Abstract: A system includes an end cover for a multi-tube fuel nozzle. The end cover includes a first side, a second side disposed opposite the first side, a plurality of fuel injectors disposed on the first side, and at least one pre-orifice disposed within a passage within the end cover between the first and second sides. The pre-orifice is configured to be removed through the end cover from the second side.

Abstract: A combustor includes an end cap having upstream and downstream surfaces and a cap shield surrounding the upstream and downstream surfaces. First and second sets of premixer tubes extend from the upstream surface through the downstream surface. A first fuel conduit supplies fuel to the first set of premixer tubes. A casing circumferentially surrounds the cap shield to define an annular passage, and a second fuel conduit supplies fuel through the annular passage to the second set of premixer tubes. A method for supplying fuel to a combustor includes flowing a working fluid through first and second sets of premixer tubes, flowing a first fuel into the first set of premixer tubes, and flowing a second fuel through an annular passage surrounding the end cap and into the second set of premixer tubes.

Abstract: A flow sleeve assembly for a combustor of a gas turbine includes an annular support sleeve disposed at a forward end of the flow sleeve assembly. The support sleeve includes a forward portion axially separated from an aft portion. An aft frame is disposed at an aft end of the flow sleeve assembly. An annular flow sleeve extends from the aft portion of the support sleeve towards the aft frame. The flow sleeve includes a forward end that is axially separated from an aft end. The forward end of the flow sleeve circumferentially surrounds the aft end of the support sleeve. An annular impingement sleeve extends between the aft end of the flow sleeve and the aft frame. A forward end of the impingement sleeve is connected to the aft end of the flow sleeve, and an aft end of the impingement sleeve is connected to the aft frame.

Abstract: A cap assembly for a bundled tube fuel injector includes an impingement plate and an aft plate that is disposed downstream from the impingement plate. The aft plate includes a forward side that is axially separated from an aft side. A tube passage extends through the impingement plate and the aft plate. A tube sleeve extends through the impingement plate within the tube passage towards the aft plate. The tube sleeve includes a flange at a forward end and an aft end that is axially separated from the forward end. A retention plate is positioned upstream from the impingement plate. A spring is disposed between the retention plate and the flange. The spring provides a force so as to maintain contact between at least a portion of the aft end of the tube sleeve and the forward side of the aft plate.

Abstract: A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold.

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 system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber disposed downstream from the fuel nozzle, an inner flow sleeve that circumferentially surrounds the combustion chamber and a plurality of injectors circumferentially arranged around the inner flow sleeve. The plurality of injectors provide for fluid communication through the inner flow sleeve and into the combustion chamber downstream from the fuel nozzle. The system further includes an outer air shield that defines an injection air plenum that surrounds the plurality of injectors. An inlet passage extends through the outer air shield to define a flow path into the injection air plenum. An outer sleeve is slidingly engaged with the outer air shield. The outer sleeve has a first position that restricts flow through the inlet passage and a second position that increases flow through the inlet passage.

Abstract: A system for supporting bundled tube segments within a combustor includes an annular sleeve that extends circumferentially and axially within the combustor, a support lug that extends radially inward from the annular sleeve and an annular support frame that is disposed within the annular sleeve. The annular support frame includes an inner ring portion, an outer ring portion and a plurality of spokes that extend radially between the inner and outer ring portions. The inner ring portion, the outer ring portion and the plurality of spokes define an annular array of openings for receiving a respective bundled tube segment. The inner ring portion is connected to each bundled tube segment and the outer ring portion is coupled to the support lug.

Abstract: A combustor cap assembly includes an annular shroud and an impingement plate coupled to the shroud. The impingement plate at least partially defines a plurality of impingement cooling holes and a cooling flow return passage. A cap plate is coupled to the impingement plate. The cap plate includes an impingement side which faces a second side portion of the impingement plate where the impingement side is axially spaced from the second side portion to define an impingement air plenum therebetween. The cooling flow return passage is in fluid communication with the impingement air plenum. A fluid conduit extends from a first side portion of the impingement plate towards a first end portion of the shroud. The fluid conduit is in fluid communication with the cooling flow return passage and provides for fluid communication out of the impingement air plenum.

Abstract: A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate to form an impingement air plenum therebetween. The combustor cap assembly further includes a flow conditioning plate coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion. The annular portion defines a plurality of flow conditioning passages. The inner band portion at least partially defines a cooling air plenum within the combustor cap assembly. The inner band portion defines an exhaust channel which is in fluid communication with the impingement air plenum and an exhaust outlet. The flow conditioning plate further defines a cooling air passage which provides for cooling air flow into the cooling air plenum.

Abstract: A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.

Abstract: A fuel distribution manifold for a combustor of a gas turbine includes an annular flange having an outer surface that extends circumferentially around the flange. A primary fuel plenum extends circumferentially within the flange. A first orifice and a second orifice extend radially through the outer surface of the flange to provide for fluid communication into the primary fuel plenum. The first orifice includes an inlet that is adjacent to the outer surface. The second orifice includes an inlet that is adjacent to the outer surface. A fuel distribution cap extends partially across the outer surface of the flange. The fuel distribution cap includes an inlet port. A fuel distribution plenum is at least partially defined within the fuel distribution cap. The fuel distribution plenum is in fluid communication with the inlet port and with the first orifice inlet and the second orifice inlet.

Abstract: A downstream nozzle for use in a combustor that includes an inner radial wall defining a combustion zone downstream of a primary nozzle and an outer radial wall surrounding the inner radial wall so to form a flow annulus therebetween. The downstream nozzle may include: an injector tube extending between the outer radial wall and the inner radial wall; a first plenum adjacent to the injector tube, and, inboard of the ceiling, a floor disposed between the inner radial wall and the outer radial wall. A feed passage may connect the first plenum to an inlet formed outboard of the outer radial wall and impingement ports may be formed through the floor of the first plenum.

Abstract: A gas turbomachine nozzle includes a base portion having a first fluid inlet and a second fluid inlet, and an outlet portion having one or more outlets. A connection section fluidically connects the base portion and the outlet portion. An orifice plug is arranged in the base portion at the second fluid inlet. The orifice plug includes one or more openings fluidically connecting the second fluid inlet and the connection section.

Abstract: A gas turbine engine having a combustor that includes: an inner radial wall defining axially stacked first and second interior chambers, wherein the first interior chamber extends axially from an end cover to a fuel nozzle, and the second interior chamber extends axially from the fuel nozzle to an inlet of the turbine; and an outer radial wall formed about the inner radial wall so to form a flow annulus therebetween. The flow annulus may include a flow conditioning section that has: conditioning passages defined therethrough for directing a flow from inlets formed at an upstream end to outlets formed at a downstream end of the flow conditioning section; and structure rigidly attaching the inner radial wall to the outer radial wall.

Abstract: A gas/liquid fuel nozzle assembly includes a premixing tube bundle having an array of mixing tubes, a fuel plenum delivering fuel to the mixing tubes, a cartridge tube disposed within the fuel plenum, and a liquid fuel cartridge disposed in the cartridge tube. The liquid fuel cartridge is spaced from the cartridge tube to define an annulus. The cartridge tube and the fuel plenum are constructed in fluid communication such that gas fuel in the plenum is injected into the annulus.

Abstract: A system for retaining a fuel nozzle premix tube includes a retention plate and a premix tube which extends downstream from an outlet of a premix passage defined along an aft side of a fuel plenum body. The premix tube includes an inlet end and a spring support feature which is disposed proximate to the inlet end. The premix tube extends through the retention plate. The spring retention feature is disposed between an aft side of the fuel plenum and the retention plate. The system further includes a spring which extends between the spring retention feature and the retention plate.

Abstract: An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.

Abstract: A transition duct for a combustor of a gas turbine generally includes a transition duct having a frame at an aft end of the transition duct. The frame generally includes a downstream end, a radially outer portion, a radially inner portion opposed to the radially outer portion, a first side portion between the radially outer and inner portions, and a second side portion opposed to the first side portion. A slot in the first side portion of the frame may have a downstream surface adjacent to the downstream end of the frame. A heat shield having an inner surface, an outer surface and a plurality of spacers may extend generally outward from the heat shield inner surface such that the inner surface is adjacent to the slot downstream surface and the frame downstream end.

Abstract: An impingement sleeve and methods for designing and forming an impingement sleeve are disclosed. In one embodiment, the impingement sleeve includes a body configured to at least partially surround a transition piece of the combustor. The impingement sleeve further includes a plurality of cooling holes defined in the body, the plurality of cooling holes having a cooling hole pattern configured to provide a desired operational value for the transition piece. At least one of the plurality of cooling holes has a chamfer extending at least partially between an inlet and an outlet of the at least one of the plurality of cooling holes. At least a portion of the plurality of cooling holes are generally longitudinally asymmetric.