Abstract: The present disclosure is directed to an assembly tool kit for a bundled tube fuel nozzle assembly. The assembly tool kit includes a plurality of pins. Each pin includes a shaft portion, a tapered portion coupled to a first end of the shaft portion, and a contoured portion coupled to a second end of the shaft portion. The contoured portion includes a cylindrical section and a frustoconical section. The tapered and shaft portions of each of the plurality of pins are positioned within a passage defined by one of a plurality of tubes forming a portion of a bundled tube fuel nozzle assembly. The contoured portion of each of the plurality of pins is positioned in one of a plurality of cap plate apertures. Each of the plurality of pins radially aligns one of the plurality of cap plate apertures with a corresponding tube of the plurality of tubes.

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 bundled tube fuel nozzle assembly includes a fuel plenum body defining a forward wall, an aft wall, an outer band, a fuel plenum defined within the fuel plenum body and a plurality of tubular passages that extends from the forward wall, through the fuel plenum and to the aft wall, wherein the fuel plenum body is formed as a singular body. The bundled tube fuel nozzle assembly further includes a plurality of tube extensions that extends downstream from the plurality of tubular passages. At least one tube extension of the plurality of tube extensions includes an upstream end that extends axially into a respective outlet of a respective tubular passage of the plurality of tubular passages.

Abstract: A fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band extending between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the forward wall, the fuel plenum and the aft wall and each tube defines a premix flow passage through and downstream from the fuel plenum body. Each tube is rigidly connected to the aft plate. A damping plate is disposed downstream from the aft plate. At least one tube of the plurality of tubes extends through a corresponding tube opening defined by the damping plate. The damping plate includes a plurality of spring members fixedly connected to the damping plate. At least one spring member of the plurality of spring members is engaged with an outer wall of the at least one tube.

Abstract: A fuel delivery system for a gas turbine combustor is provided. The fuel delivery system includes a fuel tube and an attachment assembly. The fuel tube extends from a downstream injector (e.g., a late lean injector) towards a mounting ring of the combustor and is moveably attached to the mounting ring using the attachment assembly. Accordingly, the exemplary fuel delivery system may provide fuel to a downstream injector while accommodating a thermal expansion or contraction of the fuel tube along an axial direction of the combustor.

Abstract: A bundled tube fuel nozzle includes a forward plate, an intermediate plate, an aft plate and an outer sleeve. The forward plate, the intermediate plate and the outer sleeve define a fuel plenum therebetween. An aft plate axially is spaced from the intermediate plate and the intermediate plate, the aft plate and the outer sleeve define a cooling air plenum. A plurality of tubes extends through the forward plate, the fuel plenum, the intermediate plate, the cooling air plenum and the aft plate. Each tube of the plurality of tubes extends through a respective tube opening defined by the aft plate. A radial gap is defined between an outer surface of each tube and an inner surface of the respective tube opening. The plurality of tubes comprises at least one tube that is radially loaded against the inner surface of the respective tube opening.

Abstract: The present disclosure is directed to a combustor including an annularly shaped liner that at least partially defines a hot gas path of the combustor and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies circumferentially spaced about the flow sleeve and each fuel injector assembly extends radially through the flow sleeve, the cooling flow annulus and the liner. A first portion of the flow sleeve defined between a first pair of circumferentially adjacent fuel injector assemblies of the plurality of fuel injector assemblies bulges radially outwardly with respect to an outer surface of the liner so as to enlarge a flow volume of the cooling flow annulus.

Abstract: A fuel injector assembly includes a shroud defining a fuel manifold therein. The fuel manifold is fluidly coupled to a fuel line to receive a fuel therefrom. The fuel injector assembly further includes a center body and a plurality of vanes operatively coupling the center body to the shroud. Each vane of the plurality of vanes is circumferentially spaced from circumferentially adjacent vanes to define at least one passage therebetween for routing of air therethrough. Each of the plurality of vanes has at least one outlet hole in fluid communication with the fuel manifold and at least one passage of the at least one passage for expulsion of the fuel into the at least one passage for mixing with the air. A fuel injector outlet is defined by an inner wall of the fuel injector assembly and positioned to direct a fuel-air mixture out of the fuel injector assembly.

Abstract: A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first oxidant flow path and a first perforated structure comprising a first plurality of oxidant ports, wherein the first perforated structure is disposed in the first oxidant flow path. The second combustor includes a second oxidant flow path and a second perforated structure comprising a second plurality of oxidant ports. The second perforated structure is disposed in the second oxidant flow path and the first perforated structure has at least one difference relative to the second perforated structure.

Abstract: A support frame for assembling a combustion module for a gas turbine includes a base plate disposed at a bottom end of the support frame and a support plate that is vertically separated from the base plate by one or more vertical support members. The support plate defines an opening that is sized to allow a portion of the combustion module to pass therethrough. A support block extends vertically from the base plate towards the support plate where the support block defines one or more fastener holes for connecting an aft end of a combustion liner of the combustion module to the support block. A central support column extends vertically from the base plate towards the support plate. A horizontal support extends radially outward from the central support column to align the combustion liner with the opening in the support plate.

Abstract: A fuel injector for a combustor generally includes an annular outer body having an inlet and an outlet. The outer body at least partially defines an outer flow passage. An inner flow passage extends at least partially through the outer flow passage and a radial swirler is disposed at the inlet of the outer body. The radial swirler includes a first radial passage separated from a second radial passage. The first radial passage has a first plurality of swirler vanes and the second radial passage has a second plurality of swirler vanes. The first radial passage is in fluid communication with the outer flow passage and the second radial passage is in fluid communication with the inner flow passage.

Abstract: The present application provides a fuel plenum for a micro-mixer combustor. The fuel plenum may include a first assembly plate with a first assembly plate aperture, a second assembly plate with a second assembly plate aperture, a fuel tube extending through the first assembly plate aperture of the first assembly plate and the second assembly plate aperture of the second assembly plate, and an installation insert positioned between the fuel tube and the first assembly plate aperture.

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: An air shield for an injector of a combustor includes a first section that extends axially from a first end to a second end, and a channel defined by the air shield. The channel includes at least one inlet proximate to the second end. The at least one inlet is configured to receive a channel airflow that is a portion of a surrounding airflow. The channel is configured to control a distribution of the channel airflow to the injector.

Abstract: A fuel supply system for a gas turbine combustor includes a fuel distribution manifold. A first fuel circuit extends from the fuel distribution manifold in a first circumferential direction around an outer surface of the outer casing and provides for fluid communication from the fuel distribution manifold, through the outer casing and to at least one fuel injector disposed within the outer casing. A second fuel circuit extends from the fuel distribution manifold in a second circumferential direction around the outer surface of the outer casing. The second fuel circuit provides for fluid communication from the fuel distribution manifold, through the outer casing and to at least one fuel injector within the outer casing. In particular configurations, the fuel supply system includes a shield that surrounds at least a portion of the outer casing and at least partially encases the first fuel circuit and the second fuel circuit.

Abstract: A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell.

Abstract: A combustion liner for a gas turbine combustor includes an annular main body having a forward end axially separated from an aft end, and a transitional intersection defined between the forward end and the aft end. The main body extends continuously from the forward end to the aft end. A plurality of fuel injector passages extend radially through the main body upstream from the transitional intersection. The main body comprises a conical section having a circular cross section that diverges between the forward end and the transitional intersection, and a transition section having a non-circular cross section that extends from the transitional intersection to the aft end of the main body.

Abstract: A system for controlling air flow rate of a compressed working fluid to a fuel injector of a combustor includes an outer casing that defines a high pressure plenum around a portion of the combustor, an extraction port in fluid communication with the high pressure plenum and an inlet port. The combustor includes a plurality of fuel injectors arranged around a combustion liner, an inner flow sleeve, an outer air shield that surrounds the plurality of fuel injectors and the inner flow sleeve. The outer air shield defines an injection an air plenum between the outer air shield and the inner flow sleeve and an inlet to the injection air plenum. An external fluid circuit provides fluid communication between the extraction port and the inlet port. A baffle extends between the outer casing and the outer air shield to provide flow separation between the inlet and the high pressure plenum.

Abstract: Aft frame assemblies for aft ends of gas turbine transition pieces comprise a body comprising a downstream facing seal surface on an aft end, wherein at least a portion of the downstream facing seal surface configured to be exposed to a combustion discharge stream, a heat shield disposed proximate the aft end of the body, wherein the heat shield is configured to deflect at least a portion of the combustion discharge stream away from the aft end of the body, and, one or more heat shield supports connected to the body and configured to at least partially restrict deflection of the heat shield back towards the body.

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.