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US 2010/0303616 A1Published application
Cooling system for an aero gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsAdam P. Chir, Andrew M. Rolt
Life of this patent
Estimating the term…
Abstract
A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.
Claims9
A cooling system for an aero gas turbine engine, the system having:
- a duct which diverts a portion of a bypass air stream of the engine,
- a heat exchanger located in the duct which receives cooling air for cooling components of the engine, the cooling air being cooled in the heat exchanger by the diverted bypass air stream, and
- a tail cone located at the exit of the engine;
- wherein, after cooling the cooling air, the spent diverted air stream is routed to the tail cone and ejected through a nozzle thereat.
1 more element
Dependencies are inferred from the claim text.