Brazed blade track for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11053806-B2
Application number	US-201916661572-A
Country	US
Kind code	B2
Filing date	Oct 23, 2019
Priority date	Apr 29, 2015
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

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 and shaped to extend part-way around a central axis, the first segment having a first circumferential end portion and a second circumferential end portion, and
a second segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, the second segment having a first circumferential end portion and a second circumferential end portion, and
a joint including a circumferentially-extending tongue formed by the second circumferential end portion of the first segment, a circumferentially-extending groove formed by the first circumferential end portion of the second segment and shaped to receive the circumferentially-extending tongue, and a layer of bonding material arranged at an interface formed circumferentially between the first segment and the second segment to fix the first segment to the second segment,
wherein the circumferentially-extending tongue and the circumferentially-extending groove are configured so that one-third or less of the interface between the first segment and the second segment is engaged by the layer of bonding material at any circumferential cross-sectional location,
wherein the circumferentially-extending tongue is configured to form a generally triangular shape when viewed inwardly in a radial direction toward the central axis.

2. The full-hoop blade track of claim 1 , wherein a circumferential end of the circumferentially-extending tongue is located about midway between a forward axial face of the first segment and an aft axial face of the first segment.

3. The full-hoop blade track of claim 1 , wherein the circumferentially-extending tongue is configured to form a plurality of teeth when viewed inwardly in a radial direction toward the central axis.

4. The full-hoop blade track of claim 1 , wherein the circumferentially-extending tongue is spaced apart from a forward axial face of the first segment and from an aft axial face of the first segment and the circumferentially-extending tongue is spaced apart from an outer radial face of the first segment and from an inner radial face of the first segment.

5. The full-hoop blade track of claim 1 , wherein the layer of bonding material include a braze material.

6. The full-hoop blade track of claim 1 , wherein the first segment includes an outer radial surface that faces outwardly away from the central axis and extends partway around the central axis, the first outer radial surface is continuous with a substantially consistent circumference.

7. The full-hoop blade track of claim 1 , wherein the first segment includes a forward axial face and an aft axial face spaced axially apart from the forward axial face, and the forward axial face and the aft axial face are substantially continuous and planar.

8. A full-hoop blade track for a gas turbine engine assembly, the blade track comprising
a first segment comprising ceramic-matrix composite materials and shaped to extend part-way around a central axis, the first segment having a first circumferential end portion and a second circumferential end portion, and
a second segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, the second segment having a first circumferential end portion and a second circumferential end portion, and
a joint including a tongue formed by the second circumferential end portion of the first segment, a groove shaped to receive the circumferentially-extending tongue formed by the first circumferential end portion of the second segment, and a layer of bonding material arranged at an interface formed circumferentially between the first segment and the second segment,
wherein the tongue and the groove are configured so that one-third or less of the interface between the first segment and the second segment is engaged by the layer of bonding material at any circumferential cross-sectional location,
wherein the tongue is spaced apart from a forward axial face of the first segment and from an aft axial face of the first segment and the tongue is spaced apart from an outer radial face of the first segment and from an inner radial face of the first segment.

9. The full-hoop blade track of claim 8 , wherein a circumferential end of the tongue is located about midway between the forward axial face of the first segment and the aft axial face of the first segment.

10. The full-hoop blade track of claim 8 , wherein the groove is spaced apart from a forward axial face of the second segment and from an aft axial face of the second segment and the groove is spaced apart from an outer radial face of the second segment and from an inner radial face of the second segment.

11. The full-hoop blade track of claim 10 , wherein the groove is located about midway between the outer radial face of the second segment and the inner radial face of the second segment.

12. The full-hoop blade track of claim 10 , wherein the groove is located about midway between the forward axial face of the second segment and the aft axial face of the second segment.

13. The full-hoop blade track of claim 8 , wherein the layer of bonding material include a braze material.

14. The full-hoop blade track of claim 8 , wherein a circumferential end of the tongue is located about midway between the outer radial face of the first segment and the inner radial face of the first segment.

15. The full-hoop blade track of claim 8 , wherein the outer radial face is continuous with a substantially consistent circumference.

16. The full-hoop blade track of claim 8 , wherein the forward axial face and the aft axial face are substantially continuous and planar.

17. A method of making a full-hoop blade track for a gas turbine engine assembly, the method comprising
inserting a circumferentially-extending tongue formed by an end portion of a first segment into a circumferentially-extending groove formed by an end portion of a second segment, and
brazing the first segment to the second segment with braze along an interface circumferentially between the first segment and the second segment to form a joint, the interface including the circumferentially extending tongue and the circumferentially-extending groove,
wherein the first segment and the second segment comprise ceramic-matrix composite materials and the circumferentially-extending tongue and the circumferentially-extending groove are configured so that one-third or less of the interface between the first segment and the second segment is engaged by the braze at any circumferential cross-sectional location of the joint,
wherein the circumferentially-extending tongue is configured to form steps when viewed inwardly in a radial direction toward a central axis.

Assignees

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

Inventors

• Sippel Aaron D
• Vetters Daniel K
• Shi Jun
• Thomas David J
• Eifert Andrew J
• Broadhead Peter

Classifications

• Y02T50/60

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

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title