Patent ID: 8549832
Filing Date: 2013-10-08
Classification: B64D,F02C,F05D,Y02T

Abstract:
1. A nacelle for installation at an inlet to an aircraft engine, the nacelle comprising: an inlet lip defining a leading edge of the nacelle and having a cross-sectional shape and oppositely-disposed exterior and interior surfaces, the inlet lip having a laminate construction from the interior surface to the exterior surface thereof, the laminate construction comprising a plurality of structural laminae and an anti-icing system; the anti-icing system defining the interior surface of the inlet lip and adapted to remove and prevent ice buildup on at least the inlet lip of the nacelle, the anti-icing system comprising a plurality of electrical insulation laminae and a plurality of heating elements within the laminate construction of the inlet lip, each of the additional heating elements being separated from the structural laminae of the inlet lip by the insulation laminae, each of the electrical insulation laminae and the heating elements having a cross-sectional shape that conforms to the cross-sectional shape of the inlet lip at the interior surface, the heating element comprising carbon nanotubes oriented and arranged to conduct electrical current through the heating element; and Means for passing an electrical current through the heating element to cause Joule heating of the heating element and heating of the inlet lip by thermal conduction from the interior surface to the exterior surface of the inlet lip.