Shroud arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9677412-B2
Application number	US-201414275452-A
Country	US
Kind code	B2
Filing date	May 12, 2014
Priority date	May 14, 2013
Publication date	Jun 13, 2017
Grant date	Jun 13, 2017

Abstract

A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine.

First claim

The invention claimed is:

1. A seal segment of a shroud arrangement for bounding a main hot gas flow path within a gas turbine engine, comprising:
a plate having an inboard main hot gas flow path facing side and an outboard side;
a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion;
a first cooling circuit within the plate for cooling a first portion of the plate;
a second cooling circuit within the plate for cooling a second portion of the plate; and,
one or more chimneys which define one or more inlet passages each of which extends from an inlet at the fore portion or the aft portion to one of the first or second cooling circuits,
wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another
wherein:
the one or more chimneys extend from the inlet and across an isolation chamber to the first or second cooling circuit, the isolation chamber being in fluid communication with and pressurized by the main hot gas flow path.

2. A seal segment as claimed in claim 1 , further comprising a fore attachment and an aft attachment for supportably attaching the seal segment to a carrier or engine casing, wherein the bulkhead is part of either the fore or aft attachment.

3. A seal segment as claimed in claim 1 , wherein the chimneys form part of the bulkhead.

4. A seal segment as claimed in claim 1 , wherein the seal segment is one of an annular set which are coaxial with the principal axis of the gas turbine engine when in use, and the bulkhead includes axially offset portions of a circumferentially extending wall, in which the axial offset is with respect to the principal axis.

5. A seal segment as claimed in claim 4 , wherein at least one of the axially offset portions of circumferentially extending walls is provided by at least one of the one or more chimneys.

6. A seal segment as claimed in claim 1 , wherein each cooling circuit includes two or more sub-circuits.

7. A seal segment as claimed in claim 1 , wherein the second cooling circuit terminates in one or more outlets local tolocated at a downstream edge of the plate.

8. A seal segment as claimed in claim 1 , wherein the seal segment is configured to provide one circumferentially extending segment of a segmented annular shroud, and the first cooling circuit terminates in one or more outlets local to a circumferential edge of the shroud.

9. A seal segment as claimed in claim 1 , further comprising one part of a two part seal, the two part seal separating the aft portion from the main hot gas flow path when in an assembled gas turbine engine.

10. A seal segment as claimed in claim 9 , wherein the one part of the two part seal is a flap seal.

11. A gas turbine engine including a shroud arrangement, comprising:
an engine casing; and
a seal segment according to claim 1 .

12. A gas turbine engine as claimed in claim 11 , wherein the fore portion is in fluid communication with a first air source having a first pressure and temperature, and the aft portion is attached to a second air source having a second pressure and temperature.

13. A gas turbine engine as claimed in claim 11 , wherein the aft portion is connected to a chamber which provides air to a downstream nozzle guide vane.

14. A gas turbine engine as claimed in claim 1 , wherein the second cooling circuit terminates in one or more outlets located downstream of the first cooling circuit.

Assignees

• Rolls Royce Plc

Inventors

• Jones Simon Lloyd
• Simms Mark John

Classifications

• F01D11/24 Primary

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

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F05D2260/204

  by the use of microcircuits · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic