Post FBO windmilling bumper

Patent metadata

Field	Value
Publication number	US-9777592-B2
Application number	US-201314138821-A
Country	US
Kind code	B2
Filing date	Dec 23, 2013
Priority date	Dec 23, 2013
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing. The bumper further has an axially forwardly facing surface which is axially spaced by a predetermined axial fore gap from a first flange projecting radially outwardly from a front end portion of the outer race of the bearing. The first flange of the outer race is axially trapped between the stator structure and the bumper. After decoupling, the bearing is free to axially and radially move within the radial gap and the axial fore gap.

First claim

What is claimed is:

1. A turbofan gas turbine engine comprising: a stator structure, a bearing assembly coupled to the stator structure by a shear connection, the bearing assembly including a bearing for rotatably supporting about a central axis a shaft assembly carrying a propulsive fan rotor; and a bumper mounted to the stator structure independently of the bearing assembly, the bumper encircling the bearing and having a radially inwardly facing surface spaced apart from a radially outer surface of an outer race of the bearing to define a radial gap between them, the bumper configured to restrain, in use, at least radial outward movement of the fan rotor in the event of a failure of the shear connection, and wherein the radial gap is sized to, in use, limit vibratory modes transmitted to the turbofan gas turbine engine caused by rotation of the shaft assembly after the failure of the shear connection, wherein the stator structure comprises an axially rearwardly projecting spigot projecting in a downstream direction relative to a flow of air through the propulsive fan rotor, a front end of the outer race of the bearing being axially engaged with the stator structure on the axially rearwardly projecting spigot, and wherein the outer race is free to move axially in the downstream direction relative to the bumper by a distance sufficient to allow the outer race to axially move out of engagement from the axially rearwardly projecting spigot upon failure of the shear connection.

2. The turbofan defined in claim 1 , wherein the bumper further comprises an axially forwardly facing surface which is axially spaced by a predetermined axial fore gap from a first flange projecting radially outwardly from a front end portion of the outer race of the bearing, the first flange of the outer race being axially trapped between a flange of the stator structure of the turbofan gas turbine engine and the forwardly facing surface of the bumper.

3. The turbofan defined in claim 2 , wherein said axial fore gap is sized to allow the outer race to come off the spigot when a decoupler releases the outer race from the stator structure.

4. The turbofan defined in claim 3 , wherein the outer race of the bearing has a second flange projecting radially outwardly from a rear end portion thereof, said second flange being spaced axially rearwardly by a predetermined axial aft gap from an axially rearwardly facing surface of the bumper, the bearing being free to move within said axial aft gap after decoupling.

5. The turbofan defined in claim 2 , wherein a decoupler normally connects the first flange of the bearing outer race to a radially inwardly projecting flange provided on the stator structure axially forwardly of the bearing, the first flange of the outer race and the radially inwardly projecting flange on the stator structure extending in opposite directions to provide an inverted flange mounting arrangement.

6. The turbofan defined in claim 5 , wherein the decoupler comprises a set of frangible fasteners extending through registering holes defined in the first flange and the radially inwardly projecting flange.

7. The turbofan defined in claim 2 , wherein the bumper has a mounting flange projecting radially outwardly from a containment ring portion, the mounting flange being bolted at its radially outer end to the stator structure independently from the bearing.

8. The turbofan defined in claim 2 , wherein the bearing is a thrust bearing.

9. The turbofan defined in claim 1 , wherein the radial gap has a radial thickness sized to prevent the rotor from approaching its natural frequency of vibration when rotating at windmilling speed.

Assignees

• Pratt & Whitney Canada

Inventors

• Denis David
• Bonniere Philippe
• Kojovic Milica
• Korshikov Oleg
• Raykowski Lena
• Wojtyczka Czeslaw

Classifications

• F16C19/06

  with a single row or balls · CPC title

• F01D25/164

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

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F16C2360/23

  Gas turbine engines · CPC title

• F01D21/045 Primary

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