Abstract: A system is provided with a fuel sweep system configured to couple to a flow sleeve of a combustor along a first fuel conduit. The flow sleeve is configured to be disposed about a liner of the combustor, and the first fuel conduit is configured to extend along the flow sleeve in a compressor discharge chamber disposed about the flow sleeve. The fuel sweep system includes a first fuel sweep louver adjacent a first fuel sweep opening defined through the flow sleeve.

Abstract: A cartridge tip includes a main body having an outer annular wall and an inner core each extending between a respective upstream end and a respective downstream end. The inner core is radially spaced apart from the outer annular wall such that an annular air passage is defined at least partially between the outer annular wall and the inner core. A pilot fuel circuit extends between a pilot inlet defined in the upstream end of the inner core and a pilot outlet defined in a downstream end of the inner core. The pilot fuel circuit extends at least partially along an axial centerline of the cartridge tip. A main fuel circuit extends between a main inlet in the upstream end of the inner core and a plurality of main outlets circumferentially spaced apart from one another and disposed upstream from the from the pilot outlet.

Abstract: A system is provided with a fuel sweep system configured to couple to a flow sleeve of a combustor along a first fuel conduit. The flow sleeve is configured to be disposed about a liner of the combustor, and the first fuel conduit is configured to extend along the flow sleeve in a compressor discharge chamber disposed about the flow sleeve. The fuel sweep system includes a first fuel sweep louver adjacent a first fuel sweep opening defined through the flow sleeve.

Abstract: A cartridge tip includes a main body having an outer annular wall and an inner core each extending between a respective upstream end and a respective downstream end. The inner core is radially spaced apart from the outer annular wall such that an annular air passage is defined at least partially between the outer annular wall and the inner core. A pilot fuel circuit extends between a pilot inlet defined in the upstream end of the inner core and a pilot outlet defined in a downstream end of the inner core. The pilot fuel circuit extends at least partially along an axial centerline of the cartridge tip. A main fuel circuit extends between a main inlet in the upstream end of the inner core and a plurality of main outlets circumferentially spaced apart from one another and disposed upstream from the from the pilot outlet.

Abstract: A combustor includes at least one fuel nozzle extending from the end cover and at least partially surrounded by the forward casing. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extends to the fuel injector. The fuel injection assembly further includes a shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The shielding assembly includes a venturi nozzle having a circumferentially converging portion and a circumferentially diverging portion. At least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.

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.

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.

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: 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: A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.

Abstract: A system includes a turbomachine including a first chamber configured to contain a first fluid and a second chamber configured to contain a second fluid. The turbomachine also includes a barrier disposed between the first and second chambers. The barrier is configured to separate the first fluid and the second fluid. Additionally, the barrier includes a first surface facing the first chamber and a second surface facing the second chamber. The turbomachine also includes an orifice extending from the first chamber to the second chamber. The orifice defines a fluid passageway. Additionally, the turbomachine includes a tube including a first end and a second end. The first end is coupled to the first surface and is disposed about a perimeter of the orifice. The tube is configured to at least partially contain the second fluid.

Abstract: A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.

Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

Abstract: Certain embodiments of the present disclosure include a combustor resonator having a non-uniform annulus between a combustor assembly and a resonator shell. The combustor resonator may further include resonator necks or passages having non-uniform lengths and geometries.

Abstract: A system includes a turbomachine including a first chamber configured to contain a first fluid and a second chamber configured to contain a second fluid. The turbomachine also includes a barrier disposed between the first and second chambers. The barrier is configured to separate the first fluid and the second fluid. Additionally, the barrier includes a first surface facing the first chamber and a second surface facing the second chamber. The turbomachine also includes an orifice extending from the first chamber to the second chamber. The orifice defines a fluid passageway. Additionally, the turbomachine includes a tube including a first end and a second end. The first end is coupled to the first surface and is disposed about a perimeter of the orifice. The tube is configured to at least partially contain the second fluid.

Abstract: A combustor assembly having a fuel pre-mixer including a duct for mixing an airflow and a fuel therein. Also included is a center body coaxially aligned within the duct for receiving the fuel from a fuel source and configured to distribute the fuel to at least one axial location within the duct. Further included is a planar vane section in communication with the airflow and the fuel to provide a first injection of fuel and a flow conditioning effect on the airflow. Yet further included is a swirler vane section disposed downstream of the planar vane section, wherein the swirler vane section is configured to provide a second injection of fuel and a mixing of the fuel and the airflow.

Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.

Abstract: An interface between an inlet flow conditioner and a compressor discharge air passage in a gas turbine includes a cap back plate including a curved exterior surface, and an inlet flow conditioner (IFC) cooperable with the cap back plate. An end of the IFC includes a curved exterior surface that is continued from the curved exterior surface of the cap back plate. The interface provides for more uniform and higher pressure air as well as more air supply, resulting in more uniform combustion.

Abstract: A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.

Abstract: Certain embodiments of the present disclosure include a combustor resonator having a non-uniform annulus between a combustor assembly and a resonator shell. The combustor resonator may further include resonator necks or passages having non-uniform lengths and geometries.