Brazed blade track for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10494935-B2
Application number	US-201615094502-A
Country	US
Kind code	B2
Filing date	Apr 8, 2016
Priority date	Apr 29, 2015
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

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 and a second circumferential end face,
a second segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, the second segment having a first and a second circumferential end face, and
a joint that couples the first segment to the second segment, the joint including a first biscuit that extends into the first segment along the second circumferential end face of the first segment and into the second segment along the first circumferential end face of the second segment to securely fix the second segment in place relative to the first segment.

2. The blade track of claim 1 , wherein the first biscuit comprises ceramic-containing materials.

3. The blade track of claim 2 , wherein the first biscuit comprises ceramic-matrix composite materials.

4. The blade track of claim 2 , wherein the joint includes braze material between the first biscuit and the first segment and between the first biscuit and the second segment.

5. The blade track of claim 1 , wherein substantially all of the first biscuit is received in the first segment and the second segment so that the second circumferential end face of the first segment and the first circumferential end face of the second segment face one another.

6. The blade track of claim 5 , wherein the second circumferential end face of the first segment is engaged with the first circumferential end face of the second segment.

7. The blade track of claim 1 , wherein (i) the first biscuit extends into a first blind slot formed in the second circumferential end face of the first segment spaced axially and radially from axial and radial faces of the first segment and (ii) the first biscuit extends into a second blind slot formed in the first circumferential end face of the second segment spaced axially and radially from axial and radial faces of the second segment.

8. The blade track of claim 1 , wherein the joint includes a second biscuit that extends into the first segment along the second circumferential end face of the first segment and into the second segment along the first circumferential end face of the second segment.

9. The blade track of claim 8 , wherein the second biscuit is spaced axially from the first biscuit along the central axis.

10. The blade track of claim 9 , wherein (i) the first biscuit extends into a first blind slot formed in the second circumferential end face of the first segment, (ii) the first biscuit extends into a second blind slot formed in the first circumferential end face of the second segment, (iii) the second biscuit extends into a third blind slot, spaced from the first blind slot, formed in the second circumferential end face of the first segment, and (iv) the second biscuit extends into a fourth blind slot, spaced from the second blind slot, formed in the first circumferential end face of the second segment.

11. The blade track of claim 1 , wherein the first biscuit has one of a round-disk shape, an oblong-disk shape, a rectangular-disk shape, and a diamond-disk shape.

12. A gas turbine engine assembly, the assembly comprising
a first segment comprising ceramic-matrix composite materials, the first segment having a first and a second end face,
a second segment comprising ceramic-matrix composite materials, the second segment having a first and a second end face, and
a joint that securely fixes the first segment to the second segment, the joint including a first biscuit that extends into the first segment along the second end face of the first segment and into the second segment along the first end face of the second segment.

13. The gas turbine engine assembly of claim 12 , wherein the joint includes braze material between the first biscuit and the first segment and between the first biscuit and the second segment.

14. The gas turbine engine assembly of claim 13 , wherein the first biscuit comprises ceramic-containing materials.

15. The gas turbine engine assembly of claim 12 , wherein substantially all of the first biscuit is received in the first segment and the second segment so that the second end face of the first segment and the first end face of the second segment engage one another.

16. The gas turbine engine assembly of claim 12 , wherein (i) the first biscuit extends into a first blind slot formed in the second end face of the first segment and (ii) the first biscuit extends into a second blind slot formed in the first end face of the second segment.

17. The gas turbine engine assembly of claim 12 , wherein the joint includes a second biscuit that extends into the first segment along the second end face of the first segment and into the second segment along the first end face of the second segment.

18. A method of assembling a gas turbine engine assembly, the method comprising
inserting a first biscuit into a first segment comprising ceramic-matrix composite materials along an end face of the first segment and into a second segment comprising ceramic-matrix composite materials along an end face of the second segment, and
brazing the first biscuit to the first segment and to the second segment to securely fix the second segment to the first segment.

19. The method of claim 18 , further comprising inserting a second biscuit, spaced from the first biscuit, into the first segment along the end face of the first segment and into the second segment along the end face of the second segment, and brazing the second biscuit to the first segment and to the second segment.

20. The method of claim 19 , wherein (i) the first biscuit extends into a first blind slot formed in the end face of the first segment, (ii) the first biscuit extends into a second blind slot formed in the end face of the second segment, (iii) the second biscuit extends into a third blind slot, spaced from the first blind slot, formed in the end face of the first segment, and (iv) the second biscuit extends into a fourth blind slot, spaced from the second blind slot, formed in the end face of the second segment.

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

• F05D2300/20

  Oxide or non-oxide ceramics · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title