Turbine shroud segment assembly with expansion joints

Patent metadata

Field	Value
Publication number	US-9915153-B2
Application number	US-201514708934-A
Country	US
Kind code	B2
Filing date	May 11, 2015
Priority date	May 11, 2015
Publication date	Mar 13, 2018
Grant date	Mar 13, 2018

Abstract

A shroud segment assembly for use within a turbine shroud of a gas turbine engine may generally include a forward shroud portion having a forward outer arm and a forward inner arm extending from a forward wall and an aft shroud portion having an aft outer arm and an aft inner arm extending from an aft wall. Additionally, the shroud segment assembly may include a first expansion joint positioned between the forward and aft shroud portions such that the first expansion joint extends circumferentially between the forward outer arm of the forward shroud portion and the aft outer arm of the aft shroud portion and a second expansion joint positioned between the forward and aft shroud portions such that the second expansion joint extends circumferentially between the forward inner arm of the forward shroud portion and the aft outer arm of the aft shroud portion.

First claim

What is claimed is:

1. A shroud segment assembly for use within a turbine shroud of a gas turbine engine, the shroud segment assembly comprising:
a forward shroud portion extending circumferentially between a first forward end and a second forward end, the forward shroud portion including a forward outer arm and a forward inner arm extending from a forward wall of the forward shroud portion;
a separate aft shroud portion extending circumferentially between a first aft end and a second aft end, the aft shroud portion including an aft outer arm and an aft inner arm extending from an aft wall of the aft shroud portion;
a first expansion joint positioned between the forward and aft shroud portions such that the first expansion joint extends circumferentially between the forward outer arm of the forward shroud portion and the aft outer arm of the aft shroud portion; and
a second expansion joint positioned between the forward and aft shroud portions such that the second expansion joint extends circumferentially between the forward inner arm of the forward shroud portion and the aft inner arm of the aft shroud portion,
wherein the first expansion joint includes a radially outer wall, a radially inner wall and a connecting wall extending between the radially inner and outer walls, the first expansion joint defining a forward recess between the radially inner and outer walls along a forward side of the connecting wall, the first expansion joint further defining an aft recess between the radially inner and outer walls along an aft side of the connecting wall, and
wherein ends of the radially outer wall of the first expansion joint are configured to be supported by a hanger of the gas turbine engine.

2. The shroud segment assembly of claim 1 , wherein the forward outer arm is configured to be received within the forward recess and the aft outer arm is configured to be received within the aft recess.

3. The shroud segment assembly of claim 1 , wherein the second expansion joint includes a radially outer wall, a radially inner wall and a connecting wall extending between the radially inner and outer walls, the second expansion joint defining a forward recess between the radially inner and outer walls along a forward side of the connecting wall, the second expansion joint further defining an aft recess between the radially inner and outer walls along an aft side of the connecting wall.

4. The shroud segment assembly of claim 3 , wherein the forward inner arm is configured to be received within the forward recess of the second expansion joint and the aft inner arm is configured to be received within the aft recess of the second expansion joint.

5. The shroud segment assembly of claim 3 , wherein the forward inner arm defines a forward joint recess and the aft inner arm defines an aft joint recess, the radially inner wall of the second expansion joint extending between the forward and aft inner arms so as to be received within the forward and aft joint recesses.

6. The shroud segment assembly of claim 5 , wherein the forward inner arm defines a forward radially inner surface of the forward shroud portion and the aft inner arm defines an aft radially inner surface of the aft shroud portion, the radially inner wall of the second expansion joint defining a joint inner surface of the second expansion joint, wherein the radially inner wall of the second expansion joint is received within the forward and aft joint recesses such that the joint inner surface is substantially radially aligned with the forward and aft radially inner surfaces.

7. The shroud segment assembly of claim 3 , wherein the forward inner arm defines a forward radially inner surface of the forward shroud portion and the aft inner arm defines an aft radially inner surface of the aft shroud portion, wherein the radially inner wall of the second expansion joint is disposed radially inwardly from the forward and aft radially inner surfaces.

8. The shroud segment assembly of claim 3 , wherein the radially inner wall of the second expansion joint defines at least a portion of a flowpath surface for the shroud segment assembly.

9. A shroud segment assembly for use within a turbine shroud of a gas turbine engine, the shroud segment assembly comprising:
a shroud body extending circumferentially between a first end and a second end and radially between a radially inner side and a radially outer side, the shroud body including an outer wall extending along the radially outer side of the shroud body and forward and aft walls extending radially inwardly from the outer wall, the shroud body further including a first arm extending from the forward wall in the direction of the aft wall along the radially inner side of the shroud body and a second arm extending from the aft wall in the direction of the forward wall along the radially inner side of the shroud body, the first arm being spaced apart axially from the second arm such that a circumferential slot is defined between the first and second arms that extends circumferentially between the first and second ends along the radially inner side of the shroud body; and
an expansion joint positioned within the circumferential slot between the first and second arms,
wherein the expansion joint includes a radially outer wall, a radially inner wall and a connecting wall extending between the radially inner and outer walls, the expansion joint defining a forward recess between the radially inner and outer walls along a forward side of the connecting wall, the expansion joint further defining an aft recess between the radially inner and outer walls along an aft side of the connecting wall, and
wherein the first arm defines a forward joint recess and the second arm defines an aft joint recess, the radially inner wall of the expansion joint extending between the first and second arms to be received within the forward and aft joint recesses.

10. The shroud segment assembly of claim 9 , wherein the first arm is configured to be received within the forward recess and the second arm is configured to be received within the aft recess.

11. The shroud segment assembly of claim 9 , wherein the first arm defines a forward radially inner surface and the second arm defines an aft radially inner surface, the radially inner wall defining a joint inner surface of the expansion joint, wherein the radially inner wall is received within the forward and aft joint recesses such that the joint inner surface is substantially radially aligned with the forward and aft radially inner surfaces.

12. The shroud segment assembly of claim 9 , wherein the first arm defines a forward radially inner surface and the second arm defines an aft radially inner surface, wherein the radially inner wall is disposed radially inwardly from the forward and aft radially inner surfaces.

13. The shroud segment assembly of claim 9 , wherein the radially inner wall defines at least a portion of a flowpath surface for the shroud segment assembly.

14. A shroud segment assembly for use within a turbine shroud of a gas turbine engine, the shroud segment assembly comprising:
a shroud body extending circumferentially between a first end and a second end and radially between a radially inner side and a radially outer side, the shroud body including an inner wall extending along the radially inner side of the shroud body and forward and aft walls extending radially outwardly from the inner wall, the shroud body further including a first arm extending from the forward wall in the direction of the aft wall along the radially outer side of the shroud body and a second arm extending from the aft wall in the direction of the forward wa

Assignees

• Gen Electric

Inventors

• Sener Alexander Martin

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D5/225 Primary

  by shrouding · CPC title