Ceramic matrix composite seal segment for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10619503-B2
Application number	US-201715660143-A
Country	US
Kind code	B2
Filing date	Jul 26, 2017
Priority date	May 26, 2015
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

First claim

What is claimed is:

1. A ceramic matrix composite (CMC) seal segment of a segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the turbine having an axis of rotation, said seal segment comprising:
a flange having opposing major surfaces, one major surface for facing radially inward and the other major surface for facing radially outward relative to the axis of rotation; and
a pair of circumferentially-spaced portions each extending radially outward from said major surface for facing radially outward, each portion at least partially defining a respective pin-receiving bore in the axial direction, wherein an axial length of at least one of the pin-receiving bores is at least 75% of the axial dimension of said major surface for facing radially inward of the flange.

2. The seal segment of claim 1 wherein at least one of said pair of circumferentially-spaced portions completely defines a respective pin-receiving bore.

3. The seal segment of claim 1 wherein said respective pin-receiving bores are parallel to each other and to the axis of rotation.

4. The seal segment of claim 1 further comprising an additional portion defining an additional pin-receiving bore, wherein said additional pin-receiving bore is axially aligned with one of said respective pin-receiving bores.

5. The seal segment of claim 4 wherein said additional portion is axially spaced from one of said pair of circumferentially-spaced portions.

6. The seal segment of claim 1 wherein one or both of said respective pin-receiving bores has an axial dimension at least as long as the axial dimension of said flange.

7. The seal segment of claim 1 wherein said major surface facing radially inward is curved.

8. The seal segment of claim 7 wherein the axis of rotation is the centerline of the curvature of said major surface facing radially inward.

9. A component for a gas turbine engine comprising:
a flange comprising opposing major surfaces and opposing lateral surfaces, one major surface for facing radially inward and the other major surface for facing radially outward;
a first portion extending radially outward from said flange, said first portion having a radially outward facing surface and at least partially defining a first pin-receiving bore that is parallel to one or both of said lateral surfaces, wherein said first pin-receiving bore has an axial length greater than the minimum radial dimension between said major surface for facing radially inward of said flange and said radially outward facing surface of said first portion; and
a second portion extending radially outward from said flange, said second portion at least partially defining a second pin-receiving bore, wherein said second pin-receiving bore is axially aligned with said first pin-receiving bore.

10. The component of claim 9 wherein said component is a shroud.

11. The component of claim 10 where said shroud at least partly encases a compressor or turbine of the gas turbine engine.

12. The component of claim 9 wherein said component is constructed from a ceramic matrix composite.

13. The component of claim 9 wherein said major surface for facing radially inward is curved.

14. The component of claim 13 wherein the axis of rotation is the centerline of the curvature of said major surface for facing radially inward.

15. A segmented turbine shroud radially encasing a turbine in a gas turbine engine, said shroud comprising:
a carrier comprising at least one carrier member defining a carrier bore;
a ceramic matrix composite (CMC) seal segment comprising a flange having:
a flange comprising opposing major surfaces, one major surface facing radially inward and the other major surface facing radially outward relative to an axis of rotation of the turbine;
a portion extending radially outward from the major surface facing radially outward, said portion at least partially defining a pin-receiving seal segment bore for receiving an elongated pin, wherein said pin-receiving seal segment bore is aligned with said axis of rotation, wherein an axial length of the pin-receiving seal segment bore is at least 75% of the axial dimension of said major surface for facing radially inward of the flange; and

one or more elongated pins, wherein said CMC seal segment is carried by said carrier by at least one of said elongated pins being received with said carrier bore and said seal segment bore.

16. The segmented turbine shroud of claim 15 wherein said carrier member comprises a planar flange extending radially inward toward the turbine.

17. The segmented turbine shroud of claim 16 wherein said flange extends perpendicular to the axis of rotation of said turbine.

18. The segmented turbine shroud of claim 17 wherein said carrier bore comprises a minimum lateral cross-sectional dimension of at least three-eighths inches.

19. The segmented turbine shroud of claim 18 wherein said elongated pin comprises a circular lateral cross section.

Assignees

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

Inventors

• Vetters Daniel K
• Thomas David J
• Freeman Ted
• Lamusga Joseph
• Uskert Rick
• Dierksmeier Douglas D
• Shi Jun
• Engel Todd
• Brandt Matt

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D11/02 Primary

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title