TY - GEN
T1 - Combustion Characteristics of Reflective Shuttling Detonation Combustor with Different Equivalence Ratio
AU - Miyashita, Moeno
AU - Matsuo, Akiko
AU - Shima, Eiji
AU - Kawasaki, Akira
AU - Itouyama, Noboru
AU - Matsuoka, Ken
AU - Kasahara, Jiro
N1 - Publisher Copyright:
© 2024 by Moeno Miyashita. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2024
Y1 - 2024
N2 - A three-dimensional numerical analysis was performed on a reflective shuttling detonation combustor to investigate the propagation phenomena of detonation in a fuel-rich condition, with different equivalence ratio. The computational domain was a rectangular region where the hydrogen-air premixed gas flows in from the bottom injector with changing equivalence ratio from 1.0 to 2.0. As a result, continuous propagation of detonation was observed in each case, and the same trend of the propagation mode was observed. In addition, A decrease in the temperature value during combustion and an increase in the propagation velocity were observed as the equivalent ratio increased. Both trends were consistent with the trends of CJ temperature and CJ velocity with increasing equivalent ratio.
AB - A three-dimensional numerical analysis was performed on a reflective shuttling detonation combustor to investigate the propagation phenomena of detonation in a fuel-rich condition, with different equivalence ratio. The computational domain was a rectangular region where the hydrogen-air premixed gas flows in from the bottom injector with changing equivalence ratio from 1.0 to 2.0. As a result, continuous propagation of detonation was observed in each case, and the same trend of the propagation mode was observed. In addition, A decrease in the temperature value during combustion and an increase in the propagation velocity were observed as the equivalent ratio increased. Both trends were consistent with the trends of CJ temperature and CJ velocity with increasing equivalent ratio.
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U2 - 10.2514/6.2024-2611
DO - 10.2514/6.2024-2611
M3 - Conference contribution
AN - SCOPUS:85195502600
SN - 9781624107115
T3 - AIAA SciTech Forum and Exposition, 2024
BT - AIAA SciTech Forum and Exposition, 2024
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2024
Y2 - 8 January 2024 through 12 January 2024
ER -