US20160252254A1 - Gas turbine burner hub with pilot burner - Google Patents

Gas turbine burner hub with pilot burner Download PDF

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Publication number
US20160252254A1
US20160252254A1 US15/030,916 US201415030916A US2016252254A1 US 20160252254 A1 US20160252254 A1 US 20160252254A1 US 201415030916 A US201415030916 A US 201415030916A US 2016252254 A1 US2016252254 A1 US 2016252254A1
Authority
US
United States
Prior art keywords
burner
fuel
pilot
arrangement
air duct
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.)
Abandoned
Application number
US15/030,916
Other languages
English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Patrick Lapp
Andreas Mann
Stefan Reich
Kai-Uwe Schildmacher
Sascha Staring
Daniel Vogtmann
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LAPP, PATRICK, MANN, ANDREAS, KRIEGER, TOBIAS, Böttcher, Andreas , REICH, STEFAN, SCHILDMACHER, KAI-UWE, Staring, Sascha, VOGTMANN, DANIEL
Publication of US20160252254A1 publication Critical patent/US20160252254A1/en
Abandoned legal-status Critical Current

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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
    • F23R3/34—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
    • 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
    • F23R3/36—Supply of different fuels
    • 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

Definitions

  • the invention relates to a burner arrangement, in particular a burner arrangement with a main burner and a pilot burner, and to the mixing of fuel with air.
  • Pollutants such as nitrogen oxides (NO x ) are mainly influenced by the mixing ratio of fuel to air and the efficiency of combustion. Complete combustion of the fuel is desirable if pollutants are to be reduced.
  • NO x nitrogen oxides
  • Possible fuels are gaseous fuels, such as natural gas or synthesis gas, and also liquid fuels. It is precisely in the case of the liquid fuel oil that nozzle geometry in combination with vane swirl has hitherto primarily influenced mixing of said fuel with air. No further active influencing of for example the depth of penetration of the fuel into the air stream or the swirling of the fuel and thus optimized mixing does not conventionally take place.
  • the gas is injected for example via bores in a swirl vane and premixed and swirled with the compressed air.
  • a pilot burner is typically used to stabilize the premixing flame.
  • this is an oil diffusion burner, while in the case of gas it is a pilot gas burner.
  • An object of the invention is to further develop the above-stated device such that, when the device is in operation, maximally complete combustion is achieved.
  • a burner arrangement for a combustion chamber in particular a gas turbine combustion chamber, for burning fluid fuels, with a main burner and a pilot burner arranged centrally therein, which pilot burner serves to ignite and/or to stabilize main burner combustion
  • the main burner comprising a central fuel feed arrangement arranged around the pilot burner, an annular air duct surrounding the central fuel feed arrangement for supplying combustion air, first fuel nozzles for injecting a substantially gaseous fuel into the annular air duct, wherein the first fuel nozzles are supplied by a first fuel manifold in the central fuel feed arrangement, and second fuel nozzles for injecting a substantially liquid fuel into the annular air duct, wherein the second fuel nozzles are supplied by a second fuel manifold in the central fuel feed arrangement
  • ducts are provided which branch off from at least one of the fuel manifolds and lead into the pilot burner and the pilot burner has
  • the pilot burner comprises a pilot annular air duct for supplying combustion air and the ducts lead into this pilot annular air duct.
  • the ducts leading into the pilot annular air duct are uniformly distributed around the circumference thereof.
  • the ducts branch off from the second fuel manifold and comprise nozzles at their ends leading into the pilot burner.
  • the second fuel manifold for injecting a substantially liquid fuel, i.e. oil is mechanically particularly stressed, such that it is particularly advantageous here for the nozzles to be cavitation-free and screw-fastenable should replacement be required.
  • the annular air duct comprises swirl vanes and for the first fuel nozzles to be arranged in these swirl vanes.
  • the admixture of fuel from the central fuel feed arrangement does not however replace the independent supply of gas or oil in the pilot burner, but rather in combination therewith ensures additional fuel enrichment, for which reason in advantageous embodiments the pilot burner also comprises an oil feed duct independent of the ducts, in addition to a gas feed duct independent of the ducts.
  • the additional mass flows according to the invention from the gas or oil manifolds are mixed with the compressed air in the pilot gas line and then combined with the fuel in the pilot burner. This makes possible additional fuel enrichment and mixing, which may lead to an improvement in the fuel/air mixture and thus to a reduction in pollutants.
  • the invention may also be implemented in an existing design by the simple introduction of bores and/or nozzles.
  • FIGURE shows schematically, and not to scale, a burner arrangement according to the invention.
  • the invention is described in greater detail below with reference to a drawing.
  • the FIGURE shows schematically, and not to scale, a burner arrangement 1 according to the invention, which may optionally be used in conjunction with a plurality of similar burner arrangements for example in the combustion chamber of a gas turbine plant.
  • the burner arrangement 1 has a main axis 19 and comprises a pilot burner 3 and a main burner 2 concentrically surrounding the pilot burner 3 .
  • Both pilot burner 3 and main burner 2 may optionally be operated with gaseous and/or liquid fuels, such as for example natural gas or heating oil.
  • the pilot burner 3 then comprises as fuel ducts an inner oil feed duct 18 and an inner, annular gas feed duct 17 concentrically surrounding said duct 18 . This is in turn surrounded concentrically by a pilot annular air duct 13 for supplying combustion air 14 .
  • this pilot annular air duct 13 it is additionally possible to arrange a suitable ignition system (not shown in the FIGURE).
  • swirl vanes 20 which comprise fuel nozzles 21 for supplying a fuel to a stream 14 of oxygen-containing gas, typically air.
  • the main burner 2 surrounding the pilot burner 3 comprises, relative to the main axis 19 , a radially outer annular air duct 5 for the combustion air 6 , through which extend a plurality of swirl vanes 16 of a swirl vane assembly.
  • These swirl vanes 16 have as inlet for fuel first fuel nozzles 7 , through which fuel gas may be injected into the air 6 flowing in through the annular air duct 5 .
  • the first fuel nozzles 7 are supplied via a first fuel manifold 8 in a central fuel feed arrangement 4 .
  • a second fuel manifold 10 in the central fuel feed arrangement 4 supplies second fuel nozzles 9 typically with oil.
  • the task of the pilot burner 3 is to maintain stable combustion operation in the burner arrangement 1 , since this is mostly operated with a lean mixture with a tendency towards instability.
  • the invention provides not only ducts 11 which branch off from the first fuel manifold 8 for the gas supply and lead into the pilot burner 3 but also ducts 12 which branch off from a second fuel manifold 10 for oil.
  • the ducts 12 have nozzles 15 at their ends leading into the pilot burner 3 .
  • the ducts 11 , 12 are distributed uniformly over the circumference of the pilot annular air duct 13 and may take the form of simple bores.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US15/030,916 2013-10-31 2014-10-23 Gas turbine burner hub with pilot burner Abandoned US20160252254A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102013222152.5 2013-10-31
DE102013222152 2013-10-31
PCT/EP2014/072741 WO2015062962A1 (fr) 2013-10-31 2014-10-23 Moyeu de brûleurs de turbine à gaz pourvu d'un brûleur pilote

Publications (1)

Publication Number Publication Date
US20160252254A1 true US20160252254A1 (en) 2016-09-01

Family

ID=51866131

Family Applications (1)

Application Number Title Priority Date Filing Date
US15/030,916 Abandoned US20160252254A1 (en) 2013-10-31 2014-10-23 Gas turbine burner hub with pilot burner

Country Status (3)

Country Link
US (1) US20160252254A1 (fr)
EP (1) EP3008390A1 (fr)
WO (1) WO2015062962A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3361159A1 (fr) * 2017-02-13 2018-08-15 Ansaldo Energia Switzerland AG Procédé de fabrication d'un ensemble brûleur pour une chambre de combustion de turbine à gaz et ensemble brûleur pour une chambre de combustion de turbine à gaz
US20190093895A1 (en) * 2017-09-28 2019-03-28 General Electric Company Premixed fuel nozzle
US10830445B2 (en) * 2015-12-30 2020-11-10 General Electric Company Liquid fuel nozzles for dual fuel combustors
US20220196242A1 (en) * 2020-12-22 2022-06-23 Doosan Heavy Industries & Construction Co., Ltd. Combustor nozzle, combustor, and gas turbine including the same

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015206227A1 (de) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft Brenneranordnung

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100316966A1 (en) * 2009-06-16 2010-12-16 Boettcher Andreas Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement
EP2354662A2 (fr) * 2009-12-29 2011-08-10 Ansaldo Energia S.p.A. Brûleur pour turbine à gaz et turbine à gaz avec un tel brûleur
US20120210717A1 (en) * 2011-02-21 2012-08-23 General Electric Company Apparatus for injecting fluid into a combustion chamber of a combustor
US8418469B2 (en) * 2010-09-27 2013-04-16 General Electric Company Fuel nozzle assembly for gas turbine system
US20130327045A1 (en) * 2010-10-05 2013-12-12 Timothy A. Fox Gas turbine combustion chamber with fuel nozzle, burner with such a fuel nozzle and fuel nozzle
US8905333B1 (en) * 2011-05-24 2014-12-09 Mainstream Engineering Corporation Diesel injector and method utilizing focused supercavitation to reduce spray penetration length
US20150089954A1 (en) * 2012-08-17 2015-04-02 Dürr Systems GmbH Burners having fuel plenums
US9316154B2 (en) * 2013-03-07 2016-04-19 Solar Turbines Incorporated Gas turbine fuel injector with metering cavity

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3663189D1 (en) * 1985-03-04 1989-06-08 Siemens Ag Burner disposition for combustion installations, especially for combustion chambers of gas turbine installations, and method for its operation

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100316966A1 (en) * 2009-06-16 2010-12-16 Boettcher Andreas Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement
EP2354662A2 (fr) * 2009-12-29 2011-08-10 Ansaldo Energia S.p.A. Brûleur pour turbine à gaz et turbine à gaz avec un tel brûleur
US8418469B2 (en) * 2010-09-27 2013-04-16 General Electric Company Fuel nozzle assembly for gas turbine system
US20130327045A1 (en) * 2010-10-05 2013-12-12 Timothy A. Fox Gas turbine combustion chamber with fuel nozzle, burner with such a fuel nozzle and fuel nozzle
US20120210717A1 (en) * 2011-02-21 2012-08-23 General Electric Company Apparatus for injecting fluid into a combustion chamber of a combustor
US8905333B1 (en) * 2011-05-24 2014-12-09 Mainstream Engineering Corporation Diesel injector and method utilizing focused supercavitation to reduce spray penetration length
US20150089954A1 (en) * 2012-08-17 2015-04-02 Dürr Systems GmbH Burners having fuel plenums
US9316154B2 (en) * 2013-03-07 2016-04-19 Solar Turbines Incorporated Gas turbine fuel injector with metering cavity

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10830445B2 (en) * 2015-12-30 2020-11-10 General Electric Company Liquid fuel nozzles for dual fuel combustors
EP3361159A1 (fr) * 2017-02-13 2018-08-15 Ansaldo Energia Switzerland AG Procédé de fabrication d'un ensemble brûleur pour une chambre de combustion de turbine à gaz et ensemble brûleur pour une chambre de combustion de turbine à gaz
US11199328B2 (en) 2017-02-13 2021-12-14 Ansaldo Energia Switzerland AG Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor
US20190093895A1 (en) * 2017-09-28 2019-03-28 General Electric Company Premixed fuel nozzle
US10816210B2 (en) * 2017-09-28 2020-10-27 General Electric Company Premixed fuel nozzle
US20220196242A1 (en) * 2020-12-22 2022-06-23 Doosan Heavy Industries & Construction Co., Ltd. Combustor nozzle, combustor, and gas turbine including the same
CN114659138A (zh) * 2020-12-22 2022-06-24 斗山重工业建设有限公司 燃烧室用喷嘴、燃烧室及燃气轮机
US11761633B2 (en) * 2020-12-22 2023-09-19 Doosan Enerbility Co., Ltd. Combustor nozzle, combustor, and gas turbine including the same

Also Published As

Publication number Publication date
EP3008390A1 (fr) 2016-04-20
WO2015062962A1 (fr) 2015-05-07

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AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOETTCHER, ANDREAS;KRIEGER, TOBIAS;LAPP, PATRICK;AND OTHERS;SIGNING DATES FROM 20160120 TO 20160122;REEL/FRAME:038339/0975

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION