Abstract: A low-pollution combustor and a combustion control method therefor. The low-pollution combustor includes a combustor head including a primary combustion stage and a precombustion stage, the primary combustion stage including a primary-combustion-stage channel and a primary-combustion-stage swirler disposed in the primary-combustion-stage channel. The primary combustion stage includes a pre-film plate disposed in the primary-combustion-stage channel, and the pre-film plate is radially divided into an outer-layer pre-film plate and an inner-layer pre-film plate.

Abstract: The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to utilize different fuel mixtures derived from gasification of a solid fuel. Combustion of the different fuel mixtures within the combustor can be facilitated by arranging elements of the combustor controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel mixtures.

Abstract: A combustor includes: a casing having an air chamber filled with air; at least one mixing passage forming member forming at least one mixing passage which is connected at an inlet side to the air chamber and at an outlet side to a combustion chamber and having an inlet at the inlet side of the at least one mixing passage so as to communicate with the air chamber; and at least one fuel nozzle disposed inside the air chamber and having a fuel injection hole, positioned upstream of the inlet of the at least one mixing passage forming member, for injecting fuel downstream.

Abstract: A system and method are provided for continuous monitoring and controlling of aircraft braking that can reduce brake wear and aircraft operating costs through the retention of carbon brake powder from the brakes or addition of carbon powder in a device mounted with respect to the brake disc stack. The use of carbon powder reduces brake wear by providing small particles between the brake discs, acting as a buffer between the brake discs when the brake stack is clamped together. Moreover, when carbon powder or small particles are used at application, such use reduces the roughness of the carbon surface and reduces the number of large particles from braking off the carbon surface, thereby reducing brake wear. Adaptive or selective braking may be used in conjunction with carbon powder to further reduce carbon brake wear.

Abstract: A pool nozzle assembly according to one embodiment includes a base having a hollow interior, an open first end, an open second end that is configured for securement to a wall of a pool. The pool nozzle assembly including a nozzle including a hollow ball portion and an elongated extension that protrudes radially outward from one end face of the hollow ball portion. A cover is configured to mate with the base to capture the ball portion between the cover and the base, the cover having an opening through which the elongated extension passes through.

Abstract: A fuel injection system includes an outer support defining a fuel manifold and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extending in an axial direction from the feed arm for feeding respective injection nozzles. The feed arm defines a plurality of fuel passages therethrough in fluid communication with the fuel manifold and outlet openings to supply fuel from the fuel manifold to the outlet openings. A heat shield extends from the outer support to the inner support and extends about the outer support and the feed arm to provide heat shielding to the fuel manifold and the fuel passages.

Abstract: A diffuser for distributing spray or insects from an aircraft is mounted on an aircraft and comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end for distribution of the insects. A nozzle surrounds the second end and a tube cover surrounds the second end within the nozzle. The tube cover has an aerofoil, or wing-shaped, cross section. The nozzle shape sets up an air transition volume between the aircraft and ambient air designed for a maximum wind shear over any cubic centimeter volume within the air transition volume to be less than 60 km/h, and therefore allowing distribution of insects such as mosquitoes from the aircraft without damage, or allowing aerosols to be spread as large droplets.

Abstract: A fuel injection device for a gas turbine combustor includes a pilot fuel injector disposed on an axis of the fuel injection device; an annular main fuel injector encircling the pilot fuel injector; and a plurality of main fuel injection holes formed in the main fuel injector and spaced circumferentially from each other for injecting fuel axially rearward. The main fuel injector includes an annular fuel passage forming portion, an inner ring portion on an inner peripheral side of the fuel passage forming portion, and an outer ring portion on an outer peripheral side of the fuel passage forming portion. One of a space between the fuel passage forming portion and the inner ring portion and a space between the fuel passage forming portion and the outer ring portion forms a pilot fuel supply passage, and the other one forms a main fuel supply passage.

Abstract: A combustor nozzle assembly and a gas turbine having the combustor nozzle assembly includes a nozzle casing for receiving compressed air from a compressor, a curved surface at a corner continuing from a surface of the inner surface thereof that is perpendicular to the direction of the compressed air, a fuel spray hole formed at the curved surface, and a fuel chamber having a predetermined volume and formed inside the curved surface to supply fuel into the nozzle casing through the fuel spray hole.

Abstract: A combustor assembly includes a volute wall extended annularly around a combustor centerline, extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline, and defining a combustion chamber therewithin, an annular inner wall extended at least partially along a lengthwise direction from the volute wall, an annular outer wall extended at least partially along the lengthwise direction from the volute wall, the annular inner wall and the annular outer wall being separated along a radial direction from the combustor centerline, and a primary flow passage being defined between the annular inner wall and the annular outer wall in fluid communication with the combustion chamber, and a flow passage wall extending between a portion of the volute wall and a portion of the annular outer wall.

Abstract: A fuel injector assembly for a gas turbine engine is generally provided. The first fuel injector includes a first centerbody surrounding a first walled fuel injection circuit. A first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit. The first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit. The first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody. The plurality of cooling openings is in fluid communication with the cooling circuit. The first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.

Abstract: A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a premixing chamber formed between an outer annular shroud and an inner annular hub, a number of swirler vanes disposed about the premixing chamber between the outer annular shroud and the inner annular hub, one or more liquid fuel injectors positioned about the swirler vanes, and a flow of liquid fuel in communication with the one or more liquid fuel injectors.

Abstract: A nozzle and methods of gas stripping utilizing the nozzle are provided. A nozzle is provided comprising a ceramic nozzle assembly comprising an inlet at one end of a cylindrical portion, an outlet at one end of a conical portion; the cylindrical portion transitioning to the conical portion at an end of the cylindrical portion distal from the inlet; the conical portion transitioning to the cylindrical portion at an end of the conical portion distal from the outlet; and a ceramic vane assembly within the cylindrical portion; the vane assembly comprising a central vane support located substantially concentrically within the cylindrical portion, and a plurality of angled vanes extending from the central vane support to an inner wall of the cylindrical portion; wherein the ceramic nozzle assembly and the ceramic vane assembly are manufactured such that the two assemblies comprise a single piece of ceramic.

Abstract: A fuel injection device for a gas turbine can include streamlined bodies arranged adjacent to one another in a circumferential direction. Each streamlined body can have a fuel nozzle on its trailing edge. The streamlined bodies can be split into at least a first group of streamlined bodies and a second group of streamlined bodies. All the streamlined bodies in the first group being the same and being different from the streamlined bodies in the second group. The first group of streamlined bodies includes at least two streamlined bodies adjacent to one another. Alternatively, the streamlined bodies are clustered in sets of two adjacent streamlined bodies. As yet another alternative, the streamlined bodies can be arranged such that the fuel injection device has a maximum of four-fold rotational symmetry in the plane perpendicular to the central axis.

Abstract: A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.

Abstract: A combustion burner includes a nozzle, a swirl vane having a fuel injection hole, the swirl vane being disposed in an air flow passage of an annular shape extending along an axial direction of the nozzle around the nozzle, and a partition plate having an annular shape and partitioning at least a region of the air flow passage in a radial direction of the nozzle, so as to divide at least the region into an inner flow passage facing an outer peripheral surface of the nozzle and an outer flow passage disposed on an outer side of the inner flow passage with respect to the radial direction. The fuel injection hole is disposed in the outer flow passage of the air flow passage. An end portion on an upstream side of the partition plate is disposed upstream of the fuel injection hole in the axial direction.

Abstract: A new type of burning device for producing hydrohalogen compounds.

Abstract: The compound nozzle for a cement 3D printer to produce thermally insulated composite cement is useful for producing composite thermally insulated cement sections using a 3D printer. The nozzle includes an insulation nozzle concentrically disposed in the central discharge orifice of the compound nozzle to produce a stream of insulation media axially surrounded by a stream of cement mixture extruded from the nozzle to form a wall with a cement exterior and an insulation interior. A motor-driven auger is controlled by a controller, and the cement is supplied from the top either manually or by a concrete pump. The insulating material is supplied to the insulation nozzle by a separate line that uses another pump. The system includes a cleaning mechanism to clean the internal components of the compound nozzle using water jets and a drying system to dry the internal components without disassembling the system.

Abstract: Pilot fuel injectors for combustors of gas turbine engines are provided. The pilot fuel injectors include a swirler having an exit into a combustion chamber of the combustor and a nozzle located within the swirler. The nozzle includes a primary fuel circuit configured to atomize fuel dispensed therethrough and a secondary fuel circuit having a first sub circuit having at least one injection aperture a first injection depth from the exit of the swirler and a second subcircuit having at least one second injection aperture located at a second injection depth from the exit of the swirler, wherein the first injection depth is greater than the second injection depth.

Abstract: A fuel injector assembly for a combustor is provided, including a fuel nozzle having an axial inflow swirler and one or more radial inflow swirlers spaced radially outward of the downstream end of the fuel nozzle and mounted to the combustor, wherein the airstreams produced by the swirlers airblast atomize fuel films produced by the fuel nozzle.

Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

Abstract: A burner assembly (100) for flaring low calorific gases, such as methane with high carbon dioxide content, may be configured to provide a gradual decrease in flow velocity. The burner assembly (100) may include a conical deflector (140) that creates a relatively large recirculation zone (154) downstream of the deflector (140), thereby to stabilize fluid flow. A swirl inducing structure positioned in a final stage of the burner assembly (100) further stabilizes the fluid flow and flame at different gas flow rates.

Abstract: A combustion burner includes a nozzle and a swirl vane disposed in an axial flow path extending along an axial direction of the nozzle. The swirl vane includes a tip portion for swirling gas, the gas flowing through a radially-outer region of the axial flow path, and a root portion disposed on an inner side in a radial direction of the nozzle, the root portion having a cutout on a side of a trailing edge. The radially-outer region and a radially-inner region of the axial flow path communicate with each other, at least in a range in the axial direction in which the swirl vane is disposed. The swirl vane has a pressure surface, a downstream region of the pressure surface of the root portion being defined by the cutout as a curved surface which curves in a direction opposite to the swirl direction toward the trailing edge.

Abstract: The invention relates to a shower arm with a torus regulator and a magnetic ring that is comprised of a body (1) with a body head (25), a bell (2), a cover (3), a torus (4), a mixing element (5), a ring (6), a pin (7) and a barrier (9) on the cover, a barrier (8) and a nozzle (10) on the bell, a cavity (11) for water inlet, an inlet (12) of water into the shower head (25), a space (13), a gap (14) on the mixing element, a chamber (15), gaskets (16) and (17), a thread (18), a space (19) for directed flow, pins (20) and a groove (21) on the ring, a groove (22) on the bell, a thread (23) for connecting a hose, a support surface (24), a magnetic ring (26) and an output spray (27) of water and air. When the water circulates within the space (19) underneath the torus (4), negative pressure—vacuum occurs from both the internal and the external sides of the torus cross-section that conditions suction of the air from the chamber (15) of the cone of the bell (2). This air is suctioned through the nozzle (10).

Abstract: A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.

Abstract: A gas turbine combustor includes a plurality of fuel nozzles, a premixing plate, and a plurality of annular flow sleeves. The plurality of annular flow sleeves includes an inner annular flow sleeve and an outer annular flow sleeve. The plurality of annular flow sleeves is formed to divide an airflow passage into a plurality of flow passages including an inner and an outer circumferential flow passages. The airflow passage is formed around the plurality of fuel nozzles. The airflow passage extends from an upstream side of the plurality of fuel nozzles to fuel injecting ports of the fuel nozzles. The plurality of annular flow sleeves rectifies a flow of air in each of the flow passages and guiding the flow of air to the fuel injecting ports of the fuel nozzles.

Abstract: The present disclosure provides a spraying device and a coating method. The spraying device comprises a first spray unit and a second spray unit. The first spray unit is configured to spray a first solution for wetting a surface of a substrate, and the second spray unit is configured to spray a second solution for coating the surface of the substrate. During spraying, the second spray unit and the first spray unit advance in the same direction and the second spray unit is arranged behind the first spray unit in the advancing direction. In the present disclosure, the coated liquid diffuses across the surface of the substrate more quickly and uniformly, the alignment film formed on the surface of the substrate has a uniform thickness, thus avoiding mura due to an alignment film with a non-uniform thickness and improving quality of the display panel.

Abstract: An injection system for a turbine engine combustion chamber is provided. The injection system includes a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. The first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector.

Abstract: A first head of a beauty device includes a stirring mechanism stirring bubbles, and a head case provided with an opening for allowing the bubbles stirred by the stirring mechanism to pass through. When the first head is used while being mounted to the body of the beauty device, bubbles are supplied to the stirring mechanism from the body of the beauty device. In a state where bubbles supplied to the stirring mechanism are present between the stirring mechanism and the skin, the bubbles are stirred and moved between the stirring mechanism and the skin by the stirring mechanism, and thus impurities of the skin are removed by the bubbles.

Abstract: A method for treating a gas is shown which includes the steps of: injecting a powdered compound into the gas line, injecting an aqueous phase in droplet form into the line, capturing pollutants from the gases, and recovering the powdered compound separately. The step for injecting an aqueous phase in droplet form is done so as to moisten those particles of powdered compound in the gas line, when they are injected.

Abstract: A combustor for a gas turbine generally includes a radial flow fuel nozzle having a fuel distribution manifold, and a fuel injection manifold axially separated from the fuel distribution manifold. The fuel injection manifold generally includes an inner side portion, an outer side portion, and a plurality of circumferentially spaced fuel ports that extend through the outer side portion. A plurality of tubes provides axial separation between the fuel distribution manifold and the fuel injection manifold. Each tube defines a fluid communication path between the fuel distribution manifold and the fuel injection manifold.

Abstract: A well test burner system includes a plurality of burner nozzles. At least one of the burner nozzles includes a well product inlet, an air inlet, an air/well product mixture outlet, and an automatic valve. The automatic valve is configured to automatically adjust a ratio of air and well product supplied to the air/well product mixture outlet based on the well product received via the well product inlet.

Abstract: A method for lubricating rolls, especially work rolls (2, 3) of a rolling stand, and rolling stock (6) passed between the rolls during the rolling operation, in which a lubricant-gas mixture, a lubricant-water-gas mixture, a lubricant-water mixture and/or a grease-medium mixture is applied to the rolls (2, 3) or the rolling stock (6) on the run-in side of the rolling stand, is characterized by the fact that the mixture is prepared with at least one mixing device (14, 17, 27, 29, 31, 35) in the area upstream of the rolling stand.

Abstract: The present invention is provided with an assembly for producing forficiform spray, which comprising a base body, the base body is disposed with a waterway inside; the waterway includes an inlet, an outlet and a circular cavity, the circular cavity is connected between the inlet and the outlet; the diameter of the outlet is larger than that of the inlet, the outlet is conical shaped with big end down; the joint of the inlet and the circular cavity is chamfered arc. When water flows into the cavity from the inlet, with the characteristics of the water, the outlet water forms a forficiform water of periodicity open and close; the present invention is full in granule, better suction effect, visual effect and massage effect.

Abstract: A nozzle tip for a three-way syringe device, including a co-axial tube assembly having attachment feature adapted for releasable attachment of the nozzle tip to a syringe device, and wherein the tube assembly includes an outer tube and an inner tube, the inner tube having an end section including an inclined outlet face, and wherein the inner tube is tight-fit against the interior surface of the outer tube. The nozzle tip is included in a dental apparatus including a three-way syringe device.

Abstract: The invention relates to a combustion method for glass melting, in which a flame is created both by a liquid fuel pulse and a single gaseous fuel pulse, characterized in that the fraction of the total power due to the liquid fuel varies between 20 and 80%, and in that the specific gaseous fuel pulse is limited to a value that is sufficiency low so that the NOx content of the flue gases produced does not exceed 800 mg/Sm3 for a cross-fired furnace and 600 mg/Sm3 for an end-fired furnace; an injector for implementing this method; a burner comprising one or more such injectors; a furnace comprising at least one such burner.

Abstract: A fuel system includes an external cool air source, and a fuel injector. The fuel injector includes a fuel circuit, an outer air circuit, an inner air circuit, and an outlet. The fuel circuit receives liquid fuel from a fuel inlet. The outer air circuit receives cool air from the cool air source and substantially surrounds the fuel circuit. The inner air circuit is in fluid communication with the outer air circuit and a portion of the fuel circuit substantially surrounds the inner air circuit. The outlet provides atomized fuel from the fuel circuit, outer air circuit and inner air circuit to a combustor.

Abstract: An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough. The swirling air flow is used by the injector to produce an atomised fuel spray. The air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the air passage. Viewed on a longitudinal section through the injector, the air passage has a bend downstream of the swirler, the bend changing the direction of the air passage. The vanes are configured to introduce a radial component to the air flow exiting the swirler, the radial component guiding the air flow around the bend.

Abstract: Foam dispensers, refill units for foam dispensers, and liquid pumps for use in foam dispensers are disclosed herein. In one embodiment, an inverted foam pump includes a compression chamber having an inlet valve and an outlet valve. The compression chamber is in fluid communication with a flow restrictor, an atomizer, a mixing chamber, a foaming chip and an outlet. The inlet valve, outlet valve, flow restrictor, atomizer, mixing chamber, foaming chip and outlet extend along a common axis. An air inlet is included that extends into the mixing chamber; the air inlet is an opening to atmospheric pressure. During operation, the liquid pump is located below the liquid container and liquid flowing from the compression chamber is accelerated and atomized. The atomized liquid enters the mixing chamber at a velocity sufficient to draw in air from the air inlet to mix with the liquid to form a foam.

Abstract: The present invention provides a shower apparatus that allows the user to have a shower stream with a voluminous feel, even when a small volume of water is discharged, and also with a stimulus sensation arising from water being discharged in a pulsating manner. A shower apparatus F1 periodically changes the volume of air taken into an aeration unit 43 by oscillating a main water stream ejected toward the aeration unit 43 from a throttle unit 42 in a direction crossing the direction of the ejection, so that the bubbly water discharged from a water discharge unit 44 creates a pulsating shower stream.

Abstract: An internal mix air atomizing spray nozzle assembly having a nozzle body that defines a central liquid flow passage, an air guide for directing pressurized air within the nozzle, and a downstream air cap having an upstanding impingement post and a plurality of discharge orifice defining passages about the impingement post. The air cap passages each are oriented at compound angle with respect to a central axis for discharging atomized liquid flow streams in a conical spray pattern swirling in a predetermined rotative direction about the central axis, and the impingement post has a diffuser cap that defines a flat central liquid impingement surface and an outer annular array of non radial diffuser veins for directing the atomized liquid and pressurized air in a swirling fashion about the impingement post in the same relative direction as the swirling spray pattern from the air cap passages.

Abstract: The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel. The enhanced mixing feature may include a turbulated mixing zone.

Abstract: An improved rotary disc atomizer for use in, for example, spray dryers or congealers is disclosed. The rotary disc may be directly mounted to the shaft of a high-speed electrical motor. The high-speed electrical motor comprises a permanent magnet rotor and electro-magnetic bearings. The electro-magnetic bearings may be supported by one or more upper/lower bearing housings and used to enable frictionless support of the shaft/rotor and rotary disc. The atomizer system may further comprise a gas distributor enabled to dynamically adjust the velocity at which the gas leaves the radial vanes and meets with the atomized droplets.

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 fuel injector includes pilot and main fuel injectors. The pilot fuel injector includes at least one pilot air swirler and the main fuel injector includes a main air blast fuel injector located between inner main and outer main air swirlers. A first air splitter is located between the pilot and inner main air swirlers and a second air splitter is located between the pilot and inner main air swirlers. The first air splitter has a downstream portion converging to a downstream end. The second air splitter has a downstream portion diverging to a downstream end. The second air splitter downstream end is downstream of the first air splitter downstream end and the ratio of the distance from the first air splitter downstream end to the second air splitter downstream end to the diameter of the second air splitter downstream end is in the range of 0.22 to 0.30.

Abstract: A method and a device for producing a thin article or a thin coating on a previously manufactured solid body. At least two reactive polymer materials are mixed together thoroughly and die resultant mixture is discharged via a nozzle in the form of a thin tube. This thin tube is pulverized or atomized by means of the introduction of a controlled flow of pressurized air with the result that die pulverized mixture may be sprayed onto an open mold or onto a surface or onto a previously manufactured solid body which is to be coated.

Abstract: Provided is an apparatus for removing smoke and poisonous gas. The apparatus includes a body configured to include a flux unit which supplies water and a nozzle which is connected to the flux unit and has a narrower width than the flux unit, a frame configured to surround the body and include a suction part for removing smoke, and a heat sensitive unit fixed to seal the nozzle. When the flux unit, nozzle and frame sprays fluid with a certain pressure at high speed through the nozzle, pressure energy of the fluid is changed to velocity energy, and a vacuum state is formed in a suction room at a low pressure due to a fast speed. In order for an operation to be performed as a vacuum ejector for sucking another fluid, the suction part is positioned surrounding the nozzle, and the frame is provided to surround the heat sensitive unit.

Abstract: The invention relates to a device and method for distributing a liquid and gas in a multiple-bed downflow reactor, such as a hydrocarbon processing reactor, like a hydrocracker. The device comprises respectively the method uses a distributor device comprising a substantially horizontal collecting tray provided with a central gas passage. Gas passing in downward direction through the central gas passage is forced into a swirling motion by a swirler. This swirling motion has a swirl direction around a vertical swirl axis so that the gas leaves the central gas passage as a swirl. At a location above the collecting tray, a quench fluid is ejected into gas in an ejection direction, which is, viewed in a horizontal plane, at least partly opposite to the swirl direction.

Abstract: The present invention relates to a metering module (15) for a liquid reducing agent, in particular a urea-water solution, for mixing the reducing agent with a gas, in particular air, for further introduction into an exhaust pipe (5) of an internal combustion engine (1). The metering module (15) comprises a metering valve (31) having a conduit (33), a compressed air duct (49) and a mixing chamber (35). An outlet opening of the conduit (33) for the reducing agent is arranged in the mixing chamber (35) at a distance from the mid-axis of the metering module (36).

Abstract: A metering system for a fuel atomizer includes a housing having a fuel inlet and an oxidizer inlet arranged coaxially, and an oxidizer metering device having a plurality of oxidizer channels, an oxidizer flow controller, and a fuel metering device. The oxidizer channels are spaced apart circumferentially in the housing and are arranged angled in at least one of a radially inward direction and a tangential direction to create a swirl of oxidizer flow in a mixing chamber of the fuel atomizer. The oxidizer flow controller is configured to control flow of oxidizer from the oxidizer inlet to the plurality of oxidizer channels. The fuel metering device is configured to control fuel flow from the fuel inlet to the mixing chamber.