TURBINE CLEARANCE CONTROL SYSTEM AND METHOD FOR IMPROVED VARIABLE CYCLE GAS TURBINE ENGINE FUEL BURN

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United States of America Patent

APP PUB NO 20190048796A1
SERIAL NO

16048738

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

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Patent Owner(s)

Patent OwnerAddress
RAYTHEON TECHNOLOGIES CORPORATION10 FARM SPRINGS ROAD FARMINGTON CT 06032-2568

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Carr, Scott A Manchester, US 3 18
Farris, John R Bolton, US 43 369
Griffin, David Richard Tolland, US 15 96
Hall, Theodore W Berlin, US 15 193
Hanlon, Christopher J Sturbridge, US 28 179
Ledwith,, Jr Walter A Marlborough, US 10 35
Miller, Andrew S Marlborough, US 14 50
Pimenta, David C Rocky Hill, US 8 24
Robak, Christopher W Manchester, US 9 20
White, Peter A West Hartford, US 4 56

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