EP2362142A1 - Agencement de brûleur - Google Patents

Agencement de brûleur Download PDF

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Publication number
EP2362142A1
EP2362142A1 EP10154109A EP10154109A EP2362142A1 EP 2362142 A1 EP2362142 A1 EP 2362142A1 EP 10154109 A EP10154109 A EP 10154109A EP 10154109 A EP10154109 A EP 10154109A EP 2362142 A1 EP2362142 A1 EP 2362142A1
Authority
EP
European Patent Office
Prior art keywords
carrier
fuel
burner
fuel nozzle
gas
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Withdrawn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
EP10154109A
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Tobias Krieger
Daniel Vogtmann
Ulrich Wörz
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 EP10154109A priority Critical patent/EP2362142A1/fr
Priority to US13/029,352 priority patent/US20110203283A1/en
Priority to JP2011033220A priority patent/JP2011169579A/ja
Priority to CN2011100410873A priority patent/CN102162641A/zh
Publication of EP2362142A1 publication Critical patent/EP2362142A1/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Withdrawn legal-status Critical Current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
    • F23D23/00—Assemblies of two or more burners
    • 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
    • F23C2900/07021—Details of lances
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Definitions

  • the present invention relates to a burner assembly and a gas turbine having such a burner assembly.
  • a gas turbine comprises as essential components a compressor, a turbine with moving blades and at least one combustion chamber.
  • the blades of the turbine are arranged as blade rings on a shaft extending mostly through the entire gas turbine, which is coupled to a consumer, such as a generator for power generation.
  • the shaft provided with the blades is also called turbine runner or rotor. Between the blade rings are vanes, which serve as nozzles for guiding the working fluid through the turbine.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • the vanes serve to optimize the momentum transfer.
  • a typical burner assembly for gas turbines as shown in US 6,082,111 is described and how it is used in particular in so-called tube combustion chambers, usually has an annular support with uniformly distributed around the circumference of the ring number of fuel nozzles.
  • fuel nozzle openings are arranged, with which fuel can be injected into an air supply channel.
  • the fuel nozzles represent a main stage of the burner, which is used to generate a premix flame, ie a flame, in which the air and the fuel before the Ignition can be mixed, serves.
  • premix burners are operated with lean air-fuel mixtures, ie with mixtures which contain relatively little fuel.
  • pilot burner Through the center of the annular fuel distributor ring typically extends a pilot burner, which is designed as a diffusion burner, i. it produces a flame in which the fuel is injected directly into the flame without first being mixed with air.
  • the pilot burner in addition to starting the gas turbine, also serves to stabilize the premix flame which, to minimize emissions, is often operated in a range of air to fuel mixing ratio which could lead to flame instabilities without assistive pilot flame.
  • a burner assembly such as the burner assembly described, typically includes a number of fuel nozzles machined from a block of metal and welded to the carrier to supply fuel to the combustion chamber.
  • the carrier distributes the fuel to the individual nozzles through incorporated fuel passages (distribution channels).
  • the carrier blank and thus the subsequent carrier must have a certain minimum thickness. This increases the weight of the burner assembly and the material costs. In addition, machine incorporation is laborious.
  • the carrier also heats up, but the fuel-carrying lines remain cold. This results in thermal stresses and the carrier does not meet the requirement for a long service life.
  • the burner assembly according to the invention comprises a carrier and a number of fuel nozzles, which are mounted in the flow direction on the carrier. It has been recognized that when used as a fuel distributor, the carrier has a minimum height, i. must have a certain thickness. Since the carrier designed as a fuel distributor is exposed directly to the hot gas in the combustion chamber, it must be made of high-temperature-resistant material, e.g. consist of a superalloy. These are very expensive.
  • a burner arrangement has a carrier and at least two fuel nozzles with fuel nozzle tips fixed to the carrier in the flow direction.
  • each fuel nozzle comprises a carrier-side portion, which carrier side has a contact surface, with which it bears against a bearing surface of the carrier, wherein emanating from the carrier-side portion at least two integrally formed fuel nozzle tips in the flow direction.
  • the burner assembly according to the invention has a gas supply supply system extending through the carrier to the fuel nozzle tips.
  • the gas supply supply system comprises at least one gas supply line and its passage through the carrier.
  • the carrier can be dispensed with a distribution channel in the carrier.
  • the material thickness of the carrier can be reduced, whereby weight and cost can be saved.
  • the requirements for the installation space of the burner assembly in the region of the side facing away from the fuel nozzles side of the carrier in comparison to the prior art are less stringent. Overall, the machining of the carrier is simplified.
  • the gas supply supply system comprises at least one gas supply line and its passage through the carrier.
  • the gas supply line remains largely cold during operation by the gas flowing through and the carrier is heated by the compressor air, this results in thermal stresses that do not guarantee a sufficient life. This is especially the case when the gas supply line to the carrier materially connected, e.g. is welded, for example, to cause a seal of the implementation. Also arises with additional attachment of the fuel nozzle to the support by screws a double fixation, which also have a life-shortening effect.
  • the bushing is designed as a fit instead of the weld. This may in particular be a dimensional or transitional fit.
  • both parts have the same nominal size, but the position and size of the tolerance fields can be different.
  • a fit always indicates a tolerance in which the actual dimensions of bore and shaft are allowed to move.
  • Another problem of the prior art fuel nozzle is the fixation of the fuel nozzles to the carrier, because the burner nozzles must be arranged perpendicular to the carrier in the manufacturing process.
  • the fuel nozzles can now be centered on the gas supply line, so that here no increased effort is required.
  • At least one distributor channel is provided on the carrier side, which supplies the gas supply line with gas. Since the distribution channels now lie on the downstream side of the carrier and are not directly in contact with hot gas, as was the case originally with the distribution channel, the distribution channels can now be made of less expensive material. This can significantly save costs. That is, the fuel is already distributed to the carrier before (seen in the direction of flow) and is not split after the carrier on the channels.
  • a further fuel supply line for liquid fuel through the support in particular oil line, is provided, which supplies the fuel nozzle on the carrier side with liquid fuel, in particular oil.
  • the fuel nozzle is supplied with gas and oil.
  • At least one seal is present between the carrier-side contact surface and the carrier.
  • the seal is the carrier side in the region of the fit and gas supply line, so arranged the gas pipe.
  • the at least one seal can be designed as a c-ring seal.
  • the carrier can identify a bulge, in which the seal is arranged.
  • the carrier-side contact surface of the fuel nozzle on at least one opening for attachment of the carrier-side contact surface on the support surface of the carrier.
  • the opening is a bore and the attachment is a screw or a bolt connection.
  • six holes for screw or bolt connections are provided in the carrier-side contact surface, wherein the holes are distributed over the entire carrier-side contact surface of the fuel nozzle. Due to the distribution pattern of the holes on the entire contact surface, the fuel nozzle has high natural frequencies, which can be quickly damped. Thus, the fuel nozzle is stable against natural frequencies.
  • the gas turbine according to the invention comprises a compressor section, a combustion section, a combustion chamber, a burner, a turbine section, a rotor and such a burner arrangement. As a result, the gas turbine is particularly easy.
  • FIG. 1 showing a highly schematic sectional view of a gas turbine, explaining the structure and function of a gas turbine.
  • the gas turbine 1 comprises a compressor section 3, a combustion section 4, which in the present embodiment comprises a plurality of tube combustion chambers 5 with burners 6 arranged thereon, but in principle may also comprise an annular combustion chamber, and a turbine section 7.
  • a rotor 9, also called a runner, extends extending through all sections and carries in the compressor section 3 compressor blade rings 11 and the turbine section 7 turbine blade rings 13.
  • FIG. 2 shows a known from the prior art burner 6 of the combustion section 4 in a perspective view.
  • the burner 6 comprises a fuel distributor ring 27, eight fuel nozzles 29 extending from the fuel distributor ring 27 and eight swirlers 31 arranged in the region of the tips of the fuel nozzles 29.
  • the fuel distributor ring 27 and the fuel nozzles 29 together form a burner housing through which fuel lines extend to Eindüsö réelleen which are disposed within the swirl generator 31.
  • the fuel nozzles 29 may be welded to the fuel distributor ring 27.
  • the burner can be connected to fuel supply lines.
  • the burner 6 can be attached to a tube combustion chamber so that the fuel nozzles 29 point towards the interior of the combustion chamber.
  • burner 6 has eight fuel nozzles 29, it is also possible to equip it with a different number of fuel nozzles 29.
  • the number of fuel nozzles 29 may be greater than or less than eight, for example, six fuel nozzles 29 or twelve fuel nozzles 29 may be present, each having its own swirl generator.
  • a pilot fuel nozzle is usually arranged in the center of the burner. The pilot fuel nozzle is in for clarity FIG. 2 not shown.
  • air from the compressor is passed through the swirl generators 31 where it is mixed with fuel. Subsequently, the air-fuel mixture is then burned in the combustion zone of the combustion chamber 5 to form the working medium.
  • the carrier 27 has the task of distributing the fuel to the fuel nozzles 29. It is internally provided with fuel channels, each of which supplies a number of nozzles 29 with fuel. On the carrier 27 there are 2 connections for fuel supply lines, which guide the fuel to the carrier 27, in which it is subsequently distributed to the fuel nozzles 29. These can also be different types of fuel.
  • the fuel nozzles 29 have for this purpose at least one fuel opening at which the fuel can escape.
  • the channels are typically milled by machine into a cylindrical carrier blank and then covered with welded-on elements.
  • the bushings for the pipelines are machined into the carrier blank.
  • the carrier blank and thus the subsequent carrier must have a certain minimum thickness. This increases the weight of the burner assembly and the material costs.
  • the machine incorporation is laborious and therefore associated with high costs.
  • Another problem is the production of the fuel nozzles 29 to the carrier 27, because the burner nozzles 29 must be welded perpendicular to the carrier 27. This production is also very tedious and associated with increased effort and therefore costs.
  • the fuel nozzles are welded to the swirl generator 31.
  • the carrier 27 is exposed to high temperatures such as Therefore, the carrier 27 and fuel nozzles 29 must be made of high temperature resistant material, such as corrosion-resistant nickel-based alloys. However, this material also drives up the costs greatly.
  • a burner arrangement is provided with a carrier 37 and at least two fuel nozzles 40 attached to the carrier 37 in the flow direction.
  • each fuel nozzle 40 has a carrier-side section 45, which carrier side 100 has a bearing surface 60, with which it bears against a bearing surface 55 of the carrier 37.
  • At least two integrally formed fuel nozzle tips 47a, 47b extend from the carrier-side section 45 in the flow direction, that is to say in the direction of the combustion chamber 5.
  • the fuel nozzle 40 has a gas supply supply system 120 extending through the carrier 37, which transports gas to the fuel nozzle tips 47a, 47b.
  • the gas supply supply system 120 comprises at least one gas supply line 70, one in the form of a gas tube 70 and its passage through the carrier 37.
  • the feedthrough may be a bore.
  • the implementation in particular the bore, designed as a fit 75.
  • the passage of the gas pipe 70 is therefore carried out according to the invention as a fit 75 and thus allows little flow, for example, compressor air inlet or gas outlet. This is especially a dimensional or transitional fit.
  • the carrier 37 can thus freely expand during operation. Thermal stresses are thus eliminated or greatly reduced, resulting in an increase in life.
  • the gas pipe 70 remains largely cold during operation, whereas the carrier 37 heats up. In this case, the carrier 37 expands. If, as in the prior art, the gas pipe 70 is welded to the carrier 37 for the purpose of sealing, then high stresses in the welding region can result from the thermal expansion. When welding, the service life requirements are therefore not met by the different extent of the carrier 37 and the gas pipe 70. If, in addition, the fuel nozzle 40 is still bolted to the carrier 37, the attachment of the fuel nozzle 40 to the carrier 37 is overdetermined by the welding and the screw connection, which likewise has a negative effect on the service life.
  • At least one seal 80 is preferably present on the wearer 100 end of the fit 75, particularly in the region of the fit 75 and the gas tube 70.
  • the carrier 37 can identify a bulge, in which the seal 80 is arranged.
  • Such a seal 80 may in particular be designed as a c-ring seal. These are particularly well suited as seals due to their springback properties. In principle, however, other resilient seals such as o-ring seals are possible. Due to the elasticity of the seal, excessive restrictions on relative movements, which could occur, for example, due to the operational heating of the components, can be avoided.
  • Another problem of the prior art fuel nozzle is the manufacture of the fuel nozzles 40 to the carrier 37, because the fuel nozzles 40 must be arranged perpendicular to the carrier 37 in the manufacturing process. This production is also very tedious and associated with increased effort and therefore costs.
  • through holes may be arranged through which in addition at least one oil passage is guided through the carrier 37 therethrough.
  • Codabmen 101 is at least one distribution channel (not shown), but mostly two distribution channels each for oil and gas, provided which supply the gas supply pipe 70 and the at least one oil channel already carrier downstream 101 with the appropriate fuel. Since the distribution channels are not directly in contact with the hot gas in the combustion chamber, they can be made of a low-cost material.
  • the carrier-side contact surface 60 has holes for attachment of the fuel nozzles 40 on the carrier.
  • the carrier 37 has corresponding openings or holes. Through these holes, the fuel nozzle 40 can be secured to the carrier 37 by means of a screw or a bolt connection.
  • the holes are distributed over the entire carrier-side contact surface 60. By this distribution of the holes, the fuel nozzle 40 high natural frequencies that can be quickly damped. Thus, the fuel nozzle 40 is stable against natural frequencies.
  • the screw or bolt connection secures the fuel nozzle 40 to the carrier 37 and thus takes over a large part of the pressure loads during operation.
  • the holes in the carrier-side abutment surface 60, as well as the corresponding holes / holes in the carrier 37 may be provided with large measurement tolerances, so that a quick and easy production is possible.
  • the burner assembly according to the invention it is possible to significantly increase the life of the burner assembly. This is due to the fact that the now possible free thermal deformations no longer build up disabling thermal stresses.
  • the fuel nozzle 40 can be easily centered over the gas pipe 70.
  • the c-ring seal prevents unwanted leaks; An uncontrolled gas and / or compressor air entering or exiting can thus be avoided.
  • the individual fuel nozzles 40 can now be detached from the carrier easily and non-destructively, whereby the assembly / disassembly is in particular improved. This is of enormous benefit; especially when checking already manufactured and put into operation systems.

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  • 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)
EP10154109A 2010-02-19 2010-02-19 Agencement de brûleur Withdrawn EP2362142A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP10154109A EP2362142A1 (fr) 2010-02-19 2010-02-19 Agencement de brûleur
US13/029,352 US20110203283A1 (en) 2010-02-19 2011-02-17 Burner arrangement
JP2011033220A JP2011169579A (ja) 2010-02-19 2011-02-18 バーナ装置
CN2011100410873A CN102162641A (zh) 2010-02-19 2011-02-21 燃烧器装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10154109A EP2362142A1 (fr) 2010-02-19 2010-02-19 Agencement de brûleur

Publications (1)

Publication Number Publication Date
EP2362142A1 true EP2362142A1 (fr) 2011-08-31

Family

ID=42543483

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10154109A Withdrawn EP2362142A1 (fr) 2010-02-19 2010-02-19 Agencement de brûleur

Country Status (4)

Country Link
US (1) US20110203283A1 (fr)
EP (1) EP2362142A1 (fr)
JP (1) JP2011169579A (fr)
CN (1) CN102162641A (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8915706B2 (en) * 2011-10-18 2014-12-23 General Electric Company Transition nozzle
US9366439B2 (en) * 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
KR101853464B1 (ko) 2015-06-22 2018-06-04 두산중공업 주식회사 실링구조를 포함하는 연료공급노즐.
US11230976B2 (en) * 2017-07-14 2022-01-25 General Electric Company Integrated fuel nozzle connection

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1254911B (de) * 1965-09-23 1967-11-23 Daimler Benz Ag Anordnung des Einspritzduesenkoerpers an bzw. in der Brennkammer von Gasturbinentriebwerken
DE2946393A1 (de) * 1978-11-20 1980-05-22 Rolls Royce Brenneinrichtung fuer gasturbinentriebwerke
EP0837284A2 (fr) * 1996-10-21 1998-04-22 General Electric Company Vrille autocentrante
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
US20040129797A1 (en) * 2002-10-10 2004-07-08 Volvo Aero Corporation Fuel injector
US20060026966A1 (en) * 2004-08-04 2006-02-09 Siemens Westinghouse Power Corporation Support system for a pilot nozzle of a turbine engine
EP1843099A2 (fr) * 2001-08-29 2007-10-10 Hitachi, Ltd. Chambre de combustion de turbine à gaz et procédé de fonctionnement

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5199265A (en) * 1991-04-03 1993-04-06 General Electric Company Two stage (premixed/diffusion) gas only secondary fuel nozzle
US5408825A (en) * 1993-12-03 1995-04-25 Westinghouse Electric Corporation Dual fuel gas turbine combustor
FR2721694B1 (fr) * 1994-06-22 1996-07-19 Snecma Refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes.
US5784875A (en) * 1995-11-27 1998-07-28 Innovative Control Systems, Inc. Water injection into a gas turbine using purge air
US5771696A (en) * 1996-10-21 1998-06-30 General Electric Company Internal manifold fuel injection assembly for gas turbine
JP3457907B2 (ja) * 1998-12-24 2003-10-20 三菱重工業株式会社 デュアルフュエルノズル
US6672073B2 (en) * 2002-05-22 2004-01-06 Siemens Westinghouse Power Corporation System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1254911B (de) * 1965-09-23 1967-11-23 Daimler Benz Ag Anordnung des Einspritzduesenkoerpers an bzw. in der Brennkammer von Gasturbinentriebwerken
DE2946393A1 (de) * 1978-11-20 1980-05-22 Rolls Royce Brenneinrichtung fuer gasturbinentriebwerke
EP0837284A2 (fr) * 1996-10-21 1998-04-22 General Electric Company Vrille autocentrante
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
EP1843099A2 (fr) * 2001-08-29 2007-10-10 Hitachi, Ltd. Chambre de combustion de turbine à gaz et procédé de fonctionnement
US20040129797A1 (en) * 2002-10-10 2004-07-08 Volvo Aero Corporation Fuel injector
US20060026966A1 (en) * 2004-08-04 2006-02-09 Siemens Westinghouse Power Corporation Support system for a pilot nozzle of a turbine engine

Also Published As

Publication number Publication date
US20110203283A1 (en) 2011-08-25
JP2011169579A (ja) 2011-09-01
CN102162641A (zh) 2011-08-24

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