Gas turbine engine including seal assembly with abradable coating including magnetic particles

Patent metadata

Field	Value
Publication number	US-11313281-B2
Application number	US-202016930444-A
Country	US
Kind code	B2
Filing date	Jul 16, 2020
Priority date	Jul 16, 2020
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

First claim

The invention claimed is:

1. A gas turbine engine, comprising: a compressor section, a combustor section, a turbine section, and at least one rotatable shaft; and a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area, wherein the seal assembly includes an abradable coating adjacent the contact area, and wherein the abradable coating includes magnetic particles, wherein, in normal engine operating conditions, an axial end face of the seal plate and an axial end face of the face seal are in direct contact at the contact area, and wherein, in normal engine operating conditions, the abradable coating is adjacent the contact area and is radially outward of the contact area.

2. The gas turbine engine as recited in claim 1 , wherein the abradable coating includes particles of an alloy.

3. The gas turbine engine as recited in claim 2 , wherein the alloy includes iron (Fe).

4. The gas turbine engine as recited in claim 3 , wherein the alloy further includes nickel (Ni) and aluminum (Al).

5. The gas turbine engine as recited in claim 3 , wherein the alloy further includes chrome (Cr), nickel (Ni), and carbon (C).

6. The gas turbine engine as recited in claim 1 , wherein the particles are deposited on at least one of the face seal, the seal plate, and a seal carrier supporting the face seal using a thermal spray coating process.

7. The gas turbine engine as recited in claim 1 , wherein the abradable coating includes a solid lubricant.

8. The gas turbine engine as recited in claim 7 , wherein the lubricant is hexagonal boron nitride (h-BN) or molybdenum disulfide (MoS 2 ).

9. The gas turbine engine as recited in claim 1 , wherein: the abradable coating is applied to one or both of a face seal and a seal carrier holding the face seal, the abradable coating is positioned such that, in normal engine operating conditions, the seal plate does not contact the abradable coating, the abradable coating is positioned such that, in a worn seal condition, the seal plate contacts the abradable coating and releases at least some particles of the abradable coating, and the abradable coating is a sacrificial coating.

10. The gas turbine engine as recited in claim 9 , further comprising a sensor configured to detect a presence of at least some of the released magnetic particles in lubricant.

11. The gas turbine engine as recited in claim 1 , further comprising:
a bearing assembly mounted relative to the rotatable shaft, wherein the seal assembly is adjacent the bearing assembly.

12. The gas turbine engine as recited in claim 1 , wherein the face seal is made of a carbon material.

13. The gas turbine engine as recited in claim 1 , wherein, in normal engine operating conditions, within the contact area the axial end face of the seal plate and the axial end face of the face seal are both substantially planar, smooth surfaces.

14. The gas turbine engine as recited in claim 1 , wherein, in normal engine operating conditions: the axial end face of the seal plate is either an aft-most or a fore-most surface of the seal plate, and the axial end face of the face seal is either an aft-most or a fore-most surface of the face seal.

15. A bearing compartment for a gas turbine engine, comprising: a bearing assembly; and a seal assembly including a seal plate and a face seal in contact with the seal plate at a contact area, wherein the seal assembly includes an abradable coating adjacent the contact area, and wherein the abradable coating includes magnetic particles, wherein, in normal engine operating conditions, an axial end face of the seal plate and an axial end face of the face seal are in direct contact at the contact area, and wherein, in normal engine operating conditions, the abradable coating is adjacent the contact area and is radially outward of the contact area.

16. The bearing compartment as recited in claim 15 , wherein the abradable coating further includes particles of an alloy.

17. The bearing compartment as recited in claim 16 , wherein: the abradable coating is applied to one or both of a face seal and a seal carrier holding the face seal, the abradable coating is positioned such that, in normal engine operating conditions, the seal plate does not contact the abradable coating, and the abradable coating is positioned such that, in a worn seal condition, the seal plate contacts the abradable coating and frees at least some magnetic particles of the abradable coating.

Assignees

• Raytheon Tech Corp

Inventors

• Stoyanov Pantcho P
• Wusatowska-Sarnek Agnieszka M
• Kasprow Thomas D

Classifications

• F16C33/76

  of ball or roller bearings · CPC title

• F16C2202/40

  Magnetic · CPC title

• F16C2208/70

  Polyesters, e.g. polyethylene-terephthlate [PET], polybutylene-terephthlate [PBT] · CPC title

• F16C2233/00

  Monitoring condition, e.g. temperature, load, vibration · CPC title

• F16C19/52

  with devices affected by abnormal or undesired conditions · CPC title