Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.

Abstract: A combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner and has a combustion zone. The annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of the outer liner, the inner liner, or the annular dome. The combustor steam system operably directs steam through the steam path from the at least one of the outer liner, the inner liner, or the annular dome and into the combustion chamber.

Abstract: A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone, an annular dome coupled to the outer liner and the inner liner, and a trapped vortex cavity extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome, and operably inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex cavity, and operably inject a second fuel-air mixture into the second combustion zone defined in the trapped vortex cavity to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex cavity. The steam injector operably injects steam into the trapped vortex cavity and the steam mixes with the combustion gases.

Abstract: A combustion section of a turbine engine having a primary combustion chamber and a secondary combustion chamber. The primary combustion chamber is defined, at least in part, by a combustor liner and a dome wall. A primary fuel nozzle having an outlet is located at the dome wall, wherein the outlet of the primary fuel nozzle is fluidly coupled with the primary combustion chamber. At least one opening located in an outer liner axially aft of the dome wall fluidly couples the secondary combustion chamber and the primary combustion chamber. A set of secondary fuel nozzles are fluidly coupled with the secondary combustion chamber.

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 turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.

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 swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section including a primary combustor liner having an inner liner and an outer liner. A dome wall and a dome inlet are located in the dome wall. At least one opening is located in the outer liner downstream from the dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.

Abstract: A turbine engine includes a combustor having a main combustion chamber, an annular dome positioned at a first angle ? with respect to a longitudinal centerline axis of the combustor, and a secondary combustion chamber. The secondary combustion chamber is defined by a portion of the annular dome and an aft wall positioned at a second angle ? with respect to the longitudinal centerline axis. A pilot mixer is disposed through the annular dome and injects a pilot mixer fuel-air mixture at a pilot mixer fuel-air mixture angle into the main combustion chamber and generates a first recirculation zone. A main mixer is disposed through the aft wall or the annular dome at the secondary combustion chamber. The main mixer injects a main mixer fuel-air mixture at a main mixer fuel-air mixture angle into the secondary combustion chamber to produce combustion gases and generates a second recirculation 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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

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 combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.

Abstract: A combustor for a turbine engine includes a main combustion chamber, an annular dome, and a secondary combustion chamber positioned downstream of the annular dome. A plurality of first mixing assemblies are disposed through the annular dome and include a pilot mixer. The pilot mixer injects a pilot mixer fuel-air mixture axially into the main combustion chamber and generates a first recirculation zone within the main combustion chamber. A plurality of second mixing assemblies are disposed at the secondary combustion chamber axially aft of the first mixing assemblies and include a main mixer. The main mixer injects a main mixer fuel-air mixture into the secondary combustion chamber to produce combustion gases and to generate a second recirculation zone within the secondary combustion chamber axially aft of the first recirculation zone. The secondary combustion chamber injects the combustion gases into the main combustion chamber.

Abstract: A swirler-ferrule assembly includes a radial swirler, a ferrule, a fuel nozzle, and a surface feature. The radial swirler includes a primary swirler vane having a primary air passage and a secondary swirler vane having a secondary air passage. The ferrule may be connected to the radial swirler. The surface feature may be located on the primary swirler vane and/or the ferrule. The surface feature may be configured to direct an air flow through the primary air passage away from a recirculation zone located upstream of the primary swirler vane. The surface feature has a trailing end and a distal end, and the fuel nozzle is axially aligned with the trailing end of the surface feature or is located axially downstream of the trailing end of the surface feature. The surface feature may have a plurality of grooves.

Abstract: A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.