| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060725000 | Having noise reduction means | 74 |
| 20080216481 | System for Damping Thermo-Acoustic Instability in a Combustor Device for a Gas Turbine - A system for damping thermo-acoustic instability in a combustor device for a gas turbine, the combustor device including at least one combustion chamber, in particular of an annular type, and at least one burner associated to the combustion chamber and mounted in a position corresponding to a front portion set upstream of the combustion chamber; the damping system including at least one Helmholtz resonator including a casing defining inside it a pre-set volume and a neck for hydraulic connection between the pre-set volume and the combustion chamber, the neck being connected to one side of the combustion chamber at a distance from the front upstream portion thereof provided with the at least one burner. The casing of the resonator includes structure which varies the pre-set volume within a pre-set range and structure which delivers a cooling fluid. | 09-11-2008 |
| 20080245072 | Damping of Vibration of a Combustion Chamber By Resonators - 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. | 10-09-2008 |
| 20080295518 | Airfoil acoustic impedance control - A noise control cassette for a gas turbine engine includes a perforated face sheet configured for exposure to an airflow, a non-perforated backing sheet, a core arranged between the face sheet and the backing sheet and defining a cavity between the face sheet and the backing sheet having an effective length tuned so as to provide acoustic reactance control, and an attachment face for attaching the cassette to an airfoil-shaped structure. | 12-04-2008 |
| 20090025393 | Auxiliary power unit assembly - An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and a noise reduction feature in the duct. | 01-29-2009 |
| 20090044536 | Gas turbine power generator plant and silencer for the same - A gas turbine power generator plant, intended to reduce its noise by making small the intake and exhaust outlets of the cooing air channel of a case, comprises an engine core in which a turbine, a compressor and a generator are installed on the same axis, a combustor for burning air for combustion compressed by the compressor and supplying the air to the turbine, a radiator for cooling a coolant or a lubricant, a cooling fan for ventilating the radiator with cooling air, an electric power converter for converting electric power generated by the generator, and the case for housing these constituent elements. And, a combustion air channel passing the compressor, the combustor and the turbine and a cooling air channel passing the radiator, the cooling fan and the electric power converter are formed as mutually independent channels from intake to exhaust. | 02-19-2009 |
| 20090178410 | THERMALLY CONDUCTIVE STRUCTURE - A multi-layered honeycomb structure adapted to reduce and/or eliminate thermal deformation is disclosed herein. In some embodiments, walls of the honeycomb structure comprise a first layer, optionally, a second layer, and a core layer adjacent to the first layer or between the first and second layers. The first and second layers may be compositions of Inconel or other high strength materials. The core layer may be copper or another thermally conductive material. The core layer is adapted to transmit heat between a first region of a structure and a second region. In this manner, heat can be transferred from the heated region to an unheated region, thereby reducing the temperature difference between the regions and thus the amount of thermal deformation. | 07-16-2009 |
| 20090282830 | COMBUSTOR WITH REDUCED CARBON MONOXIDE EMISSIONS - A combustor arrangement for a gas turbine engine ( | 11-19-2009 |
| 20090293481 | Method and Device for Damping Thermoacoustic Oscillations, in Particular in a Gas Turbine - The invention relates to a method for damping thermo-acoustic oscillations via a resonator having a resonator volume with thermo-acoustic oscillations induced in a cavity inclined to thermo-acoustic oscillations, and at least some of the thermo-acoustic oscillations being output from the cavity and being input into the resonator volume, with damping oscillations produced in the resonator volume, which are matched to the thermo-acoustic oscillations, with at least some of the damping oscillations being input into the cavity such that the damping oscillations and the thermo-acoustic oscillations overlap in an overlap area, and the oscillations being largely cancelled out. The invention relates to an apparatus for damping thermo-acoustic oscillations in a cavity, comprising a resonator with a resonator volume and a cavity. The invention also relates to a combustion chamber together with a method and an apparatus according to the invention, and to a gas turbine having a combustion chamber. | 12-03-2009 |
| 20100011769 | FORWARD-SECTION RESONATOR FOR HIGH FREQUENCY DYNAMIC DAMPING - 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. | 01-21-2010 |
| 20100077754 | SOUND ATTENUATION SYSTEMS AND METHODS - Methods and devices for increasing the sound attenuation properties of a noise suppression device are provided. Various embodiments include sound-attenuating cavities with improved sound capturing openings. In some embodiments, the sound capturing openings include holes surrounded by projections. In other embodiments, the sound capturing openings include angled slats. Embodiments also include sound capturing devices that include the improved sound capturing openings, such as silencers, vent hoods, barrier walls, air exchanges, and air intake and exhaust ducts. | 04-01-2010 |
| 20100077755 | SOUND ATTENUATION SYSTEMS AND METHODS - Methods and devices for increasing the sound attenuation properties of a noise suppression device are provided. In some embodiments, a sound attenuating conduit has an improved shape that provides increased sound attenuation properties. In other embodiments, the sound attenuating conduits are stacked together, and shaped to increase the air flow cross-section. Still other embodiments provide machinery that includes the improved sound attenuating conduits. | 04-01-2010 |
| 20100154423 | SYSTEM FOR MIXING GAS FLOWS IN A GAS TURBINE ENGINE, GAS TURBINE ENGINE AND AN AIRCRAFT ENGINE - A system is provided for mixing gas flows in a gas turbine engine. The system includes an annular wall structure which internally delimits a channel for a first gas flow. The wall structure includes a plurality of first wall portions. At least one of the first wall portions is movably arranged in a radial direction between a first position and a second position for mixing an external gas flow with the first gas flow. | 06-24-2010 |
| 20100186411 | GAS TURBINE - An object of the present invention is to provide a gas turbine that improves appearance of a combustion oscillation suppressing device disposed to a transition piece of a combustor. To achieve the object, a combustion oscillation suppressing device | 07-29-2010 |
| 20100192577 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A TURBOMACHINE - A turbomachine includes a combustion chamber, and at least one pre-mixer mounted to the combustion chamber. The at least one pre-mixer includes a main body having a first end portion that extends to a second end portion. The first end portion is configured to receive an amount of fuel and an amount of air and the second end portion defines an exit plane from which a fuel-air mixture discharges into the combustion chamber. The turbomachine also includes a combustion dynamics reduction system operatively coupled to the at least one pre-mixer. The combustion dynamics reduction system includes at least one of a boundary layer perturbation mechanism and an acoustic wave introduction system which disrupt a flow pattern of the fuel-air mixture within the at least one pre-mixer. | 08-05-2010 |
| 20100236245 | Gas Turbine Combustion System - A gas turbine combustion system has a combustion system wall delimiting a flow path for hot and pressurized combustion gas and at least one resonator with a resonator volume. The resonator volume is delimited by resonator walls, where one of the resonator walls is located adjacent to or is formed by the combustion system wall. The resonator has at least one cooling fluid supply opening which is open towards a cooling fluid source. It further has a neck opening which is open towards the flow path and which is implemented in the form of a neck slot. | 09-23-2010 |
| 20100251718 | DAMPING DEVICE AND GAS TURBINE COMBUSTOR - In a damping device according to the present invention, a damping device | 10-07-2010 |
| 20100293952 | Resonating Swirler - The present application provides a swirler for a turbine combustor. The swirler may include an outer wall, a passage defined by the outer wall, and an end wall. The end wall may include a number of apertures therethrough. | 11-25-2010 |
| 20100313568 | RESONATOR ASSEMBLY FOR MITIGATING DYNAMICS IN GAS TURBINES - A combustor for a gas turbine engine and related method is provided in which a plurality of combustor cans are selectively adapted with corresponding resonators. The resonators may, for example, be attached to every can in the consecutive arrangement of combustor cans, every other can, every third can or the like, and may be tuned to the same or first, second, third, etc. frequencies of operation. Such selective tuning is configured to suppress one or more of out-of-phase and in-phase dynamic interaction of streams discharged from adjacent combustor cans by changing the frequencies of pressure oscillation instabilities across the arrangement of consecutive cans. | 12-16-2010 |
| 20100319349 | Attenuation of Combustion Dynamics Using a Herschel-Quincke Filter - A can-annular gas turbine engine including a casing defining an annulus for receiving air flow from a compressor. A combustor basket is supported within the casing, and a swirler assembly is located within the basket and includes an air inlet and an outlet located in a combustion chamber. The swirler assembly is configured to discharge a fuel/air mixture from the outlet downstream into the combustion chamber. An acoustic filter is provided comprising a Herschel-Quincke tube having a first open end at the annulus and a second open end adjacent to the swirler assembly within the combustion chamber. Components of acoustic pressure oscillations travel along two paths of different lengths from one end of the Herschel-Quincke tube to the opposite end of the tube where out of phase components of the pressure oscillations interact to attenuate the pressure oscillations. | 12-23-2010 |
| 20110048020 | ACOUSTIC DAMPER - An apparatus for attenuating acoustic oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor, wherein the combustor includes at least one air/fuel mixer, includes at least one resonating tube with a closed end and an open end and a single cavity between the ends. The tube is located on the combustor wall downstream of the air/fuel mixer. | 03-03-2011 |
| 20110048021 | ACOUSTICALLY STIFFENED GAS TURBINE COMBUSTOR SUPPLY - 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. | 03-03-2011 |
| 20110138812 | Resonator System for Turbine Engines - 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. | 06-16-2011 |
| 20110179795 | INJECTOR WITH INTEGRATED RESONATOR - The system may include a turbine engine. The turbine engine may include a fuel nozzle. The fuel nozzle may include an air path. The fuel nozzle may also include a fuel path such that the fuel nozzle is in communication with a combustion zone of the turbine engine. Furthermore, the fuel nozzle may include a resonator. The resonator may be disposed in the fuel nozzle directly adjacent to the combustion zone. | 07-28-2011 |
| 20110179796 | HELMHOLTZ DAMPER FOR A COMBUSTOR OF A GAS TURBINE AND A METHOD FOR INSTALLING THE HELMHOLTZ DAMPER - 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. The second end of the second damping volume is configured to attach a connecting tube extending from the second damping volume and through the bushing in place of a respective one of the fuel lances. | 07-28-2011 |
| 20120006028 | DAMPING RESONATOR WITH IMPINGEMENT COOLING - A resonance chamber ( | 01-12-2012 |
| 20120137690 | WIDE FREQUENCY RESPONSE TUNABLE RESONATOR - A system includes a resonator controller. The resonator controller may adjust a ratio of a first fluid and a second fluid into a resonator, whereby the first fluid is different than the second fluid. Additionally, the resonator controller may control a resonance frequency of the resonator to dampen oscillations based on the ratio. | 06-07-2012 |
| 20120180486 | GAS TURBINE FUEL SYSTEM FOR LOW DYNAMICS - A combustor is provided and includes a center body having a tubular inner wall, a cartridge disposed within the tubular inner wall to define an outer annular space between an outer surface thereof and the tubular inner wall and an inner annular space having an open end and a closed end opposite the open end and an insert disposed within the outer annular space to envelop the cartridge proximate to the open end, the insert including a body having a tubular forward portion and a partially tubular aft portion, the partially tubular aft portion thereby forming a recessed track having a longitudinal axis substantially aligned with a longitudinal axis of the outer annular space. | 07-19-2012 |
| 20120234009 | GAS TURBINE COMBUSTION CHAMBER - A gas turbine combustion chamber is provided. The gas turbine includes a combustion chamber interior and a combustion chamber wall which has a substantially rotationally symmetrical cross-section, wherein on the side of the combustion chamber wall facing away from the combustion chamber interior there is arranged over the entire cross-sectional circumference of the combustion chamber wall a corrugated component which, in combination with the combustion chamber wall, embodies a plurality of separate resonance chambers and wherein openings are incorporated in the combustion chamber wall in such a way that a fluidic connection is established in each case between the combustion chamber interior and one of the resonance chambers and wherein the corrugated component has two locking rings which are connected to the combustion chamber wall in order to seal off the resonance chambers. | 09-20-2012 |
| 20120247109 | GAS TURBINE AND AIR INTAKE MANIFOLD - An intake manifold is provided for inducting combustion air for a compressor of a gas turbine. The intake manifold includes a plurality of walls that delimit against the environment. Devices are provided for controllable change of the mechanical rigidity of the walls to reduce noise which is generated or is emitted in an air intake region during operation of the gas turbine. A gas turbine is also provided and includes an air intake to which air to be compressed is fed via an intake manifold. The intake manifold having a plurality of walls that delimit against the environment. Devices are provided to controllably change a mechanical rigidity of the walls to reduce noise which is generated or emitted in an air intake region during operation of the gas turbine. | 10-04-2012 |
| 20120260657 | COMBUSTOR OF A GAS TURBINE - 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. | 10-18-2012 |
| 20120291438 | BURNER SYSTEM AND METHOD FOR DAMPING SUCH A BURNER SYSTEM - 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. | 11-22-2012 |
| 20120317986 | METHOD FOR OPERATING A COMBUSTION DEVICE AND COMBUSTION DEVICE FOR IMPLEMENTING THE METHOD - A method is provided for operating a combustion device having at least one premix burner equipped with fuel stagings and is connected to a combustion chamber. The method includes changing, during transient operating states, the fuel staging of the at least one premix burner in accordance with combustion-induced pulsations which occur in the combustion chamber. A pulsation level of the pulsations which occur in the combustion chamber is continuously determined, the fuel staging of the at least one premix burner is changed for lowering the pulsation level if the pulsation level exceeds a predetermined maximum value, and, after a predetermined time interval, by the fuel staging being reset to the undisturbed value which determines the respective operating point if within the predetermined time interval the predetermined maximum value is not exceeded. | 12-20-2012 |
| 20130000306 | GAS TURBINE COMBUSTION BURNER - In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less. | 01-03-2013 |
| 20130008167 | GAS TURBINE COMBUSTOR - A gas turbine combustor is provided with a combustor basket where combustion gas flows, the combustion gas being produced by combustion of fuel injected from a nozzle, and a first resonance device and a second resonance device mounted on an outer surface of the combustor basket. The second resonance device is disposed on a downstream side from the first resonance device in a flow of the combustion gas and damps combustion oscillation of a frequency higher than the first resonance device. The first and second resonance devices are acoustic liners each having a housing mounted to the outer surface of the combustor basket. A resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket. | 01-10-2013 |
| 20130019602 | SYSTEM FOR DAMPING OSCILLATIONS IN A TURBINE COMBUSTOR - Certain embodiments include a resonator for the head end of a turbine combustor. The resonator is partially defined by first and second plates disposed about a fuel nozzle in the head end of the turbine combustor. The resonator is further configured to receive an air flow which extends through the resonator and into the fuel nozzle. | 01-24-2013 |
| 20130025282 | RESONATOR DEVICE FOR DAMPING THE PRESSURE OSCILLATION WITHIN A COMBUSTION CHAMBER AND A METHOD FOR OPERATING A COMBUSTION ARRANGEMENT - A resonator device for damping a pressure oscillation within a combustion chamber is proposed. The resonator device has a container filled with a gas, an opening in the container and a heating element adapted to generate a flame. The flame is arranged to heat the gas within the container. The resonator device is in a combustion arrangement having a combustion chamber for defining a combustion space for burning fuel. The container is connected to the combustion chamber such that an inside of the container is in communication with the combustion space via the opening. The resonator device has a resonance frequency equal to a pressure oscillation frequency within the combustion chamber under normal load conditions. | 01-31-2013 |
| 20130042619 | COMBUSTOR RESONATOR - 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. | 02-21-2013 |
| 20130074501 | COMBUSTOR RESONATOR SECTION WITH AN INTERNAL THERMAL BARRIER COATING AND METHOD OF FABRICATING THE SAME - A combustor ( | 03-28-2013 |
| 20130160453 | COMBUSTOR AND GAS TURBINE - A combustor includes a combustion chamber and an acoustic liner, wherein through-holes through are formed in a wall of the combustion chamber, a plurality of rows of the through-holes is arranged in a lengthwise direction of the combustor, the through-holes of a first through-hole row are shifted with respect to the through-holes of a second through-hole row so that centers of the through-holes of the first and second through-hole rows adjacent each other are staggered in the circumferential direction, cooling grooves are formed so as to avoid the through-holes inside that is sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion chamber, and the cooling grooves include transverse cooling grooves extending in the circumferential direction between rows of the through-holes, and longitudinal cooling grooves extending in the lengthwise direction between the through-holes and connecting the transverse cooling grooves adjacent to each other. | 06-27-2013 |
| 20130255260 | RESONANCE DAMPER FOR DAMPING ACOUSTIC OSCILLATIONS FROM COMBUSTOR - A resonance damper for damping acoustic oscillations within a combustor housing of a gas turbine engine is provided. The resonance damper comprises a baffle plate, multiple openings, and multiple tubes. The baffle plate is configured to be attached to an interior wall of the combustor housing. The baffle plate defines a cavity with the interior wall of the combustor housing. The openings are provided on the baffle plate. Each of the tubes is received within each of the openings to define the resonance damper with the cavity. | 10-03-2013 |
| 20130283799 | RESONANCE DAMPER FOR DAMPING ACOUSTIC OSCILLATIONS FROM COMBUSTOR - A resonance damper for damping acoustic oscillations within a combustor housing of a gas turbine engine is provided. The resonance damper includes a container, an opening, and a pipe. The container is configured to be attached to an interior wall of the combustor housing and has a cavity. The opening is provided on the container. The pipe is rigidly connected to the opening to define the resonance damper with the cavity. | 10-31-2013 |
| 20130291543 | Acoustic Resonator Located at Flow Sleeve of Gas Turbine Combustor - A system includes a compressor that compresses incoming airflow, and a combustor assembly mixing the compressed incoming airflow with fuel and combusting the air and fuel mixture in a combustion zone. The combustor assembly includes a hot side downstream of the combustion zone and a cold side upstream of the combustion zone. The system also includes a turbine receiving products of combustion from the combustor. The combustor assembly includes a resonator positioned in the cold side of the combustor assembly in an annular passage between a flow sleeve and a casing of the combustor assembly. | 11-07-2013 |
| 20140013755 | COMBUSTOR - A combustor includes a breech end, a plurality of fuel nozzles connected to the breech end and extending downstream from the breech end; and a shroud that circumferentially surrounds the plurality of fuel nozzles inside the combustor. A support extends radially inside at least a portion of the shroud, and a lip seal is between the support and at least one of the plurality of fuel nozzles. | 01-16-2014 |
| 20140013756 | COMBUSTOR - 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. | 01-16-2014 |
| 20140033718 | COMBUSTOR - A combustor includes a cap assembly that extends radially across at least a portion of the combustor, wherein the cap assembly includes an upstream surface axially separated from a downstream surface, and a combustion chamber downstream from the cap assembly. A plurality of tubes extend from the upstream surface through the downstream surface of the cap assembly, and each tube provides fluid communication through the cap assembly to the combustion chamber. The downstream surface is sloped at an angle with respect to the upstream surface. | 02-06-2014 |
| 20140033719 | MULTI-STEP COMBUSTOR - The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles and a combustion zone downstream of the fuel nozzles. The combustion zone may include a number of steps such that the combustion zone expands in a radial direction downstream of the fuel nozzles. | 02-06-2014 |
| 20140053559 | NEAR-WALL ROUGHNESS FOR DAMPING DEVICES REDUCING PRESSURE OSCILLATIONS IN COMBUSTION SYSTEMS - A damping device for reducing pressure oscillations in a combustion system includes at least a portion provided with a first, outer wall, a second, inner wall, an intermediate plate interposed between the first wall and the second wall. This intermediate plate forms a spacer grid to define at least one chamber between said first wall and said second wall, first passages connecting each of said at least one chamber to the inner of the combustion system, and second passages connecting each of said at least one chamber to the outer of the combustion system. The second passages open at the same side of said chambers as the first passages, the second passages have a portion extending parallel to the inner wall. This parallel portion of said second passages is equipped with heat transfer enhancing means. | 02-27-2014 |
| 20140123649 | ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE - An acoustically dampened gas turbine engine having a combustor with an acoustic damping system is disclosed. The acoustic damping system may be formed from an acoustic damping body having at least one orifice configured to receive a combustor nozzle assembly. The acoustic damping body may be positioned in a head region of a combustor basket and may include one or more orifices in the acoustic damping body. The acoustic damping system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions. | 05-08-2014 |
| 20140157779 | SYSTEM FOR REDUCING COMBUSTION DYNAMICS AND NOx IN A COMBUSTOR - A combustor includes an end cap that extends radially across at least a portion of the combustor. The end cap includes an upstream surface axially separated from a downstream surface. A plurality of tubes extend from the upstream surface through the downstream surface of the end cap to provide fluid communication through the end cap. Each tube in a first set of the plurality of tubes has an inlet proximate to the upstream surface and an outlet downstream from the downstream surface. Each outlet has a first portion that extends a different axial distance from the inlet than a second portion. | 06-12-2014 |
| 20140196458 | DAMPING DEVICE AND GAS TURBINE COMBUSTOR - In a damping device according to the present invention, a damping device | 07-17-2014 |
| 20140208756 | System For Reducing Combustion Noise And Improving Cooling - A novel and improved system for cooling and reducing combustion noise in a gas turbine combustor is disclosed. The system includes a flow sleeve for a gas turbine combustor comprising a tubular portion and a conical portion, with a plurality of flow straighteners extending radially inward and between the tubular and conical portions and a plurality of rows of cooling holes extending about the flow sleeve, and an aft ring secured to the outlet end of the conical portion, where the aft ring includes an overlapping piston ring that is able to expand or contract in diameter. A combustion liner extends through the flow sleeve and engages an inlet of a transition duct while the piston ring of the flow sleeve also engages the transition duct to form a seal. | 07-31-2014 |
| 20140245738 | SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS - A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a plurality of tubes that extend axially through at least a portion of the combustor and a combustion chamber downstream from the plurality of tubes. A fuel injector extends through each tube to provide fluid communication into each tube at a fourth axial distance from the combustion chamber. The fourth axial distance in the first combustor is different than the fourth axial distance in the second combustor. | 09-04-2014 |
| 20140338332 | ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE - An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions. | 11-20-2014 |
| 20140345282 | COMBUSTION CHAMBER FOR A GAS TURBINE PLANT - A combustion chamber (1) for a gas turbine plant having a combustion chamber wall (10), through which combustion gases (G) flow in the direction of a downstream gas turbine, wherein the combustion chamber wall (10) has a dampening device (20) for dampening thermoacoustic vibrations caused by the combustion gases (G) and wherein the dampening device (20) comprises at least one Helmholtz resonator. The resonator volume (21) opens into the combustion chamber (1) with the resonator tube opening (M) in the combustion chamber. At least one supply opening (23) with which sealing air (S) for sealing the resonator tube opening (M) is introduced into the combustion chamber (1) via the resonator volume (21) and an at least one resonator tube (22, 22′, 22″) from a compressor plenum (2). The at least one resonator tube (22, 22′, 22″) from a compressor plenum (2). The at least one resonator tube (22′, 22″) has a tube axis (A) in the combustion chamber wall and the axis (A) lies outside of a surface normal (N) of the combustion chamber wall (10) at the site of the resonator tube opening (M). | 11-27-2014 |
| 20140345283 | COMBUSTION CHAMBER FOR A GAS TURBINE PLANT - A combustion chamber ( | 11-27-2014 |
| 20140345284 | DAMPER FOR GAS TURBINE - The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. | 11-27-2014 |
| 20140345285 | DAMPER FOR GAS TURBINES - The invention relates to a damper for reducing the pulsations in a combustion chamber of a gas turbine. The damper includes a resonator cavity with an inlet and a neck tube in flow communication with the interior of the combustion chamber and resonator cavity, and a compensation assembly pivotably connected with the neck tube. The compensation assembly is inserted between the resonator cavity and the combustion chamber to permit relative rotation between the combustion chamber and the resonator cavity. With the damper according to the present invention, by way of providing the compensation assembly, it is assured the relative rotation between the combustion chamber and the resonator cavity is compensated, hence operation life is elongated. | 11-27-2014 |
| 20150007571 | GAS TURBINE COMBUSTOR - A combustor for a gas turbine that includes a front panel, an elongated sleeve with first end and second ends and a burner mounted in the sleeve. The second end of the sleeve seallessly mounted on the front panel. The sleeve and burner are configured to enable slidable mounted of the burner in the sleeve. | 01-08-2015 |
| 20150047357 | DAMPER FOR COMBUSTION OSCILLATION DAMPING IN A GAS TURBINE - The invention relating to a A damper for combustion oscillation damping for a gas turbine, includes a resonator cavity with a box or cylinder shape, a neck in flow communication with the resonator cavity and a combustion chamber. The length L | 02-19-2015 |
| 20150059345 | SIMULTANEOUS BROADBAND DAMPING AT MULTIPLE LOCATIONS IN A COMBUSTION CHAMBER - The damper arrangement includes a plurality of interconnected volumes and a plurality of necks for connecting the damper to a combustion chamber at a plurality of contact points. The plurality of necks are connected to the plurality of volumes. | 03-05-2015 |
| 20150075168 | COMBUSTION CHAMBER SEAL SEGMENTS EQUIPPED WIHT DAMPING DEVICES - A strip seal arrangement for turbine components employs acoustic damping. A sealing plate having a front face adjacent a combustion chamber and a back face facing away from a combustion chamber configured to have one or more holes of a predefined cross-sectional area. Containers having predefined volumes are attached to the back face of the sealing plate such that the one or more holes are in fluidic communication with the one or more containers thereby creating at least one acoustic damper. The side edges of the sealing plate fit into a slots of burner front panels, creating a seal between the panels. | 03-19-2015 |
| 20150101332 | COMBUSTION CHAMBER OF A GAS TURBINE WITH IMPROVED ACOUSTIC DAMPING - A combustion chamber of a gas turbine includes an optimized arrangement of acoustic dampers. | 04-16-2015 |
| 20150113990 | HELMHOLTZ DAMPER FOR GAS TURBINE WITH COOLING AIR FLOW - A Helmholtz damper for a combustor of a gas turbine includes an enclosure defining a damping volume from which a neck portion extends and which has a flow path (F) for cooling and purging air with an inlet opening and an outlet opening to the enclosure. The outlet opening is formed in the neck portion. A seal is arranged at the neck portion adjacent to the outlet opening for cooling and purging air such that a cooling effect of the seal is provided. | 04-30-2015 |
| 20150113991 | DAMPING DEVICE FOR A COMBUSTOR OF A GAS TURBINE - The present invention relates to a damping device for a combustor of a gas turbine for suppressing combustion instabilities. More specifically, the invention relates to a design of a broadband damping device for a low emission combustor having at least one resonator for damping pressure fluctuations in the combustion chamber. It is an object of the invention to provide a damping device with a quarter wave damper having broadband characteristics. The damping device for a combustor of a gas turbine according to the invention comprises a casing defining a resonator volume, a hole at a front face of the casing for allowing fluid communication between the resonator volume and the combustion chamber, the casing having parameters such that it acts as a quarter wave damper, is characterized in that the resonator volume is limited by a rear face and at least one lateral surface of the casing, whereby at least one lateral surface is equipped with one or more cavities inside and the rear face is equipped with at least one feed hole for feeding a purging fluid into the resonator volume. The preferably groove-shaped side cavities initiate energy dissipating vertical flows. | 04-30-2015 |
| 20150113992 | DAMPER FOR GAS TURBINE - The invention relates to a damper for reducing the pulsations in a chamber of a gas turbine. The damper includes a resonator cavity and a neck in flow communication with the resonator cavity and the chamber. The neck includes a mouth to communicate with the chamber. The air flow inside the chamber flows across the mouth of the neck. The neck is so configured that the longitudinal axis of its mouth is angled 0-90° relative to the direction of the air flow inside the chamber. The damper of this invention may effectively alleviate the detrimental effect of the grazing flow and thus it enables the placement of the damper also at locations where strong grazing flows are present. | 04-30-2015 |
| 20150362189 | BURNER SYSTEM WITH RESONATOR - The present invention relates to a burner system ( | 12-17-2015 |
| 20150377139 | EXHAUST FLUE - An exhaust flue ( | 12-31-2015 |
| 20150377487 | DAMPER FOR GAS TURBINE - The present invention generally relates to a gas turbine and more in particular it is related to a damper assembly for a combustion chamber of a gas turbine. According to preferred embodiments, the present solution provides a damper assembly including protrusions on a wall of the neck. These protrusions result in a side wall reactance to the acoustic field that has the effect of decreasing the effective speed of sound in the neck. The decrease of the effective speed of sound in the neck is equivalent to an increase of the effective neck length. | 12-31-2015 |
| 20160003162 | DAMPING DEVICE FOR A GAS TURBINE, GAS TURBINE AND METHOD FOR DAMPING THERMOACOUSTIC OSCILLATIONS - A damping device for a gas turbine has at least one Helmholtz resonator and at least one duct, wherein the Helmholtz resonator has a resonator housing and at least one resonator neck pipe and the resonator housing encloses a resonance volume of the Helmholtz resonator, into which volume acoustic vibrations can be injected by means of the resonator neck pipe. The damping device enables a particularly effective damping of thermo-acoustic vibrations. For this purpose, the duct is formed with a duct jacket and at least one outlet opening. Acoustic vibrations of a fluid stream flowing through a burner plenum and a combustion chamber can be injected into the outlet opening. A cooling fluid can be applied to the duct and the at least one resonator neck pipe opens on the hot-gas side into such a duct upstream of the at least one outlet opening. | 01-07-2016 |
| 20160017810 | ACOUSTIC LINER HEAT EXCHANGER - The present disclosure provides an acoustic liner for a gas turbine engine including an acoustic structure for the absorption of acoustic excitation and a heat exchanger. The heat exchanger is able to exchange heat across the acoustic structure. | 01-21-2016 |
| 20160032842 | COMBUSTOR AND GAS TURBINE - A combustor is provided with a plurality of fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes which are disposed on the combustion chamber side. The combustor is provided with a phase adjusting unit which partially changes the flow path cross-sectional area of at least one fuel nozzle in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two fuel nozzles among the plurality of fuel nozzles. | 02-04-2016 |
| 20160153661 | HELMHOLTZ DAMPER AND GAS TURBINE WITH SUCH A HELMHOLTZ DAMPER | 06-02-2016 |
| 20160169513 | COMPENSATION ASSEMBLY FOR A DAMPER OF A GAS TURBINE | 06-16-2016 |
| 20160251979 | NANOCELLULAR FOAM DAMPER | 09-01-2016 |
