A computational fluid dynamics investigation of a pressure-gain combustor system for gas turbine applications is described. The system consists of a valved pulse combustor and an ejector, housed within a shroud. The computational fluid dynamics solver is first validated by comparing its output to experimental measurements done on a pulse combustor operating at sea-level static conditions. Subsequently, the combustor inlet pressure and temperature are increased in the simulations to more closely align with those seen downstream of a compressor. Several parameters that influence combustor performance are then varied in order to demonstrate the potential benefit of optimization efforts. Emissions calculations are also performed. It is found that efficient high-pressure operation is possible and that system pressure gain of nearly 3% (at gas turbine compatible combustor temperature ratios) is achievable, with nearly smooth exit flow, having a competitive emission index. The potential for pulse combustors to achieve ultra-low levels of NOx emissions at high-pressure conditions is also demonstrated.


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    Title :

    Numerical Investigation of Shrouded Ejector-Enhanced Pulse Combustor Performance at High Pressure



    Published in:

    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Local classification TIB:    770/7040



    Numerical Investigation of Shrouded Ejector-Enhanced Pulse Combustor Performance at High Pressure

    Yungster, Shaye / Paxson, Daniel E. / Perkins, Hugh D. | AIAA | 2016




    Operability of an Ejector Enhanced Pulse Combustor in a Gas Turbine Environment

    Paxson, D. / Dougherry, K. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2008