EP2362143B1 - Brenneranordnung - Google Patents

Brenneranordnung Download PDF

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Publication number
EP2362143B1
EP2362143B1 EP20100154116 EP10154116A EP2362143B1 EP 2362143 B1 EP2362143 B1 EP 2362143B1 EP 20100154116 EP20100154116 EP 20100154116 EP 10154116 A EP10154116 A EP 10154116A EP 2362143 B1 EP2362143 B1 EP 2362143B1
Authority
EP
European Patent Office
Prior art keywords
support
arrangement according
burner arrangement
contact surface
fuel
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.)
Active
Application number
EP20100154116
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2362143A1 (de
Inventor
Andreas Böttcher
Timothy A. Fox
Thomas Grieb
Tobias Krieger
Stephen A. Ramier
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
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 ES10154116T priority Critical patent/ES2389482T3/es
Priority to EP20100154116 priority patent/EP2362143B1/de
Priority to JP2011030726A priority patent/JP5791302B2/ja
Priority to US13/029,246 priority patent/US8955328B2/en
Priority to CN201110041090.5A priority patent/CN102162642B/zh
Publication of EP2362143A1 publication Critical patent/EP2362143A1/de
Application granted granted Critical
Publication of EP2362143B1 publication Critical patent/EP2362143B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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 more particularly to a burner assembly for gas turbines.
  • 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 a 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, that is, with mixtures containing 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 assisting the 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.
  • 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.
  • a 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 according to the invention that the carrier, when used as a fuel distributor, 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 attached to the carrier.
  • the fuel nozzle further comprises a carrier-side portion, which carrier side has a contact surface, with which it bears against a contact surface of the carrier.
  • the fuel nozzle In the flow direction, at least two integrally formed fuel nozzle tips exit from the carrier-side section.
  • the passages may for this purpose also have an inner tube or a pipe.
  • 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 area of the side facing away from the fuel nozzle side of the carrier in comparison to the prior art less strict. Overall, the machining of the carrier is simplified.
  • At least one distributor channel is provided on the carrier side, which supplies the attachment parts with fuel on the carrier side. Since the distribution channels now lie on the downstream side of the carrier and are not in direct contact with hot gas like the original 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.
  • the at least two attachment parts are at least one oil and one gas channel.
  • another oil channel is available.
  • the at least two fuel nozzle tips can each be supplied with a separate oil channel and thus also be controlled differently.
  • the attachment parts that is to say in particular the channels, are connected with the passages in the carrier-side contact surface of the carrier-side section of the fuel nozzle in a form-fitting or cohesive manner.
  • this is a screw or a welded joint.
  • through holes are provided in the carrier. Through these through holes in the carrier now the neck parts, that is, the channels are passed.
  • the attachment parts in particular the channels, preferably have an end remote from the flow direction, each having a first attachment element. Furthermore, the attachment parts, ie the channels are passed through the through holes in the carrier.
  • the attachment parts are fastened to the carrier by means of a second attachment element cooperating with the first attachment element.
  • the first fastening element and the second fastening element can be screw connections, in particular the first fastening element an external thread and the second fastening element a nut.
  • the first fastener may be a superstructure fitting on the carrier. This is connected by a welded connection or another cohesive connection to the carrier carrier side.
  • the weld or the other cohesive connection so to speak, the second fastener.
  • the weld or the other cohesive connection prevents the through holes form unwanted passages for gas or compressor air of the turbine.
  • At least one seal is present between the first fastening element and the carrier.
  • at least one seal may be present between the carrier-side contact surface of the carrier-side section and the carrier.
  • these seals are arranged around the passages to seal them permeable to air.
  • the at least one seal is a c-ring seal or an o-seal.
  • At least the fuel nozzle tips, the carrier-side portion as well as the carrier-side contact surface with the passages are formed as a casting.
  • the attachment parts are welded to the passages in the carrier-side section of the fuel nozzle.
  • the passages have an inner tube or are they piping? formed, the neck parts are welded to the inner tube or pipe.
  • attachment parts may be formed integrally with the passages at least with the fuel nozzle tips, the carrier-side portion as well as the carrier-side contact surface.
  • the carrier-side contact surface has at least one opening for attachment of the carrier-side contact surface on the carrier.
  • This can be an opening a hole.
  • the carrier has corresponding openings or holes.
  • the carrier-side contact surface may be secured to the carrier by a screw connection or a bolt connection. Bolts are often used for quick and often to be loosened connections without axial load instead of screws.
  • At least six bores for screw or bolt connections are preferably provided in the carrier-side contact surface, wherein the bores are distributed over the entire carrier-side contact surface. 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 burner arrangement is provided in particular in a gas turbine.
  • 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 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 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 support 27 there are connections 2 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 as well as the fuel nozzles 29. Therefore, carrier 27 must as well
  • Fuel nozzles 29 are 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 fastened to the carrier 37 in the flow direction ( FIG. 3 ).
  • each fuel nozzle 40 has a carrier-side section 45, which has a support surface 60 on the carrier side, with which it bears against a contact 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 carrier-side contact surface 60 has at least two projecting in the direction of the support 37 neck portions, which are designed in particular as channels, in particular as an oil passage 50 a and a gas channel 51.
  • the attachment parts can also be manufactured as a pipeline.
  • fuel is supplied to the fuel nozzle through laterally described passages 65 in the carrier-side contact surface 60 of the carrier-side section 45.
  • a non-illustrated tube may be mounted in these passages 56.
  • two oil passages 50a and 50b are provided. This embodiment is particularly advantageous because the two integrally formed fuel nozzle tips 47a, 47b, which emanate from the carrier-side section 45 in the direction of the combustion chamber 5, can now be supplied with fuel by the two oil passages 50a and 50b.
  • Through holes 37 are provided in the carrier 37, through which the oil passages 50a, 50b and the gas passage 51 are passed through the carrier 37.
  • passages 65 for the fuel appropriate. These passages 65 can be introduced later, for example, by drilling or produced at the same time in the production.
  • the channels 50a, 50b and 51 are now positively and / or materially connected to these passages 65. If the passages 65 have inner tubes or are designed as pipelines, the channels 50a, 50b and 51 are connected to them. Fuel is transported through the channels 50a, 50b and 51 and then flows through the respective passages 65 into the fuel nozzle 40 to the fuel nozzle tips 47a, 47b.
  • the channels 50a, 50b and 51 are welded to the passages 65, or are incorporated directly during manufacture, e.g. pour through.
  • At least one distributor channel (not shown), but mostly two distributor channels for oil and gas, is provided on the side of the carrier, which supplies the channels 50a, 50b and 51 in each case already with carrier carrier side with the appropriate fuel. Since the distributor rings do not come into direct contact with the hot gas in the combustion chamber, they can be made of a low-cost material.
  • the channels 50 a, 50 b, and 51 are passed through the through holes in the carrier 37.
  • the channels 50a, 50b, and 51 have an end 34 opposite to the flow direction, each having a first fastening element and being fastened to the support 37 by a second fastening element cooperating with the first fastening element.
  • first fastening element and the second fastening element may be a screw connection.
  • the fastening is provided by a support part tightly resting on the support 63, which is connected to the support 37 in a form-fitting manner, in particular by welding.
  • at least one seal may be present between the first fastening element, for example the attachment part 63 and the carrier 37.
  • the welding itself can be designed as a seal.
  • a seal may be present, in particular around the passages 65 around.
  • the seal can also be a weld here.
  • the carrier-side contact surface 60 has six holes 73 (FIG. FIG. 5 ) on.
  • the carrier 37 has corresponding openings or holes. Through these holes 73, the fuel nozzle 40 can be secured to the carrier 37 by means of a screw connection or a bolt connection.
  • the holes 73 are distributed over the entire carrier-side contact surface 60. As a result of this distribution of the bores 73, the fuel nozzle 40 has high natural frequencies, which can be quickly damped. Thus, the fuel nozzle 40 is stable against natural frequencies.
  • the screw or bolt connections attached quasi the fuel nozzle 40 in addition to the welded attachment parts 63 on the carrier 37 and thus takes over a large part of the pressure loads during operation.
  • the holes 73 in the carrier-side abutment surface 60, as well as the corresponding holes / holes in the carrier 37 are provided with large measurement tolerances, so that a quick and easy production is possible.

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)
EP20100154116 2010-02-19 2010-02-19 Brenneranordnung Active EP2362143B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
ES10154116T ES2389482T3 (es) 2010-02-19 2010-02-19 Sistema de quemador
EP20100154116 EP2362143B1 (de) 2010-02-19 2010-02-19 Brenneranordnung
JP2011030726A JP5791302B2 (ja) 2010-02-19 2011-02-16 バーナ装置
US13/029,246 US8955328B2 (en) 2010-02-19 2011-02-17 Burner arrangement
CN201110041090.5A CN102162642B (zh) 2010-02-19 2011-02-21 燃烧器装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20100154116 EP2362143B1 (de) 2010-02-19 2010-02-19 Brenneranordnung

Publications (2)

Publication Number Publication Date
EP2362143A1 EP2362143A1 (de) 2011-08-31
EP2362143B1 true EP2362143B1 (de) 2012-08-29

Family

ID=42536358

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20100154116 Active EP2362143B1 (de) 2010-02-19 2010-02-19 Brenneranordnung

Country Status (5)

Country Link
US (1) US8955328B2 (https=)
EP (1) EP2362143B1 (https=)
JP (1) JP5791302B2 (https=)
CN (1) CN102162642B (https=)
ES (1) ES2389482T3 (https=)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2327933A1 (de) * 2009-11-30 2011-06-01 Siemens Aktiengesellschaft Brenneranordnung
US9366439B2 (en) * 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
US9322558B2 (en) * 2013-06-27 2016-04-26 Siemens Aktiengesellschaft Combustor apparatus in a gas turbine engine
US10443855B2 (en) 2014-10-23 2019-10-15 Siemens Aktiengesellschaft Flexible fuel combustion system for turbine engines
CN104748132B (zh) * 2015-04-14 2017-01-25 河南宏天实业有限公司 升降式微正压保持聚能火炬燃烧器
US11230976B2 (en) * 2017-07-14 2022-01-25 General Electric Company Integrated fuel nozzle connection

Family Cites Families (18)

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Publication number Priority date Publication date Assignee Title
GB2036296B (en) * 1978-11-20 1982-12-01 Rolls Royce Gas turbine
JP2544470B2 (ja) * 1989-02-03 1996-10-16 株式会社日立製作所 ガスタ―ビン燃焼器及びその運転方法
DE69515931T2 (de) * 1994-06-10 2000-11-02 General Electric Co., Schenectady Regelung einer Gasturbinenbrennkammer
US5415000A (en) * 1994-06-13 1995-05-16 Westinghouse Electric Corporation Low NOx combustor retro-fit system for gas turbines
JPH08261467A (ja) * 1995-03-28 1996-10-11 Toshiba Corp ガスタービン燃焼器
US6122916A (en) * 1998-01-02 2000-09-26 Siemens Westinghouse Power Corporation Pilot cones for dry low-NOx combustors
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
JP4323723B2 (ja) * 1998-10-09 2009-09-02 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン燃焼器の燃料噴射組立体
US6311473B1 (en) * 1999-03-25 2001-11-06 Parker-Hannifin Corporation Stable pre-mixer for lean burn composition
JP3069347B1 (ja) * 1999-06-11 2000-07-24 川崎重工業株式会社 ガスタ―ビンの燃焼器用バ―ナ装置
US6327860B1 (en) * 2000-06-21 2001-12-11 Honeywell International, Inc. Fuel injector for low emissions premixing gas turbine combustor
JP3960166B2 (ja) * 2001-08-29 2007-08-15 株式会社日立製作所 ガスタービン燃焼器およびガスタービン燃焼器の運転方法
US6813889B2 (en) * 2001-08-29 2004-11-09 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US7121481B2 (en) * 2002-10-10 2006-10-17 Volvo Aero Corporation Fuel injector
US7197877B2 (en) * 2004-08-04 2007-04-03 Siemens Power Generation, Inc. Support system for a pilot nozzle of a turbine engine
US20100071377A1 (en) * 2008-09-19 2010-03-25 Fox Timothy A Combustor Apparatus for Use in a Gas Turbine Engine
US8365535B2 (en) * 2009-02-09 2013-02-05 General Electric Company Fuel nozzle with multiple fuel passages within a radial swirler
US8347631B2 (en) * 2009-03-03 2013-01-08 General Electric Company Fuel nozzle liquid cartridge including a fuel insert

Also Published As

Publication number Publication date
ES2389482T3 (es) 2012-10-26
CN102162642B (zh) 2015-03-11
CN102162642A (zh) 2011-08-24
EP2362143A1 (de) 2011-08-31
JP2011169577A (ja) 2011-09-01
US8955328B2 (en) 2015-02-17
US20110203285A1 (en) 2011-08-25
JP5791302B2 (ja) 2015-10-07

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