EP2196733A1 - Lance de brûleur - Google Patents

Lance de brûleur Download PDF

Info

Publication number
EP2196733A1
EP2196733A1 EP08171526A EP08171526A EP2196733A1 EP 2196733 A1 EP2196733 A1 EP 2196733A1 EP 08171526 A EP08171526 A EP 08171526A EP 08171526 A EP08171526 A EP 08171526A EP 2196733 A1 EP2196733 A1 EP 2196733A1
Authority
EP
European Patent Office
Prior art keywords
burner
lance
heat shield
opening
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Withdrawn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
EP08171526A
Other languages
German (de)
English (en)
Inventor
Marcus Fischer
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP08171526A priority Critical patent/EP2196733A1/fr
Publication of EP2196733A1 publication Critical patent/EP2196733A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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
    • F23D11/101—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 medium and fuel meeting before the burner outlet

Definitions

  • the present invention relates to a burner lance, in particular a burner lance for a gas turbine burner.
  • Such burning 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 flows through the lance, exits at its tip through several oil nozzles and thus fed to the combustion.
  • the gaseous fuels are often injected into an air supply channel surrounding the nozzle lance.
  • the lance tip is therefore usually exposed to high temperatures in the range of about 800 to 1,000 ° C. These high temperatures can lead to coking of residues of liquid fuels in the nozzle openings of the burner lance.
  • a burner lance for use in a Burner especially in a gas turbine burner to provide, which helps to overcome the disadvantages mentioned.
  • Another object of the invention is to provide an advantageous burner, in particular a gas turbine burner.
  • the first object is achieved by a burner lance according to claim 1, the second object by a burner according to claim 9.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner lance according to the invention comprises a lance tip with at least one fuel nozzle surrounded by a heat shield.
  • the heat shield is spaced from the lance tip so that there is a flow channel for a cooling fluid between the heat shield and the lance tip.
  • the heat shield has at least one outflow opening for the cooling fluid in the flow channel.
  • the heat shield has at least one upstream to the outflow and connected to a cooling fluid supply inlet.
  • the fuel nozzle is arranged in the burner lance according to the invention in a projecting over the surface of the lance tip protrusion which is at least brought to an opening of the heat shield and which can protrude in particular in the opening of the heat shield.
  • the at least bringing the projection to the opening in the heat shield makes it possible to use the heat shield not only in conjunction with gas nozzles, but in particular also in conjunction with atomizing nozzles for liquid fuels.
  • the approach of the nozzle openings makes it possible to atomize the liquid fuel without the corresponding aerosol impinges on the heat shield in the region of the opening.
  • an impact of fuel aerosol on the heat shield can be largely excluded.
  • Coking can be avoided on the heat shield, which could reduce the flow cross-section of the cooling fluid channel in the heat shield on the one hand, which would adversely affect the cooling performance.
  • the projection in which the at least one fuel nozzle is arranged, has a peripheral surface and the opening in the heat shield has an edge, between which there is a gap.
  • the gap leads to a thermal decoupling of the heat shield from the projection, so that a transfer of heat from the heat shield to the nozzle projection can be avoided.
  • the gap represents an outlet opening for the cooling fluid, so that penetration of hot combustion gases into the gap does not take place.
  • the cooling fluid flowing out through the gap cools the nozzle projection, so that its temperature is kept in a moderate range.
  • the projection may in particular be formed by a nozzle body containing the fuel nozzle, which is inserted into a recess in the lance tip adapted to the shape of the nozzle body.
  • This embodiment makes it possible to replace the nozzle body, if in spite of the thermal decoupling of the heat shield and the cooling thermally induced damage to the projection occur. But also a replacement due to other causes, for example, to realize a different atomization profile is possible.
  • the inflow opening for the cooling fluid may advantageously be arranged in a peripheral surface of the heat shield. This makes it possible to fix the heat shield over its entire circumference at its end remote from the lance tip on the lance body, which increases the stability of the arrangement.
  • a burner according to the invention is equipped with a burner lance according to the invention.
  • the burner lance can be used in particular for supplying a liquid fuel.
  • the burner can then also be equipped with fuel nozzles for gaseous fuels.
  • burner lances according to the invention and the burner according to the invention are particularly advantageous when a liquid fuel is supplied by the burner lance
  • burner lances for supplying gaseous fuels can be designed according to the burner lance according to the invention, wherein the fuel nozzle then no atomizing nozzle.
  • the use of the burner lance according to the invention in the burner according to the invention leads to the fact that the maintenance intervals for such a burner can be extended due to the increased service life of the burner lance, which lowers the operating costs.
  • Fig. 1 shows a section of a burner with a burner lance according to the invention in a sectional view.
  • Fig. 2 shows the burner lance of the burner Fig. 1 in a view on her front ..
  • a gas turbine burner shown schematically. This has a one of a substantially cylindrical wall 1 limited air supply channel 3, in the center of a burner lance 5 runs. At the top of the burner lance fuel nozzles 7 are present for injecting a fuel into the air supplied through the air supply channel 3.
  • the burner lance 5 is an oil lance for supplying a liquid fuel.
  • the distribution of the fuel nozzles 7 over the circumference of the tip is in FIG. 2 to recognize, which represents a view on the front of the top.
  • a second fuel supply system 9 which has an axial passage 11 through which the burner lance 5 is passed, so that only the end portion 13 of the burner 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.
  • 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 channel 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 However, in principle, also be implemented in the context of burners in which both by the fuel supply system 9, and by the burner lance 5 each a fuel in the same state of matter is supplied, ie for example in the context of a burner in which both by the fuel supply system 9, as well a gaseous fuel is supplied through the burner lance 5 in each case.
  • the burner lance 5 can be used as a pilot burner.
  • the fuel nozzle 7 is designed in the present embodiment as a Zerstäubungsdüse, which is supplied via a supply channel for liquid fuels 21 to be atomized liquid fuel.
  • the nozzle 7 is part of a nozzle body 23, which is inserted into a receptacle 25 in the body of the burner lance 5, which is located in the region of a frusto-conical surface 27.
  • the conical surface 27 essentially forms the tip of the burner lance 5.
  • the frusto-conical tip 20 is followed by a substantially cylindrical portion 29, over whose circumference an annular bead 31 extends.
  • a heat shield 33 is fixed, for example by means of a welding or brazing connection, which extends from the bead 31, starting over the front part of the cylindrical portion 29 and over the lateral surface 27 of the frusto-conical portion 28.
  • the end of the heat shield remote from the bead 31 has a central opening 35.
  • a plurality of openings 37 - in the present embodiment three openings - present, representing the inlet openings for cooling air.
  • the inflow openings 37 are distributed around the circumference of the frusto-conical portion around the circumference of the cylindrical part of the heat shield 33 located between the bead 31 and the frusto-conical portion in accordance with the distribution of the fuel nozzles 7, so that cooling air flowing in through the openings 37 flows without deflection can reach their axial flow direction to the nozzle bodies.
  • a cooling air channel 39 is formed. This is supplied through the opening 37 with cooling air coming from the air supply channel 3. The cooling air then flows into the cooling air duct 39, flows around the nozzle body 23 and finally exits through the central opening 35, which forms the main exit opening for the cooling air, into the combustion chamber.
  • the heat shield 33 has further openings 41 into which the nozzle bodies 23 of the fuel nozzles 7 protrude. The dimensions of the further openings 41 are selected so that the peripheral surfaces 43 of the nozzle body have a distance from the edge 45 of the openings 41.
  • a gap 47 remains between the nozzle body 23 and the heat shield 33 (best seen in FIG. 2 ).
  • This gap allows the outflow of a part of the cooling air flowing through the cooling air passage 39.
  • the cooling air flowing out through the gap 47 cools that part of the peripheral surface 43 of the nozzle body 23 which projects into the opening 41.
  • the remaining, located in the cooling air passage 39 part of this peripheral surface 43 is cooled by the main cooling air flow, which flows around the nozzle body 23 to the central outlet opening 35.
  • the gap 47 also allows thermal decoupling of the nozzle body 23 from the heat shield 33, since there is no direct heat-conducting contact between the two ,
  • the nozzle body 23 protrudes into the opening 41, there is when injecting a liquid fuel through a nozzle opening arranged in the end face 49 Even with a spray cone with a large opening angle, there is no risk that droplets of the atomized fuel will strike the material of the heat shield 33.
  • no droplets can be entrained by the cooling air flow flowing in the cooling air duct 39 in the direction of the heat shield.
  • the exiting through the gap 47 cooling air ensures that droplets that are basically on a path that would allow a hitting the edge 45 of the opening 41 are entrained by the air flow, so that the heat shield 33 reliably before a Contamination and associated possible coking is protected.

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)
EP08171526A 2008-12-12 2008-12-12 Lance de brûleur Withdrawn EP2196733A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08171526A EP2196733A1 (fr) 2008-12-12 2008-12-12 Lance de brûleur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08171526A EP2196733A1 (fr) 2008-12-12 2008-12-12 Lance de brûleur

Publications (1)

Publication Number Publication Date
EP2196733A1 true EP2196733A1 (fr) 2010-06-16

Family

ID=40626945

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08171526A Withdrawn EP2196733A1 (fr) 2008-12-12 2008-12-12 Lance de brûleur

Country Status (1)

Country Link
EP (1) EP2196733A1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012110506A1 (de) * 2012-11-02 2014-05-08 Webasto SE Hochdruckzerstäubungsbrenneranordnung
CN107076420A (zh) * 2014-08-14 2017-08-18 西门子公司 具有隔热罩的多功能燃料喷嘴
JP2017525924A (ja) * 2014-08-14 2017-09-07 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 噴霧器配列を備える多機能燃料ノズル
JP2018506693A (ja) * 2015-01-22 2018-03-08 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ スロットを有するスワーラベーンを備える燃焼器入口混合システム
DE102016226061A1 (de) 2016-12-22 2018-06-28 Siemens Aktiengesellschaft Brennerspitze zum Einbau in einen Brenner mit Luftkanalsystem und Brennstoffkanalsystem und Verfahren zu deren Herstellung
DE102017200106A1 (de) 2017-01-05 2018-07-05 Siemens Aktiengesellschaft Brennerspitze mit einem Luftkanalsystem und einem Brennstoffkanalsystem für einen Brenner und Verfahren zu deren Herstellung
DE102017200643A1 (de) 2017-01-17 2018-07-19 Siemens Aktiengesellschaft Brennerspitze mit einer Luftkanalstruktur und einer Brennstoffkanalstruktur für einen Brenner und Verfahren zur Herstellung der Brennerspitze
DE102022208337A1 (de) * 2022-08-10 2024-02-15 Rolls-Royce Deutschland Ltd & Co Kg Pilotierungsanordnung, Düsenvorrichtung, Verfahren und Gasturbinenanordnung
DE102023203942A1 (de) * 2023-04-27 2024-10-31 Rolls-Royce Deutschland Ltd & Co Kg Pilotierungsanordnung für eine düsenvorrichtung sowie düsenvorrichtung und gasturbinenanordnung mit einer pilotierungsanordnung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4198815A (en) * 1975-12-24 1980-04-22 General Electric Company Central injection fuel carburetor
EP0638769A2 (fr) * 1993-08-10 1995-02-15 ABB Management AG Injecteur de combustible pour des combustibles liquides et gazeux et procédé de sa mise en oeuvre
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor
DE19905995A1 (de) * 1999-02-15 2000-08-17 Asea Brown Boveri Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer sowie Verfahren zum Betrieb einer solchen Brennstofflanze
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US7325402B2 (en) 2004-08-04 2008-02-05 Siemens Power Generation, Inc. Pilot nozzle heat shield having connected tangs

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4198815A (en) * 1975-12-24 1980-04-22 General Electric Company Central injection fuel carburetor
EP0638769A2 (fr) * 1993-08-10 1995-02-15 ABB Management AG Injecteur de combustible pour des combustibles liquides et gazeux et procédé de sa mise en oeuvre
US5680766A (en) * 1996-01-02 1997-10-28 General Electric Company Dual fuel mixer for gas turbine combustor
DE19905995A1 (de) * 1999-02-15 2000-08-17 Asea Brown Boveri Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer sowie Verfahren zum Betrieb einer solchen Brennstofflanze
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US7325402B2 (en) 2004-08-04 2008-02-05 Siemens Power Generation, Inc. Pilot nozzle heat shield having connected tangs

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012110506A1 (de) * 2012-11-02 2014-05-08 Webasto SE Hochdruckzerstäubungsbrenneranordnung
DE102012110506B4 (de) * 2012-11-02 2017-04-27 Webasto SE Hochdruckzerstäubungsbrenneranordnung
US10125991B2 (en) 2014-08-14 2018-11-13 Siemens Aktiengesellschaft Multi-functional fuel nozzle with a heat shield
CN107076420A (zh) * 2014-08-14 2017-08-18 西门子公司 具有隔热罩的多功能燃料喷嘴
JP2017525924A (ja) * 2014-08-14 2017-09-07 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 噴霧器配列を備える多機能燃料ノズル
JP2017524890A (ja) * 2014-08-14 2017-08-31 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
JP2018506693A (ja) * 2015-01-22 2018-03-08 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ スロットを有するスワーラベーンを備える燃焼器入口混合システム
DE102016226061A1 (de) 2016-12-22 2018-06-28 Siemens Aktiengesellschaft Brennerspitze zum Einbau in einen Brenner mit Luftkanalsystem und Brennstoffkanalsystem und Verfahren zu deren Herstellung
WO2018114918A1 (fr) 2016-12-22 2018-06-28 Siemens Aktiengesellschaft Pointe de brûleur destinée à être montée dans un brûleur comprenant un système de conduit d'air et un système de conduit de combustible et procédé de fabrication associé
DE102017200106A1 (de) 2017-01-05 2018-07-05 Siemens Aktiengesellschaft Brennerspitze mit einem Luftkanalsystem und einem Brennstoffkanalsystem für einen Brenner und Verfahren zu deren Herstellung
WO2018127471A1 (fr) 2017-01-05 2018-07-12 Siemens Aktiengesellschaft Pointe de brûleur comprenant un système de conduit d'air et un système de conduit de combustible pour un brûleur et procédé de fabrication associé
DE102017200643A1 (de) 2017-01-17 2018-07-19 Siemens Aktiengesellschaft Brennerspitze mit einer Luftkanalstruktur und einer Brennstoffkanalstruktur für einen Brenner und Verfahren zur Herstellung der Brennerspitze
WO2018134058A1 (fr) 2017-01-17 2018-07-26 Siemens Aktiengesellschaft Pointe de brûleur avec une structure de conduit d'air et une structure de conduit de carburant pour un brûleur et procédé pour la fabrication d'une pointe de brûleur
DE102022208337A1 (de) * 2022-08-10 2024-02-15 Rolls-Royce Deutschland Ltd & Co Kg Pilotierungsanordnung, Düsenvorrichtung, Verfahren und Gasturbinenanordnung
US12007118B2 (en) 2022-08-10 2024-06-11 Rolls-Royce Deutschland Ltd & Co Kg Pilot arrangement, nozzle device, method and gas turbine arrangement
DE102023203942A1 (de) * 2023-04-27 2024-10-31 Rolls-Royce Deutschland Ltd & Co Kg Pilotierungsanordnung für eine düsenvorrichtung sowie düsenvorrichtung und gasturbinenanordnung mit einer pilotierungsanordnung

Similar Documents

Publication Publication Date Title
EP2196733A1 (fr) Lance de brûleur
DE69827897T2 (de) Zweistoffdüse zur Verhinderung der kohlenstoffhaltigen Ablagerung auf Oberflächen einer Gasturbinenbrennkammer
EP2196734A1 (fr) Lance de combustible pour un brûleur
EP0902233B1 (fr) Buse de pulvérisation par pression combinée
DE4212810B4 (de) Brenner mit zusätzlicher Zuführungsmöglichkeit für fluidische Stoffe, insbesondere für Gasturbinen, und Verfahren zu seinem Betrieb
DE102006007087B4 (de) Gasturbinen-Brennkammer
DE10304386B4 (de) Doppelfluid-Verwirbelungsdüse mit selbstreinigendem Zapfen
DE60037850T2 (de) Flüssigbrennstoffeinspritzdüse für Gasturbinenbrenner
EP1456583B1 (fr) Procédé d'injection d'un mélange air/carburant dans une chambre de combustion
DE4326802A1 (de) Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
EP2470834B1 (fr) Brûleur notamment destiné à des turbines à gaz
CH701539A2 (de) Vorrichtung zur Brennstoffeinspritzung bei einer Turbine.
EP2103876A2 (fr) Brûleur pour turbine à gaz avec mécanisme de rinçage pour les buses à combustible
DE2060401A1 (de) Brennstoffinjektor fuer ein Gasturbinenstrahltriebwerk
WO2011023648A2 (fr) Aube de turbulence, brûleur et turbine à gaz
DE19618856B4 (de) Vorrichtung zum Betreiben einer mit kombinierten Brennern für flüssige und gasförmige Brennstoffe bestückten Ringbrennkammer
EP2230458A1 (fr) Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
EP2264370B1 (fr) Agencement de brûleur pour une installation de combustion destinée à la combustion de combustibles fluidiques et procédé de fonctionnement d'un tel agencement de brûleur
EP2409086B1 (fr) Arrangement de brûleur pour une turbine à gaz
EP3134681B1 (fr) Corps de buse de combustible
EP2558781B1 (fr) Générateur de turbulence pour un brûleur
DE2552864A1 (de) Verfahren und brenner zum verbrennen von fluessigen brennstoffen
EP2980482A1 (fr) Brûleur pour un moteur à combustion interne et moteur à combustion interne
DE2910464A1 (de) Brennstoffinjektor fuer ein gasturbinentriebwerk
DE102018112389B4 (de) Injektorvorrichtung, Brennkammersystem und Verfahren zum Einbringen von reaktionsfähigem Fluid in eine Brennkammer

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKY No designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20101217