TURBINE SHROUD WITH SEALED BOX SEGMENTS

• US 20170298753A1
• Filed: 04/13/2016
• Published: 10/19/2017
• Est. Priority Date: 04/13/2016
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: O'Leary, Mark
• Granted Patent: US 10,458,268 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 11/16 by self-adjusting means F01D11/12 takes precedence
• CPC Class Codes: F01D 25/005 Selecting particular materials
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2240/59 Lamellar seals
• 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 shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment.

Claims

1. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and

at least one strip seal configured to resist the movement of gasses into the attachment-receiving space, the at least one strip seal member arranged to extend across a gap formed radially between the carrier segment and the runner into a radially-outwardly opening runner slot formed in a radially-outwardly facing surface of the runner.

2. The turbine shroud segment of claim 1, further comprising at least one spring member corresponding to the at least one strip seal and configured to push a corresponding strip seal toward the central axis.

3. The turbine shroud segment of claim 2, wherein the at least one spring member is arranged in a radially-inwardly opening carrier slot formed in the carrier segment and a strip seal is at least partially received in the radially-inwardly opening carrier slot.

4. The turbine shroud segment of claim 1, wherein a first strip seal is a one-piece component and extends at least most of the way around the attachment portion of the blade track segment.

5. The turbine shroud segment of claim 4, wherein the first strip seal is formed to include a gap as it extends around the attachment portion of the blade track segment sized to accommodate thermal expansion induced during use of the turbine shroud segment.

6. The turbine shroud segment of claim 4, wherein the first strip seal is sized to form an overlapped portion as it extends around the attachment portion of the blade track segment to accommodate thermal expansion induced during use of the turbine shroud segment.

7. The turbine shroud segment of claim 1, wherein the runner of the blade track segment includes a layer of coating that provides at least a portion of the radially-outwardly facing surface of the runner into which the radially-outwardly opening runner slot is formed.

8. The turbine shroud segment of claim 7, wherein the radially-outwardly opening runner slot extends through the layer of coating and into a ceramic matrix composite portion of the runner.

9. The turbine shroud segment of claim 7, wherein the radially-outwardly opening runner slot extends into the layer of coating without extending through the layer of coating into other portions of the blade track segment.

10. The turbine shroud segment of claim 1, further comprising a track-segment coupler assembly configured to attach the blade track segment to the carrier segment, wherein the track-segment coupler assembly includes a retainer plate arranged between the runner of the blade track segment and at least part of the attachment portion of the blade track segment, a support shaft that extends from the carrier segment to the retainer plate, an outer spring member arranged radially between the carrier segment and the attachment portion of the blade track segment, and an inner spring member arranged radially between the retainer plate and at least part of the attachment portion of the blade track segment.

11. The turbine shroud assembly of claim 10, wherein the attachment portion of the blade track segment has a U-shaped cross-section and cooperates with the runner of the blade track segment to define a receiving space in which the retainer plate is received.

12. A turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space channel formed by the carrier segment, and

a track-segment coupler assembly configured to attach the blade track segment to the carrier segment, wherein the track-segment coupler assembly includes a retainer plate arranged between the runner of the blade track segment and at least part of the attachment portion of the blade track segment, a support shaft that extends from the carrier segment to the retainer plate, an outer spring member arranged radially between the carrier segment and the attachment portion of the blade track segment, and an inner spring member arranged radially between the retainer plate and at least part of the attachment portion of the blade track segment.

13. The turbine shroud segment of claim 12, wherein the attachment portion of the blade track segment has a U-shaped cross-section and cooperates with the runner of the blade track segment to define a receiving space in which the retainer plate is received.

14. The turbine shroud segment of claim 13, wherein the support shaft is formed to include a threaded portion adapted to be engaged during assembly of the turbine shroud segment to apply a predetermined load onto the blade track segment that is distributed along the attachment portion of the blade track segment by the outer spring member and the inner spring member.

15. The turbine shroud assembly of claim 12, further comprising a seal member configured to resist the movement of gasses into the attachment-receiving space, the seal member arranged to extend across a gap formed radially between the carrier segment and the runner.

16. The turbine shroud assembly of claim 15, further comprising a spring member arranged in a radially-inwardly opening carrier slot formed in the carrier segment and configured to push the seal member toward the central axis.

17. The turbine shroud assembly of claim 12, wherein the runner of the blade track segment includes a layer of coating that provides at least a portion of a radially-outwardly facing surface of the runner into which a radially-outwardly opening runner slot is formed and a portion of the seal member is received in the radially-outwardly opening runner slot.

18. An assembly adapted for use in an engine, the assembly comprising

a first component comprising metallic materials, the first component formed to define an attachment-receiving space,

a second component comprising ceramic matrix composite materials, the second component formed to include a gas path facing portion shaped to extend partway around a central axis and an attachment portion that extends radially outward from the gas path facing portion into the attachment-receiving space channel formed by the first component, and

at least one strip seal configured to resist the movement of gasses into the attachment-receiving space, the at least one strip seal member arranged to extend across a gap formed radially between the first component and the gas path facing portion of the second component into a radially-outwardly opening slot formed in a radially-outwardly facing surface of the gas path facing portion of the second component.

19. The assembly of claim 18, further comprising at least one spring member corresponding to the at least one strip seal arranged in a radially-inwardly opening slot formed in the first component, wherein the at least one spring member is configured to push a corresponding strip seal toward the central axis.

20. The assembly of claim 18, further comprising a coupler assembly configured to attach the second component to the first component, wherein the coupler assembly includes a retainer plate arranged between the gas path facing portion of the second component and at least part of the attachment portion of the second component, a support shaft that extends from the first component to the retainer plate, an outer spring member arranged radially between the first component and the attachment portion of the second component, and an inner spring member arranged radially between the retainer plate and at least part of the attachment portion of the second component.