Cooling system for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsAlan Maguire, John Hoptroff
Life of this patent
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Abstract
A cooling system for a gas turbine engine (FIG. 1) comprises a pre-swirl arrangement, preferably including a pre-swirl chamber, for providing cooling air to a turbine blade disc, and a ventilation arrangement for providing ventilation air to a rotating component of the gas turbine engine. The cooling system includes an air bypass arrangement, which preferably includes first, second and third air bypass duct portions, for conveying ventilation air away from the pre-swirl arrangement.
Claims23
A cooling system for a gas turbine engine, the cooling system comprising a pre-swirl arrangement for providing cooling air to a turbine blade disc, and a ventilation arrangement for providing ventilation air to a rotating component of the gas turbine engine, characterised in that the cooling system includes an air bypass arrangement for conveying ventilation air away from the pre-swirl arrangement.
A cooling system according to claim 23, wherein the second air bypass duct portion is arranged to receive air from the first air bypass duct portion and to convey the air into the third air bypass duct portion.
Dependencies are inferred from the claim text.