TY - GEN
T1 - Performance of a RBCC combustor operating in ramjet mode
AU - Kouchi, Toshinori
AU - Kobayashi, Kan
AU - Kudo, Kenji
AU - Murakami, Atsuo
AU - Kato, Kanenori
AU - Tomioka, Sadatake
N1 - Copyright:
Copyright 2020 Elsevier B.V., All rights reserved.
PY - 2006
Y1 - 2006
N2 - The direct-connect combustion tests and the numerical simulations of the rocket-ramjet combined cycle combustor, requiring large bases to install rocket chambers, were conducted to determine whether the combustor could be operated in ramjet mode. The rocket engines in the combustor were operated at fuel rich condition as fuel injectors for the freestream. For the rocket operation alone, the combustor was operated in scramjet mode. By the secondary fuel injection from the cowl, the supersonic freestream was decelerated to subsonic speed by the combustion-generated shock train in front of the secondary injection. The subsonic combustion of the secondary injected fuel resulted in higher combustion and thrust performances. The further upstream secondary injection was suitable for the ramjet operation. By the increase in fuel flow rate of the secondary injection, the thermal load on both the rocket chamber and throat was reduced without decrease in thrust. Gas sampling measurements at the exit of the combustor revealed that the merger of the secondary fuel with the rocket plumes resulted in the decrease of the combustion and thrust performances.
AB - The direct-connect combustion tests and the numerical simulations of the rocket-ramjet combined cycle combustor, requiring large bases to install rocket chambers, were conducted to determine whether the combustor could be operated in ramjet mode. The rocket engines in the combustor were operated at fuel rich condition as fuel injectors for the freestream. For the rocket operation alone, the combustor was operated in scramjet mode. By the secondary fuel injection from the cowl, the supersonic freestream was decelerated to subsonic speed by the combustion-generated shock train in front of the secondary injection. The subsonic combustion of the secondary injected fuel resulted in higher combustion and thrust performances. The further upstream secondary injection was suitable for the ramjet operation. By the increase in fuel flow rate of the secondary injection, the thermal load on both the rocket chamber and throat was reduced without decrease in thrust. Gas sampling measurements at the exit of the combustor revealed that the merger of the secondary fuel with the rocket plumes resulted in the decrease of the combustion and thrust performances.
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U2 - 10.2514/6.2006-4867
DO - 10.2514/6.2006-4867
M3 - Conference contribution
AN - SCOPUS:34249324459
SN - 1563478188
SN - 9781563478185
T3 - Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
SP - 5325
EP - 5338
BT - Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Y2 - 9 July 2006 through 12 July 2006
ER -