Computations of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse

Remi Konagaya, Ken Naitoh, Takuma Okamoto, Kohta Tsuru

研究成果: Conference contribution

5 被引用数 (Scopus)

抄録

We propose a new type of rocket engine that uses the new compressive combustion principle based on supermulti-jets colliding with pulse, which may further improve the thermal efficiency of present rocket engines. In this research, we calculate the flow inside the combustion chamber of our new rocket engine by computation, based on the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that auto-ignition occurred near the center of the chamber, and the pressure of the combustion chamber increased to 3-6 times the value of fuel tanks.

本文言語English
ホスト出版物のタイトルAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(電子版)9781624104473
DOI
出版ステータスPublished - 2017
イベント55th AIAA Aerospace Sciences Meeting - Grapevine, United States
継続期間: 2017 1月 92017 1月 13

出版物シリーズ

名前AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting

Other

Other55th AIAA Aerospace Sciences Meeting
国/地域United States
CityGrapevine
Period17/1/917/1/13

ASJC Scopus subject areas

  • 航空宇宙工学

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