TURBINE SHROUD WITH CLAMPED FLANGE ATTACHMENT

• US 20170002674A1
• Filed: 07/01/2015
• Published: 01/05/2017
• Est. Priority Date: 07/01/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce High Temperature Composites, Inc. (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce High Temperature Composites, Inc. (Rolls-Royce Holdings Plc), Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Vetters, Daniel K., Engel, Todd, Shinavski, Robert J.
• Granted Patent: US 10,030,541 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2250/13 trapezoidal
• CPC Class Codes: F05D 2250/23 prismatic
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.

Claims

1. A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprising:

a carrier segment formed to include a dovetail slot that opens inwardly in a radial direction toward the central axis,

a blade track segment comprising ceramic-containing materials, the blade track segment 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 track retention assembly including retainer blocks that receive at least a portion of the flange included in the blade track segment,

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 track retention assembly out of the dovetail slot.

2. The turbine shroud of claim 1, 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 blade track segment.

3. The turbine shroud of claim 2, 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 radially outward from the runner.

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

5. The turbine shroud of claim 2, wherein the recess is formed to match the cross-sectional thickness of the flange.

6. The turbine shroud of claim 1, further including a pin positioned to extend through the retainer blocks.

7. The turbine shroud of claim 6, wherein the pin is positioned to extend through the flange.

8. The turbine shroud of claim 7, wherein the pin extends through radially-elongated apertures formed in the retainer blocks sized to allow movement of the pin in the radial direction.

9. The turbine shroud of claim 1, wherein the at least two retainer blocks are clamped to the flange by a clamp-load device.

10. The turbine shroud of claim 9, wherein the clamp-load device is a threaded fastener that extends through the retainer blocks.

11. The turbine shroud of claim 1, wherein the blade track segment includes another flange positioned to be received by at least two other retainer blocks included in the track retention assembly.

12. A turbine shroud segment comprising:

a carrier formed to include a dovetail slot,

a blade track comprising ceramic-containing materials, the blade track segment formed to include a runner and a flange that extends radially outward from the runner, and

a track retention assembly including two retainer blocks that receive at least a portion of the flange of the blade track, the retainer blocks being positioned in the dovetail slot of the carrier, and that cooperate to provide a dovetail shape corresponding to the dovetail slot and being sized to block radial movement of the track retention assembly radially out of the dovetail slot,

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.

13. The turbine shroud segment of claim 12, 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.

14. The turbine shroud segment of claim 13, 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 a direction of the run of the interior surface of the at least one retainer block.

15. A method of assembly of a segmented turbine shroud that extends around a central axis, the method comprising:

providing a carrier segment formed to include a dovetail slot that opens inwardly in a radial direction toward the central axis,

providing a blade track segment comprising ceramic-containing materials, the blade track segment formed to include a runner that extends partway around the central axis and a flange that extends radially outward from the runner, and

providing a track retention assembly including positioning two retainer blocks thereof to receive at least a portion of the flange included in the blade track segment, and positioning the two retainer blocks into the dovetail slot of the carrier segment to cooperate to provide a dovetail shape corresponding to the dovetail slot sized to block radial movement of the track retention assembly radially out of the dovetail slot.

16. The method of claim 15, 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, and the exterior surface is slanted to define a slope having a rise and a run, and the interior surface is slanted to define a slope having a rise and a run, and a direction of the run of the slope of the exterior surface is perpendicular to the a direction of the run of the slope of the interior surface.

17. A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprising

a carrier segment formed to include a body and an arm extending radially inward from the body,

a blade track segment comprising ceramic-containing materials, the blade track segment formed to include a runner that extends partway around the central axis and a flange that extends radially outward from the runner, and

a track retention assembly including a retainer block configured to receive at least a portion of the flange of the blade track segment;

wherein the arm is configured to receive at least a portion of the flange and the arm and the retainer block together receive the flange to provide clamped attachment of the blade track to the carrier segment.