SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE

• US 20140341717A1
• Filed: 05/12/2014
• Published: 11/20/2014
• Est. Priority Date: 05/14/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: JONES, Simon Lloyd, TAYLOR, Rupert John, BALSDON, Julian Glyn
• Granted Patent: US 9,920,647 B2
• Time in Patent Office: Days
• US Class Current: 415/144
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2260/204 by the use of microcircuits

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.

Claims

1. A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, the seal segment being upstream of a second component of the gas turbine engine relative to the hot gas flow path, the seal segment comprising:

a plate having;

a downstream trailing edge;

an inboard side which faces the hot gas flow path when in use;

an outboard side;

a first cooling circuit for cooling a first portion of the plate and a second cooling circuit for cooling a second portion of the plate, the first and second cooling circuits being fluidically isolated from one another; 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 and a cooling air chamber which extends over the two part seal on the outboard side thereof, wherein the cooling air chamber is in fluid communication with either the first or second cooling circuits.

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 the engine casing.

3. A seal segment as claimed in claim 2, wherein the 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 aft portions are fluidically isolated from one another by the bulkhead in use.

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 trailing edge of the sealing segment.

5. A gas turbine engine comprising:

a shroud arrangement which includes the seal segment of any previous claim and the second 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 second 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 second component includes at least one cavity which receives cooling air in use, 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 second component is immediately downstream of the seal segment.

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

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

12. A gas turbine engine as claimed in claim 5, wherein the seal segment includes a first cooling circuit for cooling a first portion of the plate and a second cooling circuit within the seal segment for cooling a second portion of the plate.

13. A gas turbine engine as claimed in claim 12, wherein the first cooling circuit is in fluid communication with a second supply of cooling air which is separate to the cooling air chamber.

14. A gas turbine engine as claimed in claim 13, wherein the cooling air chamber and the second supply of cooling air are supplied from different stages of a compressor of the gas turbine engine.