Aircraft engine comprising a bearing between two concentric shafts

Patent metadata

Field	Value
Publication number	US-11021992-B2
Application number	US-201816488781-A
Country	US
Kind code	B2
Filing date	Feb 26, 2018
Priority date	Feb 28, 2017
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

An inter-shaft bearing is supported by a support including a solid rigid body which is non-deformable during normal operation, but which can break in the event of an excessive stress, such as a blade failure. A damper included in the support limits the movements between the two shafts and prevents excessive instability.

First claim

The invention claimed is:

1. An aircraft engine comprising two concentric shafts extending in an engine axial direction; a bearing supporting a first of the shafts and a support connecting the bearing to a second of the shafts, the support comprises a mechanical decoupler, including a rigid body, in abutment through two opposite faces in an engine radial direction, perpendicular to an axial direction, on two abutting faces integral with the second shaft and the bearing respectively, the rigid body being able to be ruptured at a load threshold to be transmitted between the abutting faces, and a damper body housed in a cavity of the support delimited by the abutting faces.

2. The engine according to claim 1 , wherein the rigid body includes two parts, each delimiting the cavity between the abutting faces.

3. The engine according to claim 1 , wherein the decoupler is annular.

4. The engine according to claim 1 , wherein the rigid body is of brittle material.

5. The engine according to claim 4 , wherein the brittle material is a ceramic.

6. The engine according to claim 1 , wherein the rigid body extends in at least one of the radial direction with a slope in the axial direction or an angular direction perpendicular to the axial direction and to the radial direction.

7. The engine according to claim 6 , wherein the rigid body comprises two portions successively in the radial direction, the slope of a first of said portions being different from the slope of a second of said portions.

8. The engine according to claim 1 , wherein the rigid body is limited by an empty volume in the axial direction.

9. The engine according to claim 1 , wherein the damper body is pre-stressed in the radial direction between the abutting faces.

10. The engine according to any of claim 1 , wherein the mechanical decoupler further comprises side flanges extending between the second shaft and the bearing, the rigid body and the damper body being placed between the flanges.

11. The engine according to claim 10 , wherein the flanges are flexible.

12. The engine according to claim 1 , wherein the engine includes a state in which respective portions of the bearing are respectively integral with the shafts and a state in which one of said portions is movable in the radial direction with respect to the shaft with which one of said portions is integral and dampened with respect to said shaft.

Assignees

• Safran Aircraft Engines

Inventors

• Benyamin Serge

Classifications

• F05D2240/50

  Bearings · CPC title

• F01D25/164

  Flexible supports; Vibration damping means associated with the bearing · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2240/54

  Radial bearings · CPC title

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title