The present test series was conducted to ascertain the effects of various scale and geometric parameters on the combustion and pressure rise limits of a direct-connect supersonic combustor employing hydrogen fuel in a Mach 2 flow and 1-atm static pressure. The injector configuration was similar to that developed by Wagner et al. (1987). Attention is given to the effects of upstream length, fuel-injection gap, and constant-area combustor length, as well as to those of equivalence ratios and stagnation temperature. It is found that, for a given scale, combustion can be strongly dependent on such geometric factors as the use of either constant-area combustion or immediate expansion.


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    Title :

    Sensitivity of supersonic combustion to combustor/flameholder design


    Contributors:

    Conference:

    ICAS Congress ; 1988 ; Jerusalem, Israel


    Publication date :

    1988-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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