General Electric Company

Steven Joseph Lohmueller

Alfred Albert Mancini

Hukam Chand Mongia

James Neil Cooper

Beverly Stephenson Duncan

Allen Michael Danis

Duane Douglas Thomsen

Michael Louis Vermeersch

Marie Ann McMasters

Eric John Stevens

Michael Anthony Benjamin

Robert Paul Czachor

David Louis Burrus

Harjit Singh Hura

Paul Edward Sabla

Randall Charles Boehm

Marie Ann Mcmasters

A trapped vortex combustor for use in a gas turbine engine includes an outer vortex chamber wall and a dome attached to, or formed integrally with, the outer vortex chamber wall. The dome, the outer vortex chamber wall, or both define at least in part an outer trapped vortex chamber and a channel. The channel extends along the circumferential direction at a forward end of the outer vortex chamber wall, the channel configured to receive an airflow through or around the outer vortex chamber wall, the dome, or both and provide such airflow as a continuous annular airflow to the inner surface of the outer vortex chamber wall. The dome further defines a fuel nozzle opening, with all openings in the dome outward of the fuel nozzle opening along the radial direction, excepting any effusion cooling holes having a diameter less than about 0.035 inches, being in airflow communication with the channel.

Trapped vortex combustor for a gas turbine engine with a driver airflow channel

A fuel distributor is disclosed comprising a body having a unitary construction, a fuel conduit located within the body, a fuel flow path located within the body that is oriented in a circumferential direction around an axis and in flow communication with the fuel conduit, and at least one orifice located in the body in flow communication with the fuel flow path such that a fuel entering the fuel conduit exits through the orifice.

Fuel nozzle

A fuel nozzle for a gas turbine engine is disclosed, the fuel nozzle comprising at least one unitary component made using a rapid manufacturing process. In one aspect, the rapid manufacturing process is a laser sintering process. Unitary components disclosed include a conduit, swirler, distributor, venturi and a centerbody.

In a gas turbine engine combustor and method for delivering purge gas thereto, a ferrule is generally coupled to the housing and moveable relative thereto. The ferrule has a primary opening through which a combustor component extends into a combustion chamber of the combustor. The ferrule further has a plurality of purge gas openings separate from and in transversely spaced relationship with the primary opening to allow purge gas to flow through the ferrule. In a first position of the ferrule at least one purge gas opening is blocked against the flow of purge gas therethrough and at least one other purge gas opening is unblocked against purge gas flow. In a second position of the ferrule at least one of the blocked purge gas openings of the first ferrule position is unblocked to permit the flow of purge gas therethrough.

Gas turbine engine combustor and method for delivering purge gas into a combustion chamber of the combustor

A method for assembling a gas turbine engine is provided. The method includes providing a combustor having a combustor liner assembly defining a combustion chamber. An outer combustor liner includes a radially extending first end that defines a combustion chamber input opening. An axially extending second end of the outer combustor liner defines a combustion chamber output opening. The first end transitions into the second end to form an arcuate cross-sectional shape of the outer combustor liner. A dome assembly is coupled to the first end of the combustor liner that extends downstream from the dome assembly. A fuel nozzle is positioned within a cyclone formed on the dome assembly and configured in a radial configuration.

Method and apparatus for assembling gas turbine engine

A method for assembling a gas turbine engine includes coupling an axisymmetric structure within the gas turbine engine, wherein the axisymmetric structure includes at least one mounting bushing extending from a radially outer surface of the axisymmetric structure, and inserting a pin having a crowned surface at least partially into the mounting bushing such that the pin provides both axial and tangential support to the axisymmetric structure, and securing the pin to the gas turbine engine utilizing a retaining assembly.

Methods and apparatuses for assembling a gas turbine engine

A method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

Method and apparatus to decrease combustor emissions

A fuel injector includes an annular main fuel nozzle received within an annular nozzle housing, a main nozzle fuel circuit having at least one annular leg, and a pilot nozzle fuel circuit. Spray orifices of the leg extend through the fuel nozzle and spray wells through the housing are aligned with the orifices. The nozzle is designed to generate sufficient static pressure differentials between at least two different ones of the spray wells to purge the main nozzle fuel circuit. Spray well portions may be asymmetrically flared out with respect to a spray well centerline in different local streamwise directions. Some of the spray well portions may be asymmetrically flared out in a local upstream direction and others in a local downstream direction. The local streamwise direction may have an axial component parallel to a nozzle axis about which the annular nozzle housing is circumscribed and a circumferential component around the nozzle housing.

Differential pressure induced purging fuel injectors

A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.

Growing community of inventors

Reading, OH, United States of America

Steven Joseph Lohmueller