Hydrogen fueled scramjet is a candidate for use as the engine of the aerospace plane for its high specific impulse. To further improve the engine performance, analysis of combustion mode transition for a hydrogen fueled scramjet engine was investigated in this study. In order to identify the differences between Scram- and Ram-mode cycles in propulsive and economic performances for selection and optimization of operation modes, a thermodynamic cycle analysis was made with a dual-mode scramjet engine. It was found through comparative analysis that the specific impulse of the Ram-mode cycle was superior to that of the Scram-mode cycle in meeting the specific thrust requirement. From the viewpoint of performance optimization, the combustion mode transition in a dual-mode scramjet engine should occur in the range of Mach number 6–7. It was therefore concluded that a dual-mode scramjet engine should be operated as much at the Ram-mode cycle as possible when the flight Mach number is less than 6, and the combustion mode transition between Ram-mode cycle and Scram-mode cycle should take place in the range of flight Mach number 6–7.


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    Titel :

    Study on combustion mode transition of hydrogen fueled dual-mode scramjet engine based on thermodynamic cycle analysis


    Beteiligte:
    Cao, R.F. (Autor:in) / Chang, J.T. (Autor:in) / Tang, J.F. (Autor:in) / Wang, Z.Q. (Autor:in) / Yu, D.R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2014


    Format / Umfang :

    8 Seiten, 25 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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