Abstract: A control system for use with a turbine engine that is configured to operate at a rated power output is provided. The control system includes a computing device that includes a processor that is programmed to calculate an amount of fluid to be supplied for combustion in the turbine engine. The processor is also programmed to designate at least one nozzle of a plurality of nozzles to receive the fluid. Moreover, the control system includes at least one control valve coupled to the computing device. The control valve is configured to receive at least one control parameter from the computing device for use in modulating the amount of the fluid to be channeled to the nozzle such that the rated power output is generated while emission levels are maintained below a predefined emissions threshold level.

Abstract: A method is disclosed for controlling gas turbine operation in response to lean blowout of a combustion can. The gas turbine comprises a pair of combustion cans. The method includes sensing that a first combustion can is extinguished during a full load operation of the gas turbine, adjusting a fuel ratio between the fuel nozzles in each can, delivering a richer fuel mixture to the fuel nozzles nearest to the cross-fire tubes, generating a cross-fire from the second combustion can to the first combustion can, detecting a recovery of the turbine load, and adjusting the fuel ratio to the normal balanced fuel distribution between the fuel nozzles in each can.

Abstract: A fuel nozzle includes a fuel plenum, an outer body surrounding the fuel plenum, and bore holes that extend longitudinally through the outer body. The fuel nozzle also includes means for fixedly attaching the fuel plenum to the outer body and passages that provide fluid communication between the fuel plenum and the bore holes. A method for manufacturing a fuel nozzle includes drilling bore holes longitudinally through an outer body and drilling passages in the outer body to the bore holes. The method further includes inserting a fuel plenum into the outer body, wherein the passages provide a fluid communication between the bore holes and the fuel plenum, and attaching the fuel plenum to the outer body.

Abstract: A gas turbine engine having a combustor that includes: an inner radial wall defining a first interior chamber and a second interior chamber, wherein the first interior chamber extends axially from an end cover to a primary fuel injector, and the second interior chamber extends axially from the primary fuel injector to the turbine; an outer radial wall formed about the inner radial wall so that a flow annulus is formed therebetween; upstream fuel nozzles jutting into the flow annulus from the outer radial wall. The upstream fuel nozzles may include non-uniform circumferential spacing about the inner radial wall.

Abstract: A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.

Abstract: A system includes a fuel nozzle. The fuel nozzle includes a central hub with a first annular passage extending along a longitudinal axis of the fuel nozzle. A flow conditioner is disposed along the first annular passage. The flow conditioner includes at least one of a straightening vane, a mesh screen, or a multi-passage body having multiple passages generally parallel with the longitudinal axis. An outer shroud is disposed about the central hub to define a second annular passage extending along the longitudinal axis of the fuel nozzle.

Abstract: A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber.

Abstract: A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.

Abstract: A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes.

Abstract: A late lean injection (LLI) manifold is provided and includes a central nozzle and first and second side nozzles positioned at circumferential locations defined around a vessel, a connector, a first leg, to which the connector is connected, formed to define a tube extending from the central nozzle to the first side nozzle such that fuel is communicable between the connector, the central nozzle and the first side nozzle and a second leg. The second leg is formed to define a tube extending from the central nozzle to the second side nozzle such that the fuel is communicable between the central nozzle and the second side nozzle.

Abstract: A turbomachine with a trapped vortex feature includes a unibody liner formed to define a flow path for combustion products, the unibody liner including first and second portions defining first radial planes, a third portion defining a second radial plane and fourth and fifth portions extending substantially radially between proximal ends of the first and third portions and proximal ends of the second and third portions, respectively, and an injector configured to deliver a fuel or a fuel/air mixture to a space partially bound by the third, fourth and fifth portions.

Abstract: A system includes a turbine combustor, which includes a first wall disposed about a combustion chamber, a second wall disposed about the first wall, and a third wall disposed about the second wall. The third wall is configured to combine an exhaust gas with an oxidant and the combustion chamber is configured to combust a mixture of a fuel, the oxidant, and the exhaust gas.

Abstract: A combustor includes a first shroud extending circumferentially inside the combustor and at least partially defining an inlet passage. A second shroud extends circumferentially inside the combustor. The second shroud defines an outlet passage. A first plate extends radially inside the second shroud downstream from the inlet passage of the first shroud and upstream from the outlet passage of the second shroud. The first plate generally defines an inlet port and an outlet port. A second plate extends radially around the first plate downstream from the inlet port and upstream from the outlet port of the first plate. A first fluid flow path extends from the inlet passage to the inlet port. A second fluid flow path extends from the outlet port to the outlet passage. A baffle extends from the first shroud to the first plate. The baffle separates the first and second fluid flow paths.

Abstract: A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.

Abstract: A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes.

Abstract: A system for supplying fuel to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for a working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube includes a tube wall. A plurality of fuel ports through the tube wall provide fluid communication for fuel to flow through the tube wall and into the tube, and the fuel ports are non-circular.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. Injectors circumferentially arranged around the flow sleeve provide fluid communication through the flow sleeve and into the combustion chamber. A valve upstream from the injectors has a first position that permits working fluid flow to the injectors and a second position that prevents working fluid flow to the injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid through a combustion chamber, diverting a portion of the working fluid through injectors circumferentially arranged around the combustion chamber, and operating a valve upstream from the injectors to control the working fluid flow through the injectors.

Abstract: A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.

Abstract: Embodiments can provide systems and methods for detecting fuel leaks in gas turbine engines. According to one embodiment, there is disclosed a method for detecting a fuel leak in a gas turbine engine. The method may include adjusting a control valve to correspond with a desired fuel flow. The method may also include determining an actual fuel flow based at least in part on an upstream pressure in a fuel manifold and one or more gas turbine engine parameters. The method may also include comparing the desired fuel flow with the actual fuel flow. Moreover, the method may include determining a difference between the desired fuel flow and the actual fuel flow, wherein the difference indicates a fuel leak.

Abstract: A combustor includes a combustion chamber that defines a longitudinal axis. A primary reaction zone is inside the combustion chamber, and a secondary reaction zone inside the combustion chamber is downstream from the primary reaction zone. A center fuel nozzle extends axially inside the combustion chamber to the secondary reaction zone, and a plurality of fluid injectors circumferentially are arranged inside the center fuel nozzle downstream from the primary reaction zone. Each fluid injector defines an additional longitudinal axis out of the center fuel nozzle that is substantially perpendicular to the longitudinal axis of the combustion chamber.