EP4202308A1 - Vormischbrenner für eine gasturbinenanordnung für ein kraftwerk zur versorgung mit üblichen und hochreaktiven brennstoffen, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung für ein kraftwerk mit diesem brenner - Google Patents

Vormischbrenner für eine gasturbinenanordnung für ein kraftwerk zur versorgung mit üblichen und hochreaktiven brennstoffen, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung für ein kraftwerk mit diesem brenner Download PDF

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Publication number
EP4202308A1
EP4202308A1 EP21216659.9A EP21216659A EP4202308A1 EP 4202308 A1 EP4202308 A1 EP 4202308A1 EP 21216659 A EP21216659 A EP 21216659A EP 4202308 A1 EP4202308 A1 EP 4202308A1
Authority
EP
European Patent Office
Prior art keywords
injection nozzles
gas
premix
downstream
combustor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP21216659.9A
Other languages
English (en)
French (fr)
Other versions
EP4202308B1 (de
Inventor
Andrea Ciani
Mirko Ruben Bothien
Michael Klaus DUESING
Michael Thomas Maurer
Douglas Pennell
John Wood
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP21216659.9A priority Critical patent/EP4202308B1/de
Priority to CN202211645813.7A priority patent/CN116293798A/zh
Publication of EP4202308A1 publication Critical patent/EP4202308A1/de
Application granted granted Critical
Publication of EP4202308B1 publication Critical patent/EP4202308B1/de
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Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • 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
    • F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/03341—Sequential combustion chambers or burners
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the present invention relates to the technical field of the gas turbine assemblies for power plants (in the following only "gas turbine”).
  • gas turbine gas turbine assemblies
  • an incoming air flow is compressed in a compressor and then mixed with fuel (gas fuel and/or oil fuel) in a combustor before entering in a turbine wherein the hot gas expansion generates a rotating work on a rotor in turn connected to a generator for power production.
  • the present invention relates to all kinds of the above gas turbines (very general definition) wherein the combustor comprises at least a "premix burner”.
  • a premix burner is a burner configured not only for injecting the fuel in the compressed air flow but also for mixing (with a swirl) the compressed air and the fuel before injecting the mixture into the combustion chamber.
  • the present invention refers to the problem of how to improve the premix burner in order to allow feeding not only with common fuels but also with highly reactive fuels, for instance fuel comprising H2.
  • a gas turbine assembly for power plants comprises a rotor, a compressor, a combustor and a turbine unit.
  • the compressor is configured for compressing air supplied at a compressor inlet.
  • the compressed air leaving the compressor flows into the combustor provided with a plurality of burners configured for injecting fuel in the compressed air.
  • the mixture of fuel and compressed air flows into a combustion chamber where this mixture is combusted for generating a hot gas flow.
  • the expansion of this hot gas flow inside the turbine generates a rotating work on the rotor in turn connected to a generator.
  • the turbine and the compressor comprise a plurality of stages, or rows, of rotor blades that are interposed by a plurality of stages, or rows, of vanes supported by an outer casing surrounding the assembly.
  • a high turbine inlet temperature is required.
  • this high temperature involves an undesired high NOx emission level.
  • a so called “sequential" gas turbine is particularly suitable.
  • a sequential gas turbine comprises two combustors or combustion stages in series wherein each combustor is provided with a plurality of burners and with at least a combustion chamber.
  • the upstream or first combustor comprises a plurality of so-called "premix burners".
  • a premix burner is a burner configured not only for injecting the fuel in the compressed air but also for mixing with a swirl the compressed air and the fuel before injecting the mixture into the combustion chamber.
  • This swirling mixture is obtained by providing a swirling cone configured for generating a swirl in the air flow wherein this cone is provided with a plurality of fuel injecting nozzles (called premix nozzles).
  • premix nozzles This swirling mixture allows to reduce the NOx emission but the generated flame is not sufficiently stable under some conditions.
  • the burner is also provided with a pilot lance configured for injecting fuel in a more concentrate manner into a non-swirling air flow. The diffusion flame generated by the pilot is actually more stable but it generates higher NOx emission.
  • a premix burner is thus widely used because it allows to selective use a premix flame with low NOx emission during the normal operation and a more stable diffusion flame only under some conditions, for instance during the cold starting operation.
  • the present invention is not limited only to sequential gas turbines but it could be applied in all gas turbine provided with a premix burner as above described.
  • a change in fuel reactivity implies a change in flame location and behavior.
  • higher fuel reactivity like H2 forces the flame to move upstream, increasing NOx emissions, and potentially overheating the nozzles.
  • highly reactive fuels e.g. fuels containing large quantities of either higher hydrocarbons or hydrogen, including syngas and pure hydrogen
  • the flame, in particular the premix flame moves upstream compared to the case of natural gas, thus increasing the risk of flashback.
  • a solution for avoiding this flashback of the premix flame could be to lower the flame temperature (by feeding less fuel).
  • the flame temperature cannot be lowered beyond a certain limit, called “lean blow out” temperature, because under this temperature the operation of the combustor is compromised.
  • a primary object of the present invention is to provide a premix burner for a gas turbine assembly for power plants) and a method for operating this burner for overcoming the drawbacks of the current prior art practice.
  • the scope of the present invention is to provide a premix burner configured to be selectively fed by common (natural) gas fuels and by highly reactive gas fuel, for instance H2-based fuel having a high % of H2 (in vol. up to 100%).
  • the present invention refers to a new and inventive premix burner for a gas turbine assembly for a power plant.
  • the invention is not limited to a particular kind of gas turbine assembly but it can be applied to a general gas turbine comprising:
  • the gas turbine may involve a single combustion stage or a double/sequential combustion.
  • the following detailed description will refer to two not limiting example of sequential combustion gas turbines.
  • a first feature of the present invention is to provide a first gas fuel source and a second gas fuel source wherein the first source delivers natural gas fuel and the second source delivers H2-based gas fuel.
  • the scope of the present invention is, as foregoing cited, to provide a premix burner configured to be selectively fed by common (natural) gas fuels and by highly reactive gas fuel.
  • the source may be proximal or distal with respect to the burner and each source may comprise more than one feeding lines for feeding with the same fuel a plurality of components of the gas turbine.
  • premix burner suitable to be improved by the present invention is defined in the preamble of claim 1.
  • this premix burner is a premix burner comprising:
  • the swirler comprises a cone body
  • the casing comprises a tubular body
  • premix injection nozzles are fed by the fuel gas because a premixed flame generates less NOx emissions.
  • the premixed flame is not stable enough.
  • the gas flow or part of it is directed to the pilot generating a more stable flame that, however, generates higher Nox emissions.
  • the feeding of the premix injection nozzles may generate drawbacks because the flame is too reactive and a flashback effect may occur.
  • the premix burner of the present invention comprises a collar having an upstream end connected to the second end of the casing and a downstream end facing a combustion chamber.
  • the collar is provided with downstream injection nozzles connected to a second gas fuel source.
  • the second gas fuel source is a source feeding H2-based gas fuel or in general highly reactive fuel
  • this fuel is not (or only in minimal part) fed to premix nozzles (flashback problem), is not (or only in minimal part) fed to the pilot nozzles (Nox problem) but it is mainly fed to the downstream injection nozzles that involve a kind of compromise between a diffusion and a premixed flame with an acceptable Nox emissions without any flashback risk.
  • the premix injection nozzles and the pilot injection nozzles may be also connected to the second gas fuel source as also the downstream injection nozzles may be connected to the first gas fuel source so that the gas fuels may be fed to all nozzles depending on the fuel compositions and engine load of the system.
  • downstream injection nozzles are annular arranged about the burner axis A, i.e. in a plane orthogonal to the burner (pilot) axis A.
  • the downstream injection nozzles are arranged along a circumference (in a plane) inclined with respect to the burner axis A.
  • the downstream injection nozzles may disclose different axial positions.
  • each nozzle of the downstream injection nozzles is configured for generating an injected flow inclined with respect to the burner axis A, i.e. not an axial flow.
  • each nozzle of the downstream injection nozzles is a coaxial nozzle comprising an inner nozzle fed by the highly reactive H2-based fuel gas and an outer nozzle fed by compressed air.
  • the collar is provided with additional air nozzles fed by compressed air.
  • the above air nozzles are configured for generating an axial air flow.
  • the invention refers also to a method for operating such a premix burner; the method comprising the steps of:
  • the method may comprise also the step of: d) decreasing the feeding of the downstream injection nozzles and re-starting with the feeding of the premix injection nozzles and/or the pilot injection nozzles.
  • steps c) and/or d) may be performed simultaneously or a double feeding may be temporarily performed.
  • the step of "decreasing" the feeding depends on the gas fuel composition and on the engine load of the system.
  • the method allows to feed the premix injection nozzles and/or pilot injection nozzles and/or the downstream injection nozzles with the natural gas fuel or the H2-based gas fuel in different rate depending on the fuel composition and on the engine load of the system.
  • FIG. 1 is a schematic view of a first example of a gas turbine 1 comprising a sequential combustor that can be operated according to the method of the present invention.
  • figure 1 discloses a gas turbine with a high pressure and a low pressure turbine.
  • the gas turbine 1 of figure 1 comprises a compressor 3, a first combustor 31, a high-pressure turbine 5, a second combustor 32 and a low-pressure turbine 7.
  • the compressor 3 and the two turbines 5, 7 are part of or are connected to a common rotor 8 rotating around an axis 9 and surrounded by a concentric casing 10.
  • the compressor 3 is supplied with air and is provided with rotating blades 18 and stator vanes 19 configured for compressing the air entering the compressor 3.
  • the compressed air flows into a plenum 11 and from there into a plurality of first burners 12 of the first combustor 31 arranged as a ring around the axis 9.
  • Each first burner 12 is configured for injecting fuel (supplied by a first fuel supply 13) in the air flow, in particular this first burner 12 may be defined as a "premix" burner because it is configured for mixing the air and the injected fuel before the ignition point.
  • Figures 4 and 5 disclose an example of a premix burner according to the present invention.
  • the fuel/compressed air mixture flows into a first combustion chamber 4 annularly shaped where this mixture is combusted via a forced ignition, for instance by a spark igniter.
  • the resulting hot gas leaves the first combustor chamber 4 and is partially expanded in the high-pressure turbine 5 performing work on the rotor 8.
  • Downstream of the high-pressure turbine 5 the hot gas partially expanded flows into a second burner 33 where fuel supplied by a fuel lance 14 is injected.
  • the partially expanded gas has a high temperature and contains sufficient oxygen for further combustion that occurs based on a self-ignition in the second combustion chamber 6 arranged downstream of the second burner 33.
  • This second burner 33 is also called a "reheat" burner.
  • the reheated hot gas leaves the second combustion chamber 6 and flows in the low-pressure turbine 7 where it is expanded performing work on the rotor 8.
  • the low-pressure turbine 7 comprises a plurality of stages, or rows, of rotor blades 15 arranged in series in the main flow direction. Such stages of blades 15 are interposed by stages of stator vanes 16.
  • the rotor blades 15 are connected to the rotor 8 whereas the stator vanes 16 are connected to a vane carrier 17 that is a concentric casing surrounding the low-pressure turbine 7.
  • FIG. 2 is a schematic view of a second example of a gas turbine 20 comprising a sequential combustor that can be operated according to the method of the present invention.
  • figure 2 discloses a gas turbine 20 provided with a compressor 29, one turbine 21 and a sequential combustor 22.
  • the sequential combustor 22 of figure 2 comprises a plurality of so-called can combustors, i.e. a plurality of cylindrical casings wherein each can combustor houses a plurality of first burners 24, for instance four first burners 24, a first combustion chamber 25, a second burner 26, and a second combustion chamber 27.
  • an air mixer (not represented) may be provided configured for adding air in the hot gas leaving the first combustion chamber 25.
  • the sequential combustor arrangement is at least in part housed in an outer casing 28 supporting the plurality of can combustor 22 arranged as a ring around the turbine axis.
  • a first fuel is introduced via a first fuel injector (not shown) into the first burners 24 wherein the fuel is mixed with the compressed gas supplied by the compressor 29.
  • each first burner 24 of this embodiment is a "premix" burner configured for generating a premix flame and a diffusion flame.
  • Each first burner 24 of figure 2 and each first burner 12 of figure 1 is independently operable, i.e.
  • each first burner may be switched off independently of the other first burners and each first burner may be operated independently in terms of ratio between the fuel injected in the diffusion mode and the fuel injected in the premix mode.
  • the hot gas leaving the second combustion chamber 27 expands in the turbine 21 performing work on a rotor 30.
  • the premix burner 34 comprises:
  • the collar body 39 is provided with downstream injection nozzles that are connected to a second gas fuel source.
  • This fuel source is a highly reactive H2-based fuel gas source so that the downstream injection nozzles are fed by this particular kind of fuel.
  • the downstream injection nozzles are annularly arranged about the burner axis A, i.e. along a circle in a plane orthogonal to the burner axis.
  • the burner may be provided without the collar.
  • the downstream injection nozzles are arranged at the downstream end of the tubular body.
  • Figure 4 discloses a second example of a premix burner according to the invention.
  • the downstream injection nozzles are arranged along a circumference in a plane not orthogonal but inclined with respect to the burner axis (A).
  • A burner axis
  • FIG. 5 discloses a first example of a downstream nozzle according to the invention.
  • each nozzle of the downstream injection nozzles is configured for generating an injected flow inclined with respect to the burner axis A.
  • the nozzle is a coaxial nozzle comprising an inner nozzle fed by the highly reactive H2-based fuel gas and an outer nozzle fed by compressed air.
  • the collar body is provided with additional air nozzles fed by compressed air wherein each of these the air nozzles 41 is configured for generating an axial air flow.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP21216659.9A 2021-12-21 2021-12-21 Gasturbine für ein kraftwerk mit vormischbrenner versorgt mit üblichen und hochreaktiven brennstoffen sowie verfahren zu deren betrieb Active EP4202308B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP21216659.9A EP4202308B1 (de) 2021-12-21 2021-12-21 Gasturbine für ein kraftwerk mit vormischbrenner versorgt mit üblichen und hochreaktiven brennstoffen sowie verfahren zu deren betrieb
CN202211645813.7A CN116293798A (zh) 2021-12-21 2022-12-21 适合供给有普通燃料和高反应性燃料的用于针对发电厂的燃气涡轮组件的预混烧嘴

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21216659.9A EP4202308B1 (de) 2021-12-21 2021-12-21 Gasturbine für ein kraftwerk mit vormischbrenner versorgt mit üblichen und hochreaktiven brennstoffen sowie verfahren zu deren betrieb

Publications (2)

Publication Number Publication Date
EP4202308A1 true EP4202308A1 (de) 2023-06-28
EP4202308B1 EP4202308B1 (de) 2024-08-28

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EP21216659.9A Active EP4202308B1 (de) 2021-12-21 2021-12-21 Gasturbine für ein kraftwerk mit vormischbrenner versorgt mit üblichen und hochreaktiven brennstoffen sowie verfahren zu deren betrieb

Country Status (2)

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CN (1) CN116293798A (de)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6210152B1 (en) * 1998-09-16 2001-04-03 Abb Research Ltd. Burner for a heat generator and method for operating the same
US20040226297A1 (en) * 2001-10-19 2004-11-18 Timothy Griffin Burner for synthesis gas
US20090081599A1 (en) * 2006-03-27 2009-03-26 Stefano Bernero Burner for the operation of a heat generator
US20120047907A1 (en) * 2010-08-24 2012-03-01 Alstom Technology Ltd Method for operating a combustion chamber and combustion chamber
US20130224672A1 (en) * 2008-03-07 2013-08-29 Alstom Technology Ltd Method and burner arrangement for the production of hot gas, and use of said method
US20180216828A1 (en) * 2015-08-20 2018-08-02 Siemens Aktiengesellschaft A premixed dual fuel burner with a tapering injection component for main liquid fuel
US20190162414A1 (en) * 2016-06-30 2019-05-30 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6210152B1 (en) * 1998-09-16 2001-04-03 Abb Research Ltd. Burner for a heat generator and method for operating the same
US20040226297A1 (en) * 2001-10-19 2004-11-18 Timothy Griffin Burner for synthesis gas
US20090081599A1 (en) * 2006-03-27 2009-03-26 Stefano Bernero Burner for the operation of a heat generator
US20130224672A1 (en) * 2008-03-07 2013-08-29 Alstom Technology Ltd Method and burner arrangement for the production of hot gas, and use of said method
US20120047907A1 (en) * 2010-08-24 2012-03-01 Alstom Technology Ltd Method for operating a combustion chamber and combustion chamber
US20180216828A1 (en) * 2015-08-20 2018-08-02 Siemens Aktiengesellschaft A premixed dual fuel burner with a tapering injection component for main liquid fuel
US20190162414A1 (en) * 2016-06-30 2019-05-30 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor

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Publication number Publication date
CN116293798A (zh) 2023-06-23
EP4202308B1 (de) 2024-08-28

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