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
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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.
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備考 | This is an Accepted Manuscript of an article published by American Institute of Aeronautics and Astronautics
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発行日 | 2012
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出版物タイトル |
Journal of Propulsion and Power
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巻 | 28巻
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号 | 1号
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出版者 | American Institute of Aeronautics and Astronautics
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開始ページ | 106
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終了ページ | 112
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ISSN | 07484658
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NCID | AA10459896
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資料タイプ |
学術雑誌論文
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言語 |
英語
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OAI-PMH Set |
岡山大学
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論文のバージョン | author
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DOI | |
Web of Science KeyUT | |
関連URL | isVersionOf https://doi.org/10.2514/1.B34172
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