Shroud arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9611754-B2
Application number	US-201414275195-A
Country	US
Kind code	B2
Filing date	May 12, 2014
Priority date	May 14, 2013
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

A seal segment for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits, wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous path between an inlet on the outboard side of the plate and an exhaust.

First claim

The invention claimed is:

1. A seal segment for bounding a hot gas flow path within a gas turbine engine, comprising:
a plate having an inboard side which bounds the hot gas flow path in use, an outboard side and fore and aft cooling circuits,
wherein the fore and aft cooling circuits are fluidically separated from one another within the plate and each has at least one tortuous elongate path between an inlet on the outboard side of the plate and an exhaust,
wherein:
the at least one tortuous elongate path of the fore cooling circuit includes a plurality of passageways in flow series each of which traverses the plate along a circumferential length of the plate including (i) a first passageway that directs cooling fluid to flow along a first circumferential direction of the plate and (ii) a second passageway that directs cooling fluid to flow along a second circumferential direction of the plate that is opposite the first circumferential direction,
and the at least one tortuous elongate path of the aft cooling circuit includes a plurality of passageways in flow series each of which extends along an axial length of the plate, the axial length of the plate extending in a direction from upstream to downstream of the hot gas flow path.

2. A seal segment as claimed in claim 1 , wherein the fore and aft cooling circuits include respective first and second sub-circuits.

3. A seal segment as claimed in claim 2 , wherein the sub-circuits of the fore cooling circuit are located on opposite sides of a plane which extends between a leading edge and trailing edge of the plate, and the sub-circuits of the aft cooling circuit are located on opposite sides of a plane which extends between a leading edge and trailing edge of the plate.

4. A seal segment as claimed in claim 1 , wherein the fore cooling circuit includes at least one exhaust along a circumferential edge of the plate.

5. A seal segment as claimed in claim 1 , wherein the aft cooling circuit includes at least one exhaust along a trailing edge of the plate.

6. A seal segment as claimed in claim 1 , wherein exhausts are in fluid communication with the hot gas flow path in use.

7. A seal segment as claimed in claim 1 , wherein at least one of the fore and aft cooling circuits occupy at least half the axial length of the plate but not more than three-quarters the axial length of the plate.

8. A seal segment as claimed in claim 1 , wherein either or both of the at least one tortuous path of the fore and the at least one tortuous path of the aft cooling circuits include a meandering path which includes at least one U-bend which turns the trajectory of the passageway back on itself.

9. A seal segment as claimed in claim 1 , wherein at least one cooling circuit or sub-circuit is U-shaped.

10. A seal segment as claimed in claim 1 , wherein at least one cooling circuit or sub-circuit is m-shaped.

11. A seal segment as claimed in claim 1 , wherein the fore cooling circuit includes a U-shaped passageway and the aft cooling circuit includes an m-shaped passageway.

12. A seal segment as claimed in claim 10 , wherein the m-shaped passageways include an inlet along a mid portion of the m-shape.

13. A seal segment as claimed in claim 1 , wherein the cooling circuits are partitioned by a plurality of elongate walls which meet at an intersection, each of the walls extending along a longitudinal axis and having a bent portion which offsets the intersection of the walls from the intersection of the longitudinal axes of the walls such that the two are not co-located.

14. A seal segment as claimed in claim 13 , wherein a secondary inlet is provided adjacent to the intersection of the walls, and the secondary inlet provides cooling fluid to either the fore or aft cooling circuit.

15. A seal segment as claimed in claim 14 , wherein the secondary inlet is provided at the intersection of the longitudinal axes.

16. A seal segment as claimed in claim 1 , wherein each of the plurality of passageways of the aft cooling circuit directs cooling fluid to flow along an axial direction of the plate.

17. A seal segment as claimed in claim 1 , wherein the plurality of passageways of the aft cooling circuit includes a first passageway that directs cooling fluid to flow along a first axial direction of the plate, and a second passageway that directs cooling fluid to flow along a second axial direction of the plate that is opposite the first axial direction.

Assignees

• Rolls Royce Plc

Inventors

• Taylor Rupert John

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F01D11/08

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