SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE

摘要

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.

主权项

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; anda 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.