Patent ID: 8382039
Filing Date: 2013-02-26
Classification: 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; an annular-shaped cavity within the nacelle adjacent and delimited in part by an interior surface of the inlet lip; and an anti-icing system within the cavity, the anti-icing system comprising a manifold with a cross-sectional shape that conforms to the interior surface of the inlet lip comprising a U-shaped first wall that closely conforms and faces the interior surface of the inlet lip and a second wall that closely conforms to the first wall, and means for conducting air within an interior cavity defined by the first wall and the second wall of the manifold to cause heating of the inlet lip via the first wall, wherein the air conducting means does not fill the cavity within the nacelle with the air conducted thereby.