Initiation of combustion of hydrogen and hydrocarbon gaseous fuels in a supersonic flow in a channel with a variable cross section, realized with the help of a throttling jet, is studied numerically. The flow Mach numbers M = 2 and M = 1.7 are considered; the stagnation temperatures of the flow under study are 1700, 1000, 1200, and 1450 K. It is shown that the total value of the energy used in the gas, i.e., dynamic pulses of the throttling jet, increases with the length of the channel part with a constant cross section. The qualitative characteristics of the process change as the stagnation parameters decrease.


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    Title :

    Combustion initiation in a supersonic flow at various pressures, stagnation temperatures, and channel parameters



    Conference:

    XLV ACADEMIC SPACE CONFERENCE, DEDICATED TO THE MEMORY OF ACADEMICIAN S.P. KOROLEV AND OTHER OUTSTANDING NATIONAL SCIENTISTS — PIONEERS OF SPACE EXPLORATION ; 2021 ; Moscow, Russia


    Published in:

    Publication date :

    2023-07-20


    Size :

    4 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English