Abstract This paper studies the effects of liquid oxidizer flow distribution on combustion characteristics and performance of hybrid rocket motor with axial injection through numerical simulations of two-phase flow. Axial injection is widely used in hybrid rocket motor, however, the regression of burning surface may change combustion efficiency of the motor at different moments. Consequently, it is necessary for hybrid rocket motor to design injector patterns that could increase the average combustion efficiency in the whole operating process. The orifice injector plate is divided into three areas, which are recorded as zone I, zone II and zone III, respectively. Oxidizer flow distribution is achieved through changing the diameter of injector holes in various zones, and three-dimensional steady numerical simulations of two-phase flow of hybrid rocket motor with axial injector patterns at different moments are conducted. The motor adopts 98% hydrogen peroxide and hydroxyl-terminated polybutadiene as the propellants. Numerical analysis reveals that oxidizer flow distribution mainly influences the flow field structure in the pre-combustion chamber and front part of fuel grain port. Increasing oxidizer mass flow rate in zone III is beneficial for the chamber head thermal environment. Relative position in the radial direction of fuel grain inner surface and oxidizer distributed in the injector plate affects fuel regression rates, and the influence mainly exists in the front part of solid fuel grain. When the oxidizer mass flow rate in zone I is equal, the average fuel regression rate rises with the increase of oxidizer flow rate in zone II at initial moment, and decreases as the oxidizer in zone II increases at middle moment. The average combustion efficiency increases with the increase of oxidizer mass flow rate in zone II when the oxidizer in zone I remains unchanged. Both the average combustion efficiency and the chamber head thermal protection need to be considered in the design of axial injector patterns. Research results of this paper provide an important reference for the design of high performance injector patterns of hybrid rocket motor.

    Highlights Effects of oxidizer flow distribution on hybrid rocket motor performance are studied. Steady two-phase flow simulations for various injector patterns are conducted. Adding oxidizer in zone III is good for thermal environment of the chamber head. Relative position of fuel inner surface and oxidizer affects fuel regression rates. When zone I is fixed, combustion efficiency raises with oxidizer in zone II adding.


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    Titel :

    Numerical analysis of the hybrid rocket motor with axial injection based on oxidizer flow distribution


    Beteiligte:
    Tian, Hui (Autor:in) / Jiang, Xianzhu (Autor:in) / Yu, Ruipeng (Autor:in) / Zhu, Hao (Autor:in) / Zhang, Yuanjun (Autor:in) / Cai, Guobiao (Autor:in)

    Erschienen in:

    Acta Astronautica ; 192 ; 245-257


    Erscheinungsdatum :

    2021-12-15


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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