1759results about "Burners" patented technology

An apparatus is provided for manipulating droplets. The apparatus is a single-sided electrode design in which all conductive elements are contained on one surface on which droplets are manipulated. An additional surface can be provided parallel with the first surface for the purpose of containing the droplets to be manipulated. Droplets are manipulated by performing electrowetting-based techniques in which electrodes contained on or embedded in the first surface are sequentially energized and de-energized in a controlled manner. The apparatus enables a number of droplet manipulation processes, including merging and mixing two droplets together, splitting a droplet into two or more droplets, sampling a continuous liquid flow by forming from the flow individually controllable droplets, and iterative binary or digital mixing of droplets to obtain a desired mixing ratio.

This invention provides a showerhead and method for allowing reaction gases to immediately mix upon release from gas outlets and minimize deposits of unwanted contaminants on the tip of a gas outlet and faceplate of the showerhead. A post having a central opening extends into the faceplate for emitting a first gas and is directly and circumferentially surrounded by an annular opening for emitting a second gas. The post may be recessed from, flush with or extend a distance past a frontal surface of the faceplate. A plurality of apertures, for emitting the second gas, may circumferentially surround the annular opening. The annular opening releases the second gas at a pressure and velocity sufficient to intermix with first gas released from the post while simultaneously forcing any unreacted gas and gaseous mixtures away from the tip of the post and frontal surface of the faceplate, thereby avoiding depositing contaminants thereon.

A humidifier and humidity sensor for use with a breathing assistance apparatus. The humidity sensor senses absolute humidity, relative humidity and/or temperature at both the patient end and humidifier end. The humidifier may also include provision to both control independently the humidity and temperature of the gases. Further, a chamber manifold facilitates easy connection of the humidifier to various outlets, inlets and sensors. A heated conduit provides a more effective temperature profile along its length.

Apparatus suitable for atomizing and vaporizing at least a first liquid by colliding at least one gas with the first liquid. The apparatus includes a gas inlet through which the gas enters the apparatus and a first liquid inlet through which the first liquid enters the apparatus. A discharge end of the apparatus includes at least one first liquid discharge outlet through which at least one stream of the first liquid is discharged from the apparatus. The discharge end also includes at least one gas discharge outlet through which at least one stream of gas is discharged from the apparatus to collide with and thereby atomize the discharged stream of the first liquid. A first liquid passageway interconnects the first liquid inlet with the first liquid discharge outlet. A gas passageway interconnects the gas inlet with the at least one gas discharge outlet. In one embodiment, the gas passageway comprises at least one gas chamber in thermal contact with an initial portion of the first liquid passageway such that a heated quantity of the gas in the chamber preheats the first liquid in the initial portion of the first liquid passageway. In alternative embodiments, the gas passageway includes a pressure dampening chamber allowing gas to be continuously discharged without pulsating.

A reheat combustion system for a gas turbine comprises a mixing tube adapted to be fed by products of a primary combustion zone of the gas turbine and by fuel injected by a lance; a combustion chamber fed by the said mixing tube; and at least one perforated acoustic screen. The or each said acoustic screen is provided inside the mixing tube or the combustion chamber, at a position where it faces, but is spaced from, a perforated wall thereof. In use, the perforated wall experiences impingement cooling as it admits air into the combustion system for onward passage through the perforations of the said acoustic screen, and the acoustic screen damps acoustic pulsations in the mixing tube and combustion chamber.

An electrospraying apparatus and/or method is used to coat particles. For example, a flow including at least one liquid suspension may be provided through at least one opening at a spray dispenser end. The flow includes at least particles and a coating material. A spray of microdroplets suspending at least the particles is established forward of the spray dispenser end by creating a nonuniform electrical field between the spray dispenser end and an electrode electrically isolated therefrom. The particles are coated with at least a portion of the coating material as the microdroplet evaporates. For example, the suspension may include biological material particles.

In one embodiment, a combustor (28) for a gas turbine engine is provided comprising a primary combustion chamber (30) for combusting a first fuel to form a combustion flow stream (50) and a transition piece (32) located downstream from the primary combustion chamber (30). The transition piece (32) comprises a plurality of injectors (66) located around a circumference of the transition piece (32) for injecting a second fuel into the combustion flow stream (50). The injectors (66) are effective to create a radial temperature profile (74) at an exit (58) of the transition piece (32) having a reduced coefficient of variation relative to a radial temperature profile (64) at an inlet (54) of the transition piece (32). Methods for controlling the temperature profile of a secondary injection are also provided.

A lean direct injection fuel nozzle for a gas turbine is disclosed which includes a radially outer main fuel delivery system including a main inner air swirler defined in part by a main inner air passage having a radially inner wall with a diverging downstream surface, an intermediate air swirler radially inward of the main inner air swirler for providing a cooling air flow along the downstream surface of the radially inner wall of the main inner air passage, and a radially inner pilot fuel delivery system radially inward of the intermediate air swirler.

A gas turbine engine fuel nozzle assembly has concentric primary and secondary pilot fuel nozzles with circular primary and annular secondary exits respectively and a main fuel nozzle spaced radially outwardly of the pilot fuel nozzles. The primary and secondary pilot fuel nozzles include conical primary and secondary exit holes respectively. The secondary pilot fuel nozzle is located directly adjacent to and surrounding the primary pilot fuel nozzle. Alternatively the secondary pilot fuel nozzle may be radially spaced apart from the primary pilot fuel nozzle. A fuel injector having a hollow stem may be used to support the fuel nozzle assembly. A first pilot swirler may be located radially outwardly of and adjacent to the dual orifice pilot fuel injector tip, a second pilot swirler located radially outwardly of the first swirler, and a splitter radially positioned between the first and second pilot swirlers.

A humidifier apparatus for operating at an air pressure is disclosed for use with a respiratory therapy breathing apparatus that provides a breathable gas supply to patients requiring higher concentrations of liquid vapor and gas pressure. The humidifier apparatus includes a feed liquid supply bag in fluid communication with a humidifier cartridge via a conduit. The conduit enables air to flow therethrough to equalize air pressure between the humidifier cartridge and the feed liquid supply bag in response to liquid being supplied to the humidifier cartridge.

In one embodiment, a turbine system, may include a fuel nozzle, that includes a plurality of fuel passages and a plurality of air passages offset in a downstream direction from the fuel passages. In the embodiment, an air flow from the air passages is configured to intersect with a fuel flow from the fuel passages at an angle to induce swirl and mixing of the air flow and the fuel flow downstream of the fuel nozzle.

A fuel/air premixer for use in a gas turbine improves the atomization performance and mixing performance of the fuel by guiding an air so as to flow in an outward radial direction. A flow-deflecting tubular body having an annular cross section is disposed on the inside of and coaxially with a liquid film-forming body of an airblast atomizer nozzle disposed at the inlet portion of a premixing tube. The outer peripheral surface of the flow-deflecting tubular body has a wall surface which increases in outer diameter toward the tip end of a first annular passage. The inner peripheral surface of the flow-deflecting tubular body has a form in which the inner diameter has a minimum to form a contracted portion, and then increases dramatically toward the tip end.

A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer includes: a main housing surrounding the pilot housing and defining an annular cavity having an upstream end and a downstream end including an upstream wall, an outer wall and an inner wall; a plurality of fuel injection ports for introducing fuel into the cavity, with the fuel injection ports being circumferentially spaced at a designated axial location of the inner wall of the annular cavity; and a swirler arrangement including at least one swirler in flow communication with the annular cavity, the swirler being incorporated into the outer wall of the annular cavity and extending from an upstream end to a downstream end, wherein each swirler of the arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The main housing further includes a first plurality of passages oriented to provide air jets in a substantially axial direction into the annular cavity and a second plurality of passages oriented to provide air jets in a substantially radial direction into the annular cavity

The invention relates to a two-stage pressure atomizer nozzle with a nozzle body (30) having a mixing chamber (39) which is connected to an outside space via a nozzle outlet bore (33), and with a first feed duct (42) with a feed bore (41) for a liquid (37) to be atomized, through which feed bore said liquid (37) can be fed, free of swirling and under pressure, at least one further feed duct (36) for a portion of the liquid (37) to be atomized or for a second liquid (37') to be atomized opening into the chamber (39), through which feed duct said liquid (37, 37') can be fed under pressure and with swirling. The feed bore (41) of the first feed duct (42) lies on one axis (34) with the nozzle outlet bore (33). It is defined in that the outlet-side diameter (da) of the nozzle outlet bore (33) is at most as large as the diameter (dz) of the feed bore (41) and the length (L) of the nozzle outlet bore (33) is at least twice to at most ten times the outlet-side diameter (da) of the nozzle outlet bore (33).

A process heater is provided utilizing flameless combustion, the process heater having: an oxidation reaction chamber, the oxidation reaction chamber having an inlet for oxidant, an outlet for combustion products, and a flow path between the inlet and the outlet; a fuel conduit capable of transporting a fuel mixture to a plurality of fuel nozzles within the oxidation reaction chamber, each nozzle providing communication from within the fuel conduit to the oxidation chamber, with each nozzle along the flowpath between the inlet and the outlet; a preheater in communication with the oxidation chamber inlet, the preheater capable of increasing the temperature of the oxidant to a temperature resulting in the combined oxidant and fuel from the fuel nozzle closest to the oxidation chamber inlet being greater than the autoignition temperature of the combined oxidant and fuel from the fuel nozzle closest to the oxidation chamber inlet; and a process chamber in a heat exchange relationship to the oxidation reaction chamber wherein the heat transferred from the oxidation section does not causes the temperature of the mixture within the oxidation reaction chamber in the vicinity of each fuel nozzle to decrease below the auto ignition temperature of the combined mixture in the oxidation chamber in the vicinity of that fuel nozzle.

A cold gas spraying method and device, whereby the sprayed particles are accelerated in a gas flow. A powder tube and an outer nozzle body together form a Laval nozzle that produces high gas flow velocities. The injection of the sprayed particles occurs in the divergent section of the Laval nozzle.

The invention relates generally to dispensing of fluids and, in particular, to methods and systems for dispensing microfluidic or sub-microfluidic volumes of droplets of chemical, biological or other reagents or liquids. Embodiments of the invention have particular efficacy in accurately dispensing small drops having volumes from about 100 nL down into the picoliter range.

A liquid evaporator includes a liquid reservoir (3) with a liquid to be evaporated, a heater (9) and an evaporator tube (12). The evaporator tube (12) has a first porous element (1) having a first porosity and with an area in contact with the liquid in the liquid reservoir (3) and a second porous element (2) with a second porosity and with an area present on an evaporator side (50) used to dispense the evaporated liquid, and an area outside the liquid reservoir heated by the heater (9) which is not directly in connection with the liquid. The first porous element and the second porous element are in contact in contact areas with the first porous element forming a wick delivering liquid from the reservoir to the contact area.

A combustor for a gas turbine engine includes an inner liner and an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner. The outer liner is a dual walled liner with a first wall and a second wall. The combustor includes a fuel igniter comprising a tip portion configured to ignite an air and fuel mixture in the combustion chamber and an igniter tube positioning the fuel igniter relative to the combustion chamber. The igniter tube includes a plurality of holes configured to direct cooling air toward the tip portion of the fuel igniter.

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.

An inhaler for enabling inhaled administration, has a housing having an outlet duct defining a passageway through which air can be drawn by inhalation on the part of a user. The housing contains a capillary nozzle; a container for containing a quantity of liquid to be supplied to the capillary nozzle; and an electric field controller for applying a voltage to the liquid prior to issue from the container via the capillary nozzle to expose the liquid to an electric field to cause comminution of the liquid emerging from the capillary nozzle to product a spray of electrically charged droplets such that upon inhalation by the user, electrically charged droplets for the deposition in the user's airways.

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and discharging pressurized air from an accumulator into the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

The present invention relates to an exhaust gas guide of a gas turbine, which is situated between the gas turbine and a downstream waste heat boiler or a downstream gas diverter and which comprises a flow channel which has a cross-section expanding in at least some areas in the main flow direction, having installed surfaces influencing the flow. In order to achieve a more compact implementation of the exhaust gas guide and simultaneously avoid or reduce pressure losses, the installed surfaces are implemented as a swirl device generating a leading edge swirl, which is situated in the diverging area of the flow channel and is implemented to distribute the exhaust gas flow uniformly over the flow cross-sectional area upon entry into the waste heat boiler or the gas diverter. Furthermore, the present invention relates to a method for mixing the exhaust gas of a gas turbine with hot exhaust gas streams generated in an auxiliary firing of at least one burner. This thorough mixing is achieved by generating at least one leading edge swirl system in the flow channel.

An electrohydrodynamic spray apparatus includes a liquid inlet and a spray nozzle in fluid communication with the liquid inlet, where the spray nozzle has an opening downstream of the liquid inlet. An inner electrode is situated at least partially inside the spray nozzle. An outer electrode is situated external to the spray nozzle and within about 100 mm of the opening of the nozzle. The electrohydrodynamic spray apparatus can be combined with a substrate to form an electrohydrodynamic spray system. The electrohydrodynamic spray apparatus or system can be used to form nanostructures such as nanodrops, nanoparticles and thin films.

A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.

A gas turbine fuel injection system of the lean direct injector type designed to reduce nitrous oxide (NOx) emissions is provided. The configuration includes a pilot fuel injector for injecting a pilot fuel stream, and a pilot swirler for providing a swirling pilot air stream to atomize and entrain the pilot fuel stream. A main airblast fuel injector is located concentrically about the pilot fuel injector, for injecting a main fuel stream concentrically about the pilot fuel stream. Inner and outer main swirlers provide a swirling main air stream to atomize and entrain the main fuel stream. An air splitter is located between the pilot swirler and the main swirler. The air splitter is so arranged and constructed as to divide the pilot air stream exiting the pilot swirler and the air splitter, from the main air stream exiting the inner main swirler, whereby a bifurcated recirculation zone is created.

The present invention relates to a method of making nanoparticulates in a flame reactor, the nanoparticulates having controlled properties such as weight average particle size, composition and morphology. The nanoparticulates made with the method of present invention may be tailored to a specific weight average particle size range, such as from about 1 nm to about 500 nm. In addition to weight average particle size, the nanoparticulates made with the method of the present invention may include a variety of materials including metals, ceramics, organic materials, and combinations thereof. Moreover, the method of the present invention allows control over the morphology of the nanoparticulates, which allows the production of nanoparticulates with any desired morphology including spheroidal and unagglomerated; and agglomerated (aggregated) into larger units of hard aggregates.

Embodiments of the present invention generally provide chamber components with enhanced thermal properties and methods of enhancing thermal properties of chamber components including bonding materials. One embodiment of the present invention provides a method for fabricating a composite structure. The method includes applying a bonding material to a first component, and converting the bonding material applied to the first component to an enhanced bonding layer by heating the bonding material to outgas volatile species from the bonding material. The outgassed volatile species accumulates to at least 0.05% in mass of the bonding material. The method further includes contacting a second component and the enhanced bonding layer to join the first and second components.

A modular spray gun that can be configured and built to operate using a selectable spray process. The modular spray gun includes a gun body, an extension and a selectable spray atomizing component. The basic gun body and extension are used to configure a spray gun that can operate as an air spray gun, an airless spray gun, an AAA gun or an HVLP spray gun. The modular extension can be selected to allow circulating or non-circulating operation. The modular extension also permits a variety of spray nozzle assemblies to be mounted thereon depending on the selected spray process to be used with the specific gun. The modular gun body allows selective connection of an atomizing air supply and additional components specific to a particular spray process. An indicator device and/or a relief valve is provided for spray guns using an HVLP spray process to provide an indication that the spray gun is in compliance with the maximum nozzle air pressure limit, usually less than 10 psi. A new air valve seal assembly is also provided. The modular gun design can accommodate electrostatic and non-electrostatic versions.

In one aspect, the process includes providing a precursor medium comprising a liquid vehicle and a precursor to a component, and flame spraying the precursor medium under conditions effective to form a population of nanoparticles, wherein the nanoparticles include the component. The population of nanoparticles, as formed, comprises less than about 5 percent by volume particles having a particle size greater than 1.0 μm. A size distribution of the population of nanoparticles may have a d50 value less than about 500 nm, and it may be unimodal. The size distribution may have a geometric standard deviation of less than about 2. The process may occur continuously for at least four hours or more. Greater than about 90 percent by weight of the precursor to the component in the precursor medium may be converted to the component in the nanoparticles. The process typically occurs in an enclosed flame spray reactor.