A model to analyse the heterogeneous combustion process that takes place in an axisymmetric combustor of an air ducted rocket is presented, including radiation. The fuel, injected into the combustor through a simple injector, is a mixture of gaseous products, carbon particles, and MgO inert particles that results from the combustion of a solid fuel (HTPB-AP-Mg). The turbulence model used is the realizable k—π model. The adopted reaction model is a reduced kinetic scheme composed of five reactions, three in gaseous phase and two heterogeneous. The model ‘finite rate/eddy dissipation model of Magnussen and Hjertager’ is used to calculate the production terms in the gas phase, meanwhile the mixed model of Field, Baum, and Street is used for the oxidation reaction of carbon particles.

    After a detailed analysis of the numerical results, obtained with a commercial code for a specific combustor geometry and one set of boundary conditions both for the gaseous and solid phases, the existence of a special combustion pattern is found. It is composed of a turbulent diffusion jet flame attached to the injector, where only the gaseous fuel is burned, followed by a reaction region that envelops the jet of carbon particles at the aft of the combustion chamber. This jet of carbon particles oxidizes at a finite rate producing CO and CO2. The emission of CO and C(s) from the combustor is the main cause of high efficiency reduction.

    Radiation has little effect on calculated global variables, such as efficiency, mass flowrate, and total pressure loss, but on the contrary its effects on the temperature fields became important. Chilling of the gas phase was observed together with a reduction of solid particle temperature, however wall combustor temperature increased greatly.

    Simulation results are interpreted in the light of experimental observations and available numerical solutions in the literature.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Numerical analysis of heterogeneous combustion in a ducted rocket


    Beteiligte:
    Salvá, J J (Autor:in) / Tizón, J M (Autor:in) / Jenaro, G (Autor:in) / Agudo, C López (Autor:in)


    Erscheinungsdatum :

    2007-01-01


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Numerical simulation of ducted rocket motor

    Ristori, Arnaud / Dufour, Emmanuel | AIAA | 2001


    Ducted rocket combustion experiments at low gas-generator combustion temperatures

    Dijkstra, F / Mayer, A / Wilson, K et al. | AIAA | 1995


    Two phase flow combustion modelling of a ducted rocket

    Stowe, R. / Dubois, C. / Harris, P. et al. | AIAA | 2001


    Combustion Characteristics of Ducted Rocket Engine in the Mars

    Hara, Hideki / Ushijma, Masamichi / Muramatsu, Akinori et al. | AIAA | 2011