This work addresses the nature of supercritical hydrogen-oxygen flame coupling to acoustics through visualization under conditions representative of upper-stage rocket engines. A research thrust chamber that shows self-excited combustion instabilities for certain operating conditions was used. Previous analysis proved that the instabilities are connected to injector acoustics. In this study a small optical access window was mounted in the chamber wall. High-speed flame radiation imaging of UV and blue wavelengths has been applied in order to analyze the acoustic-flame interaction of one of the 42 flames. Dynamic mode decomposition results for a case with 80-bar chamber pressure showed that the flame dynamics are strongly influenced by the LOX injector acoustics, whereas for a 50-bar chamber pressure load point no flame response to injector acoustics was observed. A potential source of acoustic excitation in the oxygen injectors based on hydrodynamic effects is consistent with the observations from the two load points.


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    Title :

    Injector-Driven Flame Dynamics in a High-Pressure Multi-Element Oxygen–Hydrogen Rocket Thrust Chamber


    Contributors:

    Published in:

    Publication date :

    2019-05-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Rocket Thrust Chamber

    E. F. Baehr | NTIS | 1965




    Injector-Driven Combustion Instabilities in a Hydrogen/Oxygen Rocket Combustor

    Gröning, Stefan / Hardi, Justin S. / Suslov, Dmitry et al. | AIAA | 2016


    Rocket thrust chamber Patent

    Baehr, E. F. | NTRS | 1965