Abstract In order to describe partially premixed supersonic combustion numerically, G/Z flamelet model is developed and compared with finite rate model in hybrid RANS/LES simulation to study the strut-injection supersonic combustion flow field designed by the German Aerospace Center. A new temperature calculation method based on time-splitting method of total energy is introduced in G/Z flamelet model. Simulation results show that temperature predictions in partially premixed zone by G/Z flamelet model are more consistent with experiment than finite rate model. It is worth mentioning that low temperature reaction zone behind the strut is well reproduced. Other quantities such as average velocity and average velocity fluctuation obtained by developed G/Z flamelet model are also in good agreement with experiment. Besides, simulation results by G/Z flamelet also reveal the mechanism of partially premixed supersonic combustion by the analyses of the interaction between turbulent burning velocity and flow field.

    Highlights G/Z flamelet model is developed for partially premixed supersonic hydrogen/air combustion. Simulation results are in better agreement with experiment by G/Z flamelet model. Low temperature reaction zone is well predicted by G/Z flamelet model. Mechanism of partially premixed supersonic combustion could be revealed by G/Z flamelet model.


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    Title :

    The hybrid RANS/LES of partially premixed supersonic combustion using G/Z flamelet model


    Contributors:
    Wu, Jinshui (author) / Wang, Zhenguo (author) / Bai, Xuesong (author) / Sun, Mingbo (author) / Wang, Hongbo (author)

    Published in:

    Acta Astronautica ; 127 ; 375-383


    Publication date :

    2016-06-10


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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