Turbine shroud with sealed blade track

Patent metadata

Field	Value
Publication number	US-9938846-B2
Application number	US-201514735802-A
Country	US
Kind code	B2
Filing date	Jun 10, 2015
Priority date	Jun 27, 2014
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier component, a blade track component, and a retainer component that couples the blade track component to the carrier component. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.

First claim

What is claimed is:

1. A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprising
a first shroud segment including a first carrier segment, a first blade track segment, and a first retainer that couples the first carrier segment to the first blade track segment, the first blade track segment made from a ceramic-matrix-composite material,
a second shroud segment arranged circumferentially adjacent to the first shroud segment around the central axis, the second shroud segment including a second carrier segment, a second blade track segment, and a second retainer that couples the second carrier segment to the second blade track segment, the second blade track segment made from a ceramic-matrix-composite material, and
a circumferential seal arranged between the first shroud segment and the second shroud segment to block gasses from passing through a circumferential interface of the first shroud segment and the second shroud segment, the circumferential seal engaging a first seal-locating feature formed in the first carrier segment and a second seal-locating feature formed in the second carrier segment so that the circumferential seal is held in place circumferentially between the first shroud segment and the second shroud segment,
wherein the each carrier segment includes a central attachment body engaged with a corresponding blade track segment and a pair of end caps that extend circumferentially in opposing directions from the central attachment body and each end cap is formed to include a seal-locating feature, and
wherein a closed cavity is formed by the first shroud segment between the first carrier segment and the first blade track segment, the closed cavity extends along the central attachment body of the first carrier segment, the closed cavity is radially bounded by the blade track segment, and the closed cavity is circumferentially bounded by the pair of end caps.

2. The segmented turbine shroud of claim 1 , wherein the circumferential seal is a strip seal, the first seal-locating feature is a first seal-receiving slot that extends circumferentially into the first carrier segment, and the second seal-locating feature is a second seal-receiving slot that extends circumferentially into the second carrier segment.

3. The segmented turbine shroud of claim 1 , wherein the pair of endcaps close off circumferential ends of a radially inwardly opening channel formed by the central attachment body.

4. The segmented turbine shroud of claim 1 , wherein the central attachment body of the first carrier segment is formed to include a spar, a forward hanger bracket coupled to the spar, and an aft hanger bracket coupled to the spar.

5. The segmented turbine shroud of claim 4 , wherein the first blade track segment includes a runner, a forward hanger arm that engages the forward hanger bracket included in the first carrier segment, and an aft hanger arm that is engaged along with the aft hanger bracket of the first carrier segment by the first retainer.

6. The segmented turbine shroud of claim 1 , wherein the first blade track segment includes a runner, a forward hanger arm that engages the first carrier segment, and an aft hanger arm that is engaged along with the first carrier segment by the first retainer.

7. The segmented turbine shroud of claim 6 , wherein the forward hanger arm includes a first portion that extends outward in a radial direction and a second portion that extends forward in an axial direction and the aft hanger arm includes a first portion that extends outward in the radial direction and a second portion that extends rearward in the axial direction.

8. The segmented turbine shroud of claim 7 , wherein the first retainer forms an axially-opening channel that receives the second portion of the aft hanger arm included in the first blade track segment.

9. A turbine shroud segment comprising
a carrier segment including a central attachment body and a pair of end caps that extend in opposing directions from the central attachment body, each end cap being formed to include a seal-locating feature,
a blade track segment made from a ceramic-matrix-composite material supported by the carrier segment, and
a retainer that receives a portion of the carrier segment and a portion of the blade track segment to couple the blade track segment to the carrier segment,
wherein a closed cavity is formed between the carrier segment and blade track segment, the closed cavity extends along the central attachment body of the carrier segment, the closed cavity is radially bounded by the blade track segment, and the closed cavity is circumferentially bounded by the pair of end caps.

10. The turbine shroud segment of claim 9 , wherein the seal-locating feature included in each end cap is a seal-receiving slot that extends circumferentially into the carrier segment.

11. The turbine shroud segment of claim 10 , wherein seal-receiving slot included in each end cap is sized to receive a strip seal.

12. The turbine shroud segment of claim 9 , wherein the central attachment body of the carrier segment is formed to include a spar, a forward hanger bracket that extends radially inwardly from the spar, and an aft hanger bracket that extends radially inwardly from the spar and the closed cavity extends axially from the forward hanger bracket to the aft hanger bracket.

13. The turbine shroud segment of claim 9 , wherein the blade track segment is formed to include a runner, a forward hanger arm that extends radially outwardly from the runner, and an aft hanger arm that extends radially outwardly from the runner and the closed cavity extends axially from the forward hanger arm to the aft hanger arm.

14. The turbine shroud segment of claim 13 , wherein the forward hanger arm includes a first portion that extends outward in a radial direction and a second portion that extends forward in an axial direction and the aft hanger arm includes a first portion that extends outward in the radial direction and a second portion that extends rearward in the axial direction.

15. The turbine shroud segment of claim 14 , wherein the retainer forms an axially-opening channel that receives the second portion of the aft hanger arm included in the blade track segment.

16. A method of making a turbine shroud adapted for use in a gas turbine engine, the method comprising
assembling a first shroud segment by moving a first blade track segment made from a ceramic matrix composite material into a predetermined position relative to a first carrier and inserting a portion of both the first blade track segment and the first carrier into a first retainer to couple the first blade track segment to the first carrier,
assembling a second shroud segment by moving a second blade track segment made from a ceramic matrix composite material into a predetermined position relative to a second carrier and inserting a portion of both the second blade track segment and the second carrier into a second retainer to couple the second blade track segment to the second carrier, and
inserting a strip seal into a first seal-receiving slot formed in the first carrier and into a second seal-receiving slot formed in the second carrier so that the strip seal extends from the first shroud segment to the second shroud segment,
wherein a closed cavity is formed between the first carrier segment and first blade track segment, the closed cavity extends along the first carrier segment, the closed cavity is radially bounded by the first blade track segment, and the closed cavity is circumferentially bounded by a pair of end caps included in the fir

Assignees

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

Inventors

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

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• 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