Turbine shroud segment with flange-facing perimeter seal

Patent metadata

Field	Value
Publication number	US-2016376901-A1
Application number	US-201615004442-A
Country	US
Kind code	A1
Filing date	Jan 22, 2016
Priority date	Jun 29, 2015
Publication date	Dec 29, 2016
Grant date	—

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.

First claim

What is claimed is:

1 . 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 seal member configured to resist the movement of gasses into the attachment-receiving space, the seal member shaped to extend around the attachment portion of the blade track segment and arranged to engage a radially-outwardly facing surface of the runner.

2 . The turbine shroud segment of claim 1 , wherein the seal member is a one-piece component that extends all the way around the attachment portion of the blade track segment and along a perimeter edge of the runner.

3 . The turbine shroud segment of claim 2 , wherein the seal member comprises mica

4 . The turbine shroud segment of claim 1 , wherein the seal member is formed to include a plurality of radially-extending bleed holes adapted to conduct a flow of buffer air through the seal member to resist the movement of gasses into the attachment-receiving space.

5 . The turbine shroud segment of claim 4 , wherein the plurality of bleed holes are formed only along a leading edge of the blade track segment.

6 . The turbine shroud segment of claim 1 , wherein the runner of the blade track segment includes a layer of environmental barrier coating that provides the radially-outwardly facing surface of the runner engaged by the seal member.

7 . The turbine shroud segment of claim 6 , wherein the blade track segment includes uncoated portions and the coating applied to a radially-outwardly facing surface of the runner included in the blade track segment is smoother than the uncoated portions of the blade track segment.

8 . The turbine shroud segment of claim 1 , wherein 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, the receiving walls extend all the way around the attachment portion of the blade track segment, the attachment-receiving space is defined by the mount plate and the receiving walls, and the seal member extends radially between the receiving walls of the carrier and the runner of the blade track segment to resist the movement of gasses into the attachment-receiving space.

9 . The turbine shroud segment of claim 8 , wherein the plurality of receiving walls are formed to include seal channels that extends outwardly in the radial direction and the seal channels receive the seal.

10 . The turbine shroud segment of claim 9 , wherein the seal channels formed by the receiving walls open into one another and cooperate to form a continuous channel that extends all the way around the attachment portion of the blade track segment.

11 . The turbine shroud segment of claim 8 , wherein the seal member includes at least one metallic member shaped to form at least one U-shaped lobe that defines a pressure-activated channel, the pressure-activated channel arranged to open into the seal channels and the seal member configured to expanded when pressurized air is supplied to the seal channels.

12 . The turbine shroud segment of claim 11 , wherein the metallic member is a one-piece component that extends all the way around the attachment portion of the blade track segment and along a perimeter edge of the runner.

13 . The turbine shroud segment of claim 11 , wherein the metallic member is configured to expand in an axial direction along the central axis when pressurized air is supplied to the seal channels.

14 . The turbine shroud segment of claim 11 , wherein the metallic member is configured to expand in the radial direction when pressurized air is supplied to the seal channels.

15 . The turbine shroud segment of claim 14 , wherein the seal member includes two metallic members, each metallic member shaped to form at least one U-shaped lobe that defines a pressure-activated channel arranged to open into the seal channels, and each metallic member is a one-piece component that extends all the way around the attachment portion of the blade track segment.

16 . A turbine shroud comprising
a carrier comprising metallic materials, the carrier formed to define an attachment-receiving space, a blade track comprising ceramic matrix composite materials, the blade track formed to include a runner shaped to extend at least 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 seal member configured to resist the movement of gasses into the attachment-receiving space, the seal member arranged to engage a radially-outwardly facing surface of the runner.

17 . The turbine shroud of claim 16 , wherein the carrier includes a mount plate and at least one receiving wall that extends inwardly in a radial direction from the mount plate toward the central axis, the at least one receiving wall is formed to include a seal channel that extends outwardly in the radial direction, and the seal channel is configured to receive the seal member.

18 . The turbine shroud of claim 16 , wherein the runner of the blade track includes a layer of environmental barrier coating that provides the radially-outwardly facing surface of the runner engaged by the seal member, wherein the blade track segment includes uncoated portions, and wherein the coating applied to the radially-outwardly facing surface of the runner included in the blade track segment is smoother than the uncoated portions of the blade track segment.

19 . The turbine shroud of claim 16 , wherein the seal member is formed to include a plurality of radially-extending bleed holes adapted to conduct a flow of buffer air through the seal member to resist the movement of gasses into the attachment-receiving space and the plurality of bleed holes are formed only along a leading edge of the blade track.

20 . The turbine shroud segment of claim 16 , wherein the seal member comprises mica.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• O'Leary Mark
• Vetters Daniel K
• Brandt Matthew R
• Freeman Ted J

Classifications

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F05D2240/55

  Seals · CPC title