Shroud for a gas turbine engine

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 11994039
APP PUB NO 20220356815A1
SERIAL NO

17711405

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Abstract

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A gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end.

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Patent Owner(s)

Patent OwnerAddress
GENERAL ELECTRIC COMPANY1 RIVER ROAD SCHENECTADY NY 12345

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Craig,, III Charles William West Chester, US 11 91
Gallier, Kirk Douglas Cincinnati, US 43 160

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