EP2244015A1 - Brûleur à prémélange - Google Patents

Brûleur à prémélange Download PDF

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Publication number
EP2244015A1
EP2244015A1 EP09158558A EP09158558A EP2244015A1 EP 2244015 A1 EP2244015 A1 EP 2244015A1 EP 09158558 A EP09158558 A EP 09158558A EP 09158558 A EP09158558 A EP 09158558A EP 2244015 A1 EP2244015 A1 EP 2244015A1
Authority
EP
European Patent Office
Prior art keywords
pilot
pilot gas
channel
burner
gas
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Withdrawn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
EP09158558A
Other languages
German (de)
English (en)
Inventor
Siegfried Bode
Thomas Kunadt
Alexander Rambach
Peter Schaap
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 EP09158558A priority Critical patent/EP2244015A1/fr
Priority to RU2011147468/06A priority patent/RU2551462C2/ru
Priority to CN201080017830.5A priority patent/CN102414514B/zh
Priority to EP10702659A priority patent/EP2422136B1/fr
Priority to PCT/EP2010/051104 priority patent/WO2010121845A1/fr
Publication of EP2244015A1 publication Critical patent/EP2244015A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion

Definitions

  • the present invention relates to a premix burner having a pilot burner and an igniter.
  • Premix burners are primarily used to prevent the formation of so-called hotspots in the flame, i. the emergence of flame inhomogeneities with very hot flame areas to avoid.
  • the aim here is to reduce the NOx emissions resulting from combustion.
  • the production of NOx increases exponentially with the flame temperature. A reduction in the peak temperature (hotspots) of the flame temperature therefore leads to a reduction in NOx production.
  • a premix flame To minimize the temperature of a premix flame, it is often operated with a lean fuel-air mixture at the limit of stability, i. In comparison to the combustion air, so little fuel is added that a mixture that is just ignitable is formed.
  • lean mixtures can lead to instabilities in the premix flame which, as a result, induce pressure oscillations in the combustion system.
  • a pilot burner In order to stabilize the premixed flame of a lean mixture, therefore, a pilot burner is used which operates as a diffusion burner, i. the fuel and the combustion air are fed to the flame without being intensively mixed beforehand.
  • the proportion of the pilot fuel at the total amount of fuel to the burner is about 5 to 10%.
  • the pilot burner may also be used to ignite the flame.
  • Hybrid burners which comprise both a premix burner and a diffusion burner.
  • Premix burner is arranged concentrically around the diffusion burner.
  • the diffusion burner also includes a pilot fuel supply to use it as a pilot burner can.
  • the EP 1 712 837 A1 describes a burner, which from the basic structure forth in DE 197 57 617 A1 and WO 00/12933 similar burners described. However, there are no separate supply channels for diffusion gas, ie gas, which is used for the diffusion operation of the burner, and pilot gas, so gas, which is used to operate the pilot burner, available. Instead, both the diffusion gas and the pilot gas may be supplied through the same fuel supply passage (s). In this way, a gas supply system can be saved.
  • the pilot flame is ignited via the flame of the diffusion burner. This can therefore be done so that a diffusion burner is usually operated to start a gas turbine and the pilot burner only then when it is transferred to the premixing of the burner is needed.
  • a pilot burner is usually still available, with which the diffusion gas is ignited.
  • Such a pilot burner is for example in EP 0 193 838 B1 described. If now, as in EP 1 712 837 A1 described, only a common fuel supply system for the diffusion gas and the pilot gas is present, a suitable ignition device is necessary because the pilot burner, as it is used in conventional hybrid burners, this is not readily suitable.
  • a premix burner according to the invention comprises an air supply channel, a pilot gas supply channel which has at least one channel wall facing the pilot supply channel and a pilot gas outlet end opening into the air supply channel, and an ignition element upstream of the pilot gas outlet end in the air supply channel, which can be designed, for example, as a two-pole ignition electrode.
  • an ignition element upstream of the pilot gas outlet end in the air supply channel, which can be designed, for example, as a two-pole ignition electrode.
  • the inventive design of the premix burner allows a direct ignition of the pilot gas, d. H. without first having to ignite a diffusion flame which is supplied via its own diffusion gas channel and without its own ignition burner only having to be used for the purpose of ignition with an associated ignition gas channel.
  • pilot gas can escape from the at least one gas outlet opening in the air supply channel and form there together with the air an ignitable mixture, which flows past the ignition element located downstream.
  • the burner can therefore be simplified overall design, since fewer gas strands are necessary, resulting in a cost reduction in the manufacture of the burner.
  • the pilot gas supply channel preferably has a flow resistance downstream of the at least one gas outlet opening.
  • the flow resistance leads in the upstream gas to a pressure increase, which ensures that sufficient gas for forming an ignitable mixture in the region of the ignition element emerges through the gas outlet opening in the air supply channel.
  • the flow resistance for example, by a constriction, in particular be realized by a constriction at the pilot gas outlet end of the pilot gas supply channel.
  • a structurally simple way to realize the constriction is to arrange a arranged on the channel wall and inwardly directed projection in the interior of the channel.
  • Another possibility is to introduce an obstacle body in the pilot gas supply channel.
  • Such a body could be, for example, an aerodynamically shaped body, a grid, a mesh, etc.
  • the duct wall upstream of the ignition element may have at least two gas outlet openings offset in the flow direction. In this way, the amount of exiting pilot gas can be increased without increasing the opening cross-sections of the gas outlet openings, and thus their aerodynamics would have to be changed.
  • the pilot gas supply channel is designed as a pilot gas pipe, which is guided through an interior of the burner and which exits at an exit point located to the ignition element from the interior and projects into the air supply channel.
  • the tube wall in this case forms the channel wall, and the at least one gas outlet opening is arranged in the projecting into the air supply passage portion of the pilot gas tube.
  • Fig. 1 shows a burner according to the invention in a schematic sectional view.
  • Fig. 2 shows a pilot gas pipe with gas outlet openings arranged therein.
  • Fig. 3 shows the pilot gas pipe Fig. 2 in a section along the line III-III.
  • Fig. 4 shows the projecting into the air passage portion of the pilot gas tube in a section along its longitudinal axis.
  • Fig. 5 shows the outlet end of a second variant of the pilot gas tube.
  • Fig. 6 shows the outlet end of a third variant of the pilot gas tube.
  • Fig. 7 shows the outlet end of a fourth variant of the pilot gas tube.
  • Fig. 8 shows the outlet end of a fifth variant of the pilot gas tube.
  • Fig. 9 shows the outlet end of a sixth variant of the pilot gas tube.
  • the burner 1 is essentially rotationally symmetrical about a burner axis A with a burner output 9 which is open towards a combustion chamber 7. It has a central burner lance 13, which has a supply channel for liquid fuels and at its combustion chamber side end 15 has one or more atomizing nozzles for injecting a liquid fuel into the flame prevailing in the combustion chamber 7 flame.
  • the burner lance 13 then serves to generate a liquid fuel fed with a diffusion flame. If the burner is designed solely for general operation with gaseous fuels, instead of the described burner lance 13, a dummy is used which in its outer geometry is similar to the burner lance described, but without the atomizing nozzles at the combustion chamber end 15.
  • the annular space 19 serves to supply fuel gas into an air supply passage 21 through which the air necessary for maintaining the flame is supplied to the burner 1.
  • the annular space 19 has gas outlet openings 20.
  • the burner 1 so-called Axialgitter 30, which provide for a turbulence of the air and the fuel gas and thereby for intimate mixing of the two.
  • the intimately premixed air-fuel mixture is fed via the burner outlet 9 of the combustion chamber 7, where it is burned.
  • the premixed air-fuel mixture is made lean, that is, the amount of fuel in the mixture is kept as low as possible, thereby avoiding NOx-forming temperature spikes in the resulting premix flame.
  • a pilot flame unlike the premix flame as Diffusion flame operated, serves to stabilize the premix flame, which is operated close to the stability limit, in order to avoid the occurrence of pressure fluctuations in the combustion chamber due to combustion oscillations. In contrast to the premix flame, there is no intimate mixing of fuel and air in the diffusion flame before they are fed to the flame.
  • the pilot flame serves not only to stabilize the premix flame, but also to ignite the premix flame.
  • pilot gas tubes 23 are guided through the annular interior 19 between the cylindrical wall 17 and the burner lance 13 to the combustion chamber end of the interior 19. There, they pass through a substantially cone-shaped end wall 25 and protrude with a pipe section 27 into the air supply channel 21.
  • the combustor side ends 29 of the pilot gas tubes 23 are open and serve to inject pilot gas into the air flowing through the annular air supply passage 21.
  • In the air supply passage 21 also protrudes an igniter 31 with a two-pole ignition electrode 33 inside.
  • the tip 35 of the two-pole ignition electrode 33 which represents the actual ignition element of the burner 1, is located upstream of the open outlet ends 29 of the pilot gas tubes 23.
  • the two-pole ignition electrode 35 is located close to a pilot gas pipe. It should be noted that the tip 35 of the ignition electrode 32 does not necessarily have to be on the same radial line as one of the pilot gas tubes 23. It is only important that the tip 35 is brought close enough to one of the tubes 23.
  • the pilot gas tube 23 arranged in the vicinity of the igniter 31 is provided, in addition to the opening in the outlet end 29, with at least one gas outlet opening 37 situated upstream of the tube wall in the tube wall 29.
  • three gas outlet openings 37 a, 37 b, 37 c are provided, which are designed as offset in the axial direction of the tube 23 and in the circumferential direction of the tube 23 holes.
  • the arrangement of the holes are in the FIGS. 2 and 3 shown, where Fig. 2 a view of the holes in the pilot gas pipe 23 and Fig. 3 shows a section through the pipe wall 39 of the pilot gas pipe 23 along the line III-III.
  • the distribution of the bores 37a, 37b, 37c are chosen with a view to optimizing the distribution profile of the gas exiting through the bores 37.
  • the gas outlet openings 37 are arranged in the pilot gas tube 23 upstream of the electrode tip 35, i. Gas exiting from the gas outlet openings 37, which is injected into the air flowing through the air supply channel 21, flows along the electrode tip 35, so that the gas can be ignited by means of a spark.
  • a flow resistance is arranged in the pilot gas tube 23 downstream of the gas outlet openings. This leads to an increase in pressure upstream of the flow resistance, which ensures that sufficient pilot gas for a successful ignition through the gas outlet openings 37a, 37b, 37c in the air supply passage 21 exits.
  • FIG. 4 A detail view of the projecting into the air supply passage 21 section 27 of the pilot gas tube 23 is in Fig. 4 shown in an enlarged sectional view. In this view, only one of the extending through the pipe wall 39 gas outlet openings 37 can be seen.
  • a sleeve 41 is inserted into the pilot gas tube 23, which reduces the flow cross-section available to the pilot gas in the pilot gas tube 23 in the region of the outlet end 29. In this way the gas pressure upstream of the sleeve 41 is increased so far that sufficient pilot gas escapes through the gas outlet openings 37.
  • FIG. 5 An alternative variant for generating a flow resistance in the region of the outlet end 29 of the pilot gas tube 23 is in Fig. 5 shown.
  • the pilot gas tube 23 at the outlet end 29 a frustoconical wall portion 43, which causes the outlet opening 45 at the pilot gas outlet end 29 has a reduced compared to the flow cross-section of the pilot gas tube 23 opening cross-section. This also makes it possible to bring about a suitable pressure increase in the region upstream of the gas outlet openings 37.
  • FIG. 6 Another variant for introducing a flow resistance into the pilot gas pipe 23 is in Fig. 6 shown.
  • the pilot gas tube 23 has, shortly before the outlet end 29, a V-shaped recess 47 running around its circumference, which leads to a reduction of the flow cross-section available for the pilot gas in the region of the recess.
  • the reduction of the flow cross section in turn leads to a pressure increase upstream of the indentation 47.
  • Fig. 7 Another variant of the flow resistance is in Fig. 7 shown.
  • the pilot gas pipe 23 has an inwardly directed bead 49 which extends around the circumference of the pipe and leads to a reduction of the flow cross section available for the pilot gas and thus to an increase in pressure upstream of the bead 49, shortly before the pilot gas exit end 29.
  • FIG. 8 Yet another variant of the flow resistance is in Fig. 8 shown.
  • the pipe wall 39 is cylindrical up to the pilot gas exit end 29.
  • the pressure-increasing reduction of the flow cross-section in the pilot gas pipe 23 is effected by an aerodynamically shaped Insert 51, which is secured by means of struts 53 on the inside of the tube wall 39.
  • the attachment can be done by means of a braze or a welded joint.
  • it is also possible to fix the struts by means of a screw connection to the tube wall 39.
  • pilot gas tube 23 has up to its pilot gas outlet end 29 a cylindrical tube wall 39. Shortly before the pilot gas outlet end 29 or directly at the pilot exit end 29, a grid 55 is inserted into the pilot gas tube 23, which constitutes a flow obstacle for the pilot gas flowing through the pilot gas tube 23 and thus leads to an increase in pressure upstream of the grid 55.
  • the invention described with reference to the embodiment makes it possible for a burner in which the pilot burner has only pilot gas supply channels as the only gas supply channels to cause ignition of the burner without specially available and own fuel supply having pilot burner.
  • the burner according to the invention therefore comes with only two gas supply systems, namely the supply system for the pilot gas and the supply system for the gas in premixing from. A reduction in the complexity of the burner and the associated production costs is the result.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP09158558A 2009-04-23 2009-04-23 Brûleur à prémélange Withdrawn EP2244015A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP09158558A EP2244015A1 (fr) 2009-04-23 2009-04-23 Brûleur à prémélange
RU2011147468/06A RU2551462C2 (ru) 2009-04-23 2010-01-29 Горелка предварительного смешения
CN201080017830.5A CN102414514B (zh) 2009-04-23 2010-01-29 预混合燃烧器
EP10702659A EP2422136B1 (fr) 2009-04-23 2010-01-29 Brûleur à prémélange
PCT/EP2010/051104 WO2010121845A1 (fr) 2009-04-23 2010-01-29 Brûleur à prémélange

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09158558A EP2244015A1 (fr) 2009-04-23 2009-04-23 Brûleur à prémélange

Publications (1)

Publication Number Publication Date
EP2244015A1 true EP2244015A1 (fr) 2010-10-27

Family

ID=41036755

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09158558A Withdrawn EP2244015A1 (fr) 2009-04-23 2009-04-23 Brûleur à prémélange
EP10702659A Active EP2422136B1 (fr) 2009-04-23 2010-01-29 Brûleur à prémélange

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10702659A Active EP2422136B1 (fr) 2009-04-23 2010-01-29 Brûleur à prémélange

Country Status (4)

Country Link
EP (2) EP2244015A1 (fr)
CN (1) CN102414514B (fr)
RU (1) RU2551462C2 (fr)
WO (1) WO2010121845A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102901098A (zh) * 2012-10-23 2013-01-30 江苏中圣高科技产业有限公司 地面火炬多头高效预混型燃烧系统

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0193838B1 (fr) 1985-03-04 1989-05-03 Siemens Aktiengesellschaft Disposition de brûleur pour installations de combustion, en particulier pour chambres de combustion d'installations de turbines à gaz ainsi que procédé de sa mise en oeuvre
DE19757617A1 (de) 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
WO2000012933A1 (fr) 1998-08-26 2000-03-09 Siemens Aktiengesellschaft Bruleur hybride et procede permettant de le faire fonctionner
US20020132203A1 (en) * 2001-03-19 2002-09-19 Alstom (Schweiz) Ag Gas pipe ignitor
EP1596131A2 (fr) * 2004-05-13 2005-11-16 Ansaldo Energia S.P.A. Méthode de contrôle d'une chambre de combustion de turbine à gaz utilisant du combustible gazeux
EP1614967A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP1710502A2 (fr) * 2005-03-30 2006-10-11 Ansaldo Energia S.P.A. Ensemble brûleur à gaz de turbine à gaz
EP1712837A1 (fr) 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Ensamble brûleur et son procédé d'utilisation
WO2009032793A1 (fr) * 2007-09-06 2009-03-12 Coen Company, Inc. Pilote de brûleur avec rotor virtuel

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1502910A1 (ru) * 1987-12-18 1989-08-23 Предприятие "Средазтехэнерго" Производственного Объединения По Наладке, Совершенствованию И Эксплуатации Электростанций И Сетей "Союзтехэнерго" Запальна горелка

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0193838B1 (fr) 1985-03-04 1989-05-03 Siemens Aktiengesellschaft Disposition de brûleur pour installations de combustion, en particulier pour chambres de combustion d'installations de turbines à gaz ainsi que procédé de sa mise en oeuvre
DE19757617A1 (de) 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
WO2000012933A1 (fr) 1998-08-26 2000-03-09 Siemens Aktiengesellschaft Bruleur hybride et procede permettant de le faire fonctionner
US20020132203A1 (en) * 2001-03-19 2002-09-19 Alstom (Schweiz) Ag Gas pipe ignitor
EP1596131A2 (fr) * 2004-05-13 2005-11-16 Ansaldo Energia S.P.A. Méthode de contrôle d'une chambre de combustion de turbine à gaz utilisant du combustible gazeux
EP1614967A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP1710502A2 (fr) * 2005-03-30 2006-10-11 Ansaldo Energia S.P.A. Ensemble brûleur à gaz de turbine à gaz
EP1712837A1 (fr) 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Ensamble brûleur et son procédé d'utilisation
WO2009032793A1 (fr) * 2007-09-06 2009-03-12 Coen Company, Inc. Pilote de brûleur avec rotor virtuel

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
STREB H ET AL: "REDUKTION VON BRENNKAMMERSCHWINGUNGEN DURCH EINE VERAENDERTE ZUGABE DES PILOTGASES", SIEMENS TECHNIK REPORT, SIEMENS AG.,ERLANGEN, AT, vol. 2, no. 3, 1 April 1999 (1999-04-01), pages 85 - 89, XP000822891, ISSN: 1436-7777 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102901098A (zh) * 2012-10-23 2013-01-30 江苏中圣高科技产业有限公司 地面火炬多头高效预混型燃烧系统
CN102901098B (zh) * 2012-10-23 2015-10-07 江苏中圣高科技产业有限公司 地面火炬多头高效预混型燃烧系统

Also Published As

Publication number Publication date
RU2011147468A (ru) 2013-05-27
EP2422136A1 (fr) 2012-02-29
WO2010121845A1 (fr) 2010-10-28
CN102414514B (zh) 2014-08-20
CN102414514A (zh) 2012-04-11
RU2551462C2 (ru) 2015-05-27
EP2422136B1 (fr) 2013-04-03

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