Auxiliary device for three air flow path gas turbine engine

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United States of America Patent

PATENT NO 10400709
APP PUB NO 20150267551A1
SERIAL NO

14458619

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Abstract

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A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.

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Patent Owner(s)

Patent OwnerAddress
RTX CORPORATION10 FARM SPRINGS ROAD FARMINGTON CT 06032

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Roberge, Gary D Tolland, US 140 1355

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