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

    抜粋

    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.

    元の言語English
    ホスト出版物のタイトルAIAA Aerospace Sciences Meeting
    出版者American Institute of Aeronautics and Astronautics Inc, AIAA
    エディション210059
    ISBN(印刷物)9781624105241
    DOI
    出版物ステータスPublished - 2018 1 1
    イベントAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
    継続期間: 2018 1 82018 1 12

    Other

    OtherAIAA Aerospace Sciences Meeting, 2018
    United States
    Kissimmee
    期間18/1/818/1/12

    ASJC Scopus subject areas

    • Aerospace Engineering

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  • これを引用

    Kawaguchi, S., Konagaya, R., Tsuru, K., & Naitoh, K. (2018). Computations for improving the performance of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse. : AIAA Aerospace Sciences Meeting (210059 版). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-0668