Experimental study of disk-shaped rotating detonation Turbine engine

Junichi Higashi, Chikara Ishiyama, Soma Nakagami, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki, Hideki Moriai

Research output: Chapter in Book/Report/Conference proceedingConference contribution

58 Citations (Scopus)


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.

Original languageEnglish
Title of host publicationAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624104473
Publication statusPublished - 2017
Event55th AIAA Aerospace Sciences Meeting - Grapevine, United States
Duration: 2017 Jan 92017 Jan 13

Publication series

NameAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting


Other55th AIAA Aerospace Sciences Meeting
Country/TerritoryUnited States

ASJC Scopus subject areas

  • Aerospace Engineering


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