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.
GAS TURBINE ENGINE FAN SECTION WITH A REMOVABLE FILM MATERIAL AND CORRESPONDING METHOD OF PROTECTING SURFACES IN A FAN SECTION
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
2020-05-06
Patent
Elektronische Ressource
Englisch
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