| 摘要 |
Described is a seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, comprising: 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, comprising: providing air at a first temperature and pressure to a fore portion of the seal segment; and, providing air at a second temperature and pressure to an aft portion of the seal segment, wherein the air provided at the second temperature and pressure is delivered from a downstream direction relative to the main gas flow path of the gas turbine engine. |
