Ceramic matrix composite blade track segments

Patent metadata

Field	Value
Publication number	US-10704407-B2
Application number	US-201815950698-A
Country	US
Kind code	B2
Filing date	Apr 11, 2018
Priority date	Apr 21, 2017
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

Abstract

A turbine shroud adapted for use in a gas turbine engine includes an attachment feature and a body. The attachment feature and the body are constructed of ceramic matrix composite materials. In an illustrative embodiment, the ceramic matrix composite materials form a blade track segment.

First claim

What is claimed is:

1. A blade track segment adapted for use in a turbine shroud assembly incorporated into a gas turbine engine, the blade track segment comprising
a body comprising ceramic matrix composite material and formed to provide a polygonal cross-sectional shape defining an interior cavity, the body including a runner panel that extends partway around a central axis, a forward panel that extends radially outward and axially aft of a forward edge of the runner panel, and an aft panel that extends radially outward and axially forward of an aft edge of the runner panel,
an attachment feature comprising ceramic matrix composite material and arranged radially outward of the body and configured to be coupled to other components of the turbine shroud assembly when the blade track segment is assembled into the gas turbine engine, and
wherein the ceramic matrix composite materials include a sheet of reinforcement material that has free ends configured to form at least part of the attachment feature and a midsection configured to wrap around the interior cavity and form at least part of the runner panel, the forward panel, and the aft panel of the body,
wherein the ceramic matrix composite materials include a tube of reinforcement material constructed so as not to include a seam, and wherein the tube of reinforcement material is shaped to surround the interior cavity of the body and form at least part of the body.

2. The blade track segment of claim 1 , wherein the sheet of reinforcement material and the tube of reinforcement material are co-infiltrated with ceramic matrix material.

3. A blade track segment adapted for use in a turbine shroud assembly incorporated into a gas turbine engine, the blade track segment comprising
a body comprising ceramic matrix composite material and formed to provide a polygonal cross-sectional shape defining an interior cavity, the body including a runner panel that extends partway around a central axis, a forward panel that extends radially outward and axially aft of a forward edge of the runner panel, and an aft panel that extends radially outward and axially forward of an aft edge of the runner panel,
an attachment feature comprising ceramic matrix composite material and arranged radially outward of the body and configured to be coupled to other components of the turbine shroud assembly when the blade track segment is assembled into the gas turbine engine, and
wherein the ceramic matrix composite materials include a sheet of reinforcement material that has free ends configured to form at least part of the attachment feature and a midsection configured to wrap around the interior cavity and form at least part of the runner panel, the forward panel, and the aft panel of the body,
wherein the forward panel of the body and the aft panel of the body converge and form an interface of the body with the attachment feature,
wherein the ceramic matrix composite materials include filler reinforcement material arranged radially-inward and/or radially-outward of the interface of the body with the attachment feature to take up space as the forward panel and the aft panel diverge from one another.

4. The blade track segment of claim 3 , wherein the filler reinforcement material includes loose reinforcement fibers, and wherein the sheet of reinforcement material and the loose reinforcement fibers are co-infiltrated with ceramic matrix material.

5. The blade track segment of claim 3 , wherein the ceramic matrix composite materials include a tube of reinforcement material that is three-dimensionally woven so as not to include a seam, wherein the tube of reinforcement material is shaped to surround the interior the interior cavity of the body and form at least part of the body, wherein the filler reinforcement material is formed from three-dimensionally woven fibers of the tube of reinforcement material, and wherein the sheet of reinforcement material and the tube of reinforcement material are co-infiltrated with ceramic matrix material.

6. A blade track segment adapted for use in a turbine shroud assembly incorporated into a gas turbine engine, the blade track segment comprising
a body comprising ceramic matrix composite material and formed to provide a polygonal cross-sectional shape defining an interior cavity, the body including a runner panel that extends partway around a central axis, a forward panel that extends radially outward and axially aft of a forward edge of the runner panel, and an aft panel that extends radially outward and axially forward of an aft edge of the runner panel,
an attachment feature comprising ceramic matrix composite material and arranged radially outward of the body and configured to be coupled to other components of the turbine shroud assembly when the blade track segment is assembled into the gas turbine engine, and
wherein the ceramic matrix composite materials include a sheet of reinforcement material that has free ends configured to form at least part of the attachment feature and a midsection configured to wrap around the interior cavity and form at least part of the runner panel, the forward panel, and the aft panel of the body,
wherein the sheet of reinforcement material includes end sections that axially diverge from one another as they extend radially outward from the midsection to the free ends and that form at least part of the attachment feature,
wherein the attachment feature forms dovetail cross-sectional shape.

7. The blade track segment of claim 6 , wherein the wherein the ceramic matrix composite materials include filler reinforcement material arranged circumferentially between the end sections of the sheet of reinforcement material, and wherein the sheet of reinforcement material and the filler reinforcement material are co-infiltrated with ceramic matrix material.

8. A blade track segment adapted for use in a turbine shroud assembly incorporated into a gas turbine engine, the blade track segment comprising
a body comprising ceramic matrix composite material and formed to provide a polygonal cross-sectional shape defining an interior cavity, the body including a runner panel that extends partway around a central axis, a forward panel that extends radially outward and axially aft of a forward edge of the runner panel, and an aft panel that extends radially outward and axially forward of an aft edge of the runner panel,
an attachment feature comprising ceramic matrix composite material and arranged radially outward of the body and configured to be coupled to other components of the turbine shroud assembly when the blade track segment is assembled into the gas turbine engine, and
wherein the ceramic matrix composite materials include a sheet of reinforcement material that has free ends configured to form at least part of the attachment feature and a midsection configured to wrap around the interior cavity and form at least part of the runner panel, the forward panel, and the aft panel of the body,
wherein the sheet of reinforcement material includes end sections that axially diverge from one another as they extend radially outward from the midsection to the free ends and that form at least part of the attachment feature,
wherein the attachment feature forms a T-shaped cross-sectional shape.

9. A blade track segment adapted for use in a turbine shroud assembly incorporated into a gas turbine engine, the blade track segment comprising
a body comprising ceramic matrix ceramic material and formed to provide a polygonal cross-sectional shape defining an interior cavity, the body including a runner panel that extends partway around a central axis, a forward panel that extends radially outward and axially aft of a forward edge of the runner panel, and an aft panel that extend

Assignees

• Rolls Royce High Temperature Composites Inc
• Rolls Royce Nam Tech Inc

Inventors

• Barrett Chris
• Lamusga Joseph P
• Freeman Ted J

Classifications

• Y02T50/60

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

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2300/6034

  Orientation of fibres, weaving, ply angle · CPC title