Turbine shroud having ceramic matrix composite seal segment

Patent metadata

Field	Value
Publication number	US-10370997-B2
Application number	US-201514721651-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 rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.

First claim

What is claimed is:

1. A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine, the shroud comprising:
a carrier comprising a forward generally planar flange and an aft generally planar flange, each of said flanges extending radially inward toward the turbine perpendicular to the axis of rotation of the turbine, said forward flange comprising a forward portion defining a pin-receiving forward carrier bore extending through the forward portion and said aft flange comprising an aft portion defining a pin-receiving aft carrier bore extending through said aft portion, wherein both the forward carrier bore and aft carrier bore have an axis parallel to the axis of rotation of the turbine;
a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving seal segment bore; and
an elongated pin extending through said forward carrier bore, said seal segment bore, and said aft carrier bore,
wherein each of said carrier flange portions defining said pin-receiving forward carrier bore and said pin-receiving aft carrier bore include a respective member extending axially from said flange to thereby define the carrier bore having a length greater than the axial dimension of said flange, said member having a length sufficient to effect radial flexion between said member and said pin received within said carrier bore during operation of the gas turbine engine.

2. The shroud of claim 1 wherein the length of said carrier bore is at least 120% of the axial dimension of said flange.

3. The shroud of claim 1 wherein said carrier portion defines a carrier bore comprising a continuously curved lateral cross-section.

4. The shroud of claim 3 wherein said carrier portion defines a carrier bore having a circular lateral cross-section.

5. The shroud of claim 1 wherein said carrier bore is adapted to receive an elongated pin comprising a lateral cross-sectional dimension of at least three eighths inches.

6. The shroud of claim 1 wherein said elongated pin is hollow.

7. The shroud of claim 1 further comprising a bushing disposed around said elongated pin within said carrier bore.

8. The shroud of claim 1 wherein said carrier bore comprises a chamfered end.

9. The shroud of claim 1 wherein said carrier bore comprises a minimum lateral cross-sectional dimension of at least three eighths inches.

10. A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine, the shroud comprising a plurality of cartridges, one or more cartridges comprising:
a carrier segment comprising a plurality of opposing portion pairs, each portion defining a pin-receiving carrier bore having a circular lateral cross-section extending through the respective portion, each opposing portion pair being aligned to receive a single elongated pin within the opposing pin-receiving carrier bores defined thereby;
a ceramic matrix composite (CMC) seal segment comprising a plurality of portions each defining a pin-receiving seal segment bore; and
a plurality of elongated pins, each pin extending through each of said pair of opposing pin receiving carrier bores and one or more of said seal segment bores,
wherein said carrier segment carries a single CMC seal segment by one or more of said elongated pins;
wherein each of said carrier portions defining said pin-receiving carrier bores comprise a generally planar flange extending radially inward toward the turbine perpendicular to the axis of rotation of the turbine and a member extending axially from said flange to thereby define the carrier bore having a length greater than the axial dimension of said flange.

11. The cartridge of claim 10 wherein each of said carrier bores is adapted to receive an elongated pin comprising a lateral cross-sectional dimension of at least three eighths inches.

12. The cartridge of claim 10 wherein the length of each of said carrier bores is at least 120% of the axial dimension of said flange.

13. The shroud of claim 10 further comprising a radially compressible bushing disposed around said elongated pin within each of said carrier bores.

14. The cartridge of claim 10 wherein each of said carrier bores comprise opposing ends which are chamfered.

15. The cartridge of claim 10 wherein said carrier segment comprises at least three opposing portion pairs, each portion defining a pin-receiving carrier bore having a circular lateral cross-section, each opposing portion pair being aligned to receive a single elongated pin within the opposing pin-receiving carrier bores defined thereby.

Assignees

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

Inventors

• Vetters Daniel Kent
• Thomas David J
• Dierksmeier Douglas David
• Shi Jun
• Engel Todd

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title

• F05D2250/15

  spiral · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title