Gas turbine engine seal assemblies

Patent metadata

Field	Value
Publication number	US-10774684-B2
Application number	US-201816169965-A
Country	US
Kind code	B2
Filing date	Oct 24, 2018
Priority date	Oct 24, 2018
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

A gas turbine engine according to an example of the present disclosure includes a shaft rotatable about an axis, a bearing disposed about the shaft and within a bearing compartment, and a seal assembly positioned to seal the bearing compartment. The seal assembly includes a fixed seal and a seal runner rotatable with the shaft. The first axial face and a second axial face axially opposite the first axial face with respect to the axis. The first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion. A second surface is angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface. An oil source is positioned to provide oil into the trough portion.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a shaft rotatable about an axis;
a bearing disposed about the shaft and within a bearing compartment;
a seal assembly positioned to seal the bearing compartment, the seal assembly comprising:
a fixed seal, and
a seal runner rotatable with the shaft and having a first axial face and a second axial face axially opposite the first axial face with respect to the axis, wherein the first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion, a second surface angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface, wherein the dam is formed by a convex surface including a radially innermost point that is radially inward of a radially outer surface of the trough portion; and

an oil source positioned to provide oil into the trough portion.

2. The gas turbine engine as recited in claim 1 , wherein the fixed seal is a carbon face seal, and the seal runner is metallic.

3. The gas turbine engine as recited in claim 1 , wherein the second surface is angled between 0 and 45 degrees from the radial baseline.

4. The gas turbine engine as recited in claim 3 , wherein the second surface extends axially away from the trough portion as it extends radially outward.

5. The gas turbine engine as recited in claim 1 , wherein the trough portion is radially inward of at least a portion of the angled surface.

6. The gas turbine engine as recited in claim 1 , comprising
a nozzle assembly disposed in the bearing compartment in communication with the oil source, wherein the nozzle assembly is positioned to direct oil into the trough portion.

7. The gas turbine engine as recited in claim 6 , comprising a second nozzle assembly disposed in the bearing compartment, wherein the second nozzle assembly is positioned to direct oil toward the bearing.

8. The gas turbine engine as recited in claim 1 , wherein the seal runner includes a base portion fixed to the shaft, and the trough portion, angled surface, and dam are radially outward of the base portion.

9. The gas turbine engine as recited in claim 1 , wherein the seal runner includes a metallic annular body having a base portion, a radially outer portion, and a middle portion connecting the base portion and the radially outer portion, and the first surface and the second surface are provided by the radially outer portion.

10. A gas turbine engine comprising:
a low pressure compressor;
a high pressure compressor;
a combustor in fluid communication with the low pressure compressor and high pressure compressor;
a low pressure turbine that drives the low pressure compressor;
a high pressure turbine that drives the high pressure compressor through a shaft rotatable about an axis;
a fan driven by the low pressure turbine;
a bearing disposed about the shaft and within a bearing compartment between the high pressure compressor and the low pressure compressor, wherein the high pressure compressor includes an upstream-most stage of airfoils, and the bearing is disposed axially forward of the upstream-most stage relative to the flow of working fluid through the engine;
a seal assembly axially forward of the bearing and positioned to seal the bearing compartment, the seal assembly comprising:
a fixed seal, and
a seal runner rotatable with the shaft and having a first axial face and a second axial face axially opposite the first axial face with respect to the axis, wherein the first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion, a second surface angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface; and

an oil source positioned to provide oil into the trough portion.

11. The gas turbine engine as recited in claim 10 , wherein the fixed seal is a face seal.

12. The gas turbine engine as recited in claim 10 , wherein the seal is axially forward of the seal runner.

13. The gas turbine engine as recited in claim 12 , wherein the bearing is a thrust bearing.

14. The gas turbine engine as recited in claim 13 , wherein the fixed seal is a carbon face seal, and the seal runner is metallic.

15. The gas turbine engine as recited in claim 10 , comprising a plurality of nozzle assemblies disposed axially between the seal assembly and the bearing.

16. A gas turbine engine comprising:
a low pressure compressor;
a high pressure compressor;
a combustor in fluid communication with the low pressure compressor and high pressure compressor;
a low pressure turbine that drives the low pressure compressor;
a high pressure turbine that drives the high pressure compressor through a shaft rotatable about an axis;
a fan driven by the low pressure turbine;
a bearing disposed about the shaft and within a bearing compartment between the high pressure compressor and the low pressure compressor, wherein the high pressure compressor includes an upstream-most stage of airfoils, and the bearing is disposed axially forward of the upstream-most stage relative to the flow of working fluid through the engine;
a seal assembly positioned to seal the bearing compartment, the seal assembly comprising:
a fixed seal, and
a seal runner rotatable with the shaft and having a first axial face and a second axial face axially opposite the first axial face with respect to the axis, wherein the first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion, a second surface angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface, wherein the dam is formed by a convex surface, and the convex surface includes a radially innermost point that is radially inward of a radially outer surface of the trough portion; and
an oil source positioned to provide oil into the trough portion.

17. The gas turbine engine as recited in claim 16 , wherein the second surface is angled between 0 and 45 degrees from the radial baseline.

18. The gas turbine engine as recited in claim 17 , wherein the fixed seal is a carbon face seal, and the seal runner is metallic.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Glahn Jorn Axel
• James Denman H
• Demitraszek Anthony Sr

Classifications

• F01D25/125

  of bearings · CPC title

• F05D2240/54

  Radial bearings · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F05D2240/55

  Seals · CPC title

• F16J15/30

  with sealing rings made of carbon · CPC title