Gearbox planet squeeze film damper

• US 10,113,633 B2
• Filed: 01/28/2016
• Issued: 10/30/2018
• Est. Priority Date: 01/28/2016
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Niergarth, Daniel Alan, Miller, Brandon Wayne, Ertas, Bugra Han, Bradley, Donald Albert, Dickman, Joseph Robert
• Primary Examiner(s): Le, Huan
• Application Number:
  US15/008,907
• Publication Number:
  US 20170219079A1
• Time in Patent Office: 1,006 Days
• CPC Class Codes: F02C 7/36 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 Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F16C 19/28 with two or more rows of rollers
• CPC Class Codes: F16C 2360/23 Gas turbine engines in general F02C
• CPC Class Codes: F16C 2361/61 Toothed gear systems, e.g. support of pinion shafts in general F16H57/02
• CPC Class Codes: F16C 27/045 with a fluid film, e.g. squeeze film damping
• CPC Class Codes: F16H 2057/085 Bearings for orbital gears
• CPC Class Codes: F16H 57/0006 Vibration-damping or noise reducing means specially adapted for gearings devices for varying tension of belts, ropes or chains with damping means F16H7/0829; toothed members with construction providing vibration damping F16H55/14; reducing vibrations or noise of the gearbox casing F16H57/028; suppression of vibrations or noise of gear selectors F16H59/0208; control of hydrostatic fluid gearing preventing or reducing vibrations or noise F16H61/4183
• CPC Class Codes: F16H 57/0471 Bearing
• CPC Class Codes: F16H 57/08 of gearings with members having orbital motion
• CPC Class Codes: F16H 57/082 Planet carriers

Abstract

An epicyclic gearing arrangement includes a planet gear rotatable on a planet bearing that is mounted via a support pin to a carrier of the epicyclic gearing arrangement. A spring film damper is disposed between the cylindrical outer surface of the support pin and the opposing inner surface of the inner ring of the planet bearing and includes an annular gap.

Claims

1. A planet gearbox for connection to a carrier of an epicyclic gearing arrangement that has only a single input and a single output and that includes a ring gear surrounding planet gears and a sun gear, the planet gearbox comprising:

a support pin is configured to be fixed to the carrier, the support pin includes a hollow body that is defined by a cylindrical outer surface that is radially equidistant from a virtual central axis that extends in an axial direction, the support pin is further defined by an inner surface disposed opposite the cylindrical outer surface;

an inner ring is non-rotatably connected to the support pin and defines an inner surface opposed to the outer surface of the support pin, the inner ring defining an outer surface that defines at least one track, said at least one track defined in the outer surface being configured to receive and rotatably guide therein a plurality of cylindrical rollers;

wherein the inner ring is defined by a forward end and an aft end that is spaced axially apart from the forward end, the squeeze film damper includes a forward grove defined in the forward end of the inner ring and extending circumferentially with respect to the virtual central axis;

an outer ring defines;

an inner cylindrical surface that is disposed facing toward the at least one track, the outer ring defining an outer cylindrical surface that defines a gear tooth surface that is disposed facing toward the ring gear and that is configured to mesh with both the sun gear and the ring gear;

the respective plurality of cylindrical rollers rotatably disposed within said at least one track of the inner ring, and each of the plurality of cylindrical rollers rotatably contacting the inner cylindrical surface of the outer ring; and

a squeeze film damper disposed between the outer surface of the support pin and the inner surface of the inner ring.

2. The planet gearbox of claim 1, wherein the support pin includes at least a first oil feed hole extending through the support pin between the inner surface of the support pin and the outer surface of the support pin and defining an exit opening at the outer surface of the support pin, wherein the exit opening of the first oil feed hole is disposed in fluid communication with the squeeze film damper.

3. The planet gearbox of claim 1, wherein the squeeze film damper includes an annular gap that extends between the cylindrical outer surface of the support pin and the inner surface of the inner ring.

4. The planet gearbox of claim 3, wherein the support pin includes at least a first oil feed hole extending through the support pin between the inner surface of the support pin and the outer surface of the support pin and defining an exit opening at the outer surface of the support pin, wherein the exit opening of the first oil feed hole is disposed in fluid communication with the annular gap.

5. The planet gearbox of claim 1, wherein the forward groove defines a radial depth that extends from the inner surface of the inner ring in a direction radially away from the virtual central axis, and the squeeze film damper further includes a forward resilient seal disposed within the forward groove, the forward resilient seal defining an inner diameter and an outer diameter that is larger than the inner diameter such that the difference between the inner diameter and the outer diameter defines an uncompressed thickness of the forward resilient seal, and the uncompressed thickness of the forward resilient seal is greater than the radial depth of the forward groove.

6. The planet gearbox of claim 5, wherein the squeeze film damper includes an annular gap that is defined between the cylindrical outer surface of the support pin and the inner surface of the inner ring and wherein the squeeze film damper includes a resilient forward toroidal seal at a forward end of the annular gap and a resilient aft toroidal seal at an aft end of the annular gap.

7. The planet gearbox of claim 5, wherein the squeeze film damper includes an aft groove defined in the aft end of the inner ring and extending circumferentially with respect to the virtual central axis, the aft groove defines a radial depth that extends from the inner surface of the inner ring in a direction radially away from the virtual central axis, and the squeeze film damper further includes an aft resilient seal disposed within the aft groove, the aft resilient seal defining an inner diameter and an outer diameter that is larger than the inner diameter such that the difference between the inner diameter and the outer diameter of the aft resilient seal defines an uncompressed thickness of the aft resilient seal, and the uncompressed thickness of the aft resilient seal is greater than the radial depth of the aft groove.

8. The planet gearbox of claim 7, wherein the squeeze film damper includes an annular gap that extends between the cylindrical outer surface of the support pin and the inner surface of the inner ring in a direction radially away from the virtual central axis and wherein the dimension of the annular gap at any point around a circumference of the squeeze film damper depends upon the degree of compression of the resilient seals.

9. The planet gearbox of claim 7, wherein each of the resilient forward seal and the resilient aft seal is a toroidal seal.

10. A gas turbine engine comprising:

a fan including a plurality of blades extending radially from a hub and rotatable about a first axis of rotation defined centrally through the hub;

a compressor disposed downstream from the fan;

a turbine disposed downstream of the compressor;

a rotatable input shaft mechanically coupling the compressor to rotate in unison with the turbine;

an epicyclic gearing arrangement that has only a single input and that includes a carrier, a sun gear rotatable about a second axis of rotation that is parallel to the first axis of rotation, a ring gear disposed circumferentially around the sun gear, at least one planet gearbox that is carried by the carrier and houses a planet gear rotatable with respect to the carrier about a third axis of rotation that is parallel to the second axis of rotation, wherein the at least one planet gear meshes with both the sun gear and the ring gear; and

an engine envelope surrounding the fan, the compressor, the turbine and the epicyclic gearing arrangement, wherein one of the ring gear and the carrier is non-rotatably coupled to the engine envelope; and

the planet gearbox further including;

a support pin is configured to be fixed to the carrier, the support pin includes a hollow body that is defined by a cylindrical outer surface that is radially equidistant from a virtual central axis that extends in an axial direction, the support pin is further defined by an inner surface disposed opposite the cylindrical outer surface;

an inner ring is non-rotatably connected to the support pin and defines an inner surface opposed to the outer surface of the support pin, the inner ring defining an outer surface that defines at least one track, the at least one track defined in the outer surface being configured to receive and rotatably guide therein a plurality of cylindrical rollers;

a planet gear defines an inner cylindrical surface that is disposed facing toward the at least one track, the planet gear defining an outer cylindrical surface that defines a gear tooth surface that is disposed facing toward the ring gear and that is configured to mesh with both the sun gear and the ring gear;

the plurality of cylindrical rollers rotatably disposed within the at least one track of the inner ring, and each of the plurality of cylindrical rollers rotatably contacting the inner cylindrical surface of the planet gear; and

a squeeze film damper disposed between the outer surface of the support pin and the inner surface of the inner ring, wherein the squeeze film damper includes a resilient forward toroidal seal at a forward end of the annular gap and a resilient aft toroidal seal at an aft end of the annular gap.

11. The gas turbine engine of claim 10, wherein the support pin includes at least a first oil feed hole extending through the support pin between the inner surface of the support pin and the outer surface of the support pin and defining an exit opening at the outer surface of the support pin, wherein the exit opening of the first oil feed hole is disposed in fluid communication with the squeeze film damper.

12. The gas turbine engine of claim 10, wherein the squeeze film damper includes an annular gap that extends between the cylindrical outer surface of the support pin and the inner surface of the inner ring.

13. The gas turbine engine of claim 12, wherein the support pin includes at least a first oil feed hole extending through the support pin between the inner surface of the support pin and the outer surface of the support pin and defining an exit opening at the outer surface of the support pin, wherein the exit opening of the first oil feed hole is disposed in fluid communication with the annular gap.

14. The gas turbine engine of claim 10, wherein the inner ring is defined by a forward end and an aft end that is spaced axially apart from the forward end, the squeeze film damper includes a forward groove defined in the forward end of the inner ring and extending circumferentially with respect to the virtual central axis.

15. The gas turbine engine of claim 14, wherein the forward groove defines a radial depth that extends from the inner surface of the inner ring in a direction radially away from the virtual central axis, and the squeeze film damper further includes a forward resilient seal disposed within the forward groove, the forward resilient seal defining an inner diameter and an outer diameter that is larger than the inner diameter such that the difference between the inner diameter and the outer diameter defines an uncompressed thickness of the forward resilient seal, and the uncompressed thickness of the forward resilient seal is greater than the radial depth of the forward groove.

16. The gas turbine engine of claim 15, wherein the squeeze film damper includes an annular gap that is defined between the cylindrical outer surface of the support pin and the inner surface of the inner ring and wherein the squeeze film damper includes a resilient forward toroidal seal at a forward end of the annular gap and a resilient aft toroidal seal at an aft end of the annular gap.

17. The gas turbine engine of claim 15, wherein the squeeze film damper includes an aft groove defined in the aft end of the inner ring and extending circumferentially with respect to the virtual central axis, the aft groove defines a radial depth that extends from the inner surface of the inner ring in a direction radially away from the virtual central axis, and the squeeze film damper further includes an aft resilient seal disposed within the aft groove, the aft resilient seal defining an inner diameter and an outer diameter that is larger than the inner diameter such that the difference between the inner diameter and the outer diameter of the aft resilient seal defines an uncompressed thickness of the aft resilient seal, and the uncompressed thickness of the aft resilient seal is greater than the radial depth of the aft groove.

18. The gas turbine engine of claim 17, wherein the squeeze film damper includes an annular gap that extends between the cylindrical outer surface of the support pin and the inner surface of the inner ring in a direction radially away from the virtual central axis and wherein the dimension of the annular gap at any point around a circumference of the squeeze film damper depends upon the degree of compression of the resilient seals.