Turbine shroud with sealing features

• US 10,458,263 B2
• Filed: 09/27/2016
• Issued: 10/29/2019
• Est. Priority Date: 10/12/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: Sippel, Aaron D., Freeman, Ted J., Thomas, David J.
• Primary Examiner(s): Lee, Jr., Woody A
• Assistant Examiner(s): Legendre, Christopher R
• Application Number:
  US15/277,575
• Publication Number:
  US 20170101882A1
• Time in Patent Office: 1,127 Days
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/18 using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F05D 2230/60 Assembly methods
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/55 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 segmented turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and retainers. The blade track is mounted onto the retainers, and the retainers are attached to the carrier to support the blade track radially outside of the blades.

Claims

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

a carrier segment that extends partway around the central axis and that forms a cavity that opens in a radially-inward direction,

a first retainer positioned within the cavity of the carrier segment, the first retainer including at least one attachment post extending radially outward to attach the first retainer to the carrier segment and at least one flange extending radially inward from the attachment post,

a first blade track segment comprising ceramic-containing materials, the first blade track segment formed to include a runner that extends partway around the central axis and at least one hanger that extends radially outward from the runner into the cavity of the carrier segment to engage the at least one flange of the first retainer to mount the first blade track segment thereto, and

a compartment seal disposed to encircle the at least one hanger and engage the runner to seal a portion of the cavity disposed radially outward of the runner of the first blade track segment,

wherein the at least one flange of the first retainer includes at least one aftwardly positioned flange for engagement with an aftwardly positioned hanger included in the at least one hanger of the first blade track segment and at least one forwardly positioned flange for engagement with a forwardly positioned hanger included in the at least one hanger of the first blade track segment.

2. The assembly of claim 1, wherein the at least one attachment post of the first retainer is arranged to penetrate through an opening in the carrier segment to attach the first retainer to the carrier segment.

3. The assembly of claim 1, further comprising a second blade track segment including a runner that extends partway around the central axis and two hangers that extend radially outward from the runner of the second blade track segment, the compartment seal encircles the hangers of the first and the second blade track segments, and the compartment seal is disposed in contact with a top surface of the runner of the first blade track segment and the runner of the second blade track segment.

4. The assembly of claim 3, further comprising a second retainer configured to mount onto the second blade track segment, and the first and the second retainers are configured to attach to the carrier segment such that the runners of the first and second blade track segments are adjacent to each other and define a bottom of the cavity formed by the carrier segment.

5. The assembly of claim 1, wherein each of the hangers included in the at least one hanger is formed to have an L-shape cross section including a radially extending portion and a forwardly extending portion.

6. The assembly of claim 1, wherein the carrier segment includes a carrier body, first and second circumferential endwalls, and first and second axial endwalls, and wherein each of the first and second circumferential endwalls and the first and second axial endwalls have an end seal recess that opens radially inwardly disposed therein, and wherein each of the first and second circumferential endwalls and the first and second axial endwalls extend radially inward from the carrier body.

7. The assembly of claim 6, wherein the carrier segment includes a middle wall having a radially inner end with at least two radially-inwardly opening recesses disposed therein.

8. The assembly of claim 1, further comprising a second blade track segment and a gap seal, the second blade track segment including a runner that extends partway around the central axis and at least one hanger that extends radially outward from the runner, the gap seal extending in the axial direction and arranged between the runners of the first and second blade track segments, and the first and second blade track segments cooperate to define a recess that receives the gap seal to provide sealing between the runners of the first and second blade track segments.

9. A turbine shroud assembly that extends at least partway around a central axis, the assembly comprising

a carrier segment comprising metallic materials, the carrier segment formed to include a radially-inwardly opening cavity,

a first blade track segment comprising ceramic-matrix composite materials, the first blade track segment formed to include a runner that extends partway around the central axis and an attachment feature that extends outward in the radial direction from the runner into the radially-inwardly opening cavity of the carrier segment, and

a compartment seal that extends around the attachment feature and engages a radially-outward facing surface of the runner to seal at least a portion of the radially-inwardly opening cavity from gasses outside the radially-inwardly opening cavity,

wherein the compartment seal is formed to include a plurality of radially-expandable folds configured to allow radial expansion and contraction of the compartment seal to accommodate thermal growth and contraction of the carrier segment and the first blade track segment.

10. The assembly of claim 9, wherein the compartment seal is a one-piece component.

11. The assembly of claim 10, wherein the compartment seal forms an uninterrupted ring as it extends around the attachment feature.

12. The assembly of claim 9, wherein the carrier segment includes a carrier body, first and second circumferential endwalls that extend inward in the radial direction from circumferential ends of the carrier body, and first and second axial endwalls that extend inward in the radial direction from axial ends of the carrier body;

and

wherein each of the first and second circumferential endwalls and the first and the second axial endwalls are formed to include a radially-inwardly opening recess that each receive a portion of the compartment seal.

13. The assembly of claim 12, wherein the radially-inwardly opening recesses cooperate to form an uninterrupted ring around the attachment feature.

14. A turbine shroud assembly that extends at least partway around a central axis, the assembly comprising

a carrier segment comprising metallic materials, the carrier segment formed to include a radially-inwardly opening cavity,

a first blade track segment comprising ceramic-matrix composite materials, the first blade track segment formed to include a runner that extends partway around the central axis and an attachment feature that extends outward in the radial direction from the runner into the radially-inwardly opening cavity of the carrier segment, and

a compartment seal that extends around the attachment feature and engages a radially-outward facing surface of the runner to seal at least a portion of the radially-inwardly opening cavity from gasses outside the radially-inwardly opening cavity,

further comprising a second blade track segment including:

a runner that extends partway around the central axis and an attachment feature that extends outward in the radial direction from the runner into the radially-inwardly opening cavity of the carrier segment.

15. The assembly of claim 14, wherein chamfers along circumferential ends of the runners included in the first blade track segment and the second blade track segment cooperate to form a radially-outwardly opening channel that receives a gap seal sized to seal a circumferential gap between the first blade track segment and the second blade track segment.

16. The assembly of claim 14, wherein the compartment seal is a one-piece component that extends around the attachment feature of the second blade track segment to form a ring around the attachment features of both the first blade track segment and the second blade track segment.

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

mounting a retainer formed to include flanges and attachment posts to a blade track segment formed to include a runner and hangers so that the flanges engage the hangers,

attaching the retainer to a carrier segment by coupling the attachment posts of the retainer to the carrier segment so that the retainer and the hangers are received in a radially inwardly-opening cavity formed by the carrier segment, and

positioning at least one compartment seal in a recess of the carrier segment to engage a radially outer side of the runner of the blade track segment to seal the radially inwardly-opening cavity.