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

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

Department of Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

13 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 language	English
Title of host publication	54th AIAA Aerospace Sciences Meeting
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
Pages	1-9
Number of pages	9
ISBN (Print)	9781624103933
Publication status	Published - 2016
Event	54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States Duration: 2016 Jan 4 → 2016 Jan 8

Other

Other	54th AIAA Aerospace Sciences Meeting, 2016
Country	United States
City	San Diego
Period	16/1/4 → 16/1/8

ASJC Scopus subject areas

Aerospace Engineering

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Study of combustion chamber characteristic length in rotating detonation engine with convergent-divergent nozzle. / Kato, Yuichi; Ishihara, Kazuki; Matsuoka, Ken; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh.

54th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. p. 1-9.

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

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. American Institute of Aeronautics and Astronautics Inc, AIAA, pp. 1-9, 54th AIAA Aerospace Sciences Meeting, 2016, San Diego, United States, 16/1/4.

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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.",

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AU - Matsuo, Akiko

AU - Funaki, Ikkoh

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AB - 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.

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