Seal segment for a turbine
AssigneeROLLS-ROYCE plc
InventorsSteven D Lawer, Mark A Halliwell
Life of this patent
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Abstract
A seal segment (66) as described for a seal segment ring (64) of a turbine (16) in a gas turbine engine (10). The seal segment (66) has an inner surface (70) adapted to face the turbine blades (36) in use. Path means (72) is defined in the seal segment (66). The path means (72) is adapted to extend, in use, generally parallel to the principal axis of the turbine and has downstream inlet means (74) through which a cooling fluid to cool the seal segment can enter the path means (72) and upstream outlet means (76) from which the cooling fluid can be exhausted from the path means (72). The cooling fluid can flow along the path means (72) in a generally upstream direction opposite to the flow of gas through the turbine.
Claims20
A seal segment for a seal segment ring of a gas turbine engine, the seal segment comprising a main body having an inner surface adapted to face blades in use, wherein path means for a cooling fluid is defined in the main body, the path means extending, in use, between upstream and downstream regions of the seal segment.
A seal segment for a seal segment ring of a gas turbine engine, said seal segment having upstream and downstream regions, the seal segment comprising a main body having an inner surface adapted to face blades in use, wherein path means for a cooling fluid is defined in the main body, the path means extending, in use, between said upstream and downstream regions of the seal segment wherein the path means has downstream inlet means through which a cooling fluid to cool the segment can enter the path means, and upstream outlet means from which the cooling fluid can be exhausted from the path means, whereby cooling fluid can flow along the path means in a generally upstream direction opposite to the flow of gas through the engine.
Dependencies are inferred from the claim text.