US20170254541A1 - Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner - Google Patents

Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner Download PDF

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Publication number
US20170254541A1
US20170254541A1 US15/503,990 US201515503990A US2017254541A1 US 20170254541 A1 US20170254541 A1 US 20170254541A1 US 201515503990 A US201515503990 A US 201515503990A US 2017254541 A1 US2017254541 A1 US 2017254541A1
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United States
Prior art keywords
burner
fuel
interaction chamber
region
output
Prior art date
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Abandoned
Application number
US15/503,990
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English (en)
Inventor
Andreas Böttcher
Olga Deiss
Thomas Grieb
Matthias Hase
Werner Krebs
Patrick Lapp
Sebastian Pfadler
Daniel Vogtmann
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Siemens AG
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Siemens AG
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Publication date
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DEISS, OLGA, KREBS, WERNER, PFADLER, SEBASTIAN, LAPP, PATRICK, Böttcher, Andreas , GRIEB, THOMAS, HASE, MATTHIAS, VOGTMANN, DANIEL
Publication of US20170254541A1 publication Critical patent/US20170254541A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a burner for a gas turbine, having a central burner axis and a premix passage enclosing the burner axis at least in sections.
  • the premix passage therefore has a passage cross-sectional area which extends around the burner axis.
  • the central burner axis is an infinitely long imaginary line.
  • the passage cross-sectional area may, for example, be arranged around the burner axis annularly or as a full circle.
  • the premix passage may extend coaxially with the burner axis (same rotation axis).
  • the diameter of the ring or full circle may vary along the burner axis section.
  • the premix passage may be configured at least in sections as a ring space passage (cross section annular), which may merge into a premix passage section which is configured as a full circle in cross section.
  • the premix passage is bounded radially outward by a wall.
  • compressor air can flow through the premix passage. It is used to mix fuel and air, a burner lance or burner hub and a number of fuel injectors being arranged in the premix passage.
  • the fuel injectors which extend from the burner lance/hub in the direction of the wall, are fluidically connected to a fuel feed arrangement at least partially contained by the burner lance/hub, and have fuel nozzles.
  • the fuel injectors may, for example, comprise both fuel nozzles for gaseous fuel and fuel nozzles for oil operation. The same applies for the burner lance/hub, which as an alternative may also be configured without fuel nozzles.
  • the burner lance may also be referred to as a burner hub.
  • the burner lance may be arranged centrally in the premix passage.
  • the burner lance may extend upstream into the premix passage, so that the passage is bounded radially inward by the burner lance only in sections.
  • the premix passage may, for example, in this case have a fully circular cross-sectional area downstream of the burner lance.
  • the burner lance may, however, also extend essentially to the output of the premix passage.
  • the premix passage may be bounded radially inward at least in sections by a burner hub arranged centrally in the passage, which has an essentially frustoconically shaped lateral surface and delimits the premix passage radially inward from upstream to an end region of the hub.
  • the premix passage may merge downstream of the hub into a premix region which is fully circular in cross section.
  • the premix passage therefore has an annular passage cross-sectional area, the diameter of which may decrease in the flow direction.
  • further premix passages may be arranged in the burner hub, or for example a central pilot burner.
  • the premix passage may also be referred to as a premix channel.
  • Fuel is injected into the premix passage through the fuel injectors and can mix as far as the downstream output of the premix passage with a compressor air flow flowing through the premix passage, so that the premix burner provides at its output a fuel/air mixture to be discharged into a combustion chamber.
  • fuel may also be injected through fuel nozzles arranged directly on the burner lance.
  • premix burners have low pollution emissions during operation, they are however more susceptible to the formation of pressure pulsations.
  • the fuel feed arrangement comprises at least one fluidic oscillator having an interaction chamber, an input of the interaction chamber being connected to a fuel channel of the fuel feed arrangement, and a first output channel of the interaction chamber extending at least to a first fuel nozzle and a second output channel extending at least to a second fuel nozzle, the fluidic oscillator comprising one feedback line per output channel, the feedback line opening with one of its ends into the respective output channel in the region downstream of the at least one fuel nozzle and with the other end into an input region of the interaction chamber.
  • the at least first and the at least second fuel nozzle, or the first and second groups of fuel nozzles may be arranged on a common fuel injector and be arranged distributed in the radial direction for maximally homogeneous distribution of the fuel in the premix passage.
  • the at least first fuel nozzle could, for example, also be arranged on a suction side and the at least second fuel nozzle could be arranged on a pressure side of a fuel injector configured in the form of a swirl impeller.
  • the first and second groups of fuel nozzles may, for example, also be arranged on different fuel injectors. For example in fuel injectors essentially arranged opposite on the burner lance.
  • Fluidic oscillators have been known for a long time as fluidic control elements which function without expensive valves. For example, these are used to feed air into the boundary layer of carrying surfaces in order to avoid shedding of the boundary layer.
  • Fluidic oscillators are operated with a pressurized fluid flow applied to their input. This fluid flow is set in oscillation in the interaction chamber, so that the at least one output of the chamber alternately receives the emerging jet. A pulsating fluid flow therefore emerges from the output channels of the fluidic oscillator, the output channels ejecting the fluid alternately.
  • fluidic oscillators with feedback lines which connect an output region of the interaction chamber to an input region of the interaction chamber in order to stabilize the oscillation in the interaction chamber.
  • the feedback lines of the prior art open into the interaction chamber with one of their ends respectively close to an output of the interaction chamber and open into the interaction chamber with their other end upstream of the output close to the input of the interaction chamber.
  • the feedback lines it is now proposed to make the feedback lines open not into the output region of the interaction chamber, as in the prior art, but respectively into an output channel in a region downstream of an at least one fuel nozzle or fuel nozzle group, to which the output channel extends.
  • this makes it possible for the pressure conditions in the premix passage in the immediate premix passage region before the fuel nozzles also to have an influence on the feedback signal.
  • the output channel may have an end piece, downstream of the fuel nozzle or the fuel nozzle group, into which the feedback channel opens.
  • the feedback signal therefore becomes smaller and the fuel will flow for longer in the output channel than with reversed pressure conditions before the fuel nozzles of the output channel in the premix passage. If the static pressure in the premix passage in the region of a fuel nozzle group is lower, on application to the associated output of the interaction chamber more fuel flows through the associated output channel and the dynamic pressure in the output channel is higher.
  • the associated feedback line opens into the output channel downstream of the at least one fuel nozzle of the output channel
  • the pressure in the feedback line opening into the end region of the output channel is higher and the associated fuel jet will be shed more rapidly from the side wall in the input region of the interaction chamber and apply fuel to the next output.
  • the oscillation of the fuel jet in the interaction chamber will therefore apply fuel for longer to the output channel, of which at least one fuel nozzle opens into a region of the premix passage in which a higher pressure prevails. This compensates for the effect that less fuel generally emerges from fuel nozzles that open into a region of higher passage pressure, and more fuel is injected into regions of low pressure.
  • a more homogeneous fuel concentration can be generated in the premix passage.
  • the injection of the fuel through the at least two fuel nozzle groups, or fuel nozzles, connected to the fluidic oscillator is therefore regulated automatically, without an additional control device being required therefore.
  • the resulting more homogeneous distribution of the fuel concentration in the premix passage leads to reduced pollution emissions.
  • the fuel injection fluctuating as a function of time and position good mixing of fuel ejected by the fuel nozzle groups with the compressor air flowing past is furthermore achieved.
  • broadening of the dwell time profile of the burner is also achieved, so that an interaction of the burner with the flame and creation of thermoacoustic oscillations are reduced.
  • the dwell time profile of the burner set up during operation may be as wide as possible, the dwell time being the time taken by a fluid emerging from the fuel nozzle to reach the flame.
  • the fuel nozzles, or fuel nozzle groups, of the burner which are supplied with fuel by the fluidic oscillator cause a fluctuation of the fuel concentration profile in the compressor air flowing past, which in turn improves the thermoacoustic stability because of a broadened dwell time profile of the burner—for example in comparison with burners having conventional pressure-swirl or full-jet nozzles.
  • a frequency of the pulsating injection of the fuel may, for example, be adjusted by the size of the interaction chamber.
  • the burner may comprise a plurality of fluidic oscillators which each supply at least two output channels, respectively having at least one fuel nozzle or group of fuel nozzles, with fuel.
  • fluidic oscillators which differ in their construction.
  • the invention is not restricted to a special type of these fluidic oscillators.
  • a common feature of all these types is that they have an interaction chamber which a pressurized fluid jet enters through an input.
  • the jet is applied periodically to different side walls or side-wall regions of the interaction chamber, so that an interaction of the jet with the side walls of the chamber may be referred to, and oscillation of the jet being created so that the jet flows through the chamber periodically on different paths and in the output region consequently leaves it periodically through different outputs of the interaction chamber, or leaves a central output of the interaction chamber in different directions.
  • the jet is therefore periodically applied at least to two opposite side-wall regions, and shed again, which is induced by retardation of the flow.
  • fluidic oscillators The functionality of fluidic oscillators is prior art, for which reason the fluidic oscillators are explained only briefly here. Furthermore, a few types of fluidic oscillators are represented in the drawing.
  • the invention is independent of the type of fluidic oscillator used.
  • the invention is advantageously based on a fluidic oscillator which leads to creation of the oscillation of the incoming jet because of diverging side walls in the input region of the interaction chamber.
  • the invention is advantageously based on an essentially rotationally symmetrical configuration of the interaction chamber, with the input arranged around the rotation axis at one end of the chamber and the output region with the at least one output arranged opposite.
  • the interaction chamber widens in this type of interaction chamber in the manner of a diffuser in the direction of the output region, at least in the input region of the chamber.
  • the functionality of the feedback lines has already been explained above.
  • the first output channel extends to a first group of fuel nozzles and the second output channel extends to a second group of fuel nozzles, the feedback line respectively opening into the output channel in a region downstream of the respective group of fuel nozzles.
  • the first and second groups of fuel nozzles, or the first and second fuel nozzles may for example be arranged in a common fuel injector.
  • the fuel injector may, for example, be a swirl impeller of a swirl generator. Since different pressures prevail in the premix passage on the suction and pressure sides of the impeller, the first fuel nozzle or the first group of fuel nozzles may be arranged on the suction side, and the second fuel nozzle or fuel nozzle group may be arranged on the pressure side of the swirl impeller. According to the invention, in this way an approximately equal amount of fuel can be injected on both sides of the impeller.
  • the feedback line may also be regarded as advantageous for the feedback line to connect to the output channel downstream of the at least one fuel nozzle.
  • the output channel and the feedback line may in this case have different diameters.
  • the at least first fuel nozzle and the at least second fuel nozzle may also be regarded as advantageous for the at least first fuel nozzle and the at least second fuel nozzle to be arranged in different fuel injectors.
  • the two fuel injectors may be essentially arranged opposite one another on the burner lance.
  • the fuel concentration in the premix passage may be similar to one another in the at least two opposite regions, despite different pressure conditions in the regions.
  • the at least two fuel nozzles, or at least two fuel nozzle groups may also be regarded as advantageous for the at least two fuel nozzles, or at least two fuel nozzle groups, to be arranged in a common fuel injector and differ by their radial arrangement in the premix passage, so that the fuel concentration in the radial direction can be homogenized despite different pressure conditions in the region of the premix passage close to the burner lance and in the region of the premix passage remote from the burner lance.
  • the fluidic oscillator may be arranged in the burner hub or in the fuel injector.
  • provision may furthermore be made for the burner to comprise more than two groups of fuel nozzles, connected to the fluidic oscillator in this way, in different fuel injectors.
  • the different fuel injectors may be arranged circumferentially on the burner lance, and the associated output channels may be arranged circumferentially on the interaction chamber.
  • the at least one fuel injector may also comprise a base body, on which the fuel nozzles contained by the fuel injector are arranged, the base body being in particular a swirl impeller of a swirl generator.
  • provision may furthermore be made for the interaction chamber to comprise the input at one of its ends and an output region at an opposite end, and to be bounded by side walls or side-wall regions which extend from the input of the chamber to the output region comprising the outputs, at least two oppositely arranged side walls or side-wall regions diverging in the direction of the output, at least in the input region.
  • Aperture angles of the interaction chamber which are suitable for the creation of an oscillation, are known from the prior art.
  • An angle of at least 7.5 degrees with respect to the influx direction has been found to be particularly advantageous.
  • the fluidic oscillator may, for example, be arranged centrally in the burner lance and supply fuel injectors arranged rotationally circumferentially on the burner lance with fuel, respectively with at least one output channel of the fluidic oscillator extending respectively to a group of fuel nozzles of a fuel injector.
  • the circumferential fuel injectors may together comprise two fuel stages. A separate fluidic oscillator may be provided for each stage.
  • At least one burner is configured as claimed.
  • the burner may, for example, be a centrally arranged pilot burner of the burner arrangement.
  • the main burner of the burner arrangement may also be configured as claimed.
  • the burner according to the invention allows particularly stable combustion, in particular also during partial load operation.
  • the combustion chamber comprises at least one burner as claimed, and the gas turbine comprises at least one combustion chamber as claimed.
  • FIG. 1 schematically shows a gas turbine of the prior art in a longitudinal section
  • FIG. 4 schematically shows a detail of a combustion chamber 10 of the prior art in a longitudinal section
  • FIG. 5 schematically shows a main burner of the burner arrangement represented in FIG. 4 in a longitudinal section
  • FIG. 6 schematically shows a burner according to the invention according to a first exemplary embodiment of the invention in a longitudinal section
  • FIG. 7 schematically shows a burner according to the invention according to a second exemplary embodiment of the invention in a longitudinal section.
  • FIG. 1 shows a sectional view of a gas turbine 1 according to the prior art in a schematically simplified representation.
  • the gas turbine 1 internally comprises a rotor 3 which is mounted so as to rotate about a rotation axis 2 , has a shaft 4 is also referred to as the turbine rotor.
  • a turbine rotor Successively along the rotor 3 , there are an intake manifold 6 , a compressor 8 , a combustion system 9 having a number of combustion chambers 10 , each of which comprises a burner arrangement having burners 11 , a fuel supply system (not represented) for the burners and a housing 12 , a turbine 14 and an exhaust manifold 15 .
  • the combustion chamber 10 may, for example, be a ring combustion chamber.
  • the gas turbine could however also comprise tube combustion chambers, which are for example arranged annularly at the turbine entry.
  • air is taken in by the compressor 8 through the intake manifold 6 and compressed.
  • the compressor air L′′ provided at the end of the compressor 8 on the turbine side is guided along a burner plenum 7 to the combustion system 9 , where it is guided into the burners 11 in the region of the burner arrangement and mixed with fuel in them and/or enriched with fuel in the exit region of the burner 11 .
  • Fuel supply systems in this case supply the burners with fuel.
  • the mixture i.e. the compressor air and the fuel, are introduced into the combustion chamber 10 by the burners 11 and burn while forming a hot working-gas flow in a combustion zone inside the combustion-chamber housing 12 of the combustion chamber.
  • the working-gas flow flows along the hot-gas channel past the guide vanes 17 and the rotor blades 18 .
  • the working-gas flow expands by imparting momentum, so that the rotor blades 18 drive the rotor 3 and the generator (not represented) coupled to it.
  • FIG. 2 shows a fluidic oscillator of a first type according to the prior art in longitudinal section.
  • the oscillator 24 a comprises an interaction chamber 26 having an input 28 with an input region 30 and an oppositely arranged output region 32 with a first output 34 and a second output 36 .
  • a relatively thin feedback line 38 which connects the input region to the output region, is arranged at each output.
  • the side-wall regions 40 diverge in the direction of the output, so that the interaction chamber 26 has a triangular longitudinal section.
  • the oscillator 24 a is not constructed rotationally symmetrically, but has a constant longitudinal section perpendicularly to the plane of the drawing.
  • FIG. 4 schematically shows a detail of a combustion chamber 10 of the prior art with a burner arrangement 48 at a head end of the combustion chamber.
  • the combustion chamber comprises a combustion-chamber wall having a flame tube 50 comprising a combustion zone, and having a transition piece 52 which follows on from the flame tube and extends to a turbine entry of the gas turbine.
  • resonators 54 are arranged at the level of the flame on the combustion-chamber wall.
  • the burner arrangement 48 comprises a central pilot burner 56 having a central pilot-burner lance 58 and a pilot-burner premix passage 60 .
  • the pilot burner 56 comprises a pilot cone 62 widening conically in the flow direction.
  • Main burners 64 are arranged circularly around the central pilot burner.
  • the main burners 64 each have a burner axis 66 and a premix passage 68 arranged concentrically with the burner axis; the premix passage 68 is bounded radially outward by a wall 70 , compressor air L′′ can flow through it during operation, and it is used to mix fuel and air L′′, the premix passage 68 containing a central burner lance 72 and a number of fuel injectors, which extend from the burner lance in the direction of the wall 70 , are connected fluidically to a fuel feed arrangement which the burner lance 72 comprises, and have fuel nozzles.
  • the fuel injectors are configured as swirl impellers of a swirl generator 74 , fuel nozzles being arranged on the swirl impellers.
  • FIG. 5 shows a main burner 64 of the burner arrangement of FIG. 4 schematically in longitudinal section.
  • the burner 64 has a central burner axis 66 and a premix passage 68 enclosing the burner axis at least in sections; the premix passage is bounded radially outward by a wall 70 , compressor air L′′ can flow through it during operation, and it is used to mix fuel and air.
  • the premix passage 68 contains a central burner lance 72 and a number of fuel injectors 79 .
  • the fuel injectors 79 each comprise a base body 71 , which is arranged in the premix passage and is configured as swirl impellers 76 of a swirl generator 74 .
  • the fuel injectors 79 comprise fuel nozzles 80 , which open into the premix passage 68 on the surface of the swirl impellers 76 .
  • the fuel nozzles 80 are fluidically connected to a fuel feed arrangement 73 in order to be supplied with fuel.
  • the fuel feed arrangement 73 comprises a fuel channel 82 extending in the burner lance, and fuel feed channels 78 which extend into the swirl impellers 76 as far as the respective fuel nozzles 80 .
  • FIG. 6 schematically shows a burner 84 according to the invention in longitudinal section according to a first exemplary embodiment of the invention.
  • the fuel feed arrangement 73 has at least one fluidic oscillator 85 with an interaction chamber 26 , an input 28 of the interaction chamber being connected to the fuel channel 82 of the fuel feed arrangement 73 .
  • the interaction chamber 26 has an output region 32 with two outputs 34 and 36 .
  • a first output channel 86 extends from the output 34 to a first group of fuel nozzles 80 a in a first fuel injector 79 a .
  • a second output channel 88 extends from the output 36 to a second group of fuel nozzles 80 b in a fuel injector 79 b arranged opposite, the fluidic oscillator 85 comprising a feedback line 38 a , 38 b for each output channel, the feedback line 38 a , 38 b opening with one of its ends into the respective output channel 86 , 88 downstream of the fuel nozzles 80 a , 80 b which the output channel comprises, and with the other end into the input region 30 of the interaction chamber 26 .
  • the feedback line 38 a is connected downstream of the fuel nozzles 80 a to the output channel 86 and couples the pressure prevailing at the end of the output channel back to the input region 30 of the interaction chamber.
  • the pressure prevailing at the end of the output channel is in this case influenced by the pressure in the premix passage immediately before the fuel nozzles 80 a , so that when there is a high pressure in this region the fuel supply is switched over to the second group of fuel nozzles 80 b more slowly than would be the case with a lower pressure.
  • the group of fuel nozzles will therefore inject fuel for a longer time into the compressor air flow flowing past, before which the pressure in the premix passage is higher, so that a more uniform fuel concentration is set up at the output of the burner even when there are different pressure conditions on the two sides of the burner lance 72 .
  • This counteracts creation of pressure pulsations and reduces the production of pollution emissions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
US15/503,990 2014-09-12 2015-09-07 Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner Abandoned US20170254541A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102014218288 2014-09-12
DE102014218288.3 2014-09-12
PCT/EP2015/070355 WO2016037966A1 (de) 2014-09-12 2015-09-07 Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner

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Publication Number Publication Date
US20170254541A1 true US20170254541A1 (en) 2017-09-07

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US15/503,990 Abandoned US20170254541A1 (en) 2014-09-12 2015-09-07 Burner comprising a fluidic oscillator, for a gas turbine, and a gas turbine comprising at least one such burner

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US (1) US20170254541A1 (de)
EP (1) EP3134677B1 (de)
JP (1) JP6321282B2 (de)
CN (1) CN106662328A (de)
WO (1) WO2016037966A1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180163967A1 (en) * 2016-12-09 2018-06-14 Solar Turbines Incorporated Injector head with a resonator for a gas turbine engine
CN110529257A (zh) * 2018-05-23 2019-12-03 通用电气公司 用于燃气涡轮发动机的流体歧管阻尼器
CN113280366A (zh) * 2021-05-13 2021-08-20 中国航空发动机研究院 一种基于自激扫掠振荡燃油喷嘴的加力燃烧室结构
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11181271B2 (en) * 2018-09-17 2021-11-23 Doosan Heavy Industries & Construction Co., Ltd. Fuel nozzle, and combustor and gas turbine having the same
US11313559B2 (en) * 2015-02-27 2022-04-26 Ansaldo Energia Switzerland AG Method and device for flame stabilization in a burner system of a stationary combustion engine
CN117960415A (zh) * 2024-03-28 2024-05-03 箭牌家居集团股份有限公司 振荡器单元及出水装置

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110449309B (zh) * 2019-08-16 2020-06-26 中国航空发动机研究院 一种流体振荡器阵列及其频率同步方法
CN114856827B (zh) * 2022-05-12 2023-06-30 中国航发四川燃气涡轮研究院 可调节喷嘴位置及喷射方向的可拆卸扇形喷嘴
KR20240003230A (ko) * 2022-06-30 2024-01-08 두산에너빌리티 주식회사 제트 노즐, 연소기 및 이를 포함하는 가스터빈

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3748852A (en) * 1969-12-05 1973-07-31 L Cole Self-stabilizing pressure compensated injector
US5456594A (en) * 1994-03-14 1995-10-10 The Boc Group, Inc. Pulsating combustion method and apparatus
JP3457907B2 (ja) * 1998-12-24 2003-10-20 三菱重工業株式会社 デュアルフュエルノズル
JP2003148710A (ja) * 2001-11-14 2003-05-21 Mitsubishi Heavy Ind Ltd 燃焼器
US6718889B1 (en) * 2002-08-30 2004-04-13 Central Boiler, Inc. Draft controlled boiler fuel nozzle
US6820431B2 (en) * 2002-10-31 2004-11-23 General Electric Company Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly
EP1662202B1 (de) * 2004-11-30 2016-11-16 Siemens Aktiengesellschaft Brenner für eine Gasturbinenanlage
US8474265B2 (en) * 2009-07-29 2013-07-02 General Electric Company Fuel nozzle for a turbine combustor, and methods of forming same
EP2327933A1 (de) * 2009-11-30 2011-06-01 Siemens Aktiengesellschaft Brenneranordnung
US20110173983A1 (en) * 2010-01-15 2011-07-21 General Electric Company Premix fuel nozzle internal flow path enhancement
US20110225973A1 (en) * 2010-03-18 2011-09-22 General Electric Company Combustor with Pre-Mixing Primary Fuel-Nozzle Assembly
JP5156066B2 (ja) * 2010-08-27 2013-03-06 株式会社日立製作所 ガスタービン燃焼器
JP5908379B2 (ja) * 2012-09-24 2016-04-26 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器

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US20180163967A1 (en) * 2016-12-09 2018-06-14 Solar Turbines Incorporated Injector head with a resonator for a gas turbine engine
US10386074B2 (en) * 2016-12-09 2019-08-20 Solar Turbines Incorporated Injector head with a resonator for a gas turbine engine
CN110529257A (zh) * 2018-05-23 2019-12-03 通用电气公司 用于燃气涡轮发动机的流体歧管阻尼器
US11181271B2 (en) * 2018-09-17 2021-11-23 Doosan Heavy Industries & Construction Co., Ltd. Fuel nozzle, and combustor and gas turbine having the same
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US11913409B2 (en) 2021-05-13 2024-02-27 Aero Engine Academy Of China Afterburner structure with self-excited sweeping oscillating fuel injection nozzles
CN117960415A (zh) * 2024-03-28 2024-05-03 箭牌家居集团股份有限公司 振荡器单元及出水装置

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CN106662328A (zh) 2017-05-10
JP6321282B2 (ja) 2018-05-09
EP3134677B1 (de) 2018-03-07
EP3134677A1 (de) 2017-03-01
WO2016037966A1 (de) 2016-03-17

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