Turbomachine nacelle and anti-icing system and method therefor

Details Turbomachine nacelle and anti-icing system and method therefor Turbomachine nacelle and anti-icing system and method therefor

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/047 (2006.01) B64D 15/12 (2006.01)

Patent

CA 2725891

An anti-icing system (60,80) and method for an aircraft engine nacelle (50,70). The nacelle (50,70) has an inlet lip (56,76) that defines a leading edge of the nacelle (50,70) and has a cross-sectional shape and oppositely-disposed exterior and interior surfaces (58,59). An anti-icing system (60,80) contacts at least the inlet lip (56,76) of the nacelle (50,70). The anti-icing system (60,80) includes at least one heating element (62,82) having a cross-sectional shape that conforms to the cross- sectional shape of the inlet lip (56,76) and in which carbon nanotubes are oriented and arranged to conduct electrical current through the heating element (62,82). Passing an electrical current through the heating element (62,82) causes Joule heating of the heating element (62,82) and heating of the inlet lip (56,76) by thermal conduction.

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