Ceramic matrix composite seal segment for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9963990-B2
Application number	US-201514721705-A
Country	US
Kind code	B2
Filing date	May 26, 2015
Priority date	May 26, 2015
Publication date	May 8, 2018
Grant date	May 8, 2018

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;
a ceramic matrix composite (CMC) seal segment comprising an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin; and
one or more elongated pins,
wherein said CMC seal segment is carried by said carrier by at least one of said elongated pins being received within said bore,
wherein said CMC seal segment portion defining a pin-receiving bore comprises a curved outer surface and is radially spaced from said arcuate flange by an elongated spacing flange extending radially outward from said arcuate flange, said elongated spacing flange having an axial dimension parallel to the axis of said bore and a lateral dimension less than the axial dimension of said flange and less than a lateral dimension of said portion defining the bore, and wherein said CMC seal segment portion defines a bore having a length that is at least 70% of the length of said elongated pin received therein.

2. The shroud of claim 1 wherein said pin receiving bore has a length that is at least 80% of the length of said elongated pin received therein.

3. The shroud of claim 1 wherein said pin receiving bore has a length that is at least 75% of a parallel dimension of said arcuate flange.

4. The shroud of claim 3 wherein said pin receiving bore has a length that is at least 90% of a parallel dimension of said arcuate flange.

5. The shroud of claim 1 wherein said elongated pin passes through only a single pin-receiving bore of said CMC seal segment.

6. The shroud of claim 1 wherein the curved outer surface of portion defining bore is coaxial with bore.

7. A segmented turbine shroud radially encasing a turbine in a gas turbine engine, said shroud comprising:
a carrier; 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 and a portion defining an elongated pin-receiving bore at the distal end thereof, a radial dimension of said arcuate flange being a dimension between said inner surface and said opposing outer surface,
wherein each of said radial members defines a pin-receiving bore having an axial length greater than the minimum radial dimension of said arcuate flange, and
wherein said spacing portion has an axial dimension parallel to the axis of said bore and a lateral dimension less than the axial dimension of said flange and less than a lateral dimension of said portion defining said bore.

8. The shroud of claim 7 wherein each of said radial members defines a bore that is radially spaced from said outer surface of said arcuate flange a distance greater than the minimum radial dimension of said arcuate flange.

9. The shroud of claim 8 wherein each of said radial members defines a bore that is radially spaced from said outer surface of said arcuate flange a distance greater than twice the minimum radial dimension of said arcuate flange.

10. The shroud of claim 7 wherein at least one of said radial members defines a pin-receiving bore comprising a circular lateral cross-section.

11. The shroud of claim 7 wherein said CMC seal segment comprises at least three radial members defining pin-receiving bores.

12. The shroud of claim 7 wherein at least one of said radial members defines a pin-receiving bore having a length that is at least 70% of the length of an elongated pin received therein.

13. The shroud of claim 12 wherein at least one of said radial members defines a pin-receiving bore comprising a lateral cross-section dimension of at least three-eighths inches.

14. The shroud of claim 7 wherein at least one of said radial members defines a pin-receiving bore comprising a lateral cross-section dimension of at least three-eighths inches.

15. The shroud of claim 7 wherein at least one of said radial members defines a pin-receiving bore comprising a lateral cross-section dimension that varies along the length of said bore.

16. A segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the shroud comprising: a carrier comprising a plurality of portions each defining a pin-receiving carrier bore; a ceramic matrix composite (CMC) seal segment comprising an arcuate flange having a surface facing the turbine and a plurality of tubular portions each defining a pin-receiving seal segment bore, each of said tubular portions being radially spaced from said arcuate flange by a spacing flange having an elongated axis parallel to the axis of the bore and a radial axis intersecting the axis of the bore; and a plurality of elongated pins, each of said pins passing through at least a carrier bore and a seal segment bore to thereby mount said CMC seal segment to said carrier.

Assignees

• Vetters Daniel Kent
• Thomas David J
• Freeman Ted
• Dierksmeier Douglas David
• Shi Jun
• Engel Todd
• Rolls Royce Nam Tech Inc
• Rolls Royce Corp
• Rolls Royce High Temperature Composites Inc

Inventors

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

Classifications

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D11/08 Primary

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

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2220/32

  in gas turbines · CPC title