Lip unit for an electrically deiced turbojet engine nacelle
A lip assembly of a turbojet engine nacelle is equipped with at least one electric de-icing system. The lip assembly includes at least one electric heating member, electrically powered through at least one power conductor. Each power-supply conductor is associated with a neutral conductor or “ground” arranged in a regrouped manner adjacent to a corresponding power-supply conductor.
1. An electric de-icing system for a lip assembly of a turbojet engine nacelle of an aircraft comprising:
a plurality of electrical heating groups arranged around a periphery of the lip assembly, each group comprising a plurality of electrical heating members, each of said groups being electrically powered through a plurality of power-supply conductors and a plurality of neutral conductors arranged in pairs, wherein each of the plurality of electrical heating members define a ribbon shape having two parallel paths, one parallel path for a neutral conductor and another parallel path for the corresponding power-supply, wherein the parallel paths are connected to a pair of power-supply conductors and neutral conductors on a common side of the groups of electrical heating members such that one pair of power-supply conductors and neutral conductors is connected to at least two groups of electrical heating members.
2. The lip assembly according to claim 1 , wherein the plurality of electrical heating members are powered by an alternative current.
3. The lip assembly according to claim 2 , wherein the plurality of electrical heating members are powered by three-phase current.
4. The lip assembly according to claim 1 , wherein the electrical heating members are a heating carpet or ribbon.
5. The lip assembly according to claim 1 , wherein each electrical heating member comprises at least a resistive coil arranged between the power-supply conductor and the neutral conductor associated therewith.
6. The lip assembly according to claim 5 , wherein the resistive coil substantially extends along a length of the electrical heating member.
7. A turbojet engine nacelle comprising a lip assembly according to claim 1 .