General Electric Company

William David Magnuszewski

Nicholas Ryan Overman

Rachel Yu

A fuel injector manifold for a turbine engine includes a fuel manifold ring, a plurality of fuel injectors, and a variable fuel flow system. The fuel manifold flowpath within the fuel manifold ring, the fuel manifold flowpath receiving fuel therein. The plurality of fuel injectors in fluid communication with the fuel manifold flowpath, each of the plurality of fuel injectors having one or more fuel injector flowpaths. The variable fuel flow system disposed within the fuel manifold flowpath, the variable fuel flow system including a closed state, a partially opened state, and a fully opened state to vary a flow of the fuel from the fuel manifold flowpath to the one or more fuel injector flowpaths of each of the plurality of fuel injectors.

Fuel injector manifold having a variable fuel flow system for a turbine engine

A gas turbine engine including a compressor section for compressing air flowing therethrough to provide a compressed air flow and a reverse flow annular vortex combustor including a combustion chamber having a primary combustion zone, the combustion chamber configured to combust a mixture of a fuel flow and the compressed air flow in the primary combustion zone to generate a primary zone vortex. The reverse flow annular vortex combustor has a combustor liner and one or more driver openings extending through the combustor liner, the one or more driver openings providing a driver air flow formed of the compressed air flow. The driver air flow enters the combustion chamber as a wall of air for shaping and driving the primary zone vortex in the combustion chamber.

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Cincinnati, OH, United States of America

William David Magnuszewski