TY - GEN
T1 - Study of combustion chamber characteristic length in rotating detonation engine with convergent-divergent nozzle
AU - Kato, Yuichi
AU - Ishihara, Kazuki
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Publisher Copyright:
© 2016, All rights reserved.
PY - 2016
Y1 - 2016
N2 - 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.
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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U2 - 10.2514/6.2016-1406
DO - 10.2514/6.2016-1406
M3 - Conference contribution
AN - SCOPUS:85007591440
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
SP - 1
EP - 9
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA Aerospace Sciences Meeting, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -