System for deicing the nose cone of an aircraft turbojet with oil

1. A system for deicing the nose cone of an aircraft turbojet, said turbojet having a bearing which supports, in rotation and in thrust, a hollow low pressure compressor shaft of axis Z-Z of the engine, said low-pressure compressor shaft having slots and inter-slot spaces, two slots being separated by an inter-slot space, said bearing being lubricated with oil by two nozzles located outside the compressor shaft, said system comprises:

a feed tube fastened to the nose cone of the engine, said feed tube connecting the low-pressure compressor shaft to the engine nose cone and having a radius r;

a skin lining the wall of the engine nose cone, leaving a passage for circulation of the oil;

a plurality of radial oil-return tubes placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing; and

a centrifugal oil recovery scoop provided between the bearing and the low-pressure shaft,

wherein, when one of said nozzles faces one of said slots, oil passes through said slot toward said nose cone,

wherein, when one of said nozzles faces one of said inter-slot spaces, oil is reflected by said inter-slot space and picked up by the centrifugal scoop and directed under effect of a centrifugal force toward channels for lubricating said bearing, and

wherein a return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube.

2. A system for deicing the nose cone of an aircraft turbojet, said turbojet having a bearing which supports, in rotation and in thrust, a hollow low pressure compressor shaft of axis Z-Z of the engine, said bearing being lubricated with oil by two nozzles located outside the compressor shaft, said system comprises:

a feed tube fastened to the nose cone of the engine, said feed tube connecting the low-pressure compressor shaft to the engine nose cone and having a radius r;

a skin lining the wall of the engine nose cone, leaving a passage for circulation of the oil;

a plurality of radial oil-return tubes placed between the most eccentric part of the skin relative to the Z-Z axis and the bearing, for returning the oil to the bearing; and

wherein a return of the oil into the bearing is located at a distance R from the Z-Z axis larger than the radius r of the feed tube, and

wherein the low-pressure compressor shaft has an even number of slots separated by an even number of inter-slot spaces, the nozzles being directed toward the slots and toward the nose cone so that the oil jet from the nozzles can pass through them, the nozzles being placed relative to these slots in such a way that one of the nozzles starts to eject oil into a slot at the moment when the jet from the other nozzle starts to be reflected by an inter-slot space.

3. The deicing system as claimed in claim 2 , wherein angles of inclination of the nozzles relative to the Z-Z axis of the low-pressure compressor shaft is between 5° and 30°.

4. The deicing system as claimed in claim 3 , wherein the feed tube has a conicity of between 0° and 2°, the largest-diameter portion of the cone being located on the engine nose cone side.

5. The deicing system as claimed in claim 4 , wherein the feed tube includes a projection in its part located toward the low-pressure compressor shaft.

6. The system as claimed in claim 5 , which includes a centrifugal scoop for recovering oil that has been reflected by the inter-slot spaces of the low-pressure shaft and to direct this oil toward the bearing.

7. The deicing system as claimed in claim 6 , wherein, should a flow rate of oil in the passage for oil circulation be less than a flow rate from a nozzle, the oil spills over the projection and rejoins the centrifugal scoop under the effect of the centrifugal force.

8. An aircraft turbojet, comprising a system for deicing according to claim 2 .