Gas turbine engine with fluid damper

Patent metadata

Field	Value
Publication number	US-10731510-B2
Application number	US-201514707227-A
Country	US
Kind code	B2
Filing date	May 8, 2015
Priority date	May 16, 2014
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

A gas turbine engine includes a static structure which includes a first fluid passage and a rotatable shaft. A bearing assembly supports the rotatable shaft relative to the static structure. The bearing assembly includes an outer race with a damper passage that extends between the static structure and the outer race. A second fluid passage extends from the damper passage to a seal.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a static structure including a first fluid passage, the first fluid passage extending continuously through the static structure between an inlet and an outlet of the first fluid passage;
a rotatable shaft;
a bearing assembly supporting the rotatable shaft relative to the static structure, the bearing assembly including an outer race with a damper passage at least partially defined by the static structure and the outer race with the outlet of the first fluid passage located at an interface with the damper passage and radially outward from the damper passage;
a flange attached to the static structure and multiple fingers engaging the flange and the outer race, wherein the flange engages a flange contact surface on the static structure with the flange contact surface located axially forward of the first fluid passage in the static structure and the multiple fingers engage the flange and the outer race;
a first seal directly contacting the outer race and the static structure defining a forward edge of the damper passage;
a second seal directly contacting the outer race and the static structure defining an aft edge of the damper passage; and
a second fluid passage extending through the outer race from the damper passage to a seal.

2. The gas turbine engine of claim 1 , wherein the bearing assembly includes an inner race attached to the rotating shaft.

3. The gas turbine engine of claim 1 , wherein the damper passage is configured to contain a film of fluid.

4. The gas turbine engine of claim 1 , wherein the rotatable shaft is an inner shaft mechanically connected to a fan through a speed change device.

5. The gas turbine engine of claim 1 , wherein the bearing assembly is an inner shaft support bearing and the inner shaft is driven by a low pressure turbine and connected to a fan through a speed change device.

6. The gas turbine engine of claim 1 , wherein the seal is a carbon seal and the carbon seal includes a stationary portion and a portion that rotates with the rotatable shaft.

7. The gas turbine engine of claim 1 , wherein the first fluid passage is fluidly connected to the second fluid passage and the first fluid passage is in an axial overlapping alignment with the outer race.

8. The gas turbine engine of claim 1 , including a plenum located between the first fluid passage and the second fluid passage, wherein the plenum is defined by a radially inner side of the static structure and a radially outer side of the outer race and an outlet of the first fluid passage is located radially outward of the plenum.

9. The gas turbine engine of claim 8 , wherein the second fluid passage extends radially inward and downstream from the plenum.

10. The gas turbine engine of claim 1 , including a pump for pumping a fluid through the first fluid passage and the second fluid passage.

11. The gas turbine engine of claim 1 , wherein the inlet and the outlet of the first fluid passage is fluidly is in an axial overlapping alignment with the outer race.

12. The gas turbine engine of claim 1 , including a fluid supply passage extending through the static structure and the first fluid passage branches off of the fluid supply passage.

13. A method of distributing a fluid in a gas turbine engine comprising:
pumping a fluid through a first fluid passage to pressurize a damper passage at least partially defined by an outer race of a bearing assembly and a static structure, wherein the first fluid passage extends through the static structure, a first seal directly contacts the outer race and the static structure defining a forward edge of the damper passage and a second seal directly contacts the outer race and the static structure defining an aft edge of the damper passage, a flange is attached to the static structure, and multiple fingers engage the flange and the outer race, and the flange engages a flange contact surface on the static structure with the flange contact surface located axially forward of the first fluid passage in the static structure and the multiple fingers engage the flange and the outer race; and
directing the fluid from the damper passage through a second fluid passage extending through the outer race to lubricate a seal.

14. The method as recited in claim 13 , wherein an outlet to the second fluid passage is adjacent the seal and the first fluid passage extends continuously through the static structure between an inlet and an outlet of the first fluid passage and the first fluid passage is in an axial overlapping alignment with the outer race.

15. The method as recited in claim 13 , including forming a film of fluid in the damper passage while rotating an inner shaft mechanically connected to a fan through a speed change device.

16. The method as recited in claim 15 , including dampening a vibration traveling through the bearing assembly in the gas turbine engine with the film formed in the damper passage.

17. The method of claim 13 , including collecting the fluid in a plenum located between the first fluid passage and the second fluid passage, wherein the plenum is at least partially defined by the static structure on a radially outer side and the outer race on a radially inner side and the second fluid passage extends radially inward and downstream from the plenum and the plenum is entirely axially inward from opposing axial ends of the outer race and an outlet of the first fluid passage is located radially outward from the plenum.

Assignees

• United Technologies Corp
• Raython Tech Group

Inventors

• Hanrahan Paul R

Classifications

• F01D25/164 Primary

  Flexible supports; Vibration damping means associated with the bearing · CPC title

• F16C27/045

  with a fluid film, e.g. squeeze film damping · CPC title

• F16C19/26

  with a single row of rollers · CPC title

• F01D25/20

  using lubrication pumps · CPC title

• F16C2360/23

  Gas turbine engines · CPC title