Abstract: A combustion device includes: a combustion chamber; a plurality of hydrogen injection holes facing inside of the combustion chamber; a first air injection hole facing the inside of the combustion chamber and extending in the circumferential direction on a radially outer side with respect to the plurality of hydrogen injection holes; a second air injection hole facing the inside of the combustion chamber and extending in the circumferential direction on a radially inner side with respect to the plurality of hydrogen injection holes, the first and second air injection holes being annular; first swirling blades provided in the first air injection hole and inclined in the circumferential direction with respect to a combustion-chamber-side axial direction; and second swirling blades provided in the second air injection hole and inclined to the same side as the first swirling blades in the circumferential direction with respect to the combustion-chamber-side axial direction.

Abstract: An exhaust duct assembly for conveying exhaust gases emanating from a combustion zone to atmosphere is disclosed. The assembly includes: an exhaust gas outlet for exhausting exhaust gas into the atmosphere; and an acoustic duct portion located upstream of the exhaust gas outlet, the acoustic duct portion having a peripheral wall defining a through-passage arranged and constructed to promote propagation of sound there-through. The acoustic duct portion has a length in a flow direction that is at least 50% of an average hydraulic diameter of the through-passage.

Abstract: Embodiments of the disclosure relate to a tip for a fuel nozzle. The tip includes a tip body having a first end and a second end spatially disposed from the first end along a longitudinal axis of the tip body. A nozzle passage is disposed at the first end. An entrance cavity, a swirl chamber, and a plurality of swirl passages are disposed within the tip body. The plurality of swirl passages connects the entrance cavity and the swirl chamber. Each of the swirl passages has an opening to the entrance cavity and an exit into the swirl chamber. Fluid communication is provided from the second end to the first end such that fluid flows from the entrance cavity, through the swirl passages, into the swirl chamber, and out through nozzle passage.

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

Abstract: Annular combustion chamber for an aircraft turbomachine, said chamber having two coaxial annular walls, an inner annular wall and an outer annular wall, respectively, which are connected upstream by an annular bottom wall of the chamber, wherein an injection device passes through an axis and comprises an air injection system and a frustoconical bowl which is flared downstream and has air passage openings, the chamber further having an annular deflector placed downstream of the bottom wall substantially parallel to the latter; and wherein the air injection system, the bottom wall, the deflector and the bowl are integrally formed.

Abstract: An atomizer provides a high-quality fuel-air mixture to a gas turbine engine, by combining air input from an engine compressor and fuel input from a single low-pressure fuel supply pump. The atomizer includes an atomizer body, a main vortex chamber, a secondary vortex chamber for improving quality of the fuel-air mixture, and a fuel sleeve providing fuel to the secondary vortex chamber. The main vortex chamber includes a main outlet nozzle in fluid communication with a combustion chamber inlet of the gas turbine engine. The secondary vortex chamber includes a secondary outlet nozzle in fluid communication with the main vortex chamber. The fuel sleeve has a blind channel with a longitudinal axis and a fuel tip. The same atomizer may be used for startup mode and for all operational modes of the gas turbine engine.

Abstract: A spray device includes side-by-side spray tips that are spaced from one another at a distal end of the spray device. A first spray tip has a first fluid pathway defining a first flow area. The first fluid pathway has a first swirl chamber having an outer perimeter and flutes having inner ends that direct a first fluid into the outer perimeter of the first swirl chamber for rotating the first fluid in a circular pattern. A second spray tip has a second fluid pathway that defines a second flow area that is larger than the first flow area. The second fluid pathway has a second swirl chamber having an outer perimeter and flutes having inner ends that direct a second fluid into the outer perimeter of the second swirl chamber for rotating the second fluid in a circular pattern.

Abstract: A combustor for a gas turbine engine includes a combustor liner, a fuel swirler integral and conformal with the combustor liner to provide an outlet for fuel into the combustor, and a dilution chute surrounding the fuel swirler outlet and extending into the combustor to provide a wetting surface for fuel exiting the fuel swirler.

Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.

Abstract: A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.

Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline, each primary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; wherein the second vane angle is different from the first vane angle; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline.

Abstract: An apparatus is provided for a turbine engine. This apparatus includes a fuel conduit and a fuel nozzle. The fuel conduit includes a supply passage. The fuel nozzle includes a nozzle passage, an end wall and a nozzle orifice. The nozzle passage has a longitudinal centerline and extends longitudinally through the fuel nozzle along the longitudinal centerline from the end wall to the nozzle orifice. The nozzle passage is configured with a convergent portion and a throat portion. The nozzle passage converges radially inward towards the longitudinal centerline as the convergent portion extends longitudinally along the longitudinal centerline away from the end wall and towards the throat portion. The supply passage is fluidly coupled to the nozzle passage by a fuel aperture in the end wall. A centerline of the fuel aperture is angularly and laterally offset from the longitudinal centerline.

Abstract: An atomizer nozzle for atomizing a fluid, in particular a liquid, including a nozzle opening, a spinning chamber and at least one delivery channel for feeding the fluid into the spinning chamber, at least one delivery channel extending into the spinning chamber via at least one inlet. The spinning chamber has a curved base which is curved away from the nozzle opening, and at least one delivery channel is oriented towards the base.

Abstract: A gas turbine power generation device includes: an inlet pipe (1), a compressor (2), an air storage compartment (3), a compressor rotor (4), a compressor gear shift (6), a compressor exhaust pipeline (8), a combustion chamber intake pipeline (10), a combustion chamber intake cone (11), a combustion chamber pneumatic valve (14), a spark plug (19), a combustion chamber (21), a Tesla turbine (22), a gas collection compartment (27), an outlet pipe (28), a turbine rotor (30), a generator gear shift (32) and a generator (33).

Abstract: A combustor nozzle assembly and a gas turbine combustor including the same are provided. The combustor nozzle assembly includes a central nozzle tube, an inner nozzle tube surrounding the central nozzle tube in a spaced-apart state, an outer nozzle tube surrounding the inner nozzle tube in a spaced-apart state, a pilot fuel injector provided between the central nozzle tube and the inner nozzle tube, and a main fuel injector provided between the inner nozzle tube and the outer nozzle tube.

Abstract: A liquid fuel injector includes a cylindrical center body including a center axis, an annular shroud concentrically disposed outside the center body, an annular fuel injection body disposed between and concentrically with the center body and the shroud, and including a fuel passage formed therein, a plurality of inner swirl vanes that are arranged in an equal cycle in an inner air passage between the center body and the fuel injection body, and are provided with an inner swirl vane action surface on an upstream side, a plurality of outer swirl vanes that are arranged in an equal cycle in an outer air passage between the fuel injection body and the shroud, and an outer swirl vane action surface on the upstream side.

Abstract: A swirler apparatus for a combustor, including: primary and secondary swirlers disposed axially adjacent to each other along a swirler centerline; the primary swirler including a plurality of primary swirl vanes arrayed around the swirler centerline; and the secondary swirler including a plurality of secondary swirl vanes arrayed around the swirler centerline, each secondary swirl vane including opposed sides bounded between opposed forward and aft edges and opposed leading and trailing edges; wherein the forward edge is oriented at a first vane angle with respect to a radial direction; wherein the aft edge is oriented at a second vane angle with respect to the radial direction; and wherein the second vane angle is different from the first vane angle.

Abstract: Rotating detonation engines are provided with various improvements pertaining to performance and reliability. Improvements pertain to, for example, a fluidic valve/premixing chamber, injection/swirl, flow control and turning, ignition, and cooling. A rotating detonation engine can include a cylindrical inner shell within an outer housing, a cylindrical outer shell positioned between the inner shell and the outer housing, an annular gap between the outer shell and the outer housing functioning as a detonation chamber.

Abstract: An application device for the application in series of a paint or other coating compositions to motor vehicle bodies or add-on parts thereof has a nozzle print head which contains a plurality of nozzles arranged, for example, in one or more rows, which apply the coating composition to the surface to be coated as continuous jets or individual drops. The nozzle print head is arranged on a multi-axis coating robot. In contrast to application devices of this type known hitherto, the coating composition consists of at least two components which are to be mixed together, such as, for example, 2K paint, which are fed to the nozzle print head via separate supply lines for jointly supplying the nozzles.

Abstract: A venturi for a swirler assembly of a combustor for a gas turbine engine. The venturi has an annular wall having internal diameter of a forward end of the annular wall that is larger than an internal diameter of a middle portion of the annular wall, which is smaller than an internal diameter of an aft end of the annular wall. The internal surface of the annular wall has a plurality of grooves extending in a longitudinal direction from the forward end of the annular wall to the aft end of the annular wall. The plurality of grooves are angled with respect to a centerline axis of the annular wall and may be spiraled about the internal surface of the annular wall.

Abstract: A System for Aerodynamic Premixer for Reduced Emissions comprising a premixer is generally cylindrical in form and defined by the relationship in physical space between a first ring, a second ring, and a plurality of radial vanes. The first and second rings are found to be generally equidistant, one from the other, at all points along their facing surfaces. Radial vanes connect the first ring to the second ring and thereby form the premixer.

Abstract: A spray device includes a first spray tip having a first fluid pathway defining a first flow area, and a second spray tip includes a second fluid pathway that defines a second flow area that is larger than the first flow area of the first spray tip. The first and second spray tips are side-by-side and spaced from one another at a distal end of the spray device. When a first fluid having a volumetric flow rate is introduced into the first spray tip and a second fluid having the same volumetric flow rate is introduced into the second spray tip, the first fluid will flow through the first fluid pathway at a greater velocity than the second fluid will flow through the second fluid pathway.

Abstract: An atomizing spray device includes a housing having plural inlets and one or more outlets fluidly coupled with each other by an interior chamber. The inlets include a first inlet shaped to receive a first fluid and a second inlet shaped to receive a slurry of ceramic particles and a second fluid. The interior chamber in the housing is shaped to mix the first fluid received via the first inlet with the slurry received via the second inlet inside the housing to form a mixture in a location between the inlets and the one or more outlets. The interior chamber in the housing also is shaped to direct the mixture formed inside the housing as droplets outside of the housing via the one or more outlets such that, based on a discharged amount of the first fluid in the droplets, the first fluid promotes evaporation of the second fluid as the droplets traverse from the housing toward a surface of a component.

Abstract: A fuel injection nozzle for a combustion turbine engine has thermal stress-relief vanes, which accommodate and relieve localized thermal stresses within its monolithic, three-dimensional nozzle structure, imparted by heat transfer during engine combustion. At least one first vane is coupled to opposing, spaced nozzle sleeves at both ends. At least one cantilever-like second vane is coupled to one of the opposing sleeves on one end, while the other free or floating end is spaced by a second vane gap from the other opposing sleeve. Some embodiments include a plurality of second vanes, which have locally varying orientation, and/or structure, and/or second vane gaps, for normalizing spatially and/or temporally thermal stresses within the nozzle structure. The monolithic structure is fabricated, in some nozzle embodiments, by additive manufacturing.

Abstract: A conformal, cup-shaped fluidic oscillator spray nozzle member (100, 200, 300, 400, 500) is configured to generate one or more oscillating sprays from fluid flowing into a substantially open proximal end and distally into a substantially closed distal end wall with one or more centrally located orifices defined therein. A multi-input, multi-output cup-shaped fluidic oscillator (200, 300, 400) is configured to generate a selected fluid spray from a plurality of (e.g., 2-8) fluid product inlets which are configured in interacting pairs and feed into a common interaction region of the fluidic nozzle geometry. Optionally, an outlet “A” can be positioned in the interaction region and allow for air entrainment into the interaction region or external oscillating spray streams to generate a foamed spray of fluid product.

Abstract: In some examples, a moveable member including multiple tools is moveable relative to a fixed member to position a selected tool for performing an operation. A first connector half may be included on the fixed member for connecting to one of a plurality of second connector halves included on the moveable member. Movement of the moveable member to position the selected tool for performing the operation moves a respective second connector half associated with the selected tool into connection with the first connector half. In addition, a respective nozzle assembly may be associated with each tool. The respective nozzle assembly may receive multiple fluids including at least one fluid received through the connection between the connector halves. The nozzle assembly includes an inner nozzle that outputs a gas and an annular outer nozzle that outputs a machining liquid to generate a mixture to direct toward a tool-workpiece interface.

Abstract: A seal testing tool for use with a bearing housing of a gas turbine engine including: a first end surface; a second end surface opposite the first end surface; and a boss extending away from the first end surface. The boss extending from a proximal end located at the first end surface to a distal end located opposite the proximal end. The boss includes: a passageway extending from the distal end to the second end surface through the boss; an external surface extending from the proximal end to the distal end; and a seal groove in the external surface located at the proximal end of the boss.

Abstract: A fuel nozzle apparatus for a gas turbine engine includes: a first pilot fuel injector disposed on a centerline axis of the fuel nozzle which defines a direction of air flow through the fuel nozzle, the first pilot fuel injector being of a pressure atomizing type; an annular second pilot fuel injector at least partially surrounding the first pilot fuel injector, the second pilot fuel injector being of an air blast type and having a fuel outlet disposed axially downstream and radially outboard of the first pilot fuel injector; an annular venturi surrounding the first and second pilot fuel injectors, the venturi including a throat of minimum diameter; an array of inner swirl vanes extending between the first pilot fuel injector and the second pilot fuel injector; and an array of outer swirl vanes extending between the second pilot fuel injector and the venturi.

Abstract: Flow blurring injection utilizes a two-phase concept to generate fine sprays immediately at the interior exit, rather than a typical jet which gradually disintegrates into ligaments and then finer droplets for a conventional injector. Therefore, clean combustion is achieved with the FB injection for fuels with distinct properties without fuel preheating or hardware modification. However, in addition to the droplets, the FB injection also produces ligaments for highly viscous liquids and relatively larger droplets at spray edge, resulting in difficulty in sustaining the flame and performs incomplete combustion and higher emissions close to the combustor all. The disclosed swirl burst injector and method utilizes the advantages of FB injection and swirl atomization to further improve atomization, and overcomes the limitations of FB injection, providing a sustainable way to use both conventional and alternative fuels with improved efficiency and minimized emissions.

Abstract: The present invention relates to an apparatus for manufacturing fiber-reinforced concrete through shooting after inserting bubbles into normal concrete and a method for manufacturing the same, which: form fiber-mixed concrete in which the bubbles, fiber-mixed materials, and silica fume are mixed in the normal concrete or form the fiber-mixed concrete in which aggregates, water, and the bubbles are put into and mixed with a mixture, in which cement, the fiber-mixed materials, and silica fume are mixed; and then shoots the fiber-reinforced concrete in which excessive air included in the fiber-mixed concrete is reduced by spraying the fiber-mixed concrete with the high-pressure air when the fiber-mixed concrete is discharged, and of which a slump, drastically increased due to the large amount of bubbles, is reduced to a range of the slump of the normal concrete, thereby improving the production capacity of the fiber-reinforced concrete and shortening operating time.

Abstract: An annular combustion chamber (10) having a first annular wall (12) and a second annular wall (13) that are coaxial about an axis (X), a chamber end wall (14) connecting together the first and second walls (12, 13), and a plurality of injectors (16), the first wall (12) including first air feed holes (18) downstream from the injectors (16), the combustion chamber (10) being characterized in that for at least a first one of said injectors (16), at least three of the first holes (18) sharing the first injector as their closest injector are situated at equal distances (D) from the first injector (16).

Abstract: A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel ports, and a main purge air passage (218) in communication with the radial fuel ports and the prefilmer surface.

Abstract: A fuel injection device for injecting an air-fuel mixture to a combustion chamber in a combustor of a gas turbine engine includes a fuel injector which is arranged on an axis of the fuel injection device. The fuel injector includes a fuel injection portion for injecting fuel in the radial direction of the fuel injection device, a fuel flow path portion forming a passage through which fuel is supplied to the fuel injection portion, and a heat shield cover that covers an end portion facing toward the combustion chamber side of the fuel injection portion such that an air layer is formed between the heat shield cover and the end portion.

Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: An atomizing spray device includes a housing having plural inlets and one or more outlets fluidly coupled with each other by an interior chamber. The inlets include a first inlet shaped to receive a first fluid and a second inlet shaped to receive a slurry of ceramic particles and a second fluid. The interior chamber in the housing is shaped to mix the first fluid received via the first inlet with the slurry received via the second inlet inside the housing to form a mixture in a location between the inlets and the one or more outlets. The interior chamber in the housing also is shaped to direct the mixture formed inside the housing as droplets outside of the housing via the one or more outlets such that, based on a discharged amount of the first fluid in the droplets, the first fluid promotes evaporation of the second fluid as the droplets traverse from the housing toward a surface of a component.

Abstract: A fuel injector (10) such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22), and an injector arm (12) upstream of the head (16) comprising coaxial central channel (18) and annular channel (20), characterised in that the central channel (18) is in fluid communication with the peripheral outlet (24) and the annular channel (20) is in fluid communication with the central outlet (22).

Abstract: A pneumatic atomizing nozzle (10) which in a preferred form can be supplied with gas by means of a fan (43). The pneumatic atomizing nozzle (10) has a nozzle body (11), which bounds a flow space (21). The pneumatic atomizing nozzle (10) also has a liquid channel (27) having an outlet opening (38). Within the flow space (21), a liquid film (41) is formed, which is transported within the flow space (21) to a nozzle outlet (17) by the gas flow. The outlet opening (38) of the liquid channel (27) defines an outlet direction (A) for the liquid into the flow space (21), which in the preferred embodiment is opposite the flow direction (S) of the liquid film (41). At least in some sections, the liquid channel (27) and the outlet opening (38) extend transversely through the nozzle body (11) in a curved, wound, or meandering manner.

Abstract: The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first mount face which defines at least one first pocket and a swirler second body with an annular second mount face which abuts said annular first mount face, where said second annular mount face defines at least one second pocket. The disclosure is directed to a method of lightening a swirler assembly for a combustor of a gas turbine engine, where the method includes defining at least one pocket within an annular mount face of a swirler body.

Abstract: An aerosol hairspray product for styling and/or shaping hair wherein the product comprises: a container; a spraying device; a propellant; a hairstyling formulation comprising: (a) at least about 50% water; and (b) from about 0.01% to about 20% of a hairstyling polymer, wherein the hairstyling polymer is selected from the group consisting of: acrylates copolymers of two or more monomers of (meth)acrylic acid or one of their simple esters; acrylates/hydroxyesters acrylates copolymers of butyl acrylate, methyl methacrylate, methacrylic acid, ethyl acrylate and hydroxyethyl methacrylate; polyurethane-14/AMP-acrylates polymer blend; and mixtures thereof. The product comprises about 2% or less alcohol, or is substantially free of alcohol, and the product comprises 54% or less VOC.

Abstract: A cooling system for a fuel system in a turbine engine that is usable to cool a fuel nozzle is disclosed. The cooling system may include one or more cooling system housings positioned around the fuel nozzle, such that the cooling system housing forms a cooling chamber defined at least partially by an inner surface of the cooling system housing and an outer surface of the fuel nozzle. The fuel nozzle may extend into a combustor chamber formed at least in part by a combustor housing. The fuel nozzle may include one or more fuel exhaust orifices with an opening in an outer surface of the fuel nozzle and configured to exhaust fluids unrestricted by the housing forming the cooling system cooling chamber. The cooling system may provide cooling fluids to cool the fuel nozzle within the cooling system cooling chamber regardless of whether the fuel nozzle is in use.

Abstract: A swirler, such as for swirling air in a fuel injector of a gas turbine engine, includes a swirler body with opposed inlet and outlet ends with a swirler wall extending therebetween along a longitudinal axis. The inlet end of the swirler body defines an inlet opening. A plurality of swirl slots is defined through a portion of the swirler wall that converges toward the longitudinal axis in a direction from the inlet opening toward the outlet end of the swirler body. The swirl slots are radially off-set with respect to the longitudinal axis for imparting swirl on a flow passing from the inlet opening, through the swirl slots, and past the outlet end of the swirler body.

Abstract: A nozzle tip assembly comprises a nozzle housing and a break-up insert. The nozzle assembly is adapted for receiving multiple pre-cursor fluids from multiple lumen. The pre-cursor fluids are kept substantially separate and forced around the break-up insert into a channel formed between the insert and the nozzle housing. Fluid is forced into fluted channels on a distal end of the break-up insert into a swirl chamber where mixing occurs prior to being expelled through an exit orifice in the nozzle housing.

Abstract: A nozzle for injecting liquid includes a nozzle body defining a plurality of injection point orifices and an annular prefilmer positioned downstream of the injection point orifices for prefilming impingement of spray from the injection point orifices on the prefilmer. A swirl antechamber can be defined upstream of the injection point orifices for supplying a swirling liquid flow to the injection point orifices for impingement of a swirling flow on the prefilmer.

Abstract: The present invention generally relates to the field of pharmaceutical sciences. More specifically, the present invention includes apparatus and devices for the preparation of pharmaceutical formulations containing large diameter synthetic membrane vesicles, such as multivesicular liposomes, methods for preparing such formulations, and the use of specific formulations for therapeutic treatment of subjects in need thereof. Formation and use of the pharmaceutical formulations containing large diameter synthetic membrane vesicles produced by using the apparatus and devices for therapeutic treatment of subjects in need thereof is also contemplated.

Abstract: An air and fuel injection system for a turbine engine combustion chamber dome, including at least two fuel injection devices including a central injector and a peripheral annular injector arranged around the central injector, and an inner annular air inlet channel into which the central injector opens up to enable mixing between the fuel from the central injector and the air inlet into the inner annular channel, and at least one outer annular air inlet channel to enable enrichment of this mix with air and to stabilize the pilot combustion zone, wherein the inner annular channel and at least one outer annular channel are separated by an intermediate annular wall extending around the central injector and having a convergent inner profile.

Abstract: Nozzle for engine has coaxial arrangement of inner pilot and outer mains airblast fuel injectors and intermediate air-swirler passage sandwiched between the outer and inner air-swirler passages of the pilot and mains airblast fuel injectors, respectively. The nozzle has an annular first-splitter wall separating the pilot outer air-swirler passage from the intermediate one. An outer surface profile of the first-splitter wall defines radially inner side of the intermediate air-swirler passage. The nozzle has an annular second-splitter wall separating the intermediate air-swirler passage from mains inner air-swirler passage. An inner surface profile of second-splitter wall defines radially outer side of intermediate air-swirler passage. The outer and inner surface profile of the first and second splitters walls, respectively, have convergent sections facing each other forming convergent portion of the intermediate air-swirler passage.

Abstract: An atomizer includes an atomizer body with a plurality of air passages defined therethrough from an upstream end of the atomizer body to a downstream end thereof. The air passages together define an air circuit through the atomizer body. A fuel circuit is defined in the atomizer body extending from a fuel inlet to a respective fuel outlet opening into each air passage. The air passages can be arranged circumferentially about a central axis defined by the atomizer body. The fuel circuit can include a manifold extending circumferentially about the atomizer body in fluid communication with a fuel opening in each respective air passage.

Abstract: An air shroud for a nozzle includes an air shroud body defining an inlet and an outlet in fluid communication with one another to allow an outer airflow to issue therefrom, the air shroud body defining a downstream surface. A plurality of air wipe channels are defined within the air shroud body, wherein each of the plurality of air wipe channels is in fluid communication with at least one of a plurality of air wipe outlets and air wipe inlets. Each air wipe outlet is defined in the downstream surface of the air shroud body such that air can flow through each air wipe outlet and wipe the downstream surface of the air shroud body.

Abstract: A fragrance composition comprising a low vapor pressure VOC and at least one low vapor pressure VOC potentiator compound, which reduces, or altogether completely obviates the use of HVPVOC solvents in fragrance compositions.

Abstract: A system includes an oxidant compressor and a gas turbine engine turbine, which includes a turbine combustor, a turbine, and an exhaust gas compressor. The turbine combustor includes a plurality of diffusion fuel nozzles, each including a first oxidant conduit configured to inject a first oxidant through a plurality of first oxidant openings configured to impart swirling motion to the first oxidant in a first rotational direction, a first fuel conduit configured to inject a first fuel through a plurality of first fuel openings configured to impart swirling motion to the first fuel in a second rotational direction, and a second oxidant conduit configured to inject a second oxidant through a plurality of second oxidant openings configured to impart swirling motion to the second oxidant in a third rotational direction. The first fuel conduit surrounds the first oxidant conduit and the second oxidant conduit surrounds the first fuel conduit.