Propulsion performance of inner-cylinder-less rotating detonation engine

Ryuya Yokoo, Kesisuke Goto, Juhoe Kim, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

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

1 Citation (Scopus)

Abstract

We evaluated the propulsion performance of a nozzle-less, inner-cylinder-less rotating detonation engine (RDE). For a C2H4–O2 mixture, the RDE was tested in a low-back-pressure environment at several propellant mass flow rates ranging from 8 to 45 g/s. In high-speed imaging of the self-luminescence within the combustor, rotating luminous regions were observed at a mass flow rates greater than 22 g/s. The specific impulse efficiency was greater than 80% for all the mass flow rate, and approximately 90% in some cases, which is comparable with ones in conventional RDEs having inner cylinders. By the control surface analysis, it was clarified that propellants injection from the injector holes and pressure on the bottom of the combustion chamber account for the thrust. It was also suggested that the design of the outer cylinder of the combustion chamber and the injector arrangement may affect the thrust performance. Axial Mach number distributions within the engine were calculated under an assumption of isentropic expansion. As a result, the burned gas reached a sonic or supersonic velocity at the outlet of the combustion chamber. Axial pressure distributions also suggested that the acceleration of the burned gas was completed at a far-upstream region within the combustion chamber.

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
Engine cylinders
Combustion chambers
Propulsion
Engines
Flow rate
Propellants
Control surfaces
Surface analysis
Combustors
Gases
Pressure distribution
Mach number
Luminescence
Nozzles
Imaging techniques

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Yokoo, R., Goto, K., Kim, J., Kawasaki, A., Matsuoka, K., Kasahara, J., ... Funaki, I. (2019). Propulsion performance of inner-cylinder-less rotating detonation engine. In AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-1500

Propulsion performance of inner-cylinder-less rotating detonation engine. / Yokoo, Ryuya; Goto, Kesisuke; Kim, Juhoe; Kawasaki, Akira; Matsuoka, Ken; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh.

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

Yokoo, R, Goto, K, Kim, J, Kawasaki, A, Matsuoka, K, Kasahara, J, Matsuo, A & Funaki, I 2019, Propulsion performance of inner-cylinder-less rotating detonation engine. 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/10.2514/6.2019-1500
Yokoo R, Goto K, Kim J, Kawasaki A, Matsuoka K, Kasahara J et al. Propulsion performance of inner-cylinder-less rotating detonation engine. In AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA. 2019. (AIAA Scitech 2019 Forum). https://doi.org/10.2514/6.2019-1500
Yokoo, Ryuya ; Goto, Kesisuke ; Kim, Juhoe ; Kawasaki, Akira ; Matsuoka, Ken ; Kasahara, Jiro ; Matsuo, Akiko ; Funaki, Ikkoh. / Propulsion performance of inner-cylinder-less rotating detonation engine. AIAA Scitech 2019 Forum. American Institute of Aeronautics and Astronautics Inc, AIAA, 2019. (AIAA Scitech 2019 Forum).
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