Flexibly mounted ceramic matrix composite seal segments

Patent metadata

Field	Value
Publication number	US-10370998-B2
Application number	US-201514721684-A
Country	US
Kind code	B2
Filing date	May 26, 2015
Priority date	May 26, 2015
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

A segmented turbine shroud for radially encasing a turbine in a gas turbine engine comprises a carrier comprising a flange; a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving bore; an elongated pin extending through the pin-receiving bore; a bushing surrounding the elongated pin within the bore; and a flexible mounting member, the flexible mounting member being connected to the bushing and the carrier flange to thereby flexibly mount the CMC seal segment to the carrier.

First claim

What is claimed is:

1. A segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the shroud comprising:
a carrier comprising a flange;
a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving bore;
an elongated pin extending through said pin-receiving bore;
a bushing surrounding said elongated pin within said bore and having at least a portion extending axially beyond a first end of the bore; and
a flexible mounting member, said flexible mounting member being connected to said bushing at said portion extending axially beyond the first end of the bore and said carrier flange to thereby flexibly mount said CMC seal segment to said carrier.

2. The shroud of claim 1 wherein the radial stiffness of said flexible member is greater than the lateral stiffness of said flexible member.

3. The shroud of claim 1 wherein said flexible member is formed from sheet metal.

4. The shroud of claim 1 wherein said carrier flange extends radially inward toward the turbine perpendicular to the axis of rotation of the turbine.

5. The shroud of claim 1 wherein said carrier flange extends circumferentially about the axis of rotation of the turbine.

6. The shroud of claim 1 wherein said CMC seal segment further comprises an arcuate flange having a surface facing the turbine and a spacing flange extending radially outward from said arcuate flange to affect radial spacing of said portion defining said pin-receiving bore from said arcuate flange.

7. The shroud of claim 6 wherein said pin-receiving bore comprises a lateral cross-sectional dimension of at least three eighths inches.

8. A segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the shroud comprising:
a carrier comprising a flange;
a ceramic matrix composite (CMC) seal segment comprising an arcuate flange having a surface facing the turbine, a portion defining a pin-receiving seal segment bore which is radially spaced from said arcuate flange by a spacing flange extending radially outward from said arcuate flange;
a mounting ring defining a mounting ring bore, said mounting ring disposed at a first axial end of said seal segment bore;
a flexible mounting member connected to said carrier flange and said mounting ring; and
an elongated pin extending beyond the first axial end of said seal segment bore and into said mounting ring bore.

9. The shroud of claim 8 further comprising a pair of mounting rings and a pair of flexible mounting members, wherein each of the mounting rings define a mounting ring bore, each mounting member being connected to said carrier flange and one of said mounting rings, said elongated pin extending through said seal segment bore and each of said mounting ring bores.

10. The shroud of claim 9 wherein a first of said pair of mounting rings is disposed forward of said seal segment bore and a second of said pair of mounting rings is disposed aft of said seal segment bore.

11. The shroud of claim 8 wherein the radial stiffness of said flexible mounting member is greater than the lateral stiffness of said flexible mounting member.

12. The shroud of claim 8 wherein said carrier flange extends radially inward toward the turbine perpendicular to the axis of rotation of the turbine.

13. The shroud of claim 8 wherein said carrier flange extends circumferentially about the axis of rotation of the turbine.

14. The shroud of claim 8 wherein said pin-receiving bore comprises a lateral cross-sectional dimension of at least three eighths inches.

15. The shroud of claim 8 wherein said flexible mounting member is formed from sheet metal.

16. The shroud of claim 8 wherein the lateral stiffness of said flexible mounting member is greater than the radial stiffness of said flexible mounting member.

Assignees

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

Inventors

• Vetters Daniel Kent
• Engel Todd
• Brandt Matt

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D11/12 Primary

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title