Gas turbine engine and method for introducing oil in a gearbox arrangement

Patent metadata

Field	Value
Publication number	US-11174756-B2
Application number	US-201916299709-A
Country	US
Kind code	B2
Filing date	Mar 12, 2019
Priority date	Mar 20, 2018
Publication date	Nov 16, 2021
Grant date	Nov 16, 2021

Abstract

A gas turbine engine for an aircraft includes an engine core, a fan and a gearbox which receives an input from a turbine shaft and which outputs drive for the fan for driving the fan at a lower rotational speed than the turbine shaft. The gearbox has a sun gear which is driven by the turbine shaft. The turbine shaft and the sun gear form a spline connection which is lubricated with oil. The turbine shaft has, on its radially inner side, at least one indentation which is suitable for receiving oil, and the turbine shaft has at least one bore which extends from the indentation to the radially outer side of the turbine shaft and which is suitable for transporting oil from the at least one indentation to the radially outer side of the turbine shaft as the turbine shaft rotates.

First claim

The invention claimed is:

1. A gas turbine engine for an aircraft, comprising:
an engine core further comprising:
a turbine;
a compressor; and
a turbine shaft which connects the turbine to the compressor and wherein the turbine shaft is a hollow shaft;

a fan which is positioned upstream of the engine core, wherein the fan includes a plurality of fan blades; and
a gearbox which receives an input from the turbine shaft and which outputs a drive for the fan to drive the fan at a lower rotational speed than the turbine shaft, wherein the gearbox includes a sun gear which is driven by the turbine shaft;
a spline connection connecting the turbine shaft and the sun gear, wherein the spline connection is lubricated with oil;
wherein the turbine shaft further comprises:
an indentation on a radially inner side of the turbine shaft for receiving oil;
at least one bore which extends from the indentation to a radially outer side of the turbine shaft with respect to an axis of rotation of the gas turbine engine and to the spline connection for transporting oil from the indentation to the radially outer side of the turbine shaft and to the spline connection as the turbine shaft rotates.

2. The gas turbine engine according to claim 1 , wherein the indentation is a groove which is continuous in a circumferential direction with respect to the axis of rotation.

3. The gas turbine engine according to claim 1 , wherein the at least one bore includes a plurality of bores which extend from the indentation to the radially outer side of the turbine shaft, wherein the plurality of bores are arranged equidistantly in a circumferential direction with respect to the axis of rotation.

4. The gas turbine engine according to claim 1 , wherein the at least one bore includes a plurality of bores which extend from the indentation to the radially outer side of the turbine shaft, wherein the plurality of bores are arranged one behind another in an axial direction with respect to the axis of rotation.

5. The gas turbine engine according to claim 1 , wherein the indentation is positioned axially such that the at least one bore ends in a sealed-off region of the spline connection.

6. The gas turbine engine according to claim 1 , further comprising:
an axially front seal element in front of the spline connection:
an axially rear seal element aft of the spline connection; and
wherein the indentation is positioned axially between the axially front seal element and the axially rear seal element.

7. The gas turbine engine according to claim 6 , wherein the spline connection further comprises a toothing region and wherein the indentation is axially in front of the toothing region.

8. The gas turbine engine according to claim 1 , further comprising an oil applicator through which oil is introduced into the indentation.

9. The gas turbine engine according to claim 1 , further comprising an oil applicator oriented and positioned such that oil is sprayed directly into the indentation.

10. The gas turbine engine according to claim 1 , further comprising an oil applicator oriented and positioned such that oil is introduced indirectly into the indentation.

11. The gas turbine engine according to claim 10 , further comprising an inner shaft arranged radially inside the turbine shaft, wherein the oil applicator is oriented and positioned such that oil is sprayed onto the inner shaft and oil is one chosen from rebounded and centrifuged from the inner shaft into the indentation.

12. The gas turbine engine according to claim 11 , wherein the inner shaft includes an inner indentation into which the oil applicator sprays oil, wherein the inner indentation is situated, at a same axial position, radially opposite the indentation of the turbine shaft.

13. The gas turbine engine according to claim 12 , wherein the indentation of the inner shaft is a groove.

14. The gas turbine engine according to claim 1 ,
wherein the turbine is a first turbine, the compressor is a first compressor and the turbine shaft is a first turbine shaft;
wherein the engine core further comprises a second turbine, a second compressor and a second turbine shaft, which connects the second turbine to the second compressor; and
wherein the second turbine, the second compressor and the second turbine shaft are arranged to rotate at a higher rotational speed than the first turbine shaft.

15. A gearbox arrangement comprising:
a drive shaft formed as a hollow shaft;
an output element which is driven by the drive shaft;
a shaft-hub connection which is lubricated with oil, wherein the drive shaft and the output element are connected to one another by the shaft-hub connection;
wherein the drive shaft includes an indentation on a radially inner side of the drive shaft with respect to a rotational axis of the drive shaft for receiving oil, and wherein the drive shaft includes a bore which extends from the indentation to a radially outer side of the drive shaft and to the shaft-hub connection for transporting oil from the indentation to the radially outer side of the drive shaft and to the shaft-hub connection as the drive shaft rotates.

16. The gearbox arrangement according to claim 15 , wherein the indentation is a groove which is continuous in a circumferential direction with respect to the rotational axis.

17. The gearbox arrangement according to claim 15 , further comprising:
an axially front seal element in front of the shaft-hub connection;
an axially rear seal element aft of the shaft-hub connection; and
wherein the indentation is positioned axially so as to be situated axially between the axially front seal element and the axially rear seal element.

18. The gearbox arrangement according to claim 15 , further comprising an oil applicator through which oil is sprayed into the indentation, wherein the oil applicator is oriented and positioned such that oil is sprayed directly into the indentation.

19. The gearbox arrangement according to claim 15 , further comprising:
an inner shaft arranged radially inside the drive shaft; and
an oil applicator through which oil is sprayed into the indentation, wherein the oil applicator is oriented and positioned such that oil is sprayed onto the inner shaft and one chosen from rebounds and is centrifuged from the inner shaft into the indentation.

20. A method for introducing oil into a gearbox arrangement comprising:
providing:
a drive shaft, including a hollow shaft, an indentation on a radially inner side of the drive shaft, and a bore extending from the indentation to a radially outer side of the drive shaft;
an output element;
a shaft-hub connection connecting the drive shaft and the output element; and
a seal region in which the shaft-hub connection is sealed off;

introducing oil into the indentation;
transporting oil from the indentation through the bore to the radially outer side of the drive shaft and to the shaft-hub connection as the drive shaft rotates, wherein the oil is fed to the seal region.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Venter Gideon Daniel
• Kallianteris Christos

Classifications

• F01D25/20 Primary

  using lubrication pumps · CPC title

• F02C7/36

  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

• F16H57/0486

  with fixed gear ratio  (axle or inter-axle differentials F16H57/0483) · CPC title

• F01D25/18 Primary

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

• F02K3/06

  with front fan · CPC title