EP1624252A1 - Brûleur, turbine à gaz et procédé opératoire pour un brûleur - Google Patents

Brûleur, turbine à gaz et procédé opératoire pour un brûleur Download PDF

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Publication number
EP1624252A1
EP1624252A1 EP04018727A EP04018727A EP1624252A1 EP 1624252 A1 EP1624252 A1 EP 1624252A1 EP 04018727 A EP04018727 A EP 04018727A EP 04018727 A EP04018727 A EP 04018727A EP 1624252 A1 EP1624252 A1 EP 1624252A1
Authority
EP
European Patent Office
Prior art keywords
fuel
channel
burner
shear layer
air mixture
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Withdrawn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
EP04018727A
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German (de)
English (en)
Inventor
Malte Dr. Blomeyer
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 EP04018727A priority Critical patent/EP1624252A1/fr
Priority to PCT/EP2005/053821 priority patent/WO2006015968A1/fr
Publication of EP1624252A1 publication Critical patent/EP1624252A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • 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
    • F23C2900/06043—Burner staging, i.e. radially stratified flame core burners
    • 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 invention relates to a burner with a first and a second channel for guiding a fuel-air mixture.
  • the invention also relates to a method for operating such a burner and to a gas turbine with such a burner.
  • a burner for a furnace, in particular a gas turbine combustion chamber is known from DE 198 39 085 C2.
  • This burner has a central diffusion burner, in which fuel is added to the combustion air and this is burned in a combustion zone. The addition of the fuel takes place without a larger mixing section in the flow before the combustion zone.
  • the annular channel premix burner surrounding this central diffusion burner has an intensive premix of fuel with combustion air before this fuel / air mixture is also burned in the combustion zone.
  • the advantage of such a premix burner is the homogeneous mixture of fuel and combustion air before combustion. Such homogeneous mixing is particularly important in view of a low nitrogen oxide emission, since the nitrogen oxide formation increases exponentially with the flame temperature, with higher flame temperatures occurring in regions of higher fuel concentration.
  • the nitrogen oxide emission is essentially determined by the regions of higher fuel concentration.
  • Low nitrogen oxide emissions are also achieved in the premix burner by a comparatively low fuel concentration, ie it is burned a comparatively lean mixture.
  • flame instabilities are the starting point of combustion oscillations.
  • Stabilization of lean premix combustion is achieved by the central diffusion burner, which is less prone to combustion instabilities, but at the same time is responsible for higher nitrogen oxide concentrations due to a locally richer combustion mixture.
  • Edge flows may be particularly susceptible to fuel density fluctuations and thus the source of combustion instabilities.
  • EP 0 870 898 A2 it is known to vary the fuel concentration over the circumference of a fuel channel. By depleting the concentration level of fuel in an instability prone boundary zone, the risk of forming combustion instability from that edge zone is reduced because ignitability is reduced by leanness.
  • this inhomogeneous fuel addition has the consequence that no homogeneous fuel-air mixture is present, with the disadvantages described above with respect to the nitrogen oxide emissions.
  • Another possibility for influencing such edge zones is known from WO 97/11383 A2.
  • a radially outer flow region is retarded in an annular channel of a premixing burner with respect to the main flow.
  • the object of the invention is to provide a burner with particularly favorable properties in terms of low susceptibility to combustion oscillations and at the same time low nitrogen oxide emissions.
  • Another object of the invention is the disclosure of a method for operating a burner and the specification of a gas turbine.
  • the object directed to a burner is achieved by specifying a burner with a first channel for guiding a first fuel / air mixture and a second channel for guiding a second fuel / air mixture, wherein the first and the second fuel / air mixture for combustion in a Combustion zone are merged to form a flow shear layer, wherein the first and the second channel are separated from each other by a partition and wherein the partition has openings such that a partial exchange of mass and fuel concentration between the first and the second fuel / air mixture is formed.
  • the flow shear layer between two fuel / air mixture streams converged for combustion can be the starting point for combustion instabilities, since in such a flow shear layer transverse flows due to the shear forces can lead to an oscillation of this flow shear layer.
  • the resulting density and concentration fluctuations can now lead to the build-up of a combustion vibration during combustion.
  • the two fuel / air mixture streams to be merged can already partially exchange mass and fuel concentration via openings in a dividing wall, resulting in a less discrete and discontinuous flow shear layer. This is less susceptible to combustion oscillations.
  • the exchange of mass across transverse flows through the openings also inevitably results in an energy and momentum compensation and thus an alignment of energy and momentum of the two fuel / air mixture streams. This in turn leads to a reduction of the shear forces in the downstream forming shear layer.
  • the openings are dimensioned so that it comes through the exchange of mass to a thickening of the flow shear layer.
  • the number and size of the openings are thus adjusted so that the flow shear layer has a substantially greater thickness than a partition wall without openings. More preferably, the number and size of the openings are configured to at least double the flow shear layer thickness. In such a thickened flow shear layer, any occurring oscillations and fuel and density fluctuations are attenuated much faster than in a thinner flow shear layer. This in turn has a low susceptibility to combustion vibrations.
  • the fuel concentration over the cross section of the first and the second channel is each substantially homogeneous. Due to the instabilities in the flow shear layer, the susceptibility to combustion vibrations due to instabilities in the flow shear layer is reduced to such an extent that the emaciation of the fuel / air mixture in this zone is no longer or only marginally necessary. The thus adjustable homogeneity of the fuel concentration nitrogen oxide emissions can be reduced.
  • the second channel is annular in cross-section and surrounds the first channel.
  • the first channel is furthermore preferably a diffusion burner channel and the second channel is a premix burner channel.
  • the burner is designed as a gas turbine burner. Especially in a gas turbine combustion instabilities can lead to significant problems due to the very large power releases. Normally, ring-shaped premix burners are used in gas turbine burners, which are stabilized via a central diffusion burner. When merging the fuel gas streams, it comes to the formation of a flow shear layer described above with the disadvantageous Effects on susceptibility to combustion vibrations.
  • the object directed to a gas turbine is achieved by specifying a gas turbine with a burner according to one of the embodiments described above.
  • the object directed to a method is achieved according to the invention by specifying a method for operating a burner in which a first fuel / air mixture and a second fuel / air mixture are combined to form a flow shear layer in a combustion zone and burned there, wherein prior to the combination of the mixtures a partial exchange of mass and fuel concentration between the mixtures takes place in the flow shear layer.
  • the exchange of mass and fuel concentration over a perforated partition occurs immediately upstream of the formation of the flow shear layer.
  • the flow shear layer is widened by the exchange so that there is an attenuation for Brennstoff Whyfluktuationen in the flow shear layer.
  • the gas turbine 1 shows a gas turbine 1.
  • the gas turbine 1 has a compressor 3, a combustion chamber 5 and a turbine part 7.
  • In the combustion chamber 5 opens a burner 9.
  • combustion air 10 is sucked into the compressor 3 and there highly compressed.
  • the combustion air 10 is then supplied to the burner 9, as well as fuel 13.
  • the fuel / air mixture 11 produced in the burner 9 is burned.
  • a hot gas 15 produced by the combustion is then passed through the turbine part 7, driving the gas turbine 1.
  • FIG. 2 shows a longitudinal section of a gas turbine burner 9.
  • the gas turbine burner 9 has a first channel 23 which, as an inner annular channel, carries a fuel / air mixture 11 consisting of combustion air 10 and fuel 13. Fuel 13 may also be via a central fuel nozzle 25, be introduced in particular for an oil injection, while upstream of the first channel 23 preferably fuel gas is introduced as fuel.
  • the first channel 23 is surrounded by a likewise annular second channel 21.
  • the second channel 21 is designed as a premixing channel, in which fuel 13 is added to the combustion air 10 via inlet tubes 27. In a swirl grille 29, the fuel / air mixture 11 is imparted a twist.
  • the fuel / air mixture 11B homogenizes in the second channel 21 before it exits into the combustion zone 31.
  • a flow shear layer 33 is formed.
  • This flow shear layer 33 is formed downstream of a partition wall 35, which separates the first channel 23 and the second channel 21 immediately upstream of the combustion zone 31. Due to the differences in momentum, energy and fuel concentration of the respective fuel / air mixtures 11A, 11B from the first channel 23 and the second channel 21, fluctuations are formed in the flow shear layer 33. These fluctuations can be the starting point for combustion oscillations.
  • the partition wall 35 is provided with through openings which allow an exchange of mass and fuel concentration between the fuel / air mixtures 11A, 11B in the first channel 23 and second channel 21. This will be described in detail with reference to the following figures.
  • FIG. 3 shows the inner part of the gas turbine burner 9 from FIG. 2 in a view. Shown is the first channel 23 and the surrounding partition wall 35. Visible is a swirl lattice 41, which serves to impress a swirl for the fuel / air mixture 11A in the first channel 23. In contrast to the swirl lattice 29 of the second channel 21, which is not shown here, the combustion zone 31 connects downstream of the swirl lattice 41, while the swirl lattice 29 of the first channel 21 is still followed by a mixing section. The partition wall 35 is now provided with openings 37. The partition wall 35 is therefore executed perforated.
  • the openings 37 may also be formed with a significant length as channels. These channels are preferably aligned perpendicular to the flow direction on the partition, but may also be inclined relative to the flow direction. Preferably, an inclination is such that fuel / air mixture 11B is conducted from the premix channel 21 into the first channel 23, but there is virtually no replacement in this direction due to an upstream inclination of the openings 37 with respect to the flow from the first channel 23 to the second channel 21 , Accordingly, a tilt in the opposite direction may be suitable. This is shown in FIG.
  • FIG. 4 shows the effect of the perforation of the partition wall 35.
  • a transverse flow 39 is formed between the first channel 23 and the second channel 21.
  • this essentially leads to a flow from the second channel 21 to the first channel 23.
  • Downstream of the partition 35 forms when merging the two fuel / air mixture flows 11A, 11B from the first channel 23 and second channel 21 a Flow shear layer 33 from. Shaped, a flow shear layer 33A is shown as it would appear without the openings 37 in the dividing wall 35. Without the openings 37 and thus the cross-flows 39, the two fuel / air mixtures 11A, 11B meet for the first time downstream of the dividing wall 35 with their differences in mass, energy, momentum and fuel concentration.
  • the partial exchange achieved between the fuel / air mixtures 11A, 11B in the first channel 23 and the second channel is achieved by the upstream of the actual merging with the openings 37, which is formed comparatively thin flow shear layer 33A 21 reaches a thickening of the flow shear layer 33.
  • the fuel / air mixtures 11A, 11B have already become equal in part to both energy and momentum as well as fuel concentration.
  • the forming flow shear layer 33 is thereby thickened and presents a softened and no longer as sharp discontinuity. This results in a significant reduction in fluctuations, i. Oscillations are attenuated much faster than would be the case without a perforated partition 35. This in turn has a low susceptibility to the formation of combustion vibrations result.
  • FIG. 5 shows a further possibility of designing the perforated dividing wall 35 between the fuel / air mixtures 11A, 11B in the first channel 23 and in the second channel 21.
  • the partition 35 is provided with channel-like and in the flow direction of the fuel / air mixtures 11A, 11B inclined openings 39.
  • fuel gas is introduced as fuel.
  • the second channel 21 is formed as a premixing channel in which a fuel / air mixture 11B is generated.
  • the non-premixed fuel gas from the first channel 23 flows through the inclined openings 39 into the second channel 21, the premix channel, so that non-premixed fuel flows over to the already premixed fuel / air mixture 11B. Due to the inclination of the openings 39, this overflow is favored, so that the desired exchange of mass and fuel concentration between the first and the second fuel / air mixture 11A / 11B is achieved.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP04018727A 2004-08-06 2004-08-06 Brûleur, turbine à gaz et procédé opératoire pour un brûleur Withdrawn EP1624252A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04018727A EP1624252A1 (fr) 2004-08-06 2004-08-06 Brûleur, turbine à gaz et procédé opératoire pour un brûleur
PCT/EP2005/053821 WO2006015968A1 (fr) 2004-08-06 2005-08-04 Bruleur, turbine a gaz et fonctionnement du bruleur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04018727A EP1624252A1 (fr) 2004-08-06 2004-08-06 Brûleur, turbine à gaz et procédé opératoire pour un brûleur

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EP1624252A1 true EP1624252A1 (fr) 2006-02-08

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EP04018727A Withdrawn EP1624252A1 (fr) 2004-08-06 2004-08-06 Brûleur, turbine à gaz et procédé opératoire pour un brûleur

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WO (1) WO2006015968A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015040228A1 (fr) * 2013-09-23 2015-03-26 Siemens Aktiengesellschaft Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100504175C (zh) * 2006-04-13 2009-06-24 中国科学院工程热物理研究所 燃气轮机低热值燃烧室喷嘴结构与燃烧方法
DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999004196A1 (fr) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz
WO1999017057A1 (fr) * 1997-09-30 1999-04-08 Siemens Westinghouse Power Corporation CHAMBRE DE COMBUSTION A TRES FAIBLE EMISSION DE NO¿x?
DE19839085A1 (de) * 1998-08-27 2000-03-02 Siemens Ag Brenneranordnung mit primärem und sekundärem Pilotbrenner
DE10104695A1 (de) * 2001-02-02 2002-08-08 Alstom Switzerland Ltd Vormischbrenner sowie Verfahren zum Betrieb eines derartigen Vormischbrenners

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999004196A1 (fr) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz
WO1999017057A1 (fr) * 1997-09-30 1999-04-08 Siemens Westinghouse Power Corporation CHAMBRE DE COMBUSTION A TRES FAIBLE EMISSION DE NO¿x?
DE19839085A1 (de) * 1998-08-27 2000-03-02 Siemens Ag Brenneranordnung mit primärem und sekundärem Pilotbrenner
DE10104695A1 (de) * 2001-02-02 2002-08-08 Alstom Switzerland Ltd Vormischbrenner sowie Verfahren zum Betrieb eines derartigen Vormischbrenners

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015040228A1 (fr) * 2013-09-23 2015-03-26 Siemens Aktiengesellschaft Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz
CN105393057A (zh) * 2013-09-23 2016-03-09 西门子股份公司 用于燃气涡轮机的燃烧器和用于减少燃气涡轮机中的热声振荡的方法
CN105393057B (zh) * 2013-09-23 2017-06-30 西门子股份公司 用于燃气涡轮机的燃烧器和用于减少燃气涡轮机中的热声振荡的方法

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