TY - GEN
T1 - Numerical study for rotating detonation propagation in a two-parallel-plane combustor
AU - Kumazawa, Yoshiki
AU - Fujii, Jumpei
AU - Matsuo, Akiko
AU - Nakagami, Soma
AU - Matsuoka, Ken
AU - Kasahara, Jiro
N1 - Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2016
Y1 - 2016
N2 - Numerical simulation for the detonation wave propagation in a two-parallel-plane combustor is conducted to investigate the effect of curvature. Governing equations are two dimensional euler equations with reduced kinetic reaction model. The length of the injection wall is fixed at 40 mm and curvature is changed as a parameter. Moreover, injection gas is stoichiometric premixed gas and non-premixed gas. The following knowledge is obtained through the calculation. The pressure at the detonation front becomes gradually smaller in larger curvature. It affects the height of the injected propellants to be smaller. Propagation velocity decrease occurs at the larger curvature, and this tendency does not depend on the injection method. The degree of this effect is larger in the non-premixed injection cases. Furthermore, the whole region analysis is conducted to confirm the effect of periodic boundary. The results are different from the cases of using periodic boundary, and similar phenomenon is observed in the experiments.
AB - Numerical simulation for the detonation wave propagation in a two-parallel-plane combustor is conducted to investigate the effect of curvature. Governing equations are two dimensional euler equations with reduced kinetic reaction model. The length of the injection wall is fixed at 40 mm and curvature is changed as a parameter. Moreover, injection gas is stoichiometric premixed gas and non-premixed gas. The following knowledge is obtained through the calculation. The pressure at the detonation front becomes gradually smaller in larger curvature. It affects the height of the injected propellants to be smaller. Propagation velocity decrease occurs at the larger curvature, and this tendency does not depend on the injection method. The degree of this effect is larger in the non-premixed injection cases. Furthermore, the whole region analysis is conducted to confirm the effect of periodic boundary. The results are different from the cases of using periodic boundary, and similar phenomenon is observed in the experiments.
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U2 - 10.2514/6.2016-5102
DO - 10.2514/6.2016-5102
M3 - Conference contribution
AN - SCOPUS:85086687387
SN - 9781624104060
T3 - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
BT - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
Y2 - 25 July 2016 through 27 July 2016
ER -