Systems and methods for internal spline lubrication

Patent metadata

Field	Value
Publication number	US-11572804-B2
Application number	US-202016849523-A
Country	US
Kind code	B2
Filing date	Apr 15, 2020
Priority date	Apr 15, 2020
Publication date	Feb 7, 2023
Grant date	Feb 7, 2023

Abstract

A gas turbine engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.

First claim

The invention claimed is:

1. A gas turbine engine, comprising: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via a spline; a reference tube circumferentially extending around the shaft, the reference tube secured at a first end to the shaft for rotation therewith and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture therethrough; an oil nozzle fluidly connected to a source of lubricant, the oil nozzle defining an exit flow axis intersecting the at least one tube aperture for injecting oil through the reference tube, the shaft defining at least one shaft aperture extending therethrough, the oil nozzle aligned with the spline via the at least one tube aperture and the at least one shaft aperture.

2. The gas turbine engine of claim 1 , wherein the at least one tube aperture has a length in a circumferential direction relative to the central axis and a width in an axial direction relative to the central axis, the length greater than the width.

3. The gas turbine engine of claim 1 , wherein the at least one tube aperture has a length taken in a circumferential direction relative to the central axis, the length equal to or greater than a product of a rotational speed of the of the tube, a thickness of the tube in a radial direction, and a radius of the tube divided by a velocity of the oil exiting the oil nozzle.

4. The gas turbine engine of claim 1 , wherein the shaft defines a pool circumferentially extending around the central axis for receiving oil from the oil nozzle, the at least one shaft aperture in fluid flow communication with the pool.

5. The gas turbine engine of claim 4 , wherein the shaft has a main section and an end section, the end section defining the spline, a diameter of the main section less than that of the end section, the pool located proximate an intersection between the main section and the end section.

6. The gas turbine engine of claim 4 , wherein the exit flow axis intersects the shaft at a location axially aligned with the pool.

7. The gas turbine engine of claim 4 , wherein the shafts defines an axial protrusion and a lip extending from an end of the axial protrusion, the lip extending at least radially inwardly toward the central axis, the pool defined by the shaft at an intersection between the main and end sections, the axial protrusion, and the lip.

8. The gas turbine engine of claim 7 , wherein the at least one shaft aperture has an inlet end communicating with the pool, a tip of the lip located radially inwardly of the inlet end of the at least one shaft aperture.

9. The gas turbine engine of claim 4 , wherein the at least one shaft aperture extends at least axially through the shaft at the intersection between the main and end sections.

10. The gas turbine engine of claim 1 , wherein the at least one tube aperture has an aperture axis parallel to the exit flow axis.

11. A torque shaft assembly for a gas turbine engine, comprising: a shaft rotatable about a central axis and defining a spline at an end thereof for drivingly engaging a rotatable load; and a reference tube circumferentially extending around the shaft, the reference tube having a first end secured to the shaft for rotation therewith and a second end free relative to the shaft, the reference tube defining at least one tube aperture therethrough for receiving a jet of oil, the shaft defining at least one shaft aperture extending therethrough, a flow path extending from the at least one tube aperture to the spline via the at least one shaft aperture for lubricating the spline.

12. The torque shaft assembly of claim 11 , wherein the at least one tube aperture has a length taken in a circumferential direction relative to the central axis, the length equal to or greater than a product of a rotational speed of the of the tube, a thickness of the tube in a radial direction, and a radius of the tube divided by a velocity of the oil exiting the oil nozzle.

13. The torque shaft assembly of claim 11 , wherein the shaft defines a pool circumferentially extending around the central axis for receiving oil from the oil nozzle, the at least one shaft aperture in fluid flow communication with the pool.

14. The torque shaft assembly of claim 13 , wherein the shaft has a main section and an end section, the end section defining the spline, a diameter of the main section less than that of the end section, the pool located proximate an intersection between the main section and the end section.

15. The torque shaft assembly of claim 13 , wherein the exit flow axis intersects the shaft at a location axially aligned with the pool.

16. The torque shaft assembly of claim 13 , wherein the shafts defines an axial protrusion and a lip extending from an end of the axial protrusion, the lip extending at least radially inwardly toward the central axis, the pool defined by the shaft at an intersection between the main and end sections, the axial protrusion, and the lip.

17. The torque shaft assembly of claim 16 , wherein the at least one shaft aperture has an inlet end communicating with the pool, a tip of the lip located radially inwardly of the inlet end of the at least one shaft aperture.

18. The torque shaft assembly of claim 13 , wherein the at least one shaft aperture extends at least axially through the shaft at the intersection between the main and end sections.

19. The torque shaft assembly of claim 11 , wherein the at least one tube aperture has an aperture axis parallel to the exit flow axis.

20. A method of lubricating a spline of a shaft of a gas turbine engine, the method comprising:
surrounding a shaft with a reference tube having a first end secured to the shaft and a second end free relative to the shaft;
injecting oil through at least one tube aperture defined through the reference tube;
directing the injected oil toward the spline via at least one shaft aperture defined through the shaft; and
lubricating the spline with the injected oil.

Assignees

• Pratt & Whitney Canada

Inventors

• Bouchard Guy
• Brillon Louis

Classifications

• F05D2260/98

  Lubrication · CPC title

• F05D2240/60

  Shafts · CPC title

• F01D25/20 Primary

  using lubrication pumps · CPC title

• F01D5/066

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F01D25/18 Primary

  Lubricating arrangements (of machines or engines in general F01M) · CPC title