TY - GEN
T1 - Study of Cylindrical Rotating Detonation Engine with Propellant Injection Cooling System
AU - Ota, Kosei
AU - Goto, Keisuke
AU - Itouyama, Noboru
AU - Watanabe, Hiroaki
AU - Kawasaki, Akira
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Funding Information:
This research was subidizsed by the Grant-i-Anid for Scientific Research (2-02023)1(190945H6ant4hde) Strategic Research Fund of the Space EninegeringCo mimttee (2906-2.1.03) by2the J1apan Aerospace Expoatlionr Agency.
Funding Information:
This research was subsidized by the Grant-in-Aid for Scientific Research (2019-2023) (19H05464) and the Strategic Research Fund of the Space Engineering Committee (2019.6-2021.3) by the Japan Aerospace Exploration Agency.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - A cylindrical RDE with a propellant injection cooling system with an injector on the entire wall surface of the combustor has been tested and demonstrated. In this study, in order to search the optimum flow balance between the side and the bottom, the experiment was conducted under a total test condition of 30 g/s, and various balance condition. Under all conditions, a stable single rotating detonation was observed. In the 5.0-second combustion test, the temperature rise in the cooling area stopped and became steady state at a maximum of 850 K. This may be due to the heat exchange and film cooling effect of propellant injection. In addition, the propulsion performance was 94% of the theoretical value calculated assuming that the gas flow reached the speed of sound at the outlet of the combustor. It had been demonstrated that sufficient cooling and propulsion performance can be obtained by injecting 76% from the side wall and 24% from the bottom wall.
AB - A cylindrical RDE with a propellant injection cooling system with an injector on the entire wall surface of the combustor has been tested and demonstrated. In this study, in order to search the optimum flow balance between the side and the bottom, the experiment was conducted under a total test condition of 30 g/s, and various balance condition. Under all conditions, a stable single rotating detonation was observed. In the 5.0-second combustion test, the temperature rise in the cooling area stopped and became steady state at a maximum of 850 K. This may be due to the heat exchange and film cooling effect of propellant injection. In addition, the propulsion performance was 94% of the theoretical value calculated assuming that the gas flow reached the speed of sound at the outlet of the combustor. It had been demonstrated that sufficient cooling and propulsion performance can be obtained by injecting 76% from the side wall and 24% from the bottom wall.
UR - http://www.scopus.com/inward/record.url?scp=85126736356&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85126736356&partnerID=8YFLogxK
U2 - 10.2514/6.2021-3650
DO - 10.2514/6.2021-3650
M3 - Conference contribution
AN - SCOPUS:85126736356
SN - 9781624106118
T3 - AIAA Propulsion and Energy Forum, 2021
BT - AIAA Propulsion and Energy Forum, 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum, 2021
Y2 - 9 August 2021 through 11 August 2021
ER -