Converging–diverging nozzles are common in rocket engine systems to increase the exhaust velocity and improve thrust performance. In this study, we focused on the acceleration of subsonic burned gas without a structural throat via detonation to realize a simple and compact engine. We developed and tested a rotating detonation engine (RDE) without a throat and with a diverging channel (constant diverging angle α = 5    deg ). Gaseous C 2 H 4 and O 2 were used as the propellants, and the mass flow rate ranged from 62 to 134    g / s in the combustion tests under low back-pressure conditions. We measured pressure and thrust, as well as high-speed imaging of self-luminescence of the combustion and imaging of the exhaust plume. The pressure at the exit was less than one-fifth of the maximum pressure in the RDE, significantly below the value for a sonic flow. The results suggested that the exhaust flow was supersonic, with values up to Mach 1.7, without the need of a converging section within the engine. In addition to the estimated Mach number from the measured pressure, the exhaust plume images coherently indicated the existence of supersonic exhaust.


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    Titel :

    Supersonic Exhaust from a Rotating Detonation Engine with Throatless Diverging Channel


    Beteiligte:
    Nakata, Kotaro (Autor:in) / Ota, Kosei (Autor:in) / Ito, Shiro (Autor:in) / Ishihara, Kazuki (Autor:in) / Goto, Keisuke (Autor:in) / Itouyama, Noboru (Autor:in) / Watanabe, Hiroaki (Autor:in) / Kawasaki, Akira (Autor:in) / Matsuoka, Ken (Autor:in) / Kasahara, Jiro (Autor:in)

    Erschienen in:

    AIAA Journal ; 60 , 7 ; 4015-4023


    Erscheinungsdatum :

    2022-03-29


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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