Seal retention assembly for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10677168-B2
Application number	US-201715840458-A
Country	US
Kind code	B2
Filing date	Dec 13, 2017
Priority date	Dec 13, 2017
Publication date	Jun 9, 2020
Grant date	Jun 9, 2020

Abstract

A face seal assembly includes a seal. The assembly also includes a seal carrier including a first seal wall, a second seal wall and a base seal wall, the first seal wall, the second seal wall and the base seal wall defining a groove for receiving the seal therein, the second seal wall extending radially outwardly to a non-uniform radial location.

First claim

What is claimed is:

1. A face seal assembly comprising:
a seal; and
a seal carrier, the seal carrier including:
a main plate portion that defines anti-rotation slots and provides flanges for attachment of spring fastener features;
a cylindrical body extending away from the main plate portion; and
a seal retention structure, the seal retention structure at an end of the cylindrical body distal from the main plate portion and including; a first seal wall, a second seal wall and a base seal wall, the first seal wall, the second seal wall and the base seal wall defining a groove for receiving the seal therein, the second seal wall extending radially outwardly to a non-uniform radial location, wherein the second seal wall includes a plurality of segments extending to a common, first radial location and a plurality of recessed portions extending to a second radial location that is radially inward of the first radial location and each of the plurality of recessed portions extends circumferentially between an adjacent pair of the plurality of segments.

2. The face seal assembly of claim 1 , wherein the geometry of the seal only allows the seal to be installed into the groove with a single orientation.

3. The face seal assembly of claim 1 , wherein the groove is substantially U-shaped.

4. The face seal assembly of claim 1 , wherein the face seal assembly is disposed in a gas turbine engine.

5. The face seal assembly of claim 4 , wherein the face seal assembly is located adjacent a bearing compartment disposed proximate a main shaft assembly of the gas turbine engine.

6. The face seal assembly of claim 4 , wherein the face seal assembly is located within the compressor section of the gas turbine engine.

7. A gas turbine engine comprising:
a compressor section;
a combustion section;
a turbine section;
a main shaft assembly; and
a face seal assembly comprising:
a seal; and
a seal carrier, the seal carrier including:
a main plate portion that defines anti-rotation slots and provides flanges for attachment of spring fastener features;
a cylindrical body extending away from the main plate portion; and
a seal retention structure, the seal retention structure at an end of the cylindrical body distal from the main plate portion and including; a first seal wall, a second seal wall and a base seal wall, the first seal wall, the second seal wall and the base seal wall defining a groove for receiving the seal therein, the second seal wall extending radially outwardly to a non-uniform radial location, wherein the second seal wall includes a plurality of segments extending to a common, first radial location and a plurality of recessed portions extending to a second radial location that is radially inward of the first radial location and each of the plurality of recessed portions extends circumferentially between an adjacent pair of the plurality of segments.

8. The gas turbine engine of claim 7 , wherein the geometry of the seal only allows the seal to be installed into the groove with a single orientation.

9. The gas turbine engine of claim 7 , wherein the groove is substantially U-shaped.

10. The face seal assembly of claim 7 , wherein the face seal assembly is located adjacent a bearing compartment disposed proximate a main shaft of the gas turbine engine.

11. The face seal assembly of claim 7 , wherein the face seal assembly is located within the compressor section.

12. A method of assembling a face seal assembly in a gas turbine engine, the method comprising:
providing a seal carrier, the seal carrier including: a main plate portion that defines anti-rotation slots and provides flanges for attachment of spring fastener features; a cylindrical body extending away from the main plate portion; and a seal retention structure, the seal retention structure at an end of the cylindrical body distal from the main plate portion and including; a first seal wall, a second seal wall and a base seal wall, the first seal wall, the second seal wall and the base seal wall defining a groove, the second seal wall extending radially outwardly to a non-uniform radial location, wherein the second seal wall includes a plurality of segments extending to a common, first radial location and a plurality of recessed portions extending to a second radial location that is radially inward of the first radial location and each of the plurality of recessed portions extends circumferentially between an adjacent pair of the plurality of segments; and
providing at least one seal segment configured to be disposed within the groove defined.

13. The method as in claim 12 , wherein the geometry of the at least one seal segment only allows the at least one seal segment to be installed into the groove with a single orientation.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Miller Jonathan Logan
• Davis Michael M

Classifications

• F05D2230/60

  Assembly methods · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F16J15/06

  with solid packing compressed between sealing surfaces · CPC title