Ceramic matrix composite seal segment for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10989060-B2
Application number	US-202016845820-A
Country	US
Kind code	B2
Filing date	Apr 10, 2020
Priority date	May 26, 2015
Publication date	Apr 27, 2021
Grant date	Apr 27, 2021

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 segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the shroud comprising:
a carrier having an axial flange and a central flange that extends radially inward from the axial flange, the central flange shaped to define a carrier bore that extends axially therethrough,
a ceramic matrix composite (CMC) seal segment comprising an arcuate flange having a surface facing the turbine and a first segmented pin bore flange having a first forward segment portion and a first aft segment portion located axially aft of the first forward segment portion with a first groove defined therebetween, the first forward segment portion and the first aft segment portion arranged to locate the central flange of the carrier axially therebetween, and
an elongated pin that extends through the forward segment portion of the segmented pin bore flange, the central flange of the carrier, and the aft segment portion of the segmented pin bore flange to couple the ceramic matrix composite seal segment to the carrier.

2. The shroud of claim 1 , wherein the central flange of the carrier is integral with the axial flange.

3. The shroud of claim 1 , wherein the carrier includes a leading edge flange that extends radially inward from axial flange and is located axially forward of the central flange, and a trailing edge flange that extends radially inward from the axial flange and is located axially aft of the central flange.

4. The shroud of claim 1 , wherein the ceramic matrix composite seal segment includes a second segmented pin bore flange circumferentially spaced apart from the first segmented pin bore flange, the second segmented pin bore flange having a second forward segment portion and a second aft segment portion located axially aft of the second forward segment portion with a second groove defined therebetween.

5. The shroud of claim 1 , wherein the elongated pin has a length that is at least 50% of an axial length of the arcuate flange of the ceramic matrix composite seal segment.

6. The shroud of claim 1 , wherein said first forward segment portion and said first aft segment portion comprise a curved outer surface and are radially spaced from said arcuate flange by an elongated spacing flange extending radially outward from said arcuate flange.

7. The shroud of claim 6 , wherein said elongated spacing flange has an axial dimension parallel to the axis of said bore and a lateral dimension less than the axial dimension of said arcuate flange and less than a lateral dimension of said first segmented pin bore flange.

8. A segmented turbine shroud radially encasing a turbine in a gas turbine engine, said shroud comprising:
a carrier having an axial flange and a central flange that extends radially inward from the axial flange, the central flange defining a carrier pin-receiving bore; and
a ceramic matrix composite (CMC) seal segment carried by said carrier by a plurality of elongated pins, said CMC seal segment comprising an arcuate flange having an inner surface facing the turbine and an opposing outer surface and a plurality of radial members extending radially away from said outer surface, each of said radial members comprising a spacing portion, a forward portion defining a forward elongated pin-receiving bore, and an aft portion located axially aft of the forward portion and defining an aft elongated pin-receiving bore, the forward portion and the aft portion located at a radially outward distal end of the spacing portion, a radial dimension of said arcuate flange being a dimension between said inner surface and said opposing outer surface, and
wherein said spacing portion has an axial dimension parallel to the axis of said forward elongated pin-receiving bore and a lateral dimension less than the axial dimension of said spacing portion and wherein the lateral dimension of said spacing portion is less than a lateral dimension of said forward portion and aft portion.

9. The shroud of claim 8 , wherein a groove is defined in the spacing portion located axially aft of the forward portion and axially forward of the aft portion, and the central flange of the carrier is received by the groove.

10. The shroud of claim 8 , wherein the central flange of the carrier is integral with the axial flange.

11. The shroud of claim 9 , wherein the forward elongated pin-receiving bore and the aft elongated pin-receiving bore are radially spaced from said outer surface of said arcuate flange a distance greater than the minimum radial dimension of said arcuate flange.

12. The shroud of claim 9 , wherein the carrier further includes a forward flange that extends radially inward from axial flange and is located axially forward of the central flange, and an aft flange that extends radially inward from the axial flange and is located axially aft of the central flange.

13. The shroud of claim 12 , wherein the forward portion of the CMC seal segment is located axially aft of the forward flange of the carrier and axially forward of the central flange of the carrier when the CMC seal segment is coupled to the carrier, and the aft portion of the CMC seal segment is located axially aft of the central flange of the carrier and axially forward of the aft flange of the carrier when the CMC seal segment is coupled to the carrier.

14. The shroud of claim 8 , wherein at least one of the pin-receiving bores comprises a circular lateral cross-section.

15. The shroud of claim 8 , wherein said CMC seal segment comprises at least two radial members defining pin-receiving bores that are circumferentially spaced apart.

16. The shroud of claim 8 , wherein the elongated pins have a length that is at least 50% of an axial length of the arcuate flange of the CMC seal segment.

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

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · 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 Primary

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