Experimental performance validation of a rotating detonation engine toward a flight demonstration

Keisuke Goto, Ryuya Yokoo, Juhoe Kim, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki, Daisuke Nakata, Masaharu Uchiumi

研究成果: Conference contribution

4 被引用数 (Scopus)

抄録

Thrust measurements of rotating detonation engine of (1) ethylene / gas-oxygen and (2) methane / gas-oxygen with various throat geometries in a vacuum chamber to simulate different back-pressure conditions ranging from 1.1-104 kPa were conducted. For throatless rotating detonation engine, we defined equivalent throat area as the detonation channel area, and then tested four nozzle contraction ratios of 1, 1.5, 2.5, and 8. Engines could be successfully ignited by electric ignitors when initial pressure was high enough to have, at least, one detonation cell in RDE channel. We measured the combustor pressure and reveled that it was almost proportional to the throat mass flux regardless of contraction ratios and the propellant combinations. The specific impulse of methane / gas-oxygen case could achieve 84 ± 1% of ideal specific impulse at the optimum expansion for each back pressure.

本文言語English
ホスト出版物のタイトルAIAA Scitech 2019 Forum
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624105784
DOI
出版ステータスPublished - 2019
イベントAIAA Scitech Forum, 2019 - San Diego, United States
継続期間: 2019 1 72019 1 11

出版物シリーズ

名前AIAA Scitech 2019 Forum

Conference

ConferenceAIAA Scitech Forum, 2019
CountryUnited States
CitySan Diego
Period19/1/719/1/11

ASJC Scopus subject areas

  • Aerospace Engineering

フィンガープリント 「Experimental performance validation of a rotating detonation engine toward a flight demonstration」の研究トピックを掘り下げます。これらがまとまってユニークなフィンガープリントを構成します。

引用スタイル