Bypass engine with contrarotating turbine wheels including a reversing module
View Patent ↗A bypass aeronautical engine including a fan, an LP compressor, an HP compressor, a combustion chamber, an HP turbine, and at least one LP turbine stage is disclosed. The LP turbine stage includes a first movable bladed wheel carried by a first turbine shaft and a second movable bladed wheel turning in the opposite direction to the first wheel. The fan is driven by the second wheel via a second turbine shaft and by the first shaft via a module for reversing its direction of rotation. The reversing module includes two bevel pinions carried respectively by the first and second LP turbine shafts, and a reversing pinion.
1. An aeronautical engine comprising:
a fan;
a low pressure compressor and a high pressure compressor; a combustion chamber;
a high pressure turbine and at least one low pressure turbine stage, said low pressure turbine stage comprising a first movable bladed wheel carried by a first end of a first low pressure turbine shaft and a second movable bladed wheel carried by a first end of a second low pressure turbine shaft;
and a reversing module including a first bevel pinion connected to a second end of the first low pressure turbine shaft, a second bevel pinion connected to a second end of the second low pressure turbine shaft, and a reversing bevel pinion cooperating with the first and second bevel pinions;
wherein a rotation direction of the second wheel is opposite of a rotation direction of the first wheel,
wherein the fan is driven both by said first wheel via the first low pressure turbine shaft and by said second wheel via the second low pressure turbine shaft and by said first shaft via the reversing module, wherein the first bevel pinion and the second bevel pinion are the same size, and the first low pressure turbine shaft and second low pressure turbine shafts turn in absolute value at the same speed of rotation, and wherein the reversing bevel pinion rotates about a fixed axle which is connected to a static structure of the engine.
2. The aeronautical engine as claimed in claim 1 , wherein the reversing module is situated in the vicinity of the fan, below an inlet casing of the low pressure compressor.
3. The aeronautical engine as claimed in claim 1 , wherein a fixed turbine nozzle is positioned upstream of the first movable bladed wheel of the low pressure turbine stage.
4. The aeronautical engine as claimed in claim 1 , wherein blades of a turbine nozzle are oriented like blades of a turbine rotor and the blades of the first movable bladed wheel are oriented like vanes of a turbine stator.
5. The aeronautical engine as claimed in claim 3 , wherein blades of said turbine nozzle are oriented like blades of a turbine rotor and the blades of the first movable bladed wheel are oriented like vanes of a turbine stator.
6. The aeronautical engine as claimed in claim 1 , wherein blades of a turbine nozzle are oriented like vanes of a turbine stator and the blades of the second movable bladed wheel are oriented like blades of a turbine rotor.
7. The aeronautical engine as claimed in claim 3 , wherein blades of said turbine nozzle are oriented like vanes of a turbine stator and the blades of the second movable bladed wheel are oriented like blades of a turbine rotor.
8. The aeronautical engine as claimed in claim 1 , comprising a plurality of low pressure turbine stages, wherein the first bladed wheels for each low pressure turbine stage are connected mechanically to one another, and the second bladed wheels for each low pressure turbine stage are connected mechanically to one another.
9. The aeronautical engine as claimed in claim 1 , wherein the first and second low pressure turbine shafts each carry a bearing unit between which a ball bearing is arranged.
10. The aeronautical engine as claimed in claim 1 , in wherein the first and second low pressure turbine shafts each carry a bearing unit between which a roller bearing is arranged.
11. The aeronautical engine as claimed in claim 1 , wherein the first bevel pinion is carried by splines of the first low pressure turbine shaft and by a bearing unit mounted on a ball bearing connected to the structure of the engine.
12. The aeronautical engine as claimed in claim 1 , wherein the second bevel pinion is carried by splines of the second low pressure turbine shaft and by a bearing unit mounted on a roller bearing connected to the structure of the engine.
13. The aeronautical engine as claimed in claim 1 , wherein the fixed axle supplies lubrication to the first and second pinions.
14. The aeronautical engine as claimed in claim 1 , wherein the first and second bevel pinions and the reversing bevel pinion are provided in an enclosure of a bearing unit of the low pressure compressor.