An anti-icing system for a gas turbine engine comprises a closed circuit containing a change-phase fluid, at least one heating component for boiling the change-phase fluid, the anti-icing system configured so that the change-phase fluid partially vaporizes to a vapour state when boiled by the at least one heating component. The closed circuit has an anti-icing cavity adapted to be in heat exchange with an anti-icing surface of the gas turbine engine for the change-phase fluid to release heat to the anti-icing surface and condense. A feed conduit(s) has an outlet end in fluid communication with the anti-icing cavity to feed the change-phase fluid in vapour state from heating by the at least one heating component to the anti-icing cavity, and at least one return conduit having an outlet end in fluid communication with the anti-icing cavity to direct condensed change-phase fluid from the anti-icing cavity to the at least one heating component. A method for heating an anti-icing surface of an aircraft is also provided.


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    Titel :

    ANTI-ICING SYSTEM FOR GAS TURBINE ENGINE


    Weitere Titelangaben:

    SYSTEME ANTIGIVRAGE POUR MOTEUR A TURBINE A GAZ


    Beteiligte:
    MENHEERE DAVID (Autor:in) / ALECU DANIEL (Autor:in)

    Erscheinungsdatum :

    2018-08-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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