EP1662202A1 - Brûleur pour une turbine à gaz et procédé d'utilisation d'un tel brûleur - Google Patents

Brûleur pour une turbine à gaz et procédé d'utilisation d'un tel brûleur Download PDF

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Publication number
EP1662202A1
EP1662202A1 EP04028334A EP04028334A EP1662202A1 EP 1662202 A1 EP1662202 A1 EP 1662202A1 EP 04028334 A EP04028334 A EP 04028334A EP 04028334 A EP04028334 A EP 04028334A EP 1662202 A1 EP1662202 A1 EP 1662202A1
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EP
European Patent Office
Prior art keywords
fuel
stage
burner
fuel stage
air
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
EP04028334A
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German (de)
English (en)
Other versions
EP1662202B1 (fr
Inventor
Werner Dr. Krebs
Jürgen Dr. Meisl
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
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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
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Priority to EP04028334.3A priority Critical patent/EP1662202B1/fr
Publication of EP1662202A1 publication Critical patent/EP1662202A1/fr
Application granted granted Critical
Publication of EP1662202B1 publication Critical patent/EP1662202B1/fr
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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
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a burner with at least one air supply, a primary fuel stage and a secondary fuel stage and a gas turbine plant with such a burner. Moreover, the invention relates to a method for operating such a burner.
  • gas turbines are operated with so-called lean fuel mixtures in much of their load range, i. the combustion takes place under excess air. As a result, the combustion temperatures can be lowered, which reduces the rate of formation of nitrogen oxides compared to a stoichiometric air-fuel mixture.
  • a further reduction of the nitrogen oxide formation is achieved by operating the burner in the so-called premix mode, in which the fuel is mixed with the air before it is ignited.
  • Low-pollutant gas turbine plants are usually operated close to the lean stability limit, ie with an air-fuel mixture with a very low fuel content, ie very high excess air.
  • the gas turbine plants are susceptible to combustion vibrations whose occurrence leads to serious damage to the gas turbine plant being able to lead.
  • combustion oscillations arise due to an oscillating interaction between thermal and acoustic disturbances in the combustion process.
  • resonators which damp the vibrations are used to reduce combustion oscillations.
  • a resonator is described for example in DE 44 14 232 A1.
  • Other approaches to reducing combustion oscillations include optimizing the air-fuel mixture, adjusting the pressure losses of fuel nozzles and air passages, and actively modulating fuel flows. Such measures are described, for example, in Geoff Meyers, et al.
  • a fuel-stacked axial-flow concept is described in Michael A. Davi and Marv Weiss in GE Gas Turbine Fuel Flexibility, GE Power Systems Schenectady, NY. Between a primary fuel supply and the diffusion zone in which the combustion takes place, a secondary fuel supply stage is arranged, which also has a supplementary air supply.
  • Another object of the present invention is to provide an advantageous gas turbine plant.
  • the first object is achieved by a burner according to claim 1 and a method according to claim 14, the second object by a gas turbine plant according to claim 13.
  • the dependent claims contain advantageous embodiments of the invention.
  • An inventive burner comprises at least one air supply and assigned to an air supply a primary fuel stage, which serves as a main stage for supplying fuel, and a secondary fuel stage, which serves as an auxiliary stage for the fuel supply.
  • the secondary fuel stage is arranged in the air flow direction of the air supply upstream of the primary fuel stage.
  • the primary fuel stage and the secondary fuel stage are arranged in the air supply such that no backflow regions form between them, i. that there is no flow from the primary fuel stage to the secondary fuel stage.
  • the primary fuel stage can be used to bring about a homogeneous spatial mixture of fuel and air in the air supply characteristic of a low-emission combustion.
  • the secondary fuel stage arranged upstream as seen in the air flow direction, the temporal air-fuel mixture can be mixed in the burner to reduce combustion oscillations. It is advantageous if the fuel mass flow supplied by the secondary fuel stage is to be regulated independently of the fuel mass flow supplied by the primary fuel stage.
  • the secondary fuel stage may also be designed to supply a fuel mass flow which corresponds to a maximum of 30% of the fuel mass flow supplied by the primary fuel stage.
  • the secondary fuel stage By increasing the fuel mass flow supplied via the secondary fuel stage, it is also possible to increase the capacity for introducing fuel into the air supply, which may be expedient, for example, when using fuels with a low calorific value and / or with fuel pre-heating.
  • the secondary fuel stage thus allows an expansion of the fuel spectrum or an increased fuel flexibility of the burner.
  • Acoustic tuning of the secondary fuel stage to the primary fuel stage may be accomplished by having the secondary fuel stage impedance at a value that results in a reduction in airspeed variations or heat release variations over a burner without a secondary fuel stage.
  • the impedance hereby expresses the acoustic resistance exerted by the fuel stage with respect to a pressure wave.
  • An adaptation of the impedance can be achieved, for example, by suitably dimensioning at least one fuel passage in the region of the secondary fuel stage.
  • the fuel passage may be formed as an annular fuel distributor passage, wherein the impedance may be varied by varying the volume of the fuel distributor passage.
  • the impedance can be adapted by a fuel supply line to the secondary fuel stage is present, which is equipped with at least one acoustic filter, which may be embodied for example as a resonator.
  • the secondary fuel stage includes fuel nozzles configured to reduce the pressure loss of the fuel supplied through these nozzles from the pressure loss of the fuel supplied via the primary fuel stage nozzles.
  • the burner according to the invention can be designed, in particular, as a so-called premix burner to be operated in a premixing mode or as a hybrid burner, that is to say as a burner which is to be operated in both the diffusion and premix mode.
  • it can also be designed as a so-called.
  • Mehrbrennstoffbrenner so as a burner, which is designed for the combustion of different fuels.
  • it can be designed as a multi-fuel burner both for burning gaseous as well as for burning liquid fuels.
  • a gas turbine plant according to the invention is equipped with a burner according to the invention.
  • a burner according to the invention In her can be realized the advantages described with reference to the burner according to the invention. In particular, combustion oscillations can be reduced during operation of the system.
  • the gas turbine plant 101 has a compressor 102 for combustion air, a combustion chamber or gas turbine combustion chamber 104 and a turbine 106 for driving the compressor 102 and a generator or a working machine (not shown).
  • the turbine 106 and the compressor 102 are arranged on a common turbine shaft 108, also referred to as turbine rotor, to which the generator or the working machine is also connected and which is rotatably mounted about its central axis 109.
  • the combustor 104 is equipped with a number of burners 110 for combustion of a liquid or gaseous fuel. It is also provided on its inner wall or Brennschwandung 123 with interior trim elements 125.
  • the turbine 106 includes a number of rotatable blades 112 connected to the turbine shaft 108.
  • the blades 112 are annularly disposed on the turbine shaft 108 and thus form a number of blade rows.
  • the turbine 106 includes a number of fixed vanes 114 which are also annularly attached to an inner shell 116 of the turbine 106 to form vanes.
  • the blades 112 serve to drive the turbine shaft 108 by momentum transfer from the turbine 106 flowing through the working medium M.
  • the vanes 114 serve to flow the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 114 or a row of vanes and from a ring of blades 112 or a blade row is also referred to as a turbine stage.
  • Each guide blade 114 has a platform 118, also referred to as a blade root 119, which is arranged as a wall element for fixing the respective guide blade 114 to the inner housing 16 of the turbine 106.
  • the platform 118 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the turbine 106 flowing through the working medium M.
  • Each blade 112 is attached in an analogous manner to the turbine shaft 108 via a blade root 119, also referred to as a platform 118, the blade root 119 each carrying a profiled blade 120 extending along a blade axis.
  • each guide ring 121 is arranged on the inner housing 116 of the turbine 106.
  • the outer surface of each guide ring 121 is also exposed to the hot, the turbine 106 flowing through the working fluid M and spaced radially from the outer end 122 of the blade 112 opposite it through a gap.
  • the guide rings 121 arranged between adjacent guide blade rows serve, in particular, as cover elements which protect the inner wall 116 or other housing installation parts from thermal overload by the hot working medium M flowing through the turbine 106.
  • the gas turbine plant 101 is designed for a comparatively high outlet temperature of the working medium M emerging from the combustion chamber 104 from about 1200 ° C. to 1300 ° C.
  • the combustion chamber wall 123 is internally cooled.
  • the combustion air is simultaneously heated in a desired manner.
  • the burner according to the invention comprises an internal burner system 1, which is referred to below as a pilot burner system, and a main burner system 3 arranged concentrically around the pilot burner system 1.
  • the burner is designed as a multi-fuel burner which is suitable both for burning gaseous fuels and for burning liquid fuels.
  • it is designed as a hybrid burner, i. it can be operated both in diffusion mode and in premix mode.
  • the pilot burner system 1 includes an inner liquid fuel supply passage 5, an inner gas supply passage 7 for gaseous fuels, and an inner air supply passage 9 for supplying combustion air.
  • the inner gas supply channel 7 is arranged concentrically around the inner supply channel for liquid fuels around.
  • Around the inner gas supply channel 7 around the inner air supply channel 9 is arranged concentrically.
  • the inner supply channel for liquid fuels opens via a nozzle 11 into the combustion chamber 13.
  • the inner gas supply channel 7, however, opens via outlet openings 15 in the air supply channel 9, where a mixing of the gaseous fuel with the air.
  • a suitable ignition system is also arranged, which is not shown in Figure 2.
  • the pilot burner system 1 serves to maintain a pilot flame supporting the stability of the burner flame and, in principle, allows the burner to operate as a diffusion burner or as a burner with a premixed air-fuel mixture.
  • the main burner system 3 arranged concentrically around the pilot burner system 1 comprises a primary fuel stage 20, a secondary fuel stage 50 and an air supply channel 17 arranged concentrically around the pilot burner system 1.
  • the two fuel stages 20, 50 are arranged axially one behind the other in the air supply direction (arrow A) and serve for supply a gaseous fuel. They each include a number of nozzle tubes 22, 52 having fuel nozzles 24, 54 disposed therein, with the nozzle tubes 54 of the secondary fuel stage 50 being disposed upstream of the nozzle tubes 22 of the primary fuel stage 20 as viewed in the air supply direction.
  • the two fuel stages each comprise 20 distributed over the circumference of the main burner system 3 nozzle tubes 22, 52, on which the fuel nozzles 24, 54 are arranged radially.
  • the nozzle tubes 22, 52 are each connected to ring manifolds 26 and 56, via which the gaseous fuel is supplied to them.
  • the ring manifold 26 of the primary fuel stage 20 and the ring manifold 56 of the secondary fuel stage 50 are each supplied with gas via a number of evenly distributed around the pilot combustion system 1 around gas supply lines 28, 58.
  • the main burner system 3 also includes a supply system 19 for supplying liquid fuels, which will not be discussed further.
  • the impedance of the secondary fuel stage 50 is matched to the impedance of the primary fuel stage 20 by suitably dimensioning the ring manifold 56 and resonators 60 disposed in the gas supply lines 58.
  • Both fuel stages 20,50 are separately controllable, wherein the secondary fuel stage is controlled such that it receives a maximum of 30% of the fuel mass flow of the main burner 3.
  • An optimization of the air-fuel mixture in the burner is achieved by suitable arrangement of the nozzles 54 de secondary fuel stage.
  • the nozzles 54 are configured such that the pressure loss of the fuel via these nozzles 54 is lower than the pressure loss of the fuel via the nozzles 24 of the primary fuel stage 20.
  • the secondary fuel stage 50 fulfills various tasks. It serves, for example, to reduce fluctuations in the number of air-burners in the burner, that is to say temporal variations in the air-fuel mixture ratio. This can be accomplished by properly dividing the fuel mass flow to the primary fuel stage 20 and the secondary fuel stage 50. Proper partitioning also makes it possible to vary the spatial air-fuel mixture field in the burner.
  • the use of the secondary fuel stage 50 also increases the capacity for introducing fuel into the air supply passage, which may be useful, for example, when using fuels with a low calorific value and / or with fuel pre-heating.
  • the secondary fuel stage 50 thus allows in particular an extension of the fuel spectrum or an increased fuel flexibility of the burner.
  • the aforementioned effects can be achieved or maintained even with changes in the ambient conditions, the combustion gas properties or the performance of the turbine system.
  • the burner according to the invention may in particular be part of a gas turbine plant.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP04028334.3A 2004-11-30 2004-11-30 Brûleur pour une turbine à gaz Active EP1662202B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04028334.3A EP1662202B1 (fr) 2004-11-30 2004-11-30 Brûleur pour une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04028334.3A EP1662202B1 (fr) 2004-11-30 2004-11-30 Brûleur pour une turbine à gaz

Publications (2)

Publication Number Publication Date
EP1662202A1 true EP1662202A1 (fr) 2006-05-31
EP1662202B1 EP1662202B1 (fr) 2016-11-16

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011023669A1 (fr) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brûleur notamment destiné à des turbines à gaz
WO2011023648A3 (fr) * 2009-08-26 2012-11-15 Siemens Aktiengesellschaft Aube de turbulence, brûleur et turbine à gaz
WO2014074369A1 (fr) * 2012-11-07 2014-05-15 Siemens Aktiengesellschaft Système d'insonorisation pour une chambre de combustion d'un moteur à turbine à gaz
ITMI20122154A1 (it) * 2012-12-17 2014-06-18 Ansaldo Energia Spa Gruppo bruciatore, camera di combustione comprendente detto gruppo bruciatore e metodo per alimentare detto gruppo bruciatore
EP1975513A3 (fr) * 2007-03-14 2015-05-20 Ansaldo Energia S.p.A. Brûleur à prémélange pour turbine à gaz, en particulier une microturbine
WO2016037966A1 (fr) * 2014-09-12 2016-03-17 Siemens Aktiengesellschaft Brûleur comprenant un oscillateur fluidique pour une turbine à gaz et turbine à gaz comprenant au moins un brûleur de ce type
EP3421885A1 (fr) * 2017-06-28 2019-01-02 MAN Diesel & Turbo SE Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement
CN109237514A (zh) * 2018-08-08 2019-01-18 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

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993010401A1 (fr) * 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP0747636A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Chambre de combustion avec faible émissions pour turbines à gaz industrielles
WO2000034715A1 (fr) * 1998-12-09 2000-06-15 Abb Alstom Power Uk Ltd. Modification de la dynamique de reaction de combustion
GB2348484A (en) * 1997-03-10 2000-10-04 Gen Electric Premixer for a combustion chamber
EP1067337A1 (fr) * 1999-07-07 2001-01-10 ROLLS-ROYCE plc Chambre de combustion avec injection étagée de combustible
US20010052229A1 (en) * 1998-02-10 2001-12-20 General Electric Company Burner with uniform fuel/air premixing for low emissions combustion
EP1172610A1 (fr) * 2000-07-13 2002-01-16 Mitsubishi Heavy Industries, Ltd. Buse d'alimentation en combustible pour une chambre de combustion de turbine à prémélange
US6490864B1 (en) * 1999-10-08 2002-12-10 Alstom (Switzerland) Ltd Burner with damper for attenuating thermo acoustic instabilities
EP1416226A2 (fr) * 2002-10-31 2004-05-06 General Electric Company Injecteur de carburant à impédance acoustique adaptée et ensemble injecteur de carburant - résonateur accordable

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993010401A1 (fr) * 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
EP0747636A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Chambre de combustion avec faible émissions pour turbines à gaz industrielles
GB2348484A (en) * 1997-03-10 2000-10-04 Gen Electric Premixer for a combustion chamber
US20010052229A1 (en) * 1998-02-10 2001-12-20 General Electric Company Burner with uniform fuel/air premixing for low emissions combustion
WO2000034715A1 (fr) * 1998-12-09 2000-06-15 Abb Alstom Power Uk Ltd. Modification de la dynamique de reaction de combustion
EP1067337A1 (fr) * 1999-07-07 2001-01-10 ROLLS-ROYCE plc Chambre de combustion avec injection étagée de combustible
US6490864B1 (en) * 1999-10-08 2002-12-10 Alstom (Switzerland) Ltd Burner with damper for attenuating thermo acoustic instabilities
EP1172610A1 (fr) * 2000-07-13 2002-01-16 Mitsubishi Heavy Industries, Ltd. Buse d'alimentation en combustible pour une chambre de combustion de turbine à prémélange
EP1416226A2 (fr) * 2002-10-31 2004-05-06 General Electric Company Injecteur de carburant à impédance acoustique adaptée et ensemble injecteur de carburant - résonateur accordable

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1975513A3 (fr) * 2007-03-14 2015-05-20 Ansaldo Energia S.p.A. Brûleur à prémélange pour turbine à gaz, en particulier une microturbine
CN102906500B (zh) * 2009-08-26 2016-03-09 西门子公司 扰流叶片、燃烧器和燃气轮机
CN102597631A (zh) * 2009-08-26 2012-07-18 西门子公司 尤其用于燃气轮机的燃烧器
RU2536465C2 (ru) * 2009-08-26 2014-12-27 Сименс Акциенгезелльшафт Горелка, в частности, для газовых турбин
WO2011023648A3 (fr) * 2009-08-26 2012-11-15 Siemens Aktiengesellschaft Aube de turbulence, brûleur et turbine à gaz
CN102597631B (zh) * 2009-08-26 2014-08-13 西门子公司 尤其用于燃气轮机的燃烧器
RU2535433C2 (ru) * 2009-08-26 2014-12-10 Сименс Акциенгезелльшафт Направляющая лопатка, горелка и газовая турбина
WO2011023669A1 (fr) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brûleur notamment destiné à des turbines à gaz
CN102906500A (zh) * 2009-08-26 2013-01-30 西门子公司 扰流叶片、燃烧器和燃气轮机
WO2014074369A1 (fr) * 2012-11-07 2014-05-15 Siemens Aktiengesellschaft Système d'insonorisation pour une chambre de combustion d'un moteur à turbine à gaz
CN104769361A (zh) * 2012-11-07 2015-07-08 西门子公司 用于燃气轮机发动机的燃烧器的声阻尼系统
WO2014097153A1 (fr) * 2012-12-17 2014-06-26 Ansaldo Energia S.P.A. Ensemble brûleur, chambre de combustion comprenant ledit ensemble brûleur et procédé pour fournir du carburant audit ensemble brûleur
CN105102894B (zh) * 2012-12-17 2017-07-11 安萨尔多能源公司 燃烧器组件、包括所述燃烧器组件的燃烧室以及将燃料供应到所述燃烧器组件的方法
ITMI20122154A1 (it) * 2012-12-17 2014-06-18 Ansaldo Energia Spa Gruppo bruciatore, camera di combustione comprendente detto gruppo bruciatore e metodo per alimentare detto gruppo bruciatore
WO2016037966A1 (fr) * 2014-09-12 2016-03-17 Siemens Aktiengesellschaft Brûleur comprenant un oscillateur fluidique pour une turbine à gaz et turbine à gaz comprenant au moins un brûleur de ce type
EP3421885A1 (fr) * 2017-06-28 2019-01-02 MAN Diesel & Turbo SE Chambre de combustion d'une turbine à gaz, turbine à gaz et son procédé de fonctionnement
DE102017114362A1 (de) * 2017-06-28 2019-01-03 Man Diesel & Turbo Se Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben
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
CN109237514A (zh) * 2018-08-08 2019-01-18 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

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