Abstract: A fuel nozzle assembly includes a fuel plenum for delivering fuel to a combustion zone of a combustor. At least one narrow-band acoustic damper is provided in the fuel nozzle assembly. The narrow-band acoustic damper is tuned to dampen pressure oscillations within the combustor. The narrow-band acoustic damper may be a quarter-wave tube mounted to a cap plate within or adjacent to the fuel nozzle assembly.

Abstract: A combustion system includes a head end comprising a liquid fuel cartridge. The liquid fuel cartridge has liquid fuel injection ports and is configured to produce combustion products via a diffusion flame. A liner is configured to deliver the combustion products from the head end to an aft frame, and an injector having an outlet is located along the liner between the head end and the aft frame. The injector outlet delivers a stream of oxidant inwardly into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame. A method of producing combustion products having characteristics of a premixed flame in a liquid fuel combustion system is also provided herein.

Abstract: An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage.

Abstract: A fuel nozzle assembly includes a flange body. The flange body includes a base portion that defines an aperture. The flange body is connected to a conduit. The flange body and the conduit define a fuel flow passage to a fuel plenum of the fuel nozzle assembly. The fuel nozzle assembly further includes an insert that is partially disposed within the aperture of the base portion. The insert includes an orifice disposed within the aperture of the base portion and a forward portion of the insert extends axially outwardly from the aperture. The orifice is in fluid communication with the fuel flow passage.

Abstract: An object includes a fluid chamber extending between a first surface and a vertically opposed second surface, the first surface including a fluid passage opening therethrough. A self-breaking support, initially configured to support the first surface, once broken creates a broken support disposed between the first surface and the vertically opposed second surface. The support includes: a base having a first end coupled to the first surface and a second opposing end. The first end of the base is wider than the second end, and a fluid passage extends through the first base for fluidly coupling the fluid chamber and the fluid passage opening in the first surface. A self-breaking link is disposed between the second opposing end of the first base and the second surface.

Abstract: The present disclosure is directed to an end cover assembly for a combustor of a turbomachine. The end cover assembly includes an end cover and a bundled tube fuel nozzle assembly positioned downstream from the end cover. The bundled tube fuel nozzle assembly includes a plurality of fuel nozzle tubes. A flame detector sight tube couples to the end cover. The flame detector sight tube is aligned with one of the fuel nozzle tubes.

Abstract: A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.

Abstract: An endcover assembly for a combustor includes an endcover and a fuel nozzle rigidly connected to the endcover. The fuel nozzle includes a plurality of tubes that extends axially through a first plate, a fuel plenum and a second plate where each tube includes an inlet defined upstream of the first plate and an outlet disposed downstream from the second plate. The endcover assembly further includes an inlet flow conditioner having a forward end connected to the endcover and an aft end axially spaced from the forward end. The inlet flow conditioner circumferentially surrounds at least a portion of the fuel nozzle. A support plate is joined to the aft end of the inlet flow conditioner. Each tube of the fuel nozzle extends through a corresponding tube hole defined by the support plate. The fuel nozzle is connected to the support plate.

Abstract: The present disclosure provides assemblies for cooling a liquid fuel cartridge unit within a combustor head end. In one embodiment, the cooling is accomplished passively as air from the head end air plenum is directed into a cooling channel radially outward of a liquid fuel delivery conduit. In another embodiment, the cooling of the liquid fuel cartridge unit is accomplished actively as air is directed through a first air flow conduit radially inward of the liquid fuel delivery conduit and then redirected through a second air flow conduit radially outward of the liquid fuel delivery conduit.

Abstract: A system and method for igniting liquid fuel in a gas turbine combustor is provided. A liquid fuel cartridge, which is located within the head end, is in flow communication with a liquid fuel supply. A gaseous fuel nozzle is located proximate the liquid fuel cartridge and in flow communication with an auxiliary gaseous fuel supply. A controller is in communication with the liquid fuel supply, the auxiliary gaseous fuel supply, and an igniter located proximate or within the head end. The controller is configured to sequentially: initiate a gaseous fuel flow from the auxiliary gaseous fuel supply to the gaseous fuel nozzle; initiate the igniter to combust the gaseous fuel flow; initiate a liquid fuel flow from the liquid fuel supply to the liquid fuel cartridge; and terminate the gaseous fuel flow from the auxiliary gaseous fuel supply.

Abstract: A fuel nozzle assembly includes a flange body including a stem. The flange body defines a flow passage therethrough. The fuel nozzle assembly further includes a conduit assembly having an inner tube that is disposed within an outer tube. A purge passage is defined radially between the inner tube and the outer tube and a fuel passage is defined within the inner tube. The outer tube and the inner tube are connected to the stem with the inner tube being connected to the stem via a flexible coupling disposed within the purge passage. The purge passage is in fluid communication with an inlet flow plenum and with a plurality of premix tubes of the fuel nozzle assembly.

Abstract: A combustion liner assembly includes a combustion liner having an upstream end portion and a downstream end portion and a resonator disposed proximate to the upstream end portion of the combustion liner. The resonator includes a plurality of circumferentially spaced inlet apertures disposed along a radially outer surface of the resonator, an air chamber defined within the resonator and a plurality of outlet apertures disposed along a radially inner surface of the resonator. The plurality of inlet apertures provide for fluid flow into the air chamber and the plurality of outlet apertures provide for fluid flow out of the air chamber and into a radial flow passage defined within the combustor.

Abstract: A liquid fuel cartridge unit for a gas turbine combustor includes a cartridge tip having an aft plate and a side wall circumscribing the aft plate. First injection ports are defined through the side wall, and second injection ports are defined through the side wall upstream of the first injection ports, relative to fuel flow through the cartridge tip. Nested conduits extend into the cartridge tip with the concentric conduits defining therebetween respective flow passages. The first injection ports are in fluid communication with a first flow passage, and the second injection ports are in fluid communication with a second flow passage. A method of assembling the liquid fuel cartridge unit is also provided.

Abstract: A fuel nozzle assembly includes a forward plate and an aft plate which is axially spaced from the forward plate. The aft plate includes a first side surface and a second side surface. A cooling air plenum is defined within the bundled tube fuel nozzle assembly and is at least partially defined by the aft plate. A plurality of tubes extends through the forward plate, the cooling air plenum and the aft plate. A micro-cooling channel is disposed along the second side surface of the aft plate and is in fluid communication with the cooling air plenum and is in fluid communication with an exhaust aperture. A cover plate is connected to the aft plate and covers the micro-cooling channel.

Abstract: An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.

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: 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 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: An igniter for a combustor of a turbomachine includes a fuel inlet in fluid communication with a mixing plenum. The mixing plenum is positioned upstream of a mixing channel. An air inlet is in fluid communication with the mixing plenum and an ignition source is in operative communication with the mixing channel. The igniter may include a mounting flange configured for coupling the igniter to the combustor. The ignition source may be positioned proximate to a downstream end of the mixing channel and upstream of the mounting flange. The mixing channel may define a venturi shape. The venturi shape includes a converging section between an upstream end of the mixing channel and a venturi throat.

Abstract: A gas turbine includes a compressor, a turbine, and a combustor disposed downstream from the compressor and upstream from the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange and the flange is coupled to an internal face of the end cover. A fuel port is integrally joined with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside of the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.