Abstract To lucubrate the velocity deficit of rotating detonation wave (RDW) fueled by hydrocarbon fuel, experiments are conducted in an elaborate combustor with full/half inner cylinder. The results show that the introduction of half hollow section alters the RDW propagation mode from counter-rotating two-wave mode to single-wave mode, accompanied by an obvious increase in the propagation velocity. In the combustor with half inner cylinder, the promotion effect of hollow part on the propagation velocity has been proved with segmented calculation method. Deflagrations in the form of “reverse flame” are observed to spread in the annular part, consuming the propellants ahead of the RDW. This pre-detonation combustion is believed to reduce the propagation velocity and the pressure ratio of RDW. Besides, some weak pressure perturbations can also be captured along with the “reverse flame”, indicating that there is a weak pressure wave propagating against the RDW. To some extent, this weak pressure wave can be seen as the precursor or the limit of a counter rotating detonation wave.

    Highlights Directly show the reaction zone in different chamber sections. Capture of deflagration in the annular chamber part. Discussion on the deficit of detonation wave propagation velocity. Analyses on the relationships between detonation and deflagration.


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    Titel :

    Experimental investigation on rotating detonation engine with full/half inner cylinder


    Beteiligte:
    Huang, Si-Yuan (Autor:in) / Zhou, Jin (Autor:in) / Liu, Wei-Dong (Autor:in) / Liu, Shi-Jie (Autor:in) / Peng, Hao-Yang (Autor:in) / Yuan, Xue-Qiang (Autor:in) / Zhang, Hai-Long (Autor:in)

    Erschienen in:

    Acta Astronautica ; 212 ; 84-94


    Erscheinungsdatum :

    2023-07-28


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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