Numerical simulation is performed and compared with a firing test of an H 2 O 2 / polyethylene hybrid rocket engine equipped with a catalyzer. The simulation is performed assuming an axisymmetric flow, unsteady Reynolds-averaged Navier–Stokes equations are solved based on a single-phase flow. Stable pressure oscillations are observed during the firing test and could be explained by the simulation with the formation of large-scale vortices at the end of the fuel grain and in the postcombustion chamber. These vortices transport unburnt fuel to the nozzle and play a major role in the mixing process in the postchamber. Two semi-empirical approaches are applied and provide a good order of magnitude for the frequency and frequency shift during the firing test. Another simulation has been performed with an added oxidizer postchamber injection. It revealed that small-scale vortices along the fuel grain in the baseline case are probably generated by the oscillatory motion of the flow due to pressure fluctuations in the engine.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Vortex Shedding Influence on Hybrid Rocket Pressure Oscillations and Combustion Efficiency


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2016-06-03


    Format / Umfang :

    9 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






    Combustion Instability Involving Vortex Shedding in Hybrid Rocket Motors

    Pastrone, Dario / Casalino, Lorenzo / Codegone, Marco et al. | AIAA | 2013


    Large-Eddy Simulation of Vortex Shedding and Pressure Oscillations in Solid Rocket Motors

    Bernardini, M. / Cimini, M. / Stella, F. et al. | AIAA | 2020