| 摘要 |
Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement. |
