Gas turbine engine ring seal

Patent metadata

Field	Value
Publication number	US-10145308-B2
Application number	US-201514611920-A
Country	US
Kind code	B2
Filing date	Feb 2, 2015
Priority date	Feb 10, 2014
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.

First claim

What is claimed is:

1. A gas turbine engine comprising:
engine static structure that includes first and second case portions secured to one another at a joint that provides a groove extending in an axial direction;
first and second members fluidly separating cavities from one another; and
a seal assembly constrained by the engine structure, the seal assembly includes a carrier and a seal that engages the first member, wherein the first member is a duct providing a turbine exhaust flow path, and the second member constrained by the carrier, and the carrier has an end in the groove, the end is removably captured between the first and second case portions.

2. The gas turbine engine according to claim 1 , wherein the carrier has first and second legs, and the second leg supporting the seal.

3. The gas turbine engine according to claim 2 , wherein the groove provides an attachment feature that receives the first leg which provides the end.

4. The gas turbine engine according to claim 3 , wherein the first and second case portions are first and second outer case structures secured to one another at the joint which includes a flange.

5. The gas turbine engine according to claim 4 , wherein the first outer case structure provides an outer diameter, and the second outer case structure includes an inner diameter that radially locates relative to and is nested with respect to the outer diameter, the groove provided at the inner and outer diameters.

6. The gas turbine engine according to claim 1 , wherein the duct includes a radially extending flange against which the seal engages.

7. The gas turbine engine according to claim 2 , wherein the carrier is generally S-shaped and provides first and second annular recesses respectively arranged between the first leg and an intermediate leg and the intermediate leg and the second leg.

8. The gas turbine engine according to claim 7 , wherein the second member has an end constrained between the intermediate leg and the engine static structure.

9. The gas turbine engine according to claim 8 , wherein the cavities includes first, second and third cavities, the second member separates the first and third cavities, and the seal separates the second and third cavities.

10. The gas turbine engine according to claim 9 , wherein the first cavity is configured to be at a greater pressure than the second cavity, and the second cavity is configured to be at a greater pressure than the third cavity.

11. The gas turbine engine according to claim 1 , wherein the seal is one of a brush seal, W seal or piston seal.

12. The gas turbine engine according to claim 11 , wherein the seal is secured to the carrier to provide an integrated line replaceable unit.

13. The gas turbine engine according to claim 1 , wherein the seal assembly is annular, the carrier is generally S-shaped and has first, intermediate and second legs, the second leg supports the seal, the carrier provides first and second annular recesses respectively arranged between the first leg and an intermediate leg and the intermediate leg and the second leg, the seal arranged in the second annular recess, and the first annular recess configured to receive a portion of the engine static structure.

14. The gas turbine engine according to claim 13 , wherein the seal is one of a brush seal, W seal or piston seal, the seal extending axially beyond a terminal end of the second leg.

15. The gas turbine engine according to claim 13 , wherein the seal is secured to the carrier to provide an integrated line replaceable unit.

16. A gas turbine engine comprising:
engine static structure;
first and second members fluidly separating cavities from one another;
a seal assembly constrained by the engine structure, the seal assembly includes a carrier and a seal that engages the first member, wherein the first member is a duct providing a turbine exhaust flow path, and the second member constrained by the carrier; and
wherein the carrier has first and second legs with the first leg constrained by an attachment feature on the engine static structure, and the second leg supporting the seal, wherein the engine static structure includes first and second case portions secured to one another at a joint, the carrier arranged at the joint, wherein the joint includes a groove that provides the attachment feature, wherein the first and second case portions are first and second outer case structures secured to one another at a flanged joint, the groove extending in an axial direction, wherein the first outer case structure provides an outer diameter, and the second outer case structure includes an inner diameter that radially locates relative to the outer diameter, the groove provided at the inner and outer diameters, wherein the second outer case structure includes a protrusion arranged adjacent to the first leg to axially retain the carrier within the groove.

Assignees

• United Technologies Corp

Inventors

• Roy Thill Carson A
• Broomer Mark
• Davis Timothy M
• Mcgarrah Craig R
• Rogers Mark J
• Keene Russell E
• Swift Anthony B

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/56

  Brush seals · CPC title

• F16J15/0887

  the sealing effect being obtained by elastic deformation of the packing · CPC title

• F05D2240/58

  Piston ring seals · CPC title