Segmented turbine shroud with sealing features

Patent metadata

Field	Value
Publication number	US-10934871-B2
Application number	US-201615049672-A
Country	US
Kind code	B2
Filing date	Feb 22, 2016
Priority date	Feb 20, 2015
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.

First claim

What is claimed is:

1. A turbine shroud for a gas turbine engine, the turbine shroud comprising
a metallic carrier adapted to be coupled to a turbine case, the metallic carrier including a plurality of carrier segments located circumferentially adjacent to one another to form a carrier ring around a central axis with carrier segment gaps circumferentially between adjacent carrier segments, and
a ceramic-matrix composite blade track coupled to the metallic carrier, the ceramic-matrix composite blade track including a plurality of ceramic-matrix composite track segments located circumferentially adjacent to one another to form a track ring around the central axis with track segment gaps circumferentially between adjacent ceramic-matrix composite track segments, each of the plurality of ceramic-matrix composite track segments having a first circumferential end, a second circumferential end, and a central section interconnecting the first circumferential end and the second circumferential end, the first circumferential end of one track segment cooperating with the second circumferential end of an adjacent track segment to define a gap forming a tortuous track gas path for gases moving radially through the ceramic-matrix composite blade track, the tortuous track gas path extends radially away from the central axis through track gaps between circumferentially adjacent track segments,
wherein the carrier segment gaps are circumferentially spaced apart from the track segment gaps to define a tortuous carrier gas path radially through the carrier segment gaps of the metallic carrier and a circumferential section is defined radially between the ceramic-matrix composite blade track and the metallic carrier in flow communication with the tortuous track gas path and the tortuous carrier gas path.

2. The turbine shroud of claim 1 , further comprising a plurality of strip seal elements that extend circumferentially across the carrier segment gaps radially outward of the track segment gaps between carrier segments.

3. The turbine shroud of claim 1 , wherein the first circumferential end has a non-linear shape when viewed axially along the central axis and the second circumferential end has a non-linear shape complementary to the first circumferential end when viewed axially along the central axis.

4. The turbine shroud of claim 1 , wherein the first circumferential end of each track segment forms a radially-inner surface of the ceramic-matrix composite blade track and overlaps the second circumferential end of a circumferentially adjacent track segment.

5. The turbine shroud of claim 4 , wherein the second circumferential end of each track segment forms a radially-outer surface of the ceramic-matrix composite blade track and overlaps the first circumferential end of a circumferentially adjacent track segment.

6. The turbine shroud of claim 1 , wherein the first circumferential end has a non-linear shape when viewed radially outward away from the central axis and the second circumferential end has a non-linear shape complementary to the first circumferential end when viewed radially outward away from the central axis.

7. The turbine shroud of claim 6 , wherein the first circumferential end has a non-linear shape when viewed axially along the central axis and the second circumferential end has a non-linear shape complementary to the first circumferential end when viewed axially along the central axis.

8. The turbine shroud of claim 1 , wherein the first circumferential end of each track segment forms an axially-forward surface of the ceramic-matrix composite blade track.

9. The turbine shroud of claim 8 , wherein the second circumferential end of each track segment forms an axially-aft surface of the ceramic-matrix composite blade track.

10. A ceramic-matrix composite blade track for use in a turbine shroud of a gas turbine engine including a metallic carrier adapted to be coupled to a turbine case, the metallic carrier including a plurality of carrier segments located circumferentially adjacent to one another to form a carrier ring around a central axis with carrier segment gaps circumferentially between adjacent carrier segments, the blade track comprising
a plurality of ceramic-matrix composite track segments comprising ceramic-matrix composite materials, the plurality of ceramic-matrix composite track segments located circumferentially adjacent to one another to form a track ring around a central axis with track segment gaps circumferentially between adjacent ceramic-matrix composite track segments,
wherein each ceramic-matrix composite track segment has a first circumferential end, a second circumferential end, and a central section interconnecting the first circumferential end and the second circumferential end, the first circumferential end cooperates with the second circumferential end of an adjacent ceramic-matrix composite track segment to define a C-shaped groove sized to receive a corresponding tongue of the adjacent ceramic-matrix composite track segment, and the first circumferential end cooperates with the second circumferential end of the adjacent ceramic-matrix composite track segment to form a tortuous gas path for gases moving radially through the ceramic-matrix composite blade track, the tortuous gas path extending radially away from the central axis through track gaps between circumferentially adjacent ceramic-matrix composite track segments, wherein the tortuous gas path is a through flow path communicating between an inner and outer surface of the ceramic-matrix composite track segments,
wherein the track segment gaps are arranged circumferentially spaced apart from the carrier segment gaps to define a tortuous carrier gas path radially through the carrier segment gaps and a circumferential section is defined radially between the ceramic-matrix composite blade track segments and the metallic carrier in flow communication with the tortuous track gas path and the tortuous carrier gas path.

11. The blade track of claim 10 , wherein the first circumferential end has a non-linear shape when viewed radially outward away from the central axis and the second circumferential end has a non-linear shape complementary to the first circumferential end when viewed radially outward away from the central axis.

12. The blade track of claim 11 , wherein the first circumferential end has a non-linear shape when viewed axially along the central axis and the second circumferential end has a non-linear shape complementary to the first circumferential end when viewed axially along the central axis such that the first circumferential end cooperates with the second circumferential end to form the tortuous gas path extending radially away from the central axis through track gaps between circumferentially adjacent track segments.

13. The blade track of claim 10 , wherein the first circumferential end of each track segment forms an axially-forward surface of the ceramic-matrix composite blade track.

14. The blade track of claim 13 , wherein the first circumferential end of each track segment forms an axially-aft surface of the ceramic-matrix composite blade track.

15. A ceramic-matrix composite blade track for use in a turbine shroud for a gas turbine engine, the turbine shroud including a metallic carrier adapted to be coupled to a turbine case, the metallic carrier including a plurality of carrier segments located circumferentially adjacent to one another to form a carrier ring around a central axis with carrier segment gaps circumferentially between adjacent carrier segments, the blade track comprising
a plurality of ceramic-matrix composite track segme

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Plc
• Rolls Royce Corp

Inventors

• Freeman Ted J
• Broadhead Peter
• Sippel Aaron D
• Thomas David J
• Lamusga Joseph P

Classifications

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2240/40

  Use of a multiplicity of similar components · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title