A fuel nozzle for a combustor may include a primary fuel passage having a primary fuel outlet. A secondary fuel passage having a secondary fuel outlet. A valve located within the secondary fuel passage. The valve may include a stationary hub having a plurality of first angled surfaces. The valve may include a movable sleeve having a plurality of second angled surfaces. Each of the plurality of first angled surfaces aligns axially with a respective one of the plurality of second angled surfaces to define a slot therebetween. The valve is movable between a plurality of positions to open, to close, or to partially open the slots.

An afterburner for use with a gas turbine engine includes a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from a pilot can be injected. The exit apertures can be protrusions or slots in some forms. In some embodiments, cooling passages are arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures.

A free-vortex combustor is disclosed that generates vortices which: enhance fuel air mixing, recirculate the air, provide cooling for the combustor walls, and provide low emissions and a substantially uniform exit temperature profile. The combustor is provided fuel or fuel and air through a fuel-injector which atomizes the fuel. A first air swirler couples to the fuel-injector with a prechamber wall abutting the first swirler. A second swirler abuts a downstream end of the prechamber wall. And, a main chamber abuts the second swirler. Each of the first and second swirlers have features that cause the flow to create a vortex in the prechamber and main chamber, respectively. The features creating the swirl are blades or angled orifices. The vortex causes a pressure depression along the centerline and causes backflow along the centerline that improves mixing and improves cooling.

An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.

A trapped vortex combustor for use in a gas turbine engine includes an outer vortex chamber wall and a dome attached to, or formed integrally with, the outer vortex chamber wall. The dome, the outer vortex chamber wall, or both define at least in part an outer trapped vortex chamber and a channel. The channel extends along the circumferential direction at a forward end of the outer vortex chamber wall, the channel configured to receive an airflow through or around the outer vortex chamber wall, the dome, or both and provide such airflow as a continuous annular airflow to the inner surface of the outer vortex chamber wall. The dome further defines a fuel nozzle opening, with all openings in the dome outward of the fuel nozzle opening along the radial direction, excepting any effusion cooling holes having a diameter less than about 0.035 inches, being in airflow communication with the channel.

Combustor assemblies and methods for assembling combustor assemblies are provided. For example, a combustor assembly comprises an annular inner liner and an annular outer linear, each extending generally along an axial direction. The outer liner includes an outer flange extending forward from its upstream end. The combustor assembly also comprises a combustor dome extending between an inner liner upstream end and the outer liner upstream end and including an inner flange extending forward from a radially outermost end of the combustor dome. The inner liner, outer liner, and combustor dome define a combustion chamber therebetween, and the combustor dome and a portion of the outer liner together define an annular cavity of the combustion chamber. The inner and outer flanges define an airflow opening therebetween, and a chute member is positioned within the airflow opening to define an air chute for providing a flow of air to the annular cavity.

A combustion chamber for a gas turbine is provided. The combustion chamber has a pilot burner device, a fuel injector and an ignitor unit. The pilot burner device has a pilot body with a pilot surface which is facing an inner volume of the combustion chamber. The fuel injector has a fuel outlet for injecting a fuel into the inner volume. The ignitor unit is adapted for igniting the fuel inside the inner volume, wherein the ignitor unit is arranged at the pilot surface such that fuel which passes the ignitor unit is ignitable. The pilot body includes a recess, wherein the fuel outlet is arranged within the recess.

A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.

A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce emissions where the trapped vortex is formed using ammonia injected into an annular cavity located in a wall surrounding a combustion chamber of the combustor assembly. The annular cavity, and therefore the trapped vortex, is positioned such that when the combustion occurs within the combustion chamber the position of the annular cavity, and therefore of the trapped vortex, is downstream of a flame front. The emissions resulting from combustion travel through the combustion chamber and pass by the annular cavity before exiting the combustion chamber. The trapped vortex in the combustion chamber supplies NH.sub.2 radicals, resulting from the ammonia of the trapped vortex, to the passing by emissions and converts NOx and/or N.sub.2O in the emissions to non-polluting products, mainly water and nitrogen.

Disclosed herein is an apparatus. The apparatus comprises an injector coupled to a head portion of a combustion chamber, the injector comprising a plurality of injector elements distributed away from an inner annulus and in an outer annulus. A geometry of combustion chamber comprises a body portion, an optional shoulder portion, and a throat portion. An inner wall of combustion chamber converges radially inward towards the throat. The plurality of injector elements in combination with the geometry of the combustion chamber are configured to confine a predetermined percentage of mass flow associated with combustion to a predetermined outer annulus of the chamber.