CPC F02C 7/36 (2013.01) [F16H 1/36 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2260/40311 (2013.01)] | 10 Claims |
1. An aircraft turbine engine, comprising:
a turbine shaft having a first axis of rotation,
a propulsion propeller connected to a propeller shaft having a second axis of rotation parallel to and spaced from the first axis, and
a mechanical reduction gear coupled to the turbine shaft and configured to drive in rotation the propeller shaft, the reduction gear comprising a sun gear, a ring gear, and at least two planet gears meshed with the sun gear and the ring gear,
wherein the turbine shaft is connected to the sun gear,
wherein the propeller shaft is secured to the ring gear which comprises an internal toothing,
wherein each of the planet gears comprises a first external toothing which is located outside the ring gear and which is meshed with an external toothing of the sun gear,
wherein each of the planet gears comprises a second external toothing which is located inside the ring gear and which is meshed with the internal toothing of the ring gear,
wherein the sun gear and the planet gears are located below a horizontal plane passing through the second axis,
and wherein the turbine engine further comprises an equipment comprising a shaft carrying a pinion, wherein the pinion is meshed with the toothing of the ring gear and located above the horizontal plane.
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