Gas turbine combustor fuel nozzle assembly and combustor liner having dilution holes in arrangements

Number of patents in Portfolio can not be more than 2000

United States of America

PATENT NO 12215869
APP PUB NO 20240280265A1
SERIAL NO

18452958

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Importance

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Abstract

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A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.

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Patent Owner(s)

  • GENERAL ELECTRIC COMPANY

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Benjamin, Michael A Cincinnati, US 116 710
Patel, Nayan Vinod Liberty Township, US 2 0

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