Turbine shroud segment with buffer air seal system

• US 10,094,234 B2
• Filed: 01/22/2016
• Issued: 10/09/2018
• Est. Priority Date: 06/29/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc), Rolls-Royce North America Technologies Inc.
• Inventors: O'Leary, Mark, Vetters, Daniel K., Brandt, Matthew R., Freeman, Ted J.
• Primary Examiner(s): Kraft, Logan
• Assistant Examiner(s): Christensen, Danielle M
• Application Number:
  US15/004,444
• Publication Number:
  US 20160376906A1
• Time in Patent Office: 991 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 11/10 using sealing fluid, e.g. steam
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/24 for turbines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Claims

1. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment includes a mount plate and a plurality of receiving walls that extend inwardly in a radial direction from the mount plate toward the central axis 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 the 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 seal member that extends radially between the receiving walls of the carrier segment and the runner of the blade track segment to resist the movement of gasses into the attachment-receiving space,

wherein at least one of the receiving walls included in the carrier segment is formed to include buffer air passageways configured to discharge buffer air along the seal member to resist the movement of gasses into the attachment-receiving space,

wherein the plurality of receiving walls are formed to include a seal channel that extends outwardly in the radial direction and the seal channel receives the seal member, and

wherein the seal channel formed by the receiving walls extends all the way around the attachment portion of the blade track segment.

2. The turbine shroud segment of claim 1, wherein the buffer air passageways are arranged along an axially forward side of the carrier segment along the central axis.

3. The turbine shroud segment of claim 1, wherein the buffer air passageways are located to discharge buffer air into the seal channel formed by the receiving walls.

4. The turbine shroud segment of claim 1, wherein the plurality of receiving walls of the carrier segment are formed to include at least one buffer groove that extends outwardly in the radial direction into the receiving walls, the at least one buffer groove is arranged radially outward of at least a portion of the seal member, and the buffer air passageways are located to discharge buffer air into the at least one buffer groove formed by the receiving walls.

5. The turbine shroud of claim 4, wherein the plurality of receiving walls are formed to include a seal channel that receives the seal member, wherein the buffer groove is smaller than the seal channel, and wherein the buffer groove extends outward in the radial direction from the seal channel.

6. The turbine shroud segment of claim 4, wherein the receiving walls of the carrier segment are formed to include at least one buffer dam that extends into the buffer groove and the buffer dam is sized to restrict the flow of buffer air through the buffer groove so that different portions of the buffer groove are pressurized at different levels when buffer air is supplied to the buffer groove from the buffer air passageways.

7. The turbine shroud segment of claim 6, wherein the buffer groove extends all the way around the attachment-receiving space defined by the carrier segment.

8. The turbine shroud segment of claim 1, wherein the seal member is formed to include a plurality of bleed holes adapted to conduct buffer air through the seal member.

9. The turbine shroud segment of claim 8, wherein the plurality of bleed holes are formed only along a leading edge of the blade track segment.

10. The turbine shroud segment of claim 8, wherein the plurality of bleed holes are each aligned with a buffer air passageway formed in the carrier segment to receive buffer air being conducted through the buffer air passageway.

11. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment including a mount plate and a wall that extends inwardly in a radial direction from the mount plate toward the central axis,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis, and

a seal member that extends radially between the wall of the carrier segment and the runner of the blade track segment to resist the movement of gasses between the wall of the carrier segment and the runner of the blade track segment, wherein the wall included in the carrier segment is formed to include a plurality of buffer air passageways configured to discharge buffer air along the interface of the carrier segment and the seal member,

wherein the wall of the carrier segment is formed to include a buffer groove that extends outwardly in the radial direction, wherein the buffer groove is arranged radially outward of at least a portion of the seal member, and wherein the buffer air passageways are located to discharge buffer air into the buffer groove, and

wherein the wall is formed to include a seal channel that receives the seal member, the buffer groove is smaller than the seal channel, and the buffer groove extends outward in the radial direction from the seal channel.

12. The turbine shroud segment of claim 11, wherein the blade track segment is formed to include an attachment portion that extends radially outward, and wherein the seal channel formed by the receiving walls extends all the way around the attachment portion of the blade track segment.

13. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment including a mount plate and a wall that extends inwardly in a radial direction from the mount plate toward the central axis,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis, and

a seal member that extends radially between the wall of the carrier segment and the runner of the blade track segment to resist the movement of gasses between the wall of the carrier segment and the runner of the blade track segment, wherein the wall included in the carrier segment is formed to include a plurality of buffer air passageways configured to discharge buffer air along the interface of the carrier segment and the seal member,

wherein the wall of the carrier segment is formed to include a buffer groove that extends outwardly in the radial direction, wherein the buffer groove is arranged radially outward of at least a portion of the seal member, and wherein the buffer air passageways are located to discharge buffer air into the buffer groove, and

wherein the wall of the carrier segment is formed to include at least one buffer dam that extends into a buffer groove and the buffer dam is sized to restrict the flow of buffer air along the buffer groove so that different portions of the buffer groove are pressurized at different levels when buffer air is supplied to the buffer groove from the buffer air passageways.

14. The turbine shroud segment of claim 13, wherein the seal member is formed to include a plurality of bleed holes adapted to conduct buffer air through the seal member.

15. The turbine shroud segment of claim 14, wherein the plurality of bleed holes are each aligned with a buffer air passageway formed in the carrier segment to receive buffer air being conducted through the buffer air passageway.

16. The turbine shroud segment of claim 13, wherein the plurality of buffer air passageways are formed only along a leading edge of the wall included in the carrier segment.

17. The turbine shroud segment of claim 13, wherein the wall is formed to include a seal channel that receives the seal, the buffer groove is smaller than the seal channel, and the buffer groove extends outward in the radial direction from the seal channel.

18. The turbine shroud segment of claim 13, wherein the blade track segment is formed to include an attachment portion that extends radially outward, and wherein the seal channel formed by the receiving walls extends all the way around the attachment portion of the blade track segment.

19. A turbine shroud segment adapted for use in a gas turbine engine having a central axis about which primary components of the engine rotate, the turbine shroud segment comprising

a carrier segment comprising metallic materials, the carrier segment including a mount plate and a wall that extends inwardly in a radial direction from the mount plate toward the central axis,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around the central axis, and

a seal member that extends radially between the wall of the carrier segment and the runner of the blade track segment to resist the movement of gasses between the wall of the carrier segment and the runner of the blade track segment, wherein the wall included in the carrier segment is formed to include a plurality of buffer air passageways configured to discharge buffer air along the interface of the carrier segment and the seal member,

wherein the seal member is formed to include a plurality of bleed holes adapted to conduct buffer air through the seal member, and

wherein the plurality of bleed holes are formed only along a leading edge of the blade track segment.

20. The turbine shroud segment of claim 19, wherein the blade track segment is formed to include an attachment portion that extends radially outward, and wherein the seal channel formed by the receiving walls extends all the way around the attachment portion of the blade track segment.