TY - GEN
T1 - Numerical Investigation of Rotating Detonation Engine with Injection from the Combustor Side Wall
AU - Sada, Takumi
AU - Matsuo, Akiko
AU - Shima, Eiji
AU - Watanabe, Hiroaki
AU - Kawasaki, Akira
AU - Matsuoka, Ken
AU - Kasahara, Jiro
N1 - Funding Information:
This study was financially supported by JSPS KAKENHI Grants No. JP19H05464 and by the Institute of Space and Astronautical Science of the Japan Aerospace Exploration Agency. Part of the numerical results in this research wereobtainedusinguspercomputingsrourceesta ybeCrscienceeCnter, TohokunUiversity.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - Numerical analysis of cylindrical rotating detonation engine (RDE) with injectors on the combustor side wall is conducted using the stoichiometric H2-Air premixed gas. The combustor is 70 mm in length and 20 mm in diameter. The results are compared to the conventional injector configuration, which has injectors on the combustor bottom, and the combustion features with side injection are investigated. The instantaneous pressure and temperature fields show the characteristics of propagating waves are different depending on the injector configuration. From the spatiotemporal average profiles, the combustion occurs more rapidly in the case of injection from the bottom. However, the case of injection from the side wall also shows the consumption of fuel. Compared to the theoretical values, the specific impulse is 106 % from the bottom and 103 % from the side. In this combustor length, both injection conditions can provide similar thrust performance to the theoretical values.
AB - Numerical analysis of cylindrical rotating detonation engine (RDE) with injectors on the combustor side wall is conducted using the stoichiometric H2-Air premixed gas. The combustor is 70 mm in length and 20 mm in diameter. The results are compared to the conventional injector configuration, which has injectors on the combustor bottom, and the combustion features with side injection are investigated. The instantaneous pressure and temperature fields show the characteristics of propagating waves are different depending on the injector configuration. From the spatiotemporal average profiles, the combustion occurs more rapidly in the case of injection from the bottom. However, the case of injection from the side wall also shows the consumption of fuel. Compared to the theoretical values, the specific impulse is 106 % from the bottom and 103 % from the side. In this combustor length, both injection conditions can provide similar thrust performance to the theoretical values.
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U2 - 10.2514/6.2022-4108
DO - 10.2514/6.2022-4108
M3 - Conference contribution
AN - SCOPUS:85135237059
SN - 9781624106354
T3 - AIAA AVIATION 2022 Forum
BT - AIAA AVIATION 2022 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2022 Forum
Y2 - 27 June 2022 through 1 July 2022
ER -