Gas turbine engine and cooling system
AssigneeRolls-Royce North American Technologies Inc.
InventorsEric Sean Donovan, William Daniel Feltz, Steven Wesley Tomlinson
Life of this patent
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Abstract
One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique cooling system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooling one or more objects of cooling. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
Claims22
A cooling system for use with a gas turbine engine, comprising:
- a heat exchanger operative to cool air of a first working fluid stream of the gas turbine engine;
- a cooling medium inlet for said heat exchanger structured to receive a cooling medium from a second working fluid stream in one of a first fan bypass duct and a second fan bypass duct in fluid communication with a fan of the gas turbine engine;
- and
- a cooling medium outlet for said heat exchanger structured to discharge the cooling medium to a third working fluid stream in the other of a first fan bypass duct and a second fan bypass duct in fluid communication with another fan of the gas turbine engine,
- wherein said cooling system is structured to transfer heat from the air of the first working fluid stream to the cooling medium and discharge the cooling medium into the third working fluid stream.
A cooling system for use with a gas turbine engine, comprising:
- a heat exchanger structured to remove heat from an object of cooling;
- a heat exchanger inlet in fluid communication with a first fan bypass duct in fluid communication with a fan of the gas turbine engine;
- and
- a heat exchanger outlet in fluid communication with a second fan bypass duct in fluid communication with another fan of the gas turbine engine,
- wherein said heat exchanger removes heat from the object of cooling using pressurized air received from said first fan bypass duct through said heat exchanger inlet and discharged into said second fan bypass duct through said heat exchanger outlet.
A gas turbine engine, comprising:
- a first fan;
- a second fan in fluid communication said first fan;
- a compressor system in fluid communication with at least one of said first fan and said second fan;
- a combustor in fluid communication with said compressor system and structured to receive a first working fluid stream discharged by said compressor system;
- a turbine system in fluid communication with said combustor to receive and extract power from the first working fluid stream, said turbine system being drivingly coupled to said first fan, said second fan and said compressor system;
- a first bypass duct in fluid communication with said second fan and structured to conduct a second working fluid stream;
- a second bypass duct in fluid communication with said first fan and structured to conduct a third working fluid stream;
- and
- a heat exchanger in fluid communication with the second working fluid stream and the third working fluid stream and operable to remove heat from an object of cooling using air extracted from the second working fluid stream and discharged into the third working fluid stream.
Dependencies are inferred from the claim text.