Abstract: There is described a method for operating an inhalation chamber. A duct in the inhalation chamber extends from an opening for a source of gas to an opening for patient output, the duct comprising two portions, of which the shapes are complementary to form the duct, and displaceable in relation with each other. A MDI (or pMDI) and/or a nebulizer are connected to the inhalation chamber. A relative displacement is made between the two portions of the duct to close the duct and shunt the dead volume of the inhalation chamber, making a direct passage from the source of gas to the patient. If the nebulizer or the MDI is connected, a relative displacement is made between the two portions of the duct to open the duct to an inner volume of the inhalation chamber where the nebulizer or the MDI is dispensing aerosol. Other configurations are possible.

Abstract: An acoustic resonator for a fan includes an annular shape internal volume defining by a housing, housing and internal volume are coaxial relative to the longitudinal axle of the acoustic resonator, internal volume comprises at least one coaxial helical channel, the at least one coaxial channel comprise an inlet and outlet corresponding to inlet and outlet of the acoustic resonator characterized in that the acoustic resonator comprises adjusting means provide for modified the length between inlet and outlet of the acoustic resonator according an acoustic frequency to lower noise.

Abstract: A system for assisting in the removal of an MWD tool from a pipe is disclosed. The system comprises: a stand-off bracket, a winch assembly configured to be mounted to the stand-off bracket, and a coupling. The winch assembly comprises a winch, a power supply for supplying power to the winch, and a controller for operating the winch. The coupling comprises a collar interface, configured to be mounted to a collar that contains a measurement while drilling (MWD) tool, and a stand-off bracket interface, configured to receive an end of the stand-off bracket distal from the winch. A method for operating the system is also disclosed.

Abstract: A method of calibrating a furnace includes determining a first flame stabilization period for the furnace that avoids detachment of a flame from a burner within a burner box of the furnace, determining a second flame stabilization period that is longer than the first flame stabilization period and avoids emission of a combustion tone from the furnace, and configuring a controller of the same or another furnace to utilize a flame stabilization period that has a duration between the first and second flame stabilization periods. Each flame stabilization period commences upon ignition of a premixed mixture of air and fuel at the burner while an inducer fan operates within a first range of fan speeds, and terminates when the rotational speed of the inducer fan increases to a second range speeds that is greater than the entire first range.

Abstract: A baffle assembly and burner including the baffle assembly. The baffle assembly includes a collar having a central axis. A plurality of vanes are secured to the collar. Each vane includes a leg extending from the collar at a first angle with respect to the central axis. The first angle of the leg is configured to impart rotation to a flow of fluid through the baffle assembly. An impingement plate extends from the leg at a second angle with respect to the central axis. The second angle is greater than the first angle.

Abstract: An air intake coupling has at least one noise suppression hole formed therein. A gas-air mixer elbow is fluidly coupled to the air intake coupling. A burner box assembly is fluidly coupled to the gas-air mixer elbow via a gas-air plenum box. A heat-exchange tube has a first end that is fluidly coupled to the burner box assembly. A fan is fluidly coupled to a second end of the heat-exchange tube via a cold-end header box.

Abstract: A nozzle for uniform plasma processing comprises an inlet portion and an outlet portion. The inlet portion has a side surface substantially parallel to a vertical axis. The inlet portion comprises a plurality of gas channels. The outlet portion is coupled to the inlet portion. The outlet portion comprises a plurality of outlets. At least one of the outlets is at an angle other than a right angle relative to the vertical axis.

Abstract: A flare gas assembly having an air pipe with an upper open end, a first conduit in surrounding relationship to the air pipe and having a first conduit upper end, a second conduit in surrounding relationship to the first conduit and having a second conduit upper end, and a third conduit in surrounding relationship to the second conduit and having a third conduit upper end, the upper ends of the air pipe, the first conduit and the second conduit being below the upper end of the third conduit, there being an air source connected to the air pipe to provide air to the air pipe at a desired flow rate.

Abstract: A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.

Abstract: The present disclosure is directed to a combustion section for a gas turbine engine including a combustor assembly, an outer casing, a fuel injector assembly, and an inner casing. An inner liner and an outer liner are each extended at least partially along a lengthwise direction and at an acute angle. A dome assembly is extended between the inner liner and the outer liner, and the inner liner, and the outer liner together define a combustion chamber therebetween. A bulkhead assembly defining a plurality of walls is coupled to the inner liner and generally surrounding the outer liner and dome assembly. The outer casing surrounds the combustor assembly. The inner casing, the outer casing, and the combustor assembly together define a primary flowpath. An oxidizer flows through the primary flowpath in serial flow through the plenum and the fuel injector assembly into the combustion chamber.

Abstract: In a burner in which fuel and gaseous oxidant are fed into the burner and combusted to produce a flame that extends out of an end of the burner, the noise produced by the burner is lessened by incorporating into the burner a baffle composed of a metal plate having a certain distribution of holes through the plate and a layer of metal filaments, and optionally a second metal plate.

Abstract: A wave rotor includes an inlet end plate, a rotor drum, and an outlet end plate. The inlet end plate is arranged to direct a flow of gasses into rotor passages formed in the rotor drum. The rotor drum is arranged to receive the gasses. The outlet end plate is arranged to direct the gasses out of the rotor drum.

Abstract: A gas turbine engine includes a combustor which has at least one annular wall defining a combustion chamber therein. The annular wall is formed by a circumferential array of panels overlapping one with another to define a plurality of radial gaps between respective adjacent two panels. The radial gaps are configured in a spiral pattern and are in fluid communication with the combustion chamber and a space outside the combustor to allow air surrounding the annular wall to enter the combustion chamber via the radial gaps for film cooling.

Abstract: The present invention discloses a novel apparatus and way for controlling combustion dynamics in a premix combustion system. The apparatus comprises a hemispherical dome assembly with a plurality of dome dampers having a predetermined damper volume and air supply with the damper in fluid communication with the combustion chamber. The dome dampers are pressurized with a volume of air to dampen pressure waves received from the combustion chamber. One or more combustor frequencies can be targeted through use of the present invention.

Abstract: A gas turbine combustion instability control device has a combustion unit provided with a hollow combustion chamber, a gas turbine connected to the inside of the combustion chamber and a dynamic pressure sensor which is provided to the inside of the combustion chamber and measures the combustion dynamics of the inside of the combustion chamber; a diagnosis module which processes combustion dynamic pressure signals (p) according to the combustion dynamics measured by the dynamic pressure sensor to calculate the kurtosis value (k) of the dynamic pressure signals, and compares the same with a kurtosis reference value (kth) to evaluate the combustion instability; and a combustion control unit for controlling the operation of the combustion part according to the determination of the diagnosis module.

Abstract: A system includes a control system. The control system includes a coherence derivation system configured to derive a coherence between respective outputs of each of a plurality of combustors coupled to a gas turbine system, and a phase derivation system configured to derive a phase difference between the respective outputs of each of the plurality of combustors coupled to the gas turbine system. The control system is configured to derive an indication of an impending lean blowout (LBO) or an actual LBO of at least one of the plurality of combustors based at least in part on the coherence derivation, the phase derivation, or a combination thereof.

Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.

Abstract: The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

Abstract: A gas assist flare tip for enhancing smokeless combustion of a flare gas. The assist tip which has a shroud positioned on a flare stack, the shroud having an outer annular portion and an inner tubular portion which fits over the riser. There is an annular plenum which is partially formed by the tubular portion and the outer portion and has an annular vent proximate the open end of the riser. There is at least one air jet eductor having a discharge outlet opening into the plenum.

Abstract: A dampener or resonator is provided within a combustor casing to mitigate combustion dynamics. The combustor casing head end volume is reduced by the resonator to mitigate combustion dynamics. The resonator is formed by a ring shaped plate that carries a continuous inwardly protruding wall or segmented inwardly protruding wall portions. The resonator can be a stand alone part that is inserted into the combustor casing or it can be integrally formed with the combustor casing.

Abstract: An acoustic damper of the present invention is objected to obtain a sound absorption effect of a combustor in an extensive range of frequency band. The acoustic damper includes an acoustic pipe body attached to a combustor so as to communicate with an inside of the combustor, and the acoustic pipe body is provided with a plurality of passages whose extension lengths are different from each other inside the acoustic pipe body.

Abstract: A combustion chamber is provided and includes a combustion device and a supply circuit arranged to feed fuel at a plurality of locations of the combustion device. The supply circuit includes manifolds collecting fuel to be distributed among at least some of the locations, ducts extending from the manifolds and feeding the locations. Some of the ducts carry valves having a plurality of predetermined working positions, each working position corresponding to a different fuel flow through the valve.

Abstract: A combustion device (1) for a gas turbine includes portions (12) having an inner and an outer wall (13, 14) with an interposed noise absorption plate (15) having a plurality of holes (16). The combustion device (1) further has first passages (17) connecting zones between the inner wall (13) and the plate (15) to the inside of the combustion device (1) and second passages (21) for cooling the inner wall (13). The portions (12) also have an inner layer (22) between the inner wall (13) and the plate (15) defining inner chambers (23), each connected to at least a first passage (17), and an outer layer (24) between the outer wall (14) and the plate (15) defining outer chambers (25) connected to the inner chambers (23) via the holes (16) of the plate (15).

Abstract: A combustion device for a gas turbine includes an interior portion, an inner wall having a plurality of first passages and an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into a third passage. An intermediate layer is disposed between the inner wall and the outer wall and defines a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages.

Abstract: A combustor liner may include an annular inner liner and an annular outer liner with a plurality of air holes thereon. The outer liner may be positioned circumferentially around the inner liner such that an annular cooling space is defined between the inner and the outer liner. The combustor liner may also include at least one resonator coupled to the outer liner such that a base of the resonator is separated from the outer liner to form a gap with an external surface of the outer liner. The combustor liner may also include a throat extending from the base of the resonator penetrating the inner liner and the outer liner. The combustor liner may further include a grommet assembly that allows for relative thermal expansion between the inner liner and the outer liner proximate the throat.

Abstract: Certain embodiments of the present disclosure include a combustor resonator having a non-uniform annulus between a combustor assembly and a resonator shell. The combustor resonator may further include resonator necks or passages having non-uniform lengths and geometries.

Abstract: The object of the invention is to provide a lightweight mechanism that changes the distribution of a flow rate of air for combustion supplied into each burner, without providing a mechanical movable part in a passage for high-temperature and high-pressure air for combustion in a combustor having a plurality of burners such as a pilot burner and a main burner. The combustor equipped with an air flow rate distribution control mechanism based on a fluidic element in accordance with the present invention has a plurality of burners such as a main burner and a pilot burner, wherein with the fluidic element being disposed upstream of a passage of air for combustion that is supplied to each burner, and means for sucking out or blowing out air into a control air passage of the fluidic element being provided, the distribution of a flow rate of the air flowing into the burners is controlled by changing a flow direction of the air for combustion.

Abstract: A Helmholtz damper for a combustor of a gas turbine includes first and second damping volumes. The combustor has a combustion chamber disposed in a housing and closed off by a front plate at which a plurality of burners are exchangeably fastened. The burners are supplied with fuel via fuel lances which extend from outside the housing through a bushing of the housing to the associated burner. The first damping volume has a first end and a second end, the first end of the first damping volume being configured to attach a connecting passage extending to a front panel such that the Helmholtz damper is connectable with the front plate of the combustion chamber in place of one of the burners. The second damping volume has a first end and a second end and is arranged in series with the first damping volume along an axis of the Helmholtz damper with the first end of the second damping volume being detachably connected to the second end of the first damping volume so as to form a combined larger damping volume.

Abstract: A tubular burner has: a mixing tube inclusive of an inlet port, a venturi section, and a tapered tube section; and a flame hole member having a plurality of flame holes and being adapted to be fitted into a front end region of the mixing tube. A flame hole member has a front plate and a rear plate, both of sheet metal make. The front plate has a first flame hole in the central portion of the front plate, and a plurality of second flame holes located around a periphery of the first flame hole. The rear plate has a first ventilation hole in the center thereof so as to lie opposite to the first flame hole, and a plurality of second ventilation holes of smaller diameter than the first ventilation hole.

Abstract: A gas turbine including a combustion oscillation suppressing device disposed to a transition piece of a combustor to define a gas space S, and having a plurality of vent holes through which a gas space L and the inside of the transition piece communicate. The combustion oscillation suppressing device is formed of a first member and a second member which define the gas space, the second member having the plurality of vent holes, and a portion of a transition piece wall includes the second member. A distance from the second member to the first member in the radial direction of the transition piece is a height of the gas space, and when the height of the gas space varies along an axial direction of the transition piece, an opening ratio ?p of each of the plurality of vent holes is adjusted depending on the height of the gas space.

Abstract: A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.

Abstract: The invention relates to a device for providing a gas/combustion air mixture for a gas burner, comprising a fan (11) for providing a combustion air flow, a gas control device for providing a gas flow and a mixing device (13) for mixing the combustion air flow and the gas flow, thus providing the gas/combustion air mixture. Said mixing device (13) and the fan (11) are connected together on one side, and on the other side, the mixing device and the gas control device are connected together. According to the invention, the mixing device (13) and the fan (11) are connected together in such a manner that a vibration absorber (15) is arranged between a connecting section (12) of the mixing device (13) and a connecting section (10) of the fan (11).

Abstract: A vented combustion chamber for an insect attractant engine is provided for a flying insect trapping device of the type that relies upon combustion of a fuel to generate a flow of carbon dioxide to attract flying insects. The combustion chamber, which is generally tubular and horizontally oriented in operation, is vented through a hole formed in one side of the chamber wall that extends from the outer surface of the chamber into the interior thereof. During operation of the device, this through-hole allows gas inside the chamber to be vented to the outside, changing the effective length of the combustion chamber for the purposes of wave generation is changed so that creation of a resonance cycle or standing wave, and the resulting acoustic phenomenon of howling, is prevented.

Abstract: Combustor. The combustor includes a duct through which an air/fuel mixture flows, including a flame-anchoring region. An insulating material is located proximate the flame-anchoring anchoring region whereby combustion instability is decreased.

Abstract: A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and the outer peripheral surface of the liner. The at least one side wall of each resonator surrounds a subset of a plurality of holes that extend substantially radially through the liner. A plurality of cooling passages extends generally longitudinally within the liner. Each cooling passage has an inlet in fluid communication with the exterior of the liner and an outlet in fluid communication with the inner cavity of a respective one of the resonators. A coolant, such as compressor air, can enter and flow along the cooling passages to thereby cool the liner and purge the inner cavity of the resonator.

Abstract: Combustor. The combustor includes an axially symmetric tube along with means for introducing fuel and air into the tube. A swirler is disposed within the tube to impart rotation in a first direction to the air/fuel mixture. A plurality of holes downstream of the swirler are disposed around the tube and offset at an angle relative to an inward normal to the tube wall. Air is injected through the offset holes to impart rotation to the air/fuel mixture in a second direction opposite to the first direction. A combustion chamber having a diameter larger than that of the tube receives and burns the air/fuel mixture from the tube.

Abstract: In one embodiment, a system includes a variable geometry resonator configured to couple to a fluid path upstream from a combustor of a turbine engine. The variable geometry resonator is configured to dampen pressure oscillations in the fluid path and the combustor.

Abstract: A control module for preventing acoustic resonance noise generation from a heat exchanger of a heating furnace, comprising a control signal generated by the control module. The control signal is configured to operate an induction fan of the heating furnace at more than one speed for a given heat demand mode of the heating furnace.

Abstract: An exemplary combustor includes at least a portion having an inner liner and an outer cover plate, which together form an interposed cooling chamber. A plurality of hollow elements extend from the liner and protrude into the cooling chamber. Each hollow element defines a damping volume connected to an inner volume of the combustion chamber via a calibrated duct. During operation, the hollow elements damp pressure pulsations and, in addition, also transfer heat.

Abstract: A combustor includes an upstream surface that extends radially across at least a portion of the combustor, a downstream surface that extends radially across at least a portion of the combustor and is axially separated from the upstream surface, and a plurality of tubes that extend through the downstream surface. A resonator is upstream from at least one of the tubes, and a fluid passage extends through the resonator and into the least one tube.

Abstract: A gas turbine combustor having a Helmholtz resonator in a post-swirler homogenization zone upstream of the combustor zone. Embodiments of the present invention provide Helmholtz resonators that include cavities that occupy a remainder of a post-swirler homogenization zone, which also includes at least one flow-directing structure that passes a fuel/oxidizer mixture from a main swirler assembly into a combustion zone of a combustor. Thus, an open annular region of the combustor is converted into a multi-purpose zone that includes at least one Helmholtz resonator.

Abstract: A burner body is disclosed for use in a gas burner assembly. The burner body includes a sidewall and a main gas conduit, the main gas conduit having an inlet and an outlet; a plurality of primary burner ports disposed within the sidewall so as to be in communication with the outlet of the main gas conduit; a simmer flame port disposed within the sidewall in a spaced relation with the primary burner ports for providing a reignition source therefore; and a stability chamber disposed within the burner body, wherein the stability chamber comprises at least a first expansion region and a second expansion region, wherein the second expansion region has a greater volume than the first expansion region.

Abstract: A combustion apparatus has a burner, a combustion box containing therein a heat exchanger, an exhaust passage in fluid communication with the combustion box, a fan for supplying the burner with combustion air, and a predetermined length of air suction duct in fluid communication with a suction opening formed in a fan casing. The air suction duct has: on a downstream end thereof, an outlet cylindrical portion which is smaller in diameter than a diameter of the suction opening in the fan casing and which lies opposite to the suction opening; and a flange portion which overhangs radially outward from a perimeter of the air suction duct adjacent to the outlet cylindrical portion into contact with that peripheral portion of the fan casing which forms the suction opening. The flange portion is provided with an auxiliary suction opening in fluid communication with a space surrounding the outlet cylindrical portion.

Abstract: A resonator system for a turbine engine can improve acoustic performance and cooling effectiveness. During engine operation, a combustor liner exhibits alternating hot and cold regions in the circumferential direction corresponding to the non-uniform temperature distribution of the combustion flame. Accordingly, high flow resonators are formed with the liner in substantial alignment with the hot regions of the fluid flow within the liner, and low flow resonators are formed with the liner in substantial alignment with cold regions of the fluid flow within the liner. As a result, appropriate amounts of cooling can be provided to the liner so that cooling air usage is optimized. Alternatively or in addition, the liner can include two or more rows of resonators, which can provide an enhanced acoustic damping response. The resonators in the first row can be aligned with or offset from the resonators in the second row.

Abstract: In one aspect, a fuel oxygenation apparatus includes a fuel oil supply fluidically coupled to the inlet of a positive displacement pump for delivery of the fuel oil to a fuel oil burner. An oxygen supply is fluidically coupled to the inlet of the positive displacement pump. During the suction cycle, a momentary vacuum is created at the pump inlet side drawing oxygen gas into the fuel line where it admixes with the fuel oil supply. Oxygenating the fuel prior to combustion increases efficiency of the burner and reduces undesirable emissions.

Abstract: A burner system is provided that includes at least two adjacent burners that are separate from each other. Each of the two burners has at least one combustion chamber and a head end. The head end includes at least a fuel injection and a fuel-air premix. Each burner has a cap with a cap side and cap upper side, wherein at least the cap upper side is arranged ahead of the head end, seen in the direction of flow. In this manner, a burner plenum is formed between the cap upper side and the head end. The at least two burner plenums thus formed have an acoustic connection. A method for damping such a burner system is also provided.

Abstract: The present specification generally relates to improvements to combustors such as burners and engines. In one aspect, the specification presents an acoustically enhanced ejector system which can be used as part of an intake system for a combustor. In another aspect, the specification teaches the use of a combustor combustion chamber as an oscillator to magnify a harmonic frequency of a pulsating frequency of the combustor. In still other aspects, the specification presents a combustion chamber having an inlet with a plurality of tangentially spaced apertures, and an in-line intake system connected to the apertures.

Abstract: The invention relates to a heat exchanger for a mobile heating device comprising a burner, the heat exchanger having a carrier body with an inner face and an outer face. The inner face of the carrier body is formed as an inner exhaust gas duct for conducting exhaust gas of the burner. Furthermore, a channeling is arranged between the inner face and the outer face of the carrier body for conducting a heat transfer medium. The heat transfer medium is in heat conducting contact, via the inner face, with exhaust gas in the inner exhaust gas duct. At the outer face of the carrier body, an outer exhaust gas duct for conducting exhaust gas of the burner is provided. The heat transfer medium is in heat conducting contact via the outer face of the carrier body with exhaust gas flowing in the outer exhaust gas duct. The present invention further relates to a mobile heating device having a burner and to such a heat exchanger and to a motor vehicle comprising such a heating device.

Abstract: A dampener or resonator is provided within a combustor casing to mitigate combustion dynamics. The combustor casing head end volume is reduced by the resonator to mitigate combustion dynamics. The resonator is formed by a ring shaped plate that carries a continuous inwardly protruding wall or segmented inwardly protruding wall portions. The resonator can be a stand alone part that is inserted into the combustor casing or it can be integrally formed with the combustor casing.

Abstract: A method of combustion stability control for a gas turbine engine is provided, and includes the steps of receiving by a stability controller, information regarding environmental and operating conditions, and comparing the environmental and operating conditions to pre-programmed information to determine if a likelihood of combustion instability exists. The method further includes the steps of determining optimal fuel modulation frequency and amplitude for the environmental condition to reduce combustion instability, if a likelihood of combustion instability exists, and actuating at least one fuel modulation valve to, at the optimal fuel modulation frequency and amplitude, reduce combustion instability, if a likelihood of combustion instability exists. Systems for modulating fuel flow are also provided.