EP2327933A1 - Brenneranordnung - Google Patents

Brenneranordnung Download PDF

Info

Publication number
EP2327933A1
EP2327933A1 EP09177514A EP09177514A EP2327933A1 EP 2327933 A1 EP2327933 A1 EP 2327933A1 EP 09177514 A EP09177514 A EP 09177514A EP 09177514 A EP09177514 A EP 09177514A EP 2327933 A1 EP2327933 A1 EP 2327933A1
Authority
EP
European Patent Office
Prior art keywords
fuel
arrangement according
burner arrangement
distributor ring
fuel distributor
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Withdrawn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
EP09177514A
Other languages
German (de)
English (en)
French (fr)
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 EP09177514A priority Critical patent/EP2327933A1/de
Priority to CN201080054090.2A priority patent/CN102639939B/zh
Priority to EP10779300.2A priority patent/EP2507557B1/de
Priority to PCT/EP2010/067000 priority patent/WO2011064086A1/de
Priority to US13/512,452 priority patent/US9103552B2/en
Priority to RU2012127366/06A priority patent/RU2562900C2/ru
Priority to ES10779300T priority patent/ES2432237T3/es
Publication of EP2327933A1 publication Critical patent/EP2327933A1/de
Withdrawn legal-status Critical Current

Links

Images

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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23D2211/00—Thermal dilatation prevention or compensation
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

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 uniformly distributed around the circumference of the ring nozzle lances.
  • 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 mix before igniting become, serve.
  • 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 assistive pilot flame.
  • the fuel distributor ring is characterized by a short service life.
  • the burner arrangement comprises a fuel distributor ring ring and a number of fuel nozzles which are mounted in the flow direction to the fuel distributor ring.
  • the fuel distributor ring has an annular surface in the flow direction.
  • the fuel distributor ring an outer side facing the middle of the ring and an opposite outer side.
  • At least one slot is now present on the surface between the fuel nozzles.
  • This discharge slot results in a better heat distribution in the material of the fuel distributor, whereby the voltages are reduced and sets a longer life expectancy.
  • the relief slot can vary in depth, width and length and be adapted to the respective Brennstoffverteilerring.
  • the at least one slot extends on the surface from the outside to the inside.
  • stress relief is provided over a wide surface area.
  • a plurality of fuel nozzles are present, wherein between each adjacent fuel nozzle, a slot is present.
  • the entire surface ring of the fuel distributor ring is coated with relief slots.
  • the at least one slot is substantially Y-shaped.
  • the at least one Y-shaped slot comprises two arms and one leg, wherein the two arms of the substantially Y-shaped slot point to the outside of the fuel distributor ring.
  • the two arms of the substantially y-shaped slot may also face towards the inside of the fuel distributor ring.
  • At least one recess is arranged on the surface. Due to the at least one recess, especially in connection with the slots, an optimized geometry results, which results in a better heat distribution in the material of the fuel distributor ring. Due to the better heat distribution no locally excessive voltages occur and the required service life cycles can be achieved. The voltage can thus be reduced in this range from originally over 950MPa to 600MPa.
  • the at least one recess preferably also partially includes the outside of the fuel distributor ring.
  • the at least one recess is substantially round.
  • the at least one recess may have a radius, wherein the radius decreases seen in the flow direction.
  • the fuel distributor ring preferably comprises at least one nickel alloy, in particular a nickel-molybdenum alloy, or a nickel-chromium-iron-molybdenum alloy. These alloys are particularly resistant to high temperatures.
  • the fuel distributor ring comprises in its interior at least two fuel channels for two combustion stages A and B.
  • the two fuel channels comprise two supply connections.
  • the fuel nozzles can be supplied separately and separately depending on the load state of the engine fuels.
  • 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 fuel distributor ring 27 has the task of distributing the fuel to the fuel nozzles 29. It is internally provided with two fuel channels 41, 42 each of which supplies a number of nozzles 29 (4 nozzles 29 in this particular case) with fuel as a stage A and a stage B ( FIG. 3 and FIG. 4 ).
  • the two fuel passages 41 and 42 include two supply ports 51, 52 for supplying fuel. These can also be different types of fuel.
  • the fuel distributor ring 27 flows from the outside with up to 500 ° C warm compressor air, but from the inside with cold fuel, which in extreme cases can only have a temperature of 20 ° C. As a result, very high voltages occur at the fuel distributor ring 27. Especially on the nozzles 29 facing surface side 45 of the fuel distributor ring 27 occur very high voltages, so that the life can not be achieved.
  • the fuel distributor ring 27 there are a number of fuel nozzles 29, which are mounted in the flow direction on the fuel distributor ring 27.
  • the fuel distributor ring 27 in the flow direction, an annular surface 54 and a ring-facing outer inner side 56 and an outer opposite outer side 58 on.
  • At least one slot 60 is present on the surface 45 between the fuel nozzles 29.
  • This is essentially y-shaped ( FIG. 3 and FIG. 5 ).
  • substantially Y-shaped means that all forms are here encompassed which approximately remind one of the letter Y, that is to say have two arms 62 and one leg 63.
  • all spaces on the surface 45 between the nozzles 29 are provided with such slots 60.
  • the slot 60, and in particular the y-shaped slot 60 may extend on the surface 54 from the outside 58 to the inside 56.
  • the two arms 62 of the substantially Y-shaped slot 60 can advantageously be arranged on the outside 58 of the surface 54 of the fuel distributor ring 27.
  • recesses 66 may be arranged on the surface 54 ( FIG. 5 ).
  • These recesses 66 are arranged on the surface 54 such that they partially also comprise the outside 58 of the fuel distributor ring 27, that is, there is a recess from the outside 58 of the fuel distributor 27.
  • the recess 66 may vary in depth and shape. However, this is preferably a substantially circular recess 66.
  • the recesses 66 may have a radius and the radius seen in the flow direction decrease. This makes it even more effective to avoid the high thermal gradient during operation and the resulting stresses.
  • the fuel distributor ring 27 preferably comprises at least one nickel alloy, in particular a nickel-molybdenum alloy. This material is particularly heat-resistant and therefore particularly suitable for burners.
  • the burner assembly according to the invention can be used in particular in a gas turbine.
  • slots 60 and recesses 66 according to the invention can be built into existing fuel distributor rings 27 in terms of production technology, since they do not require any far-reaching conversions and are therefore easy to implement in terms of manufacturing technology. Even on the previous aero performance of the burner creates only minimal impact.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP09177514A 2009-11-30 2009-11-30 Brenneranordnung Withdrawn EP2327933A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP09177514A EP2327933A1 (de) 2009-11-30 2009-11-30 Brenneranordnung
CN201080054090.2A CN102639939B (zh) 2009-11-30 2010-11-08 燃烧器装置
EP10779300.2A EP2507557B1 (de) 2009-11-30 2010-11-08 Brenneranordnung
PCT/EP2010/067000 WO2011064086A1 (de) 2009-11-30 2010-11-08 Brenneranordnung
US13/512,452 US9103552B2 (en) 2009-11-30 2010-11-08 Burner assembly including a fuel distribution ring with a slot and recess
RU2012127366/06A RU2562900C2 (ru) 2009-11-30 2010-11-08 Горелка
ES10779300T ES2432237T3 (es) 2009-11-30 2010-11-08 Disposición de quemador

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09177514A EP2327933A1 (de) 2009-11-30 2009-11-30 Brenneranordnung

Publications (1)

Publication Number Publication Date
EP2327933A1 true EP2327933A1 (de) 2011-06-01

Family

ID=42112003

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09177514A Withdrawn EP2327933A1 (de) 2009-11-30 2009-11-30 Brenneranordnung
EP10779300.2A Not-in-force EP2507557B1 (de) 2009-11-30 2010-11-08 Brenneranordnung

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10779300.2A Not-in-force EP2507557B1 (de) 2009-11-30 2010-11-08 Brenneranordnung

Country Status (6)

Country Link
US (1) US9103552B2 (zh)
EP (2) EP2327933A1 (zh)
CN (1) CN102639939B (zh)
ES (1) ES2432237T3 (zh)
RU (1) RU2562900C2 (zh)
WO (1) WO2011064086A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013147632A1 (en) * 2012-03-29 2013-10-03 General Electric Company Bi-directional end cover with extraction capability for gas turbine combustor

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016037966A1 (de) * 2014-09-12 2016-03-17 Siemens Aktiengesellschaft Brenner mit fluidischem oszillator, für eine gasturbine und gasturbine mit mindestens einem derartigen brenner
DE102015218687A1 (de) * 2015-09-29 2017-04-13 Siemens Aktiengesellschaft Brenneranordnung für eine Ringbrennkammer mit Resonatoren
CN108266274B (zh) * 2016-12-30 2019-09-17 中国航发商用航空发动机有限责任公司 发动机、喷油嘴及其集油环
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
CN110566959A (zh) * 2019-09-10 2019-12-13 宁波方太厨具有限公司 灶具火盖及包括其的燃烧器

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0526152A1 (en) * 1991-08-01 1993-02-03 General Electric Company Flashback resistant fuel staged premixed combustor
EP0924458A1 (de) * 1997-12-22 1999-06-23 Asea Brown Boveri AG Brenner
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
US6634175B1 (en) * 1999-06-09 2003-10-21 Mitsubishi Heavy Industries, Ltd. Gas turbine and gas turbine combustor
US20040040310A1 (en) * 2002-09-03 2004-03-04 Prociw Lev Alexander Stress relief feature for aerated gas turbine fuel injector
WO2008034227A1 (en) * 2006-09-18 2008-03-27 Pratt & Whitney Canada Corp. Internal fuel manifold having temperature reduction feature

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5524438A (en) * 1994-12-15 1996-06-11 United Technologies Corporation Segmented bulkhead liner for a gas turbine combustor
US5836164A (en) * 1995-01-30 1998-11-17 Hitachi, Ltd. Gas turbine combustor
US6122916A (en) * 1998-01-02 2000-09-26 Siemens Westinghouse Power Corporation Pilot cones for dry low-NOx combustors
GB2333832A (en) * 1998-01-31 1999-08-04 Europ Gas Turbines Ltd Multi-fuel gas turbine engine combustor
US6089025A (en) * 1998-08-24 2000-07-18 General Electric Company Combustor baffle
RU2258822C1 (ru) * 2003-11-27 2005-08-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Способ регулирования подачи топлива в камеру сгорания газотурбинной установки и устройство для его осуществления
RU2290565C1 (ru) * 2005-03-28 2006-12-27 Открытое акционерное общество "Авиадвигатель" Топливная форсунка камеры сгорания газотурбинного двигателя
GB2432655A (en) * 2005-11-26 2007-05-30 Siemens Ag Combustion apparatus
DE102007043626A1 (de) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität
ES2389482T3 (es) * 2010-02-19 2012-10-26 Siemens Aktiengesellschaft Sistema de quemador
US8590311B2 (en) * 2010-04-28 2013-11-26 General Electric Company Pocketed air and fuel mixing tube
US8938978B2 (en) * 2011-05-03 2015-01-27 General Electric Company Gas turbine engine combustor with lobed, three dimensional contouring

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0526152A1 (en) * 1991-08-01 1993-02-03 General Electric Company Flashback resistant fuel staged premixed combustor
EP0924458A1 (de) * 1997-12-22 1999-06-23 Asea Brown Boveri AG Brenner
US6082111A (en) 1998-06-11 2000-07-04 Siemens Westinghouse Power Corporation Annular premix section for dry low-NOx combustors
US6634175B1 (en) * 1999-06-09 2003-10-21 Mitsubishi Heavy Industries, Ltd. Gas turbine and gas turbine combustor
US20040040310A1 (en) * 2002-09-03 2004-03-04 Prociw Lev Alexander Stress relief feature for aerated gas turbine fuel injector
WO2008034227A1 (en) * 2006-09-18 2008-03-27 Pratt & Whitney Canada Corp. Internal fuel manifold having temperature reduction feature

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013147632A1 (en) * 2012-03-29 2013-10-03 General Electric Company Bi-directional end cover with extraction capability for gas turbine combustor

Also Published As

Publication number Publication date
RU2012127366A (ru) 2014-01-10
ES2432237T3 (es) 2013-12-02
EP2507557A1 (de) 2012-10-10
CN102639939B (zh) 2014-11-12
EP2507557B1 (de) 2013-09-25
RU2562900C2 (ru) 2015-09-10
CN102639939A (zh) 2012-08-15
US20120234010A1 (en) 2012-09-20
WO2011064086A1 (de) 2011-06-03
US9103552B2 (en) 2015-08-11

Similar Documents

Publication Publication Date Title
DE102007004864C5 (de) Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
EP2507557B1 (de) Brenneranordnung
EP2340397B1 (de) Brennereinsatz für eine gasturbinenbrennkammer und gasturbine
CH707752A2 (de) Vormischsystem für eine Gasturbine.
DE102010060283A1 (de) Brennstoffdüsenbaugruppe für eine Gasturbine und Verfahren für den Zusammenbau derselben
DE112014006633T5 (de) Gasturbinenbrennkammer, Gasturbine, Steuervorrichtung und Steuerverfahren
EP1847696A1 (de) Bauteil für eine gestufte Verbrennung in einer Gasturbine und entsprechende Gasturbine.
WO2014191495A1 (de) Gasturbinen-ringbrennkammer mit tangentialeindüsung als späte mager-einspritzung
CH701773B1 (de) Brenner mit einem Einlassleitschaufelsystem.
WO2012016748A2 (de) Gasturbinenbrennkammer
DE102008002934A1 (de) Brennstoffdüse für ein Gasturbinentriebwerk und Verfahren zur Herstellung desselben
DE112017001173T5 (de) Brenneranordnung, brennkammer und gasturbine
EP2808611B1 (de) Injektor zum Einbringen eines Brennstoff-Luft-Gemisches in eine Brennkammer
CH707575A2 (de) Brennkammer mit aerodynamischen Stützstreben.
EP2409087A2 (de) Verfahren zum betrieb eines brenners und brenner, insbesondere für eine gasturbine
EP2362141A1 (de) Brenneranordnung
EP2362142A1 (de) Brenneranordnung
WO2010049195A1 (de) Gasturbine mit kühleinsatz
EP3004741B1 (de) Rohrbrennkammer mit einem flammrohr-endbereich und gasturbine
EP2151630B1 (de) Swirler
EP2271876B1 (de) Brenneranordnung für fluidische brennstoffe und verfahren zum herstellen einer brenneranordnung
EP2808610A1 (de) Gasturbinen-Brennkammer mit Tangentialeindüsung als späte Mager-Einspritzung
EP2808612A1 (de) Gasturbinen-Brennkammer mit Tangentialeindüsung als späte Mager-Einspritzung
EP1642065B1 (de) Brennereinheit für eine gasturbine und gasturbine
EP2310741B1 (de) Brennstoffeinsatz

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 MK MT NL NO PL PT RO SE SI SK SM TR

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: 20111202