Abstract: A system includes a fuel control system configured to control a fuel flow to one or more combustors and an oxidant control system configured to control an oxidant flow to each combustor of the one or more combustors, wherein the oxidant flow is configured to at least partially react with the fuel flow within the one or more combustors to form an exhaust gas flow. The system also includes an exhaust gas system configured to direct a recirculation flow of the exhaust gas flow to each combustor of the one or more combustors; and a controller coupled to the fuel control system, the oxidant control system, and the exhaust gas system. The controller is configured to independently control a fuel-to-oxidant ratio and an exhaust gas-to-oxidant ratio. The FOR is the fuel flow divided by the oxidant flow, and the EGOR is the recirculation flow divided by the oxidant flow.

Abstract: A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.

Abstract: A gas turbomachine includes a compressor portion, a turbine portion operatively connected to the compressor portion, and a combustor assembly fluidically connected to the turbine portion. The combustor assembly includes at least one nozzle including at least one fuel gas injector portion and at least one water injector portion. A fuel system is fluidically connected to the at least one nozzle. The fuel system includes at least one fuel gas manifold, a water injector purge manifold and a water injector manifold. The at least one fuel gas manifold is selectively fluidically connectable to the water injector portion of the nozzle through the water injector purge manifold.

Abstract: A system includes a fuel control system configured to control a fuel flow to one or more combustors and an oxidant control system configured to control an oxidant flow to each combustor of the one or more combustors, wherein the oxidant flow is configured to at least partially react with the fuel flow within the one or more combustors to form an exhaust gas flow. The system also includes an exhaust gas system configured to direct a recirculation flow of the exhaust gas flow to each combustor of the one or more combustors; and a controller coupled to the fuel control system, the oxidant control system, and the exhaust gas system. The controller is configured to independently control a fuel-to-oxidant ratio and an exhaust gas-to-oxidant ratio. The FOR is the fuel flow divided by the oxidant flow, and the EGOR is the recirculation flow divided by the oxidant flow.

Abstract: A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one through baffle hole. At least one diluent shroud is affixed to the at least one baffle plate and is configured to guide a diluent flow toward a mixing chamber of the at least one fuel nozzle. Further disclosed is a method for introducing a diluent flow into a mixing chamber of a fuel nozzle including urging the diluent flow from a plenum through a baffle plate gap between a baffle plate and an outer surface of the fuel nozzle. The diluent flow is directed via at least one diluent shroud extending from the baffle plate toward a plurality of air swirler holes extending through a fuel nozzle tip. The diluent flow is flowed through the plurality of air swirler holes into the mixing chamber.

Abstract: Methods and apparatus for a mounting assembly for a liner of a gas turbine engine combustor are provided. The combustor includes a combustor liner and a radially outer annular flow sleeve. The mounting assembly includes an inner ring surrounding a radially outer surface of the liner and including a plurality of axially extending fingers. The mounting assembly also includes a radially outer ring coupled to the inner ring through a plurality of spacers that extend radially from a radially outer surface of the inner ring to the outer ring.

Abstract: A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The method also includes coupling a transition piece to the liner second end. The transition piece includes an outer wall. The method further includes coupling a plurality of lean-direct injectors along at least one of the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the wall.

Abstract: A method for assembling a gas turbine engine includes providing at least one combustor assembly defining a combustion chamber. At least one fuel nozzle is positioned at a forward end of the combustion chamber. The at least one fuel nozzle is configured to inject a premixed fuel/air mixture into the combustion chamber. A catalytic material is applied to at least a portion of the at least one fuel nozzle.

Abstract: A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow communication with the chamber and is configured to inject a first fluid stream. The assembly further includes at least one second fluid passage defining at least one second fluid inlet within the wall. The second fluid inlet is adjacent to the first fluid inlet and is coupled in flow communication with the chamber. The method also includes injecting the first fluid stream and injecting the second fluid stream into the chamber at an oblique angle with respect to the first fluid stream, thereby intersecting and mixing the second fluid stream with the first fluid stream.

Abstract: A combustor has a flow sleeve and a flow liner defining a generally axial flow direction of compressor discharge air toward combustor burners. A casing is secured to the forward end of the flow sleeve defining an annular plenum along the interior of the flow sleeve. Openings through the flow sleeve supply compressor discharge air into the plenum where the air changes direction for flow through apertures into and generally coaxially with the free air stream. The axial injection minimizes or eliminates energy losses due to cross flow injection within the axial air stream while continuing to cool the liner.

Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one through baffle hole. At least one diluent shroud is affixed to the at least one baffle plate and is configured to guide a diluent flow toward a mixing chamber of the at least one fuel nozzle. Further disclosed is a method for introducing a diluent flow into a mixing chamber of a fuel nozzle including urging the diluent flow from a plenum through a baffle plate gap between a baffle plate and an outer surface of the fuel nozzle. The diluent flow is directed via at least one diluent shroud extending from the baffle plate toward a plurality of air swirler holes extending through a fuel nozzle tip. The diluent flow is flowed through the plurality of air swirler holes into the mixing chamber.

Abstract: A method for assembling a gas turbine engine includes providing at least one combustor assembly defining a combustion chamber. At least one fuel nozzle is positioned at a forward end of the combustion chamber. The at least one fuel nozzle is configured to inject a premixed fuel/air mixture into the combustion chamber. A catalytic material is applied to at least a portion of the at least one fuel nozzle.

Abstract: A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix composite material, a forward end of the combustor liner provided with a plurality of circumferentially arranged bolt holes. An inner metal ring is located about an outside surface of the forward end of the combustor liner, the inner metal ring provided with a second plurality of circumferentially spaced bolt holes, with a plurality of bolts extending through the first and second pluralities of bolt holes and secured by self-locking nuts. An outer metal ring is spaced radially outwardly of the inner metal ring, with a plurality of circumferentially spaced struts extending between the inner and outer rings.

Abstract: A gas turbine combustor. The gas turbine combustor may include a central combustion nozzle with a catalyst therein and a number of outer combustion nozzles surrounding the central combustion nozzle.

Abstract: A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The method also includes coupling a transition piece to the liner second end. The transition piece includes an outer wall. The method further includes coupling a plurality of lean-direct injectors along at least one of the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the wall.

Abstract: A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow communication with the chamber and is configured to inject a first fluid stream. The assembly further includes at least one second fluid passage defining at least one second fluid inlet within the wall. The second fluid inlet is adjacent to the first fluid inlet and is coupled in flow communication with the chamber. The method also includes injecting the first fluid stream and injecting the second fluid stream into the chamber at an oblique angle with respect to the first fluid stream, thereby intersecting and mixing the second fluid stream with the first fluid stream.

Abstract: Methods and apparatus for a mounting assembly for a liner of a gas turbine engine combustor are provided. The combustor includes a combustor liner and a radially outer annular flow sleeve. The mounting assembly includes an inner ring surrounding a radially outer surface of the liner and including a plurality of axially extending fingers. The mounting assembly also includes a radially outer ring coupled to the inner ring through a plurality of spacers that extend radially from a radially outer surface of the inner ring to the outer ring.