General Electric Company

Chunyang Wu

Jonathan Dwight Berry

Baifang Zuo

Almaz Kamilevich Valeev

Michael John Hughes

Jason Thurman Stewart

Willy Steve Ziminsky

Kevin Weston McMahan

Christian Xavier Stevenson

Abdul Rafey Khan

Jong Ho Uhm

Derrick Walter Simons

Roy M Washam

Leonid Borisovich Zvedenuk

Kevin Weston Mcmahan

Almaz Valeev

A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture.

Premixing apparatus for gas turbine system

The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.

Combustor with a lean pre-nozzle fuel injection system

A combustor for a gas turbine engine includes a plurality of primary nozzles configured to diffuse or premix fuel into an air flow through the combustor; and a secondary nozzle configured to premix fuel with the air flow. Each premixing nozzle includes a center body, at least one vane, a burner tube provided around the center body, at least two cooling passages, a fuel cooling passage to cool surfaces of the center body and the at least one vane, and an air cooling passage to cool a wall of the burner tube. The cooling passages prevent the walls of the center body, the vane(s), and the burner tube from overheating during flame holding events.

Flame tolerant secondary fuel nozzle

A turbomachine includes a compressor section, a combustor operatively connected to the compressor section, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a plurality of mixing tube elements. Each of the plurality of mixing tube elements includes a conduit having a first fluid inlet, a second fluid inlet arranged downstream from the first fluid inlet, a discharge end arranged downstream from the first and second fluid inlets, and a vortex generator arranged between the first and second fluid inlets. The vortex generator is configured and disposed to create multiple vortices within the conduit to mix first and second fluids passing through each of the plurality of mixing tube elements.

Turbomachine including a mixing tube element having a vortex generator

A combustor includes an end cap having a perforated downstream plate and a combustion chamber downstream of the downstream plate. A plenum is in fluid communication with the downstream plate and supplies a cooling medium to the combustion chamber through the perforations in the downstream plate. A method for cooling a combustor includes flowing a cooling medium into a combustor end cap and impinging the cooling medium on a downstream plate in the combustor end cap. The method further includes flowing the cooling medium into a combustion chamber through perforations in the downstream plate.

Apparatus and method for cooling a combustor cap

A combustor includes an end cap that extends radially across a portion of the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap. Premixer tubes extend from a premixer tube inlet proximate to the upstream surface through the downstream surface to provide fluid communication through the end cap and include means for conditioning flow through the plurality of premixer tubes. A method for conditioning flow through a combustor includes flowing a working fluid through a first and second set of premixer tubes that extend axially through an end cap, wherein the second set of premixer tubes includes means for conditioning flow through the second set of premixer tubes, and flowing a fuel through the first or second set of premixer tubes.

Combustor and method for conditioning flow through a combustor

A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.

Annular ring-manifold quaternary fuel distributor

A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

Growing community of inventors

Greer, SC, United States of America

Chunyang Wu