Abstract: A swirler for a fuel nozzle assembly of a gas turbine includes a first wall, a second wall extending circumferentially about a swirler centerline axis, a splitter wall, a first plurality of radial swirl vanes extending between the first wall and the splitter wall, a second plurality of radial swirl vanes extending between the splitter wall and the second wall, and a plurality of vortex generating elements including at least one of (i) a first plurality of vortex generating elements arranged on the first wall, (ii) a second plurality of vortex generating elements arranged on a radial wall portion of the splitter wall, or (iii) a third plurality of vortex generating elements arranged on an axial wall portion of the splitter wall.

Abstract: A gas turbine engine, comprising: a compressor section, a combustion section, and a turbine section in a serial flow arrangement, with the combustion section comprising: a combustor liner that at least partially defines a combustion chamber; and a fuel-air mixer fluidly coupled with the combustion chamber and comprising: a mixing tube defining a mixing channel including a mixing tube inlet, a mixing tube outlet fluidly coupled with the combustion chamber, and a mixing channel centerline, the mixing tube inlet including a fuel inlet to receive fuel and an air inlet to receive air; a first set of air jets fluidly coupled with the mixing channel and axially spaced downstream of the mixing tube inlet; and a second set of air jets fluidly coupled with the mixing channel and axially spaced downstream of the first set of air jets.

Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.

Abstract: A combustor for a turbine engine includes a combustion chamber including an outer liner and an inner liner, an annular dome, and a trapped vortex cavity (TVC) downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer and a first main mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into a first combustion zone, and the first main mixer injects a first main mixer fuel-air mixture radially into the first combustion zone. A plurality of second mixing assemblies are disposed at the TVC axially aft of the first mixing assemblies and include a second main mixer. The second main mixer injects a second main mixer fuel-air mixture into a second combustion zone defined by the TVC and axially aft of the first combustion zone. The TVC injects the combustion gases into the combustion chamber.

Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.

Abstract: A combustor for a turbine engine includes a combustion chamber including an outer liner and an inner liner, and an annular dome. A plurality of first mixing assemblies includes a pilot mixer and a first main mixer, the first mixing assemblies disposed through the annular dome. The pilot mixer injects a pilot mixer fuel-air mixture axially into a first combustion zone, and the first main mixer injects a first main mixer fuel-air mixture radially into the first combustion zone. A plurality of second mixing assemblies includes a second main mixer, the second mixing assemblies being axially aft of the plurality of first mixing assemblies. The second main mixer injects a second main mixer fuel-air mixture radially into a second combustion zone that is axially aft of, and separate from, the first combustion zone.

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and emission needs require the use of alternative fuels, which combust at higher temperatures and faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

Abstract: A turbine engine has a compression section, a combustion section, and a turbine section in serial flow arrangement. The combustion section has a combustor liner and dome wall collectively forming at least a portion of a combustion chamber. The dome wall has a fuel nozzle opening. The combustion section has a fuel nozzle extending through the fuel nozzle opening. The fuel nozzle has a gaseous fuel supply channel, and a compressed air channel. The combustion section includes a gaseous fuel channel fluidly coupled to the gaseous fuel supply channel.

Abstract: A turbine engine has a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section has a combustion liner and dome wall collectively forming at least a portion of a combustion chamber. The dome wall has a fuel nozzle opening. The combustion section has a fuel nozzle assembly extending through the fuel nozzle opening. The fuel nozzle assembly has a gaseous fuel supply, a compressed air supply, a mixer, a fuel nozzle and a first swirler.

Abstract: A combustion section for a turbine engine. The combustion section has a wall and a fuel nozzle. The wall at least partially forms a combustion chamber. The fuel nozzle opens to the combustion chamber through the wall. The fuel nozzle has a fuel nozzle body and a swirler. The fuel nozzle body defines a central channel. The swirler is provided within the central channel.

Abstract: A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.

Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

Abstract: A combustion section for a turbine engine. The combustion section has a wall and a fuel nozzle. The wall at least partially forms a combustion chamber. The fuel nozzle opens to the combustion chamber through the wall. The fuel nozzle has a fuel nozzle body and a swirler. The fuel nozzle body defines a central channel. The swirler is provided within the central channel.

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.

Abstract: A combustion section for a turbine engine. The combustion section has a wall and a fuel nozzle. The wall at least partially forms a combustion chamber. The fuel nozzle opens to the combustion chamber through the wall. The fuel nozzle has a fuel nozzle body and a swirler. The fuel nozzle body defines a central channel. The swirler is provided within the central channel.

Abstract: A gas turbine engine, comprising a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising: a combustor liner that at least partially defines a combustion chamber; and a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and comprising: a rich fuel supply configured to provide a rich mixture of gaseous fuel and air; a lean fuel supply configured to provide a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture; a rich fluid passage fluidly coupled to the rich fuel supply to emit the rich mixture into the combustion chamber; and a lean fluid passage fluidly coupled to the lean fuel supply to emit the lean mixture into the combustion chamber.

Abstract: A turbine engine has a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section has a combustor liner and dome wall collectively forming at least a portion of a combustion chamber. The dome wall has a fuel nozzle opening. The combustion section has a fuel nozzle assembly extending through the fuel nozzle opening. The fuel nozzle assembly has a first body, a second body, a first swirler and a second swirler.

Abstract: A gas turbine engine, comprising: a compressor section, a combustion section, and a turbine section in a serial flow arrangement, with the combustion section comprising: a combustor liner that at least partially defines a combustion chamber; and a fuel-air mixer fluidly coupled with the combustion chamber and comprising: a mixing tube defining a mixing channel including a mixing tube inlet, a mixing tube outlet fluidly coupled with the combustion chamber, and a mixing channel centerline, the mixing tube inlet including a fuel inlet to receive fuel and an air inlet to receive air; a first set of air jets fluidly coupled with the mixing channel and axially spaced downstream of the mixing tube inlet; and a second set of air jets fluidly coupled with the mixing channel and axially spaced downstream of the first set of air jets.

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.

Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.