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

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

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
DOIs
Publication statusPublished - 2019 Jan 1
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: 2019 Jan 72019 Jan 11

Publication series

NameAIAA Scitech 2019 Forum

Conference

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

Fingerprint

Detonation
Demonstrations
Engines
Oxygen
Methane
Gases
Propellants
Combustors
Nozzles
Ethylene
Mass transfer
Vacuum
Geometry

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Goto, K., Yokoo, R., Kim, J., Kawasaki, A., Matsuoka, K., Kasahara, J., ... Uchiumi, M. (2019). Experimental performance validation of a rotating detonation engine toward a flight demonstration. In AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-1501

Experimental performance validation of a rotating detonation engine toward a flight demonstration. / Goto, Keisuke; Yokoo, Ryuya; Kim, Juhoe; Kawasaki, Akira; Matsuoka, Ken; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh; Nakata, Daisuke; Uchiumi, Masaharu.

AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (AIAA Scitech 2019 Forum).

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

Goto, K, Yokoo, R, Kim, J, Kawasaki, A, Matsuoka, K, Kasahara, J, Matsuo, A, Funaki, I, Nakata, D & Uchiumi, M 2019, Experimental performance validation of a rotating detonation engine toward a flight demonstration. in AIAA Scitech 2019 Forum. AIAA Scitech 2019 Forum, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Scitech Forum, 2019, San Diego, United States, 19/1/7. https://doi.org/10.2514/6.2019-1501
Goto K, Yokoo R, Kim J, Kawasaki A, Matsuoka K, Kasahara J et al. Experimental performance validation of a rotating detonation engine toward a flight demonstration. In AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA. 2019. (AIAA Scitech 2019 Forum). https://doi.org/10.2514/6.2019-1501
Goto, Keisuke ; Yokoo, Ryuya ; Kim, Juhoe ; Kawasaki, Akira ; Matsuoka, Ken ; Kasahara, Jiro ; Matsuo, Akiko ; Funaki, Ikkoh ; Nakata, Daisuke ; Uchiumi, Masaharu. / Experimental performance validation of a rotating detonation engine toward a flight demonstration. AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (AIAA Scitech 2019 Forum).
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