EP3209941B1 - Gasturbineneinheit mit multifluid-brennstoffversorgung - Google Patents

Gasturbineneinheit mit multifluid-brennstoffversorgung Download PDF

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Publication number
EP3209941B1
EP3209941B1 EP15804947.8A EP15804947A EP3209941B1 EP 3209941 B1 EP3209941 B1 EP 3209941B1 EP 15804947 A EP15804947 A EP 15804947A EP 3209941 B1 EP3209941 B1 EP 3209941B1
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EP
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Prior art keywords
nozzles
gas turbine
line
turbine unit
fuel
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EP15804947.8A
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English (en)
French (fr)
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EP3209941A1 (de
Inventor
Enrico GOTTARDO
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Ansaldo Energia SpA
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Ansaldo Energia SpA
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07008—Injection of water into the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07009—Injection of steam into the combustion chamber
    • 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 a gas turbine unit with a multifluid fuel supply.
  • the need of minimizing pollutant emissions is accompanied by the need of maintaining adequate flame stability across a wide range of operating conditions, in order not to degrade plant performance.
  • the above-mentioned needs may push toward conflicting directions, whereby it is not always possible to achieve satisfactory compromises.
  • EP 2 487 419 A2 discloses a gas turbine unit comprising a combustion chamber and a supply system.
  • the combustion chamber is provided with a plurality of burner assemblies, each of which comprises a respective lance injector.
  • the supply system is configured to supply fuel to the burner assemblies.
  • Another example of a known gas turbine unit is disclosed in EP 2 489 934 A2 .
  • the object of the present invention is therefore to provide a gas turbine unit that enables overcoming the described limitations and, in particular, reducing the emission of polluting substances without compromising flame stability.
  • a gas turbine unit is provided as defined in claim 1. Further detailed characteristics and advantages are described in the dependent claims.
  • Figure 1 schematically shows a gas turbine unit 1 and a control device 2 for the gas turbine unit 1.
  • Il gas turbine unit 1 comprises un compressor 3, an annular-type combustion chamber 5, a turbine 7 and a supply system 8 for supplying fuel to the combustion chamber 5.
  • Sensors 9.1, ..., 9.N measure respective plant quantities and provide corresponding measurement signals S M1 , ..., S MN to the control device 2.
  • the supply system 8 supplies the combustion chamber 5 with a regulated flow of one or more types of fuel, such as, and by way of non-limitative example, natural gas, HFO (Heavy Fuel Oil), Bunker C, syngas and diesel fuel.
  • fuel such as, and by way of non-limitative example, natural gas, HFO (Heavy Fuel Oil), Bunker C, syngas and diesel fuel.
  • the combustion chamber 5 uses natural gas as the primary fuel and diesel fuel as a secondary or back-up fuel.
  • the primary fuel and the secondary fuel are supplied to the combustion chamber 5 through a first fuel supply line 10 and a second fuel supply line 11, respectively, which are mutually independent.
  • the supply system 8 supplies the combustion chamber 5 with a flow of inert fluid through an inert supply line 12.
  • An inert fluid means a fluid in a liquid or gaseous state that does not take part in the combustion reactions.
  • an inert fluid is substantially without either combustible components, or oxidizing (combustion) agents.
  • the inert fluid supplied to the combustion chamber 5 could be nitrogen or demineralized water.
  • the combustion chamber 5 is provided with a plurality of burner assemblies 15 (for example 24 burner assemblies 15), which use the fuels supplied by the supply system 8.
  • the supply system 8 comprises regulating members controlled by respective regulators to control the flow rates of primary fuel, secondary fuel and inert fluid to the burner assemblies 15.
  • Each burner assembly 15 comprises a main burner 17, a partial premix pilot burner 18 and a lance injector 20, the structure of which shall be described in greater detail below.
  • a lance injector means an injector generally having an elongated shape, with a predominant axial longitudinal dimension and defined by one or more coaxial tubular bodies. In particular, it is meant to indicate a type of injector designed to be inserted along the main axis of a burner or burner assembly.
  • a lance injector is meant to be supplied indifferently with a gas fuel (such as natural gas, syngas) or a liquid fuel (such as diesel fuel, HFO or Bunker C).
  • a gas fuel such as natural gas, syngas
  • a liquid fuel such as diesel fuel, HFO or Bunker C
  • a lance injector can also receive a flow of a liquid or gaseous inert fluid, which does not take part in the combustion.
  • the regulating members of the supply system 8 comprise: a first main regulating valve 21, arranged between the first fuel supply line 10 and the main burners 17 and controlled by a first main regulator 22; a second main regulating valve 32, arranged between the second fuel supply line 10 and the main burners 17 and controlled by a second main regulator 34; a partial premix regulating valve 23, arranged between the first fuel supply line 10 and the pilot burners 18 and controlled by un partial premix regulator 24; a first lance regulating valve 26, arranged between the first fuel supply line 10 and a lance supply line 25, which is fluidically coupled to the lance injectors 20; a second lance regulating valve 27, arranged between the inert supply line 12 and the lance supply line 25; and a secondary regulating valve 28, arranged between the second fuel supply line 11 and the lance injectors 20.
  • first lance regulator 30 generically means the assembly of physical components (hardware) and possible program code portions (software) that enable performing the functions of regulating the flow-rate of primary fuel and the flow-rate of inert fluid to the lance injectors 20 via the first lance regulating valve 26 and the second lance regulating valve 27, based on the setpoints determined by the control device 2 and the measurement signals.
  • processing modules that are configured to determine fluid flow rates based on the assigned load conditions and the degrees of opening of the first lance regulating valve 26 and the second lance regulating valve 27 based on the determined flow rates; and actuator members that can be operated to achieve the desired degrees of opening of the first lance regulating valve 26 and the second lance regulating valve 27.
  • the definition also includes an embodiment where separate regulator devices operating in a coordinated manner are provided for the first lance regulating valve 26 and the second lance regulating valve 27.
  • the secondary regulating valve 28 is controlled by a second lance regulator 31.
  • the supply system 8 may also comprise further elements not shown, in particular manifolds for uniformly distributing the fluid flows leaving the regulating members to the burner assemblies 15.
  • burner assemblies 15 One of the burner assemblies 15 is shown in detail in Figure 3 . It is understood that the other burner assemblies 15 have the same structure.
  • the burner assembly 15 extends along an axis A, around which the main burner 17 is peripherally arranged and with the pilot burner 18 arranged centrally.
  • the lance injector 20 is inserted inside the pilot burner 18, always along axis A.
  • the main burner 17 is of the premix type, is arranged around the pilot burner 18 and is equipped with a swirler, indicated with reference numeral 33.
  • the swirler 33 is radially defined between a body 35 and a substantially truncated cone shaped wall 36.
  • the body 35 has a cylindrical axial cavity and, outwardly, also has a truncated cone shape.
  • the swirler 33 also comprises a plurality of blades 37, defining between them respective flow channels 38 to convey a flow of combustion air, with a diagonal flow path with respect to axis A, towards the combustion chamber 5.
  • the main burner 17 receives the flow of primary fuel supplied by the first main regulating valve 21 through a first premix conduit 39, which extends around axis A and terminates in an annular manifold, made inside the body 35 and communicating with the flow channels 38' through passageways made in the blades 37.
  • a second premix conduit 40 receives the flow of fuel supplied by the second main regulating valve 32 and injects it downstream of the blades 37.
  • the swirler 33 provides vigorous mixing of air that forms in the flow channels 38 and the flow of fuel, with an amount of air exceeding the theoretical stoichiometric ratio to generate a lean premixed flame.
  • the pilot burner 18 comprises a first truncated cone shaped body 41 and a second truncated cone shaped body 42, between which an axial type of swirler 43 is defined ( Figures 1 and 3 ).
  • the first truncated cone shaped body 41 extends around axis A and has an axial through cavity, in which the lance injector 20 is housed.
  • the second truncated cone shaped body 42 which is hollow, is arranged around the first truncated cone shaped body 41, is coaxial to the latter and is connected to outer truncated cone shaped surface of the body 35.
  • the swirler 43 comprises a plurality of blades 45, which are arranged in the space between the first truncated cone shaped body 41 and the second truncated cone shaped body 42.
  • Flow channels 44 are defined between adjacent pairs of blades 45.
  • the blades 45 extend beyond the front edge of the first truncated cone shaped body 41, up to the front edge of the second truncated cone shaped body 42.
  • a radially internal edge of the blades 45 is free for a distance, while the radially outer edge ends close to the front edge of the second truncated cone shaped body 42.
  • the pilot burner 18 is provided with its separate nozzle systems and receives the flow of primary fuel coming from the partial premix regulating valve 23 through the partial premix conduits 46, 47 concentric about axis A. Alternatively, the pilot burner 18 is supplied only by partial premix conduit 46.
  • the lance injector 20 comprises an outer tubular body 50 that extends along axis A.
  • An inner tubular body 51 is housed in an axial through cavity of the tubular body 50 and defines a secondary delivery line 52 and a secondary return line 53.
  • the secondary delivery line 52 is defined by the inner tubular body 51 and is coupled to a respective branch of the second fuel supply line 11 through a connector 54.
  • the secondary return line 53 is defined by an annular air space between the outer tubular body 50 and the inner tubular body 51.
  • a terminal element 55 placed at an injection tip of the lance injector 20, forms a chamber that connects the secondary delivery line 52 and the secondary return line 53.
  • the terminal element 55 also has one or more central nozzles 56 shaped to produce a diffusion flame in the combustion chamber 5.
  • the outer tubular body 50 houses an internal supply line 58 that is arranged concentrically around the secondary delivery line 52 and the secondary return line 53.
  • the internal supply line 58 is fluidically coupled with the lance supply line 12 through a connector 59 to receive primary fuel, inert fluid or a mixture of primary fuel and inert fluid, according to the settings of the first lance regulator 30 determined according to the operating conditions of the gas turbine unit 1.
  • the internal supply line 58 can be defined by an annular air space in the outer tubular body 50 or by a plurality of separate conduits.
  • a plurality of peripheral nozzles 60 arranged in a ring around axis A and the central nozzles 56 enables injection into the combustion chamber 5 of the fluid flow received through the internal supply line 58.
  • the peripheral nozzles 60 are shaped so as to generate a diffusion flame in the combustion chamber 5 when the fluid flow determined by the first lance regulator 30 contains a fuel fraction (in practice, when the first lance regulating valve 26 is not completely closed).
  • the composition of the fluid supplied to the combustion chamber 5 through the internal supply line 58 is controlled by the first lance regulator 30 according to the operating conditions.
  • the injection of a controlled flow rate of inert fluid enables controlling combustion conditions, in particular the temperature, in the central region of the burner, where the flame is of the diffused type. This allows achieving benefits in pollutant emission levels of the pilot flame and preserving the combustion stabilization effect.
  • the diffusion flame is generated via the injection of diesel fuel through the central nozzles 56.
  • the first lance regulator 30 can supply a controlled flow rate of just inert fluid, which locally cools the diffusion flame region, especially at the base of the flame.
  • the peripheral nozzles 60 are thus used exclusively to control flame temperature and the reduction of pollutant emission levels, while the stabilization function is performed by the central nozzles 56.
  • the injection of diesel fuel could be suspended and the peripheral nozzles 60 could be used to generate a diffusion flame.
  • the first lance regulator 30 determines the proportioning between the flow rate of primary fuel and the flow rate of inert fluid according to required load conditions of the gas turbine unit 1.
  • the first lance regulator 30 balances the stabilization effect according to the power requested, by acting on the first lance regulating valve 26 to regulate the flow rate of primary fuel; and the flame temperature control effect, by acting on the second lance regulating valve 27 to regulate the flow rate of inert fluid.
  • the lance regulator 30 can interrupt the supply of inert fluid and provide just the primary fuel. In this case, the flame generated by the lance injector 20 with the primary fuel is purely diffusive, but of extremely small size, given the position of the peripheral nozzles 60 in the immediate vicinity of axis A of the burner assembly 15.
  • the mixture of fuel and inert fluid injected close to axis A of the burner assembly 15 in controlled proportions enables reducing pollutant emissions from the diffusion flame to the minimum allowed by the stability limit of the burner assembly 15, which has, at the same time, been improved.
  • the burner assemblies 15 comprise lance injectors 120 set up to inject primary fuel and inert fluid (or a mixture of the two) and does not have lines and nozzles for the injection of a secondary fuel.
  • each lance injector 120 comprises a tubular body 150, which extends along an axis and has an empty axial through cavity 151.
  • the tubular body 151 houses an internal supply line 158 that is fluidically coupled with the lance supply line 12 through a connector 159 to receive primary fuel, inert fluid or a mixture of primary fuel and inert fluid, according to the settings of the first lance regulator 30 determined according to the operating conditions of the gas turbine unit 1.
  • the axial cavity 151 may be used to allow the passage of cooling air, in particular for the purpose of avoiding overheating of the tubular body 151 close to the flame region.
  • Peripheral nozzles 160 arranged in a ring around axis enable injection into the combustion chamber 5 of the fluid flow received through the internal supply line 158.
  • the peripheral nozzles 160 are shaped so as to generate a diffusion flame in the combustion chamber 5 when the fluid flow determined by the first lance regulator 30 contains a fuel fraction.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Claims (9)

  1. Gasturbineneinheit, enthaltend:
    eine Brennkammer (5), die mit einer Vielzahl von Brenneranordnungen (15) versehen ist, wobei jede Brenneranordnung (15) einen jeweiligen Lanzeninjektor (20; 120) aufweist; und
    ein Versorgungssystem (8), das für die Versorgung der Brenneranordnungen (15) mit Brennstoff konfiguriert ist;
    wobei jeder Lanzeninjektor (20; 120) eine Vielzahl von ersten Düsen (60; 160) und eine erste interne Fluidleitung (58; 158) aufweist, die in Fluidverbindung mit den ersten Düsen (60; 160) steht;
    wobei das Versorgungssystem (8) eine erste Brennstoffversorgungsleitung (10) und eine Inert-Versorgungsleitung (12) aufweist, die dafür konfiguriert sind, einen Primärbrennstoff bzw. ein Inertfluid den ersten Düsen (60; 160) durch die erste interne Fluidleitung (58; 158) zuzuführen;
    wobei in jeder Brenneranordnung (15) der Lanzeninjektor (20; 120) aufweist:
    einen äußeren rohrförmigen Körper (50), der sich entlang einer Achse (A) erstreckt, und einen inneren rohrförmigen Körper (51), der in einem axialen Durchgangshohlraum des rohrförmigen Körpers (50) untergebracht ist;
    eine oder mehrere zweite Düsen (56); und
    eine zweite interne Fluidleitung (52, 53), die in Fluidverbindung mit der einen oder den mehreren zweiten Düsen (56) steht;
    und wobei das Versorgungssystem (8) eine zweite Brennstoffversorgungsleitung (11) aufweist, die dafür konfiguriert ist, einen Sekundärbrennstoff der einen oder den mehreren zweiten Düsen (56) durch die zweite interne Fluidleitung (52, 53) zuzuführen;
    dadurch gekennzeichnet, dass die zweite interne Fluidleitung (52, 53) enthält:
    eine Abgabeleitung (52), die durch den inneren rohrförmigen Körper (51) gebildet ist;
    eine Rückführleitung (53), die durch einen ringförmigen Luftraum zwischen dem äußeren rohrförmigen Körper (50) und dem inneren rohrförmigen Körper (51) gebildet ist;
    ein Abschlusselement (55), das an einer Einspritzspitze des Lanzeninjektors (20) angeordnet ist und eine Kammer bildet, die die Abgabeleitung (52) und die Rückführleitung (53) verbindet und mit der einen oder den mehreren zweiten Düsen (56) versehen ist,
    wobei die Abgabeleitung (52) und die Rückführleitung (53) koaxial sind; und
    wobei die erste interne Fluidleitung (58) in dem äußeren rohrförmigen Körper (50) konzentrisch außerhalb der zweiten internen Fluidleitung (52, 53) angeordnet ist.
  2. Gasturbineneinheit nach Anspruch 1, enthaltend Regulierelemente (26, 27, 30), die dafür konfiguriert sind, eine erste Durchflussmenge des Primärbrennstoffs und eine zweite Durchflussmenge von Inertfluid zu den ersten Düsen (60) zu regulieren.
  3. Gasturbineneinheit nach Anspruch 2, wobei die Regulierelemente (26, 27, 30) ein erstes Regulierventil (26), das zwischen der ersten Brennstoffversorgungsleitung (10) und der ersten internen Fluidleitung (58; 158) angeordnet ist, ein zweites Regulierventil (27), das zwischen der Inert-Versorgungsleitung (12) und der ersten internen Fluidleitung (58; 158) angeordnet ist, und einen Regulierer (30) aufweisen, der dafür konfiguriert ist, die erste Durchflussmenge von Primärbrennstoff und die zweite Durchflussmenge von Inertfluid mit dem ersten Regulierventil (26) bzw. dem zweiten Regulierventil (27) zu regulieren.
  4. Gasturbineneinheit, wobei der Regulierer (30) dafür konfiguriert ist, den ersten Düsen (60; 160)
    ausschließlich Primärbrennstoff in einem ersten Betriebszustand;
    ausschließlich Inertfluid in einem zweiten Betriebszustand;
    eine Mischung aus Primärbrennstoff und Inertfluid in einem dritten Betriebszustand zuzuführen.
  5. Gasturbineneinheit nach einem der vorstehenden Ansprüche, wobei die ersten Düsen (60; 160) so geformt sind, dass sie eine Diffusionsflamme in der Brennkammer (5) erzeugen.
  6. Gasturbineneinheit nach einem der vorstehenden Ansprüche, wobei die ersten Düsen (60) um die eine oder die mehreren zweiten Düsen (56) herum angeordnet sind.
  7. Gasturbineneinheit nach einem der vorstehenden Ansprüche, enthaltend einen Vormisch-Hauptbrenner (17) koaxial mit dem Lanzeninjektor (20), der mit einem ersten Verwirbler (33) mit einem diagonalen Durchflussweg versehen ist.
  8. Gasturbineneinheit nach Anspruch 7, enthaltend einen Pilotbrenner (18) koaxial mit dem Lanzeninjektor (20) und dem Hauptbrenner (17), der mit einem axialen zweiten Verwirbler (43) versehen ist.
  9. Gasturbineneinheit nach Anspruch 8, wobei der Pilotbrenner (18) radial zwischen dem Hauptbrenner (17) und dem Lanzeninjektor (20) enthalten ist.
EP15804947.8A 2014-10-20 2015-10-20 Gasturbineneinheit mit multifluid-brennstoffversorgung Active EP3209941B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI20141808 2014-10-20
PCT/IB2015/058085 WO2016063222A1 (en) 2014-10-20 2015-10-20 Gas turbine unit with multifluid fuel supply and method of supplying a burner of a gas turbine unit

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EP3209941A1 EP3209941A1 (de) 2017-08-30
EP3209941B1 true EP3209941B1 (de) 2020-08-19

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Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3524799A1 (de) * 2018-02-13 2019-08-14 Siemens Aktiengesellschaft Verfahren zum betreiben einer brenneranordnung einer gasturbine
CN113091094B (zh) * 2021-05-13 2023-05-23 中国联合重型燃气轮机技术有限公司 燃气轮机燃烧室喷嘴及喷嘴中预混燃料和空气的方法
CN113091095B (zh) * 2021-05-13 2023-05-23 中国联合重型燃气轮机技术有限公司 燃气轮机燃烧室喷嘴及喷嘴中预混燃料和空气的方法
EP4187072A1 (de) * 2021-11-26 2023-05-31 Ansaldo Energia Switzerland AG Schweröleinspritzdüse und verfahren zur steuerung einer schweröleinspritzdüse
CN114754378B (zh) * 2022-06-13 2022-08-19 成都中科翼能科技有限公司 一种燃气轮机燃烧器结构

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040172951A1 (en) * 2001-07-19 2004-09-09 Frank Hannemann Method for operating a burner of a gas turbine and a power plant

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1659339A1 (de) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Verfahren zum Anfahren eines Brenners
JP4728176B2 (ja) * 2005-06-24 2011-07-20 株式会社日立製作所 バーナ、ガスタービン燃焼器及びバーナの冷却方法
US8312722B2 (en) * 2008-10-23 2012-11-20 General Electric Company Flame holding tolerant fuel and air premixer for a gas turbine combustor
JP2011094573A (ja) * 2009-10-30 2011-05-12 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器及び発電システム
US9017064B2 (en) * 2010-06-08 2015-04-28 Siemens Energy, Inc. Utilizing a diluent to lower combustion instabilities in a gas turbine engine
US20120208136A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120210717A1 (en) * 2011-02-21 2012-08-23 General Electric Company Apparatus for injecting fluid into a combustion chamber of a combustor
US8448442B2 (en) * 2011-05-19 2013-05-28 General Electric Company Flexible combustor fuel nozzle
US20120308947A1 (en) * 2011-06-06 2012-12-06 General Electric Company Combustor having a pressure feed

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040172951A1 (en) * 2001-07-19 2004-09-09 Frank Hannemann Method for operating a burner of a gas turbine and a power plant

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CN107110505B (zh) 2020-12-18
CN107110505A (zh) 2017-08-29
WO2016063222A1 (en) 2016-04-28
WO2016063222A9 (en) 2016-09-29
EP3209941A1 (de) 2017-08-30

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