4009results 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.

PCT No. PCT / JP97 / 01954 Sec. 371 Date Feb. 20, 1998 Sec. 102(e) Date Feb. 20, 1998 PCT Filed Jun. 9, 1996 PCT Pub. No. WO97 / 48294 PCT Pub. Date Dec. 24, 1997A flavor generation piece (12) incorporates a formed body (32) of a material containing a flavor substance. A heater (42) heats the flavor generation piece (12) without burning it, thereby generating a flavor. The heater (42) has a tank (46) mounted in a heat-insulating holder (44) to store a combustible gas. A combustion portion (52) for burning the combustible gas is disposed on the tank (46). Ignition or extinction of the combustion portion (52) is selected by a switch (58). The upper portion of the heat-insulating holder (44) forms a heat exchange duct (62) surrounding the combustion portion (52) and providing an exhaust path (64). An air pipe (74) is disposed to cross the heat exchange duct (62) transversely in the exhaust path (64). Heat exchange is performed between a fluid flowing in the exhaust path (64) and a fluid flowing in the air pipe (74). A socket (76) communicating with the air pipe (74) to detachably mount the flavor generation piece (12) is disposed on the outer side surface of the heat-insulating holder (44).

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.

A turbine containing system is disclosed. The system includes an intake section, a compressor section downstream from the intake section, a combustor section having a primary combustion system downstream from the intake section, a secondary combustion system downstream from the primary combustion system, a turbine section, an exhaust section and a load. The secondary combustion system includes an injector for transversely injecting a secondary fuel into a stream of combustion products of the primary combustion system. The injector including a coupling, a wall defining an airfoil shape circumscribing a fuel mixture passage, and at least one exit for communication between said fuel mixture passage and said stream of primary combustion products.

A dispenser bottle having a first receiving container for a first active fluid and at least a second receiving container for a second active fluid, wherein the receiving containers each have a respective outlet for the active fluid and the outlets are arranged adjacently such that the two active fluids can be applied in a common application field of an application region, and wherein the outlets each comprise a respective discharge nozzle, which nozzles are spaced from one another such that the active fluids intermix only after departing the discharge nozzles.

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.

Compressor discharge air flows through a heat exchanger in heat exchange relation with cooling water and is supplied at reduced temperature in atomizing air and purge modes to combustors in a dual-fuel gas turbine. The heat exchanger has a pair of bypass passages in parallel with a temperature regulating valve controlling flow of water through the heat exchanger in response to the temperature of the compressor discharge air exiting the heat exchanger. Should the flow control valve close in response to low temperature of the compressor discharge air, in the air atomizing mode, the bypass passages with orifices therein provide a minimum protective flow of cooling water to the heat exchanger. In the purge mode where only half the air flow and heat rejection is required in the heat exchanger and the flow control valve closes, a bypass valve in one of the bypass passages closes to enable reduced flow of cooling water through the heat exchanger.

A TFT formed on an insulating substrate source, drain and channel regions, a gate insulating film formed on at least the channel region and a gate electrode formed on the gate insulating film. Between the channel region and the drain region, a region having a higher resistivity is provided in order to reduce an Ioff current. A method for forming this structure comprises the steps of anodizing the gate electrode to form a porous anodic oxide film on the side of the gate electrode; removing a portion of the gate insulating using the porous anodic oxide film as a mask so that the gate insulating film extends beyond the gate electrode but does not completely cover the source and drain regions. Thereafter, an ion doping of one conductivity element is performed. The high resistivity region is defined under the gate insulating film.

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-conditioning skid for an engine. The fuel-conditioning skid includes an inlet that is connectable to a source to receive a flow of fuel containing undesirable compounds. An outlet is connectable to the engine to deliver a flow of fuel that is substantially free of undesirable compounds. An inlet cleaner is in fluid communication with the inlet and is operable to remove a portion of the undesirable compounds. A compressor is in fluid communication with the inlet cleaner to receive the flow of fuel at a first pressure and discharge the flow of fuel at a second pressure. The second pressure is greater than the first pressure. A purifier is in fluid communication with the inlet cleaner to receive the flow of fuel. The purifier is operable to remove substantially all of the remaining undesirable compounds from the flow of fuel.

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 method for operating a gas turbine engine facilitates reducing an amount of emissions from a combustor. The combustor includes a mixer assembly including a pilot mixer, a main mixer, and a centerbody that extends therebetween. The pilot mixer includes a pilot fuel nozzle and a plurality of axial swirlers. The main mixer includes a main swirler and a plurality of fuel injection ports. The method comprises injecting fuel into the combustor through the pilot mixer, such that the fuel is discharged downstream from the pilot mixer axial swirlers, and directing flow exiting the pilot mixer with a lip extending from the centerbody into a pilot flame zone downstream from said pilot mixer.

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.