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ID 56125
フルテキストURL
著者
Kouchi, Toshinori graduate school of Natural Science and Technology, Okayama University
Masuya, Goro Tohoku University
Mitani, Tohru Japan Aerospace Exploration Agency
Tomioka, Sadatake Japan Aerospace Exploration Agency
抄録
A sidewall compression scramjet engine operated in two combustion modes under Mach 6 flight condition, weak- and 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. Our 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. Our simulations demonstrated that low ignition capability resulted in the weak mode. We demonstrated that the presence of additional igniters on the sidewalls improved the ignition capability and achieved the intensive mode in the entire Φ range.
備考
This is an Accepted Manuscript of an article published by American Institute of Aeronautics and Astronautics
発行日
2012
出版物タイトル
Journal of Propulsion and Power
28巻
1号
出版者
American Institute of Aeronautics and Astronautics
開始ページ
106
終了ページ
112
ISSN
07484658
NCID
AA10459896
資料タイプ
学術雑誌論文
言語
English
OAI-PMH Set
岡山大学
論文のバージョン
author
DOI
Web of Sience KeyUT
関連URL
isVersionOf https://doi.org/10.2514/1.B34172