EP2422136B1 - Pre-mix burner - Google Patents

Pre-mix burner Download PDF

Info

Publication number
EP2422136B1
EP2422136B1 EP10702659A EP10702659A EP2422136B1 EP 2422136 B1 EP2422136 B1 EP 2422136B1 EP 10702659 A EP10702659 A EP 10702659A EP 10702659 A EP10702659 A EP 10702659A EP 2422136 B1 EP2422136 B1 EP 2422136B1
Authority
EP
European Patent Office
Prior art keywords
pilot
burner
pilot gas
passage
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.)
Active
Application number
EP10702659A
Other languages
German (de)
French (fr)
Other versions
EP2422136A1 (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 EP10702659A priority Critical patent/EP2422136B1/en
Publication of EP2422136A1 publication Critical patent/EP2422136A1/en
Application granted granted Critical
Publication of EP2422136B1 publication Critical patent/EP2422136B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/34—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.
  • the premix burner is concentric around the diffusion burner arranged around.
  • 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 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 pilot gas supply channel is designed as a pilot gas tube, which is guided through an interior of the burner and which exits from the interior at an exit point located to the ignition element 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.
  • the channel wall may have upstream of the ignition element 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 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 outlet 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.

Description

Die vorliegende Erfindung betrifft einen Vormischbrenner, welcher einen Pilotbrenner und einen Zünder aufweist.The present invention relates to a premix burner having a pilot burner and an igniter.

Vormischbrenner werden in erster Linie dazu verwendet, das Entstehen sogenannter Hotspots in der Flamme, d.h. das Entstehen von Flammeninhomogenitäten mit sehr heißen Flammenbereichen, zu vermeiden. Ziel ist es hierbei, die bei der Verbrennung entstehenden NOx-Emissionen zu verringern. Die Produktion von NOx steigt exponentiell mit der Flammentemperatur. Eine Verringerung von Spitzenwerten (Hotspots) der Flammentemperatur führt daher zu einer Verminderung der NOx-Produktion.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.

Um die Temperatur einer Vormischflamme möglichst gering zu halten, wird diese häufig mit einem mageren Brennstoff-LuftGemisch an der Grenze der Stabilität betrieben, d.h. es wird im Verhältnis zur Verbrennungsluft so wenig Brennstoff beigemischt, dass ein gerade noch zündfähiges Gemisch entsteht. Derart magere Gemische können jedoch zu Instabilitäten in der Vormischflamme führen, die im Ergebnis Druckschwingungen im Verbrennungssystem induzieren. Um die Vormischflamme eines mageren Gemisches zu stabilisieren, findet daher ein Pilotbrenner Verwendung, der als Diffusionsbrenner betrieben wird, d.h. der Brennstoff und die Verbrennungsluft werden ohne vorher intensiv vermischt zu werden, der Flamme zugeführt. Der Anteil des Pilotbrennstoffes an der dem Brenner insgesamten Brennstoffmenge beträgt ca. 5 bis 10 %. Außer zum Stabilisieren der Vormischflamme kann der Pilotbrenner auch zum Zünden der Flamme zur Anwendung kommen.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. However, such lean mixtures can lead to instabilities in the premix flame which, as a result, induce pressure oscillations in the combustion system. 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%. In addition to stabilizing the premix flame, the pilot burner may also be used to ignite the flame.

Dokumente EP1596 131 und WO 2009/032973 offenbaren auch einen Vormischbrenner.Documents EP1596 131 and WO 2009/032973 also disclose a premix burner.

In DE 197 57 617 A1 und WO 00/12933 sind sogenannte Hybridbrenner beschrieben, die sowohl einen Vormischbrenner, als auch einen Diffusionsbrenner umfassen. Der Vormischbrenner ist konzentrisch um den Diffusionsbrenner herum angeordnet. Der Diffusionsbrenner umfasst zudem auch eine Pilotbrennstoffzufuhr, um ihn als Pilotbrenner einsetzen zu können.In DE 197 57 617 A1 and WO 00/12933 Hybrid burners are described which comprise both a premix burner and a diffusion burner. The premix burner is concentric around the diffusion burner arranged around. The diffusion burner also includes a pilot fuel supply to use it as a pilot burner can.

Die EP 1 712 837 A1 beschreibt einen Brenner, welcher vom Grundaufbau her den in DE 197 57 617 A1 und WO 00/12933 beschriebenen Brennern gleicht. Jedoch sind keine getrennten Zufuhrkanäle für Diffusionsgas, also Gas, welches zum Diffusionsbetrieb des Brenners Verwendung findet, und Pilotgas, also Gas, welches zum Betreiben des Pilotbrenners Verwendung findet, vorhanden. Statt dessen können sowohl das Diffusionsgas als auch das Pilotgas durch denselben Brennstoffzufuhrkanal bzw. dieselben Brennstoffzufuhrkanäle zugeführt werden. Auf diese Weise kann ein Gaszufuhrsystem eingespart werden.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.

Üblicherweise wird die Pilotflamme über die Flamme des Diffusionsbrenners gezündet. Dies kann deshalb so erfolgen, da ein Diffusionsbrenner in der Regel zum Anfahren einer Gasturbine betrieben wird und der Pilotbrenner erst anschließend, wenn zum Vormischbetrieb des Brenners übergegangen wird, benötigt wird. Hierzu ist in der Regel noch ein Zündbrenner vorhanden, mit dem das Diffusionsgas gezündet wird. Ein derartiger Zündbrenner ist beispielsweise in EP 0 193 838 B1 beschrieben. Wenn nun, wie in EP 1 712 837 A1 beschrieben, lediglich ein gemeinsames Brennstoffzufuhrsystem für das Diffusionsgas und das Pilotgas vorhanden ist, ist eine geeignete Zündvorrichtung notwendig, da der Zündbrenner, wie er in üblichen Hybridbrennern Verwendung findet, hierzu nicht ohne weiteres geeignet ist.Usually, 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. For this purpose, 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.

Es ist daher Aufgabe der vorliegenden Erfindung, einen Brenner ohne eigene Diffusionsgaszufuhr zur Verfügung zu stellen, welcher eine Zündanordnung aufweist, die das Vorhandensein eines eigenen Zündbrenners überflüssig macht.It is therefore an object of the present invention to provide a burner without its own diffusion gas supply, which has an ignition arrangement which renders the existence of a separate pilot burner superfluous.

Diese Aufgabe wird durch einen Vormischbrenner nach Anspruch 1 gelöst. Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.This object is achieved by a premix burner according to claim 1. The dependent claims contain advantageous embodiments of the invention.

Ein erfindungsgemäßer Vormischbrenner umfasst einen Luftzufuhrkanal, einen Pilotgaszufuhrkanal, welcher wenigstens eine dem Pilotzufuhrkanal zugewandte Kanalwand und ein in den Luftzufuhrkanal mündendes Pilotgasaustrittsende aufweist, sowie einen zum Pilotgasaustrittsende im Luftzufuhrkanal stromauf gelegenes Zündelement, das beispielsweise als zweipolige Zündelektrode ausgebildet sein kann. In der Kanalwand des Pilotgaszufuhrkanals ist wenigstens eine stromauf zum Zündelement gelegene Gasaustrittsöffnung vorhanden.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. In the channel wall of the pilot gas supply channel, at least one gas outlet opening located upstream of the ignition element is present.

Die erfindungsgemäße Ausgestaltung des Vormischbrenners ermöglicht ein direktes Zünden des Pilotgases, d. h. ohne dass zuvor eine über einen eigenen Diffusionsgaskanal versorgte Diffusionsflamme gezündet werden muss und ohne dass ein eigener lediglich zum Zwecke der Zündung vorhandener Zündbrenner mit zugehörigen Zündgaskanal nötig ist. Zum Zwecke der Zündung kann Pilotgas aus der wenigstens einen Gasaustrittsöffnung in den Luftzufuhrkanal austreten und dort zusammen mit der Luft ein zündfähiges Gemisch bilden, welches am stromab gelegenen Zündelement vorbeiströmt. Der Brenner kann daher insgesamt konstruktiv vereinfacht werden, da weniger Gasstränge nötig sind, was zu einer Kostenreduzierung bei der Herstellung des Brenners führt.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. For the purpose of ignition 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.

Im erfindungsgemäßen Brenner weist der Pilotgaszufuhrkanal stromab der wenigstens einen Gasaustrittsöffnung einen Strömungswiderstand auf. Der Strömungswiderstand führt im stromauf befindlichen Gas zu einer Druckerhöhung, welche sicherstellt, dass genügend Gas zum Bilden eines zündfähigen Gemischs im Bereich des Zündelements durch die Gasaustrittsöffnung in dem Luftzufuhrkanal austritt. Der Strömungswiderstand kann beispielsweise durch eine Verengung, insbesondere durch eine Verengung am Pilotgasaustrittsende des Pilotgaszufuhrkanals, realisiert sein.In the burner according to the invention, the pilot gas supply channel 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.

Eine konstruktiv einfache Möglichkeit, die Verengung zu realisieren besteht darin, einen an der Kanalwand angeordneten und nach innen gerichteten Vorsprung im Inneren des Kanals anzuordnen. Alternativ besteht auch die Möglichkeit, die Verengung durch eine in den Kanal eingesetzte, den Kanalquerschnitt verringernde Hülse zu realisieren. Eine weitere Möglichkeit besteht darin, einen Hinderniskörper in den Pilotgaszufuhrkanal einzubringen. Ein solcher Körper könnte beispielsweise ein aerodynamisch geformter Körper, ein Gitter, ein Geflecht, etc. sein.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. Alternatively, it is also possible to realize the constriction by an inserted into the channel, the channel cross-section reducing sleeve. 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.

Bei dem erfindungsgemäßen Vormischbrenner ist der Pilotgaszufuhrkanal als Pilotgasrohr ausgebildet, welches durch einen Innenraum des Brenners geführt ist und welches an einer zum Zündelement stromauf gelegenen Austrittsstelle aus dem Innenraum austritt und in den Luftzufuhrkanal hinein ragt. Die Rohrwand bildet hierbei die Kanalwand, und die wenigstens eine Gasaustrittsöffnung ist im in den Luftzufuhrkanal hineinragenden Abschnitt des Pilotgasrohres angeordnet. Das Einbringen eines oder mehrer Pilotgasrohre ist insbesondere auch nachträglich in bereits bestehende Brenner möglich, so dass bestehende Brenner umgerüstet werden können.In the premix burner according to the invention, the pilot gas supply channel is designed as a pilot gas tube, which is guided through an interior of the burner and which exits from the interior at an exit point located to the ignition element 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. The introduction of one or more pilot gas tubes is particularly subsequently possible in existing burners, so that existing burners can be converted.

Gemäß einer vorteilhaften Ausgestaltung des erfindungsgemäßen Vormischbrenners kann die Kanalwand stromauf zum Zündelement wenigstens zwei in Strömungsrichtung versetzte Gasaustrittsöffnungen aufweisen. Auf diese weise lässt sich die Menge an austretendem Pilotgas vergrößern, ohne dass die Öffnungsquerschnitte der Gasaustrittsöffnungen vergrößert, und damit ihre Aerodynamik verändert werden müsste.According to an advantageous embodiment of the premix burner according to the invention, the channel wall may have upstream of the ignition element 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.

Um ein breiteres Profil des in den Luftzufuhrkanal eingebrachten Pilotbrennstoffes zu verbreitern ist es möglich, wenigstens zwei senkrecht zur Strömungsrichtung der durch den Luftzufuhrkanal strömenden Luft versetzte Gasaustrittsöffnungen in der Kanalwand stromauf zum Zündelement anzuordnen.In order to broaden a wider profile of the pilot fuel introduced into the air supply duct, it is it is possible to arrange at least two gas outlet openings, offset perpendicular to the flow direction of the air flowing through the air supply channel, in the channel wall upstream of the ignition element.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung eines Ausführungsbeispiels unter Bezugnahme auf die beiliegenden Figuren.

  • Fig. 1 zeigt einen erfindungsgemäßen Brenner in einer schematischen Schnittansicht.
  • Fig. 2 zeigt ein Pilotgasrohr mit darin angeordneten Gasaustrittsöffnungen.
  • Fig. 3 zeigt das Pilotgasrohr aus Fig. 2 in einem Schnitt entlang der Linie III-III.
  • Fig. 4 zeigt den in den Luftkanal hineinragenden Abschnitt des Pilotgasrohres in einem Schnitt entlang seiner Längsachse.
  • Fig. 5 zeigt das Austrittsende einer zweiten Variante des Pilotgasrohres.
  • Fig. 6 zeigt das Austrittsende einer dritten Variante des Pilotgasrohres.
  • Fig. 7 zeigt das Austrittsende einer vierten Variante des Pilotgasrohres.
  • Fig. 8 zeigt das Austrittsende einer fünften Variante des Pilotgasrohres.
  • Fig. 9 zeigt das Austrittsende einer sechsten Variante des Pilotgasrohres.
Further features, properties and advantages of the present invention will become apparent from the following description of an embodiment with reference to the accompanying figures.
  • 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.

Nachfolgend wird mit Bezug auf Fig. 1 ein Ausführungsbeispiel für den erfindungsgemäßen Brenner beschrieben. Der Brenner 1 ist im Wesentlichen rotationssymmetrisch um eine Brennerachse A mit einem zu einer Brennkammer 7 hin offenen Brennerausgang 9 aufgebaut. Er weist eine zentrale Brennerlanze 13 auf, die einen Zufuhrkanal für flüssige Brennstoffe aufweist und an ihrem brennkammerseitigen Ende 15 eine oder mehrere Zerstäubungsdüsen zum Eindüsen eines flüssigen Brennstoffes in die in der Brennkammer 7 herrschende Flamme besitzt. Die Brennerlanze 13 dient dann zum Erzeugen einer mit flüssigem Brennstoff gespeisten Diffusionsflamme. Falls der Brenner allein auf den allgemeinen Betrieb mit gasförmigen Brennstoffen ausgelegt ist, kommt statt der beschriebenen Brennerlanze 13 eine Attrappe zur Anwendung, die in ihrer äußerer Geometrie der beschriebenen Brennerlanze gleicht, jedoch ohne die Zerstäubungsdüsen am brennkammerseitigen Ende 15.Hereinafter, with reference to Fig. 1 an embodiment for the burner according to the invention described. 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.

Um die Brennerlanze 13 herum ist eine zylindrische Wand 17 vorhanden, die einen zwischen der Wand 17 und der Brennerlanze 13 gebildeten Innenraum 19 umschließt. Der ringförmige Innenraum 19 dient zur Zufuhr von Brenngas in einen Luftzufuhrkanal 21, durch den die zum Aufrechterhalten der Flamme nötige Luft dem Brenner 1 zugeführt wird. Hierzu weist der ringförmige Innenraum 19 Gasaustrittsöffnungen 20 auf. Stromauf des Brennerausgangs 9 weist der Brenner 1 sogenannte Axialgitter 30 auf, die für eine Verwirbelung der Luft und des Brenngases und dadurch für eine innige Vermischung der beiden sorgen. Das innig vorgemischte Luft-Brennstoff-Gemisch wird über den Brennerausgang 9 der Brennkammer 7 zugeführt, wo es verbrannt wird.Around the burner lance 13 around a cylindrical wall 17 is present, which encloses a space 19 formed between the wall 17 and the burner lance 13. 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. For this purpose, the annular space 19 has gas outlet openings 20. Upstream of the burner outlet 9, 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.

Um die Bildung NOx gering zu halten, wird das vorgemischte Luft-Brennstoff-Gemisch mager eingestellt, d.h. der Brennstoffanteil im Gemisch wird so gering wie möglich gehalten, wodurch NOx-bildende Temperaturspitzen in der entstehenden Vormischflamme vermieden werden können. Eine Pilotflamme, die im Gegensatz zum Vormischflamme als Diffusionsflamme betrieben wird, dient dazu, die Vormischflamme, die nahe an der Stabilitätsgrenze betrieben wird, zu stabilisieren, um das Entstehen von Druckschwankungen in der Brennkammer aufgrund von Verbrennungsschwingungen zu vermeiden. In der Diffusionsflamme erfolgt im Unterschied zur Vormischflamme keine innige Vermischung von Brennstoff und Luft, bevor diese der Flamme zugeführt werden. Die Pilotflamme dient nicht nur zum Stabilisieren der Vormischflamme, sondern auch zum Zünden der Vormischflamme.To minimize formation of NOx, 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.

Um eine Pilotflamme zu speisen, sind Pilotgasrohre 23 durch den ringförmigen Innenraum 19 zwischen der zylinderförmigen Wand 17 und der Brennerlanze 13 bis zum brennkammerseitigen Ende des Innenraums 19 geführt. Dort treten sie durch eine im Wesentlichen kegelmantelförmige Stirnwand 25 hindurch und ragen mit einem Rohrabschnitt 27 in den Luftzufuhrkanal 21 hinein. Die brennkammerseitigen Enden 29 der Pilotgasrohre 23 sind offen und dienen zum Eindüsen von Pilotgas in die durch den ringförmigen Luftzufuhrkanal 21 strömende Luft. In den Luftzufuhrkanal 21 ragt außerdem ein Zünder 31 mit einer zweipoligen Zündelektrode 33 hinein. Die Spitze 35 der zweipoligen Zündelektrode 33, die das eigentliche Zündelement des Brenners 1 darstellt, befindet sich stromauf zu den offenen Austrittsenden 29 der Pilotgasrohre 23. Sie ist so angeordnet, dass sie weitgehend auf derselben Radiallinie wie eines der Pilotgasrohre 23 angeordnet ist. Auf diese Weise befindet sich die zweipolige Zündelektrode 35 nahe an einem Pilotgasrohr. Es sei angemerkt, dass die Spitze 35 der Zündelektrode 32 nicht notwendigerweise auf derselben Radiallinie wie eines der Pilotgasrohre 23 liegen muss. Es ist lediglich von Bedeutung, dass die Spitze 35 nahe genug an eines der Rohre 23 herangeführt ist.To feed a pilot 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. It is arranged so that it is arranged substantially on the same radial line as one of the pilot gas tubes 23. In this way, 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.

Das in der Nähe des Zünders 31 angeordnete Pilotgasrohr 23 ist zusätzlich zu der Öffnung im Austrittsende 29 mit wenigstens einer in der Rohrwand stromauf zum Austrittsende 29 gelegenen Gasaustrittsöffnung 37 ausgestattet. Im vorliegenden Ausführungsbeispiel sind drei Gasaustrittsöffnungen 37a, 37b, 37c vorhanden, die als in Axialrichtung des Rohres 23 sowie in Umfangsrichtung des Rohres 23 versetzte Bohrungen ausgeführt sind. Die Anordnung der Bohrungen sind in den Figuren 2 und 3 dargestellt, wobei Fig. 2 eine Ansicht auf die Bohrungen im Pilotgasrohr 23 und Fig. 3 einen Schnitt durch die Rohrwand 39 des Pilotgasrohres 23 entlang der Linie III-III zeigt. Die Verteilung der Bohrungen 37a, 37b, 37c sind im Hinblick auf eine Optimierung des Verteilungsprofils des durch die Bohrungen 37 austretenden Gases gewählt.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. in the present embodiment, 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.

Die Gasaustrittsöffnungen 37 sind im Pilotgasrohr 23 stromauf zur Elektrodenspitze 35 angeordnet, d.h. aus den Gasaustrittsöffnungen 37 austretendes Gas, welches in die durch den Luftzufuhrkanal 21 strömende Luft eingedüst wird, strömt entlang der Elektrodenspitze 35, so dass das Gas mittels eines Zündfunkens gezündet werden kann.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.

Um den Austritt einer für die Zündung hinreichenden Gasmenge durch die Gasaustrittsöffnungen 37a bis 37c zu gewährleisten, ist in dem Pilotgasrohr 23 stromab von den Gasaustrittsöffnungen ein Strömungswiderstand angeordnet. Dieser führt dazu, dass stromauf zum Strömungswiderstand eine Druckerhöhung stattfindet, die dafür sorgt, dass genügend Pilotgas für eine erfolgreiche Zündung durch die Gasaustrittsöffnungen 37a, 37b, 37c in den Luftzufuhrkanal 21 austritt.In order to ensure the discharge of a sufficient amount of gas for the ignition through the gas outlet openings 37a to 37c, 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.

Eine Detailansicht des in den Luftzufuhrkanal 21 hineinragenden Abschnitts 27 des Pilotgasrohres 23 ist in Fig. 4 in einer vergrößerten Schnittansicht dargestellt. In dieser Ansicht ist lediglich eine der sich durch die Rohrwand 39 erstreckenden Gasaustrittsöffnungen 37 zu erkennen. Am Pilotgasaustrittsende 29 ist eine Hülse 41 in das Pilotgasrohr 23 eingeführt, welche den Strömungsquerschnitt, der dem Pilotgas im Pilotgasrohr 23 zur Verfügung steht, im Bereich des Austrittsendes 29 verringert. Auf diese Weise wird der Gasdruck stromauf zur Hülse 41 soweit erhöht, dass genügend Pilotgas durch die Gasaustrittsöffnungen 37 austritt.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. At the pilot gas outlet end 29, 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.

Eine alternative Variante zum Erzeugen eines Strömungswiderstandes im Bereich des Austrittsendes 29 des Pilotgasrohres 23 ist in Fig. 5 dargestellt. Statt einer Hülse 41 weist das Pilotgasrohr 23 am Austrittsende 29 einen kegelstumpfförmigen Wandabschnitt 43 auf, der dazu führt, dass die Austrittsöffnung 45 am Pilotgasaustrittsende 29 einen im Vergleich zum Strömungsquerschnitt des Pilotgasrohres 23 verringerten Öffnungsquerschnitt aufweist. Auch hierdurch kann eine geeignete Druckerhöhung im Bereich stromauf zur Gasaustrittsöffnungen 37 herbeigeführt werden.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. Instead of a sleeve 41, 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.

Eine weitere Variante zum Einführen eines Strömungswiderstandes in das Pilotgasrohr 23 ist in Fig. 6 dargestellt. In dieser Variante weist das Pilotgasrohr 23 kurz vor dem Austrittsende 29 eine um seinen Umfang umlaufende v-förmige Einbuchtung 47 auf, die zu einer Verringerung des für das Pilotgas zur Verfügung stehenden Strömungsquerschnittes im Bereich der Einbuchtung führt. Die Verringerung des Strömungsquerschnittes führt wiederum zu einer Druckerhöhung stromauf der Einbuchtung 47.Another variant for introducing a flow resistance into the pilot gas pipe 23 is in Fig. 6 shown. In this variant, 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.

Eine weitere Variante des Strömungswiderstandes ist in Fig. 7 dargestellt. In dieser Variante weist das Pilotgasrohr 23 kurz vor dem Pilotgasaustrittsende 29 einen nach innen gerichteten und um den Rohrumfang umlaufenden Wulst 49 auf, der zu einer Verringerung des für das Pilotgas zur Verfügung stehenden Strömungsquerschnittes und somit zu einer Druckerhöhung stromauf des Wulstes 49 führt.Another variant of the flow resistance is in Fig. 7 shown. In this variant, 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 outlet end 29.

Noch eine weitere Variante des Strömungswiderstandes ist in Fig. 8 dargestellt. In dieser Variante ist die Rohrwand 39 bis zum Pilotgasaustrittsende 29 zylinderförmig ausgebildet. Die druckerhöhende Verringerung des Strömungsquerschnittes im Pilotgasrohr 23 erfolgt durch einen aerodynamisch geformten Einsatz 51, der mittels Streben 53 an der Innenseite der Rohrwand 39 befestigt ist. Die Befestigung kann mittels einer Hartlöt- oder einer Schweißverbindung erfolgen. Alternativ ist es auch möglich, die Streben mittels einer Schraubverbindung an der Rohrwand 39 zu fixieren.Yet another variant of the flow resistance is in Fig. 8 shown. In this variant, 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. Alternatively, it is also possible to fix the struts by means of a screw connection to the tube wall 39.

Noch eine weitere Variante für den Strömungswiderstand im Pilotgasrohr 23 ist in Fig. 9 dargestellt. Auch das in Fig. 9 dargestellte Pilotgasrohr 23 weist bis zu seinem Pilotgasaustrittsende 29 eine zylinderförmige Rohrwand 39 auf. Kurz vor dem Pilotgasaustrittsende 29 oder direkt am Pilotaustrittsende 29 ist ein Gitter 55 in das Pilotgasrohr 23 eingesetzt, welches ein Strömungshindernis für das durch das Pilotgasrohr 23 strömende Pilotgas darstellt und somit zu einer Druckerhöhung stromauf des Gitters 55 führt.Yet another variant for the flow resistance in the pilot gas pipe 23 is in Fig. 9 shown. Also in Fig. 9 illustrated 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.

Die anhand des Ausführungsbeispiels beschriebe Erfindung ermöglicht es bei einem Brenner, in dem der Pilotbrenner lediglich Pilotgaszufuhrkanäle als einzige Gaszufuhrkanäle aufweist, eine Zündung des Brenners ohne eigens dafür vorhandenen und eigene Brennstoffzufuhr aufweisenden Zündbrenner herbeizuführen. Der erfindungsgemäße Brenner kommt daher mit lediglich zwei Gaszufuhrsystemen, nämlich dem Zufuhrsystem für das Pilotgas und dem Zufuhrsystem für das Gas im Vormischbetrieb, aus. Eine Reduktion der Komplexität des Brenners und damit einhergehend der Herstellungskosten ist das Ergebnis.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.

Claims (4)

  1. Premix burner (1) having an air feed passage (21),
    at least one pilot gas feed passage (23), which has at least one passage wall (39) pointing to the air feed passage (21) and a pilot gas discharge end (29) which opens into the air feed passage (21), and an ignition element (35) which is located in the air feed passage (21) upstream of the pilot gas discharge end (29),
    characterized in that
    the passage wall (39) of the pilot gas feed passage (23) has at least one gas discharge opening (37) upstream of the ignition element (35) and wherein the pilot gas feed passage (29) has a flow resistance (41, 43, 47, 49, 51, 55) downstream of the at least one gas discharge opening (37) and wherein the flow resistance is realized by means of a constriction (41, 43, 47, 49) of the pilot gas feed passage (23) and wherein the constriction is realized by means of an inwardly oriented protrusion (47, 49) which is arranged on the passage wall (39), or the constriction is realized by means of a sleeve (41) which is inserted into the passage (23) and reduces the passage cross section, or the constriction is realized by means of a body (51, 55) which is inserted into the passage (23) and reduces the passage cross section, and the at least one pilot gas feed passage is formed as at least one pilot gas pipe (23) which is guided through an internal space (19) of the burner (1) and which exits from the internal space (19) at an exit point, which is located upstream of the ignition element (35), and projects into the air feed passage (21), wherein the pipe wall forms the passage wall and the at least one gas discharge opening (37) is arranged in the section (27) of the pilot gas pipe (23) which projects into the air feed passage (21).
  2. Premix burner (1) according to Claim 1,
    characterized in that
    the constriction is arranged at the pilot gas discharge end (41, 43, 47, 49) of the pilot gas feed passage (23).
  3. Premix burner (1) according to one of the preceding claims,
    characterized in that
    the passage wall (39) upstream of the ignition element (35) has at least two gas discharge openings (37a, 37b, 37c) which are staggered in the flow direction of the air in the air feed passage (21).
  4. Premix burner (1) according to one of the preceding claims,
    characterized in that
    the passage wall (39) upstream of the ignition element (35) has at least two gas discharge openings (37a, 37b, 37c) which are staggered perpendicularly to the flow direction of the air in the air feed passage (21).
EP10702659A 2009-04-23 2010-01-29 Pre-mix burner Active EP2422136B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10702659A EP2422136B1 (en) 2009-04-23 2010-01-29 Pre-mix burner

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09158558A EP2244015A1 (en) 2009-04-23 2009-04-23 Pre-mix burner
EP10702659A EP2422136B1 (en) 2009-04-23 2010-01-29 Pre-mix burner
PCT/EP2010/051104 WO2010121845A1 (en) 2009-04-23 2010-01-29 Pre-mix burner

Publications (2)

Publication Number Publication Date
EP2422136A1 EP2422136A1 (en) 2012-02-29
EP2422136B1 true EP2422136B1 (en) 2013-04-03

Family

ID=41036755

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09158558A Withdrawn EP2244015A1 (en) 2009-04-23 2009-04-23 Pre-mix burner
EP10702659A Active EP2422136B1 (en) 2009-04-23 2010-01-29 Pre-mix burner

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09158558A Withdrawn EP2244015A1 (en) 2009-04-23 2009-04-23 Pre-mix burner

Country Status (4)

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

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102901098B (en) * 2012-10-23 2015-10-07 江苏中圣高科技产业有限公司 Ground flare multi-head high-efficiency premixed type combustion system

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3663189D1 (en) 1985-03-04 1989-06-08 Siemens Ag Burner disposition for combustion installations, especially for combustion chambers of gas turbine installations, and method for its operation
SU1502910A1 (en) * 1987-12-18 1989-08-23 Предприятие "Средазтехэнерго" Производственного Объединения По Наладке, Совершенствованию И Эксплуатации Электростанций И Сетей "Союзтехэнерго" Pilot burner
DE19757617A1 (en) 1997-12-23 1999-03-25 Siemens Ag Combustion system
WO2000012933A1 (en) 1998-08-26 2000-03-09 Siemens Aktiengesellschaft Hybrid burner and method for operating a hybrid burner
US6443728B1 (en) * 2001-03-19 2002-09-03 Alstom (Schweiz) Ag Gas pipe ignitor
ITTO20040309A1 (en) * 2004-05-13 2004-08-13 Ansaldo Energia Spa METHOD FOR CHECKING A GAS COMBUSTER OF A GAS TURBINE
EP1614967B1 (en) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Method and premixed combustion system
ITTO20050208A1 (en) * 2005-03-30 2006-09-30 Ansaldo Energia Spa GAS BURNER GROUP FOR A GAS TURBINE
EP1712837A1 (en) 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Burner assembly and method of operating it
WO2009032793A1 (en) * 2007-09-06 2009-03-12 Coen Company, Inc. Burner pilot with virtual spinner

Also Published As

Publication number Publication date
CN102414514A (en) 2012-04-11
EP2244015A1 (en) 2010-10-27
EP2422136A1 (en) 2012-02-29
CN102414514B (en) 2014-08-20
RU2551462C2 (en) 2015-05-27
RU2011147468A (en) 2013-05-27
WO2010121845A1 (en) 2010-10-28

Similar Documents

Publication Publication Date Title
EP1754002B1 (en) Staged premix burner with an injector for liquid fuel
EP1812756B1 (en) Burner starting method
DE19533055B4 (en) Double fuel mixer for a gas turbine combustor
DE102010016888B4 (en) Method and device for burner nozzles with protection against flame holding
DE69719688T2 (en) Gas turbine burners and operating methods therefor
EP1436546B1 (en) Burner for synthesis gas
DE102008044422A1 (en) Method and apparatus for the combustion of fuel in a gas turbine
DE102014117621A1 (en) Fuel injector with premix pilot nozzle
EP2257736B1 (en) Method for the production of hot gas
EP0687860A2 (en) Self igniting combustion chamber
DE102009043830A1 (en) Flame-holding tolerant fuel / air premixer for a gas turbine combustor
WO2005080878A1 (en) Premix burner and method for burning a low-calorie combustion gas
CH701459A2 (en) Vormischpilotanordnung for a fuel nozzle for a turbine combustor.
CH702737A2 (en) Combustion chamber with two combustion chambers.
DE4446842A1 (en) Method and device for feeding a gaseous fuel into a premix burner
CH703230B1 (en) Gas turbine with single-stage fuel injection.
CH697703A2 (en) Fuel nozzle assembly.
EP2601447A2 (en) Gas turbine combustion chamber
EP1754937B1 (en) Burner head and method of combusting fuel
DE102007036953B3 (en) burner
EP2409086B1 (en) Burner assembly for a gas turbine
EP2037173B1 (en) Burner head and method for one-step combustion of fuel in a combustion zone separated from the burner head
EP2422136B1 (en) Pre-mix burner
WO2006015968A1 (en) Burner, gas turbine and operation of a burner
DE112014000656T5 (en) Gas turbine injector with cavity for metering

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

17P Request for examination filed

Effective date: 20111021

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

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 604980

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130415

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010002771

Country of ref document: DE

Effective date: 20130529

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20130403

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130714

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130805

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130704

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130803

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

26N No opposition filed

Effective date: 20140106

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010002771

Country of ref document: DE

Effective date: 20140106

REG Reference to a national code

Ref country code: HU

Ref legal event code: AG4A

Ref document number: E019059

Country of ref document: HU

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20140131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140129

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20140129

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140930

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140129

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140129

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140131

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: HU

Payment date: 20150319

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 604980

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150129

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150129

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130403

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502010002771

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: TR

Payment date: 20220127

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230126

Year of fee payment: 14

Ref country code: DE

Payment date: 20220617

Year of fee payment: 14