EP4202308B1 - Gasturbine für ein kraftwerk mit vormischbrenner versorgt mit üblichen und hochreaktiven brennstoffen sowie verfahren zu deren betrieb - Google Patents

Gasturbine für ein kraftwerk mit vormischbrenner versorgt mit üblichen und hochreaktiven brennstoffen sowie verfahren zu deren betrieb Download PDF

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Publication number
EP4202308B1
EP4202308B1 EP21216659.9A EP21216659A EP4202308B1 EP 4202308 B1 EP4202308 B1 EP 4202308B1 EP 21216659 A EP21216659 A EP 21216659A EP 4202308 B1 EP4202308 B1 EP 4202308B1
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EP
European Patent Office
Prior art keywords
gas
injection nozzles
gas turbine
combustor
fuel
Prior art date
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EP21216659.9A
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English (en)
French (fr)
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EP4202308A1 (de
Inventor
Andrea Ciani
Mirko Ruben Bothien
Michael Klaus DUESING
Michael Thomas Maurer
Douglas Pennell
John Wood
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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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
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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.
  • US2018216828 refers to a premixed dual fuel burner. US2018216828 refers to the problem of switching from gas to liquid fuel.
  • US2004226297 relates to a burner, for operation in a combustion chamber, preferably in combustion chambers of gas turbines, which substantially comprises a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream.
  • US2004226297 refers to the risk of flashback in case of H2 based fuel.
  • US2012047907 refers to a premix combustion chamber of a gas turbine. US2012047907 refers to problem of reducing the NOx emissions, in particular in case of use a H2 based fuel.
  • US6210152 refers to burners of gas turbines operated in premix mode. US6210152 refers to the problem of the flame instability.
  • a primary object of the present invention is to provide a gas turbine for a power plant and a method for operating this gas turbine for overcoming the drawbacks of the current prior art practice.
  • the scope of the present invention is to provide a gas turbine with 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 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 the gas turbine with 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 gas turbine with 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.
  • a premix burner used in the gas turbine according to the invention 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.
  • a collar is provided 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 H2-based gas 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.
  • 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 gas turbine assembly; 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 of the gas turbine 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.
  • figure 3 is a first example of a premix burner of the gas turbine according to the invention.
  • 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 of a gas turbine 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
  • figure 5 discloses a first example of a downstream nozzle of the gas turbine 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)

Claims (14)

  1. Gasturbine für ein Kraftwerk, wobei die Gasturbine umfasst:
    - einen Verdichter zur Erzeugung eines Druckluftstroms;
    - eine Brennkammer zum Zugeben von Brennstoff zur Druckluft und zum Erzeugen eines Heißgasstroms;
    - eine durch den heißen Gasstrom angetriebene Turbine;
    - eine erste Brennstoffgas-Quelle von Erdgas-Brennstoff;
    - eine zweite Brennstoffgas-Quelle von H2-basiertem Brennstoffgas;
    wobei die Brennkammer wenigstens einen Vormischbrenner (34) umfasst, der umfasst:
    - eine Verwirbelungsvorrichtung (35), die einen konischen Körper umfasst und ein stromaufwärts gelegenes Ende, das mit Druckluft gespeist wird, und ein stromabwärts gelegenes Ende aufweist, wobei die Verwirbelungsvorrichtung dazu konfiguriert ist, den Luftstrom zu verwirbeln, und mit Vormisch-Injektionsdüsen (36) versehen ist, die mit der ersten Brennstoffgas-Quelle verbunden sind;
    - ein Gehäuse (37), das einen rohrförmigen Körper umfasst und ein erstes Ende, das mit dem stromabwärts gelegenen Ende der Verwirbelungsvorrichtung (35) verbunden ist, und ein zweites Ende aufweist;
    - eine Pilotlanze (38), die die Verwirbelungsvorrichtung (35) axial erweitert und ein stromabwärts gelegenes Ende aufweist, das in dem Gehäuse (37) untergebracht ist, wobei das stromabwärts gelegene Ende der Pilotlanze (38) mit Pilot-Injektionsdüsen versehen ist, die mit der ersten Brennstoffgas-Quelle verbunden sind;
    - einen mit dem Gehäuse (37) integral ausgebildeten Kragen (39), der ein stromaufwärts gelegenes Ende, das mit dem zweiten Ende des Gehäuses (37) verbunden ist, und ein stromabwärts gelegenes Ende, das einer Brennkammer zugewandt ist, aufweist;
    wobei der Kragen (39) mit stromabwärts gelegenen Injektionsdüsen (40) versehen ist, die mit der zweiten Brennstoffgas-Quelle verbunden sind.
  2. Gasturbine nach Anspruch 1, wobei die Vormisch-Injektionsdüsen (36) und die Pilot-Injektionsdüsen auch mit der zweiten Brennstoffgas-Quelle verbunden sind; wobei die stromabwärts gelegenen Injektionsdüsen (40) auch mit der ersten Brennstoffgas-Quelle verbunden sind, so dass die Brennstoffgase allen Düsen mit entsprechenden Durchsätzen zugeführt werden können, abhängig von den Brennstoffzusammensetzungen und der Maschinenlast des Systems.
  3. Gasturbine nach einem der vorangehenden Ansprüche, wobei die stromabwärts gelegenen Injektionsdüsen (40) ringförmig um die Brennerachse (A) angeordnet sind.
  4. Gasturbine nach einem der vorangehenden Ansprüche 1 bis 3, wobei die stromabwärts gelegenen Injektionsdüsen (40) an unterschiedlichen axialen Stellen angeordnet sind.
  5. Gasturbine nach einem der vorangehenden Ansprüche, wobei jede Düse der stromabwärts gelegenen Injektionsdüsen (40) dazu konfiguriert ist, eine in Bezug auf die Brennerachse (A) geneigte Injektionsströmung zu erzeugen.
  6. Die Gasturbine nach einem der vorangehenden Ansprüche, wobei jede Düse der stromabwärts gelegenen Injektionsdüsen (40) eine koaxiale Düse ist, die eine innere, mit Brennstoffgas gespeiste Düse und eine äußere, mit Druckluft gespeiste Düse umfasst.
  7. Gasturbine nach einem der vorangehenden Ansprüche, wobei der Kragen (39) mit zusätzlichen Luftdüsen (41) versehen ist, die mit Druckluft gespeist werden.
  8. Gasturbine nach Anspruch 7, wobei die Luftdüsen (41) dazu konfiguriert sind, einen axialen Luftstrom zu erzeugen.
  9. Gasturbine nach einem der vorangehenden Ansprüche, wobei die Gasbrennkammer eine sequentielle Brennkammer (22) ist, wobei die sequentielle Brennkammer (22) umfasst:
    - eine erste Brennkammer, die mit mehreren Vormischbrennern (12, 24) ausgestattet ist;
    - eine zweite Brennkammer, die mit mehreren zweiten Brennern (26, 33) ausgestattet ist, die mit heißem Gas aus der ersten Brennkammer gespeist werden.
  10. Gasturbine nach Anspruch 9, wobei die erste und die zweite Brennkammer ringförmig sind und durch eine Turbinenstufe getrennt sind.
  11. Gasturbine nach Anspruch 9, wobei die sequentielle Brennkammer mehrere Dosenbrenner umfasst, wobei jeder Dosenbrenner den ersten und den zweiten Brenner umfasst, die durch einen Verdünnungsluftmischer getrennt sind.
  12. Verfahren zum Betreiben einer Gasturbinenanordnung für ein Kraftwerk, wobei das Verfahren die Schritte umfasst:
    a) Bereitstellen einer Gasturbine nach einem der vorangehenden Ansprüche 1 bis 11;
    b) Bespeisen der Vormisch-Injektionsdüsen und/oder der Pilot-Injektionsdüsen mit Brennstoffgas aus der ersten Brennstoffquelle, während die Bespeisung der stromabwärts gelegenen Injektionsdüsen nicht durchgeführt wird;
    c) Verringern der Bespeisung der Vormisch-Injektionsdüsen und/oder der Pilot-Injektionsdüsen und Starten der Bespeisung der stromabwärts gelegenen Injektionsdüsen mit H2-basiertem Brennstoff aus der zweiten Brennstoffquelle.
  13. Verfahren nach Anspruch 12, wobei das Verfahren den Schritt umfasst:
    d) Verringern der Bespeisung der stromabwärts gelegenen Injektionsdüsen und erneutes Starten oder Erhöhen der Bespeisung der Vormisch-Injektionsdüsen und/oder der Pilot-Injektionsdüsen.
  14. Verfahren nach Anspruch 12 oder 13, wobei die Stopp- und Startphasen in den Schritten c) und/oder d) gleichzeitig durchgeführt werden oder eine doppelte Bespeisung vorübergehend durchgeführt werden kann.
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)

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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

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WO2026027101A1 (en) * 2024-08-02 2026-02-05 Nuovo Pignone Tecnologie - S.R.L. Fuel burner tube for a burner for highly reactive gas fuels
WO2026027100A1 (en) * 2024-08-02 2026-02-05 Nuovo Pignone Tecnologie - S.R.L. Fuel burner tube for a burner for highly reactive gas fuels

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EP0987493B1 (de) * 1998-09-16 2003-08-06 Abb Research Ltd. Brenner für einen Wärmeerzeuger
EP1436546B1 (de) * 2001-10-19 2016-09-14 General Electric Technology GmbH Brenner für synthesegas
EP1999410B1 (de) * 2006-03-27 2015-12-02 Alstom Technology Ltd Brenner für den betrieb eines wärmeerzeugers
EP2257736B1 (de) * 2008-03-07 2015-11-25 Alstom Technology Ltd Verfahren zum erzeugen von heissgas
EP2423591B1 (de) * 2010-08-24 2018-10-31 Ansaldo Energia IP UK Limited Verfahren zum Betrieb einer Brennkammer
EP3133342A1 (de) * 2015-08-20 2017-02-22 Siemens Aktiengesellschaft Vorgemischter dualer brennstoffbrenner mit sich verschmälernder einspritzkomponente für den hauptflüssigbrennstoff
JP2018004138A (ja) * 2016-06-30 2018-01-11 川崎重工業株式会社 ガスタービン燃焼器

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