Electric power supply circuit for a turbojet engine nacelle
The present invention relates to an electric power supply circuit ( 1 ) for a turbojet engine nacelle including at least one electric generator ( 2 ) mechanically connected to the shaft of a turbojet engine, said generator being capable of directly supplying electric power to a first electric power device other than a simple monitoring or supervising unit, characterized in that said generator is capable of directly supplying electric power to at least one second electric power device other than a monitoring or supervising unit, as well as to a nacelle including such an electric circuit.
1. An electric power supply circuit for a turbojet engine nacelle, comprising:
at least one electric generator mechanically connected to a shaft of the turbojet engine, said generator being internal to the nacelle and directly supplying electric power without passing through an airplane network to a first electric power device other than a simple monitoring or supervising unit;
wherein said generator directly supplies electric power without passing through the airplane network to at least one second electric power device other than a monitoring or supervising unit, and
wherein one of the electric power devices is an electric deicing device and the other electric power device is a thrust reverser device.
2. The electric power supply circuit according to claim 1 , wherein the thrust reverser device comprises an electrodynamic braking output line able to at least partially power the electric deicing device.
3. The electric power supply circuit according to claim 1 , wherein the electric power devices further comprise a variable nozzle device.
4. The electric power supply circuit according to claim 1 , wherein the generator is situated at an accessory gear box of the turbojet engine.
5. The electric power supply circuit according to claim 1 , further comprising at least two electric generators for safety reasons.
6. The electric power supply circuit according to claim 1 , wherein at least one electric power device is associated with a converter, of the AC-AC type.
7. The electric power supply circuit according to claim 1 wherein at least one electric power device comprises at least one control line coming from an airplane monitoring unit.
8. A turbojet engine nacelle, comprising at least one electric power supply circuit according to claim 1 .
9. The electric power supply circuit according to claim 1 , wherein the electric generator is of a generator/starter type.
10. The electric power supply circuit according to claim 9 , wherein the electric generator in a starter mode can be powered by a return line of one of the electric power devices.
11. The electric power supply circuit according to claim 1 , wherein at least one of the electric power devices operates in direct current, owing to at least one direct current motor.
12. The electric power supply circuit according to claim 11 , wherein a converter makes it possible to steer the associated electric power device by regulating the power supply of the device via a nacelle monitoring and/or airplane monitoring unit.
13. The electric power supply circuit according to claim 12 , wherein the generator is steered by at least one electric monitoring unit of the nacelle.
14. The electric power supply circuit according to claim 12 , wherein the electric generator can be steered using supervisory signals coming from the first and/or second electric power devices via the monitoring unit of the nacelle.
15. The electric power supply circuit according to claim 1 , further comprising at least one electric switch that can be controlled by an airplane monitoring unit.
16. The electric power supply circuit according to claim 15 , wherein each electric power device powered by the generator is associated with a steerable switch.
17. A method for controlling an electronic power supply circuit for a turbojet engine nacelle, the method comprising:
directly supplying electric power without passing through an airplane network to a first electric power device other than a simple monitoring or supervising unit by at least one electric generator which is internal to the nacelle and mechanically connected to a shaft of the turbojet engine;
directly supplying electric power without passing through the airplane network to at least one second electric power device other than a monitoring or supervising unit by said generator, wherein one of the electric power devices is an electric deicing device and the other electric power device is a thrust reverser device; and
suspending the electric deicing device during a few seconds of operation of the thrust reverser device such that the at least one electric generator is sized according to a maximum power between the electric deicing device and the thrust reverser device.