Mounted ceramic matrix composite component with clamped flange attachment

Patent metadata

Field	Value
Publication number	US-10605121-B2
Application number	US-201816005118-A
Country	US
Kind code	B2
Filing date	Jun 11, 2018
Priority date	Jul 1, 2015
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The assembly also includes a retention assembly for coupling the supported component to the carrier.

First claim

What is claimed is:

1. An assembly for a gas turbine engine, the assembly comprising
a carrier component formed to include a dovetail slot that opens inwardly in a radial direction toward the central axis,
a supported component comprising ceramic-containing materials, the supported component being formed to include a runner and a flange that extends from the runner, and
a retention assembly including retainer blocks that receive at least a portion of the flange included in the supported component, wherein the retainer blocks are positioned in the dovetail slot of the carrier segment and cooperate to provide a dovetail shape corresponding to the dovetail slot and being sized to block movement of the retention assembly out of the dovetail slot, wherein at least one of the retainer blocks is formed to include a recess that receives at least a portion of the flange of the supported component, and wherein the flange from one side to another side has a constant cross-sectional thickness at each point along a length of the flange that extends outward from the runner.

2. The assembly of claim 1 , wherein the recess is formed to match at least a portion of a profile created by the flange.

3. The assembly of claim 1 , wherein the recess is formed to match the cross-sectional thickness of the flange.

4. The assembly of claim 1 , wherein the retainer blocks are clamped to the flange by a clamp-load device.

5. The assembly of claim 4 , wherein the clamp-load device is a threaded fastener that extends through the retainer blocks.

6. The assembly of claim 1 , wherein the runner is arcuate and shaped to extend partway around a central axis.

7. The assembly of claim 6 , wherein the flange extends radially outward from the runner away from the central axis.

8. The assembly of claim 1 , wherein each retainer block includes an exterior surface configured to engage with a surface of the dovetail slot of the carrier, and an interior surface configured to engage an exterior surface of the flange.

9. The assembly of claim 8 , wherein the exterior surface of at least one of the retainer blocks faces towards the runner of the blade track and at least one of the interior surfaces of the retainer block faces away from the runner of the blade track.

10. The assembly of claim 9 , wherein the exterior surface of the at least one retainer block is slanted to define a rise and a run, and the interior surface of the at least one retainer block is slanted to define a rise and a run, and a direction of the run of the exterior surface of the at least one retainer block is perpendicular to the direction of the run of the interior surface of the at least one retainer block.

11. A turbine engine assembly, the assembly comprising
a carrier component formed to include a dovetail slot that opens inwardly in a radial direction toward the central axis,
a supported component comprising ceramic-containing materials, the supported component being formed to include a flange that extends from another portion of the supported component, and
a retention assembly including retainer blocks that receive at least a portion of the flange included in the supported component, wherein the retainer blocks are positioned in the dovetail slot of the carrier component and cooperate to provide a dovetail shape corresponding to the dovetail slot and being sized to block movement of the retention assembly out of the dovetail slot, and a pin positioned to extend through the retainer blocks.

12. The assembly of claim 11 , wherein the pin is positioned to extend through the flange.

13. The assembly of claim 12 , wherein the pin extends through radially-elongated apertures formed in the retainer blocks sized to allow movement of the pin in the radial direction.

14. The assembly of claim 11 , wherein the supported component includes another flange positioned to be received by at least two other retainer blocks included in the retention assembly.

15. The assembly of claim 11 , wherein the flange from one side to another side has a constant cross-sectional thickness at each point along a length of the flange that extends outward from the runner.

16. A turbine engine assembly, the assembly comprising
a carrier component formed to include a dovetail slot that opens inwardly in a radial direction toward the central axis,
a supported component comprising ceramic-containing materials, the supported component being formed to include a runner that extends partway around the central axis and a flange that extends radially outward from the runner, and
a retention assembly including retainer blocks that receive at least a portion of the flange included in the supported component, wherein the retainer blocks are positioned in the dovetail slot of the carrier component and cooperate to provide a dovetail shape corresponding to the dovetail slot and being sized to block movement of the retention assembly out of the dovetail slot, and wherein the at least two retainer blocks are clamped to the flange by a clamp-load device, and wherein the clamp-load device is a threaded fastener that extends through the retainer blocks.

17. The assembly of claim 16 , wherein the recess is formed to match at least a portion of a profile created by the flange.

18. The assembly of claim 16 , wherein the flange from one side to another side has a constant cross-sectional thickness at each point along a length of the flange that extends outward from the runner.

19. The assembly of claim 18 , wherein the recess is formed to match the cross-sectional thickness of the flange.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce High Temperature Composites Inc
• Rolls Royce North America Tech Inc

Inventors

• Vetters Daniel K
• Engel Todd
• Shinavski Robert J

Classifications

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• F05D2250/13

  trapezoidal · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2250/23

  prismatic · CPC title