Abstract: Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of fuel and air travelling along each flow slot from its inlet end to its outlet end such that the swirler provides a swirling mix of the fuel and air, at least one vane having an edge adjacent an inlet end of a flow slot configured to generate within the flow slot one or more flow vortices that extend along the slot thereby to enhance mixing of the fuel and air travelling along the slot.

Abstract: A mixing chamber formed in a chassis outfitted with separate inlet channels for conveying pressurized liquid phase and gaseous phase and an outlet channel linking the mixing chamber with a spray nozzle via a flow tube. A separate cylindrical packing chamber is formed in the chassis, within which packing chamber a rotor with vanes is set, the vanes of which rotor intermittently close the inlet channels of the two phases formed in separate sectors of said packing chamber as demarcated by the rotor vanes, wherein the gaseous phase inlet channel is closed alternately with at least one liquid phase inlet channel conveying liquid phase into the mixing chamber via open inter-vane channels, wherein also the sector of the packing chamber containing the gaseous phase inlet channel is separated from the mixing chamber by a continuous section of a partition that closes off the rotor's inter-vane channels within this sector.

Abstract: A combined exhaust gas aftertreatment/dust ejector unit (10) is provided for use with a combustion process (14) and an air cleaner (16) of the combustion process (14). The unit (10) includes an elongate housing (30) containing an exhaust gas aftertreatment device (40) and having a radial exhaust gas outlet (34) to direct an exhaust gas flow (12) radially from the housing (30), and a dust ejector (60) including an ejector outlet (62) positioned in the exhaust gas outlet (34). The exhaust gas outlet (34) and the ejector outlet (62) have elliptical shaped cross sections (68,70), with the ejector outlet cross section (70) spaced inwardly from the exhaust gas outlet (34) to define a reduced flow area (72) for the exhaust gas flow (12) to accelerate the exhaust gas flow (12) past the ejector outlet (62).

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: Disclosed is a cross flow apparatus including a surface and at least one outlet located at the surface. The cross flow apparatus further includes at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet.

Abstract: Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a pluralkity of vanes arranged in a circle, flow slots being defined between adjacent vanes in a circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of air and fuel traveling along each flow slot fom its inlet end to its outlet end such that the swirler provides a swirling mix of the air and fuel, at least one vane being configured to generate a flow vortex that extends from an edge of the vane adjacent an outlet end of a flow slot to within the swirling mix thereby to improve the mix of air and fuel in the swirling mix.

Abstract: A swirler passage is provided for mixing fuel and compressor air with at least two side walls; at least first and second conduits arranged inside at least one of the at least two side walls, the first conduit forming a fuel gas conduit and the second conduit forming an air conduit, the fuel gas conduit connected to a gas fuel supply and the air conduit connected to an air supply; a tube connected to the fuel gas conduit and entirely traversing the air conduit inside the side wall; a fluid passage connected to the air conduit and surrounding the tube; at least one fuel outlet opening of the tube arranged on the side wall; and at least one air outlet opening of the fluid passage arranged on the side wall and surrounding the fuel outlet opening.

Abstract: A fuel nozzle assembly is disclosed. The fuel nozzle assembly comprises an outer burner tube and an inner burner tube defining a pre-mixing annulus therebetween. The fuel nozzle assembly further comprises a swirler assembly, the swirler assembly comprising a plurality of swirler vanes disposed in an annular array about the inner burner tube and configured to interact with primary air upstream of the pre-mixing annulus. The fuel nozzle assembly further comprises an air injection feature configured to flow secondary air into the pre-mixing annulus downstream of the swirler assembly such that the secondary air flows in a generally linear path longitudinally with respect to the pre-mixing annulus and adjacent at least one of the outer burner tube and the inner burner tube.

Abstract: A nozzle structure of a bidet with swirling water current is provided, in which a user controls water spraying angle of water current sprayed from an outlet of a cleaning nozzle, and the water current with swirling force is sprayed in a circular pattern without causing an eccentricity, thereby increasing cleaning power and reducing water consumption.

Abstract: A fuel nozzle including a swirler assembly that includes a shroud, a hub, and a plurality of vanes extending between the shroud and the hub. Each vane includes a pressure sidewall and an opposite suction sidewall coupled to the pressure sidewall at a leading edge and at a trailing edge. At least one suction side fuel injection orifice is formed adjacent to the leading edge and extends from a first fuel supply passage to the suction sidewall. A fuel injection angle is oriented with respect to the suction sidewall. The suction side fuel injection orifice is configured to discharge fuel outward from the suction sidewall. At least one pressure side fuel injection orifice extends from a second fuel supply passage to the pressure sidewall and is substantially parallel to the trailing edge. The pressure side fuel injection orifice is configured to discharge fuel tangentially from the trailing edge.

Abstract: A gas turbine equipped with a burner, which has an axial swirler for generating turbulence in a flow of comburent air, a secondary supply line of fuel gas, a main supply line of fuel gas arranged concentrically around the secondary line, and a pilot line of fuel gas. Accordingly, the burner is ignited by firing a spark and feeding, towards the spark, comburent air and fuel gas which is synthesis gas.

Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.

Abstract: A mixer having a unitary construction is disclosed comprising an annular housing having an axis and at least a first swirler having a plurality of vanes arranged circumferentially around the axis such that circumferentially adjacent vanes form at least one flow passage that is oriented at least partially in an axial direction with respect to the axis. In another exemplary embodiment, a mixer having a unitary construction is disclosed comprising a swirler having a plurality of radial vanes arranged circumferentially around the axis and oriented at least partially in a radial direction.

Abstract: Provided is a nozzle tip assembly having a radially inner annular wall and a radially outer annular wall at least partially surrounding the radially inner annular wall and forming therebetween a flow passage for routing air from an upstream end of the nozzle tip assembly to a downstream end of the nozzle tip assembly. Additionally, the nozzle tip assembly has a bleed path for bleeding air from the downstream end of the flow passage into a heat shield that surrounds a fuel delivery device that directs fuel to a plurality of spraywells.

Abstract: An exhaust-gas system has an exhaust-gas pipe for guiding an exhaust-gas flow and an injection nozzle mounted to the exhaust-gas pipe for injecting reducing agent into the exhaust-gas flow. Downstream of the injection nozzle, the exhaust-gas pipe branches into at least two exhaust-gas lines. A fluid divider, formed with a front face that faces upstream into the gas flow, is disposed between the injection nozzle and the branching. The front face is oriented with respect to the cross section of the exhaust-gas pipe and the injection nozzle, such that the exhaust-gas flow and the medium are divided among the exhaust-gas lines in a predefined dividing ratio.

Abstract: A swirler for premixing a flow of fuel and a flow of air provided to a burner for a gas turbine engine is provided. The burner is provided with a swirler for mixing the air and the fuel and wherein the swirler is provided with swirler wings, wherein a channel formed between two adjacent swirler wings defines a passage. The swirler includes one fuel tube for gaseous fuel positioned in parallel on each side of a mixing rod in the passage, wherein the fuel tubes are provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for efficiently distributing fuel in a flow of air passing through the swirler passage.

Abstract: An applicator assembly for mixing at least a first and a second component is provided. The applicator assembly includes a manifold configured for operable engagement with first and second source of component, the manifold including first and second component channels therethrough, an elongated shaft extending distally from the manifold, the elongated shaft including first and second component lumens extending the length thereof, the first and second component channels in fluid communication with the first and second component lumens, a tip assembly defining a first chamber, an intermediate chamber and a final chamber, wherein the first chamber is configured to receive a distal end of the elongated shaft, the second chamber is configured to receive an insert, and the final chamber is configured to receive the first and second components prior to the mixture being ejected from an outlet defined in the distal end of the tip assembly.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: Provided is a manual air-actuated spray paint apparatus and associated method for evenly disbursing paint in a controlled manner. Such an apparatus preferably includes a portable reservoir for holding the paint therein and a hand-actuated paint applicator removably coupled thereto. A mechanism for simultaneously discharging a single stream of paint and a volume of air may also be included. A discharge spout is removably mated to and in fluid communication with the paint applicator for mixing the single paint stream and the volume of air as they pass through the spout. A trigger is pivotally mated to the housing and is articulated between tensioned and released positions to activate the paint discharging mechanism. When the trigger is engaged, the paint is directed upwardly out of the reservoir and travels out the discharge spout to be applied to the surface intended to receive the paint.

Abstract: The present invention relates to a flow discharge device (30) for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve (34) disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means (50) disposed between the valve (34) and the second gaseous fluid. The swirler means (50) comprises a plurality of radially extending circumferentially spaced vanes (61, 63, 65). In use the swirler means (50) swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.

Abstract: A swirling device for injecting a medium into a turbine is provided. The swirling device includes a central axis, a central passage in an axial direction along the central axis and an outer perimeter. The swirling device further includes a first duct and a second duct. The first duct and the second duct are adapted for guiding the medium from a region surrounding the outer perimeter to the central passage. The first duct includes a first depth in the axial direction and the second duct includes a second depth in the axial direction. The first depth and the second depth are different.

Abstract: A fuel nozzle for imparting swirl to a fuel/fuel-air mixture is provided. The fuel nozzle includes a holding unit and a nozzle insert, wherein the holding unit and the nozzle insert form a flow path and subsequently a swirl chamber, wherein the nozzle insert includes an inlet start and an inlet end. The inlet start and the inlet end are bent in a substantially circular manner such that an unbroken circle is formed, such that a fuel flowing into the swirl chamber has imparted to it a radially inwardly directed circular, in particular spiral movement. A burner and a gas turbine are also provided.

Abstract: A swirler for premixing a flow of fuel and a flow of air provided to a burner for a gas turbine engine is provided. The burner is provided with a swirler for mixing the air and the fuel and wherein the swirler is provided with swirler wings, wherein a channel formed between two adjacent swirler wings defines a passage. The swirler includes one fuel tube for gaseous fuel positioned in parallel on each side of a mixing rod in the passage, wherein the fuel tubes are provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for efficiently distributing fuel in a flow of air passing through the swirler passage.

Abstract: A burner 1 for combustion chamber is provided with a cylindrical mixing portion 3 that mixes air for combustion (oxidizing agent) and fuel in the interior thereof and has one end 3a that opens to a combustion portion 2; a spray nozzle (fuel spraying portion) 5 that sprays fuel in the mixing portion 3, being disposed on another end 3b of the mixing portion 3; first blowing ports 6 that introduce the air for combustion to the mixing portion 3 to form a swirling flow with the fuel, being disposed to open to the inner wall of the mixing portion 3; and second blowing ports 7 that additionally introduce the air for combustion to the mixing portion 3, opening in a direction different from the first blowing ports 6 and being disposed further to the other end 3b side of the mixing portion 3 than the swirling flow.

Abstract: A gas turbine engine pilot assembly includes a swirler having high and low pressure sides. A hood at least partially encloses the swirler on the high pressure side. The hood is secured over the swirler, in one example. The hood includes an aperture creating a tortuous path from the high pressure side to the low pressure side through the swirler. The hood reduces the differential pressure across the swirler by reducing the velocity and pressure of the air before entering the swirler. In one example, the hood includes first and second spaced apart walls interconnected by a perimeter wall. The walls form a generally annular structure, in one example. At least one of the walls includes an array of apertures communicating with a cavity interiorly arranged within the walls upstream from the swirler. Air from the high pressure side flows through the apertures and is slowed before passing through the swirler and into a combustion chamber.

Abstract: A vortex-generating nozzle-end ring includes a body having an outer periphery and an aperture disposed through the body, the aperture defining an inner periphery of the body, the body being adaptable to the end of a nozzle, and at least one tab extending from the inner periphery radially inwardly toward the center of the aperture. In another embodiment, a nozzle includes a housing having a central longitudinal axis having an inlet and an outlet; a vortex-generating nozzle-end ring disposed on the outlet, including a body having an outer periphery and an aperture disposed through the body, the aperture defining an inner periphery of the body, the body being adaptable to the end of nozzle; and at least one tab extending from the inner periphery radially inwardly toward the center of the aperture.

Abstract: A burner for burning substances, in particular uncondensed offgas from a condenser of a drying installation, is intended to be fed with fuel, oxidizer and substances to be burned. The burner includes an axial feed inlet for feeding the burner with offgas and a set of fuel injection nozzles distributed around the axial feed inlet.

Abstract: A pressurized spray system. The spray system has a flow path through which contents must pass to be dispensed from the system to the atmosphere. By maintaining the proper proportions of restrictions in the flow path to the spray nozzle exit orifice, a relatively constant mean particle size distribution may be obtained throughout the life of the spray system as the pressure decays.

Abstract: The invention relates to a two-fluid nozzle with a main nozzle, having a mixing chamber and a nozzle orifice connected to said mixing chamber and positioned downstream thereof. According to the invention a ring of secondary air nozzles surrounding the nozzle orifice is provided. Use, e.g. for evaporation cooling.

Abstract: A swirler arrangement for injecting a fluid into a tubular swirling chamber is provided. The swirler arrangement includes a first radial swirler device and a second radial swirler device. The swirler arrangement is fixed around an internal circulation zone of the tubular swirling chamber. The first radial swirler device includes first vanes, wherein the first vanes are formed to inject the fluid into the internal circulation zone with a first injecting angle. The second radial swirler device includes second vanes, wherein the second vanes are formed to inject the fluid into the internal circulation zone with a second injecting angle. The first injecting angle and the second injecting angle are defined by an angle between an injecting direction of the fluid and the tangential direction along the inner surface. A method of injecting a fluid into a tubular swirling chamber by the swirler arrangement is also provided.

Abstract: A fuel injector for a gas turbine engine may include a pilot assembly extending along a longitudinal axis. The pilot assembly may be configured to direct a pilot fuel-air mixture to a combustor of the gas turbine engine. The fuel injector may also include a rich catalyst module circumferentially disposed about the pilot assembly. The catalyst module may be configured to simultaneously direct a stream of compressed air and a stream of first fuel-air mixture therethrough without intermixing. The fuel injector may also include a post mix zone disposed downstream of the catalyst module. The post mix zone may be configured to mix the compressed air and the first fuel air mixture to create a main fuel-air mixture. The fuel injector may further include an air swirler disposed downstream of the post mix zone. The air swirler may be configured to direct the main fuel-air mixture to the combustor without intermixing with the pilot fuel-air mixture.

Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor is provided. The fuel injector has an annular flow passage which conveys fuel to a prefilming lip at an end of the flow passage. The fuel injector also has plurality of fuel distributor slots which are circumferentially spaced around and in fluid communication with the other end of the flow passage to deliver respective fuel streams into the flow passage. The slots are configured so that the fuel streams enter the flow passage at a swirl angle of at least 80° relative to the axis of the flow passage.

Abstract: A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.

Abstract: A bearing plate assembly for a turbine engine fuel injector includes a bearing plate 30, with an opening 80 bordered by a race 82. A swivel ball 90 nests inside the race and is rotatable relative thereto. A lock, which may be a tip bushing 108 resists disengagement of the swivel ball from the race. A fuel injector nozzle 38 extends through an opening 98 in the swivel ball. During engine operation, the ball can swivel inside the race to accommodate rotational movement of the nozzle about lateral and radial axes.

Abstract: A fuel nozzle having a fuel conveying member surrounded by a sheath. An air passage is defined between the fuel conveying member and the sheath for directing air to an air swirler provided at one end of the fuel conveying member. At one flow director is provided in the air passage for promoting air and fuel uniformity and distribution at a spray tip of the fuel nozzle.

Abstract: A retaining ring is provided for use in conjunction with a carburetor assembly having a flow passage therethrough for conducting a fuel-air mixture into a combustion chamber, the carburetor assembly comprising an air flow modifier and a fuel injector receiving element adjacent thereto. The retaining ring comprises a collar configured to engage the fuel injector receiving element so as to maintain its position adjacent the air flow modifier, and a retaining portion coupled to the collar and configured to engage the air flow modifier to secure the airflow modifier to the combustion chamber. The retaining portion cooperates with the collar to form an aperture through the retaining ring for receiving the carburetor assembly.

Abstract: In one embodiment, a flow switch can comprise: a deflector having a diverging upstream portion; an aperture located in a downstream portion of the deflector; and a divider disposed downstream of the deflector. The deflector can be capable of diverting a fluid stream that contacts the upstream portion, around the deflector. The aperture can be capable of allowing a flow of a displacing fluid such that the displacing fluid can inhibit the diverted fluid stream from converging to pass through the divider. The divider can be capable of allowing a flow of the displacing fluid therethrough.

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: An absorbent composite comprising a bound particulate absorbent polymer in which two or more nearly spherical absorbent polymer particles are bound to each other and a web-like absorbent polymer, wherein the bound particulate absorbent polymer and the web-like absorbent polymer are bound to a substrate. The composite has a large absorption and a high absorbing speed in which the absorbent polymer is kept uniformly dispersed on the support throughout before and after absorption.

Abstract: A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of a can-type configuration which combusts fuel premixed with air and delivers the hot gases to a turbine. Fuel is premixed with air through a swirler and is delivered to the combustor with a high degree of swirl motion about a central axis. This swirling mixture of reactants is conveyed downstream through a flow path that expands; the mixture reacts, and establishes an upstream central recirculation flow along the central axis. A cooling assembly is located on the swirler co-linear with the central axis in which cooler air is conveyed into the prechamber between the recirculation flow and the swirler surface.

Abstract: A modular fuel nozzle air swirler for a gas turbine engine has a body defining a fuel passage extending between an inlet end and a discharge end of the body. An annular cap is removably secured to the discharge end of the body via cooperating interlocking members.

Abstract: A gas mixing system for a semiconductor wafer processing chamber is described. The mixing system may include a gas mixing chamber concentrically aligned with a gas transport tube that extends to a blocker plate. The gas mixing chamber and the transport tube are separated by a porous barrier that increases a duration of gas mixing in the gas mixing chamber before processes gases migrate into the transport tube. The system may also include a gas mixing insert having a top section with a first diameter and a second section with a second diameter smaller than the first diameter and concentrically aligned with the top section. The processes gases enter the top section of the insert and follow channels through the second section that cause the gases to mix and swirl in the gas mixing chamber. The second section extends into the gas mixing chamber while still leaving space for the mixing and swirling around the sidewalls and bottom of the mixing chamber.

Abstract: The catching nozzle according to the invention for a powder conveying device has a tubular powder flow duct and a shoulder, with which the position of the catching nozzle is predetermined in the powder conveying device and that is arranged between a upstream catching nozzle section and a downstream catching nozzle section. The shoulder has a duct for dosage air, wherein the duct connects the upstream catching nozzle section to the downstream catching nozzle section. The downstream catching nozzle section is developed such that it forms, with a hose socket that can be pushed over the downstream catching nozzle section, another duct for dosage air in order to lead the dosage air up to the downstream end of the catching nozzle.

Abstract: A multi-purpose showerhead includes a flexible conduit having a head end coupled to an water outlet of a faucet, a first water supply channel and a first water return channel being fitted within the flexible conduit, wherein the first water supply channel is connected to the water outlet of the faucet while the first water return channel is provided with a back flow opening extending outward near the head end; a showerhead main body having a shank member and a head member at the top of the shank member, the inside thereof being brought in a connected state. Meanwhile, a second, third, and fourth water supply channels as well as a second, third, and fourth water return channels are available. Moreover, return flow chambers and a blade wheel are disposed within the head member. In addition, a brush body and water-spraying perforations are fitted on the surface thereof. The adjustment knob permits the control of the switching of the water flow channels.

Abstract: The invention provides a method and apparatus for introducing a high-density hydrocarbon liquid into a hydrocracking reactor. The method comprises atomizing the high-density hydrocarbon liquid and injecting the atomized liquid into the hydrocracking reactor. The method may also comprise mixing hydrogen with the high-density hydrocarbon liquid prior to atomizing the high-density hydrocarbon liquid. The apparatus comprises an injection valve for introducing a high-density hydrocarbon liquid into a hydrocracking reactor comprises an atomizer coupled to receive the high-density hydrocarbon liquid. The atomizer comprises a nozzle configured to atomize the high-density hydrocarbon liquid and inject the high-density hydrocarbon liquid into the hydrocracking reactor. The injection valve may also comprise a mixer coupled to receive hydrogen and the high-density hydrocarbon liquid. The mixer may be configured to mix the hydrogen and high-density hydrocarbon liquid and deliver the mixture to the atomizer.

Abstract: Systems and methods for producing ozonated water on demand. In particular, these systems comprise a water source, an ozone source, and a nozzle that mixes ozone and water to form a highly concentrated, ozonated water solution. Instead of requiring the ozonated water to be re-circulated to achieve a desired ozone concentration, the nozzle is configured to form the ozonated water solution in a single pass through the nozzle. Additionally, instead of requiring the ozonated water to be discharged into a pressurized tank to increase ozone absorption, the nozzle allows the ozonated water to be openly discharged. In some cases, the nozzle comprises a venturi with multiple ozone inlets to increase mixing. Additionally, in some cases the nozzle comprises a single pass mixing mechanism that mixes the water and ozone to form the high concentrate, ozonated water solution in a single pass through the nozzle.

Abstract: The present invention relates to an apparatus and a process for dissolving gas in a liquid is provided. The process comprises: tangentially introducing a liquid into a cylindrical chamber having a cylindrical inner wall with sufficient volume and pressure to develop a vortex in the flowing liquid; introducing gas into the flowing liquid during at least a portion of its travel along vessel, the gas being introduced orthogonally to the stream through means located at the chamber inner wall for developing gas bubbles within the liquid. The apparatus comprises: a cylindrical chamber having a cylindrical inner wall, the chamber being oriented in any direction enclosed at both ends and with an entry port to introduce liquid to develop a spiral flow of liquid along the chamber inner wall toward the output end, a porous wall to permit the introduction of gas orthogonally into the stream to develop gas bubbles within the stream, and an exit port to discharge the mixture of gas bubbles and liquid.

Abstract: An apparatus and method for minimizing and/or preventing thermal degradation of fuel in a fuel injector is disclosed. The body of the injector includes a fuel gallery with a contoured scarf formed therein. The scarf is configured to minimize and/or prevent fuel recirculation thus reducing the likelihood that fuel will dwell in an area long enough to sufficient to cause the degradation of the fuel.

Abstract: The invention relates to the field of turbomachines and concerns a device (20a, 20b) for injecting a mixture of air and fuel into a combustion chamber (4) of a turbomachine (1). It relates more specifically to an injection device (20b) provided with a novel sliding bushing (30b) and with a novel annular cup (50b) for retaining the sliding bushing, making it possible to improve the air feed of the injection device.

Abstract: Apparatus for mixing two fluids has separate supply lines for delivering the fluids to a mixing head. Flow rate of fluid in one supply line is monitored by arranging a pressure transducer to measure a pressure drop across an orifice in an orifice plate arranged in the supply line and a controller is responsive to the detected flow rate to control flow rate of fluid in the other supply line to achieve a desired flow ratio of both fluids at the mixing head for producing a mixed fluid having the correct proportions of both fluids. The fluids may be a concentrate syrup and a plain or carbonated water to produce a beverage.