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

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Title of host publicationAIAA Propulsion and Energy Forum, 2021
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106118
DOIs
Publication statusPublished - 2021
EventAIAA Propulsion and Energy Forum, 2021 - Virtual, Online
Duration: 2021 Aug 92021 Aug 11

Publication series

NameAIAA Propulsion and Energy Forum, 2021

Conference

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

ASJC Scopus subject areas

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

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