Aircraft engine nacelle ice protection system
First Claim
Patent Images
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.
2 Assignments
0 Petitions
Accused Products
Abstract
A nacelle inlet lip (22) for an aircraft engine (16) comprises a structural body (30) and an ice protection system (60). The ice protection system (60) comprises a plurality of ice-protectors (62, 64, 66) independently controllable to allow inner zones (52, 54, 56) to be operated in different modes, different power levels, different time intervals and/or different energy amounts. In this manner, an inner aft zone (52), an inner mid zone (54), and an inner aft zone (56) can be anti-iced and/or de-iced to best preserve desired airflow patterns, to minimize ice particle shed size, and to optimize power consumption.
45 Citations
20 Claims
-
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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19)
-
-
20. An ice-susceptible portion of an aircraft, comprising a structural body and an ice protection system;
-
the structural body defining a leading edge and having a wall portion with a plurality of zones located sequentially aft from the leading edge, these zones including a fore zone located just aft of the leading edge, a mid zone located aft of the fore zone, and an zone located aft of the mid zone; the ice protection system having an ice-protector associated with each of the zones; each ice-protector being independently controllable to allow the zones to be operated in different modes, different power levels, and/or different time intervals; the ice protector associated with the fore zone operable in an anti-icing mode wherein power is continuously supplied to this ice-protector to prevent ice from forming on this zone, the ice protector associated with the mid zone operable in an anti-icing mode wherein power is continuously supplied to this ice-protector to prevent ice from forming on this zone and is also operable in a deicing mode wherein power is intermittently supplied to this ice-protector to remove ice formed on this zone, and the ice protector associated with the aft zone operable in a de-icing mode wherein power is intermittently supplied to this ice-protector to remove ice formed on this zone.
-
Specification