Flexible support structure for a geared architecture gas turbine engine

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United States of America Patent

PATENT NO 9239012
SERIAL NO

14604811

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Abstract

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A gas turbine engine includes a fan shaft and a support which supports the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.

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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
Husband, Jason South Glastonbury, US 81 1010
McCune, Michael E Colchester, US 268 6476

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