Shaft assembly for aircraft engine

Patent metadata

Field	Value
Publication number	US-10968834-B2
Application number	US-201916456573-A
Country	US
Kind code	B2
Filing date	Jun 28, 2019
Priority date	Jun 28, 2019
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.

First claim

The invention claimed is:

1. An aircraft engine comprising: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.

2. The aircraft engine of claim 1 , wherein each of the at least two axially spaced apart annular ring seals is received within a respective one of at least two axially spaced apart grooves.

3. The aircraft engine of claim 2 , wherein a portion of the first transmission shaft is received within the second transmission shaft, the at least two axially spaced apart grooves extending from an outer surface of the first transmission shaft and toward the axis.

4. The aircraft engine of claim 1 , wherein a portion of the first transmission shaft is received within the second transmission shaft, the first and second transmission shafts axially movable one relative to the other between a baseline position in which one of the at least two annular ring seals is disengaged from one of the first and second transmission shafts and a retention position in which both of the at least two annular ring seals are engaged to both of the first and second transmission shafts.

5. The aircraft engine of claim 4 , wherein an inner surface of the second transmission shaft defines a step-down diameter portion axially aligned with the one of the at least two annular ring seals in the baseline position.

6. The aircraft engine of claim 1 , wherein the first and second transmission shafts are in driving engagement with each other via a spline coupling.

7. The aircraft engine of claim 1 , further comprising a bearing rotatably supporting the first transmission shaft proximate a connection between the first and second transmission shaft.

8. The aircraft engine of claim 7 , wherein the bearing is a journal bearing.

9. A method of retaining a tower shaft and a quill shaft to one another comprising:
transmitting a rotational input from an engine shaft of an aircraft engine to an engine accessory with a tower shaft and a quill shaft engaged to the tower shaft;
sealing a connection between the quill shaft and the tower shaft with a first annular ring seal disposed between the quill shaft and the tower shaft; and
upon removal of the engine accessory from the aircraft engine, retaining the quill shaft in engagement with the tower shaft with both the first annular ring seal and a second annular ring seal disposed between the quill shaft and the tower shaft and axially offset from the first annular ring seal.

10. The method of claim 9 , further comprising maintaining an axial position of the first annular ring seal and the second annular ring seal relative to the tower shaft.

11. The method of claim 9 , wherein retaining the quill shaft in engagement with the tower shaft includes axially moving the quill shaft away from the tower shaft from a baseline position in which only the first annular ring seal is engaged to both of the quill shaft and the tower shaft to a retention position in which both of the first annular ring seal and the second annular ring seal are engaged to the quill shaft and the tower shaft.

12. The method of claim 11 , wherein an inner surface of the quill shaft defines a step-down diameter portion at the second annular ring seal in the baseline position, the method comprising providing a sealing engagement between the tower shaft and the quill shaft solely via the first annular ring seal in the baseline position.

13. The method of claim 9 , wherein transmitting the rotational input from the engine shaft to the engine accessory via the tower shaft and the quill shaft includes transmitting a rotation of the tower shaft to the quill shaft via a spline coupling between the tower shaft and the quill shaft.

14. The method of claim 9 , wherein transmitting the rotational input from the engine shaft to the engine accessory via the tower shaft and the quill shaft includes radially supporting the tower shaft and the quill shaft proximate to connection between the tower shaft and the quill shaft.

15. The method of claim 9 , wherein retaining the quill shaft in engagement with the tower shaft with both the first annular ring seal and the second annular ring seal includes increasing a force exerted by the second annular ring seal on both of the quill shaft and the tower shaft while translating the quill shaft relative to the tower shaft.

16. A shaft assembly for an aircraft engine, comprising: a tower shaft drivingly engageable to an engine shaft of the aircraft engine; a quill shaft in driving engagement with the tower shaft and drivingly engageable to an engine accessory, the tower shaft concentrically partially received within the quill shaft; and at least two axially spaced apart annular ring seals disposed radially between the quill shaft and the tower shaft, the at least two annular ring seals biased against both of the tower shaft and the quill shaft.

17. The shaft assembly of claim 16 , wherein each of the at least two axially spaced apart annular ring seals is received within a respective one of at least two axially spaced apart grooves.

18. The shaft assembly of claim 17 , wherein the at least two axially spaced apart grooves extend from an outer surface of the tower shaft and toward an axis of rotation of the shaft assembly.

19. The shaft assembly of claim 16 , wherein the tower shaft and the quill shaft are axially movable one relative to the other between a baseline position in which one of the at least two annular ring seals is disengaged from one of the tower shaft and the quill shaft and a retention position in which both of the two annular ring seals are biased against both of the tower shaft and the quill shaft.

20. The shaft assembly of claim 19 , wherein an inner surface of the quill shaft defines a step-down diameter portion axially aligned with one of the at least two annular ring seals in the baseline position.

Assignees

• Pratt & Whitney Canada

Inventors

• Labbe Michel
• Pokrzywa Lukasz

Classifications

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C7/36 Primary

  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

• F16D2001/103

  the torque is transmitted via splined connections · CPC title

• F16D3/76

  shaped as an elastic ring centered on the axis, surrounding a portion of one coupling part and surrounded by a sleeve of the other coupling part · CPC title

• F16D1/104

  having retaining means rotating with the coupling and acting only by friction · CPC title