EP3361161B1 - Brenneranordnung für eine brennkammer eines gasturbinenkraftwerks und brennkammer mit der besagten brenneranordnung - Google Patents

Brenneranordnung für eine brennkammer eines gasturbinenkraftwerks und brennkammer mit der besagten brenneranordnung Download PDF

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Publication number
EP3361161B1
EP3361161B1 EP17155917.2A EP17155917A EP3361161B1 EP 3361161 B1 EP3361161 B1 EP 3361161B1 EP 17155917 A EP17155917 A EP 17155917A EP 3361161 B1 EP3361161 B1 EP 3361161B1
Authority
EP
European Patent Office
Prior art keywords
burner
conduit
premix
pilot
pilot burner
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.)
Active
Application number
EP17155917.2A
Other languages
English (en)
French (fr)
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EP3361161A1 (de
Inventor
Christoph Gaupp
Urs Benz
Michael Maurer
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 EP17155917.2A priority Critical patent/EP3361161B1/de
Priority to KR1020180016828A priority patent/KR20180093816A/ko
Priority to US15/894,407 priority patent/US20180231255A1/en
Priority to CN201810148905.1A priority patent/CN108426269A/zh
Publication of EP3361161A1 publication Critical patent/EP3361161A1/de
Application granted granted Critical
Publication of EP3361161B1 publication Critical patent/EP3361161B1/de
Active legal-status Critical Current
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
    • F23R3/28—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
    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • 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
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the present invention relates to a burner assembly for a combustor of a gas turbine power plant.
  • the present application refers to a combustor comprising said burner assembly.
  • a gas turbine power plant (in the following only gas turbine plant) comprises a rotor provided with an air compressor, with at least one combustor, which is arranged downstream of the compressor and fed with the air coming from the compressor, and with at least one gas turbine, which is arranged downstream of the combustor and fed with the gas coming from the combustor that has undergone combustion.
  • the compressor comprises an inlet supplied with air and a plurality of blades and vanes configured for compressing the air entering the compressor.
  • the compressed air leaving the compressor flows into a plenum and from there into at least one burner assembly of the combustor. Inside the burner assembly, the compressed air is mixed with at least one fuel. The mixture of such fuel and the compressed air is then combusted. The resulting hot gas leaves the combustor chamber and expands in the turbine performing work on the rotor.
  • the burner assembly used in gas turbine plants of the last generation are preferably of the premix type, as they are characterized by low emissions.
  • This kind of burner assembly is known, for example from document US2007/0231762 or US2002/124549 , the latter covering the features specified in the preamble of claim 1.
  • Said burner assembly comprises a premix burner and a pilot burner.
  • the premix burner is configured so as to swirl incoming combustion air and mix it with the fuel into a premix region.
  • the pilot burner comprises a pilot lance centrally arranged in the burner assembly.
  • the pilot lance is configured to inject fuel into the combustion air axially in order to create fuel-rich zones ensuring that flame being not extinguished.
  • the injection of fuel via the pilot lance is lowered in order to reduce pollutants, and the injection of fuel via the premix burner is increased.
  • the burner assemblies of this known type have a structure made of a plurality of component parts that need to be assembled together. Therefore the assembling of each burner assembly require several steps and is, consequently, highly burdensome.
  • An object of the present invention is therefore to provide a burner assembly for a combustor that enables avoiding, or at least mitigating, the described drawbacks.
  • the structure of the burner assembly is noticeably simplified.
  • the number of the component parts of the burner assembly is in fact reduced and the pilot burner has a reduced axial length with respect to the prior art solutions as the burner assembly can be fixed only to the combustor wall and the pilot burner and the premix burner do not need any more to be coupled to other fixed structures of the combustor (i.e. pressure vessel) or of the gas turbine plant as normally made in prior art solution.
  • the reduced axial length of the pilot burner the thermal expansion displacement of the pilot burner are advantageously reduced.
  • the fact that the burner assembly can be fixed only to the combustor wall greatly simplifies the assembly operation with evident advantages in terms of saving costs and time.
  • the premix burner and the pilot burner are a monolithic body.
  • the premix burner and the pilot burner are two separated pieces fixed together.
  • the pilot burner is fixed to an inner surface of the premix burner.
  • the pilot burner is fixed to the inlet portion of the premix burner along at least two contact zones axially displaced. In this way the fixing between the pilot burner and the premix burner is furthermore stable and reliable.
  • the pilot burner comprises at least two concentric conduits; at least one of the conduits being provided with an extendible portion.In this way relative axial displacements in the pilot burner due to thermal expansions are compensated.
  • the premix burner comprises at least one fuel supply conduit provided with a further extendible portion. In this way relative axial displacements in the premix burner due to thermal expansions are compensated.
  • a further object of the present invention is to provide a combustor for a gas turbine power plant having a simplified structure.
  • Reference number 1 in figure 1 indicate a burner assembly for a combustor 9 of a gas turbine power plant (here only partially illustrated).
  • Burner assembly 1 comprises a pilot burner 2 extending along a longitudinal axis A and a premix burner 3 extending about the pilot burner 2.
  • Pilot burner 2 and premix burner 3 are coupled to a fuel supply assembly 4 (schematically represented in the attached figures) which is connected to a respective fuel supply circuit (not illustrated).
  • the fuel supply assembly 4 is arranged along the longitudinal axis A.
  • variants of the fuel supply assembly 4 can be provided in order to supply the fuel from other sides of the burner assembly 1.
  • fuel supply assembly 4 can comprise metal rigid hoses or/and flexible hoses connected to the pilot burner 2 and to the premix burner 3.
  • the pilot burner 2 comprises a lance 5 which is provided with a first conduit 6 supplied, in use, with a first fuel, with a second conduit 7 supplied, in use, with air and with a third conduit 8 supplied, in use, with a second fuel.
  • the first fuel is gas and the second fuel is fuel oil.
  • first conduit 6, the second conduit 7 and the third conduit 8 are concentric and extend about the longitudinal axis A.
  • the third conduit 8 extends along the longitudinal axis A
  • the first conduit 6 extends about the third conduit 8
  • the second conduit 7 extends about the first conduit 6.
  • the first conduit 6 and the third conduit 8 are supplied with the respective first fuel and second fuel by the fuel supply assembly 4.
  • the fuel is supplied along a flow direction D (indicated by an arrow in figures 1 and 2 ) towards the inside of the combustor 9.
  • the second conduit 7 has an axial length lower than the axial length of the first conduit 6 and the third conduit 8.
  • the lance 5 has an end tip 10 which faces inside the combustor 9.
  • the lance 5 is schematically represented in the attached drawings.
  • the lance 5 is provided with a plurality of first nozzles (not illustrated) connected to the first conduit 6, with a plurality of second nozzles (not illustrated) connected to the second conduit 7 and with a plurality of third nozzles (not illustrated) connected to the third conduit 8.
  • the lance end tip 10 has preferably a circular section and is provided with a circular edge 15.
  • the end tip 10 comprises an end surface 16 which is defined by a respective end wall 17 and is preferably planar.
  • the premix burner 3 extends about the pilot burner 2 and substantially comprises an inlet portion 20 coupled to the supply assembly 4, an injection portion 21 coupled to the inlet portion 20 and an outlet portion 22 coupled to the injection portion 21 and to the combustor 9.
  • the inlet portion 20 comprises a fuel supply conduit 23 which is preferably annular and extends about a respective inlet portion of the pilot burner 2.
  • the dimensions of the fuel supply conduit 23 are designed so as to allow an easy insertion of the pilot burner 2 into the substantially cylindrical seat defined by the fuel supply conduit 23.
  • the fuel supply conduit 23 is supplied with fuel by the fuel supply assembly 4 along a flow direction D (indicated by an arrow in figures 1 and 2 ) towards the inside of the combustor 9.
  • the fuel supplied to the fuel supply conduit 23 is gas.
  • a plurality of air inlet channels 24 (represented in dotted lines) which are configured to supply air to the second conduit 7 of the pilot burner 2.
  • the air supplied through the air inlet channels 24 is air collected in a plenum 25 (only partially visible in the drawings) in communication with the outlet of the compressor of the plant.
  • the injection portion 21 is preferably defined by a truncated-cone shaped swirler 26 provided with air slots 27 (the air slots are not well visible in the attached drawings - dotted arrows indicate the air flowing through said air slots) and fuel nozzles 28.
  • the air slots 27 are supplied with the air collected in the plenum 25 in communication with the outlet of the compressor of the plant.
  • Fuel nozzles 28 are supplied with fuel by the fuel supply conduit 23.
  • the injection portion 21 is provided with a first end 29a and a second end 29b; the second end 29b having a section diameter lower than the section diameter of the first end 29a.
  • the inlet portion 20 is coupled to the second end 29b, while the outlet portion 22 is coupled to the first end 29a.
  • the injection portion 21 is made by two shells assembled together.
  • the outlet portion 22 has preferably a cylindrical shape and is generally defined as CBO (cylindrical burner outlet) .
  • the outlet portion 22 is coupled to a wall 31 of the combustor 9.
  • the pilot burner 2 and the premix burner 3 are integral.
  • pilot burner 2 and the premix burner 3 are rigidly fixed together.
  • the pilot burner 2 is fixed to at least a portion of an inner surface of the premix burner 3.
  • the inner surface of the premix burner 3 is the surface of the premix burner 3 facing, in use, the pilot burner 2.
  • the premix burner 3 and the pilot burner 2 are two separated pieces fixed together.
  • the premix burner 3 and the pilot burner 2 are directly fixed together.
  • the premix burner 3 and the pilot burner 2 can be made as a monolithic body.
  • the monolithic body can be obtained by additive manufacturing or by casting processes.
  • the pilot burner 2 is fixed to the inlet portion 20 of the premix burner 3.
  • the outer surface of the pilot burner 2 is fixed to the inner surface of the inlet portion 20 of the premix burner 3.
  • the outer surface of the second conduit 7 is fixed to the inner surface of the inlet portion 20.
  • the outer surface of the second conduit 7 is fixed to the inner surface of the inlet portion 20 at the boundary with the injection portion 21.
  • the fixing of the pilot burner 2 is made along at least one contact zone 30 (schematically represented in the attached figure by a black dot) of the inner surface of the inlet portion 20.
  • the fixing of the pilot burner 2 to the inner surface of the inlet portion 20 can be made, for example, by welding, by bolts or by clamping means, by casting of by additive manufacturing.
  • the pilot burner 2 and the premix burner 3 are fixed together so as to define a sliding interface 35 between the pilot burner 2 and the inlet portion 20 of the premix burner 3.
  • Said sliding interface 35 allows relative axial movements between the pilot burner 2 and the premix burner 3 due to thermal expansions.
  • the sliding interface 35 is defined by an air gap 36 between the pilot burner 2 and the inlet portion 20 of the premix burner 3.
  • the sliding interface 35 is defined by an air gap 36 between the outer surface of the second conduit 7 and the inner surface of the inlet portion 20 of the premix burner 3.
  • the air gap 36 is preferably arranged along the inlet portion 20 near the injection portion 21.
  • the outer surface of the pilot burner 2 is fixed to the inner surface of the inlet portion 20 of the premix burner 3.
  • the outer surface of the first conduit 6 is fixed to the inner surface of the inlet portion 20.
  • the inner surface of the inlet portion 20 is fixed to the outer surface of the first conduit 6 near the beginning of the second conduit 7.
  • the fixing of the pilot burner 2 is made along at least one contact zone 30 (schematically represented in the attached figure by a black dot) of the inner surface of the inlet portion 20.
  • the fixing of the pilot burner 2 to the inner surface of the inlet portion 20 can be made, for example, by welding, by bolts or by clamping means, by casting of by additive manufacturing.
  • the fixing of the pilot burner 2 to the premix burner 3 can be made along at least two contact zones axially displaced in order to ensure a more stable coupling.
  • the pilot burner 2 and the premix burner 3 can be coupled according to a combination of the coupling illustrated in figure 1 and figure 2 .
  • the first conduit 6, the second conduit 7 and the third conduit 8 of the pilot burner 2 and the fuel supply conduit 23 of the premix burner 3 are provided with at least one extendible portion 37.
  • extendible portions 37 can be provided in order to compensate the axial displacement due to thermal expansions of the first conduit 6, the second conduit 7 and the third conduit 8 of the pilot burner 2 and of the fuel supply conduit 23 of the premix burner 3.
  • the second conduit 7 does not require the extendible portion as the thermal expansions are compensated by the sliding between the pilot burner 2 and the inlet portion 20 of the premix burner 3.
  • the extendible portions 37 are defined by a corrugated portions of the conduit.
  • the extendible portions can be defined by a helical wrapped portion of the conduit.

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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 (8)

  1. Brenneranordnung für eine Brennkammer (9), umfassend:
    • einen Pilotbrenner (2), der sich entlang einer Längsachse (A) erstreckt, wobei der Pilotbrenner (2) eine Lanze (5) umfasst, die mit einer ersten Leitung (6), der im Betrieb ein erster Brennstoff zugeführt wird, mit einer zweiten Leitung (7), der im Betrieb Luft zugeführt wird, und einer dritten Leitung (8) versehen ist, der im Betrieb ein zweiter Brennstoff zugeführt wird;
    • einen Vormischbrenner (3), der den Pilotbrenner (2) umgibt und einen Einlassteil (20) umfasst, der mit einer Brennstoffzufuhranordnung (4) gekoppelt ist, und einen Einspritzteil (21), der sich im Betrieb um die Längsachse (A) erstreckt und mit dem Einlassteil (20) gekoppelt ist, wobei der Einspritzteil (21) durch einen kegelstumpfförmigen Verwirbler (26) gebildet ist, der mit Luftschlitzen (27) und Brennstoffdüsen (28) versehen ist;
    wobei die Brenneranordnung dadurch gekennzeichnet ist, dass der Pilotbrenner (2) mit dem Vormischbrenner (3) einstückig ist und an einer inneren Oberfläche des Einlassteils (20) des Vormischbrenners (3) befestigt ist, so dass eine Gleitfläche (35) zwischen dem Pilotbrenner (2) und dem Vormischbrenner (3) gebildet ist, wobei die Gleitfläche (35) durch einen Luftspalt (36) zwischen dem Pilotbrenner (2) und dem Einlassteil (20) des Vormischbrenners (3) gebildet ist, um relative axiale Verschiebungen aufgrund der Wärmeausdehnung zwischen dem Pilotbrenner (2) und dem Vormischbrenner (3) zu erlauben.
  2. Brenneranordnung nach Anspruch 1, wobei die erste Leitung (6), die zweite Leitung (7) und die dritte Leitung (8) konzentrisch sind, wobei die zweite Leitung (7) eine axiale Länge hat, die geringer ist als die axiale Länge der ersten Leitung (6) und der dritten Leitung (8), wobei der Vormischbrenner (3) und der Pilotbrenner (2) ein monolithischer Körper sind und die Gleitfläche (35) durch den Luftspalt (36) zwischen der äußeren Oberfläche der zweiten Leitung (7) und der inneren Oberfläche des Einlassteils (20) des Vormischbrenners (3) gebildet ist.
  3. Brenneranordnung nach Anspruch 1, wobei der Vormischbrenner (3) und der Pilotbrenner (2) zwei getrennte, aneinander befestigte Teile sind.
  4. Brenneranordnung nach einem der vorhergehenden Ansprüche, wobei der Einspritzteil (21) mit einem ersten Ende (29a) und einem zweiten Ende (29b) versehen ist, wobei das zweite Ende (29b) einen zweiten Querschnittsdurchmesser hat, der geringer ist als der erste Querschnittsdurchmesser des ersten Endes (29a), wobei der Einlassteil (20) mit dem zweiten Ende (29b) gekoppelt ist.
  5. Brenneranordnung nach Anspruch 4, wobei der Pilotbrenner (2) an dem Einlassteil (20) des Vormischbrenners (3) entlang mindestens zwei axial versetzten Kontaktzonen befestigt ist.
  6. Brenneranordnung nach einem der vorhergehenden Ansprüche, wobei der Pilotbrenner (2) mindestens zwei konzentrische Leitungen (7; 8; 9) umfasst, wobei mindestens eine der Leitungen 7; 8; 9) mit einem ausziehbaren Teil (37) versehen ist.
  7. Brenneranordnung nach einem der vorhergehenden Ansprüche, wobei der Vormischbrenner (3) mindestens eine Kraftstoffzufuhrleitung (23) umfasst, die mit einem weiteren ausziehbaren Teil (37) versehen ist.
  8. Brennkammer für ein Gasturbinenkraftwerk, umfassend die Brenneranordnung (1) nach einem der vorhergehenden Ansprüche.
EP17155917.2A 2017-02-13 2017-02-13 Brenneranordnung für eine brennkammer eines gasturbinenkraftwerks und brennkammer mit der besagten brenneranordnung Active EP3361161B1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP17155917.2A EP3361161B1 (de) 2017-02-13 2017-02-13 Brenneranordnung für eine brennkammer eines gasturbinenkraftwerks und brennkammer mit der besagten brenneranordnung
KR1020180016828A KR20180093816A (ko) 2017-02-13 2018-02-12 가스 터빈 발전소의 연소기를 위한 버너 조립체 및 상기 버너 조립체를 포함하는 연소기
US15/894,407 US20180231255A1 (en) 2017-02-13 2018-02-12 Burner assembly for a combustor of a gas turbine power plant and combustor comprising said burner assembly
CN201810148905.1A CN108426269A (zh) 2017-02-13 2018-02-13 燃烧器组件和包括所述燃烧器组件的燃烧室

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17155917.2A EP3361161B1 (de) 2017-02-13 2017-02-13 Brenneranordnung für eine brennkammer eines gasturbinenkraftwerks und brennkammer mit der besagten brenneranordnung

Publications (2)

Publication Number Publication Date
EP3361161A1 EP3361161A1 (de) 2018-08-15
EP3361161B1 true EP3361161B1 (de) 2023-06-07

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EP17155917.2A Active EP3361161B1 (de) 2017-02-13 2017-02-13 Brenneranordnung für eine brennkammer eines gasturbinenkraftwerks und brennkammer mit der besagten brenneranordnung

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US (1) US20180231255A1 (de)
EP (1) EP3361161B1 (de)
KR (1) KR20180093816A (de)
CN (1) CN108426269A (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures
US11692711B2 (en) 2021-08-13 2023-07-04 General Electric Company Pilot burner for combustor

Citations (1)

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Publication number Priority date Publication date Assignee Title
US20090255102A1 (en) * 2008-04-11 2009-10-15 Mcmasters Marie Ann Repair of fuel nozzle component

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Publication number Priority date Publication date Assignee Title
IT1263683B (it) * 1992-08-21 1996-08-27 Westinghouse Electric Corp Complesso di ugello per combustibile per una turbina a gas
AU2001272682A1 (en) * 2000-06-15 2001-12-24 Alstom Power N.V. Method for operating a burner and burner with stepped premix gas injection
DE10050248A1 (de) * 2000-10-11 2002-04-18 Alstom Switzerland Ltd Brenner
DE102004027702A1 (de) 2004-06-07 2006-01-05 Alstom Technology Ltd Injektor für Flüssigbrennstoff sowie gestufter Vormischbrenner mit diesem Injektor
WO2009126534A1 (en) * 2008-04-11 2009-10-15 General Electric Company Combustor component and method of manufacture
EP2873924A1 (de) * 2013-11-15 2015-05-20 Siemens Aktiengesellschaft Intelligentes Steuerungsverfahren mit prädiktiver Emissionsüberwachungsfähigkeit für eine Gasturbinenverbrennungskammer
BR112016012361B1 (pt) * 2013-12-23 2021-11-09 General Electric Company Aparelho de bocal de combustível para um motor de turbina a gás
EP3026347A1 (de) * 2014-11-25 2016-06-01 Alstom Technology Ltd Brennkammer mit ringförmigem Wirbelkörper
WO2016138271A1 (en) * 2015-02-25 2016-09-01 Parker-Hannifin Corporation Direct injection multipoint nozzle
EP3073198B1 (de) * 2015-03-27 2019-12-25 Ansaldo Energia Switzerland AG Integriertes zweikraftstofffördersystem

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090255102A1 (en) * 2008-04-11 2009-10-15 Mcmasters Marie Ann Repair of fuel nozzle component

Also Published As

Publication number Publication date
EP3361161A1 (de) 2018-08-15
US20180231255A1 (en) 2018-08-16
CN108426269A (zh) 2018-08-21
KR20180093816A (ko) 2018-08-22

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