Ceramic matrix composite ring shroud retention methods-CMC pin-head

Patent metadata

Field	Value
Publication number	US-9945257-B2
Application number	US-201514858508-A
Country	US
Kind code	B2
Filing date	Sep 18, 2015
Priority date	Sep 18, 2015
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

The present disclosure is directed to a retention assembly for a stationary gas turbine component. A first stationary gas turbine wall defines a first wall cavity and a second stationary gas turbine wall constructed from a ceramic matrix composite defines a second wall cavity. A pin shaft constructed from a first material includes a first shaft end and a second shaft end. A pin head constructed from the ceramic matrix composite includes a first pin head end and a second pin head end. The pin head defines a pin head cavity extending inward from the first pin head end. The first shaft end is positioned in the first wall cavity, and the second shaft end is positioned in the pin head cavity. The second pin head end is positioned in the second wall cavity. The first material is different from the ceramic matrix composite.

First claim

What is claimed is:

1. A retention assembly for a stationary ceramic matrix composite gas turbine component, comprising:
a first stationary gas turbine wall defining a first wall cavity extending inward from a first surface of the first stationary gas turbine wall, the first wall cavity extending from the first surface only partially through the first stationary gas turbine wall;
a second stationary gas turbine wall constructed from a ceramic matrix composite and defining a second wall cavity extending inward from a second surface of the second stationary gas turbine wall, the second surface facing the first surface and the second wall cavity extending from the second surface only partially through the second stationary gas turbine wall;
a pin shaft constructed from a first material and comprising a first shaft end and a second shaft end; and
a pin head constructed from the ceramic matrix composite and comprising a first pin head end facing the first surface and a second pin head end, the pin head defining a pin head cavity extending from the first pin head end toward the second pin head end;
wherein the first shaft end is positioned in the first wall cavity, the second shaft end is positioned in the pin head cavity, the second pin head end is positioned in the second wall cavity, and the first material is different from the ceramic matrix composite.

2. The retention assembly of claim 1 , wherein the first stationary gas turbine wall is a turbine shroud mount and the second stationary gas turbine wall is a turbine shroud,
wherein the second wall cavity is concave, and
wherein the second pin head end is convex.

3. The retention assembly of claim 1 , wherein a length, a width, or a diameter of the pin head cavity is relatively longer than a respective length, width, or diameter of the second shaft end.

4. The retention assembly of claim 3 , further comprising:
a potting material positioned in the pin head cavity.

5. The retention assembly of claim 3 , wherein the first material is a metallic material.

6. The retention assembly of claim 1 , wherein the pin shaft and the pin head comprise an assembled radial length to substantially prevent radial movement between the first stationary gas turbine wall and the second stationary gas turbine wall.

7. The retention assembly of claim 1 , wherein an outer surface of the first pin head end is flat.

8. The retention assembly of claim 1 , wherein the second wall cavity has a substantially circular cross-section, and further wherein a diameter of the second wall cavity is substantially the same as a diameter of the pin head to substantially prevent axial and circumferential movement between the second stationary gas turbine wall and the pin head.

9. A gas turbine, comprising:
a compressor;
a combustion section; and
a turbine section, the turbine section comprising:
a turbine shroud mount defining a turbine shroud mount cavity extending outward from a radially inner surface of the turbine shroud mount, the turbine shroud mount cavity extending from the radially inner surface only partially through the turbine shroud mount; and
a turbine shroud constructed from a ceramic matrix composite and defining a turbine shroud cavity extending radially inward from a radially outer surface of the turbine shroud, the radially outer surface facing the radially inner surface and the turbine shroud cavity extending from the radially outer surface only partially through the turbine shroud;
a pin shaft constructed from a first material and comprising a first shaft end and a second shaft end; and
a pin head constructed from the ceramic matrix composite and comprising a first pin head end facing the radially inner surface and a second pin head end, the pin head defining a pin head cavity extending radially inward from the first pin head end toward the second pin head end;
wherein the first shaft end is positioned in the turbine shroud mount cavity, the second shaft end is positioned in the pin head cavity, the second pin head end is positioned in the turbine shroud cavity, and the first material is different from the ceramic matrix composite.

10. The gas turbine of claim 9 , wherein a length, a width, or a diameter of the pin head cavity is relatively longer than a respective length, width, or diameter of the second shaft end.

11. The gas turbine of claim 10 , further comprising:
a potting material positioned in the pin head cavity.

12. The gas turbine of claim 9 , wherein an outer surface of the first pin head end is flat.

13. The gas turbine of claim 10 , wherein the first material is a metallic material.

14. The gas turbine of claim 9 , wherein the pin shaft and the pin head comprise an assembled radial length to substantially prevent radial movement between the turbine shroud mount and the turbine shroud.

15. The gas turbine of claim 9 , wherein the turbine shroud cavity has a substantially circular cross-section.

16. The gas turbine of claim 9 , wherein the turbine shroud cavity has a substantially circular cross-section, and further wherein a diameter of the turbine shroud cavity is substantially the same as a diameter of the pin head to substantially prevent axial movement between the turbine shroud and the pin head.

17. A method for retaining a stationary component in a gas turbine, the method comprising:
forming a turbine shroud mount cavity in a turbine shroud mount, the turbine shroud mount cavity extending radially outward from a radially inner surface of the turbine shroud mount and only partially through the turbine shroud mount;
forming a turbine shroud cavity in a turbine shroud constructed from a ceramic matrix composite, the turbine shroud cavity extending radially inward from a radially outer surface of the turbine shroud and only partially through the turbine shroud;
forming a pin head cavity in a first pin head end of a pin head, the pin head constructed from the ceramic matrix composite and having a second pin head end, the pin head cavity extending radially inward from the first pin head end toward the second pin head end;
placing a first end of a pin shaft into the turbine shroud mount cavity, the pin shaft constructed of a first material different from the ceramic matrix composite;
placing a second end of the pin shaft into the pin head cavity of the pin head, the first pin head end facing the radially inner surface; and
placing the second pin head end into the turbine shroud cavity, wherein the radially outer surface faces the radially inner surface.

18. The method of claim 17 , wherein the pin head cavity is formed with a length, a width, or a diameter relatively longer than a respective length, width, or diameter of the pin shaft.

19. The method of claim 18 , further comprising: placing a potting material in the pin head cavity prior to placing the second end of the pin shaft into the pin head cavity.

20. The method of claim 17 , wherein the turbine shroud is formed with a length, a width, or a diameter substantially the same as a respective length, width, or diameter of the pin head.

Assignees

• Gen Electric

Inventors

• Fitzpatrick Dylan James
• Tura Christopher Paul

Classifications

• F02C3/04

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

• F05D2220/32

  in gas turbines · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/08

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

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title