EP2470834A1 - Brûleur notamment destiné à des turbines à gaz - Google Patents

Brûleur notamment destiné à des turbines à gaz

Info

Publication number
EP2470834A1
EP2470834A1 EP10749631A EP10749631A EP2470834A1 EP 2470834 A1 EP2470834 A1 EP 2470834A1 EP 10749631 A EP10749631 A EP 10749631A EP 10749631 A EP10749631 A EP 10749631A EP 2470834 A1 EP2470834 A1 EP 2470834A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
swirl
nozzles
burner according
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.)
Granted
Application number
EP10749631A
Other languages
German (de)
English (en)
Other versions
EP2470834B1 (fr
Inventor
Andreas Böttcher
Mariano Cano Wolff
Andre Kluge
Tobias Krieger
Sascha Staring
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
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
Publication of EP2470834A1 publication Critical patent/EP2470834A1/fr
Application granted granted Critical
Publication of EP2470834B1 publication Critical patent/EP2470834B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/36—Supply of different fuels

Definitions

  • the present invention relates to a burner and, more particularly, to a gas turbine combustor having a central fuel supply arrangement.
  • the invention relates to a gas turbine.
  • the burner described in EP 0 276 696 B1 is a hybrid burner for premixing operation with gas and / or oil, as it is used in particular for gas turbine plants.
  • the burner comprises a central fuel supply arrangement, in which also a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • the possibility for feeding in inert materials is provided.
  • the central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with a swirler blading therein having a plurality of blades and gas pre-mixing nozzle pipes located upstream of the blades.
  • inlet nozzles for oil in the area of the swirl blading which allow premixing of the main air flow with oil.
  • the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes themselves, as described, for example, in EP 0 580 683 B1.
  • Fuel injection through the blade as in EP 0 580 683 Bl further fuel injection can be used by the blade.
  • This additional fuel injection should be controllable separately from the main gas stage, i.
  • an additional, second gas channel must be introduced into the central fuel supply device of the burner.
  • a difficulty now is that the additional gas channel meets the necessary strength criteria, while having a long life.
  • the object of the present invention is therefore to provide a burner, in particular a gas turbine burner, with two fuel passages which has a long service life. It is a second object of the present invention to provide an advantageous gas turbine.
  • the first object is achieved by the specification of a burner according to claim 1, the second object by a gas turbine according to claim 8.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner has a central fuel supply arrangement and an annular air duct surrounding the central fuel supply arrangement for supplying combustion air.
  • swirl vanes are arranged, which first fuel nozzles for injecting a substantially gaseous fuel into the combustion air and second fuel nozzles for injecting a substantially gaseous Have fuel in the combustion air.
  • the first fuel nozzles are fed by a fuel distributor supply in the fuel supply arrangement and the second fuel nozzles by a fuel distributor channel in the fuel supply arrangement.
  • the burner has a fuel flow direction.
  • the fuel distributor supply now comprises a supply pipe, which is connected downstream with the swirl blade, and a ring attachment, wherein the supply pipe is connected upstream with the ring attachment and wherein the ring attachment is arranged upstream of the fuel distribution channel.
  • This causes a spatial separation of the two fuel passages, that is, the feed tube with the ring attachment and the original fuel distribution channel are spatially separated.
  • the original fuel distribution channel is more or less parallel to the supply pipe.
  • the ring attachment acts to pull out the high voltages from the component, that is, the fuel supply assembly and distribute it evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the fuel supply assembly is significantly extended.
  • the original aero design is not or only insignificantly influenced.
  • already manufactured machines can be easily provided with such a ring attachment and such a feed tube due to the now easier production and now easier installation.
  • the ring attachment comprises a separate pipe connection. This supplies the feed pipe with fuel.
  • a plurality of swirl vanes are provided, each of these swirl vanes having a separate supply pipe, wherein each of the separate supply pipes is connected to the one ring attachment.
  • the first fuel injection is fed by a first manifold and the second fuel injection is fed by a second manifold, the manifold being integrated in the swirl vane, and wherein the swirl vane between the first and second manifolds is split into two vane halves.
  • the distribution pipes and the respective nozzles can be supplied separately with fuel. As a result, a controlled control of the fuel flow is possible.
  • Both blade halves preferably have a locating pin downstream and a sliding seat upstream. By the dowel pin and the sliding seat, the two blade halves are now thermally separately expandable, which also stresses are reduced.
  • the fuel distribution channel and the supply pipe are separated by a web, wherein the web is made flexible.
  • the web can be made of an elastic material and / or it can also act elastically by means of a corresponding geometric design and thus compensate for stresses. This can be effected for example by a curved or corrugated web.
  • a burner is provided in a gas turbine.
  • FIG. 2 shows a schematic diagram of a swirl blade
  • FIG. 3 shows a schematic diagram of a combustion chamber hub with two integrated gas stages and an oil channel
  • FIG 4 shows a cross section of a combustion chamber hub according to the invention with ring attachment and swirl blade
  • FIG 5 is a plan view of a ring attachment with swirl blades.
  • FIG. 1 shows a burner in a highly schematized schematic diagram.
  • the burner which may optionally be used in conjunction with a plurality of similar burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both the pilot burner system and the main burner system may optionally be operated with gaseous and / or liquid fuels, such as natural gas or fuel oil.
  • the pilot burner system includes an inner oil supply passage 1 which may be concentrically surrounded by an inner annular gas supply passage 3. This, in turn, can be be surrounded concentrically surrounding air supply channel or Inertstoffzubuchkanal 5.
  • a suitable ignition system may be arranged in or on this air supply channel (not shown in the figure).
  • the pilot burner system has a combustion chamber 7 zuwerende outlet opening 9, in whose area a twist blading 11 may be arranged in the air supply duct. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected into the supplied air or the added inert material by means of oil nozzles 15 downstream of the swirl blading.
  • the pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame.
  • a diffusion burner in which the fuel is injected directly into the flame.
  • the main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend.
  • These swirl blades 19 have first fuel nozzles 21 and second fuel nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply channel 17.
  • oil can be injected by means of oil nozzles 25.
  • the first fuel nozzles 21 and second fuel nozzles 23 located in the swirl blades 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27.
  • the Swirl vane 19 and the hub 27 have a fuel flow direction.
  • this first and second annular fuel distributor channels 29 and 31 are arranged, which supply the fuel nozzles 21 and 23 with gas.
  • an annular oil distribution channel 33 is arranged, which supplies the oil nozzles 25 with oil.
  • the fuel distributor channels 29, 31 and the oil distribution channel 33 are supplied with fuel via fuel supply channels 35, 37 or via an oil supply channel 39.
  • the fuel supply channels 35, 37 supply the fuel distribution channels 29, 31 with fuel.
  • For the oil supply channel 39 is a separate oil supply pipe 43 before.
  • FIG. 2 shows a schematic representation of a swirl blade 19 with two integrated gas stages B and D.
  • the swirl blade 19 has two independent
  • the one fuel distribution channel 29 with the outlet nozzles 21 can be used, for example, for injecting a different medium D than the second fuel distribution channel 31 via the outlet nozzles 23 (medium B).
  • both media to be injected through the fuel distribution channels 29 and 31 of the swirl vane 19 will be gaseous, e.g. As the one medium natural gas and the other medium coal gas.
  • an inert material such as water vapor can be injected via these outlet nozzles 21 and / or 23 if necessary.
  • FIG. 3 shows a fuel hub 27 with the fuel distributor channel 29 and 31 with openings, which leads the fuel into the blade 19.
  • the two fuel distribution channels 29 and 31 are arranged substantially parallel and separated by a web 50.
  • At least one of the fuel distributor channels 29 is then designed as a feed tube 55 (FIG. 4).
  • the feed tube 55 opens downstream into a manifold 65 (or alternatively 70). Upstream, the feed tube 55 is connected to the ring attachment 60 ( Figure 5).
  • the ring attachment 60 seen in the flow direction, the fuel distribution channel 31 (or alternatively 29) upstream.
  • the original fuel distribution channel 31 is parallel to the supply pipe 55.
  • the ring attachment 60 is supplied with a separate pipe connection 75.
  • the original fuel distribution channel 31 (or alternatively 29) is supplied with another channel 80.
  • the two leading gas passages namely the feed tube 55 with the ring attachment 60 and the original fuel distribution channel 31 (or alternatively 29) according to the invention spatially decoupled.
  • the ring attachment 60 acts to pull the high stresses out of the hub 27 and distribute them evenly over the component. This results in a defusing of the installation space due to lower voltages. Thus, the life of the burner hub 27 is substantially extended.
  • the ring attachment 60 does not or only insignificantly influences the original aero design. Also already manufactured machines can easily be provided with such a ring attachment 60 and such a feed tube 55 due to the now easier production and now easier installation.
  • Such a burner hub 27 is preferably used in conjunction with a divided swirl blade 19.
  • This comprises the first fuel injection 21, which is fed by a first distributor pipe 65, and the second fuel injection 23, which is fed by a second distributor pipe 70.
  • the manifold 65, 70 integrated in the swirl blade 19.
  • the split swirl vane 19 is now interposed between the first and second manifolds 65 and 70 divided into two vane halves 19a, 19b.
  • the blade halves 19a, 19b also have downstream of a fitting pin 90a, 90b and upstream of a sliding seat 85a, 85b, which is mounted so to speak in the hub 27 itself.
  • the web 50 in order to obtain an additional voltage reduction, can be made flexible.
  • the web 50 can be made of an elastic material. Additionally or alternatively, the web 50 can also act elastically by a corresponding geometry and thus compensate for stresses. This can e.g. be effected by a curved or corrugated web 50.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un brûleur comportant un dispositif d'alimentation en combustible central (27), un canal d'air annulaire (17) entourant le dispositif d'alimentation en combustible central (27), pour l'alimentation en air de combustion, et des aubes de turbulence (19) disposées dans le canal d'air annulaire (17), présentant des premières buses à combustible (21) destinées à introduire un combustible essentiellement gazeux dans l'air de combustion, et des deuxièmes buses à combustible (23) destinées à introduire un combustible essentiellement gazeux dans l'air de combustion. Les premières buses à combustible (21) sont alimentées par une alimentation de distribution de combustible dans le dispositif d'alimentation en combustible (27), et les deuxièmes buses à combustible (23) sont alimentées par un canal de distribution de combustible (31) dans le dispositif d'alimentation en combustible (27). L'alimentation de distribution de combustible comporte un tube d'alimentation (55) relié en aval aux aubes de turbulence (19), et un élément rapporté annulaire (60). Le tube d'alimentation (55) est relié en amont à l'élément rapporté annulaire (60) et, vu dans le sens d'écoulement, l'élément rapporté annulaire (60) est monté en amont du canal de distribution de combustible (31). L'invention concerne également une turbine à gaz comportant un tel brûleur.
EP10749631.7A 2009-08-26 2010-08-24 Brûleur notamment destiné à des turbines à gaz Not-in-force EP2470834B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200910038848 DE102009038848A1 (de) 2009-08-26 2009-08-26 Brenner, insbesondere für Gasturbinen
PCT/EP2010/062284 WO2011023669A1 (fr) 2009-08-26 2010-08-24 Brûleur notamment destiné à des turbines à gaz

Publications (2)

Publication Number Publication Date
EP2470834A1 true EP2470834A1 (fr) 2012-07-04
EP2470834B1 EP2470834B1 (fr) 2015-07-15

Family

ID=43125513

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10749631.7A Not-in-force EP2470834B1 (fr) 2009-08-26 2010-08-24 Brûleur notamment destiné à des turbines à gaz

Country Status (5)

Country Link
EP (1) EP2470834B1 (fr)
CN (1) CN102597631B (fr)
DE (1) DE102009038848A1 (fr)
RU (1) RU2536465C2 (fr)
WO (1) WO2011023669A1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8978384B2 (en) * 2011-11-23 2015-03-17 General Electric Company Swirler assembly with compressor discharge injection to vane surface
US9217570B2 (en) * 2012-01-20 2015-12-22 General Electric Company Axial flow fuel nozzle with a stepped center body
DE102012213852A1 (de) 2012-08-06 2014-02-06 Siemens Aktiengesellschaft Lokale Verbesserung der Mischung von Luft und Brennstoff in Brennern mit Drallerzeugern
EP2864706B1 (fr) 2012-08-06 2016-11-02 Siemens Aktiengesellschaft Amélioration locale du mélange d'air et de combustible dans des brûleurs pourvus de générateurs de tourbillon comprenant des extrémités à aube entrecroisées dans la zone extérieure
EP2703622B1 (fr) 2012-08-31 2014-12-31 Caterpillar Motoren GmbH & Co. KG Tête de cylindre avec manchon de capteur
CN103528094B (zh) * 2013-07-10 2015-04-08 辽宁省燃烧工程技术中心（有限公司） 一种燃气轮机气体燃料干式低氮燃烧装置
DE102015205069B4 (de) * 2015-03-20 2020-04-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbrennungsvorrichtung
DE102015206227A1 (de) * 2015-04-08 2016-10-13 Siemens Aktiengesellschaft Brenneranordnung
CN109237514B (zh) * 2018-08-08 2024-02-23 中国华能集团有限公司 一种用于燃气轮机的双管路气体燃料燃烧器
CN110454781B (zh) * 2019-08-20 2024-07-16 广东万和电气有限公司 一种分气盘及灶具燃烧器
CN114110662B (zh) * 2021-11-25 2023-02-10 同济大学 一种燃气轮机低氮燃烧室

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276696B1 (fr) * 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
EP0580683B1 (fr) 1991-04-25 1995-11-08 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
DE19549140A1 (de) * 1995-12-29 1997-07-03 Asea Brown Boveri Verfahren zum Betrieb einer Gasturbogruppe mit niederkalorischem Brennstoff
EP1394471A1 (fr) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brûleur
EP1507119A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brûleur et méthode de fonctionnement d'une turbine à gaz
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
EP1614967B1 (fr) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP1662202B1 (fr) * 2004-11-30 2016-11-16 Siemens Aktiengesellschaft Brûleur pour une turbine à gaz
GB2437977A (en) * 2006-05-12 2007-11-14 Siemens Ag A swirler for use in a burner of a gas turbine engine
EP2161502A1 (fr) * 2008-09-05 2010-03-10 Siemens Aktiengesellschaft Brûleur à prémélange pour un combustible pauvre et riche

Non-Patent Citations (1)

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Title
See references of WO2011023669A1 *

Also Published As

Publication number Publication date
DE102009038848A1 (de) 2011-03-03
CN102597631A (zh) 2012-07-18
RU2536465C2 (ru) 2014-12-27
WO2011023669A1 (fr) 2011-03-03
EP2470834B1 (fr) 2015-07-15
RU2012111248A (ru) 2013-10-10
CN102597631B (zh) 2014-08-13

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