Advanced stationary sealing cooled cross-section for axial retention of ceramic matrix composite shrouds

Patent metadata

Field	Value
Publication number	US-10273821-B2
Application number	US-201514850383-A
Country	US
Kind code	B2
Filing date	Sep 10, 2015
Priority date	Sep 10, 2015
Publication date	Apr 30, 2019
Grant date	Apr 30, 2019

Abstract

In one aspect, the present subject matter is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a first seal layer defining a first seal layer aperture extending therethrough. A second seal layer defines an elongated slot extending therethrough. The elongated slot includes a first end and a second end. A third seal layer defines a third seal layer aperture extending therethrough. The second seal layer is positioned between the first seal layer and the third seal layer such that the first seal layer aperture is in fluid communication with the first end and the third seal layer aperture is in fluid communication with the second end.

First claim

What is claimed is:

1. A gas turbine sealing assembly, comprising:
a first static gas turbine wall;
a second static gas turbine wall; and
a seal disposed between the first static gas turbine wall and the second static gas turbine wall, the seal comprising:
a top seal layer defining a top seal layer aperture extending through the top seal layer;
a middle seal layer defining an elongated slot extending through the middle seal layer; and
a bottom seal layer defining a bottom seal layer aperture extending through the bottom seal layer, wherein the middle seal layer is positioned between the top seal layer and the bottom seal layer such that the top seal layer aperture is in fluid communication with a first position in the elongated slot and the bottom seal layer aperture is in fluid communication with a second position in the elongated slot;
wherein the top seal layer, the middle seal layer, and the bottom seal layer each comprise a first wall connected to a second wall by a convolution, and wherein the convolution of the top seal layer defines the top seal layer aperture, the convolution of the middle seal layer defines the elongated slot, and the convolution of the bottom seal layer defines the bottom seal aperture.

2. The gas turbine sealing assembly of claim 1 , wherein the first static gas turbine wall comprises a turbine shroud assembly mount and the second gas static gas turbine wall comprises a stator vane assembly mount.

3. The gas turbine sealing assembly of claim 1 , wherein the first wall of the top seal layer, the middle seal layer, and the bottom seal layer is a first inner wall, and wherein the second wall of the top seal layer, the middle seal layer, and the bottom seal layer is a second inner wall, and wherein the convolution of the top seal layer, the middle seal layer, and the bottom seal layer is a middle convolution.

4. The gas turbine sealing assembly of claim 1 , wherein the bottom seal layer supports and positions the middle seal layer and the middle seal layer supports and positions the top seal layer.

5. The gas turbine sealing assembly of claim 1 , wherein the first seal layer aperture or the bottom seal layer aperture comprise a circular cross-section.

6. The gas turbine sealing assembly of claim 1 , wherein the elongated slot is at least five times longer than first seal layer aperture and the bottom seal layer aperture.

7. The gas turbine sealing assembly of claim 1 , wherein the elongated slot is at least ten times longer than first seal layer aperture and the bottom seal layer aperture.

8. The gas turbine sealing assembly of claim 1 , wherein the first seal layer aperture and the bottom seal layer aperture comprise the same cross-sectional area.

9. The gas turbine sealing assembly of claim 1 , wherein the first seal layer aperture and the bottom seal layer aperture comprise the same shape.

10. A gas turbine, comprising:
a compressor;
a combustion section;
a turbine section comprising:
a turbine shroud mount; and
a stator vane mount; and

a seal disposed between the turbine shroud mount and the stator vane mount, the seal comprising:
a top seal layer defining a top seal layer aperture extending through the top seal layer;
a middle seal layer defining an elongated slot extending through the middle seal layer; and
a bottom seal layer defining a bottom seal layer aperture extending through the bottom seal layer, wherein the middle seal layer is positioned between the top seal layer and the bottom seal layer such that the top seal layer aperture is in fluid communication with a first position in the elongated slot and the bottom seal layer aperture is in fluid communication with a second position in the elongated slot, and the first position is a first end of the elongated slot and the second position is a second end of the elongated slot;
wherein the top seal layer, the middle seal layer, and the bottom seal layer each comprise a first wall connected to a second wall by a convolution, and wherein the convolution of the top seal layer defines the top seal layer aperture, the convolution of the middle seal layer defines the elongated slot, and the convolution of the bottom seal layer defines the bottom seal aperture.

11. The gas turbine of claim 10 , wherein the first wall of the top seal layer, the middle seal layer, and the bottom seal layer is a first inner wall, and wherein the second wall of the top seal layer, the middle seal layer, and the bottom seal layer is a second inner wall, and wherein the convolution of the top seal layer, the middle seal layer, and the bottom seal layer is a middle convolution.

12. The gas turbine of claim 10 , wherein the top seal layer, the middle seal layer, and the bottom seal layer each comprise three or more convolutions.

13. The gas turbine of claim 10 , wherein the bottom seal layer supports and positions the middle seal layer and the middle seal layer supports and positions the top seal layer.

14. The gas turbine of claim 10 , wherein the elongated slot is at least five times longer than the top seal layer aperture and the bottom seal layer aperture.

15. The gas turbine of claim 10 , wherein the elongated slot is at least ten times longer than the top seal layer aperture and the bottom seal layer aperture.

Assignees

• Gen Electric

Inventors

• Fitzpatrick Dylan James

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F02C3/04

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

• F02C7/28 Primary

  Arrangement of seals · CPC title

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F16J15/02

  between relatively-stationary surfaces (F16J15/46, F16J15/48 take precedence) · CPC title