EP2359065A2 - Lance à combustible pour brûleur - Google Patents

Lance à combustible pour brûleur

Info

Publication number
EP2359065A2
EP2359065A2 EP09752330A EP09752330A EP2359065A2 EP 2359065 A2 EP2359065 A2 EP 2359065A2 EP 09752330 A EP09752330 A EP 09752330A EP 09752330 A EP09752330 A EP 09752330A EP 2359065 A2 EP2359065 A2 EP 2359065A2
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
lance
fuel lance
slots
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Withdrawn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
EP09752330A
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 EP09752330A priority Critical patent/EP2359065A2/fr
Publication of EP2359065A2 publication Critical patent/EP2359065A2/fr
Withdrawn legal-status Critical Current

Links

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.
  • a burner lance for example.
  • a gas turbine combustor and more particularly to an internal ⁇ material lance for LIQUID fuels.
  • Such fuel lances are used, for example, in burners which can be operated both with liquid fuel and 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 top by Oldusen in a combustion chamber. After exiting the nozzle, the oil in the combustion chamber, in which compressor air is introduced, burned.
  • gaseous fuels are often emegusted in an air supply duct 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 0 C because of the near flame. These high temperatures can lead to coking of residual liquid fuels in the Dusen lance.
  • the fuel passages in the fuel lance are prefilled with cooling water in order to wash 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.
  • Object of the present invention is, therefore, an internal ⁇ material lance for use in a burner, particularly in a gas turbine combustor, to provide for disposal, which helps to overcome the disadvantages mentioned.
  • Another object of the invention is to provide an advantageous burning, in particular a gas turbine burner, at your disposal.
  • 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 Dusenflache is provided between the Brennstoffdusen with slots. It may in particular be formed as a ring surface, such as a conical annular surface, wherein the slots senk ⁇ right torecis ⁇ chtung the annular surface through this dur ⁇ fen.
  • 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 effect on the air flowing along the fuel lance or on fuel emitted 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 service life of this fuel lance.
  • the interim rule ⁇ the Brennstoffdusen below the Dusenflache duri ⁇ fen.
  • 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 occurrence of thermal stresses during the fuel lance spooling .
  • the slots then ideally extend from the Dusenflache to the] ichigem Kuhlfluidkanal.
  • the slots form passage openings from the nozzle surface to the coolant 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 cone ⁇ stump forms the Dusenflache, and the Kuhlfluidkanale have at least to the top surface of the truncated cone to open Austritto réelleen.
  • 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 reeled. In the presence of such can be gangso réelleen By ⁇ particular in each case arranged between the through openings of adjacent Brennstoffdusen a slot reasonable.
  • 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 in this case be used to supply a liquid fuel, wherein in addition to the fuel lance Brennstoffdusen for gaseous fuels can be present.
  • the use of the inventive fuel lance in the novel Brenner leads due to increased life ⁇ life of the fuel lance means that maintenance intervals can be extended for such a burner, which reduces operating costs.
  • 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 of Fig. 2 in a view of its front.
  • a gas turbine burner is shown in FIG. This has one of a substantially cylindrical wall 1 limited air supply channel 3, in the center of a fuel lance 5 runs. At the top 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 Ollanze for supplying a liquid fuel.
  • the burner comprises a second fuel supply system 9, which has an axial passage 11, through which the fuel lance 5 hm preparegeschreibt 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 blades 15 located at the downstream end of the fuel supply system 9 and extending through the air supply passage 3. through Fuel supply ducts 17, a fuel, in the present embodiment, a gaseous fuel, passed into the swirl vanes 15, from where it is injected through Duseno réelleen 19 in the air flowing through the air supply duct 3 air.
  • the invention can also be used in the context of burners can be realized, in which both by 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 by both the fuel supply system, and by the fuel lance each a gaseous fuel For example, then the fuel lance can be used as a pilot burner.
  • Fuel lance 5 is shown in FIG. FIG. 3 also shows a frontal view of the end portion as viewed along the axial direction of the fuel lance 5.
  • the end portion 13 comprises a substantially cylindrical portion 20, followed by a substantially truncated conical tip 21 connects.
  • three fuel nozzles 7 are distributed uniformly in the circumferential direction, as shown in particular in FIG. 3. 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.
  • Kuhlluftkanalen 25 which in a central opening 27 mouths. This be ⁇ is where the deck of the truncated cone runs.
  • the cooling air ducts 25 are fed by feed openings 29 in the cylindrical section 20 of the end section 13 of the nozzle lance 5. During operation of the burner, part of the air flowing through the air feed channel 3 flows through the food openings 29 into the cooling air duct 25. This air has temperatures However, the tip 21 is heated in the gas operation of the burner shown by the prevailing flame in the flame chamber to temperatures of about 800 to 1,000 0 C, the cooler than the temperature of the top.
  • the fuel passage 31 and the fuel nozzles 7 of the fuel lance 5 are spooled to avoid coking.
  • This winding is typically performed with water having a temperature of about 25 ° C. Due to the high Temperaturdif ⁇ ference between the rinse water on the one hand and the tip 21 on the other hand, there is in this case in the tip to Thermospannun- gene, which are defined degrade.
  • the nozzle surface forming the lateral surface 23 of the tip 21 is provided with slots 33.
  • the slots 33 extend in the present exemplary embodiment through the lateral surface 23 through to the Kuhlluftkanalen 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 food 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 ⁇ wells arranged in the present embodiment in the middle between two Brennstoffdusen. 7
  • the slots 33 can also be offset in the clockwise or counterclockwise direction in comparison with the exemplary embodiment shown in FIG.
  • the deformation of the truncated cone lateral surface 23 in the region of the cooling air ducts 25 which is made possible by the slits 33 then enables the thermal stresses occurring during the winding process to be reduced.
  • optional through holes 30 are the Brennstoffdu ⁇ sen 7 around the existing, up to the Kuhlluftkanalen 25 rich and allow the passage of Kuhlfluid.
  • the provision of the slots 33 in the fuel lance of the burner according to the invention advantageously makes it possible to reduce thermal stresses during the winding of the fuel lance with rinsing water, without the slots adversely affecting the aerodynamics in the region of 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)

Abstract

L'invention concerne une lance à combustible (5) pour brûleur, en particulier pour un brûleur de turbine à gaz. Cette lance (5) comprend une pointe (21) qui présente une surface d'ajutage (23) pourvue d'au moins deux ajutages à combustible (7), la surface d'ajutage étant pourvue de fentes (33) entre les ajutages à combustible.
EP09752330A 2008-12-12 2009-11-05 Lance à combustible pour brûleur Withdrawn EP2359065A2 (fr)

Priority Applications (1)

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

Applications Claiming Priority (3)

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
EP09752330A EP2359065A2 (fr) 2008-12-12 2009-11-05 Lance à combustible pour brûleur

Publications (1)

Publication Number Publication Date
EP2359065A2 true EP2359065A2 (fr) 2011-08-24

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 Before (1)

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

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US8663348B2 (en) * 2010-08-11 2014-03-04 General Electric Company Apparatus for removing heat from injection devices and method of assembling same
US20160010865A1 (en) * 2013-02-05 2016-01-14 Siemens Aktiengesellschaft Fuel lances having thermally insulating coating
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
DE102013208069A1 (de) * 2013-05-02 2014-11-06 Siemens Aktiengesellschaft Brennerlanze für einen Brenner einer Gasturbine
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
JP6429994B2 (ja) * 2014-08-14 2018-11-28 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 熱シールドを備える多機能燃料ノズル
US10196983B2 (en) 2015-11-04 2019-02-05 General Electric Company Fuel nozzle for gas turbine engine
DE102015222661A1 (de) * 2015-11-17 2017-05-18 Siemens Aktiengesellschaft Strömungshülse für Brennstoffeindüsung mit Zeitverzögerung
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
US11022313B2 (en) 2016-06-22 2021-06-01 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
DE102019103640A1 (de) * 2019-02-13 2020-08-13 Mitsubishi Hitachi Power Systems Europe Gmbh Brennstoffdüse mit Dehnungsschlitzen für einen Kohlenstaubbrenner
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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Also Published As

Publication number Publication date
CN102265091A (zh) 2011-11-30
JP5340410B2 (ja) 2013-11-13
WO2010066516A3 (fr) 2011-04-21
RU2529970C2 (ru) 2014-10-10
RU2011128704A (ru) 2013-01-20
WO2010066516A2 (fr) 2010-06-17
CN102265091B (zh) 2014-04-09
US20110247338A1 (en) 2011-10-13
JP2012511687A (ja) 2012-05-24
EP2196734A1 (fr) 2010-06-16
US8973367B2 (en) 2015-03-10

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