Study of Cylindrical Rotating Detonation Engine with Propellant Injection Cooling System

Kosei Ota, Keisuke Goto, Noboru Itouyama, Hiroaki Watanabe, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

研究成果: Conference contribution

1 被引用数 (Scopus)

抄録

A cylindrical RDE with a propellant injection cooling system with an injector on the entire wall surface of the combustor has been tested and demonstrated. In this study, in order to search the optimum flow balance between the side and the bottom, the experiment was conducted under a total test condition of 30 g/s, and various balance condition. Under all conditions, a stable single rotating detonation was observed. In the 5.0-second combustion test, the temperature rise in the cooling area stopped and became steady state at a maximum of 850 K. This may be due to the heat exchange and film cooling effect of propellant injection. In addition, the propulsion performance was 94% of the theoretical value calculated assuming that the gas flow reached the speed of sound at the outlet of the combustor. It had been demonstrated that sufficient cooling and propulsion performance can be obtained by injecting 76% from the side wall and 24% from the bottom wall.

本文言語English
ホスト出版物のタイトルAIAA Propulsion and Energy Forum, 2021
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624106118
DOI
出版ステータスPublished - 2021
イベントAIAA Propulsion and Energy Forum, 2021 - Virtual, Online
継続期間: 2021 8月 92021 8月 11

出版物シリーズ

名前AIAA Propulsion and Energy Forum, 2021

Conference

ConferenceAIAA Propulsion and Energy Forum, 2021
CityVirtual, Online
Period21/8/921/8/11

ASJC Scopus subject areas

  • エネルギー(全般)
  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学
  • 機械工学

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