In the present study, attempts were made to investigate the effect of the protrusion configuration on the performance and combustion stability behavior of the hybrid rocket motor. The protrusion configurations used for study include circular, star, multi-hole and fin. All the protrusion configurations were tested by placing at 0.7X/L location in a hybrid rocket motor. The wax and gaseous oxygen were used as a fuel and oxidizer, respectively. The regression rate and combustion efficiency were improved upon inserting the protrusion in hybrid rocket motor. Among the protrusion configurations, multi-hole case showed the highest improvement in regression rate and combustion efficiency. The hybrid rocket with/without protrusion case exhibited the first and second longitudinal acoustic modes which are dominant throughout the combustion. Upon inserting the protrusion, the stability of the combustion was improved significantly. Among all the protrusion cases, the star case exhibited the higher stable combustion. The frequency range of longitudinal acoustic modes was changing while changing the protrusion configuration.


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    Titel :

    Effect of Protrusion Configuration on Combustion Stability of Hybrid Rocket Motor


    Weitere Titelangaben:

    Lect.Notes Mechanical Engineering


    Beteiligte:
    Sivaramakrishna, Gullapalli (Herausgeber:in) / Kishore Kumar, S. (Herausgeber:in) / Raghunandan, B. N. (Herausgeber:in) / Dinesh, Mengu (Autor:in) / Kumar, Rajiv (Autor:in)


    Erscheinungsdatum :

    24.07.2022


    Format / Umfang :

    15 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch







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