TY - GEN
T1 - Cylindrical rotating detonation engine cooling by means of propellant injection
AU - Goto, Keisuke
AU - Ota, Kosei
AU - Kawasaki, Akira
AU - Watanabe, Hiroaki
AU - Itouyama, Noboru
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Funding Information:
RDE development was subsidized by a “Study on Innovative Detonation Propulsion Mechanism,” Research-and-Development Grant Program (Engineering) from the Institute of Space and Astronautical Science, the Japan Aerospace Exploration Agency, and a “Research and Development of an Ultra-High-Thermal-Efficiency Rotating Detonation Engine with Self-Compression Mechanism,” Advanced Research Program for Energy and Environmental Technologies, the New Energy and Industrial Technology Development Organization. The fundamental device development was subsidized by Grant-in-Aid for Specially Promoted Research No. 19H05464, Grant-in-Aid for Scientific Researches (A) No. 24246137, (B) No. 17H03480, and Grant-in-Aid for JSPS Fellows No. 19J15418. The test piece and test chamber were manufactured by Yasuda-Koki Co., Ltd, Mizutani-Seiki Co., Ltd, Hakudo Co., Ltd, Nakashima Special Co., Ltd.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested and demonstrated. Thrust measurement of the cylindrical RDE (24-mm-diameter) was conducted with monitoring K-type thermocouples inserted in combustor wall. Single rotating detonation wave was observed in the testing conditions ranging from 31 to 59 g/s in this study. Combustion tests for 4.0 ~ 4.9 s were successfully done, and all injector side wall temperature increases were suppressed compared to that of combustor base plate, which had no cooling structure. This could be due to the cooling effect by the heat exchange of propellant injection. In the 4.9 s combustion test with 31 g/s, all thermocouples inserted in the combustor side wall which had the propellant injector surface showed a temperature decreasing 2.5 s after ignition even though the combustion was continuing, and implied the combustion mode shift.
AB - An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested and demonstrated. Thrust measurement of the cylindrical RDE (24-mm-diameter) was conducted with monitoring K-type thermocouples inserted in combustor wall. Single rotating detonation wave was observed in the testing conditions ranging from 31 to 59 g/s in this study. Combustion tests for 4.0 ~ 4.9 s were successfully done, and all injector side wall temperature increases were suppressed compared to that of combustor base plate, which had no cooling structure. This could be due to the cooling effect by the heat exchange of propellant injection. In the 4.9 s combustion test with 31 g/s, all thermocouples inserted in the combustor side wall which had the propellant injector surface showed a temperature decreasing 2.5 s after ignition even though the combustion was continuing, and implied the combustion mode shift.
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U2 - 10.2514/6.2020-3855
DO - 10.2514/6.2020-3855
M3 - Conference contribution
AN - SCOPUS:85091311451
SN - 9781624106026
T3 - AIAA Propulsion and Energy 2020 Forum
SP - 1
EP - 9
BT - AIAA Propulsion and Energy 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy 2020 Forum
Y2 - 24 August 2020 through 28 August 2020
ER -