Turbomachine comprising a speed reduction gear integrating an electric machine

Patent metadata

Field	Value
Publication number	US-12516634-B2
Application number	US-202418426683-A
Country	US
Kind code	B2
Filing date	Jan 30, 2024
Priority date	Jan 31, 2023
Publication date	Jan 6, 2026
Grant date	Jan 6, 2026

Abstract

An aircraft turbomachine includes a speed reduction gear having an input pinion connected to a power shaft and an output pinion connected to a propeller shaft. An electric machine is integrated into the speed reduction gear and is configured to provide electrical power to the propeller shaft or to take mechanical power from the propeller shaft. The electric machine has a rotor driven in rotation about an axis coaxial with a longitudinal axis of the turbomachine and a stator connected to a casing. The input pinion includes an input shaft offset from an axis of the output pinion, and the speed reduction gear has two parallel intermediate transmission lines configured to transmit the torque from the input pinion to the output pinion to drive the rotor in rotation.

First claim

The embodiments of the disclosure in which an exclusive property or privilege is claimed are defined as follows:

1 . A turbomachine having a longitudinal axis and comprising:
a power shaft, a propeller shaft centered on the longitudinal axis, at least one speed reduction gear, the at least one speed reduction gear comprising an input pinion connected to the power shaft and an output pinion connected to the propeller shaft, and at least one electric machine which is integrated into the speed reduction gear and which is configured to provide electrical power to the propeller shaft or to take mechanical power from the propeller shaft, the at least one electric machine comprising a rotor configured to be driven in rotation about an axis coaxial with the longitudinal axis and a stator connected to a casing of the turbomachine, wherein the input pinion comprises an input axis offset relative to an axis of the output pinion, which is coaxial with the longitudinal axis, and the speed reduction gear comprises at least two intermediate transmission lines that are parallel and are configured to transmit the torque from the input pinion to the output pinion, which is configured to drive the rotor in rotation, wherein the speed reduction gear comprises a drive wheel which comprises a first external toothing meshing with an internal toothing of the output pinion and a second external toothing meshing with an external toothing of a complementary pinion.

2 . The turbomachine according to claim 1 , wherein each intermediate transmission line comprises a first intermediate pinion mounted to rotate about an axis of rotation and comprising a first toothing configured to mesh with an external toothing of the input pinion.

3 . The turbomachine according to claim 1 , wherein each intermediate transmission line comprises a second intermediate pinion mounted to rotate about an axis of rotation and comprising a second toothing configured to mesh with an external toothing of the output pinion.

4 . The turbomachine according to claim 1 , wherein the rotor is hollow and is passed through at least in part by the propeller shaft.

5 . The turbomachine according to claim 1 , wherein the stator extends radially outside the rotor.

6 . The turbomachine according to claim 1 , wherein an air inlet is arranged below the speed reduction gear in a vertical direction perpendicular to the longitudinal axis.

7 . A turbomachine having a longitudinal axis and comprising:
a power shaft, a propeller shaft centered on the longitudinal axis, at least one speed reduction gear, the at least one speed reduction gear comprising an input pinion connected to the power shaft and an output pinion connected to the propeller shaft, and at least one electric machine which is integrated into the speed reduction gear and which is configured to provide electrical power to the propeller shaft or to take mechanical power from the propeller shaft, the at least one electric machine comprising a rotor configured to be driven in rotation about an axis coaxial with the longitudinal axis and a stator connected to a casing of the turbomachine, wherein the input pinion comprises an input axis offset relative to an axis of the output pinion, which is coaxial with the longitudinal axis, and the speed reduction gear comprises at least two intermediate transmission lines that are parallel and are configured to transmit the torque from the input pinion to the output pinion, which is configured to drive the rotor in rotation, wherein the speed reduction gear comprises a drive wheel driven, on the one hand, by the output pinion and driving, on the other hand, by a complementary pinion mounted on the rotor, the complementary pinion of the rotor comprising an axis parallel to the axis of the propeller shaft, wherein the drive wheel comprising first teeth meshing with second teeth of the output pinion, wherein the rotor has a cylindrical body and the complementary pinion extending radially outside the cylindrical body of the rotor.

8 . The turbomachine according to claim 7 , wherein the drive wheel comprises a first external toothing meshing with an internal toothing of the output pinion and a second external toothing meshing with an external toothing of the complementary pinion.

9 . The turbomachine according to claim 7 , wherein the drive wheel has an upstream end engaging the output pinion and a downstream end engaging the complementary pinion, the complementary pinion being mounted to an upstream end of the rotor.

10 . A turbomachine having a longitudinal axis and comprising:
a power shaft, a propeller shaft centered on the longitudinal axis, at least one speed reduction gear, the at least one speed reduction gear comprising an input pinion connected to the power shaft and an output pinion connected to the propeller shaft, at least one electric machine which is integrated into the speed reduction gear and which is configured to provide electrical power to the propeller shaft or to take mechanical power from the propeller shaft, the at least one electric machine comprising a rotor configured to be driven in rotation about an axis coaxial with the longitudinal axis and a stator connected to a casing of the turbomachine, and a pitch change system having a shaft coupled to an end of the propeller shaft, the shaft of the pitch change system being arranged coaxially with the axis of the propeller shaft, wherein the input pinion comprises an input axis offset relative to an axis of the output pinion, which is coaxial with the longitudinal axis, and the speed reduction gear comprises at least two intermediate transmission lines that are parallel and are configured to transmit the torque from the input pinion to the output pinion, which is configured to drive the rotor in rotation.

11 . The turbomachine according to claim 10 , wherein the pitch change system is arranged at least partly inside the rotor.

Assignees

• Safran Trans Systems

Inventors

• Fernandez Maxime
• Douy Yohan
• Morelli Boris Pierre Marcel
• Peltier Jordane Emile André

Classifications

• F16H1/22

  with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title

• B64D35/024

  of series type · CPC title

• F05D2260/4031

  as in toothed gearing · CPC title

• B64C11/306

  specially adapted for contrarotating propellers · CPC title