Study of combustion chamber characteristic length in rotating detonation engine with convergent-divergent nozzle

Yuichi Kato, Kazuki Ishihara, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

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

7 Citations (Scopus)

Abstract

A rotating detonation engine is an engine using continuous detonation in an annular combustor, and make thrust. Because detonation wave propagates in supersonic and in very small region, the combustor can be shortened. Programs in the combustor are high pressure loss when propellant is injected and necessity of cooling due to high heat flux. However, the physics of detonation combustion in an annular combustor is still not clear. Especially combustion efficiency, influence of injector shape of a rotating detonation combustor are not reported a lot. This paper reports measurement result of combustor stagnation pressure and influence of injector on characteristic velocity efficiency. Then convergent-divergent nozzle was used to increase thrust efficiency. In addition we measured temperature of the combustor and estimated heat flux.

Original languageEnglish
Title of host publication54th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-9
Number of pages9
ISBN (Print)9781624103933
Publication statusPublished - 2016
Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
Duration: 2016 Jan 42016 Jan 8

Other

Other54th AIAA Aerospace Sciences Meeting, 2016
CountryUnited States
CitySan Diego
Period16/1/416/1/8

ASJC Scopus subject areas

  • Aerospace Engineering

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  • Cite this

    Kato, Y., Ishihara, K., Matsuoka, K., Kasahara, J., Matsuo, A., & Funaki, I. (2016). Study of combustion chamber characteristic length in rotating detonation engine with convergent-divergent nozzle. In 54th AIAA Aerospace Sciences Meeting (pp. 1-9). American Institute of Aeronautics and Astronautics Inc, AIAA.