Combustor technology development main focus is on understanding the requirements for fuel injection, fuel/air mixing, and chemical reaction, and their performance in the scramjet combustor environment. While combustion technology is relatively mature for rocket, ramjet, and turbojet engines, this is not the case for dual‐mode scramjet combustion, and more so for multimode, combined cycle propulsion operation. The combustor entry conditions, such as Mach number and thermodynamic state of the gas, are defined by taking into consideration propulsion cycle efficiencies, temperature limitations imposed by materials, and by‐product gas dissociation. Combustion occurs when a fuel reacts with the oxygen in the air, and the chemical reaction produces thermal energy. As a propulsion device, the scramjet is geometrically simple compared with any other engine. The scramjet combustor design must account for many processes to properly occur in order for the combustor to operate in flight, e.g. fuel/air mixing, ignition, flame holding, and flame propagation.


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    Title :

    Scramjet Combustor


    Contributors:

    Published in:

    Publication date :

    2022-11-18


    Size :

    38 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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