Solar Turbines Inc.

Gareth W Oskam

John Frederick Lockyer

Rajeshriben Patel

Nathan J Kirksey

Douglas C Rawlins

Georgina J McGee

Gregory Michael Balow

Yonduck Sung

Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer is disclosed that utilizes an air nozzle, in combination with one or more fuel jets, to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.

Micromix fuel injection air nozzles

A fuel injector for a gas turbine engine may include an injector housing having a central cavity configured to be fluidly coupled to a combustor of the turbine engine. The central cavity may also be configured to direct a first fuel into the combustor substantially unmixed with air. The fuel injector may also include an annular air discharge outlet circumferentially disposed about the downstream end of the central cavity. The air discharge outlet may be configured to discharge compressed air into the combustor circumferentially about the first fuel from the central cavity. The fuel injector may also include an annular fuel discharge outlet circumferentially disposed about the air discharge outlet at the downstream end. The fuel discharge outlet may be configured to discharge a second fuel into the combustor circumferentially about the compressed air from the air discharge outlet.

Gas turbine and fuel injector for the same

A method of operating a gas turbine engine includes directing a stream of liquid fuel to the combustor through a nozzle of a dual fuel injector. The method may also include directing a first quantity of compressed air to the stream of liquid fuel proximate the nozzle, and directing a second quantity of compressed air to the stream of liquid fuel downstream of the nozzle. The second quantity of compressed air may be larger than the first quantity of compressed air. The method may further include delivering the compressed air and the stream of liquid fuel to the combustor in a substantially unmixed manner.

Method of operating a gas turbine engine

A dual fuel injector for a gas turbine engine includes a central cavity extending along a longitudinal axis from a first end to a second end, and a first fuel discharge outlet configured to direct a first fuel into the central cavity at the first end. The fuel injector may also include a first air discharge opening circumferentially disposed about the first fuel discharge outlet and configured to direct a first quantity of air into the central cavity, and a second air discharge opening circumferentially disposed about the central cavity and configured to discharge a second quantity of air into the central cavity downstream of the first air discharge outlet. The fuel injector may further include a second fuel discharge outlet circumferentially disposed about the central cavity and configured to discharge a second fuel therethrough. The second fuel may be different from the first fuel.

Lean direct fuel injector

A dual fuel injector includes an apparatus for injecting liquid pilot fuel into a gas turbine engine. The injector includes a liquid pilot fuel feedline having an outlet that sprays fuel on the conically-shaped pintle swirler that causes the fuel to form a cylindrically-shaped film on the interior of a pilot fuel-air mixing passage. The film of fuel is broken up into droplets at a downstream end of the pilot fuel-air mixing passage by shearing forces exerted on the film by separate streams of air flowing within and externally of the pilot fuel-air mixing passage.

Liquid pilot fuel injection method and apparatus for a gas turbine

A dual fuel injector for injecting liquid and/or gaseous fuel into a gas turbine engine includes a plurality of hollow spoke members for injecting gaseous fuel that are located upstream of a plurality of main air swirling vanes that are in turn upstream of a plurality of air-blast atomizers for injecting main liquid fuel. A pilot fueling arrangement is provided that is capable of starting the gas turbine engine using either gaseous or liquid fuel. The injector includes a labyrinth-shaped cooling passage capable of providing cooling air to cylindrical walls of an injector centerbody.

Growing community of inventors

San Diego, CA, United States of America

Gareth W Oskam