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US 10,760,492 B2Granted
Cooling air architecture for compact size and performance improvement
AssigneeRaytheon Technologies Corporation
InventorsJohn W. Golan, Frederick M. Schwarz
Life of this patent
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Abstract
A gas turbine engine has a fan and a compressor section with a first lower pressure location and a second higher pressure location. A heat exchanger and a higher pressure tap from the second higher pressure location pass through the heat exchanger. Air in the higher pressure tap is cooled by air from a lower pressure tap from the first lower pressure location. A valve controls flow to the heat exchanger from the lower pressure tap, the valve being controlled to limit flow from the lower pressure tap under certain conditions.
Claims17
A gas turbine engine comprising:
- a fan, a turbine section, and a compressor section said compressor section having a first lower pressure location and a second higher pressure location;
- and
- a heat exchanger and a higher pressure tap from said second higher pressure location passing through said heat exchanger, and air in said higher pressure tap being cooled by air from a lower pressure tap from said first lower pressure location, and a valve controlling flow to said heat exchanger from said lower pressure tap, said valve being controlled to limit flow from said lower pressure tap, said valve is moved to limit the flow of air from said lower pressure tap when the engine is operating at an idle condition;
- wherein air from said higher pressure tap being maintained separate from air from said lower pressure tap across said heat exchanger;
- and
- wherein said air from said higher pressure tap being delivered to said turbine section downstream of said heat exchanger.
3 more elements
Dependencies are inferred from the claim text.