Method and system for a ceramic matrix composite shroud hanger assembly

Patent metadata

Field	Value
Publication number	US-9874104-B2
Application number	US-201514634060-A
Country	US
Kind code	B2
Filing date	Feb 27, 2015
Priority date	Feb 27, 2015
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

Abstract

A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud.

First claim

What is claimed is:

1. A shroud and shroud hanger assembly for a gas turbine engine, said assembly comprising:
a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion, said shroud hanger assembly includes a diagonal web member that extends from a radially inner end of a forward radially extending leg to a radially outer end of an aftward radially extending leg of said aftward hanger portion; and
a shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud.

2. The shroud and hanger assembly of claim 1 , wherein said forward and aftward hanger portions are configured to couple together using a mechanical fastener connection.

3. The shroud and hanger assembly of claim 1 , wherein said forward and aftward hanger portions are configured to couple together using a bolted connection.

4. The shroud and hanger assembly of claim 1 , wherein the first coefficient of thermal expansion is equal to the second coefficient of thermal expansion.

5. The shroud and hanger assembly of claim 1 , wherein the first and second materials are ceramic matrix composite materials.

6. The shroud and hanger assembly of claim 1 , wherein said shroud is supported radially by a pin extending thorough radially outwardly extending walls of said shroud and extending through radially inwardly extending legs of said aftward hanger portion.

7. The shroud and hanger assembly of claim 1 , wherein said shroud hanger assembly includes an axial web member extending axially between a forward radially extending leg and an aftward radially extending leg of said aftward hanger portion.

8. The shroud and hanger assembly of claim 1 , wherein said aftward hanger portion is supported radially by a first tab extending axially from a radially outer end of a forward leg of said aftward hanger portion and a second tab extending axially from a radially outer end of an aftward leg of said aftward hanger portion, said first and said second tabs configured to engage circumferential lips of a casing surrounding said shroud and hanger assembly.

9. A method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly, said method comprising:
clamping a forward hanger portion and a separate aftward hanger portion of a shroud hanger assembly together, a forward radially extending wall of the shroud positioned between the forward hanger portion and the aftward hanger portion, the forward radially extending wall receiving a clamping force on a forward side from the forward hanger portion and on an aftward side from the aftward hanger portion providing a load transfer joint between the shroud and the shroud hanger assembly;
coupling the shroud hanger assembly to a casing of a turbine; and
transferring load from a nozzle through a diagonal web member of the shroud hanger assembly to the casing.

10. The method of claim 9 , wherein clamping a forward hanger portion and a separate aftward hanger portion comprises clamping the forward radially extending wall between the forward hanger portion and the aftward hanger portion at the load transfer joint.

11. A gas turbine engine comprising:
a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, said shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion, said shroud hanger assembly includes a diagonal web member that extends from a radially inner end of a forward radially extending leg to a radially outer end of an aftward radially extending leg of said aftward hanger portion; and
a shroud formed of a second material having a second coefficient of thermal expansion, said forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of said shroud.

12. The gas turbine engine of claim 11 , wherein said forward and aftward hanger portions are configured to couple together using a mechanical fastener connection.

13. The gas turbine engine of claim 11 , wherein said forward and aftward hanger portions are configured to couple together using a bolted connection.

14. The gas turbine engine of claim 11 , wherein the first coefficient of thermal expansion is equal to the second coefficient of thermal expansion.

15. The gas turbine engine of claim 11 , wherein the first and second materials are ceramic matrix composite materials.

16. The gas turbine engine of claim 11 , wherein said shroud is supported radially by a pin extending thorough radially outwardly extending walls of said shroud and extending through radially inwardly extending legs of said aftward hanger portion.

17. The gas turbine engine of claim 11 , wherein said shroud hanger assembly includes an axial web member extending axially between a forward radially extending leg and an aftward radially extending leg of said aftward hanger portion.

18. The gas turbine engine of claim 11 , wherein said aftward hanger portion is supported radially by a first tab extending axially from a radially outer end of a forward leg of said aftward hanger portion and a second tab extending axially from a radially outer end of an aftward leg of said aftward hanger portion, said first and said second tabs configured to engage circumferential lips of a casing surrounding said shroud and hanger assembly.

Assignees

• Gen Electric

Inventors

• Shapiro Jason David

Classifications

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F05D2260/15

  Load balancing · CPC title