Properly tuned Helmholtz resonator damping devices are an effective method for eliminating high frequency combustion instability in rocket engine thrust chambers. A program was implemented with the objective of extending Helmholtz resonator theory to thrust chamber conditions to establish a standard design procedure. By using systematic cold-flow testing and hot firings, empirical design equations were formulated. An effort is currently underway to extend the design theory to other types of acoustical damping devices such as quarter-wave tubes and slots.


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    Titel :

    Rocket combustion instability suppression with cavity resonators


    Beteiligte:
    Counts, R. H. (Autor:in)


    Erscheinungsdatum :

    01.08.1972


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch