TY - GEN
T1 - Propulsive performane of cylindrical rotating detonation engine with propellant injection cooing
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:
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.
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:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested with three combustor length of 21, 30, and 6 mm. 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 with the combustor length of 30 and 69 mm in this study. Cooling effect due to the propellant injection was confirmed as the nearly saturated temperature response in the combustor side wall. when the chamber length is more than 30 mm, the specific impulse maintained more than 80% of theoretical value assuming sonic condition at the chamber exit. The result indicated that modest combustor length as an efficient thruster exists in the range of 30 to 69 mm.
AB - An engine cooling concept for cylindrical rotating detonation engine which had an injector surface on the combustor side wall has been tested with three combustor length of 21, 30, and 6 mm. 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 with the combustor length of 30 and 69 mm in this study. Cooling effect due to the propellant injection was confirmed as the nearly saturated temperature response in the combustor side wall. when the chamber length is more than 30 mm, the specific impulse maintained more than 80% of theoretical value assuming sonic condition at the chamber exit. The result indicated that modest combustor length as an efficient thruster exists in the range of 30 to 69 mm.
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M3 - Conference contribution
AN - SCOPUS:85100300890
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 7
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -