FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE

Number of patents in Portfolio can not be more than 2000

United States of America

APP PUB NO 20200025032A1
SERIAL NO

16298319

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Husband, Jason South Glastonbury, US 59 157
McCune, Michael E Colchester, US 205 2443

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