Experimental study of research of centrifugal-compressor-radial-turbine type rotating detonation engine

Chikara Ishiyama, Koji Miyazaki, Soma Nakagami, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

研究成果: Conference contribution

17 被引用数 (Scopus)

抄録

Rotating detonation engines (RDEs) can get thrust or work by keeping detonation waves propagating in circumferential direction. Our objective is to apply rotating detonation engines (RDEs) to aircraft engines since we expect that the aircraft such as airplanes is to fly longer range by more simple structure. In this study, we designed a rotating detonation turbine engine (RDTE) with a single stage centrifugal compressor and a single stage radial flow turbine. The outer diameter of RDTE is about 200 mm. The revolution speed is 110000 rpm and rated air mass flow rate was 0.610 kg/s. We made two-parallel-plane rotating detonation combustor. We performed hot test with ethylene and oxygen. We analyzed several combustion modes with streak pictures and pressure time history. We observed the number of detonation waves, quenching and re-ignition phenomena by streak pictures.

本文言語English
ホスト出版物のタイトル52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624104060
DOI
出版ステータスPublished - 2016
イベント52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016 - Salt Lake City, United States
継続期間: 2016 7 252016 7 27

出版物シリーズ

名前52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016

Other

Other52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
CountryUnited States
CitySalt Lake City
Period16/7/2516/7/27

ASJC Scopus subject areas

  • Engineering(all)

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