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

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    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.

    Original languageEnglish
    Title of host publicationAIAA Aerospace Sciences Meeting
    PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
    Edition210059
    ISBN (Print)9781624105241
    DOIs
    Publication statusPublished - 2018 Jan 1
    EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
    Duration: 2018 Jan 82018 Jan 12

    Other

    OtherAIAA Aerospace Sciences Meeting, 2018
    CountryUnited States
    CityKissimmee
    Period18/1/818/1/12

    ASJC Scopus subject areas

    • Aerospace Engineering

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  • Cite this

    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. In AIAA Aerospace Sciences Meeting (210059 ed.). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-0668