Bearing preload using external gearbox reaction

Patent metadata

Field	Value
Publication number	US-11434784-B2
Application number	US-201916568812-A
Country	US
Kind code	B2
Filing date	Sep 12, 2019
Priority date	Sep 12, 2019
Publication date	Sep 6, 2022
Grant date	Sep 6, 2022

Abstract

A method of operating a gas turbine engine in a multi-engine aircraft, the gas turbine engine having an engine shaft mounted for rotation in a bearing and a gearbox connected to the engine shaft for torque transmission therebetween, includes axially preloading the bearing using an axially biasing element disposed between the gas turbine engine and the gearbox. The axially biasing element reacts against the gearbox to exert an axial preload force on the bearing and the engine shaft of the gas turbine engine.

First claim

What is claimed is:

1. A method of operating a gas turbine engine in a multi-engine aircraft, the gas turbine engine having an engine shaft mounted for rotation in a bearing, and a gearbox connected to the engine shaft for torque transmission therebetween, the gearbox mounted to the gas turbine engine with a gimbal joint, the method comprising applying an axial preload force on the bearing using an axially biasing element of an axially flexible coupling, the axially flexible coupling disposed between and interconnecting the gas turbine engine and the gearbox, wherein the axially biasing element reacts against the gearbox to exert axial preload force on the bearing and the engine shaft of the gas turbine engine, and compressing the axially biasing element using the gimbal joint.

2. The method according to claim 1 , comprising:
the axially flexible couple in one of: the engine shaft; and a rotary connector shaft of the gearbox.

3. A method of operating a gas turbine engine in a multi-engine aircraft, the gas turbine engine having an engine shaft mounted for rotation in a bearing, and a gearbox connected to the engine shaft for torque transmission therebetween, the method comprising:
applying an axial preload force on the bearing using an axially biasing element of an axially flexible coupling, the axially flexible coupling disposed between and interconnecting the gas turbine engine and the gearbox, wherein the axially biasing element reacts against the gearbox to the exert the axial preload force on the bearing and the engine shaft of the gas turbine engine,
the axially flexible coupling comprises a sleeve surrounding a shank, the sleeve and shank engaging a resilient member and including matching axial splines, and lubricating the matching axial splines using a spline lubrication system.

4. A multi-engine aircraft comprising:
at least two prime mover gas turbine engines each capable of providing motive power in flight to the aircraft and respectively including an engine casing supporting an engine shaft mounted for rotation in a bearing;
a gearbox including a gearbox housing mounted to the engine casing with a gimbal joint, the gearbox housing supporting a rotary connector shaft; and
an axially flexible coupling including an axially biasing element disposed between the gas turbine engine and the gearbox, the axially biasing element configured to bias against the gearbox housing to exert an axial preload force on the engine shaft and the bearing.

5. The multi-engine aircraft according to claim 4 wherein the gimbal joint is mounted to the engine casing with the axial fasteners to compress the axially biasing element.

6. The multi-engine aircraft according to claim 5 wherein the axial fasteners comprise threaded bolts.

7. The multi-engine aircraft according to claim 4 wherein the axially flexible coupling comprises a sleeve surrounding a shank, and the axially biasing element comprises a resilient member, the sleeve and shank engaging the resilient member.

8. The multi-engine aircraft according to claim 7 wherein the sleeve and shank include matching axial splines.

9. The multi-engine aircraft according to claim 8 including a spline lubrication system.

10. The multi-engine aircraft according to claim 7 wherein the resilient member is selected from the group consisting of: a helical spring; a conical disc spring; an annular wave spring; a ring spring; and an elastomeric block.

11. The multi-engine aircraft according to claim 4 wherein the axially biasing element comprises a pair of radial flanges joined with an annular sleeve.

12. The multi-engine aircraft according to claim 11 wherein the pair of radial flanges comprise a plurality of radial spokes.

13. The multi-engine aircraft according to claim 12 wherein the pair of radial flanges comprise a plurality of axial spokes.

14. The multi-engine aircraft according to claim 4 wherein the bearing comprises a ball bearing.

15. The multi-engine aircraft according to claim 4 wherein the axially flexible coupling is disposed in the engine shaft or the rotary connector shaft.

Assignees

• Pratt & Whitney Canada

Inventors

• Brillon Louis
• Carrieres Alain

Classifications

• B64D35/08

  characterised by the transmission being driven by a plurality of power plants (for hybrid-electric power plants B64D35/022) · CPC title

• F01D25/186 Primary

  for sliding contact bearing · CPC title

• B64D35/02

  specially adapted for specific power plants · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• F02C7/06

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