A fan section to be incorporated into a gas turbine engine has a rotor and a plurality of fan blades. The fan blades deliver air into a bypass duct defined inwardly of the nacelle and into a core engine. There are static vanes inward of the nacelle. A surface of the fan section is provided with a removable film material. A gas turbine engine and a method of refurbishing a surface are also disclosed.


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    Title :

    GAS TURBINE ENGINE FAN SECTION WITH A REMOVABLE FILM MATERIAL AND CORRESPONDING METHOD OF PROTECTING SURFACES IN A FAN SECTION


    Additional title:

    BLÄSERABSCHNITT EINES GASTURBINENMOTORS MIT EINEM LÖSBAREN FILMMATERIAL UND ZUGEHÖRIGES VERFAHREN ZUM OBERFLÄCHENSCHUTZ IN EINEM BLÄSERABSCHNITT
    SECTION DE SOUFFLANTE POUR MOTEUR À TURBINE À GAZ AVEC UN FILM AMOVIBLE ET PROCÉDÉ DE PROTECTION DES SURFACES DANS UNE SECTION DE SOUFFLANTE


    Contributors:

    Publication date :

    2020-05-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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





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