Mechanism and control of combustion-mode transition in a scramjet engine

Toshinori Kouchi, Goro Masuya, Tohru Mitani, Sadatake Tomioka

研究成果: Article査読

50 被引用数 (Scopus)

抄録

A sidewall compression scramjet engine operated in two combustion modes under Mach 6 flight condition, weakand intensive-combustion modes. The weak mode occurred below the overall fuel equivalence ratio (φ) of around 0.4. Transition from the weak mode to the intensive mode occurred at φ ∼ 0:4, accompanied by a sudden increase in thrust. Mechanisms of the transition were numerically investigated in this study. Simulations captured the sudden increase in thrust at the mode transition. In the weak mode, combustion occurred in only a region near the topwall where an igniter was installed. The combustion region expanded toward the cowl with boundary-layer separation at the mode transition. Simulations demonstrated that low ignition capability resulted in the weak mode. This study demonstrated that the presence of additional igniters on the sidewalls improved the ignition capability and achieved the intensive mode in the entire φ range.

本文言語English
ページ(範囲)106-112
ページ数7
ジャーナルJournal of Propulsion and Power
28
1
DOI
出版ステータスPublished - 2012

ASJC Scopus subject areas

  • 航空宇宙工学
  • 燃料技術
  • 機械工学
  • 宇宙惑星科学

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