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

Toshinori Kouchi, Goro Masuya, Tohru Mitani, Sadatake Tomioka

Research output: Contribution to journalArticle

41 Citations (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)106-112
Number of pages7
JournalJournal of Propulsion and Power
Volume28
Issue number1
DOIs
Publication statusPublished - 2012

ASJC Scopus subject areas

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science

Fingerprint Dive into the research topics of 'Mechanism and control of combustion-mode transition in a scramjet engine'. Together they form a unique fingerprint.

  • Cite this