Turbine shroud with sealed box segments

Patent metadata

Field	Value
Publication number	US-10458268-B2
Application number	US-201615097343-A
Country	US
Kind code	B2
Filing date	Apr 13, 2016
Priority date	Apr 13, 2016
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

A turbine shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment.

First claim

What is claimed is:

1. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and
at least one strip seal configured to resist movement of gases after into the attachment-receiving space, the at least one strip seal arranged to extend across a gap formed radially between the carrier segment and the runner into a radially-outwardly opening runner slot formed in a radially-outwardly facing surface of the runner,
wherein a first strip seal is a one-piece component and extends at least most of the way around the attachment portion of the blade track segment, and
wherein the first strip seal is formed to include a gap as it extends around the attachment portion of the blade track segment sized to accommodate thermal expansion induced during use of the turbine shroud segment.

2. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and
at least one strip seal configured to resist movement of gases after into the attachment-receiving space, the at least one strip seal arranged to extend across a gap formed radially between the carrier segment and the runner into a radially-outwardly opening runner slot formed in a radially-outwardly facing surface of the runner,
wherein a first strip seal is a one-piece component and extends at least most of the way around the attachment portion of the blade track segment, and
wherein the first strip seal is sized to form an overlapped portion as it extends around the attachment portion of the blade track segment to accommodate thermal expansion induced during use of the turbine shroud segment.

3. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and
at least one strip seal configured to resist movement of gases after into the attachment-receiving space, the at least one strip seal arranged to extend across a gap formed radially between the carrier segment and the runner into a radially-outwardly opening runner slot formed in a radially-outwardly facing surface of the runner,
wherein the runner of the blade track segment includes a layer of coating that provides at least a portion of the radially-outwardly facing surface of the runner into which the radially-outwardly opening runner slot is formed, and
wherein the radially-outwardly opening runner slot extends through the layer of coating and into a ceramic matrix composite portion of the runner.

4. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment,
at least one strip seal configured to resist movement of gases after into the attachment-receiving space, the at least one strip seal arranged to extend across a gap formed radially between the carrier segment and the runner into a radially-outwardly opening runner slot formed in a radially-outwardly facing surface of the runner, and
a track-segment coupler assembly configured to attach the blade track segment to the carrier segment, wherein the track-segment coupler assembly includes a retainer plate arranged between the runner of the blade track segment and at least part of the attachment portion of the blade track segment, a support shaft that extends from the carrier segment to the retainer plate, an outer spring member arranged radially between the carrier segment and the attachment portion of the blade track segment, and an inner spring member arranged radially between the retainer plate and at least part of the attachment portion of the blade track segment.

5. The turbine shroud assembly of claim 4 , wherein the attachment portion of the blade track segment has a U-shaped cross-section and cooperates with the runner of the blade track segment to define a receiving space in which the retainer plate is received.

6. A turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment,
a track-segment coupler assembly configured to attach the blade track segment to the carrier segment, wherein the track-segment coupler assembly includes a retainer plate arranged between the runner of the blade track segment and at least part of the attachment portion of the blade track segment, a support shaft that extends from the carrier segment to the retainer plate, an outer spring member arranged radially between the carrier segment and the attachment portion of the blade track segment, and an inner spring member arranged radially between the retainer plate and at least part of the attachment portion of the blade track segment,
a seal member configured to resist movement of gases after into the attachment-receiving space, the seal member arranged to extend across a gap formed radially between the carrier segment and the runner, and
a spring member arranged in a radially-inwardly opening carrier slot formed in the carrier segment and configured to push the seal member toward the central axis.

7. A turbine shroud segment comprising
a carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and
a track-segment coupler assembly configured to attach the blade track segment to the carrier segment, wherein the track-segment coupler assembly includes a retainer plate arranged between the runner of the blade track segment and at least part of the attachment portion of the blade track segment, a support shaft that extends from the carrier segment to the ret

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• O'Leary Mark

Classifications

• F05D2240/55

  Seals · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title