distributions, heat fluxes and thrusts. The computation reproduces the prevention of engine unstart in the combustion tests with bleeding. Bleeding of 0.6% in a captured flow rate suppresses the flow separation and extends the start limit from the fuel equivalence ratio (φ) of 0.5 to 1.0. The computation at φ=1.0 shows that small-scale circular diffusion flames are anchored around individual fuel jets near the injectors. These structures disappear to form a large-scale envelope diffusion flame downstream of the combustor. The circular flames near the injectors account for 80% of the combustion efficiency and control the thrust performance.

本文言語English
ホスト出版物のタイトル12th AIAA International Space Planes and Hypersonic Systems and Technologies
出版ステータスPublished - 2003 12月 1
イベント12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003 - Norfolk, VA, United States
継続期間: 2003 12月 152003 12月 19

出版物シリーズ

名前12th AIAA International Space Planes and Hypersonic Systems and Technologies

Conference

Conference12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003
国/地域United States
CityNorfolk, VA
Period03/12/1503/12/19

ASJC Scopus subject areas

  • 宇宙惑星科学
  • 航空宇宙工学
  • 制御およびシステム工学

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