Gas turbine engine with ring damper

Patent metadata

Field	Value
Publication number	US-10724375-B2
Application number	US-201615042187-A
Country	US
Kind code	B2
Filing date	Feb 12, 2016
Priority date	Feb 12, 2016
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

A damper seat for a ring damper that redirects axial loads and is disposed within a gas turbine engine with at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis.

First claim

What is claimed is:

1. A gas turbine engine comprising:
at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis;
a ring damper;
a radial channel formed in one of the disk or the ring damper and having a damper neutral axis extending radially from the rotational axis and axially spaced from the disk neutral axis;
a damper seat located in only one of the disk or the ring damper and formed by the radial channel having a profile that axially redirects at least a portion of a centrifugal load of the ring damper, the profile having an apex; and
a slipping portion that is integral with the damper seat and the apex is sized such that the slipping portion does not abut the apex;
wherein the other one of the disk or the ring damper is seated within the damper seat.

2. The gas turbine engine of claim 1 wherein the profile comprises at least one ramp oriented at an angle relative to the damper neutral axis, with the ramp abutting the slipping portion.

3. The gas turbine engine of claim 2 wherein the profile further comprises an apex extending from the slipping portion.

4. The gas turbine engine of claim 3 wherein the profile further comprises another ramp on an axial opposite side of the apex than the one ramp.

5. The gas turbine engine of claim 4 wherein the other ramp is oriented in an opposite direction than the one ramp.

6. The gas turbine engine of claim 5 wherein the other ramp is oriented at an angle greater than the one ramp.

7. The gas turbine engine of claim 1 wherein the profile has two surfaces on opposite sides of the apex and at least one of the surfaces abuts the slipping portion.

8. The gas turbine engine of claim 7 wherein both surfaces abut the slipping portion.

9. The gas turbine engine of claim 1 wherein the profile has axially spaced first and second ramp surfaces.

10. The gas turbine engine of claim 9 wherein the first and second ramp surfaces converge and the slipping portion is received between the first and second ramp surfaces.

11. The gas turbine engine of claim 10 wherein the profile defines an inverted V shape opening radially inward.

12. The gas turbine engine of claim 9 wherein the first and second ramp surfaces diverge and the ring damper wraps around the first and second ramp surfaces.

13. The gas turbine engine of claim 12 wherein the ring damper comprises the channel in which the first and second ramp surfaces are received.

14. The gas turbine engine of claim 13 wherein the ring damper channel has a bottom spaced from the first and second ramps.

15. The gas turbine engine of claim 1 wherein the at least one disk comprises multiple axially arranged disks.

16. The gas turbine engine of claim 1 wherein the at least one disk comprises one of a compressor rotor disk or a turbine rotor disk.

17. The gas turbine engine of claim 1 wherein the other one of the disk or the ring damper is in contact with the damper seat when seated within the damper seat.

18. A gas turbine engine comprising:
at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis;
a ring damper;
a radial channel formed in one of the disk or ring damper and having a damper neutral axis extending radially from the rotational axis and axially spaced from the disk neutral axis;
a damper seat formed by the radial channel having a profile that axially redirects at least a portion of a centrifugal load of the ring damper; and
a slipping portion that is integral with the damper seat and ring damper;
wherein one of the disk or ring damper is seated within the damper seat and the profile comprises a pair of axially spaced stubs and the ring damper has a channel receiving the stubs and having width greater than the spacing of the stubs.

19. A gas turbine engine comprising:
at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis;
a radial channel having a damper neutral axis extending radially from the rotational axis and axially spaced from the disk neutral axis;
a ring damper;
a damper seat having a profile comprising a pair of ramps where one ramp is oriented at an angle greater than the other ramp and on an axial opposite side of the other ramp forming an apex therebetween; and
a slipping portion that is integral with the damper seat and ring damper;
wherein the profile is shaped such that the ring damper is seated resulting in a differential strain applied to the channel on opposite sides of the ring damper in response to a centrifugal load from the ring damper.

20. A method of damping a centrifugal load on a rotating disk in a gas turbine engine comprising:
moving a ring damper along a pair of ramped surfaces of a radial channel located within a portion of the rotating disk radially inward of an airfoil, the pair of ramped surfaces each angled at differing angles and defining an apex;
maintaining a space between the ring damper and the apex of the radial channel;
forming two contact points between the ring damper and the pair of ramped surfaces; and
redirecting at least a portion of the centrifugal load in the axial direction at the two contact points.

21. The method of claim 20 where at least a portion of a centrifugal load acting on the ring damper results in a differential strain applied to the channel on opposite sides of the ring damper in response to a centrifugal load from the ring damper.

22. A ring damper assembly comprising:
at least one disk rotatable about a rotational axis and having a disk neutral axis extending radially from the rotational axis;
a ring damper about the rotational axis;
a radial channel formed in one of the ring damper or the disk and having a damper neutral axis extending radially from the rotational axis and axially spaced from the disk neutral axis;
a damper seat located in only one of the disk or the ring damper and formed by the radial channel having a profile that axially redirects at least a portion of a centrifugal load of the ring damper; and
a slipping portion that is integral with the damper seat;
wherein the other one of the disk or the ring damper is seated within the damper seat and the profile has an apex sized such that the slipping portion does not abut the apex.

23. The ring damper assembly of claim 22 wherein the profile comprises at least one ramp oriented at an angle relative to the damper neutral axis, with the ramp abutting the slipping portion.

24. The ring damper assembly of claim 23 wherein the one ramp oriented at an angle relative to the damper neutral axis, with the ramp abutting the slipping portion.

25. The ring damper assembly of claim 22 wherein the profile has two surfaces on opposite sides of the apex and at least one of the surfaces abuts the slipping portion.

Assignees

• Gen Electric

Inventors

• Prescott Jeffrey Miles Mcmillen
• Wesling Richard Alan
• Simeone Peter Andrew

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F16F15/14

  using masses freely rotating with the system, {i.e. uninvolved in transmitting driveline torque, e.g. rotative dynamic dampers (compensation of inertia forces F16F15/22; weights for balancing rotating bodies F16F15/32)} · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title