Abstract: A fire suppression nozzle can include a first fluid channel configured to be in fluid communication with a first fluid having a first flow velocity and a second fluid channel configured to be in fluid communication with a second fluid having a second flow velocity. A mixer can be disposed between the first fluid channel and the second fluid channel such that the mixer is configured to induce streamwise vorticity in at least the first fluid exiting first fluid channel to cause mixing of the first fluid and the second fluid to reduce a flow speed of a mixture of the first fluid and the second fluid.

Abstract: A mister apparatus includes a portable mister body having an air inlet and an air outlet, a fan configured to draw air in through the air inlet and force the air out the air outlet, a reservoir configured to contain a liquid, the reservoir having a reservoir outlet, a liquid outlet, the liquid outlet being disposed adjacent to or downstream of the air outlet, and a pump in fluid communication with the reservoir. The pump is operable to move the liquid from the reservoir and out of the liquid outlet such that the liquid exiting the liquid outlet enters into the air exiting the air outlet to form a mist.

Abstract: Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.

Abstract: Combustor systems are provided. For example, a combustor system comprises a combustor having forward and aft ends and including annular inner and outer liners that each extend generally along an axial direction and define a combustion chamber therebetween. The combustor system also comprises a fuel nozzle having an outlet defined in an outlet end of the fuel nozzle and including a pilot swirler. The outlet is positioned at the forward end of the combustor to direct a fuel-air mixture into the combustion chamber. The combustor system further comprises a main mixer attached to the outlet end of the fuel nozzle and extending about the outlet. A total combustor airflow through the combustor comprises a pilot swirler airflow that is greater than about 14% of the total combustor airflow and a main mixer airflow that is less than about 50% of the total combustor airflow.

Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.

Abstract: A fuel spray nozzle, for atomising liquid fuel in gas, including: an gas passage; a liquid fuel passage; a swirler provided in the gas passage and including vanes such that, when gas passes through the gas passage, the swirler produces a jet flow of gas from between adjacent vanes and a turbulent flow of gas in the wake of each vane; a prefilming surface for receiving liquid fuel from the liquid fuel passage, and gas from the gas passage, wherein the prefilming surface includes areas that receive jet flow of gas from the gas passage, in use; wherein the fuel spray nozzle is configured to direct the liquid fuel passing through the liquid fuel passage to the areas on the prefilming surface that receive a jet flow of gas from the gas passage.

Abstract: The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve.

Abstract: The present disclosure is directed to a combustor system including a fuel nozzle comprising a main fuel injector defining an angled main injection port. Each angled main injection port defines an inlet end and an outlet end. The outlet end is oriented downstream relative to the inlet end at an angle relative to a centerline axis of the fuel nozzle. The angled main injection port permits egress of fuel from a main fuel circuit to the combustion chamber. The fuel nozzle further defines a radial main injection port. The outlet end is oriented along an axial direction approximately equal relative to the inlet end and radially outward thereof relative to the centerline axis. The radial main injection port is extended perpendicular relative to the centerline axis.

Abstract: Embodiments of a combustion section including a fuel injector assembly are provided. The combustion section includes the fuel injector assembly coupled to an outer casing and a liner assembly. The fuel injector assembly includes a body defining a first inlet opening and a second inlet opening spaced apart from one another along a first direction. The body further defines a fuel-oxidizer mixing passage therewithin extended along a second direction at least partially orthogonal to the first direction. The first inlet opening and the second inlet opening are each in fluid communication with the fuel-oxidizer mixing passage. The body defines an outlet opening at the fuel-oxidizer mixing passage at a distal end relative to the first inlet opening and the second inlet opening. The first inlet opening and the second inlet opening are each configured to admit a flow of oxidizer to the fuel-oxidizer mixing passage.

Abstract: The present invention relates to a device for spraying a product, in particular a cosmetic product, makeup product or care product, said device comprising: a container containing the product, and a dispensing head (3) comprising a body (5), and an endpiece, in particular a diffuser (7), attached to the body, the body and the endpiece (7) being configured to allow the product to be sprayed through outlet orifices about a longitudinal axis (Y) of the endpiece, in particular in at least two different directions, which are in particular diametrically opposite, the dispensing head (3) comprising at least first (15) and second (16) chambers, in particular concentric chambers, through which the flow of product successively passes before emerging from the outlet orifices, at least one opening between the first and second concentric chambers being able to be offset angularly with respect to at least one of the outlet orifices.

Abstract: The present disclosure is directed to a fuel injector including a centerbody defining an air inlet opening defined substantially radially through the centerbody; an outer sleeve surrounding the centerbody, and an end wall coupled to the centerbody and the outer sleeve. The outer sleeve defines a radially oriented first air inlet port defined radially outward of the air inlet opening at the centerbody. A mixing passage is defined between the outer sleeve and the centerbody. A first fuel injection port is defined substantially axially through the end wall to the mixing passage. The first fuel injection port defines a first fuel injection opening at the mixing passage between the first air inlet port at the outer sleeve and the air inlet opening at the centerbody.

Abstract: A fuel injector assembly for a gas turbine engine includes a centerbody extended along a lengthwise direction, the centerbody defining a first fuel nozzle, and an annular shroud defining a second fuel nozzle directly surrounding the centerbody and extended along the lengthwise direction. A passage is defined through the annular shroud and extended generally along the lengthwise direction. The passage defines an exit opening disposed at a downstream end adjacent to the combustion chamber and in fluid communication therewith. The annular shroud defines a fuel inlet opening disposed at an upstream end of the passage. The annular shroud defines an air inlet opening in fluid communication with the passage. The air inlet opening is disposed between the fuel inlet opening and the exit opening.

Abstract: A gas burner for a cooking appliance includes a frustoconically-shaped crown having a plurality of gas ports defined therein, a cover positioned above the crown, and a shell secured to the cover and positioned on the crown. The shell defines a hollow chamber positioned between the crown and the cover.

Abstract: A liquid fuel cartridge unit for a gas turbine combustor includes a cartridge tip having an aft plate and a side wall circumscribing the aft plate. First injection ports are defined through the side wall, and second injection ports are defined through the side wall upstream of the first injection ports, relative to fuel flow through the cartridge tip. Nested conduits extend into the cartridge tip with the concentric conduits defining therebetween respective flow passages. The first injection ports are in fluid communication with a first flow passage, and the second injection ports are in fluid communication with a second flow passage. A method of assembling the liquid fuel cartridge unit is also provided.

Abstract: A carbon formed body covers an outlet of a dryer. The carbon formed body is formed into a disc made from isotropic high-density graphite, and elongated holes are provided along a spiral line so as to penetrate through the disc. Hence, the opening areas of the carbon formed body can be extended while preventing reduction in the strength of the carbon formed body. Therefore, when the dryer that includes the carbon formed body attached to the outlet is in use, a smaller pressure loss is caused at the carbon formed body and the heat accumulation phenomenon is prevented. Furthermore, breakage of carbon formed bodies is inhibited at the time of manufacturing.

Abstract: The present invention relates to a device for spraying a product, in particular a cosmetic product, makeup product or care product, said device comprising: a container containing the product, and a dispensing head (3) comprising a body (5), and an endpiece, in particular a diffuser (7), attached to the body, the body and the endpiece (7) being configured to allow the product to be sprayed through outlet orifices about a longitudinal axis (Y) of the endpiece, in particular in at least two different directions, which are in particular diametrically opposite, the dispensing head (3) comprising at least first (15) and second (16) chambers, in particular concentric chambers, through which the flow of product successively passes before emerging from the outlet orifices, at least one opening between the first and second concentric chambers being able to be offset angularly with respect to at least one of the outlet orifices.

Abstract: A fuel injection device, for a gas turbine, which enhances uniform distribution in concentration of fuel gas and water vapor in a combustion chamber with a simple structure and at low cost to effectively reduce NOx, is provided. The fuel injection device mixes fuel gas and water vapor and injects fuel gas and water vapor into a combustion chamber. The fuel injection device includes a nozzle housing having a mixing chamber, and the nozzle housing includes a first introduction passage to introduce fuel gas from an outer circumference of the nozzle housing in a circumferential direction of the mixing chamber; and a second introduction passage to introduce water vapor from the outer circumference of the nozzle housing in a circumferential direction of the mixing chamber. Fuel gas and water vapor are swirled about an axis C of the mixing chamber and mixed in the mixing chamber.

Abstract: A disposable medical grade tank and mod assembly for dose controlled smokeless administration of a plurality of vaporized chemicals, and method of use thereof.

Abstract: A fuel injector assembly for a combustor including an axially staged fuel injector includes an injector body having an inner wall and a boss that is rigidly connected to the injector body the boss includes an inner wall. The inner wall of the boss and the inner wall of the injector body together define a flow passage of the fuel injector assembly. The injector body defines an inlet to the flow passage and the boss defines an outlet of the flow passage.

Abstract: A combustor is equipped with a burner case, and a base plate spreading from a downstream end of the burner case in a radial direction. The base plate defines a purging air space at an upstream side of the base plate. The combustor includes a purging air flow passage configured to inject purging air in the purging air space to a downstream side relative to the base plate. An outflow opening of the purging air flow passage is defined within at least one of a radial range from an inner circumferential surface of the burner case and an axial range from the downstream end of the burner case.

Abstract: A swirler includes a swirler body and a plurality of axial swirl vanes extending radially outward from the swirler body. At least one of the swirler body or vanes includes a spring channel defined therethrough. A fuel injector for a gas turbine engine can include an inner air swirler and/or outer air swirler as described above.

Abstract: An equipment for cleaning welding torches having a reserve of a pressurized fluid and a dispensing device designed to dispense a flow of dry ice at low temperature onto a welding torch in order to clean it of welding slag, wherein the dispensing device comprises a manual needle regulation valve, a dispensing nozzle to dispense dry ice and an adapter sleeve designed to receive the outer shroud or body of welding torch, wherein the dispensing device is designed to be coupled to welding torch to be cleaned by means of a male-female coupling, with adapter sleeve acting as the female part and the tip of supply nozzle as the male part, so that dispensing device can be adapted to the usual dimensions of welding torches.

Abstract: Systems, methods and apparatus are provided through which in some implementations a pneumatic ported atomizing fluid delivery manifold includes a fluid delivery housing, the fluid delivery housing having a frustum geometry, the fluid delivery housing has a first end and a second end, the first end has a first plane and the second end having a second plane, the fluid delivery housing has at least one chamber through which cleaning solution is operable to pass from the first end to the second end, and a free-floating pneumatic rotating exit tube positioned along a longitudinal center axis of the fluid delivery housing, the free-floating pneumatic rotating exit tube have only air passing through the free-floating pneumatic rotating exit tube.

Abstract: For producing synthesis gas by autothermal reformation of gaseous, liquid and/or solid fuels, the fuel is reacted with an oxidizing agent in a reaction space at a pressure of 10 to 120 bar and a reaction space temperature of 800 to 2,000° C. to obtain synthesis gas, wherein the oxidizing agent is introduced centrally in the upper region of the reaction space and wherein a flame is formed in the reaction space. The oxidizing agent is introduced into the reaction space separate from the fuel.

Abstract: An air blocker ring assembly including a proximal end and a distal end, a blocker ring, and a blocker ring support cooperating with the blocker ring to form a circumferentially extending split line at an interface between the blocker ring and the blocker ring support. The proximal end of the proximal ring assembly has a circumferential leading edge, and the circumferentially extending split line is located at least one of radially inside or radially outside the leading edge.

Abstract: An air blocker ring assembly includes a proximal end, a distal end, a blocker ring, and a blocker ring support. The blocker ring has a first protrusion, a second protrusion, and a third protrusion. The blocker ring support has a recess. The first protrusion of the blacker ring is received in the recess. The blocker ring is circumferentially discontinuous about a circumferential slot. At least a portion of the first protrusion is located circumferentially opposite the slot, and the second and third protrusions terminate at the slot.

Abstract: A fuel nozzle includes a center body that extends axially along an axial centerline for a length. A shroud circumferentially surrounds the center body for at least a portion of the length of the center body. A plurality of helical passages circumferentially surround the center body along at least a portion of the length of the center body, and a fuel port in each helical passage has a different convective time.

Abstract: There is provided methods for administering a toroidal pharmaceutical composition to a subject. The method includes dispensing a toroidal pharmaceutical composition, and allowing the toroidal pharmaceutical composition to contact a target organ of the subject, thereby administering the toroidal pharmaceutical composition. There are additionally provided toroidal aerosol delivery systems.

Abstract: A fuel injector includes a pilot fuel injector, configured to inject the fuel into a combustion chamber, and a main fuel injector provided coaxially with the pilot fuel injector so as to surround the pilot fuel injector and configured to have a main flow path to generate a premixed air-fuel mixture. The main flow path includes an outer main air passage located radially outwardly and configured to supply a compressed air in an axial direction into an annular premixed air-fuel mixture passage, an inner main air passage located radially inwardly and configured to supply the compressed air into the premixed air-fuel mixture passage from a radially inner side. The injector further includes a main fuel injection port to inject the fuel from an axially upstream side into the inner main air passage.

Abstract: A gas turbine engine including a combustor with a combustion liner having inner and outer walls is disclosed herein. The gas turbine engine further includes a swirler system adapted to receive a fuel injector and a flow splitter operable to bifurcate an airflow exiting the swirler system into a first bifurcated flow and a second bifurcated flow. A shroud is positioned downstream of the flow splitter and is configured to deflect the first bifurcated flow in a first direction radially inward and the second bifurcated flow in a second direction radially outward. The second bifurcated flow cools both of the inner and outer walls of the combustor liner.

Abstract: A device for injecting a liquid, particularly an aqueous urea solution, into an exhaust gas flow has at least one atomizing nozzle which is designed as a two-component nozzle and by means of which the liquid is injected into the exhaust gas flow by means of pressurized air such that the liquid can be mixed with the pressurized air first directly upon exiting, or after exiting, the respective atomizing nozzle outside of the atomizing nozzle. The atomizing nozzle, or each atomizing nozzle, has a nozzle base body, a nozzle air cap and a nozzle insert which are formed as turning parts. The respective atomizing nozzle can be connected to a nozzle lance via the nozzle base body, and the nozzle air cap and the nozzle insert are received and held in the nozzle base body.

Abstract: A fuel nozzle assembly for a gas turbine, the assembly including: a cylindrical center body; a cylindrical shroud coaxial with and extending around the center body, and a turning guide having an downstream edge extending in a passage between the center body and an inlet to the shroud, wherein the turning guide extends only partially around the center body.

Abstract: A fuel injection lance for an ore-smelting furnace includes a central conduit, a first conduit and a second conduit. The first and second conduits are concentric with the central conduit. A central conduit is connected to a fuel mixture. The first and second conduits are in flow communication with a gas source. The first and second conduits have gas flowing at independently controllable gas flow rates relative to the other conduit. A swirl portion has a cylindrical body with a hollow interior cylinder, and vertical and helical channels formed within the body portion. Vertical channels traverse the body portion vertically to the outer surface adjacent to the bottom surface. Helical channels traverse the outer surface in a helical pattern. Vertical channels intersect with corresponding helical channels at a predetermined angle selected to provide a desired particle distribution of a fuel injected into the furnace.

Abstract: A two-fluid nozzle is provided. The two-fluid nozzle includes a main nozzle, a mixing chamber and a nozzle orifice connected to the mixing chamber and positioned downstream of the mixing chamber. A ring of secondary air nozzles surrounding the nozzle orifice is also provided.

Abstract: HVOF torches introduce fuel and oxidizer reactants into a central passage so as to form a concentric stream having an axial stream of oxidizer surrounded by an annular stream of fuel that is positioned against a sidewall that bounds the central passage. The fuel can be introduced so as to swirl about the axial stream of oxidizer. The torch can be formed by a body having the central passage therethrough and an insert residing in the central passage and having an oxidizer passage therethrough. A portion of the insert can have a reduced cross section so as to form an annular fuel chamber, from which the flow of fuel into a passage first section is restricted so as to distribute the fuel against the sidewall. The torch can be provided with a cooling jacket to prevent damage to the body.

Abstract: A fuel injection valve includes: a nozzle body provided with an injection hole at a tip portion; a needle that is located slidably in the nozzle body and includes a seat portion seated on a seat position in the nozzle body; and an air bubble generation means generating air bubbles in a fuel flowing through the nozzle body, and when a curvature radius is R, a length of a curve is L and a constant is a, an inner peripheral shape of the injection hole includes a curving part passing through a region surrounded by a clothoid curve which is expressed by R×L=a2 and of which the constant a is 0.95 and an clothoid curve of which the constant a is 1.05 or a region surrounded by approximate curves of the clothoid curves at a cross-section surface along a direction of axis of the injection hole.

Abstract: In certain embodiments, a feed injector system includes an inner channel configured to convey at least one of a solid fuel feed or a liquid reactant or moderator to a reaction zone. A first oxidizer channel extends around the inner channel, wherein the first oxidizer channel is configured to convey a first oxidizer stream to the reaction zone. A second oxidizer channel extends around the first oxidizer channel, wherein the second oxidizer channel is configured to convey a second oxidizer stream to the reaction zone. Additionally, a third channel extends around the inner channel and the first and second oxidizer channels, wherein the third channel is configured to convey at least one of the solid fuel feed or the liquid reactant or moderator to the reaction zone.

Abstract: A swirler for fuel injection in a gas turbine engine includes a frustoconical swirler body. A first and a second air flow path direct air in generally opposed circumferential directions into the swirler. These air paths intermix and create turbulence. As this turbulence encounters fuel droplets, the fuel is atomized, and uniformly distributed within the air flow. A shear layer is created adjacent an inner surface of the swirler body. In a separate feature, a third air flow path is directed into the air.

Abstract: A nozzle includes a center body and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. A plurality of apertures pass through the center body to the annular passage, and a plenum extends inside the center body and is in fluid communication with the plurality of apertures. A cooling medium is in fluid communication with the plenum. A method for cooling a nozzle includes flowing a cooling medium through a plenum across a surface of the nozzle.

Abstract: A nozzle includes a center body that defines an axial centerline and a shroud circumferentially surrounding at least a portion of the center body to define an annular passage between the center body and the shroud. A plurality of vanes between the center body and the shroud comprise a radially outward portion separated from the shroud. A method for enhancing flow through a nozzle includes flowing a fuel through a center body and flowing a fluid stream across a vane located between the center body and a shroud surrounding at least a portion of the center body. The method further includes flowing the fluid stream between a radially outward portion of the vane and the shroud, wherein the radially outward portion of the vane is separated from the shroud.

Abstract: A combustor nozzle includes a single-piece swirler. The single-piece swirler includes a center body extending axially along the single-piece swirler, a first fuel passage inside the center body, and a plurality of vanes extending radially from the center body. A method for fabricating a combustor nozzle includes casting a single-piece swirler having a center body and a plurality of vanes extending radially from the center body.

Abstract: The invention concerns a spray nozzle for a fluidized bed device, said nozzle comprising a central liquid outlet (15) for a liquid coating agent and an annular air outlet (17) for conveying spraying air coaxially. An enclosing body (1) having a central recess (4) is maintained in a wall of the box of the fluidized bed device. Said enclosing body (1) is connected to a spraying air source through an air duct (6) and an axially mobile nozzle head (14) is centrally mounted inside said enclosing body (1). Said nozzle head (14) is connected to a liquid coating agent source through a liquid duct (10), said liquid duct (10) having a flexible tubular section (12) and being centrally guided inside the air duct (6).

Abstract: A pilot burner (150, 350) for a gas turbine engine delivers an inner non-swirling fuel-oxidant mixture surrounded by an outer swirling fuel-oxidant mixture, thereby providing enhanced mixing with no recirculation zone. At least one fluid-restricting inlet port (166, 366) provides an oxidant to an inner mixing passage (160, 360). The inner mixing passage (160, 360) includes a plurality of fuel outlets (168). An outer annular mixing passage (180) receives oxidant from an upstream port (181) surrounding the inner mixing passage and includes at least one swirler element (186, 386) and fuel outlets (188).

Abstract: Technology is presented for the high efficiency concentration of fine and ultrafine airborne particles into a small fraction of the sampled airflow by condensational enlargement, aerodynamic focusing and flow separation. A nozzle concentrator structure including an acceleration nozzle with a flow extraction structure may be coupled to a containment vessel. The containment vessel may include a water condensation growth tube to facilitate the concentration of ultrafine particles. The containment vessel may further include a separate carrier flow introduced at the center of the sampled flow, upstream of the acceleration nozzle of the nozzle concentrator to facilitate the separation of particle and vapor constituents.

Abstract: Methods and systems for a feed injector are provided. The feed injector system includes a plurality of annular channels that are substantially concentric about a longitudinal axis. The plurality of annular channels direct a flow of fluid substantially axially therethrough from a respective source to a reaction zone. The feed injector system also includes a swirl member extending into the fluid flow path defined in at least one of the plurality of annular channels wherein the swirl member is configured to impart a circumferential flow direction to fluid flowing through the at least one annular channel.

Abstract: Spray nozzle systems and methods of use are described herein. The spray nozzle system may include a stationary tube, a rigid rotor, and a sub-medium supply source. The stationary tube may be in fluid communication with a pressurized air source. The substantially rigid rotor is in fluid communication with the pressurized air source. The substantially rigid rotor includes a substantially rigid conduit that is in fluid communication with the passages of the stationary tube and the rotor. A portion of the conduit is substantially arched such that an outlet of the conduit is offset a radial distance in a radial direction from the rotor axis. Pressurized air ejected from the outlet produces directional components of the pressurized air in the direction of rotation about the rotor axis; and during use, the pressurized air rotates the rotor and sucks sub-medium from the sub-medium supply source into the stationary tube passage.

Abstract: A main swirler of a triple annular configuration that is partitioned by a pre-filmer and a separator is installed in an inlet port of a main air flow channel. The vicinity of the inner wall of the main air flow channel provided with a main fuel injection port is bulged radially outward from the innermost surface (innermost surface of a small swirler) of a main swirler. Further, a distance from the main fuel injection port and the pre-filmer is set such that an effective opening area between the pre-filmer and “the inner wall of the main air flow channel provided with the main fuel injection port” is equal to an effective opening area of the small swirler. The swirling directions of the swirlers of the main swirler are “clockwise”-“counter-clockwise”-“clockwise” respectively along the radial outward direction when the swirling direction of the innermost swirler is taken as “clockwise”.

Abstract: A nozzle includes an inlet at an upstream end of the nozzle, a discharge outlet at a downstream end of the nozzle, and a fluid delivery passage extending between the inlet and the discharge outlet. Exterior and interior walls of the nozzle have downstream tip ends that are relatively longitudinally movable at one or more interfaces. An internal insulating gap is interposed between the interior and exterior walls to insulate fuel from ambient temperature conditions exterior to the nozzle. One or more flexible seal structures internal to the nozzle isolate a portion of the insulating gap from any ambient fluid entering into the gap through the one or more interfaces while providing relative movement between interior and exterior walls of the nozzle.

Abstract: An air-blast fuel injector is disclosed which includes an outer air circuit having an exit portion, an inner air circuit having an outlet configured to direct air toward the exit portion of the outer air circuit, and a fuel circuit radially outboard of the inner air circuit and having an exit communicating with the outer air circuit upstream from the exit portion of the outer air circuit.

Abstract: An air-blast fuel injector is disclosed which includes an outer air circuit having an exit portion, an inner air circuit having an outlet configured to direct air toward the exit portion of the outer air circuit, and a fuel circuit radially outboard of the inner air circuit and having an exit communicating with the outer air circuit upstream from the exit portion of the outer air circuit.