Cylindrical rotating detonation engine cooling by means of propellant injection

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

研究成果: Conference contribution

抄録

An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested and demonstrated. Thrust measurement of the cylindrical RDE (24-mm-diameter) was conducted with monitoring K-type thermocouples inserted in combustor wall. Single rotating detonation wave was observed in the testing conditions ranging from 31 to 59 g/s in this study. Combustion tests for 4.0 ~ 4.9 s were successfully done, and all injector side wall temperature increases were suppressed compared to that of combustor base plate, which had no cooling structure. This could be due to the cooling effect by the heat exchange of propellant injection. In the 4.9 s combustion test with 31 g/s, all thermocouples inserted in the combustor side wall which had the propellant injector surface showed a temperature decreasing 2.5 s after ignition even though the combustion was continuing, and implied the combustion mode shift.

本文言語English
ホスト出版物のタイトルAIAA Propulsion and Energy 2020 Forum
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ページ1-9
ページ数9
ISBN(印刷版)9781624106026
DOI
出版ステータスPublished - 2020
イベントAIAA Propulsion and Energy 2020 Forum - Virtual, Online
継続期間: 2020 8 242020 8 28

出版物シリーズ

名前AIAA Propulsion and Energy 2020 Forum

Conference

ConferenceAIAA Propulsion and Energy 2020 Forum
CityVirtual, Online
Period20/8/2420/8/28

ASJC Scopus subject areas

  • Energy(all)
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

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