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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Sensitivity of supersonic combustion to combustor/flameholder design


    Beteiligte:

    Kongress:

    ICAS Congress ; 1988 ; Jerusalem, Israel


    Erscheinungsdatum :

    01.01.1988


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Effects of Flameholder Configuration on a Staged Supersonic Combustor

    Lee, Kyungjae / Kang, Sanghun / Lee, Yangji et al. | AIAA | 2012


    Flow and Combustion in a Supersonic Cavity Flameholder

    Cisneros-Garibay, Esteban / Pantano, Carlos / Freund, Jonathan B. | AIAA | 2022



    Flame Flashback in a Supersonic Combustor Fueled by Ethylene with Cavity Flameholder

    Sun, Ming-Bo / Cui, Xing-Da / Wang, Hong-Bo et al. | AIAA | 2015