Shroud arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9689273-B2
Application number	US-201414275249-A
Country	US
Kind code	B2
Filing date	May 12, 2014
Priority date	May 14, 2013
Publication date	Jun 27, 2017
Grant date	Jun 27, 2017

Abstract

Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement.

First claim

The invention claimed is:

1. A shroud arrangement for a gas turbine engine, comprising:
a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a carrier via at least one fore attachment and at least one aft attachment, the fore and aft attachments restricting radial movement of the seal segment relative to the carrier, and wherein the fore and aft attachments are simultaneously slidably engaged with the carrier from an axial direction; and,
a shear key,
wherein the seal segment includes a first receiving part that receives a first part of the shear key, and the carrier includes a second receiving part that receives a second part of the shear key, and the shear key thereby prevents axial movement of the seal segment relative to the carrier, the axis being the principal rotational axis of the engine.

2. A shroud arrangement as claimed in claim 1 , wherein the seal segment and carrier form a shroud cassette which axially engages an engine casing.

3. A shroud arrangement as claimed in claim 2 , wherein either the fore and aft attachments engage with the carrier from a downstream direction or the cassette engages with the engine casing from a downstream direction, relative to the main gas flow path of the gas turbine engine.

4. A shroud arrangement as claimed in claim 3 , wherein the cassette axially engages with the engine casing in an opposite direction to the axial engagement of the seal segment relative to the carrier.

5. A shroud arrangement as claimed in claim 1 , wherein the fore and aft attachments include bird mouth formations.

6. A shroud arrangement as claimed in claim 1 wherein the seal segment is one of a plurality of similar seal segments which abut one another circumferentially to provide the shroud arrangement in use,
wherein the shear key engages with the seal segment at a circumferential edge such that it is at least partially obscured by an adjacent seal segment when the seal segment is part of the assembled shroud arrangement.

7. A shroud arrangement as claimed in claim 6 , wherein the shear key is received within an open ended slot which is provided in the circumferential edge, the open ended slot being partially defined by the seal segment and carrier.

8. A shroud arrangement as claimed in claim 1 , further comprising a supporting member which includes one of the fore or aft attachments, wherein the axial retainer is part of the supporting member.

9. A shroud arrangement as claimed in claim 1 , wherein either or both of the fore and aft attachments provide a bulkhead which partitions the space between the seal segment and an engine casing so as to provide a fore portion and an aft portion which are substantially fluidically isolated in use.

10. A shroud arrangement as claimed in claim 9 , wherein the bulkhead includes a slot for the shear key.

11. A gas turbine engine comprising the shroud arrangement of claim 1 .

12. A shroud arrangement as claimed in claim 1 , wherein the shear key is received in a slot which is formed partially by the seal segment and partially by the carrier.

13. A shroud arrangement as claimed in claim 1 , wherein the seal segment and carrier are attached to one another to form a shroud cassette and wherein the shear key is snugly received in a slot provided in a circumferential edge of the shroud cassette.

14. A shroud arrangement as claimed in claim 1 , wherein the fore and aft attachments are integrally formed with the seal segment.

15. A shroud arrangement as claimed in claim 1 , wherein the seal segment engages with corresponding fore and aft carrier attachments.

Assignees

• Rolls Royce Plc

Inventors

• Jones Simon Lloyd
• Simms Mark John

Classifications

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F01D11/08 Primary

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

• 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

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title