Gas turbine engines with heat recovery systems

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 11867121
APP PUB NO 20220307418A1
SERIAL NO

17211345

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ATTORNEY / AGENT: (SPONSORED)

Importance

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Abstract

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A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway extending at least partially radially therethrough through which a fluid coolant flows and another of the multiple guide vanes includes a heated fluid passageway extending at least partially radially therethrough through which the fluid coolant flows and receives heat from exhaust airflow from the core airflow path.

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Patent Owner(s)

Patent OwnerAddress
GENERAL ELECTRIC COMPANY1 RIVER ROAD SCHENECTADY NY 12345

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Sharma, Ashish Garching, DE 109 1627
Simonetti, Michael West Chester, US 9 24
Vitt, Paul Hadley Evendale, US 33 240

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