An experimental program is being conducted for developing the technology required by a hydrocarbon-fueled engine capable of operating as a scramjet in the Mach 5.6-7.0 range. A series of tests have been run to define scramjet combustor design criteria applicable to a scramjet configuration involving a pair of modular, axisymmetric combustors mounted on the lower surface of a supersonic/hypersonic missile. The airbreathing pilot combustor incorporates an external mainstream fuel injector which serves as the primary fuel injection stage for the supersonic combustor; it has been demonstrated that the pilot promotes the efficient combustion of either gaseous ethylene or preheated JP-5, when they are injected into the mainstream flow as a primary fuel.


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    Title :

    Hydrocarbon-fueled scramjet combustor investigation


    Contributors:
    Kay, I. W. (author) / Peschke, W. T. (author) / Guile, R. N. (author)

    Publication date :

    1990-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Hydrocarbon-fueled scramjet combustor investigation

    KAY, I. / PESCHKE, W. / GUILE, R. | AIAA | 1990


    Hydrocarbon-fueled scramjet combustor investigation

    KAY, I. W. / PESCHKE, W. T. / GUILE, R. N. | AIAA | 1992


    Hydrocarbon-fueled scramjet combustor investigation

    Kay, I. W. / Peschke, W. T. / Guile, R. N. | NTRS | 1992


    Experimental Characterization of Hydrocarbon-Fueled, Axisymmetric, Scramjet Combustor Flowpaths

    Gruber, M. / Smith, S. / Mathur, T. et al. | British Library Conference Proceedings | 2011