Abstract: A fuel injector having an injector body, a mixing circuit, and at least one injector is provided. The injector body has a plurality of manifolds, an inlet, and an outlet. The manifolds are configured for receiving fuel, and the inlet is configured for receiving air. The mixing circuit is positioned within the injector body. The mixing circuit is configured for receiving fuel from at least one of the manifolds, and air from the inlet to create an air-fuel mixture that exits the outlet. The least one fuel injector is positioned radially outwardly from the mixing circuit. The at least one injector receives fuel from at least one of the plurality of manifolds and injects fuel to the outlet.

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: 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: Disclosed herein are apparatuses, methods, and systems for transition piece contouring. In an embodiment, a high thermal stress section of a transition piece and a low thermal stress section of a transition piece is a determined The low thermal stress section of the transition piece may be contoured to intercept hot gas flow.

Abstract: A system for supporting fuel nozzles inside a combustor includes a ring that circumferentially surrounds the fuel nozzles inside the combustor, a support plate that extends radially inside at least a portion of the ring, and a first connection between the support plate and at least one of the fuel nozzles inside the combustor. A second connection is between the support plate and the ring. A method for supporting fuel nozzles in a combustor includes surrounding the fuel nozzles with a ring, connecting a support plate to the ring, and connecting the support plate to at least one fuel nozzle.

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.

Abstract: A system for supplying a working fluid to a combustor includes a combustion chamber and a flow sleeve that circumferentially surrounds at least a portion of the combustion chamber. A tube provides fluid communication for the working fluid to flow through the flow sleeve and into the combustion chamber, wherein the tube comprises an axial centerline. A first set of injectors are circumferentially arranged around the tube and angled radially with respect to the axial centerline of the tube, wherein the first set of injectors provide fluid communication for the working fluid to flow through a wall of the tube.

Abstract: A system for supplying a working fluid 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 the working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube spirals between the flow sleeve and the liner.

Abstract: A combustor includes a combustion chamber and a casing that circumferentially surrounds the combustion chamber to at least partially define an annular passage between the casing and the combustion chamber. A fuel plenum extends radially through the casing to provide fluid communication through the casing to the annular passage, and a liner extends inside at least a portion of the fuel plenum to prevent fuel from directly impinging upon at least a portion of the fuel plenum. A method of reducing thermal stresses in a combustor includes flowing a fuel inside a fuel plenum that extends radially through a casing, shielding at least a portion of the fuel plenum from direct impingement by the fuel radially inward of the casing, and flowing the fuel from the fuel plenum into an annular passage between the casing and a combustion chamber.

Abstract: A secondary fuel nozzle for a turbine includes a passive purge air passageway which provides purge air to the secondary nozzle at all times that the nozzle is in operation. The passive purge air passageway draws in air from a location adjacent an upstream end of the nozzle. Because of a pressure differential between air located at the downstream end of the nozzle and air located at the upstream end of the nozzle, purge air will run through the passive purge air passageway at all times the nozzle is in operation. There is no need for a supply of compressed purge air.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and fuel injectors provide fluid communication to the combustion chamber. A distribution manifold circumferentially surrounds the fuel injectors and defines an annular plenum. A fluid passage through the distribution manifold provides fluid communication through the distribution manifold. A radial cross-sectional area of the annular plenum varies around the flow sleeve. 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 a distribution manifold that circumferentially surrounds fuel injectors circumferentially arranged around the combustion chamber, and changing at least one of a pressure or flow rate of the diverted portion of the working fluid.

Abstract: According to one aspect of the invention, a fuel nozzle assembly for a turbine includes an outer conduit of a fuel nozzle and a cap assembly to receive at least a portion of the fuel nozzle. The assembly also includes a spring disposed about the outer conduit and within an annular recess of the cap assembly, wherein the spring provides frictional damping to resist movement of the fuel nozzle.

Abstract: A combustor includes first and second annular casings with a joint between the first and second annular casings. A flow sleeve surrounds a combustion chamber to define an annular passage, and an annular shield inside the first annular casing extends downstream from the joint and prevents a working fluid flowing through the annular passage from contacting at least a portion of the first annular casing. A method for reducing thermal stresses in a combustor includes flowing a working fluid from a compressor through an annular passage between a combustion chamber and a flow sleeve inside the combustor, shielding the working fluid flowing through the annular passage from contact with at least a portion of a joint between first and second annular casings, and shielding the working fluid flowing through the annular passage from contact with at least a portion of the first annular casing downstream from the joint.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber, and fuel injectors circumferentially arranged around the combustion chamber. A combustor casing surrounds the combustion chamber. A distribution manifold encloses the fuel injectors, and a plenum passes through the combustor casing. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber, diverting a portion of the working fluid into a plenum, and flowing the diverted portion of the working fluid outside of the compressor and the combustor. The method further includes flowing the diverted portion of the working fluid through a combustor casing and through a distribution manifold that encloses fuel injectors circumferentially arranged around the combustion chamber.

Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle. A flow sleeve circumferentially surrounds the combustion chamber, and a plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the distribution manifold provides fluid communication through the distribution manifold to the plurality of fuel injectors. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber and diverting a portion of the working fluid through a distribution manifold that circumferentially surrounds a plurality of fuel injectors circumferentially arranged around the combustion chamber.

Abstract: A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.

Abstract: A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.

Abstract: According to one aspect of the invention, a gas turbine engine includes a combustor, a fuel nozzle placed in an end of the combustor, and a passage configured to receive an air flow from a compressor discharge casing, wherein the passage directs the air flow into a chamber downstream of the nozzle, wherein a chamber pressure is lower than a compressor discharge casing pressure. The gas turbine engine also includes a flow control device configured to control the air flow from the compressor discharge casing into the passage.

Abstract: A combustor includes a casing that encloses at least a portion of the combustor. A fuel conduit extends downstream from the casing and includes a tortuous path for fuel flow inside the fuel conduit. A method for supplying fuel to a combustor includes flowing a working fluid through tubes that extend axially through an end cap. The method further includes supplying a fuel through a fuel conduit into the end cap, supplying a diluent through a diluent conduit that extends axially inside the fuel conduit, and swirling the fuel flowing through the fuel conduit around the diluent flowing through the diluent conduit.