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EP4206535B1 - Brenneranordnung mit inline-injektoren - Google Patents

Brenneranordnung mit inline-injektoren Download PDF

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Publication number
EP4206535B1
EP4206535B1 EP21218284.4A EP21218284A EP4206535B1 EP 4206535 B1 EP4206535 B1 EP 4206535B1 EP 21218284 A EP21218284 A EP 21218284A EP 4206535 B1 EP4206535 B1 EP 4206535B1
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EP
European Patent Office
Prior art keywords
line
burner
nozzles
crossflow
burner assembly
Prior art date
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Active
Application number
EP21218284.4A
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English (en)
French (fr)
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EP4206535A1 (de
Inventor
Michael Thomas Maurer
Andrea Ciani
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Priority to EP21218284.4A priority Critical patent/EP4206535B1/de
Priority to CN202211725530.3A priority patent/CN116379472A/zh
Publication of EP4206535A1 publication Critical patent/EP4206535A1/de
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Publication of EP4206535B1 publication Critical patent/EP4206535B1/de
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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
    • 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
    • F23R3/36—Supply of different fuels
    • 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]

Definitions

  • the present invention relates to a burner assembly with in-line injectors.
  • gas turbine engines especially if used in electric power production plants, may be fed with different types of fuel.
  • fuel gas of different nature and characteristics natural gas, syngas
  • fuel oils like diesel fuel can be injected into gas turbines.
  • burner assemblies having multiple injectors or burners.
  • Axial lance injectors specifically designed to deliver fuel oil, extend along a burner axis.
  • premix diagonal burners have frustoconical shape and are arranged around the respective pilot burners.
  • the diagonal burners may be supplied with any of fuel oil, fuel gas or hydrogen.
  • a premix diagonal burner has a plurality of swirl blades that define mixing channels and cause a rotation around the burner axis of air flowing therethrough.
  • Fuel feed passages extend radially trough the blades and discharge into the mixing channels through outlets in the lateral faces (intrados and/or extrados) of the blades.
  • Crossflow fuel injection is thus achieved. While crossflow injection is beneficial when gas is supplied, because efficient mixing of air and fuel is obtained, problem may rise when highly reactive fuels such as hydrogen are used.
  • crossflow injection is sensitive to momentum flux ratio changes also associated with a fuel with different Wobbe Index.
  • US 2004/050057 A1 discloses a burner assembly for a heavy-duty gas turbine engine comprising a main burner, extending around a burner axis and including, a swirler, having a plurality of blades circumferentially distributed around the burner axis, wherein mixing channels are defined between respective pairs of adjacent blades.
  • In-line injectors are arranged at inlet sections of respective mixing channels.
  • a burner assembly for a heavy-duty gas turbine engine comprising a main burner, extending around a burner axis and including:
  • the burner assembly thus includes several burners that allow operation on multiple fuels, including hydrogen, and are also flexible enough to cope with a wide range of operating conditions as currently required by market and regulatory authorities.
  • the monolithic inner body prevents any leakage from the hydrogen plenum, which may otherwise occur because of ageing of seals or native defects.
  • the in-line injectors are configured to deliver fuel substantially in the flow direction of air entering the mixing channels and avoid vortices which are normally associated with crossflow injection and may result in low velocity regions. Thus, flow velocity is not disturbed the risk of flame hold or flashback is reduced when highly reactive fuels like hydrogen are used.
  • the in-line injectors are located at the inlet of the mixing channels, substantially the whole length thereof is available to achieve sufficient mixing, so greater mixing effect associated with crossflow flow injection is not necessary.
  • the in-line injectors comprise respective airfoil-shaped posts with a trailing edge, wherein the in-line nozzles discharge at the respective trailing edge.
  • the in-line nozzles are configured to discharge along a tangent to a camber line of the respective in-line injector at the trailing edge.
  • the delivered fuel flow is thus consistent in direction with the air flow entering the mixing channels and turbulence that may cause drop of velocity is avoided.
  • lateral surfaces of the in-line injectors form lobes at least at the trailing edge and/or are provided with vortex generators, arranged upstream of the respective trailing edge and configured to swirl the flow.
  • Lobes and vortex generators may be designed to cause a swirl around the average flow direction, without causing recirculation or stagnation of the flow. Sufficient flow velocity may thus me preserved at any location to prevent flame hold and flashback when highly reactive fuels are used.
  • the burner assembly comprises a first plenum integrated in the inner body and fluidly coupled to the in-line nozzles of the in-line injectors.
  • the blades are provided with respective first crossflow nozzles, configured to discharge into the mixing channels of the respective blades in a first crossflow direction, transverse to the flow direction, through lateral surfaces of the respective blades.
  • the burner assembly comprises a second plenum fluidly coupled to the first crossflow nozzles and fluidly decoupled from the in-line nozzles, wherein the first plenum is fluidly decoupled from the first crossflow nozzles, the second plenum being preferably integrated in the inner body.
  • the burner assembly comprises second crossflow nozzles in the frustoconical outer surface of the inner body, configured to discharge in a second crossflow direction, transverse to the flow direction and preferably distinct from the first crossflow direction.
  • the burner assembly comprises a third plenum fluidly coupled to the second crossflow nozzles and fluidly decoupled from the in-line nozzles, wherein the first plenum is fluidly decoupled from the second crossflow nozzles, the third plenum being preferably integrated in the inner body.
  • Additional crossflow nozzles and plena allow to optimize separate and decoupled delivery paths for supply of additional kinds of fuels other than hydrogen, such as fuel gas and fuel oil.
  • the in-line injectors are arranged so as to discharge upstream of the first crossflow nozzles of the blades defining the respective mixing channels.
  • injection discharge upstream of the first crossflow nozzles has the advantage that the fuel flow delivered may help breaking and cross low velocity regions.
  • the in-line injectors extend from the inner body into the annular space, preferably each at a median plane of the respective mixing channel.
  • the burner assembly comprises a pilot burner, coaxially housed in the main burner, and a lance injector extending along the burner axis through the pilot burner.
  • a gas turbine engine comprising a combustor equipped with a plurality of burner assemblies according to any one of the preceding claims and a hydrogen supply line, fluidly coupled to the in-line injectors.
  • the gas turbine engine comprises a fuel oil supply line and a fuel gas supply line, each fluidly coupled to at least one of the pilot burner and the lance injector.
  • a heavy-duty gas turbine engine is indicated as a whole by reference numeral 1 and comprises a compressor 2, a combustor 3, a turbine 5 a fuel supply system 6 and a control system 7.
  • the compressor 2 and the turbine 5 are mounted to a same shaft, which extends along a main axis A.
  • the combustor 3 is of the annular type and is arranged about the main axis A between the compressor 2 and the turbine 5.
  • the combustor 3 comprises a plurality of burner assemblies 10, which are circumferentially distributed around the axis A, and an annular combustion chamber 11 (part of which is visible in figure 2 ) .
  • the burner assemblies 10 are mounted to respective burner seats of the combustor 3 by respective burner inserts 12.
  • the fuel supply system 6 is configured to supply different types of fuel to the combustor 3, including fuel oil, fuel gas, such as natural gas or syngas, and highly reactive fuel, namely fuel with high hydrogen content and simply identified as hydrogen in what follows for the sake of simplicity.
  • a fuel oil supply line 6a, a fuel gas supply line 6b and a hydrogen line 6c are provided for this purpose.
  • At least the fuel gas supply line 6b and the hydrogen supply line 6c may be mutually connected e.g. by interconnection lines and control valves (see e.g. control valve 6d, figure 2 ), whereby the control system 7 is enabled to supply pure fuel gas or hydrogen or a mixture thereof in accordance with design preferences and circumstances.
  • the proportion of fuel gas and hydrogen may be controlled as well.
  • the control system 7 defines a load set-point for the gas turbine engine 1 and operates engine actuators (orientable inlet guide vanes of the combustor 3 and fuel valves of the fuel supply system 6) to supply air and fuel flows to the combustor 3 so that the load set-point is met.
  • FIGS 2 and 3 show in detail one of the burner assemblies 10 and a portion of the combustion chamber 11.
  • the burner assembly 10 extends along an axis B and comprises a peripheral main burner 15, a central pilot burner 16 and a lance injector 17, all coaxially arranged about the burner axis B. More precisely, the pilot burner 16 is coaxially housed in the main burner 15 and the lance injector 17 extends along the burner axis B through the pilot burner 16.
  • At least the main burner 15 and possibly also the pilot burner 16 and the lance injector 17 may receive all available types of fuel, i.e. fuel oil, fuel gas and hydrogen. In other embodiments, however, the main burner 15 may receive fuel gas and hydrogen only and the pilot burner 16 and the lance injector 17 may receive fuel oil and/or fuel gas only.
  • the main burner 15 is of the premix type, arranged about the pilot burner 16 and fixed to the respective burner insert 12. More in detail, the main burner 15 extends through a central opening 12a of the burner insert 12, so that the outlet of the main burner 15 is within the combustion chamber 11.
  • the main burner 15 is arranged around the pilot burner 4 and is provided with a vortex or turbulence generating device, referred to as diagonal swirler, and indicated by reference numeral 20.
  • the diagonal swirler 20 extends about the burner axis B and is radially defined between an inner body 21 and an outer body 22 of the main burner 15.
  • the inner body 21 has a frustoconical outer surface 21a and in one embodiment is a monolithic body, e.g. made by an additive manufacturing process such as SLM (Selective Laser Melting).
  • the outer body 22 is axially hollow and comprises a frustoconical wall 22a and, in one embodiment, a cylindrical wall 22b connected to the frustoconical wall 22a by a joining portion 22c.
  • the frustoconical wall 22a coaxially accommodates the inner body 21, so that a substantially annular space 23 forming a passage for feeding the air-fuel mixture is defined between a frustoconical inner surface 22d of the frustoconical wall 22a of the outer body 22 and the frustoconical outer surface 21a of the inner body 21.
  • the diagonal swirler 20 comprises a plurality of blades 24 which extend in the annular space 23 between the inner body 21 and the outer body 22 around the burner axis B. Pairs of adjacent blades 24 define respective mixing channels 25 and are configured to cause a rotation around the burner axis B of a fluid flowing through the mixing channels 25. Inlets of the mixing channels 25 are defined at a larger base of the frustoconical wall 22a of the outer body 22 and allow the introduction of an air flow from the compressor 2.
  • the blades 24 are also provided with first crossflow nozzles 27 configured to discharge fuel gas and/or fuel oil in a first crossflow direction CF1, which is transverse to a flow direction F of fluid flowing through the mixing channels 25.
  • a plenum 28 is formed in the inner body 22 and is fluidly coupled to one or both of the fuel oil supply line 6a and the fuel gas supply line 6b on one side and to the first crossflow nozzles 27 through built-in channels (not shown).
  • Second crossflow nozzles 30 are formed in the frustoconical outer surface 21a of the inner body 21 and are configured to discharge fuel gas and/or fuel oil in a second crossflow direction CF2, transverse to the flow direction F and distinct from the first crossflow direction CF1.
  • the first crossflow direction CF1 may be a circumferential direction and the second crossflow direction CF2 may lie in a plane perpendicular to the first crossflow direction CF1.
  • a plenum 32 separate and isolated from the plenum 28, is formed in the inner body 21 and is fluidly coupled to one or both of the fuel oil supply line 6a and the fuel gas supply line 6b on one side and to the second crossflow nozzles 30.
  • the main burner 15 comprises also a plurality of in-line injectors 35, arranged at inlet sections of respective mixing channels 25 and have respective in-line nozzles 36, configured to discharge in a respective flow direction F of fluid flowing through the respective mixing channel 25.
  • in a respective flow direction F of fluid flowing through the respective mixing channel 25 means that, at the nozzles 36, the fuel delivered by the in-line injectors 35 has a component of velocity parallel to the velocity of the fluid that is greater than any component of velocity perpendicular to the velocity of the fluid.
  • the position of the in-line nozzles 36 is upstream of the first crossflow nozzles 27 and may be upstream or inside an inlet portion the respective mixing channels 25.
  • the in-line injectors 35 are arranged so as to discharge upstream of the first crossflow nozzles 27 of the blades 24 defining the respective mixing channels 25.
  • the in-line injectors 35 comprise respective airfoil-shaped posts 35a having a leading edge 35b and a trailing edge 35c and extending into the annular space 23 perpendicularly from the inner body 21 into the annular space (23).
  • the in-line injectors 35 are each at a median plane of the respective mixing channel 25.
  • the in-line injectors 35 may be slightly displaced and/or oriented toward the suction side of the blade 24 defining the respective mixing channel 25.
  • the in-line nozzles 36 are arranged at the trailing edge 35c of the respective in-line injector 35 and discharge therethrough.
  • An annular hydrogen plenum 40 is integrated in the inner body 21 and is fluidly coupled at least to the hydrogen line 6c and preferably to the fuel gas supply line 6b on one side and to the in-line nozzles 36 of the in-line injectors 35 on the other side, so that hydrogen or a mixture of hydrogen and fuel gas may be supplied to the main burner 15. More precisely, a chamber 41 extends longitudinally from a base portion to a tip portion of each in-line injector 35 ( figure 4 ) and is coupled to the hydrogen plenum 40 through a passage in the inner body 21. Feed passages 42 extend from the chamber 41 to respective nozzles 36.
  • the flow direction F at the trailing edges 35c of the in-line injectors 35 is aligned with a tangent to a camber line C of the respective in-line injector at the trailing edge 35c ( figure 5 ).
  • the hydrogen plenum 40 may also receive fuel gas or a mixture of fuel gas and hydrogen in some operating conditions, such as during startup transients. A ratio of fuel gas and hydrogen may be controlled by the control system 7 in accordance with design preferences.
  • the plenum 28 and the plenum 32 are fluidly decoupled from the in-line nozzles 36; likewise, the hydrogen plenum 40 is fluidly decoupled from the first crossflow nozzles 27 and from the second crossflow nozzles 30. Accordingly, hydrogen leakage toward the first crossflow nozzles 27 and the second crossflow nozzles 30 is prevented.
  • the plena 28, 32, 40 have respective fuel inlets at respective distinct angular positions. In figure 2 only the fuel inlet 40a of the hydrogen plenum 40 is shown.
  • the trailing edges 35c of the in-line injectors are straight.
  • lateral surfaces of the in-line injectors 35 form lobes 35d at least at the trailing edge 35c.
  • the lateral surfaces of the in-line injectors 35 are provided with vortex generators 35e, arranged upstream of the respective trailing edge 35c (here straight) and configured to swirl the flow.
  • Fuel supply to the combustor 3 is controlled by the control system 7.
  • fuel supply is controlled to cause a step transition from fuel gas or fuel oil supply (dashed line) to hydrogen supply (solid line) or vice versa, as shown in figures 8a and 8b , respectively.
  • hydrogen supply is increased gradually (e.g. according to a ramp), while the other active fuel, fuel gas or fuel oil, is correspondingly decreased ( figure 9a ) or, vice versa, hydrogen supply is decreased while the other fuel to be activated, fuel gas or fuel oil, is correspondingly increased ( figure 9b ).
  • the plena may have any suitable configuration and arrangement whereby the hydrogen plenum is separated and decoupled from the other plena.

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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)

Claims (14)

  1. Brenneranordnung für eine Hochleistungsgasturbine, aufweisend einen Hauptbrenner (15), der sich um eine Brennerachse (B) herum erstreckt und aufweist:
    einen Drallkörper (20), der eine Mehrzahl von Schaufeln (24) hat, die im Umfang um die Brennerachse (B) verteilt sind, wobei Mischkanäle (25) jeweils zwischen Paaren beieinanderliegender Schaufeln (24) definiert sind;
    eine Mehrzahl von Inline-Injektoren (35), die jeweils an Einlassabschnitten der Mischkanäle (25) angeordnet sind und jeweils Inline-Düsen (36) haben, die dazu konfiguriert sind, in einer jeweiligen Strömungsrichtung (F) eines durch den jeweiligen Mischkanal (25) strömenden Fluids einzudüsen;
    dadurch gekennzeichnet, dass der Drallkörper (20) ein diagonaler Drallkörper ist und dass der Hauptbrenner (15) einen inneren Körper (21), der eine kegelstumpfförmige Außenoberfläche (21a) hat, und einen äußeren Körper (22) aufweist, der eine kegelstumpfförmige Innenoberfläche (22d) hat, wobei zwischen der kegelstumpfförmigen Außenoberfläche (21a) des inneren Körpers (21) und der kegelstumpfförmigen Innenoberfläche (22d) des äußeren Körpers (22) ein ringförmiger Raum (23) definiert ist und wobei sich die Schaufeln (24) in dem ringförmigen Raum (23) erstrecken.
  2. Brenneranordnung gemäß Anspruch 1, wobei die Inline-Injektoren (35) jeweils flügelprofil-förmige Säulen (35a) mit einer hinteren Kante (35b) haben, wobei die Inline-Düsen (36) jeweils an der hinteren Kante (35b) eindüsen.
  3. Brenneranordnung gemäß Anspruch 2, wobei die Inline-Düsen (36) dazu konfiguriert sind, entlang einer Tangente zu einer Wölbungslinie (C) des jeweiligen Inline-Injektors (35) an der hinteren Kante (35b) einzudüsen.
  4. Brenneranordnung gemäß Anspruch 2 oder 3, wobei seitliche Oberflächen der Inline-Injektoren (35) mindestens an der hinteren Kante (35b) Lappen (35d) ausbilden und/oder mit Wirbel-Generatoren (35e) ausgestattet sind, die jeweils stromaufwärts von der hinteren Kante (35b) angeordnet und dazu konfiguriert sind, die Strömung zu verwirbeln.
  5. Brenneranordnung gemäß einem der vorhergehenden Ansprüche, umfassend ein erstes Plenum (40), das in den inneren Körper integriert ist und mit den Inline-Düsen (36) der Inline-Injektoren (35) fluidisch gekoppelt ist.
  6. Brenneranordnung gemäß Anspruch 5, wobei die Schaufeln (35) jeweils mit Querströmungsdüsen (27) ausgestattet sind, die dazu konfiguriert sind, in die Mischkanäle (25) der jeweiligen Schaufeln (24) in einer ersten Querströmungsrichtung (CF1), die quer zur Strömungsrichtung (F) verläuft, durch seitliche Oberflächen der jeweiligen Schaufeln (24) einzudüsen.
  7. Brenneranordnung gemäß Anspruch 6, umfassend ein zweites Plenum (28), das mit den ersten Querströmungsdüsen (27) fluidisch gekoppelt ist und von den Inline-Düsen (36) fluidisch entkoppelt ist, wobei das erste Plenum (40) von den ersten Querströmungsdüsen (27) fluidisch entkoppelt ist, wobei das zweite Plenum (28) vorzugsweise in den inneren Körper (21) integriert ist.
  8. Brenneranordnung gemäß Anspruch 6 oder 7, umfassend zweite Querströmungsdüsen (30) in der kegelstumpfförmigen Außenoberfläche (21a) des inneren Körpers (21), die dazu konfiguriert sind, in einer zweiten Querströmungsrichtung (CF2) einzudüsen, die quer zur Strömungsrichtung (F) verläuft und sich vorzugsweise von der ersten Querströmungsrichtung (CF1) unterscheidet.
  9. Brenneranordnung gemäß Anspruch 8, abhängig von Anspruch 8, umfassend ein drittes Plenum (32), das mit den zweiten Querströmungsdüsen (30) fluidisch gekoppelt ist und von den Inline-Düsen (36) fluidisch entkoppelt ist, wobei das erste Plenum (40) von den zweiten Querströmungsdüsen (30) fluidisch entkoppelt ist, wobei das dritte Plenum (32) vorzugsweise in den inneren Körper (21) integriert ist.
  10. Brenneranordnung gemäß einem der vorhergehenden Ansprüche, wobei sich die Inline-Injektoren (35) von dem inneren Körper (21) vorzugsweise jeweils in einer Mittelebene des jeweiligen Mischkanals (25) in den ringförmigen Raum (23) hinein erstrecken.
  11. Brenneranordnung gemäß einem der vorhergehenden Ansprüche, wobei die Inline-Injektoren (35) so angeordnet sind, dass sie stromaufwärts von den ersten Querströmungsdüsen (27) der Schaufeln (24) eindüsen, die die jeweiligen Mischkanäle (25) definieren.
  12. Brenneranordnung gemäß einem der vorhergehenden Ansprüche, umfassend einen Vorbrenner (21), der in dem Hauptbrenner (15) koaxial untergebracht ist, und einen Lanzeninjektor (22), der sich entlang der Brennerachse (B) durch den Vorbrenner (21) erstreckt.
  13. Gasturbine, umfassend eine Brennkammereinrichtung, die mit einer Mehrzahl von Brenneranordnungen (10) gemäß einem der vorhergehenden Ansprüche ausgestattet ist, und eine Wasserstoff-Zufuhrleitung (6c), die mit den Inline-Injektoren (35) fluidisch gekoppelt ist.
  14. Gasturbine gemäß Anspruch 13, abhängig von Anspruch 12, umfassend eine Brennöl-Zuleitung (6a) und eine Brenngas-Zuleitung (6b), die mit mindestens einem aus dem Vorbrenner (21) und dem Lanzeninjektor (17) fluidisch gekoppelt sind.
EP21218284.4A 2021-12-30 2021-12-30 Brenneranordnung mit inline-injektoren Active EP4206535B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP21218284.4A EP4206535B1 (de) 2021-12-30 2021-12-30 Brenneranordnung mit inline-injektoren
CN202211725530.3A CN116379472A (zh) 2021-12-30 2022-12-30 带有直列式喷射器的喷燃器组件

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EP4206535B1 true EP4206535B1 (de) 2025-02-19

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992007221A1 (en) * 1990-10-23 1992-04-30 Rolls-Royce Plc Gasturbine combustion chamber and method of operation thereof
US20080078182A1 (en) * 2006-09-29 2008-04-03 Andrei Tristan Evulet Premixing device, gas turbines comprising the premixing device, and methods of use
US20200318550A1 (en) * 2019-04-08 2020-10-08 Doosan Heavy Industries & Construction Co., Ltd. Combustor and gas turbine having the same

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6786047B2 (en) * 2002-09-17 2004-09-07 Siemens Westinghouse Power Corporation Flashback resistant pre-mix burner for a gas turbine combustor
EP1645805A1 (de) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brenner für fluidische Brennstoffe und Verfahren zum Betreiben eines derartigen Brenners
US9395084B2 (en) * 2012-06-06 2016-07-19 General Electric Company Fuel pre-mixer with planar and swirler vanes
WO2014114533A1 (en) * 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Burner system having turbulence elements
EP3236157A1 (de) * 2016-04-22 2017-10-25 Siemens Aktiengesellschaft Wirbler zum mischen von kraftstoff mit luft in einem verbrennungsmotor
RU2747655C2 (ru) * 2017-11-17 2021-05-11 Ансальдо Энергия Свитзерленд Аг Горелка промежуточного подогрева для газовой турбины и газовая турбина, содержащая такую горелку промежуточного подогрева

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992007221A1 (en) * 1990-10-23 1992-04-30 Rolls-Royce Plc Gasturbine combustion chamber and method of operation thereof
US20080078182A1 (en) * 2006-09-29 2008-04-03 Andrei Tristan Evulet Premixing device, gas turbines comprising the premixing device, and methods of use
US20200318550A1 (en) * 2019-04-08 2020-10-08 Doosan Heavy Industries & Construction Co., Ltd. Combustor and gas turbine having the same

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CN116379472A (zh) 2023-07-04
EP4206535A1 (de) 2023-07-05

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