EP2196734A1 - Lance de combustible pour un brûleur - Google Patents

Lance de combustible pour un brûleur Download PDF

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Publication number
EP2196734A1
EP2196734A1 EP08171548A EP08171548A EP2196734A1 EP 2196734 A1 EP2196734 A1 EP 2196734A1 EP 08171548 A EP08171548 A EP 08171548A EP 08171548 A EP08171548 A EP 08171548A EP 2196734 A1 EP2196734 A1 EP 2196734A1
Authority
EP
European Patent Office
Prior art keywords
fuel
lance
burner
fuel lance
tip
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.)
Withdrawn
Application number
EP08171548A
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Jürgen MEISL
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
Priority to EP08171548A priority Critical patent/EP2196734A1/fr
Priority to PCT/EP2009/064664 priority patent/WO2010066516A2/fr
Priority to RU2011128704/06A priority patent/RU2529970C2/ru
Priority to EP09752330A priority patent/EP2359065A2/fr
Priority to US13/133,741 priority patent/US8973367B2/en
Priority to JP2011539985A priority patent/JP5340410B2/ja
Priority to CN200980149749.XA priority patent/CN102265091B/zh
Publication of EP2196734A1 publication Critical patent/EP2196734A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling

Definitions

  • the present invention relates to a burner lance, for example for a gas turbine combustor, and more particularly to a fuel lance for liquid fuels.
  • Such fuel lances are used for example in burners, which can be operated both with liquid fuel, as well as with gaseous fuel.
  • the lance for operation with the liquid fuels such as oil
  • the oil then flows through the lance and exits at its tip through oil nozzles into a combustion chamber. After exiting the nozzle, the oil in the combustion chamber, in which compressor air is introduced, burned.
  • gaseous fuels are often injected into an air supply channel surrounding the nozzle lance and mixed there with compressor air before the mixture is introduced into the combustion chamber.
  • the lance tip When operated with gaseous fuels, the lance tip is usually exposed to high temperatures in the range of up to about 1000 ° C due to the near flame. These high temperatures can lead to coking of liquid fuel residues in the nozzle lance.
  • a flushing of the fuel passages in the fuel lance with a cooling water Before switching the burner to operate with a liquid fuel is therefore usually a flushing of the fuel passages in the fuel lance with a cooling water to flush away any deposits.
  • the temperature of the cooling water is only about 25 ° C, which can lead to a thermal shock in the hot fuel lance.
  • high temperature gradients develop in the region of the nozzles, so that considerable thermoelectric voltages can occur in the lance tip. The repeated occurrence of such thermal stresses can lead to cracks in the area of the nozzles, as a result of which the starting numbers and thus the service life of the fuel nozzle are reduced.
  • the object of the present invention is therefore to provide a fuel lance for use in a burner, in particular in a gas turbine burner, which helps to overcome the mentioned disadvantages.
  • a further object of the invention is to provide an advantageous firing, in particular a gas turbine burner.
  • the first object is achieved by a fuel lance for a burner, in particular for a gas turbine burner, according to claim 1, the second object by a burner, in particular a gas turbine burner according to claim 8.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner lance for a burner in particular for a gas turbine burner, comprises a tip which has a nozzle surface with at least two fuel nozzles.
  • the nozzle surface is slotted between the fuel nozzles. It may in particular be formed as an annular surface, such as a conical annular surface, wherein the slots extend perpendicular to the circumferential direction of the annular surface through this.
  • the slits in the nozzle surface allow the lance tip to dissipate thermal stresses through free deformation, thus reducing the thermal gradient of the fuel lance.
  • the slots have no significant aerodynamic influence on the air flowing along the fuel lance or on fuel injected through the fuel nozzles into the airflow.
  • the slots also mean only a minor modification of the fuel lance, which can also be made with very little effort. Therefore, existing fuel lances can be retrofitted with little effort, which increases the possible starting numbers and the life of this fuel lance.
  • the tip cooling air channels may be present, which extend between the fuel nozzles below the nozzle surface.
  • the tip of the fuel lance may be cooled during operation of the burner to minimize the temperature of the tip, thereby further reducing the incidence of thermal stress during purging of the fuel lance.
  • the slots then ideally extend from the nozzle surface to the respective cooling fluid channel. In other words, the slots form passage openings from the nozzle surface to the cooling fluid channel. This embodiment allows a particularly high flexibility of the corresponding material areas for the reduction of thermal voltages.
  • the tip of the fuel lance may be in the shape of a truncated cone.
  • the lateral surface of the truncated cone forms the nozzle surface
  • the cooling fluid channels have at least open outlet openings towards the top surface of the truncated cone.
  • passage openings may be present around the fuel nozzles which are in fluid communication with the air supply channels. Compressor air exiting through these openings can then be used to cool the tip of the lance, in particular in the region of the nozzles to be spooled. In the presence of such passage openings, in particular a respective slot can be arranged in each case between the passage openings of adjacent fuel nozzles.
  • a burner according to the invention which may in particular be a gas turbine burner, is equipped with a fuel lance according to the invention.
  • the fuel lance can be used here for supplying a liquid fuel, wherein in addition to the fuel lance fuel nozzles for gaseous fuels can be present.
  • Fig. 1 shows a section of a burner according to the invention in a sectional view.
  • Fig. 2 shows the tip of the nozzle lance of the burner according to the invention in Fig. 1 in a perspective view.
  • Fig. 3 shows the tip Fig. 2 in a view on her front.
  • a gas turbine burner shown in Fig. 1 .
  • This has one of a substantially cylindrical wall 1 bounded air supply channel 3, in the center of a fuel lance 5 extends.
  • fuel nozzles 7 At the tip of the fuel lance are fuel nozzles 7 for injecting a fuel into the air supplied through the air supply passage 3.
  • the fuel lance 5 is an oil lance for supplying a liquid fuel.
  • the fuel lance burner includes a second fuel supply system 9, which has an axial passage 11 through which the fuel lance 5 is passed, so that only the end portion 13 of the fuel lance 5 protrudes from the fuel supply system 9.
  • the fuel supply system 9 is connected to swirl vanes 15 located at the downstream end of the fuel supply system 9 and extending through the air supply passage 3. through Fuel supply channels 17, a fuel, in the present embodiment, a gaseous fuel, passed into the swirl vanes 15, from where it is injected through nozzle openings 19 in the air flowing through the air supply duct 3 air.
  • the burner shown is a so-called “dual fuel burner", so a burner that can be operated with both gaseous fuels, as well as with liquid fuels.
  • the invention can also be implemented in the context of burners in which both the fuel supply system, and by the fuel lance each a fuel in the same state of matter is supplied, so for example in the context of a burner in which both by the fuel supply system, and by the fuel lance in each case a gaseous fuel is supplied.
  • the fuel lance can be used as a pilot burner.
  • FIG. 2 A perspective view of the end portion 13 of the fuel lance 5 is shown in FIG Fig. 2 shown.
  • Fig. 3 also shows a frontal view of the end portion in the direction along the axial direction of the fuel lance 5.
  • the end portion 13 comprises a substantially cylindrical portion 20, followed by a substantially frusto-conical tip 21 connects.
  • a substantially cylindrical portion 20 In the lateral surface 23 of the frusto-conical tip 21, three fuel nozzles 7 are distributed uniformly in the circumferential direction, in particular Fig. 3 lets recognize. It should be noted at this point, however, that a tip with three fuel nozzles represents only one possible embodiment variant and that more or fewer fuel nozzles or a different distribution of the nozzles in the lateral surface are possible.
  • cooling air channels 25 which open into a central opening 27. This is located where the top surface of the truncated cone runs.
  • the cooling air channels 25 are fed through feed openings 29 in the cylindrical portion 20 of the end portion 13 of the nozzle lance 5.
  • This air has temperatures that are cooler
  • the tip 21 is heated in the gas operation of the illustrated burner by the prevailing flame in the flame chamber to temperatures of about 800 to 1,000 ° C.
  • the fuel passage 31 and the fuel nozzles 7 of the fuel lance 5 are purged to allow coking avoid.
  • This rinsing is typically carried out with water having a temperature of about 25 ° C. Due to the high temperature difference between the rinsing water on the one hand and the tip 21 on the other hand, it comes here in the peak to thermal stresses that are defined breakdown.
  • the nozzle surface forming lateral surface 23 of the tip 21 is provided with slots 33.
  • the slots 33 extend in the present embodiment through the lateral surface 23 through to the cooling air passages 25, so that during operation of the burner cooling air can escape through the slots 33 to lock them against the entry of hot combustion gases.
  • the slots 33 also extend to the feed openings 29. However, they can also be arranged only in the lateral surface 23 of the truncated cone, so that no slot section extends through the cylindrical portion 20.
  • the slots 33 are each arranged in the middle between two fuel nozzles 7 in the present embodiment. Depending on the fluidic conditions in the region of the tip (for example, taking into account the twist generated by the swirl generators 15), however, the slots 33 can also be offset in the clockwise or counterclockwise direction in comparison with the embodiment shown in the FIG. In addition, it is possible to provide a plurality of slots if they extend only through the lateral surface 23 of the truncated cone 21, but not through the cylindrical portion 20. The possible through the slots 33 deformation of the truncated cone surface 23 in the region of the cooling air channels 25 then allows the degradation of the thermal stresses occurring during the rinsing process.
  • optional through holes 30 are present, which extend to the cooling air passages 25 and allow the passage of cooling fluid. In this way, a particularly effective cooling of the material of the lance tip in the region of the nozzle openings to be reeled 7 can be achieved, whereby the thermal shock during flushing and thus the degraded thermoelectric voltages are reduced.
  • the provision of the slots 33 in the fuel lance of the burner according to the invention advantageously allows the removal of thermal stresses during flushing of the fuel lance with rinse water, without the slots adversely affect the aerodynamics in the tip of the fuel lance. Due to the improved reduction of the thermal voltages, the life of the fuel lance is extended. The introduction of the slots in existing fuel lances without slots is also feasible without much effort, so that existing fuel lances can be converted with little effort.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)
EP08171548A 2008-12-12 2008-12-12 Lance de combustible pour un brûleur Withdrawn EP2196734A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP08171548A EP2196734A1 (fr) 2008-12-12 2008-12-12 Lance de combustible pour un brûleur
PCT/EP2009/064664 WO2010066516A2 (fr) 2008-12-12 2009-11-05 Lance à combustible pour brûleur
RU2011128704/06A RU2529970C2 (ru) 2008-12-12 2009-11-05 Топливная трубка для горелки
EP09752330A EP2359065A2 (fr) 2008-12-12 2009-11-05 Lance à combustible pour brûleur
US13/133,741 US8973367B2 (en) 2008-12-12 2009-11-05 Fuel lance for A burner
JP2011539985A JP5340410B2 (ja) 2008-12-12 2009-11-05 バーナ用燃料ランス
CN200980149749.XA CN102265091B (zh) 2008-12-12 2009-11-05 用于燃烧器的燃料喷管

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08171548A EP2196734A1 (fr) 2008-12-12 2008-12-12 Lance de combustible pour un brûleur

Publications (1)

Publication Number Publication Date
EP2196734A1 true EP2196734A1 (fr) 2010-06-16

Family

ID=40627425

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08171548A Withdrawn EP2196734A1 (fr) 2008-12-12 2008-12-12 Lance de combustible pour un brûleur
EP09752330A Withdrawn EP2359065A2 (fr) 2008-12-12 2009-11-05 Lance à combustible pour brûleur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09752330A Withdrawn EP2359065A2 (fr) 2008-12-12 2009-11-05 Lance à combustible pour brûleur

Country Status (6)

Country Link
US (1) US8973367B2 (fr)
EP (2) EP2196734A1 (fr)
JP (1) JP5340410B2 (fr)
CN (1) CN102265091B (fr)
RU (1) RU2529970C2 (fr)
WO (1) WO2010066516A2 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013208069A1 (de) * 2013-05-02 2014-11-06 Siemens Aktiengesellschaft Brennerlanze für einen Brenner einer Gasturbine
DE102015222661A1 (de) * 2015-11-17 2017-05-18 Siemens Aktiengesellschaft Strömungshülse für Brennstoffeindüsung mit Zeitverzögerung
DE102019103640A1 (de) * 2019-02-13 2020-08-13 Mitsubishi Hitachi Power Systems Europe Gmbh Brennstoffdüse mit Dehnungsschlitzen für einen Kohlenstaubbrenner

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8663348B2 (en) * 2010-08-11 2014-03-04 General Electric Company Apparatus for removing heat from injection devices and method of assembling same
EP2938926A1 (fr) * 2013-02-05 2015-11-04 Siemens Aktiengesellschaft Lances à combustible présentant un revêtement pour isolation thermique
DE102013202940A1 (de) 2013-02-22 2014-09-11 Siemens Aktiengesellschaft Kühlung einer Brennstofflanze durch den Brennstoff
CN103175221A (zh) * 2013-03-19 2013-06-26 哈尔滨工程大学 一种用于化学回热循环的气体辅助双燃料喷嘴
US9366190B2 (en) * 2013-05-13 2016-06-14 Solar Turbines Incorporated Tapered gas turbine engine liquid gallery
JP6191918B2 (ja) 2014-03-20 2017-09-06 三菱日立パワーシステムズ株式会社 ノズル、バーナ、燃焼器、ガスタービン、ガスタービンシステム
US10125991B2 (en) * 2014-08-14 2018-11-13 Siemens Aktiengesellschaft Multi-functional fuel nozzle with a heat shield
US10196983B2 (en) 2015-11-04 2019-02-05 General Electric Company Fuel nozzle for gas turbine engine
US11022313B2 (en) 2016-06-22 2021-06-01 General Electric Company Combustor assembly for a turbine engine
US10197279B2 (en) 2016-06-22 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US10337738B2 (en) 2016-06-22 2019-07-02 General Electric Company Combustor assembly for a turbine engine
US11181269B2 (en) 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
CN109883713B (zh) * 2019-01-18 2020-11-20 北京动力机械研究所 一种能够减少轴向热应力的工艺喷管
JP7191723B2 (ja) * 2019-02-27 2022-12-19 三菱重工業株式会社 ガスタービン燃焼器及びガスタービン
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures
CN114151197B (zh) * 2021-10-20 2022-12-16 中国航发四川燃气涡轮研究院 一种薄壁高筋圆转方机匣的冷却引流结构

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EP0552477A1 (fr) * 1992-01-21 1993-07-28 Westinghouse Electric Corporation Buse pour deux combustibles pour turbine à gaz
US20010042798A1 (en) * 2000-02-03 2001-11-22 Gulati Suresh T. Refractory burner nozzle with stress relief slits
US20060027232A1 (en) * 2004-08-04 2006-02-09 Siemens Westinghouse Power Corporation Pilot nozzle heat shield having connected tangs
EP1760403A2 (fr) * 2005-09-01 2007-03-07 General Electric Company Injecteur de carburant pour turbines à gaz

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FR2817016B1 (fr) * 2000-11-21 2003-02-21 Snecma Moteurs Procede d'assemblage d'un injecteur de combustible pour chambre de combustion de turbomachine
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JP2003247425A (ja) 2002-02-25 2003-09-05 Mitsubishi Heavy Ind Ltd 燃料ノズル、燃焼器およびガスタービン
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0552477A1 (fr) * 1992-01-21 1993-07-28 Westinghouse Electric Corporation Buse pour deux combustibles pour turbine à gaz
US20010042798A1 (en) * 2000-02-03 2001-11-22 Gulati Suresh T. Refractory burner nozzle with stress relief slits
US20060027232A1 (en) * 2004-08-04 2006-02-09 Siemens Westinghouse Power Corporation Pilot nozzle heat shield having connected tangs
EP1760403A2 (fr) * 2005-09-01 2007-03-07 General Electric Company Injecteur de carburant pour turbines à gaz

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013208069A1 (de) * 2013-05-02 2014-11-06 Siemens Aktiengesellschaft Brennerlanze für einen Brenner einer Gasturbine
DE102015222661A1 (de) * 2015-11-17 2017-05-18 Siemens Aktiengesellschaft Strömungshülse für Brennstoffeindüsung mit Zeitverzögerung
DE102019103640A1 (de) * 2019-02-13 2020-08-13 Mitsubishi Hitachi Power Systems Europe Gmbh Brennstoffdüse mit Dehnungsschlitzen für einen Kohlenstaubbrenner

Also Published As

Publication number Publication date
US20110247338A1 (en) 2011-10-13
CN102265091B (zh) 2014-04-09
CN102265091A (zh) 2011-11-30
JP5340410B2 (ja) 2013-11-13
WO2010066516A2 (fr) 2010-06-17
EP2359065A2 (fr) 2011-08-24
RU2529970C2 (ru) 2014-10-10
US8973367B2 (en) 2015-03-10
WO2010066516A3 (fr) 2011-04-21
RU2011128704A (ru) 2013-01-20
JP2012511687A (ja) 2012-05-24

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