A heating system for a gas turbine engine (10, Fig 1) comprising a nanomaterial heating element 502, an ice detection system (Fig 4), and a heater controller (Fig 4). The ice detection system is configured to transmit a signal to the heater controller to apply a current to the nanomaterial heating element. The nanomaterial heating element may comprise carbon nanotubes. The ice detection system may be based upon an input from a pilot or a sensor which is comprised within the gas turbine engine or airframe.


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    Titel :

    Heating system


    Beteiligte:

    Erscheinungsdatum :

    2022-06-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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