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 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: Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions of an intervening strip (244, 444) is provided from apertures (226A, 226B, 426) in a resonator box (262, 462) adjacent and upstream from the intervening strip (244, 444). This film cooling also cools weld seams (280) along the lateral walls (268, 270) of the resonator boxes (262, 462). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (244, 444). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.

Abstract: An end cap for a fuel injector of a turbine engine is disclosed. The end cap includes an annular first surface including a plurality of perforations. The annular first surface is exposed to a combustion chamber of the turbine engine. The end cap is coupled to an end face of the fuel injector to define an enclosed cavity. The enclosed cavity and the plurality of perforations form an array of Helmholtz resonators.

Abstract: An improved induced draft gas burner assembly (31, 131, 231, 331, 431, 531, 631) for low NOx residential and light commercial gas furnaces (10, 10a) is disclosed. The improved burner includes an upstream assembly coupled to a fuel inlet (55) and an air inlet (43). The air inlet (43) is coupled to a neck (41, 141, 241, 341, 441, 541, 641) extending between the air inlet (43) and the outlet of the neck (41, 141, 241, 341, 441, 541, 641), both of which may be disposed within an optional chamber (42, 142, 242, 342, 442). If used, such a chamber (42, 142, 242, 342, 442) also includes an outlet coupled to a burner (46, 146, 246, 346, 546, 646). In practice, the chamber (42, 142, 242, 342, 442) and neck (41, 141, 241, 341, 441, 541, 641) behave as a Helmholtz resonator that can be tuned to provide an upstream impedance Zup that exceeds the downstream impedance Zdown of the components downstream of the burner assembly (31, 131, 231, 331, 431, 531, 631).

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: Device for damping oscillations of a combustion chamber that includes at least one resonator connected to a pre-chamber in a vibration-damping manner. The pre-chamber is connected to a combustion chamber in a vibration-damping manner via at least one passage channel. This abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Abstract: A burner is disclosed which includes a vortex generator for a combustion air stream, means for the admission of fuel into the combustion air stream and air inlet ducts, the combustion air stream enters a vortex chamber of the vortex generator via air inlet ducts. The fuel is injected into the combustion air asymmetrically via the injection means.

Abstract: A combustion control system for a turbine engine is disclosed. The combustion control system includes a fuel injector having a main fuel supply and pilot fuel supply coupled to a combustor of the turbine engine. The combustion control system also includes a sensor coupled to a transfer tube. The transfer tube is fluidly coupled to the combustor, and the sensor is configured to detect a pressure pulse in the combustor. A semi-infinite coil is also coupled to the transfer tube. The combustion control system also includes a controller electrically connected to the sensor. The controller is configured to compare an amplitude of the pressure pulse within a frequency range to a threshold amplitude, and adjust the pilot fuel supply in response to the comparison.

Abstract: A thermo acoustic damper for a combustor includes at least one resonator in flow communication with a flow channel of the combustor. The resonator includes an enclosed volume and at least one baffle plate positioned in the enclosed volume dividing the enclosed volume into at least two volumes. A plurality of feed tubes extend inwardly into at least one of the at least two volumes from the flow channel and are configured to reduce thermo acoustic dynamics of the combustor. A combustor includes an enclosed combustor cap volume and a plurality of fuel nozzles extending through the combustor cap volume. At least one baffle plate is located in the combustor cap volume dividing the combustor cap volume into at least two volumes. A plurality of feed tubes extend inwardly into at least one of the at least two volumes from a flow channel.

Abstract: A combustion chamber (1), in particular in a gas turbine, has at least two burners (A-H) that are connected to a fuel supply (3) via controllable fuel valves (2? and 2). Each burner (A to H) is assigned at least one optical measuring device (4) for detecting chemiluminescent radiation, and the combustion chamber (1) is assigned a pressure sensor (7) for detecting a combustion chamber pressure. The optical measuring device (4) and the pressure sensor (7) are connected to a computing and control device, which calculates a correlation value from the incoming measured values. A high correlation value signifies that the associated burner is prone to pulsation. The computing and control device (6) is designed in such a way that it determines the burner or a burner group with the highest correlation and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group, and the pulsation tendency thereof is thereby reduced.

Abstract: A combustion chamber for a gas turbine engine comprising at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the interior of the combustion chamber. The cavity extends around at least part of the neck and is spaced apart therefrom to define a cooling chamber therebetween. The cooling chamber allows the neck and the cavity to be cooled with a flow of cooling air. The sunken neck allows the resonator to be located within enclosures with minimal volume without compromising on the damping properties afforded.

Abstract: In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor basket (6), a transition piece (7) or a bypass duct (11) so as to form a first internal space (31) having a predetermined capacity; and a first throat (32) having a predetermined length which has one end (32a) open to a side wall (20a) of the object body (20) and has the other end (32b) open to a first internal space (31); wherein, a first resistive element (33) having a multiple number of through-holes is inserted and engaged to one end (32a).

Abstract: An injection assembly for use with a combustor is provided. The injection assembly includes an effusion plate that has a plurality of plate openings and a plate sleeve having a sidewall portion that includes a forward edge. The forward edge is coupled to the effusion plate such that the effusion plate is oriented obliquely with respect to a centerline extending through the combustor. The injection assembly also includes a plurality of ring extensions where each of the ring extensions is coupled to one of the plurality of plate openings. Each ring extension extends rearwardly into the plate sleeve.

Abstract: A heat apparatus (1), in particular for providing heating in a space, such as central heating, or for heating tap water in, for instance a boiler, comprising: a burner; provided with a guide channel for air supply and/or flue gas discharge; wherein in the guide channel a sound reflecting structure (10) is included extending transversely relative to the guide channel, and designed for damping a sound caused by the burner by means of sound reflection.

Abstract: Abatement systems are described. An abatement system includes a combustion chamber and a fuel burner ring coupled with the combustion chamber. Another abatement system includes a combustion chamber and a fuel flow control mechanism coupled with the combustion chamber.

Abstract: Disclosure is made of methods, systems, and apparatus for changing characteristics of noise of premixed flames supported on burners by heating burner passageways by an amount that attenuates combustion noises arising from premixed flames.

Abstract: A burner includes: a body defining an interior cavity; a burning surface located in the body and defining, at least in part, the interior cavity; a defusing surface located on an exterior portion of the body; ports on the body extending through the defusing and burning surfaces and configured to provide fluid communication between the interior cavity and ambient air outside the body; and an opening larger than at least one of the ports, the opening providing fluid communication between the interior cavity and a space outside of the body. A method of burning a gas and reducing acoustic feedback in a combustion device are also described.

Abstract: Disclosure is made of methods, systems, and apparatus for changing characteristics of noise of premixed flames supported on burners by heating burner passageways by an amount that attenuates combustion noises arising from premixed flames.

Abstract: A combustor wall of a gas turbine engine is provided with an acoustic damper component. The component has a first metering passage, a first damping chamber, a first damping passage, a second damping chamber and a second damping passage. Air flows through the damper to be ejected into the combustion chamber from the second damping passage at a selected velocity and volumetric flow. The flow being sufficient to damp instabilities from the combustion process.

Abstract: A resonator for damping pressure waves or instabilities in a system supported by acoustic energy wherein the resonator adopts the use of counter-bored openings on the downstream side of the resonator within the flow path of the system. The resonator includes a first member and a second member where the second member includes a plurality of openings therethrough with each hole having a counter-bore on its upstream side. The first member has a size substantially smaller than the diameter of said flow path and a first plurality of openings therethrough. The openings are in fluid communication with the flow path. The second member has a size generally equal to the first member and a second plurality of openings therethrough, which openings are in fluid communication with the flow path.

Abstract: The present invention relates to a method and a device for affecting thermoacoustic oscillations in a combustion system (i) comprising at least one burner (2) and at least one combustor (3), modulated injection of fuel being carried out. In order to improve the action of affecting the thermoacoustic oscillations, the modulated injection of the fuel is carried out into a recirculation zone (7) which forms in the combustor (3).

Abstract: A method for operating a furnace with a multi-burner system for generating a hot gas is provided. The furnace has a combustion chamber with a plurality of burners, each having a fuel feed. The method includes regulating a first fuel feed to at least one of the plurality of burners as a function of pressure pulsations that occur in the combustion chamber so as to achieve a steady operation of the furnace. The multi-burner system may be a gas turbine, preferably of a power plant.

Abstract: A combustion system having at least one wall enclosing a combustion chamber and forming a plurality of burner or burner nozzle openings. Disposed within each of the openings is a premix burner or burner nozzle, each of which has a premixed fuel/oxidant outlet proximate the combustion chamber and a fuel/oxidant inlet distal from the combustion chamber. At least a portion of the premix burners or burner nozzles are sized to produce different fuel/oxidant delivery disturbance response times in response to a pressure disturbance within the combustion system. Differences in fuel/oxidant delivery response times are achieved by using burners or burner nozzles having different internal dimensions, different volume flow rates, and, optionally, by varying the fuel/oxidant ratios of the mixtures flowing through the burners or burner nozzles.

Abstract: Aspects of the invention are directed to a system for improving the damping performance of an acoustic resonator. According to aspects of the invention, a resonator, such as a Helmholtz resonator, can be attached to a surface of a combustor component in a turbine engine. The combustor component includes a region in which a plurality of passages extend through the thickness of the component. The resonator is attached to the component so as to enclose at least some of the passages. The passages are in fluid communication with a cavity defined between the component surface and the resonator. Resonator performance is a function of the length of the passages in the component. According to aspects of the invention, resonator performance can be improved by reducing the length of the passages in the component by reducing the thickness of the component in a region that includes the plurality of passages.

Abstract: A combustion chamber suitable for a gas turbine engine is provided with at least one Helmholtz resonator having a resonator cavity and a resonator neck in flow communication with the chamber interior. The resonator neck is provided with at least cooling holes extending through its wall for improved damping and cooling, at least one of the holes is directed towards the resonator cavity.

Abstract: The gas-fired heating apparatus, especially a water heater, has a combustion chamber (2a); an atmospheric gas burner (5) within the combustion chamber (2a); a combustion gas/air supply system (18) having an intake device (16) for combustion gas and primary air to be mixed with the combustion gas, which is arranged outside of the combustion chamber, and an oscillation-damping air supply chamber (11) provided with at least one air inlet (12), which is connected upstream to the intake device (16) and is constructed as a Helmholtz resonator to reduce noise and stabilize combustion. To provide sufficient primary air under adverse spatial conditions the air supply chamber (11) has an exterior wall (11?) and a pattern (13, 14) of perforations in the exterior wall, which are formed as additional air inlets for additional supply of the primary air.

Abstract: A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.

Abstract: An acoustic resonator for use in an engine is provided. The acoustic resonator includes a cavity having a volume, an aperture, and a passage connecting the aperture and the cavity. The aperture has a profiled surface for delaying separation of fluid entering the passage and for reducing losses caused by fluid separation.

Abstract: This invention relates to a burner, especially a gas turbine burner, wherein a Helmholtz resonator downstream of a fuel inlet position in directly linked with a burner channel. In this manner, combustion oscillations do not arrive at the fuel inlet position, thereby reducing acoustic disturbances and air ration deviations which are the main cause for the formation of combined oscillations. The invention also relates to a method for operating a burner and a gas turbine.

Abstract: A method for operating a gas turbine engine includes coupling an anti-resonant frequency system to a combustor including a premixer assembly and a plurality of damper tubes, and adjusting the anti-resonant frequency system until the anti-resonant frequency of the damper tubes is approximately equal to the combustor resonant frequency.

Abstract: A venturi tube has a configuration of baffles affixed thereto that serve to greatly reduce the susceptibility of a gas burning appliance to wind gusts. The baffles cooperate to force incoming primary combustion air through a circuitous route before introduction into a flow of gaseous fuel. The circuitous route in combination with the volume of air that is contained within the baffling serves to substantially reduce flame blowout.

Abstract: The gas-fired heater, especially a water heater, has an atmospheric gas burner (5) arranged within a nearly or completely closed combustion chamber (2) and associated with a premixing gas/air supply system (8) with a fuel gas feed nozzle (10). In order to avoid oscillations, which lead to sound waves and combustion instabilities, an oscillation-damping air supply chamber (11, 11?, 11?) is connected to the entrance (8a) of the gas/air supply system (8) for combustion air, within which the fuel gas feed nozzle is arranged. The air supply chamber (11, 11?, 11?) is provided with at least one air entrance (12, 12?, 12?). The air supply chamber can be box-like, duct-like embracing or extending around the combustion chamber or it can be a pipe with different diameter pipe sections.

Abstract: In a burner (1) having an interior space (22) surrounded by at least one shell (8, 9) in which burner (1) fuel is injected through fuel nozzles (6) arranged at the burner shells (8, 9) into a combustion air stream (23) flowing within the interior space (22), the fuel/air mix which is formed flows to a flame front (3) in a combustion chamber (2) within a delay time (?), where it is ignited, the formation of combustion-driven thermoacoustic oscillations is avoided by virtue of the fact that means (24), which allow fuel to be injected into the combustion air stream (23) via at least two fuel injection holes (25) distributed over the length of the means (24) are arranged so as to project from the burner base (27) into the interior space (22) substantially in the direction of the combustion chamber (2), so that the delay time (?) between injection of the fuel and its combustion at the flame front (3) corresponds to a distribution (12) which avoids combustion-driven oscillations in premix operation.

Abstract: The present invention relates to a method and a device (1) for affecting thermoacoustic oscillations in a combustion system (6) comprising at least one burner (7) and at least one combustor (8). In order to improve the action of affecting the thermoacoustic oscillations, a gas flow forming in the e region of the burner (7) is excited acoustically, modulated injection of fuel is carried out, the acoustic excitation of the gas flow and the modulated injection of the fuel are coordinated in order to affect the same interference frequency.

Abstract: The present invention comprises systems and methods for detecting flame blowout precursors in combustors. The blowout precursor detection system comprises a combustor, a pressure measuring device, and blowout precursor detection unit. A combustion controller may also be used to control combustor parameters. The methods of the present invention comprise receiving pressure data measured by an acoustic pressure measuring device, performing one or a combination of spectral analysis, statistical analysis, and wavelet analysis on received pressure data, and determining the existence of a blowout precursor based on such analyses. The spectral analysis, statistical analysis, and wavelet analysis further comprise their respective sub-methods to determine the existence of blowout precursors.

Abstract: A method of reducing engine noise generation by decoupling: acoustic and hydrodynamic fluctuation generated by a compressor and a fuel supply system; from acoustic and hydrodynamic fluctuation of a combustor, by: deflecting fuel jets into a fuel nozzle mixing chamber in a number of counter-rotating adjacent pairs of fuel laden vortices; emitting a resulting fuel-air mixture into the combustor downstream from the fuel nozzle mixing chamber.

Abstract: The invention relates to a burner apparatus (1) for burning fuel (5) with air (4) to combustion gas, in particular within a combustion turbine, comprising a premixing chamber (3) for premixing fuel (5) and air (4) with. The premixing chamber (3) having an air inlet (8) for air (4) to enter said premixing chamber (3), a fuel inlet (11) for a gaseous or liquid fuel (5) to enter said premixing chamber (3), and an outlet (12) for a mixture of air (4) an fuel (5) wherein, the fuel inlet (11) being located between said air inlet (8) and said outlet (12). The burner apparatus (1) Further comprises at least one air blocking member (2) situated at the air inlet (8) for stabilising a burner premixing flame by locally blocking the flow of air (4) entering said premixing chamber (3) so that downstream said outlet (12) a locally inhomogeneous fuel concentration (23) results generating a locally hot stream of combustion gas being hotter than the average flame temperature.

Abstract: A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.

Abstract: A gas turbine combustor (10) having a first grouping (64) of pre-mix burners (12, 12?, 12?) having mixing passages (36) that are geometrically different than the mixing passages (38) of a second grouping (66) of pre-mix burners (14, 14?, 14?). The aerodynamic differences created by these geometric differences provide a degree of control over combustion properties of the respective flames (44, 46) produced in a downstream combustion chamber (40) when the two groupings of burners are fueled by separate fuel stages (52, 54). The geometric difference between the fuel passages of the two groupings may be outlet diameter, slope of convergence of the passage diameter, or outlet contour. The fuel injection regions (16, 18) of all of the burners may be identical to reduce cost and inventory complexity. The burners may be arranged in a ring (60) with a center pre-mix burner (68) being identical to burners of either of the groupings.

Abstract: The combustion vibration estimating apparatus comprises an inputting unit for inputting limiting values of plant data, weather data and internal pressure variation, an internal pressure variation characteristic grasping unit for making internal pressure variation of a combustor into a mathematical model from the input plant data and weather data, a combustion vibration region estimating unit for applying a limiting value of the internal pressure variation to the mathematical model obtained by the internal pressure variation characteristic grasping unit to obtain combustion vibration-prone to be generated region, and an outputting unit for outputting a combustion vibration region estimation result by the combustion vibration region estimating unit.

Abstract: The objective is to provide a gas turbine and the combustor thereof in which super high frequency combustion oscillation and the generation of NOx are reduced. The fluctuation in pressure which induces the fluctuation in heat liberation is suppressed in the gas turbine combustor comprising a plurality of main fuel supply nozzles, each having a premixing nozzle at the top end part thereof, by providing in the space upstream from the premixing nozzles partition elements for dividing the space along the axis of the combustor or a honeycomb element having air passages in the axial direction, or by providing premixing nozzles composed of cylindrical elements with many holes.

Abstract: A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surface part (21) facing the combustion chamber (1), gastightly encloses an intermediate space (3), into which cooling air can be fed for purposes of convective cooling of the combustion-chamber wall (2).

Abstract: A method for eliminating or substantially reducing unstable combustion conditions within a combustion chamber. By adding hydrogen to the inlet fuel mixture, the method provides a means for altering the overall combustion (reaction) rate and the resulting characteristic reaction time that, in turn, will eliminate or substantially reduce undesirable pressure oscillations.

Abstract: A sound shield is positioned between the burner chamber of a furnace and the portion of the furnace immediately in front of the burner chamber which is typically a removable door. The removable door has slotted vents that allow air to be drawn into the burner chamber. The sound shield is positioned between the slotted vents and the burner chamber in such a manner so as to prevent substantial amounts of burner noise being produced by burning fuel from escaping through the vents. This is done without unduly restricting the flow of air through the slotted vents to the burner chamber.

Abstract: A sound shield is positioned between the burner chamber of a furnace and the portion of the furnace immediately in front of the burner chamber which is typically a removable door. The removable door has slotted vents that allow air to be drawn into the burner chamber. The sound shield is positioned between the slotted vents and the burner chamber in such a manner so as to prevent substantial amounts of burner noise being produced by burning fuel from escaping through the vents. This is done without unduly restricting the flow of air through the slotted vents to the burner chamber.

Abstract: In a burner (10) for the production of a hot gas, which burner (10) opens with a burner outlet (22) edged with an outlet edge (16, 17) into a combustion chamber (23), in which a fuel-air mixture flowing out from the burner outlet (22) with the formation of an outflow boundary layer (18′) forms a flame (20) after the ignition of the burner (10), the combustion process is improved in that, to prevent periodic releases of heat and the therewith connected thermoacoustic oscillations in the combustion chamber (23), means (21) are arranged at the burner outlet (22) for changing the thickness of the outflow boundary layer (18′).

Abstract: In a method for injecting fuel into a burner (1), which burner (1) comprises an inner chamber (22) enclosed by at least one shell (8, 9), at which inner chamber fuel is injected through fuel nozzles (6) into a combustion air stream (23) flowing inside the inner chamber (22), the resulting fuel/air mixture flows within a time-lag (&tgr;) to a flame front (3) in a combustion chamber (2), and is ignited there, the formation of thermoacoustic, ignition-driven vibrations is achieved in that the fuel is injected in such a way by means of fuel nozzles (6) distributed over the burner length that the time-lag (&tgr;) between the injection of the fuel and its combustion at the flame front (3) corresponds to a distribution (12) that varies systematically over the burner length for the various fuel nozzles and reduces the vibrations.

Abstract: A burner (1), fed with a mixture of fuel and air, comprising a body (2) consisting of two half-shells having a plane of symmetry, inside said body a Venturi tube (3) being defined, provided with and inlet (4) into which said mixture of fuel and air is introduced, said Venturi tube (3) communicating upwardly with a distributing chamber (5) of said mixture of fuel and air, said distributing chamber (5) communicating upwardly with a burner head (8), closed upwardly by a diffuser (9), on which openings are made for the outflow and the subsequent combustion of said mixture of fuel and air, said distributing chamber (5) exhibits a first portion (6) and a second portion (7), said first portion (6), communicating with said Venturi tube, comprising at least a first stretch (6a; 6c; 6e) having a cross section of substantially constant width and at least a second stretch (6b; 6d) having cross section that increases progressively along a direction parallel to said plane of symmetry towards an end of said distributing cha

Abstract: The invention is a device for muffling the sound of escaping gas from a dispensing pipe for natural gas or any similar gaseous fuel, where the dispensing pipe has one or more first orifices. The device is an insert that may be placed into the dispensing pipe. The insert has second orifices through which the natural gas or any similar gaseous fuel escapes, and the second orifices are smaller than the first orifices.