Abstract: A combustor includes combustion liner that defines a combustion chamber that extends from a forward end to an aft end. The combustor further includes a fuel nozzle. The combustor further includes a first air injection apparatus that is disposed at a first air injection stage and that is fluidly coupled to an air supply. The first air injection apparatus includes a bluff body that has a side wall and a downstream plate. The first air injection apparatus is configured to introduce air at a downstream end into the combustion chamber at the first air injection stage. The combustor further includes a second air injection apparatus that is disposed at a second air injection stage and that is fluidly coupled to the air supply. The second air injection stage is positioned downstream of the fuel nozzle and the first air injection stage.

Abstract: Combustors and methods of operation are provided. The combustor includes a combustion liner that defines a combustion chamber and that extends along an axial centerline from a forward end to an aft end. The combustor further includes a center fuel nozzle that extends along the axial centerline at least partially within the combustion chamber. The combustor further includes a plurality of outer fuel nozzles that surround the center fuel nozzle. The plurality of outer fuel nozzles terminates at the forward end. A venturi injector is positioned in the combustor within the combustion chamber downstream of the center fuel nozzle. The combustor further includes an injector that is coupled to the combustion liner and downstream of the venturi injector.

Abstract: A combustor includes a combustion liner that extends along an axial centerline from a forward end to an aft end. The combustion liner defines a combustion chamber. The combustor includes a center fuel nozzle that extends along the axial centerline at least partially within the combustion chamber. The combustor further includes a plurality of outer fuel nozzles that surround the center fuel nozzle. The plurality of outer fuel nozzles terminate at the forward end. The combustor further includes a vortex generating element that is configured to induce a recirculation zone for the stabilization of a flame. The combustor further includes a fuel injector that is coupled to the combustion liner at least partially downstream of center fuel nozzle. The combustor further includes an air injector that is coupled to the combustion liner downstream of the fuel injector.

Abstract: Gas turbine systems and methods of operation are provided. The gas turbine system includes a combustion section having at least one combustor and an ammonia supply system. The method includes generating flash-atomizing ammonia. The flash-atomizing ammonia is generated by pressurizing ammonia from the ammonia supply system to an injection pressure that is greater than a combustion chamber pressure within the combustor. The flash-atomizing ammonia is further generated by heating the ammonia to an injection temperature greater than a boiling temperature of ammonia at the combustion chamber pressure. The method further includes providing the flash-atomizing ammonia to the combustor.

Abstract: A fuel injector is provided and includes a first tube, having first and second opposing ends, which is supplied with fuel, and one or more second tubes disposed within the first tube, each of the one or more second tubes being supplied with air and having sidewalls defining injection holes through which the fuel enters the one or more second tubes to mix with the air, and an outlet end of the sidewalls corresponding to the second end of the first tube.

Abstract: A method for reducing the amount of carbon monoxide and oxygen emissions in an oxyfuel hydrocarbon combustion system, comprising the steps of feeding defined amounts of hydrocarbon fuel and an oxidizer (e.g., air) to one or more combustors in the engine and igniting the mixture to form a first combustor exhaust stream; determining the amount of carbon monoxide present at the head end of a combustor in the initial combustor exhaust stream; identifying one or more target locations within the combustor at a point downstream from the first exhaust stream for injecting free hydrogen and a supplemental oxidizer; injecting hydrogen and the supplemental oxidizer into the combustor at specified downstream locations based on the amount of detected carbon monoxide; and injecting a diluent (e.g., CO2) into the combustor at a point further downstream in the combustor exhaust to control the exhaust temperature.

Abstract: A fuel injector is provided and includes a first tube, having first and second opposing ends, which is supplied with fuel, and one or more second tubes disposed within the first tube, each of the one or more second tubes being supplied with air and having sidewalls defining injection holes through which the fuel enters the one or more second tubes to mix with the air, and an outlet end of the sidewalls corresponding to the second end of the first tube.