Numerical Investigation of Rotating Detonation Engine with Injection from the Combustor Side Wall

Takumi Sada, Akiko Matsuo, Eiji Shima, Hiroaki Watanabe, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara

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

Abstract

Numerical analysis of cylindrical rotating detonation engine (RDE) with injectors on the combustor side wall is conducted using the stoichiometric H2-Air premixed gas. The combustor is 70 mm in length and 20 mm in diameter. The results are compared to the conventional injector configuration, which has injectors on the combustor bottom, and the combustion features with side injection are investigated. The instantaneous pressure and temperature fields show the characteristics of propagating waves are different depending on the injector configuration. From the spatiotemporal average profiles, the combustion occurs more rapidly in the case of injection from the bottom. However, the case of injection from the side wall also shows the consumption of fuel. Compared to the theoretical values, the specific impulse is 106 % from the bottom and 103 % from the side. In this combustor length, both injection conditions can provide similar thrust performance to the theoretical values.

Original languageEnglish
Title of host publicationAIAA AVIATION 2022 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106354
DOIs
Publication statusPublished - 2022
EventAIAA AVIATION 2022 Forum - Chicago, United States
Duration: 2022 Jun 272022 Jul 1

Publication series

NameAIAA AVIATION 2022 Forum

Conference

ConferenceAIAA AVIATION 2022 Forum
Country/TerritoryUnited States
CityChicago
Period22/6/2722/7/1

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Nuclear Energy and Engineering
  • Aerospace Engineering

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