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US 8,127,547 B2Granted
Gas turbine engine with air and fuel cooling system
AssigneeUnited Technologies Corporation
InventorsJames W. Norris, Andrew P. Berryann
Life of this patent
Estimating the term…
Abstract
A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger.
Claims11
A system for cooling air in a gas turbine engine comprising:
- a first heat exchanger in contact with cooling air delivered to a turbine section in a gas turbine engine;
- a second heat exchanger positioned around a fuel nozzle adjacent to a combustion section in the gas turbine engine, and the second heat exchanger positioned in contact with fuel being delivered into the combustion section by the fuel nozzle;
- and
- an intermediate fluid for transferring heat from the first heat exchanger to the second heat exchanger, said intermediate fluid being provided by a heat pipe.
1 more element
A gas turbine engine comprising:
- a compression section;
- a combustion section;
- a turbine section;
- and said combustion section including a fuel supply for delivering fuel into the combustion section;
- a first heat exchanger in contact with cooling air to be delivered to the turbine section in a gas turbine engine;
- a second heat exchanger positioned around a fuel nozzle adjacent the fuel supply system, and the second heat exchanger positioned in contact with fuel being delivered into the combustion section by the fuel nozzle;
- and
- an intermediate fluid for transferring heat from the first heat exchanger to the second heat exchanger.
5 more elements
Dependencies are inferred from the claim text.