Patent ID: 9611754
Date: 2017-04-04
CPC Classifications: F01D,F05D

Claim:
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.