TY - GEN
T1 - Experimental performance validation of a rotating detonation engine toward a flight demonstration
AU - Goto, Keisuke
AU - Yokoo, Ryuya
AU - Kim, Juhoe
AU - Kawasaki, Akira
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
AU - Nakata, Daisuke
AU - Uchiumi, Masaharu
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 Scientific Researches (A) No. 24246137 and (B) No. 17H03480. The test piece and test chamber were manufactured by Yasuda-Koki Co., Ltd, Mizutani-Seiki Co., Ltd, Nakamura-Construction Co., Ltd, and Mashinax Co., Ltd.
Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - Thrust measurements of rotating detonation engine of (1) ethylene / gas-oxygen and (2) methane / gas-oxygen with various throat geometries in a vacuum chamber to simulate different back-pressure conditions ranging from 1.1-104 kPa were conducted. For throatless rotating detonation engine, we defined equivalent throat area as the detonation channel area, and then tested four nozzle contraction ratios of 1, 1.5, 2.5, and 8. Engines could be successfully ignited by electric ignitors when initial pressure was high enough to have, at least, one detonation cell in RDE channel. We measured the combustor pressure and reveled that it was almost proportional to the throat mass flux regardless of contraction ratios and the propellant combinations. The specific impulse of methane / gas-oxygen case could achieve 84 ± 1% of ideal specific impulse at the optimum expansion for each back pressure.
AB - Thrust measurements of rotating detonation engine of (1) ethylene / gas-oxygen and (2) methane / gas-oxygen with various throat geometries in a vacuum chamber to simulate different back-pressure conditions ranging from 1.1-104 kPa were conducted. For throatless rotating detonation engine, we defined equivalent throat area as the detonation channel area, and then tested four nozzle contraction ratios of 1, 1.5, 2.5, and 8. Engines could be successfully ignited by electric ignitors when initial pressure was high enough to have, at least, one detonation cell in RDE channel. We measured the combustor pressure and reveled that it was almost proportional to the throat mass flux regardless of contraction ratios and the propellant combinations. The specific impulse of methane / gas-oxygen case could achieve 84 ± 1% of ideal specific impulse at the optimum expansion for each back pressure.
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U2 - 10.2514/6.2019-1501
DO - 10.2514/6.2019-1501
M3 - Conference contribution
AN - SCOPUS:85083943750
SN - 9781624105784
T3 - AIAA Scitech 2019 Forum
BT - AIAA Scitech 2019 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Scitech Forum, 2019
Y2 - 7 January 2019 through 11 January 2019
ER -