TY - GEN
T1 - Experimental study of disk-shaped rotating detonation Turbine engine
AU - Higashi, Junichi
AU - Ishiyama, Chikara
AU - Nakagami, Soma
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
AU - Moriai, Hideki
N1 - Funding Information:
This study was subsidized by Advanced Research Program for Energy and Environmental Technologies, New Energy and Industrial Technology Development Organization (NEDO). The authors would like to thank the Japan Aerospace Exploration Agency.
Publisher Copyright:
© 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
Copyright:
Copyright 2017 Elsevier B.V., All rights reserved.
PY - 2017
Y1 - 2017
N2 - A rotating detonation turbine engine has simpler structure and higher thermal efficiency than a conventional gas turbine engine. In this study, we designed a rotating detonation turbine engine with single stage centrifugal compressor, combustion chamber, and single stage radial flow turbine which are placed on one side of rotor disk. We performed cold flow experiments and combustion experiments. As results of cold flow test, compressor can supply air 52 g/s. In combustion experiments, we supply pressured oxidizer and fuel from outside of engine. As a results, combustion propagation speed was 600 - 1300 m/s. this is about 25 – 45 % of Chapman – Jouget detonation velocity. In addition, rotational speed rises by 160 rpm during combustion.
AB - A rotating detonation turbine engine has simpler structure and higher thermal efficiency than a conventional gas turbine engine. In this study, we designed a rotating detonation turbine engine with single stage centrifugal compressor, combustion chamber, and single stage radial flow turbine which are placed on one side of rotor disk. We performed cold flow experiments and combustion experiments. As results of cold flow test, compressor can supply air 52 g/s. In combustion experiments, we supply pressured oxidizer and fuel from outside of engine. As a results, combustion propagation speed was 600 - 1300 m/s. this is about 25 – 45 % of Chapman – Jouget detonation velocity. In addition, rotational speed rises by 160 rpm during combustion.
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U2 - 10.2514/6.2017-1286
DO - 10.2514/6.2017-1286
M3 - Conference contribution
AN - SCOPUS:85017193420
T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 55th AIAA Aerospace Sciences Meeting
Y2 - 9 January 2017 through 13 January 2017
ER -