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

Sota Kawaguchi, Remi Konagaya, Kohta Tsuru, Ken Naitoh

研究成果: Conference contribution

抄録

We have previously proposed 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 in two cases of injection nozzle distributions, half-sphere and sphere-like. We used the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that in the sphere-like injection nozzle distribution, combustion efficiency and the pressure of combustion chamber are higher than those in the half-sphere injection nozzle distribution.

本文言語English
ホスト出版物のタイトルAIAA Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
210059
ISBN(印刷版)9781624105241
DOI
出版ステータスPublished - 2018
イベントAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
継続期間: 2018 1 82018 1 12

出版物シリーズ

名前AIAA Aerospace Sciences Meeting, 2018
番号210059

Other

OtherAIAA Aerospace Sciences Meeting, 2018
国/地域United States
CityKissimmee
Period18/1/818/1/12

ASJC Scopus subject areas

  • 航空宇宙工学

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