| Co-Investigator(Kenkyū-buntansha) |
Matsuo Akiko 慶応義塾大学, 理工学部, 教授 (70276418)
Funaki Ikkoh 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 准教授 (50311171)
Nishioka Makihito 筑波大学, システム情報工学研究科, 教授 (70208148)
Sakakita Hajime 国立研究開発法人産業技術総合研究所, 研究グループ長 (90357088)
Maeda Shinichi 埼玉大学, 学内共同利用施設等, 助教 (60709319)
Matsuoka Ken 名古屋大学, 大学院工学研究科, 助教 (40710067)
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| Budget Amount *help |
¥46,410,000 (Direct Cost: ¥35,700,000、Indirect Cost: ¥10,710,000)
Fiscal Year 2015: ¥4,550,000 (Direct Cost: ¥3,500,000、Indirect Cost: ¥1,050,000)
Fiscal Year 2014: ¥8,970,000 (Direct Cost: ¥6,900,000、Indirect Cost: ¥2,070,000)
Fiscal Year 2013: ¥12,870,000 (Direct Cost: ¥9,900,000、Indirect Cost: ¥2,970,000)
Fiscal Year 2012: ¥20,020,000 (Direct Cost: ¥15,400,000、Indirect Cost: ¥4,620,000)
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| Outline of Final Research Achievements |
In the present study, we elucidated performance of rotating detonation engines experimentally and numerically. We made models for predicting the stabilization condition in which detonation waves can propagate in the rotating detonation engines. We also elucidated the mechanism of detonation generation and quench. In the two flat disc shaped rotating detonation engine, we show the whole structure of the flow field including injection, mixing of fuel and oxidizer. We discovered a new detonation wave (forward tilting detonation wave) in this disc shaped engine. By the two-dimensional computational fluid dynamics analysis, we elucidated the effect of injector shapes and burned gases on detonation waves. We successfully performed the flight test of a pulse detonation engine and the sled test of a rotating detonation engine.
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