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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    Title :

    ULTRA-HIGH TEMPERATURE TURBO GENERATOR


    Additional title:

    ULTRAHOCHTEMPERATURTURBOGENERATOR
    TURBOGÉNÉRATEUR À ULTRA-HAUTE TEMPÉRATURE


    Contributors:

    Publication date :

    2025-02-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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