EP0995066A1 - Arrangement of burners for heating installation, in particular a gas turbine combustion chamber - Google Patents

Arrangement of burners for heating installation, in particular a gas turbine combustion chamber

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Publication number
EP0995066A1
EP0995066A1 EP98943638A EP98943638A EP0995066A1 EP 0995066 A1 EP0995066 A1 EP 0995066A1 EP 98943638 A EP98943638 A EP 98943638A EP 98943638 A EP98943638 A EP 98943638A EP 0995066 A1 EP0995066 A1 EP 0995066A1
Authority
EP
European Patent Office
Prior art keywords
burner
air duct
fuel
air
inlets
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP98943638A
Other languages
German (de)
French (fr)
Other versions
EP0995066B1 (en
Inventor
Bernd Prade
Holger Streb
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
Publication of EP0995066A1 publication Critical patent/EP0995066A1/en
Application granted granted Critical
Publication of EP0995066B1 publication Critical patent/EP0995066B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame
    • 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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/82—Preventing flashback or blowback
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • Burner arrangement for a furnace in particular a gas turbine combustion chamber
  • the present invention is in the field of burner assemblies for combustion plants, particularly for gas turbine combustors. Such burner assemblies are often designed for different fuels and different modes of operation, with great struggles to improve the assemblies and modes of operation so that pollutant emissions are reduced in view of increasingly stringent regulations for the emission of pollutants worldwide.
  • the present invention is particularly concerned with reducing nitrogen oxide emissions, hereinafter referred to as NOx.
  • Air and fuel are first mixed as evenly as possible and only then burned together in a flame area of a combustion chamber.
  • the combustion temperature can be kept lower overall than in the border area between fuel and air, and at the same time a desired ratio of fuel and air can be maintained evenly. This leads to a lower emission of pollutants, especially NOx.
  • premix burners The disadvantage of premix burners is that the combustion cannot be kept stable in all load conditions that the control range of premix burners is usually smaller than that of diffusion burners.
  • pilot burners which are usually arranged in the center of a main burner and stabilize the combustion of the main burner with their small but stable flame. Pilot burners are also needed to support the ignition of a main burner.
  • pilot burners can generate a considerable proportion of NOx in relation to the total pollutant emissions if they are operated as diffusion burners. For this reason, it is already suggested there that a pilot burner should also be designed as a premix burner, but which can be kept in a stable operating range, even if the main burner is operated in a different operating range. This measure can lead to a significant reduction in pollutant emissions.
  • a burner arrangement according to claim 1 is used to achieve the object. Advantageous and preferred refinements are described in the dependent claims.
  • the burner arrangement according to the invention for a combustion system, in particular a gas turbine combustion chamber, with a main burner and a pilot burner, which is used to ignite and / or stabilize the main burner, is in its
  • the pilot burner can always or temporarily be operated as a premix burner and the supply of fuel and combustion air to the pilot burner takes place through a lance-like supply system with concentrically arranged channels that are approximately circular in cross-section.
  • these channels is in particular the air channel for supplying combustion air for the pilot burner.
  • Inlets for fuel are arranged on this air duct, the fuel being supplied through ducts lying concentrically inside or outside of the air duct.
  • a swirl generator is arranged in the air duct in the air flow direction before the inlets. In this way, air already provided with a swirl reaches the inlets, so that there is a direct swirling of air and fuel at the inlets.
  • the fuel inlets can also be integrated into aerodynamically optimized swirl generation elements.
  • the pilot burner is typically designed for premixing operation with fuel gas, with several inlets approximately evenly distributed over the circumference being provided on the air duct.
  • the lance-like delivery system of the pilot burner consists of two or more concentrically arranged annular channels, one annular channel directly inside and / or outside the air channel for supplying fuel, in particular fuel gas.
  • Inlets in the partition between the air duct and the inner or outer ring duct bring the fuel, which is under higher pressure than the combustion air, into the air duct and is distributed there very evenly in the swirl flow generated by the swirl generator.
  • the inlets should be arranged at a certain distance from the swirl generator in order to reliably prevent flames from striking back to the swirl generator. The exact distance depends on the flow velocity of the air flowing in the air duct and the geometric conditions in the air duct.
  • the swirl generator can produce an axial and / or radial and / or tangential swirl, the swirl strength and the length of the pre-mixing section available for mixing with the fuel being selected so that the meridional flow rate is high in order to prevent the flames from striking back prevent, and that no so-called hub separation can occur, that is, the flow does not separate from the walls of the air duct.
  • the air duct has a diffuser at its end region opening into the furnace in a special embodiment of the invention, in particular formed by an increasing cross-section in the end region in the direction of flow.
  • a cooling system arranged concentrically to the air duct can be used, in which air, air-fuel mixture or steam cools the end region of the air duct.
  • the inlets for fuel are designed as mixing elements in the air duct of the pilot burner.
  • they can be designed in the form of small tubes, which distribute the fuel very finely in the air with a large number of inlet openings.
  • the arrangement of additional swirl generator blades with inlet openings for fuel is also possible.
  • the drawing shows a burner as known in principle from EP 093 838. The one from this
  • main burner 1 is supplied with main combustion air 2, into which fuel gas is injected finely distributed via a main fuel gas supply 3 and a main fuel gas injector 20 and / or via a main fuel oil supply 4 and a main fuel oil injector 21.
  • main combustion air 2 into which fuel gas is injected finely distributed via a main fuel gas supply 3 and a main fuel gas injector 20 and / or via a main fuel oil supply 4 and a main fuel oil injector 21.
  • main swirl generator 5 in particular in the form of a diagonal grid.
  • the main burner 1 In the center of the main burner 1 there is a pilot burner for igniting and stabilizing the main flame, the combustion air of which is supplied through an air duct 6, in a manner known per se.
  • a central fuel channel 7 for the operation of this pilot burner as a diffusion burner which, however, is possible according to the main idea of the present invention. is rarely used because the operation of the pilot burner as a diffusion burner generates too much NOx.
  • the air duct 6 has inlets 10, 11 through which fuel can be mixed into the combustion air of the pilot burner.
  • the concentric lance-like structure of the burner enables this fuel to be supplied through an outer fuel channel 8 and outer inlets 10 and / or through an inner fuel channel 9 and inner inlets 11.
  • mixing elements 15 can also be used, in the present exemplary embodiment in the form of small perforated tubes for more even distribution of fuel.
  • fuel oil or fuel gas can be considered as fuel, for which purpose the corresponding inlets or mixing elements must be suitably dimensioned.
  • the arrangement of the swirl generators in the flow direction upstream of the fuel inlets also has the advantage that, in the event of malfunctions, the flames of the pilot burner can in no case strike back further than the swirl generator 12.
  • the air duct 6 can be designed as a diffuser 13 in its end region.
  • a cooling system 14 in particular with a system which is concentrically arranged around the diffuser and which is cooled by means of air, air-fuel mixture or steam.
  • a burner according to the invention is connected in a manner known per se via corresponding control valves with its air inlet 16 an air supply connected and with its fuel inlets 17, 18, 19 for the central fuel channel 7, the outer fuel channel 8 or the inner fuel channel 9 to a fuel supply.
  • Burners according to the invention enable stable and low-pollutant operation in wide load ranges and are particularly suitable for combustion chambers of gas turbine systems.

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

Abstract

The invention concerns an arrangement of burners for a heating installation, in particular a gas turbine combustion chamber, comprising a main burner (1) and a pilot flame for lighting and/or stabilising the main burner (1). Said pilot flame is permanently or temporarily used as premix burner, and a supply system (6, 7, 8, 9) in the form of a pipe for supplying fuel and combustion air, said system including at least an air duct (6) with a more or less circular cross-section, and which is provided with intakes (10; 11) for the fuel. In the direction of the air flow upstream of said intakes (10; 11) which are arranged preferably at regular intervals on the periphery of the air duct (6), a vortex generator (12) is provided in the air duct (6). The latter acts as diffuser (13) at its end zone emerging into the heating installation and with in particular an end zone (13) ever widening in cross-section and also capable of being cooled. The vortex generator (12) upstream of the fuel intakes (10; 11) ensures stable and safe functioning of the pilot flame with slight production of NOx.

Description

Beschreibungdescription
Brenneranordnung für eine Feuerungsanlage, insbesondere eine GasturbinenbrennkammerBurner arrangement for a furnace, in particular a gas turbine combustion chamber
Die vorliegende Erfindung liegt auf dem Gebiet der Brenneranordnungen für Feuerungsanlagen, insbesondere für Gasturbinenbrennkammern. Solche Brenneranordnungen sind oft für verschiedene Brennstoffe und verschiedene Betriebsweisen ausge- legt, wobei es im Hinblick auf weltweit immer strengere Bestimmungen zum Ausstoß von Schadstoffen große Anstrengungen gibt, die Anordnungen und Betriebsweisen so zu verbessern, daß der Schadstoffaustoß verringert wird. Bei der vorliegenden Erfindung geht es insbesondere um die Verringerung des Ausstoßes von Stickoxiden, im folgenden als NOx bezeichnet.The present invention is in the field of burner assemblies for combustion plants, particularly for gas turbine combustors. Such burner assemblies are often designed for different fuels and different modes of operation, with great struggles to improve the assemblies and modes of operation so that pollutant emissions are reduced in view of increasingly stringent regulations for the emission of pollutants worldwide. The present invention is particularly concerned with reducing nitrogen oxide emissions, hereinafter referred to as NOx.
Besonders umweltfreundliche Brenner mit einem geringem Ausstoß an NOx sind aus der EP 0 108 361 Bl und der EP 0 193 838 Bl bekannt. Aus diesen Schriften kann man entnehmen, das der Ausstoß an NOx erheblich reduziert werden kann, wenn Brenneranordnungen nicht als Diffusionsbrenner betrieben werden, sondern als Vormischbrenner . Bei Diffusionsbrennern wird Brennstoff mehr oder weniger gleichmäßig verteilt in einen Luftstrom direkt eingesprüht und im Grenzbereich zwischen Luft und Brennstoff verbrannt. Bei Vor ischbrennern werdenParticularly environmentally friendly burners with low NOx emissions are known from EP 0 108 361 Bl and EP 0 193 838 Bl. From these documents it can be seen that the emission of NOx can be considerably reduced if burner arrangements are not operated as a diffusion burner but as a premix burner. In diffusion burners, fuel is sprayed more or less evenly into an air stream and burned in the border area between air and fuel. With pre-burners
Luft und Brennstoff zunächst möglichst gleichmäßig vermischt und erst danach gemeinsam in einem Flammenbereich einer Brennkammer verbrannt. Durch die vorherige gleichmäßige Durchmischung kann die Verbrennungstemperatur insgesamt nied- riger gehalten werden als im Grenzbereich zwischen Brennstoff und Luft, wobei gleichzeitig auch ein gewünschtes Verhältnis von Brennstoff und Luft gleichmäßig eingehalten werden kann. Dies führt zu einem geringeren Ausstoß an Schadstoffen, insbesondere an NOx.Air and fuel are first mixed as evenly as possible and only then burned together in a flame area of a combustion chamber. As a result of the previous uniform mixing, the combustion temperature can be kept lower overall than in the border area between fuel and air, and at the same time a desired ratio of fuel and air can be maintained evenly. This leads to a lower emission of pollutants, especially NOx.
Nachteil von Vormischbrennern ist es, daß die Verbrennung nicht in allen Lastzuständen stabil gehalten werden kann, so daß der Regelbereich von Vormischbrennern meist kleiner ist als der von Diffusionsbrennern.The disadvantage of premix burners is that the combustion cannot be kept stable in all load conditions that the control range of premix burners is usually smaller than that of diffusion burners.
Zur Erweiterung des Regelbereiches werden sogenannte Pilotbrenner eingesetzt, die meist im Zentrum eines Hauptbrenners angeordnet sind und mit ihrer zwar kleinen aber stabilen Flamme die Vebrennung des Hauptbrenners stabilisieren. Auch zur Unterstützung beim Zünden eines Hauptbrenners werden Pilotbrenner gebraucht.To expand the control range, so-called pilot burners are used, which are usually arranged in the center of a main burner and stabilize the combustion of the main burner with their small but stable flame. Pilot burners are also needed to support the ignition of a main burner.
Aus der EP 0 938 381 Bl ist auch bekannt, daß solche Pilotbrenner einen erheblichen Anteil an NOx bezogen auf den gesamten Schadstoffausstoß erzeugen können, wenn sie als Diffusionsbrenner betrieben werden. Deshalb wird dort schon vorge- schlagen, einen Pilotbrenner ebenfalls als Vormischbrenner auszubilden, der aber in einem stabilen Betriebsbereich gehalten werden kann, auch wenn der Hauptbrenner in einem anderen Betriebsbereich betrieben wird. Diese Maßnahme kann zu einer erheblichen Verringerung des Schadstoffaustoßes führen.It is also known from EP 0 938 381 B1 that such pilot burners can generate a considerable proportion of NOx in relation to the total pollutant emissions if they are operated as diffusion burners. For this reason, it is already suggested there that a pilot burner should also be designed as a premix burner, but which can be kept in a stable operating range, even if the main burner is operated in a different operating range. This measure can lead to a significant reduction in pollutant emissions.
Ausgehend von der EP 0 193 838 Bl, auf die vollinhaltlich ausdrücklich Bezug genommen wird, ist es Aufgabe der vorliegenden Erfindung, die dort beschriebene Brenneranordnung so zu verbessern, daß der Pilotbrenner im Vormischbetrieb siche- rer und mit noch geringerem Ausstoß an NOx betrieben werden kann. Die bekannte Anordnung weist nämlich eine Vormisch- strecke auf, an deren Ausgang zur Brennkammer eine Drallbeschaufelung angeordnet ist, die gleichzeitig als Flammenhalter dient. Durch diese Anordnung kann eine optimale Vermi- schung von Luft und Brennstoff, insbesondere Brenngas nicht erreicht werden, wobei zusätzlich bei bestimmten Betriebsstörungen die Pilotflamme in die Vormischstrecke zurückschlagen könnte, was unerwünscht ist.Starting from EP 0 193 838 B1, to which full reference is expressly made, it is the object of the present invention to improve the burner arrangement described there in such a way that the pilot burner can be operated more reliably in premix mode and with even lower NOx emissions . This is because the known arrangement has a premixing section, at the outlet of which is a swirl blading which also serves as a flame holder. With this arrangement, an optimal mixing of air and fuel, in particular fuel gas, cannot be achieved, and in the case of certain malfunctions the pilot flame could also strike back into the premixing section, which is undesirable.
Zur Lösung der Aufgabe dient eine Brenneranordung gemäß dem Anspruch 1. Vorteilhafte und bevorzugte Ausgestaltungen sind in den abhängigen Ansprüchen beschrieben. Die erfindungsgemäße Brenneranordnung für eine Feuerungsanlage, insbesondere eine Gasturbinenbrennkammer, mit einem Hauptbrenner und einem Pilotbrenner, der zum Zünden und/oder zur Stabilisierung des Hauptbrenners dient, ist in ihremA burner arrangement according to claim 1 is used to achieve the object. Advantageous and preferred refinements are described in the dependent claims. The burner arrangement according to the invention for a combustion system, in particular a gas turbine combustion chamber, with a main burner and a pilot burner, which is used to ignite and / or stabilize the main burner, is in its
Grundaufbau der Brenneranordnung aus der EP 0 193 838 Bl sehr ähnlich. Der Pilotbrenner ist immer oder zeitweise als Vormischbrenner betreibbar und die Zufuhr von Brennstoff und Verbrennungsluft zum Pilotbrenner erfolgt durch ein lanzenar- tig aufgebautes Zuführsystem mit konzentrisch ineinander angeordneten, im Querschnitt etwa kreisringförmigen Kanälen. Unter diesen Kanälen befindet sich insbesondere der Luftkanal zur Zuführung von Verbrennungsluft für den Pilotbrenner. An diesem Luftkanal sind Einlasse für Brennstoff angeordnet, wo- bei der Brennstoff durch konzentrisch innen oder außen zu dem Luftkanal liegende Kanäle zugeführt wird. Grundsätzlich ist auch eine Zuführung durch einzelne Rohrleitungen zu den Einlassen möglich. Erfindungsgemäß ist in dem Luftkanal in Luftströmungsrichtung vor den Einlassen ein Drallerzeuger ange- ordnet. Auf diese Weise gelangt schon mit einem Drall versehene Luft zu den Einlassen, so daß direkt eine starke Ver- wirbelung von Luft und Brennstoff an den Einlassen erfolgt. Zur Steigerung der Länge des Vermischungsweges können die Brennstoffeinlasse auch in aerodynamisch optimierte Drall- erzeugungselemente integriert werden.Basic structure of the burner arrangement from EP 0 193 838 B1 is very similar. The pilot burner can always or temporarily be operated as a premix burner and the supply of fuel and combustion air to the pilot burner takes place through a lance-like supply system with concentrically arranged channels that are approximately circular in cross-section. Among these channels is in particular the air channel for supplying combustion air for the pilot burner. Inlets for fuel are arranged on this air duct, the fuel being supplied through ducts lying concentrically inside or outside of the air duct. In principle, it is also possible to feed individual pipes to the inlets. According to the invention, a swirl generator is arranged in the air duct in the air flow direction before the inlets. In this way, air already provided with a swirl reaches the inlets, so that there is a direct swirling of air and fuel at the inlets. To increase the length of the mixing path, the fuel inlets can also be integrated into aerodynamically optimized swirl generation elements.
Typischerweise wird der Pilotbrenner für den Vormischbetrieb mit Brenngas ausgelegt, wobei an dem Luftkanal mehrere etwa gleichmäßig über den Umfang verteilte Einlasse vorgesehen sind.The pilot burner is typically designed for premixing operation with fuel gas, with several inlets approximately evenly distributed over the circumference being provided on the air duct.
Unterhalb der Einlasse ist der Luftkanal frei von Einbauten, insbesondere ohne einen Flammenhalter ausgebildet. Der Einbau von turbulenzerzeugenden Elementen vor den Brennstoffeinläs- sen zur Verbesserung der Mischung ist gegebenenfalls möglich. Gemäß einer bevorzugten Ausführungsform der Erfindung besteht das lanzenartig aufgebaute Zuführsystem des Pilotbrenners aus zwei oder mehreren konzentrisch zueinander angeordneten Ringkanälen, wobei ein Ringkanal unmittelbar innerhalb und/oder außerhalb des Luftkanals zur Zufuhr von Brennstoff, insbesondere Brenngas dient. Durch Einlasse in der Zwischenwand zwischen Luftkanal und innerem beziehungsweise äußerem Ringkanal gelangt der unter höherem Druck als die Verbrennungsluft stehende Brennstoff in den Luftkanal und verteilt sich dort in der durch den Drallerzeuger erzeugten Drallströmung sehr gleichmäßig. Dabei sollten die Einlasse mit einem gewissen Abstand von dem Drallerzeuger angeordnet sein, um sicher zu verhindern, daß Flammen bis zum Drallerzeuger zurückschlagen können. Der genaue Abstand hängt von der Strömungsgeschwin- digkeit der im Luftkanal strömenden Luft und den geometrischen Verhältnissen im Luftkanal ab.Below the inlets, the air duct is free of internals, in particular without a flame holder. It may be possible to install turbulence-generating elements in front of the fuel inlets to improve the mixture. According to a preferred embodiment of the invention, the lance-like delivery system of the pilot burner consists of two or more concentrically arranged annular channels, one annular channel directly inside and / or outside the air channel for supplying fuel, in particular fuel gas. Inlets in the partition between the air duct and the inner or outer ring duct bring the fuel, which is under higher pressure than the combustion air, into the air duct and is distributed there very evenly in the swirl flow generated by the swirl generator. The inlets should be arranged at a certain distance from the swirl generator in order to reliably prevent flames from striking back to the swirl generator. The exact distance depends on the flow velocity of the air flowing in the air duct and the geometric conditions in the air duct.
Der Drallerzeuger kann einen axialen und/oder radialen und/oder tangentialen Drall erzeugen, wobei die Drallstärke und die Länge der für die Vermischung mit dem Brennstoff zur Verfügung stehende Vormischstrecke so gewählt werden, daß die meridionale Strömungsgeschwindigkeit groß ist, um ein Zurückschlagen der Flammen zu verhindern, und daß keine sogenannte Nabenablösung auftreten kann, das heißt die Strömung sich nicht von den Wänden des Luftkanals ablöst.The swirl generator can produce an axial and / or radial and / or tangential swirl, the swirl strength and the length of the pre-mixing section available for mixing with the fuel being selected so that the meridional flow rate is high in order to prevent the flames from striking back prevent, and that no so-called hub separation can occur, that is, the flow does not separate from the walls of the air duct.
Um die Stabilität der Pilotflamme weitgehend zu erhöhen, weist der Luftkanal an seinem in die Feuerungsanlage mündenden Endbereich in einer besonderen Ausführungsform der Erfin- düng einen Diffusor auf, insbesondere gebildet durch eine in Strömungsrichtung zunehmende Erweiterung des Querschnittes im Endbereich.In order to increase the stability of the pilot flame to a large extent, the air duct has a diffuser at its end region opening into the furnace in a special embodiment of the invention, in particular formed by an increasing cross-section in the end region in the direction of flow.
Da die Pilotflamme anders als beim Stand der Technik nicht mehr durch einen Flammenhalter gehalten wird, besteht dieSince, unlike in the prior art, the pilot flame is no longer held by a flame holder, there is
Möglichkeit, daß sich die Wände des Luftkanals im Endbereich stark erhitzen, was durch eine Wandkühlung in Grenzen gehal- ten werden kann. Dabei kann insbesondere ein konzentrisch zum Luftkanal angeordnetes Kühlsystem verwendet werden, bei welchem Luft, Luft-Brennstoff-Gemisch oder Dampf den Endbereich des Luftkanals kühlt.Possibility that the walls of the air duct become very hot in the end area, which is limited by wall cooling. can be. In particular, a cooling system arranged concentrically to the air duct can be used, in which air, air-fuel mixture or steam cools the end region of the air duct.
Bei einer besonders bevorzugten Ausführungsform sind die Einlasse für Brennstoff als Einmischelemente im Luftkanal des Pilotbrenners ausgeführt. Sie können beispielsweise in der Form von kleinen Röhrchen ausgebildet sein, die mit einer Vielzahl von Einlaßöffnungen den Brennstoff sehr fein im Luft anal verteilen. Auch die Anordnung von zusätzlichen Drallerzeuger- schaufeln mit Einlaßöffnungen für Brennstoff ist möglich.In a particularly preferred embodiment, the inlets for fuel are designed as mixing elements in the air duct of the pilot burner. For example, they can be designed in the form of small tubes, which distribute the fuel very finely in the air with a large number of inlet openings. The arrangement of additional swirl generator blades with inlet openings for fuel is also possible.
Ein bevorzugtes Ausführungsbeispiel der Erfindung, auf die sie jedoch nicht beschränkt ist, wird im folgenden anhand der Zeichnung näher erläutert.A preferred embodiment of the invention, to which it is not limited, is explained in more detail below with reference to the drawing.
Die Zeichnung zeigt einen Brenner, wie er aus der EP 093 838 vom prinzipiellen Aufbau her bekannt ist. Die aus dieserThe drawing shows a burner as known in principle from EP 093 838. The one from this
Schrift bekannten Komponenten sind daher nur schematisch dargestellt und teilweise auch weggelassen. Beim Lastbetrieb eines solchen Brenners wird der Hauptbrenner 1 mit Hauptverbrennungsluft 2 versorgt, in welche fein verteilt über eine Hauptbrenngaszufuhr 3 und eine Hauptbrenngaseindüsung 20 Brenngas und/oder über eine Hauptbrennölzufuhr 4 und eine Hauptbrennöleindüsung 21 Brennöl eingedüst wird. Dies erfolgt im Bereich eines Hauptdrallerzeugers 5, insbesondere in Form eines Diagonalgitters. Auf diese Weise wird der Brennstoff mit der Hauptverbrennungsluft vorgemischt, so daß sich eine Schadstoffarme Verbrennung erreichen läßt. Im Zentrum des Hauptbrenners 1 befindet sich in an sich bekannter Weise ein Pilotbrenner zum Zünden und zur Stabilisierung der Hauptflamme, dessen Verbrennungsluft durch einen Luftkanal 6 zugeführt wird. Für den Betrieb dieses Pilotbrenners als Diffusionsbrenner gibt es einen zentralen Brennstoffkanal 7, der aber gemäß dem Hauptgedanken der vorliegenden Erfindung mög- liehst selten benutzt werden soll, da der Betrieb des Pilotbrenners als Diffusionsbrenner zu viel NOx erzeugt. Um dies zu vermeiden, weist der Luftkanal 6 Einlasse 10, 11 auf, durch welche Brennstoff der Verbrennungsluft des Pilotbren- ners zugemischt werden kann. Der konzentrische lanzenartige Aufbau des Brenners gibt dabei die Möglichkeit, diesen Brennstoff durch einen äußeren Brennstoffkanal 8 und äußere Einlasse 10 und/oder durch einen inneren Brennstoffkanal 9 und innere Einlasse 11 zuzuführen. Statt einfacher Einlaßöffnun- gen in den Wänden des Luftkanals 6 können auch Einmischelemente 15 verwendet werden, im vorliegenden Ausführungsbeispiel in Form kleiner perforierter Röhrchen zur gleichmäßigeren Verteilung von Brennstoff. Als Brennstoff kommen grundsätzlich Brennöl oder Brenngas in Betracht, wozu die entspre- chenden Einlasse beziehungsweise Einmischelemente geeignet dimensioniert sein müssen.Components known from the text are therefore only shown schematically and in some cases also omitted. During the load operation of such a burner, the main burner 1 is supplied with main combustion air 2, into which fuel gas is injected finely distributed via a main fuel gas supply 3 and a main fuel gas injector 20 and / or via a main fuel oil supply 4 and a main fuel oil injector 21. This takes place in the area of a main swirl generator 5, in particular in the form of a diagonal grid. In this way, the fuel is premixed with the main combustion air, so that low-pollution combustion can be achieved. In the center of the main burner 1 there is a pilot burner for igniting and stabilizing the main flame, the combustion air of which is supplied through an air duct 6, in a manner known per se. There is a central fuel channel 7 for the operation of this pilot burner as a diffusion burner, which, however, is possible according to the main idea of the present invention. is rarely used because the operation of the pilot burner as a diffusion burner generates too much NOx. In order to avoid this, the air duct 6 has inlets 10, 11 through which fuel can be mixed into the combustion air of the pilot burner. The concentric lance-like structure of the burner enables this fuel to be supplied through an outer fuel channel 8 and outer inlets 10 and / or through an inner fuel channel 9 and inner inlets 11. Instead of simple inlet openings in the walls of the air duct 6, mixing elements 15 can also be used, in the present exemplary embodiment in the form of small perforated tubes for more even distribution of fuel. In principle, fuel oil or fuel gas can be considered as fuel, for which purpose the corresponding inlets or mixing elements must be suitably dimensioned.
Ganz wesentlich für die vorliegende Erfindung ist die Anordnung eines Drallerzeugers 12 mit Abstand oberhalb der Ein- lasse 10, 11. Diese Anordnung erlaubt die Erzeugung einesThe arrangement of a swirl generator 12 at a distance above the inlets 10, 11 is very important for the present invention. This arrangement allows the generation of a
Dralls schon vor dem Zumischen von Brennstoff, wodurch sich eine gleichmäßigere und Schadstoffarme Verbrennung ergibt. Die Anordnung der Drallerzeuger in Strömungsrichtung vor den Einlassen für Brennstoff hat außerdem den Vorteil, daß bei Störungen die Flammen des Pilotbrenners keinesfalls weiter als bis zum Drallerzeuger 12 zurückschlagen können.Swirls before the addition of fuel, which results in a more even and low-pollution combustion. The arrangement of the swirl generators in the flow direction upstream of the fuel inlets also has the advantage that, in the event of malfunctions, the flames of the pilot burner can in no case strike back further than the swirl generator 12.
Zur weiteren Stabilisierung der Pilotflamme kann der Luftkanal 6 in seinem Endbereich als Diffusor 13 ausgebildet wer- den. Zur Vermeidung einer Überhitzung der Wände des Diffusors 13 können diese besonders bevorzugt mit einem Kühlsystem 14 ausgestattet sein, insbesondere mit einem konzentrisch um den Diffusor liegenden System, welches mittels Luft, Luft-Brennstoff-Gemisch oder Dampf gekühlt wird.To further stabilize the pilot flame, the air duct 6 can be designed as a diffuser 13 in its end region. To prevent the walls of the diffuser 13 from overheating, they can particularly preferably be equipped with a cooling system 14, in particular with a system which is concentrically arranged around the diffuser and which is cooled by means of air, air-fuel mixture or steam.
Ein erfindungsgemäßer Brenner wird in an sich bekannter Weise über entsprechende Steuerventile mit seinem Lufteinlaß 16 an eine Luftversorgung angeschlossen und mit seinen Brennstoff- einlässen 17, 18, 19 für den zentralen Brennstoffkanal 7, den äußeren Brennstoffkanal 8 beziehungsweise den inneren Brennstoffkanal 9 an eine Brennstoffversorgung.A burner according to the invention is connected in a manner known per se via corresponding control valves with its air inlet 16 an air supply connected and with its fuel inlets 17, 18, 19 for the central fuel channel 7, the outer fuel channel 8 or the inner fuel channel 9 to a fuel supply.
Erfindungsgemäße Brenner ermöglichen einen in weiten Lastbereichen stabilen und Schadstoffarmen Betrieb und eignen sich insbesondere für Brennkammern von Gasturbinenanlagen. Burners according to the invention enable stable and low-pollutant operation in wide load ranges and are particularly suitable for combustion chambers of gas turbine systems.

Claims

Patentansprüche claims
1. Brenneranordnung für eine Feuerungsanlage, insbesondere eine Gasturbinenbrennkammer, mit einem Hauptbrenner (1) und einem Pilotbrenner, der zum Zünden und/oder zur Stabilisierung des Hauptbrenners (1) dient, wobei1. Burner arrangement for a furnace, in particular a gas turbine combustion chamber, with a main burner (1) and a pilot burner, which is used to ignite and / or stabilize the main burner (1), wherein
- der Pilotbrenner immer oder zeitweise als Vormischbrenner betreibbar ist,- the pilot burner can always or temporarily be operated as a premix burner,
- zur Zufuhr von Brennstoff und Verbrennungsluft zum Pilotbrenner ein lanzenartig aufgebautes Zufuhrsystem (6, 7, 8, 9) vorhanden ist, welches zumindest einen im Querschnitt etwa kreisringförmigen Luftkanal (6) aufweist,a lance-like supply system (6, 7, 8, 9) is provided for supplying fuel and combustion air to the pilot burner and has at least one air duct (6) which is approximately circular in cross section,
- Einlasse (10; 11) für Brennstoff an dem Luftkanal (6) angeordnet sind, d a d u r c h g e k e n n z e i c h n e t, daß in Luftströmungsrichtung vor den Einlassen (10; 11) für den Brennstoff ein Drallerzeuger (12) in dem Luftkanal (6) angeordnet ist.- Inlets (10; 11) for fuel are arranged on the air duct (6), so that a swirl generator (12) is arranged in the air duct (6) in the air flow direction before the inlets (10; 11) for the fuel.
2. Brenneranordnung nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, daß für den Brennstoff Brenngas mehrere etwa gleichmäßig über den Umfang verteilte Einlasse (10; 11) an dem Luftkanal (6) vorhanden sind.2. Burner arrangement according to claim 1, d a d u r c h g e k e n n z e i c h n e t that several approximately uniformly distributed inlets (10; 11) are present on the air duct (6) for the fuel fuel gas.
3. Brenneranordnung nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, daß der Luftka- nal (6) in Strömungsrichtung unterhalb der Einlasse (10; 11) frei von Einbauten ist.3. Burner arrangement according to claim 1 or 2, so that the air duct (6) in the flow direction below the inlets (10; 11) is free of internals.
4. Brenneranordnung nach Anspruch 1, 2 oder 3, d a d u r c h g e k e n n z e i c h n e t, daß zur Zufuhr von Brennstoff ein zum Luftkanal (6) etwa konzentrisch innen (9) und/oder außen (8) angeordneter Ringkanal vorhanden ist, der durch die Einlasse (11 bzw. 10) mit dem Luftkanal (6) in Verbindung steht. 4. Burner arrangement according to claim 1, 2 or 3, characterized in that for supplying fuel to the air channel (6) is arranged approximately concentrically inside (9) and / or outside (8) arranged annular channel which through the inlets (11 or 10) is connected to the air duct (6).
5. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß die Einlasse5. burner arrangement according to one of the preceding claims, d a d u r c h g e k e n n z e i c h n e t that the inlets
(10; 11) mit Abstand von dem Drallerzeuger (12) angeordnet sind, vorzugsweise mit solchem Abstand, daß ein Zurückschlagen der Flammen in den Drallerzeuger (12) vermieden wird.(10; 11) are arranged at a distance from the swirl generator (12), preferably at a distance such that flames are prevented from striking back into the swirl generator (12).
6. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß der Dral- lerzeuger (12) axialen und/oder radialen und/oder tangen- tialen Drall erzeugt, vorzugsweise unter Vermeidung von Strömungsablösungen an den Wänden des Luftkanals (6).6. Burner arrangement according to one of the preceding claims, that the swirl generator (12) generates axial and / or radial and / or tangential swirl, preferably while avoiding flow separations on the walls of the air duct (6).
7. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß der Luftkanal (6) an seinem in die Feuerungsanlage mündenden Endbereich als Diffusor (13) ausgebildet ist, insbesondere einen sich zunehmend im Querschnitt erweiternden Endbereich (13) aufweist .7. Burner arrangement according to one of the preceding claims, that the air duct (6) is designed as a diffuser (13) at its end region opening into the firing system, in particular has an end region (13) that is increasingly widening in cross section.
8. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß der Endbereich (13) des Luftkanals mit einer Wandkühlung (14) versehen ist, insbesondere mittels eines konzentrisch angeordneten Kühlsystems für Luft, Luft-Brennstoff-Gemisch und/oder Dampf.8. Burner arrangement according to one of the preceding claims, that the end area (13) of the air duct is provided with a wall cooling (14), in particular by means of a concentrically arranged cooling system for air, air-fuel mixture and / or steam.
9. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, daß die Einlasse (10; 11) als im Luftkanal angeordnete Einmischelemente (15) ausgebildet sind, vorzugsweise als Röhrchen oder Drallerzeugerschaufeln mit einer Vielzahl von Einlaßöffnungen. 9. Burner arrangement according to one of the preceding claims, so that the inlets (10; 11) are designed as mixing elements (15) arranged in the air duct, preferably as tubes or swirl generator blades with a large number of inlet openings.
EP98943638A 1997-07-17 1998-07-07 Arrangement of burners for heating installation, in particular a gas turbine combustion chamber Expired - Lifetime EP0995066B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19730734 1997-07-17
DE19730734 1997-07-17
PCT/DE1998/001871 WO1999004196A1 (en) 1997-07-17 1998-07-07 Arrangement of burners for heating installation, in particular a gas turbine combustion chamber

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EP0995066A1 true EP0995066A1 (en) 2000-04-26
EP0995066B1 EP0995066B1 (en) 2001-09-26

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JP (1) JP2001510885A (en)
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000049337A1 (en) * 1999-02-16 2000-08-24 Siemens Aktiengesellschaft Burner arrangement and method for operating a burner arrangement
US6354072B1 (en) * 1999-12-10 2002-03-12 General Electric Company Methods and apparatus for decreasing combustor emissions
EP1239219A4 (en) 1999-12-15 2003-03-12 Osaka Gas Co Ltd Fluid distributor, burner device, gas turbine engine, and cogeneration system
US6327860B1 (en) * 2000-06-21 2001-12-11 Honeywell International, Inc. Fuel injector for low emissions premixing gas turbine combustor
US6367262B1 (en) * 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6363726B1 (en) * 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
DE10104695B4 (en) * 2001-02-02 2014-11-20 Alstom Technology Ltd. Premix burner for a gas turbine
US6484489B1 (en) * 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US6848260B2 (en) 2002-09-23 2005-02-01 Siemens Westinghouse Power Corporation Premixed pilot burner for a combustion turbine engine
EP1460339A1 (en) * 2003-03-21 2004-09-22 Siemens Aktiengesellschaft Gas turbine
US7303388B2 (en) * 2004-07-01 2007-12-04 Air Products And Chemicals, Inc. Staged combustion system with ignition-assisted fuel lances
EP1624252A1 (en) * 2004-08-06 2006-02-08 Siemens Aktiengesellschaft Burner, Gas Turbine and Method for Operating a Burner
ITTO20050208A1 (en) * 2005-03-30 2006-09-30 Ansaldo Energia Spa GAS BURNER GROUP FOR A GAS TURBINE
EP1764553A1 (en) * 2005-09-14 2007-03-21 Enel Produzione S.p.A. High-stability premix burner for gas turbines
EP2023041A1 (en) * 2007-07-27 2009-02-11 Siemens Aktiengesellschaft Premix burner and method for operating a premix burner
JP5193088B2 (en) * 2009-02-20 2013-05-08 三菱重工業株式会社 Combustor and gas turbine
US20100307160A1 (en) * 2009-06-03 2010-12-09 Vinayak Barve Convex Pilot Cone
EP2397764A1 (en) 2010-06-18 2011-12-21 Siemens Aktiengesellschaft Turbine burner
GB201511841D0 (en) 2015-07-07 2015-08-19 Rolls Royce Plc Fuel spray nozel for a gas turbine engine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3241162A1 (en) 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim PRE-MIXING BURNER WITH INTEGRATED DIFFUSION BURNER
ATE42821T1 (en) * 1985-03-04 1989-05-15 Siemens Ag BURNER ARRANGEMENT FOR COMBUSTION PLANTS, IN PARTICULAR FOR COMBUSTION CHAMBERS OF GAS TURBINE PLANTS, AND METHOD FOR THEIR OPERATION.
JP3335713B2 (en) * 1993-06-28 2002-10-21 株式会社東芝 Gas turbine combustor
GB9326367D0 (en) * 1993-12-23 1994-02-23 Rolls Royce Plc Fuel injection apparatus
US5467926A (en) * 1994-02-10 1995-11-21 Solar Turbines Incorporated Injector having low tip temperature
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
JP2950720B2 (en) * 1994-02-24 1999-09-20 株式会社東芝 Gas turbine combustion device and combustion control method therefor
JP3449802B2 (en) * 1994-10-31 2003-09-22 東京瓦斯株式会社 Gas combustion equipment
FR2727192B1 (en) * 1994-11-23 1996-12-20 Snecma INJECTION SYSTEM FOR A TWO-HEAD COMBUSTION CHAMBER
JP3939756B2 (en) * 1995-09-22 2007-07-04 シーメンス アクチエンゲゼルシヤフト Especially for gas turbine burners
GB9607010D0 (en) * 1996-04-03 1996-06-05 Rolls Royce Plc Gas turbine engine combustion equipment

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9904196A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct

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JP2001510885A (en) 2001-08-07
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WO1999004196A1 (en) 1999-01-28

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