Abstract A three-dimensional numerical simulation of a combustion chamber with a continuous rotating detonation wave was studied. A nozzle-type main system feeding was located at the end part of the chamber, and an additional feeding from the inner and outer walls of the annular channel was considered. A hydrogen-oxygen mixture was considered as a fuel. A detailed kinetic mechanism by Z. Hong (2010) consisting of 20 reactions with 9 components was used to simulate chemical processes. Various relations of the fuel were considered: lean mixture [H2]:[O2] = 1:1, stoichiometric mixture [H2]:[O2] = 2:1, and rich mixture [H2]:[O2] = 3:1. Besides, either the same mixture, or additional oxygen, or air was supplied from the side-wall feeding system. For all the considered feeding options, a detonation mode was obtained, and the traction characteristics were calculated.

    Highlights A simulation of an engine powered by a hydrogen-air mixture was carried out. Hong's kinetic mechanism was considered. The influence of the fuel concentration on the processes in the chamber was studied. Traction characteristics were obtained and analyzed for all cases.


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    Titel :

    The use of detailed kinetics for modeling aerospace propulsion devices


    Beteiligte:
    Nikitin, V.F. (Autor:in) / Mikhalchenko, E.V. (Autor:in) / Stamov, L.I. (Autor:in)

    Erschienen in:

    Acta Astronautica ; 204 ; 761-767


    Erscheinungsdatum :

    2022-09-21


    Format / Umfang :

    7 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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