Patent ID: 7780117
Filing Date: 2010-08-24
Classification: B64D,F02C,F05D

Abstract:
1. A nacelle inlet lip for an aircraft engine, comprising a structural body and an ice protection system; the structural body defining the leading edge of the aircraft engine and having an inner wall portion defining an inlet for the aircraft engine; the inner wall portion having a plurality of inner zones located sequentially aft from the leading edge, these inner zones including an inner fore zone located just aft of the leading edge, an inner mid zone located aft of the inner fore zone, and an inner aft zone located aft of the inner mid zone; the ice protection system having an ice-protector associated with each of the inner zones; each ice-protector being independently controllable to allow the inner zones to be operated in different modes, different power levels, and/or different time intervals; the inner mid zone being operable in an anti-icing mode, wherein power is continuously supplied to its ice-protector to prevent ice from forming on this zone, and a deicing mode, wherein power is intermittently supplied to its ice-protector to remove ice formed on this zone.