Turbine shroud assembly with pinned shroud attachment

Patent metadata

Field	Value
Publication number	US-12203376-B2
Application number	US-202318211035-A
Country	US
Kind code	B2
Filing date	Jun 16, 2023
Priority date	Jun 18, 2021
Publication date	Jan 21, 2025
Grant date	Jan 21, 2025

Abstract

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

First claim

What is claimed is:

1. A turbine shroud assembly adapted for use with a gas turbine engine, the turbine shroud assembly comprising
a carrier shaped to include an outer wall, a first support wall, a second support wall spaced axially from the first support wall relative to an axis, and a third support wall located between the first support wall and the second support wall, and wherein the first support wall, the second support wall, and the third support wall extend radially inward from the outer wall and the second support wall is formed to include an installation aperture that extends axially through the second support wall, wherein the third support wall is formed to include a first plate that extends radially inward from the outer wall and a second plate that extends radially inward from the outer wall and is spaced apart axially from the first plate to define an axially extending gap therebetween,
a seal segment that includes a seal body that defines a gas path of the turbine shroud assembly, a first mount flange that extends from the seal body into a space between the first support wall and the third support wall of the carrier, and a second mount flange that extends from the seal body into a second space between the second support wall and the third support wall of the carrier, the second mount flange being spaced apart axially from the first mount flange to locate the third support wall axially between the first mount flange and the second mount flange,
a first pin that extends axially through the first mount flange of the seal segment into both the first support wall and the third support wall of the carrier to couple the first mount flange with the carrier, and
a second pin that extends axially through the second mount flange of the seal segment into both the second support wall and the third support wall of the carrier to couple the second mount flange with the carrier, wherein the first pin and the second pin are adhered together,
wherein the first pin extends axially into a blind hole formed in the first support wall.

2. The turbine shroud assembly of claim 1 , wherein the first pin extends into the first plate and terminates axially before the second plate and the second pin extends into the second plate and terminates axially before the first plate.

3. The turbine shroud assembly of claim 1 , wherein the second pin is circumferentially aligned with the first pin.

4. The turbine shroud assembly of claim 1 , wherein the second pin contacts the first pin.

5. The turbine shroud assembly of claim 1 , wherein the first support wall is formed to define a channel that extends circumferentially and opens radially inward and wherein the turbine shroud assembly further includes a seal located in the channel and engaged with the first support wall and the seal body of the seal segment.

6. The turbine shroud assembly of claim 5 , wherein the second support wall is formed to define a second channel that extends circumferentially and opens radially inward and wherein the turbine shroud assembly further includes a second seal located in the second channel and engaged with the second support wall and the seal body of the seal segment.

7. The turbine shroud assembly of claim 6 , wherein the seal includes a first seal element, a second seal element, and a third seal element located axially between the first seal element and the second seal element.

8. The turbine shroud assembly of claim 1 , further including a plug that extends into the second support wall to block axial movement of the first pin and the second pin.

9. The turbine shroud assembly of claim 8 , wherein the plug includes a shaft that extends into the second support wall and a head that extends from the shaft and engages the second support wall.

10. The turbine shroud assembly of claim 8 , further comprising a retainer pin that extends through the outer wall of the carrier and into the plug.

11. The turbine shroud assembly of claim 1 , wherein the second pin is adhered to the first pin with a glue configured to burn away during operation of the turbine shroud.

12. The turbine shroud assembly of claim 1 , wherein the first pin is in direct confronting relation with the second pin.

13. The turbine shroud assembly of claim 1 , wherein the outer wall, the first support wall, the second support wall, and the third support wall form a unitary, one-piece component.

14. The turbine shroud assembly of claim 1 , wherein the first pin is sized such that the entire first pin is configured to move through the installation aperture in the second support wall.

15. A turbine shroud assembly adapted for use with a gas turbine engine, the turbine shroud assembly comprising
a carrier shaped to include an outer wall, a first support wall, a second support wall spaced axially from the first support wall relative to an axis, and a third support wall located between the first support wall and the second support wall, and wherein the first support wall, the second support wall, and the third support wall extend radially inward from the outer wall and the second support wall is formed to include an installation aperture that extends axially through the second support wall, wherein the third support wall is formed to include a first plate that extends radially inward from the outer wall and a second plate that extends radially inward from the outer wall and is spaced apart axially from the first plate to define an axially extending gap therebetween,
a seal segment that includes a seal body that defines a gas path of the turbine shroud assembly, a first mount flange that extends from the seal body into a space between the first support wall and the third support wall of the carrier, and a second mount flange that extends from the seal body into a second space between the second support wall and the third support wall of the carrier, the second mount flange being spaced apart axially from the first mount flange to locate the third support wall axially between the first mount flange and the second mount flange,
a first pin that extends axially through the first mount flange of the seal segment into both the first support wall and the third support wall of the carrier to couple the first mount flange with the carrier,
a second pin that extends axially through the second mount flange of the seal segment into both the second support wall and the third support wall of the carrier to couple the second mount flange with the carrier, wherein the first pin and the second pin are adhered together,
a plug that extends into the second support wall to block axial movement of the first pin and the second pin, and
a retainer pin that extends through the outer wall of the carrier and into the plug.

Assignees

• Rolls Royce Corp

Inventors

• Freeman Ted J
• Sippel Aaron D
• Thomas David J

Classifications

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F16B19/02

  Bolts or sleeves for positioning of machine parts, e.g. notched taper pins, fitting pins, sleeves, eccentric positioning rings · CPC title

• F05D2300/50212

  dissimilar · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title