タイトル | Supersonic Exhaust from a Rotating Detonation Engine with Throatless Diverging Channel |
DOI | https://doi.org/10.2514/1.J061300 |
本文(外部サイト) | https://nagoya.repo.nii.ac.jp/record/2003924/files/AIAAJournal_revision_without_correction_footnote_forRepository.pdf |
参考URL | https://nagoya.repo.nii.ac.jp/records/2003924 |
著者(英) | Nakata, Kotaro; Ota, Kosei; Ito, Shiro; Ishihara, Kazuki; Goto, Keisuke; Itouyama, Noboru; Watanabe, Hiroaki; Kawasaki, Akira; Matsuoka, Ken; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh; Higashino, Kazuyuki; Braun, James; Meyer, Terrence; Paniagua, Guillermo |
発行日 | 2022-07 |
発行機関など | American Institute of Aeronautics and Astronautics |
刊行物名 | AIAA Journal |
巻 | 60 |
号 | 7 |
開始ページ | 4015 |
終了ページ | 4023 |
言語 | eng |
抄録 | Converging–diverging nozzles are common in rocket engine systems to increase the exhaust velocity and improve thrust performance. In this study, we focused on the acceleration of subsonic burned gas without a structural throat via detonation to realize a simple and compact engine. We developed and tested a rotating detonation engine (RDE) without a throat and with a diverging channel (constant diverging angle α=5 deg). Gaseous C2H4 and O2 were used as the propellants, and the mass flow rate ranged from 62 to 134 g/s in the combustion tests under low back-pressure conditions. We measured pressure and thrust, as well as high-speed imaging of self-luminescence of the combustion and imaging of the exhaust plume. The pressure at the exit was less than one-fifth of the maximum pressure in the RDE, significantly below the value for a sonic flow. The results suggested that the exhaust flow was supersonic, with values up to Mach 1.7, without the need of a converging section within the engine. In addition to the estimated Mach number from the measured pressure, the exhaust plume images coherently indicated the existence of supersonic exhaust. |
URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/1223676 |
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