High thrust measured for pulsed engine based on supermulti-jets colliding

Kenichiro Ashikawa, Jumpei Tsuchiya, Ken Ayukawa, Junya Mikoda, Kodai Kinoshita, Hiroki Makimoto, Remi Konagaya, Ken Naitoh

研究成果: Conference contribution

1 被引用数 (Scopus)


A prototype engine based on a new compressive combustion principle due to colliding pulsed supermulti-jets for aerospace was designed and developed by ourselves, in order to achieve very high thermal efficiency even for small combustion chambers. Experimental results on combustion reliably suggests high compression, combustion noise level comparable to that of traditional engines, and nearly-complete air-insulation effect on combustion chamber walls. While combustion at a lean burning condition occurs for the upstream fuel tank condition of about 3bar and for only a very small combustion-chamber diameter of 18mm, we also measured the thrust over about 100 N. Then, conversion evaluations based on the experimental data show that the present new engine due to the supermulti-jets colliding with pulse has a potential of thrust comparable to those of recent rocket engines having high thermal efficiency due to recycle of heat from chamber wall. If some geometrical optimizations are added, we get a possibility that thermal efficiency of the present new engine will be over 50%. Maximum thrust may be large because pulse type of combustion induces large pressure difference between upstream and downstream of combustion chamber, i.e., negative pressure in chamber after combustion, which leads to more gas supplied into the chamber.

ホスト出版物のタイトル2018 Joint Propulsion Conference
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
出版ステータスPublished - 2018
イベント54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018 - Cincinnati, United States
継続期間: 2018 7月 92018 7月 11


名前2018 Joint Propulsion Conference


Conference54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
国/地域United States

ASJC Scopus subject areas

  • 航空宇宙工学
  • 制御およびシステム工学


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