An injection system includes a radial swirler defining an axis and including a plurality of radial swirl vanes configured to direct a radially inward flow of compressor discharge air entering swirler inlets between the radial swirl vanes in a swirling direction around the axis. The radial swirler includes an outlet oriented in an axial direction to direct swirling compressor discharge air in an axial direction. An injector ring is included radially outward from of the swirler inlets. The fuel injector ring is aligned with the axis and includes a plurality of injection orifices directed towards the swirler inlets for injecting fuel into the radial swirler.

In a combustor including a plurality of combustion nozzles, and a gas turbine including the same, fuel can be uniformly mixed with compressed air for each combustion nozzle. The combustor includes a plurality of combustion nozzles arranged in a nozzle casing, and each combustion nozzle includes a nozzle shroud for taking in compressed air; an injection cylinder concentrically disposed in the nozzle shroud and configured to be supplied with fuel for mixing with the compressed air; and a plurality of swirlers circumferentially arranged around the injection cylinder and configured to inject the fuel from the injection cylinder into the shroud. The plurality of swirlers divide an interior space of the nozzle shroud into a plurality of fluid flow regions, and include a pair of adjacent swirlers spaced apart from each other by a circumferential distance that differs from a circumferential distance between another pair of adjacent swirlers.

An air swirler arrangement comprises a coaxial arrangement of an inner and an outer air swirler passage. Each air swirler passage comprises a radial flow swirler. Air swirler arrangement comprises a coaxial arrangement of first, second and third members. Second member has radially extending upstream portion spaced axially from first member and a convergent portion. Third member has a radially extending upstream portion spaced axially from the upstream portion of second member and a radially inner surface having convergent and divergent downstream portions and a radially outer surface having a divergent downstream portion. First, second and third members the vanes of the radial flow swirlers is a monolithic structure. Plurality of circumferentially spaced passages are provided within the third member and each passage has an inlet in the surface and an outlet arranged to direct fluid onto the divergent portion of the surface or the surface of the third member.

A device is disclosed herein which provides a domed cover of a combustion chamber enclosure applicable for use in Stirling Cycle engines, Ericsson Cycle engines, Rankine Cycle engines or other external combustion heat engine types which allows for the free flow of combustion air from the outer margins of the device toward the combustion air inlet in a vortexual fluid flow to achieve a more balanced stoichiometric ratio of the fuel/air mixture before ignition. This may be achieved by the employment of vanes to direct combustion air in a swirling vortexual flow as the combustion air enters the combustion chamber. Thermal barrier coatings and insulative materials may also be employed to minimize parasitic heat loss.

The present disclosure includes air spinners for use in duct burners, and duct burners and duct burner kits including a plurality of air spinners. Air spinners may include a plurality of blades extending radially outward from a fuel path and configured to impart rotation to air flowing between the blades, where the air spinner is configured to be coupled to a fuel runner of a duct burner such that the air spinner encircles a fuel outlet of the fuel runner with the axis of the fuel path extending at a non-parallel angle from an axis of the fuel runner. Duct burners can comprise a plurality of air spinners coupled to a plurality of fuel runners. Duct burner kits can comprise a plurality of air spinners configured to be coupled (e.g., without welding) to a plurality of fuel runners.

A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.

The present disclosure includes air spinners for use in duct burners, and duct burners and duct burner kits including a plurality of air spinners. Air spinners may include a plurality of blades extending radially outward from a fuel path and configured to impart rotation to air flowing between the blades, where the air spinner is configured to be coupled to a fuel runner of a duct burner such that the air spinner encircles a fuel outlet of the fuel runner with the axis of the fuel path extending at a non-parallel angle from an axis of the fuel runner. Duct burners can comprise a plurality of air spinners coupled to a plurality of fuel runners. Duct burner kits can comprise a plurality of air spinners configured to be coupled (e.g., without welding) to a plurality of fuel runners.

Flue gases are produced in a combustion chamber of a burner unit, in particular for the combustion of exhaust air. Combustion gas can be supplied to a gas burner via a combustion gas line and feed air, in particular exhaust air that can be used as feed air, is supplied to said burner via a feed air line. The feed air is divided into primary air and secondary air by a device. The primary air is mixed with the combustion gas, in a mixing zone, to form a primary air/combustion gas mixture, said primary air/combustion gas mixture being supplied to the combustion chamber. A flue gas re-circulation system comprises a through-flow chamber which is connected to the combustion chamber and in which the secondary air is mixed with the flue gases occurring in the combustion chamber to form a secondary air/flue-gas mixture. The secondary air/flue-gas mixture is supplied to the primary air/combustion gas mixture in the combustion chamber by means of a device. At least one internal cylindrical surface of the through-flow chamber forms a Coanda profile in the direction of flow. A device for the temperature control of objects, in particular for drying painted vehicle bodies, comprises a temperature-control tunnel that is accommodated in a housing and that defines at least one tunnel section comprising at least one air outlet and at least one air inlet. A heating assembly, in which a hot primary gas can be generated by means of a burner unit of this type, is associated with the tunnel section.

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

The present disclosure includes air spinners for use in duct burners, and duct burners and duct burner kits including a plurality of air spinners. Air spinners may include a plurality of blades extending radially outward from a fuel path and configured to impart rotation to air flowing between the blades, where the air spinner is configured to be coupled to a fuel runner of a duct burner such that the air spinner encircles a fuel outlet of the fuel runner with the axis of the fuel path extending at a non-parallel angle from an axis of the fuel runner. Duct burners can comprise a plurality of air spinners coupled to a plurality of fuel runners. Duct burner kits can comprise a plurality of air spinners configured to be coupled (e.g., without welding) to a plurality of fuel runners.