Segmented turbine shroud with sealing features

Patent metadata

Field	Value
Publication number	US-2016245102-A1
Application number	US-201615049672-A
Country	US
Kind code	A1
Filing date	Feb 22, 2016
Priority date	Feb 20, 2015
Publication date	Aug 25, 2016
Grant date	—

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, a ceramic-matrix composite blade track coupled to the metallic carrier, the ceramic-matrix composite blade track including a plurality of track segments located circumferentially adjacent to one another to form a track ring around the central axis with track segment gaps circumferentially between adjacent track segments, wherein the carrier segment gaps are circumferentially spaced apart from the track segment gaps so that a tortuous gas path radially through the carrier segment gaps of the metallic carrier and the track gaps of the ceramic-matrix composite blade track is formed.

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

3 . The turbine shroud of claim 1 , wherein each 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; and the first circumferential end cooperates with the second circumferential end to form a tortuous gas path extending radially away from the central axis through track gaps between circumferentially adjacent track segments.

4 . The turbine shroud of claim 3 , 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.

5 . The turbine shroud of claim 3 , 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.

6 . The turbine shroud of claim 5 , 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.

7 . The turbine shroud of claim 1 , wherein each 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 and the first circumferential end cooperates with the second circumferential end to form a tortuous gas path extending axially along the central axis through track gaps between circumferentially adjacent track segments.

8 . The turbine shroud of claim 7 , 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.

9 . The turbine shroud of claim 8 , 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 a tortuous gas path extending radially away from the central axis through track gaps between circumferentially adjacent track segments.

10 . The turbine shroud of claim 7 , wherein the first circumferential end of each track segment forms an axially-forward surface of the ceramic-matrix composite blade track.

11 . The turbine shroud of claim 10 , wherein the second circumferential end of each track segment forms an axially-aft surface of the ceramic-matrix composite blade track.

12 . A blade track for use in a turbine shroud of a gas turbine engine, the blade track comprising
a plurality of track segments comprising ceramic-matrix composite materials, the plurality of track segments located circumferentially adjacent to one another to form a track ring around a central axis with track segment gaps circumferentially between adjacent track segments, wherein each 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, and the first circumferential end cooperates with the second circumferential end to form a tortuous gas path extending axially along the central axis through track gaps between circumferentially adjacent track segments.

13 . The blade track of claim 12 , 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.

14 . The blade track of claim 13 , 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 a tortuous gas path extending radially away from the central axis through track gaps between circumferentially adjacent track segments.

15 . The blade track of claim 12 , wherein the first circumferential end of each track segment forms an axially-forward surface of the ceramic-matrix composite blade track.

16 . The blade track of claim 15 , wherein the second circumferential end of each track segment forms an axially-aft surface of the ceramic-matrix composite blade track.

17 . A blade track for use in a turbine shroud for a gas turbine engine, the turbine shroud comprising
a plurality of track segments comprising ceramic-matrix composite materials, the plurality of track segments located circumferentially adjacent to one another to form a track ring around a central axis with track segment gaps circumferentially between adjacent track segments, wherein each 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, and the first circumferential end cooperates with the second circumferential end to form a tortuous gas path extending radially away from the central axis through track gaps between circumferentially adjacent track segments.

18 . The blade track of claim 17 , 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.

19 . The blade track of claim 17 , 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.

20 . The blade track of cla

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

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2250/182

  crenellated, notched · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title