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 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: 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 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 bundled tube fuel nozzle assembly including a fuel plenum and an air plenum. A plurality of mixing tubes extend through the fuel plenum and the air plenum. At least one resonator is positioned in the air plenum surrounding at least one of the plurality of mixing tubes.

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: 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: An object includes an annular outer body having an interior surface; and an annular inner body disposed inside the annular outer body, the annular inner body having an exterior surface defining an annular passage with the interior surface of the annular outer body. A plurality of suspension elements connects the interior surface of the annular outer body to the exterior surface of the annular inner body, each suspension element configured to substantially rigidly locate a position of the annular outer body relative to the annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction. Each suspension element has an at least partially tear-shaped cross-section.

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 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 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: A combustor includes an inlet flow conditioner having a sleeve and a conditioner plate. The conditioner plate defines a plurality of apertures. The sleeve extends axially from the conditioner plate to a forward plate of a nozzle segment. The sleeve, the conditioner plate and the forward plate define an inlet flow plenum. The inlet flow plenum is in fluid communication with an inlet of a tube that defines a premix passage of the nozzle segment.

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: The present application provides a combustor with a radial penetration. The combustor may include a combustion chamber, a liner surrounding the combustion chamber, a flow sleeve surrounding the liner, a penetration tube extending through the liner and the flow sleeve with the radial penetration positioned within the penetration tube, a flange extending from the penetration tube about the flow sleeve, and a ferrule positioned about the flange and the radial penetration so as to limit leakage about the radial penetration.

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 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 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 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: A bundled tube fuel nozzle assembly including a fuel plenum and an air plenum. A plurality of mixing tubes extend through the fuel plenum and the air plenum. At least one resonator is positioned in the air plenum surrounding at least one of the plurality of mixing tubes.