A cooling system for an aircraft capable of travelling at hypersonic speeds includes an inlet (22) configured to receive a first medium and a thermodynamic device (24) fluidly connected to the inlet (22). The thermodynamic device (24) includes at least one turbine and a compressor operably coupled via a shaft. An outlet of the at least one turbine is directly fluidly connected to an inlet of the compressor. An electric generator (34) is operably coupled to the at least one turbine.


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    Titel :

    ULTRA-HIGH TEMPERATURE TURBO GENERATOR


    Weitere Titelangaben:

    ULTRAHOCHTEMPERATURTURBOGENERATOR
    TURBOGÉNÉRATEUR À ULTRA-HAUTE TEMPÉRATURE


    Beteiligte:
    WATSON KIREI O (Autor:in) / BRUNO LOUIS J (Autor:in) / LIAO XIAOHONG (Autor:in) / PESS MATTHEW L (Autor:in) / GOSSE KAYLA (Autor:in) / ERNST JEFF (Autor:in) / SPIERLING TODD A (Autor:in)

    Erscheinungsdatum :

    12.02.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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