Seal segment for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10641120-B2
Application number	US-201615219047-A
Country	US
Kind code	B2
Filing date	Jul 25, 2016
Priority date	Jul 24, 2015
Publication date	May 5, 2020
Grant date	May 5, 2020

Abstract

A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a housing;
at least one compressor positioned within the housing;
at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and
a seal segment positioned along a portion of the housing and comprising:
a radially outer wall having a first length extending annularly around a portion of the engine, the radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member;
a radially inner wall positioned intermediate the outer wall and the portion of the engine and having a second length, the radially outer wall comprised of ceramic matrix composite material;
a first lateral wall and a second lateral wall, extending between the outer wall and the inner wall;
a rib member integrally formed with and extending between the outer wall and the inner wall intermediate the first and second lateral walls without overlapping the at least one elongate aperture of the outer wall;
a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and
a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage.

2. The engine of claim 1 , wherein a distance between the first lateral wall and the rib member is greater than a distance between the second lateral wall and the rib member.

3. The engine of claim 1 , wherein the rib member includes a plurality of openings configured to permit flow of cooling gases between the first and second cooling gas passages through the openings.

4. The engine of claim 1 , wherein at least the radially inner wall is comprised of a ceramic material.

5. The gas turbine engine of claim 1 , further comprising a connector member including a shaft connected to an inner end, wherein the inner end is sized and configured to be received through the slot and to straddle the slot after being rotated, and wherein the connector member supports the seal segment when the inner end straddles the slot.

6. A gas turbine engine, comprising:
a housing;
at least one compressor positioned within the housing;
at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and
a seal segment positioned along a portion of the housing and comprising:
a radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member;
a radially inner wall positioned intermediate the outer wall and at least one of the at least one compressor and the at least one turbine, the radially outer wall comprised of ceramic matrix composite material;
a first lateral wall extending between the outer and inner walls;
a second lateral wall extending between the outer and inner walls;
a rib member integrally formed with and extending between the outer wall and the inner wall and intermediate the first and second lateral walls without overlapping the at least one elongate aperture of the outer wall;
a first cooling passage bounded by the outer wall, the inner wall, the rib member, and the first lateral wall; and

a second cooling passage bounded by the outer wall, the inner wall, the rib member, and the second lateral wall, the second cooling passage having a smaller cross-section than the first cooling passage.

7. The engine of claim 6 , wherein a volume of the first cooling passage is greater than a volume of the second cooling passage.

8. The engine of claim 6 , wherein a distance between the first lateral wall and the rib member is greater than a distance between the second lateral wall and the rib member.

9. The engine of claim 6 , wherein the outer wall has a first length extending annularly around a portion of the engine and the inner wall has a second length extending annularly around the portion of the engine, and the rib member extends continuously along the first and second lengths.

10. The engine of claim 6 , wherein the outer wall has a first length extending annularly around a portion of the engine and the inner wall has a second length extending annularly around the portion of the engine, and the rib member includes a plurality of rib sections positioned along the first and second lengths.

11. The engine of claim 6 , wherein the rib member includes a plurality of openings configured to permit flow of cooling gases between the first and second cooling passages through the openings.

12. The gas turbine engine of claim 6 , further comprising a connector member including a shaft connected to an inner end, wherein the inner end is sized and configured to be received through the slot and to straddle the slot after being rotated, and wherein the connector member supports the seal segment when the inner end straddles the slot.

13. A gas turbine engine, comprising:
a housing;
at least one compressor positioned within the housing;
at least one turbine operably coupled to the at least one compressor and including a plurality of blades extending radially from a longitudinal axis of the engine; and
a seal segment positioned along a portion of the housing and comprising:
a radially outer wall including at least one elongate aperture extending along a width of the seal segment and defining a slot on and through the radially outer wall configured to receive a connector member;
a radially inner wall positioned intermediate the outer wall and the blades of the turbine, the radially outer wall comprised of ceramic matrix composite material;
a first lateral wall extending between the outer and inner walls;
a second lateral wall extending between the outer and inner walls; and

a rib member integrally formed with and extending between the outer wall and the inner wall and intermediate the first and second walls without overlapping the at least one elongate aperture of the outer wall, wherein the outer wall, the inner wall, the rib member, and the first lateral wall define a first rectangular cross-section of the seal segment, and wherein the outer wall, the inner wall, the rib member, and the second lateral wall define a second rectangular cross-section of the seal segment.

14. The engine of claim 13 , wherein an area of the first rectangular cross-section is greater than an area of the second rectangular cross-section.

15. The engine of claim 13 , wherein the first cross-section has an elongate shape.

16. The engine of claim 15 , wherein the elongate shape is substantially perpendicular.

17. The engine of claim 13 , wherein a distance between the first lateral wall and the rib member is greater than a distance between the second lateral wall and the rib member.

18. The engine of claim 13 , wherein the outer wall has a first length extending annularly around a portion of the engine and the inner wall has a second length extending annularly around the portion of the engine, and the rib member extends continuously along the first and second lengths.

19. The engine of claim 13 , wherein the seal segment is comprised of a plurality of fabric layers.

20. The engine of claim 13 , wherein the seal segment is comprised of a three

Assignees

• Rolls Royce Corp
• Rolls Royce North America Tech Inc
• Rolls Royce Nam Tech Inc

Inventors

• Thomas David John
• Freeman Ted Joseph
• Lamusga Joseph Pan

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D11/08 Primary

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

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2300/2261

  of silicon · CPC title