ELECTRICAL ASSISTED ICE REDUCTION MECHANISMS FOR GAS TURBINE ENGINE OR AIRCRAFT
A gas turbine engine is provided. The gas turbine engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and togethe...
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Format: | Patent |
Sprache: | eng |
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Zusammenfassung: | A gas turbine engine is provided. The gas turbine engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; and one or more graphene layers coupled to, or integrated into, a portion of the gas turbine engine, wherein the one or more graphene layers are configured to reduce ice buildup or ice formation. The one or more graphene layers include graphene or an allotrope thereof. |
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