Ceramic matrix full hoop blade track

Patent metadata

Field	Value
Publication number	US-10954809-B2
Application number	US-201815989666-A
Country	US
Kind code	B2
Filing date	May 25, 2018
Priority date	Jun 26, 2017
Publication date	Mar 23, 2021
Grant date	Mar 23, 2021

Abstract

A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

First claim

What is claimed is:

1. A full hoop blade track for a gas turbine engine, the blade track comprising
a first segment comprising ceramic-matrix composite materials, the first segment including a band shaped to extend part-way around a central axis and an attachment tongue that extends about the central axis from a circumferential end of the band of the first segment,
a second segment comprising ceramic-matrix composite materials, the second segment including a band shaped to extend part-way around the central axis and an attachment tongue that extends about the central axis from a circumferential end of the band of the second segment, and
a joint that couples the first segment to the second segment, the joint including a tube of reinforcement fibers that receives the attachment tongues of the first segment and the second segment, wherein the tube of reinforcement fibers is co-infiltrated with ceramic-containing matrix material along with the first segment and the second segment in order to couple the first segment to the second segment,
wherein the tube of reinforcement fibers has a radially-inner surface that is coextensive or flush with a radially-inner surface of the first segment and a radially-inner surface of the second segment.

2. The blade track of claim 1 , wherein the tube of reinforcement fibers is woven or braided such that the tube of reinforcement fibers lacks a seam that extends circumferentially along the blade track.

3. The blade track of claim 2 , wherein the tube of reinforcement fibers includes ceramic-containing fibers such that the co-infiltrated tube of reinforcement fibers is part of a ceramic matrix composite component.

4. The blade track of claim 1 , wherein the attachment tongue of the first segment and the attachment tongue of the second segment each have a circumferential cross-sectional shape smaller than the circumferential cross-sectional shape of the band included in each of the first segment and the second segment.

5. The blade track of claim 4 , wherein the edges of the attachment tongues included in the first and the second segments are spaced radially and axially apart from the edges of the bands included in the first and the second segments when viewed in the circumferential direction.

6. The blade track of claim 1 , wherein the first segment includes a second attachment tongue that extends about the central axis from another circumferential end of the band of the first segment, the second attachment tongue adapted to be received in another tube of reinforcement fibers so as to create a second joint.

7. A gas turbine engine assembly, comprising
a first segment comprising ceramic-matrix composite materials, the first segment including a main body and an attachment tongue that extends from an end of the main body of the first segment,
a second segment comprising ceramic-matrix composite materials, the second segment including a main body and an attachment tongue that extends from an end of the main body of the second segment, and
a joint that couples the first segment to the second segment, the joint including a tube of reinforcement fibers that receives the attachment tongues of the first segment and the second segment, wherein the tube of reinforcement fibers is fixed with the attachment tongue of the first segment and the attachment tongue of the second segment, and wherein the main body of the first segment, the main body of the second segment, and the tube of reinforcement fibers define a portion of a flow path configured to be exposed to flow path gases,
wherein the tube reinforcement fibers has a radially-inner surface that is coextensive or flush with a radially-inner surface of the first segment and a radially-inner surface of the second segment.

8. The gas turbine engine of claim 7 , wherein the tube of reinforcement fibers is woven or braided such that the tube of reinforcement fibers lacks a seam.

9. The gas turbine engine of claim 7 , wherein the tube of reinforcement fibers includes ceramic-containing fibers such that the tube of reinforcement fibers is part of a ceramic matrix composite component.

10. The gas turbine engine of claim 7 , wherein the attachment tongue of the first segment and the attachment tongue of the second segment each have a circumferential cross-sectional shape smaller than a circumferential cross-sectional shape of the main body included in each of the first segment and the second segment.

11. The gas turbine engine of claim 10 , wherein edges of the attachment tongues included in the first and the second segments are spaced radially and axially apart from edges of the main bodies included in the first and the second segments when viewed in the circumferential direction.

12. The gas turbine engine of claim 7 , wherein the first segment includes a second attachment tongue that extends about a central axis from another end of the main body, the second attachment tongue is adapted to be received in another tube of reinforcement fibers so as to create a second joint.

13. The gas turbine engine of claim 7 , wherein the attachment tongue of the first segment and the attachment tongue of the second segment each extend circumferentially from a respective attachment surface of the main body included in each of the respective first segment and the respective second segment, the attachment surface of the first segment and the attachment surface of the second segment face the joint when the attachment tongue of the first segment and the attachment tongue of the second segment are received within the tube, and edges of each attachment tongue included in the first segment and the second segment are spaced apart radially from edges of the main body included in each of the first segment and the second segment when viewed in the circumferential direction.

14. The gas turbine engine of claim 13 , wherein the edges of each attachment tongue included in the first segment and the second segment are spaced apart axially from the edges of the main body included in each of the first segment and the second segment when viewed in the circumferential direction.

15. A method of making a full hoop blade track for a gas turbine engine, the method comprising:
chemical vapor infiltrating ceramic material preforms with silicon-carbide fibers, the preforms including a first blade track segment having a first band and a first tongue, a second blade track segment having a second band and a second tongue, and a joint having a tube of reinforcement fibers,
assembling the full hoop blade track by inserting the first tongue formed on the first segment into a first end of the tube of reinforcement fibers and inserting the second tongue formed on the second segment into a second end of the tube of reinforcement fibers,
aligning a radially-inner surface of the first segment with a radially-inner surface of the joint and aligning a radially-inner surface of the second segment with the radially-inner surface of the joint so that the radially-inner surface of the joint is coextensive or flush with the radially-inner surface of the first segment and the radially-inner surface of the second segment, and
slurry infiltrating and melt infiltrating the first segment, the second segment, and the joint to bond the first segment, the second segment, and the joint together so that each of the first segment, the second segment, and the joint each form a portion of a radially-inward facing surface of the full hoop blade track.

Assignees

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

Inventors

• Sippel Aaron D
• Varney Bruce E
• Freeman Ted J
• Barrett Christopher

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2220/32

  in gas turbines · CPC title

• C23C16/045

  Coating cavities or hollow spaces, e.g. interior of tubes; Infiltration of porous substrates · CPC title