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

B - Operations, Transporting

64

D

B64D 15/04 (2006.01) B64D 29/00 (2006.01)

Patent

CA 2725696

An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross- sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall.

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