Pre-assembly method for an aircraft turbomachine

Patent metadata

Field	Value
Publication number	US-12103709-B2
Application number	US-202318311414-A
Country	US
Kind code	B2
Filing date	May 3, 2023
Priority date	May 4, 2022
Publication date	Oct 1, 2024
Grant date	Oct 1, 2024

Abstract

A pre-assembly method for an aircraft turbomachine, including preliminarily assembling, outside the turbomachine, the following components with each other: a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of the at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of the at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.

First claim

The invention claimed is:

1. A pre-assembly method for an aircraft turbomachine, comprising preliminarily assembling, outside the turbomachine, the following components with each other:
a reduction gear configured to transmit a rotation between at least two rotors of the aircraft turbomachine while modifying a speed and torque ratio from one to another one of said at least two rotors, the reduction gear comprising a stator member,
a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors,
a bearing support provided with a flange located radially outside the bearing support, the flange being configured to receive fixing elements for dismountably connecting to a casing of the turbomachine,
at least one bearing mounted on the bearing support and configured to rotatably support the shaft, and
an attachment element extending from the stator member to the bearing support so as to fix the stator member to the bearing support, wherein the attachment element extends from one side of the reduction gear to another side of the reduction gear.

2. The method according to claim 1 , comprising shrink-fitting the at least one bearing on at least one of the shaft and the bearing support.

3. The method according to claim 1 , wherein the bearing support comprises an element for assembly with a casing of the aircraft turbomachine.

4. The method according to claim 1 , wherein the components further comprise a second shaft kinematically coupled to the reduction gear.

5. The method according to claim 4 , wherein the second shaft and the shaft are provided on either side of the reduction gear.

6. The method according to claim 1 , wherein the shaft has an abutment for an axial positioning of the corresponding rotor, the abutment being located such that the rotor is kept away from the at least one bearing.

7. The method according to claim 1 , wherein the at least one bearing is chosen among a ball bearing, a roller bearing or a tapered roller bearing.

8. The method according to claim 1 , wherein the rotor kinematically coupled to the shaft is a fan or a propeller of the aircraft turbomachine.

9. The method according to claim 1 , wherein at least some of the components have elements for fixing to parts of the aircraft turbomachine distinct from said components, the fixing elements all being provided on the same side of a module comprising the pre-assembled components.

10. A method for assembling an aircraft turbomachine, comprising obtaining a first turbomachine portion comprising a rotor, mounting the module obtained by the method of claim 9 on the first portion, and assembling a second portion comprising a rotor with the shaft of the module.

11. A module for an aircraft turbomachine, made by the pre-assembly method according to claim 1 , comprising the following components assembled with each other:
the reduction gear configured to transmit a rotation between the at least two rotors of the aircraft turbomachine while modifying the speed and torque ratio from one to another one of said at least two rotors, the reduction gear comprising a stator member,
the shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors,
the bearing support,
the at least one bearing mounted on the bearing support and configured to rotatably support the shaft, and
the attachment element extending from the stator element to the bearing support so as to fix the stator member to the bearing support, wherein the attachment element extends from one side of the reduction gear to another side of the reduction gear.

12. The module for an aircraft turbomachine according to claim 11 , the module further comprising first fixing elements configured to fix the shaft to a first one of said rotors, second fixing elements configured to fix the reduction gear to a second one of said rotors, and third fixing elements configured to fix the bearing support to a casing of the aircraft turbomachine.

13. The module for an aircraft turbomachine according to claim 12 , wherein the first fixing elements are provided at one end of the shaft opposed to the reduction gear.

14. The method of claim 1 , wherein the flange protrudes radially outwardly of the bearing support.

15. The method of claim 1 , wherein the stator member is a ring gear of the reduction gear.

16. A pre-assembly method for an aircraft turbomachine, comprising preliminarily assembling, outside the turbomachine, the following components with each other:
a reduction gear configured to transmit a rotation between at least two rotors of the aircraft turbomachine while modifying a speed and torque ratio from one to another one of said at least two rotors, the reduction gear comprising a stator member, wherein the stator member is a ring gear of the reduction gear,
a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors,
a bearing support,
at least one bearing mounted on the bearing support and configured to rotatably support the shaft, and
an attachment element extending from the stator member to the bearing support so as to fix the stator member to the bearing support, wherein the attachment element extends from one side of the reduction gear to another side of the reduction gear.

Assignees

• Safran Trans Systems

Inventors

• Simon Adrien Louis
• Beck Guillaume Julien
• Douy Yohan
• Peltier Jordane Emile André
• Seban Jérémy David

Classifications

• F16H1/28

  with gears having orbital motion · CPC title

• F02C7/36 Primary

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F01D25/16

  Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F05D2230/70

  Disassembly methods · CPC title