Dual source cooling air shroud arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9920647-B2
Application number	US-201414275354-A
Country	US
Kind code	B2
Filing date	May 12, 2014
Priority date	May 14, 2013
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

Abstract

A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.

First claim

The invention claimed is:

1. A seal segment of a shroud arrangement for bounding a hot gas flow path within an operating gas turbine engine, the seal segment being disposed upstream of and spaced from a downstream component of the gas turbine engine relative to the hot gas flow path, the seal segment comprising:
a cooling air chamber; and
a plate having:
a downstream trailing edge;
an inboard side which faces the hot gas flow path;
an outboard side;
a first cooling circuit for cooling a fore portion of the plate and a second cooling circuit for cooling an aft portion of the plate, the first cooling circuit and the second cooling circuit being fluidically isolated from one another; and
a first part of a two part seal attached to the plate on the outboard side thereof, a second part of the two part seal being attached to the downstream component that is disposed downstream and spaced from the seal segment, the first part of the two part seal partially defining an isolation chamber which is in fluid communication with the hot gas flow path via the downstream trailing edge of the plate,

wherein the cooling air chamber extends over the two part seal on the outboard side thereof,
wherein the cooling air chamber is in fluid communication with the second cooling circuit, and
wherein when the two part seal is closed, the two part seal prevents the leakage of hot gas from the isolation chamber to the cooling air chamber.

2. A seal segment as claimed in claim 1 , wherein the first part of the two part seal is appended from a supporting member which attaches the seal segment to a casing of the gas turbine engine.

3. A seal segment as claimed in claim 2 , wherein a first part of the supporting member provides a bulkhead which defines a fore portion and an aft portion on the outboard side of the seal segment, wherein the fore and the aft portions of the bulkhead are fluidically isolated from one another by the bulkhead in the operating gas turbine engine.

4. A seal segment as claimed in claim 3 , wherein the first part of the two part seal is a sealing flange which extends in a downstream direction towards the downstream trailing edge of the seal segment.

5. A gas turbine engine comprising: a shroud arrangement which includes the seal segment of claim 1 and the downstream component.

6. A gas turbine engine as claimed in claim 5 , wherein the two part seal is a flap seal.

7. A gas turbine engine as claimed in claim 5 , wherein the downstream component includes a gas washed surface which is exposed to the hot gas flow path.

8. A gas turbine engine as claimed in claim 5 , wherein the downstream component in the operating gas turbine engine includes at least one cavity which receives cooling air, the at least one cavity being in fluid communication with the cooling air chamber which extends across the two part seal on the outboard side thereof.

9. A gas turbine engine as claimed in claim 5 , wherein the fluid communication between the isolation chamber and the hot gas flow path is via an inlet which is defined by the downstream trailing edge of the seal segment and an upstream portion of the downstream component.

10. A gas turbine engine as claimed in claim 5 , wherein the downstream component is a nozzle guide vane.

11. A gas turbine engine as claimed in claim 5 , wherein the second cooling circuit is positioned within the seal segment.

12. A gas turbine engine as claimed in claim 11 , wherein the first cooling circuit is in fluid communication with a supply of cooling air.

13. A gas turbine engine as claimed in claim 12 , wherein the air for the first cooling circuit and second cooling circuit are supplied from different stages of a compressor of the gas turbine engine.

14. A seal segment as claimed in claim 1 , the first part of the two part seal comprising a sealing flange against which the second part of the two part seal is biased.

15. A seal segment as claimed in claim 14 , wherein the sealing flange is appended from a supporting member which attaches the seal segment to a casing of the gas turbine engine.

16. A seal segment as claimed in claim 1 , wherein an inlet to the isolation chamber is defined by the downstream trailing edge of the plate.

17. A seal segment of a shroud arrangement for bounding a hot gas flow path within an operating gas turbine engine, the seal segment being disposed upstream of and spaced from a downstream component of the gas turbine engine relative to the hot gas flow path, the seal segment comprising:
a cooling air chamber; and
a plate having:
a downstream trailing edge;
an inboard side which faces the hot gas flow path;
an outboard side;
a first cooling circuit disposed within the plate for cooling a fore portion of the plate and a second cooling circuit disposed within the plate for cooling an aft portion of the plate, the first cooling circuit and the second cooling circuit being fluidically isolated from one another;
a first part of a two part seal attached to the plate on the outboard side thereof, the second part of the two part seal being attached to the downstream component that is downstream and spaced from the seal segment, the first part of the two part seal partially defining an isolation chamber which is in fluid communication with the hot gas flow path via the downstream trailing edge of the plate, wherein the cooling air chamber extends over the two part seal on the outboard side thereof,

wherein the cooling air chamber is in fluid communication with the second cooling circuit, and
wherein when the two part seal is closed, the two part seal prevents the leakage of hot gas from the isolation chamber to the cooling air chamber.

18. A seal segment as claimed in claim 17 , the first part of the two part seal comprising a sealing flange against which the second part of the two part seal is biased.

Assignees

• Rolls Royce Plc

Inventors

• Jones Simon Lloyd
• Taylor Rupert John
• Balsdon Julian Glyn

Classifications

• F05D2260/204

  by the use of microcircuits · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/24 Primary

  by selectively cooling-heating stator or rotor components · CPC title

• F05D2240/11

  Shroud seal segments · CPC title