Turbojet with step-down mechanism
Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.
1. A turbojet engine comprising:
a fan,
a compressor,
a combustion chamber and
a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear,
wherein the first reduction gear is rotatably coupled to i) the turbine via a turbine shaft, ii) the fan via a fan shaft and iii) the second reduction gear via a reduction shaft and wherein the second reduction gear is coupled to the compressor via a compressor shaft such that the compressor shaft is rotationally coupled to the turbine shaft via the first reduction gear, the reduction shaft and the second reduction gear;
the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.
2. The turbojet engine according to claim 1 , wherein the bearing is a roller bearing.
3. The turbojet engine according to claim 1 , wherein the turbojet engine is a turbofan engine comprising a casing disposed downstream of the fan and separating a primary flowpath from a secondary flowpath, and the bearing is supported by said casing.
4. The turbojet engine according to claim 3 , further comprising a fan bearing arranged between the fan shaft and the casing.
5. The turbojet engine according to claim 3 , comprising a compressor bearing arranged between the compressor shaft and the casing.
6. The turbojet engine according to claim 1 , comprising a second bearing arranged to support the reduction shaft.
7. The turbojet engine according to claim 1 , comprising an inter-shaft bearing arranged between the compressor shaft and the turbine shaft.
8. The turbojet engine according to claim 1 , wherein said bearing is arranged radially outside the compressor shaft, the turbine shaft and the reduction shaft.
9. The turbojet engine according to claim 1 , comprising a compressor bearing arranged between the compressor shaft and a structural member downstream of the compressor.
10. The turbojet engine according to claim 1 , wherein the reduction shaft is a planet carrier common to the first reduction gear and to the second reduction gear.
11. The turbojet engine according to claim 6 , wherein the second bearing is a roller bearing.