EP0995066B1 - 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 Download PDF

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Publication number
EP0995066B1
EP0995066B1 EP98943638A EP98943638A EP0995066B1 EP 0995066 B1 EP0995066 B1 EP 0995066B1 EP 98943638 A EP98943638 A EP 98943638A EP 98943638 A EP98943638 A EP 98943638A EP 0995066 B1 EP0995066 B1 EP 0995066B1
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EP
European Patent Office
Prior art keywords
burner
air duct
fuel
inlets
air
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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.)
Expired - Lifetime
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EP98943638A
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German (de)
French (fr)
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EP0995066A1 (en
Inventor
Bernd Prade
Holger Streb
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Siemens AG
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Siemens AG
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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

  • the present invention is in the field of burner assemblies for combustion plants, in particular for gas turbine combustion chambers. Such burner arrangements are often for different ones Fuels and different modes of operation, taking into account increasingly stringent regulations worldwide great efforts to emit pollutants there to improve the arrangements and modes of operation so that pollutant emissions are reduced.
  • In the present Invention is particularly concerned with reducing the Emissions of nitrogen oxides, hereinafter referred to as NOx.
  • Particularly environmentally friendly burners with low emissions NOx are from EP 0 108 361 B1 and EP 0 193 838 B1 known. From these writings it can be seen that the NOx emissions can be significantly reduced if burner arrangements are not operated as diffusion burners, but as a premix burner. With diffusion burners Fuel more or less evenly distributed in one Airflow sprayed directly and in the border area between Air and fuel burned. With premix burners Air and fuel are initially mixed as evenly as possible and only then together in a flame area Combustion chamber burned. By the previous even Mixing can lower the overall combustion temperature be kept as in the border area between fuel and air, with a desired ratio at the same time of fuel and air can be maintained evenly. This leads to a lower emission of pollutants, in particular at NOx.
  • premix burners The disadvantage of premix burners is that the combustion cannot be kept stable in all load conditions, so that the control range of premix burners is usually smaller than that of diffusion burners.
  • pilot burners are used to expand the control range used, mostly in the center of a main burner are arranged and with their small but stable Flame stabilize the combustion of the main burner. Also pilot burners are used to support the ignition of a main burner second hand.
  • the burner arrangement according to the invention for a furnace, in particular a gas turbine combustor, with a Main burner and a pilot burner for ignition and / or serves to stabilize the main burner is in your Basic structure of the burner arrangement from EP 0 193 838 B1 very much similar.
  • the pilot burner is always or temporarily as a premix burner operable and the supply of fuel and Combustion air to the pilot burner takes place through a lance-like constructed feed system with concentric nested in cross section approximately circular channels.
  • the air duct in particular is located below these ducts for supplying combustion air for the pilot burner.
  • On Inlets for fuel are arranged in this air duct the fuel through to the inside or outside concentrically Air duct lying ducts is supplied.
  • a swirl generator is arranged in front of the inlets. In this way, swirls already arrive Air to the inlets, so that a strong swirling directly of air and fuel at the inlets.
  • the Fuel inlets also in aerodynamically optimized swirl elements to get integrated.
  • the pilot burner is typically used for premixing designed with fuel gas, with several approximately on the air duct Inlets distributed evenly over the circumference are provided are.
  • the air duct is free of internals, especially designed without a flame holder.
  • the installation of turbulence generating elements in front of the fuel inlets it is possible to improve the mixture.
  • the pilot burner's lance-like delivery system two or more ring channels arranged concentrically to each other, with an annular channel immediately inside and / or outside the air duct to supply fuel, in particular Fuel gas is used.
  • fuel in particular Fuel gas
  • Through inlets in the partition between Air duct and inner or outer ring duct comes under higher pressure than the combustion air Fuel in the air duct and is distributed there the swirl flow generated by the swirl generator very much evenly.
  • the inlets should be with a certain Distance from the swirl generator to be arranged safely prevent flames from returning to the swirl generator can. The exact distance depends on the flow velocity the air flowing in the air duct and the geometric Conditions in the air duct.
  • the swirl generator can be axial and / or radial and / or generate tangential swirl, the swirl strength and the length of time for mixing with the fuel Available pre-mixing section should be chosen so that the meridional flow velocity is great to kick back to prevent the flames, and that no so-called Hub detachment can occur, that is the flow itself does not detach from the walls of the air duct.
  • a diffuser in particular formed by an in Flow direction increasing expansion of the cross section in the End area.
  • pilot flame does not differ from the state of the art is held by a flame holder Possibility that the walls of the air duct in the end area heat up strongly, which is limited by wall cooling can be.
  • a concentric to Air duct arranged cooling system can be used, in which Air, air-fuel mixture or steam the end area of the air duct cools.
  • the inlets are for fuel as mixing elements in the air duct of the Pilot burner.
  • the drawing shows a burner as it comes from the The basic structure of EP 0 193 838 B1 is known.
  • the Components known from this document are therefore only schematic shown and partially omitted.
  • the main burner 1 becomes the load operation of such a burner with main combustion air 2, in which finely divided via a main fuel gas supply 3 and a main fuel gas injection 20 fuel gas and / or via a main fuel oil supply 4 and a main fuel oil injector 21 fuel oil is injected.
  • 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 premixed with the main combustion air so that low-pollution combustion can be achieved.
  • the main burner 1 is in a known per se Way a pilot burner to ignite and stabilize the Main flame, the combustion air through an air duct 6 is fed.
  • this pilot burner as a diffusion burner there is a central fuel channel 7 which but as far as possible according to the main idea of the present invention should rarely be used because of the operation of the pilot burner Generates too much NOx as a diffusion burner.
  • the air duct has 6 inlets 10, 11, through which fuel the combustion air of the pilot burner can be added.
  • the concentric lance-like Building the burner gives you the opportunity to use this fuel through an outer fuel channel 8 and outer inlets 10 and / or through an inner fuel channel 9 and to supply inner inlets 11.
  • Mixing elements can also be in the walls of the air duct 6 15 are used in the present exemplary embodiment in the form of small perforated tubes for more uniform Distribution of fuel. Basically come as fuel Fuel oil or fuel gas into consideration, for which the corresponding Inlets or mixing elements suitable must be dimensioned.
  • the arrangement is very important for the present invention a swirl generator 12 at a distance above the inlets 10, 11.
  • This arrangement allows the generation of a Swirls before adding fuel, which causes results in a more even and low-pollution combustion.
  • the arrangement of the swirl generator in the flow direction before Inlets for fuel also have the advantage that Do not disturb the pilot burner flames under any circumstances than can strike back to the swirl generator 12.
  • the air duct can be used to further stabilize the pilot flame 6 are formed in its end region as a diffuser 13.
  • these can be particularly preferably with a cooling system 14 be equipped, especially with a concentric around the Diffuser lying system, which uses air, air-fuel mixture or steam is cooled.
  • a burner according to the invention is made 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 one in wide load ranges stable and low-pollution operation and are suitable especially for combustion chambers of gas turbine plants.

Description

Die vorliegende Erfindung liegt auf dem Gebiet der Brenneranordnungen für Feuerungsanlagen, insbesondere für Gasturbinenbrennkammern. Solche Brenneranordnungen sind oft für verschiedene Brennstoffe und verschiedene Betriebsweisen ausgelegt, 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, in particular for gas turbine combustion chambers. Such burner arrangements are often for different ones Fuels and different modes of operation, taking into account increasingly stringent regulations worldwide great efforts to emit pollutants there to improve the arrangements and modes of operation so that pollutant emissions are reduced. In the present Invention is particularly concerned with reducing the Emissions of nitrogen oxides, hereinafter referred to as NOx.

Besonders umweltfreundliche Brenner mit einem geringem Ausstoß an NOx sind aus der EP 0 108 361 B1 und der EP 0 193 838 B1 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 Vormischbrennern werden 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 niedriger 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.Particularly environmentally friendly burners with low emissions NOx are from EP 0 108 361 B1 and EP 0 193 838 B1 known. From these writings it can be seen that the NOx emissions can be significantly reduced if burner arrangements are not operated as diffusion burners, but as a premix burner. With diffusion burners Fuel more or less evenly distributed in one Airflow sprayed directly and in the border area between Air and fuel burned. With premix burners Air and fuel are initially mixed as evenly as possible and only then together in a flame area Combustion chamber burned. By the previous even Mixing can lower the overall combustion temperature be kept as in the border area between fuel and air, with a desired ratio at the same time of fuel and air can be maintained evenly. This leads to a lower emission of pollutants, in particular at 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, so 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.So-called pilot burners are used to expand the control range used, mostly in the center of a main burner are arranged and with their small but stable Flame stabilize the combustion of the main burner. Also pilot burners are used to support the ignition of a main burner second hand.

Aus der EP 0 193 838 B1 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 vorgeschlagen, 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 0 193 838 B1 that such pilot burners a significant proportion of NOx based on the total Can produce pollutant emissions when used as a diffusion burner operate. Therefore it is already suggested there a pilot burner also as a premix burner train, but kept in a stable operating range can be, even if the main burner is in another Operating area is operated. This measure can too lead to a significant reduction in pollutant emissions.

Ausgehend von der EP 0 193 838 B1, 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 sicherer und mit noch geringerem Ausstoß an NOx betrieben werden kann. Die bekannte Anordnung weist nämlich eine Vormischstrecke auf, an deren Ausgang zur Brennkammer eine Drallbeschaufelung angeordnet ist, die gleichzeitig als Flammenhalter dient. Durch diese Anordnung kann eine optimale Vermischung 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 the full content express reference is made to the task of the present Invention, the burner assembly described there to improve that the pilot burner in premix operation more safely and operate with even lower NOx emissions can. The known arrangement namely has a premixing section swirl blading at the exit to the combustion chamber is arranged, which also serves as a flame holder serves. This arrangement allows optimal mixing of air and fuel, especially not fuel gas can be achieved, in addition to certain operational problems knock the pilot flame back into the premixing section could what is undesirable.

Zur Lösung der Aufgabe dient eine Brenneranordung gemäß dem Anspruch 1. Vorteilhafte und bevorzugte Ausgestaltungen sind in den abhängigen Ansprüchen beschrieben. A burner arrangement according to the Claim 1. Advantageous and preferred configurations are described in the dependent claims.

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 ihrem Grundaufbau der Brenneranordnung aus der EP 0 193 838 B1 sehr ähnlich. Der Pilotbrenner ist immer oder zeitweise als Vormischbrenner betreibbar und die Zufuhr von Brennstoff und Verbrennungsluft zum Pilotbrenner erfolgt durch ein lanzenartig 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 Einlässe für Brennstoff angeordnet, wobei der Brennstoff durch konzentrisch innen oder außen zu dem Luftkanal liegende Kanäle zugeführt wird. Grundsätzlich ist auch eine Zuführung durch einzelne Rohrleitungen zu den Einlässen möglich. Erfindungsgemäß ist in dem Luftkanal in Luftströmungsrichtung vor den Einlässen ein Drallerzeuger angeordnet. Auf diese Weise gelangt schon mit einem Drall versehene Luft zu den Einlässen, so daß direkt eine starke Verwirbelung von Luft und Brennstoff an den Einlässen erfolgt. Zur Steigerung der Länge des Vermischungsweges können die Brennstoffeinlässe auch in aerodynamisch optimierte Drallerzeugungselemente integriert werden.The burner arrangement according to the invention for a furnace, in particular a gas turbine combustor, with a Main burner and a pilot burner for ignition and / or serves to stabilize the main burner is in your Basic structure of the burner arrangement from EP 0 193 838 B1 very much similar. The pilot burner is always or temporarily as a premix burner operable and the supply of fuel and Combustion air to the pilot burner takes place through a lance-like constructed feed system with concentric nested in cross section approximately circular channels. The air duct in particular is located below these ducts for supplying combustion air for the pilot burner. On Inlets for fuel are arranged in this air duct the fuel through to the inside or outside concentrically Air duct lying ducts is supplied. Basically is also a feed through individual pipes to the inlets possible. According to the invention in the air duct in the air flow direction A swirl generator is arranged in front of the inlets. In this way, swirls already arrive Air to the inlets, so that a strong swirling directly of air and fuel at the inlets. To increase the length of the mixing path, the Fuel inlets also in aerodynamically optimized swirl elements to get integrated.

Typischerweise wird der Pilotbrenner für den Vormischbetrieb mit Brenngas ausgelegt, wobei an dem Luftkanal mehrere etwa gleichmäßig über den Umfang verteilte Einlässe vorgesehen sind.The pilot burner is typically used for premixing designed with fuel gas, with several approximately on the air duct Inlets distributed evenly over the circumference are provided are.

Unterhalb der Einlässe ist der Luftkanal frei von Einbauten, insbesondere ohne einen Flammenhalter ausgebildet. Der Einbau von turbulenzerzeugenden Elementen vor den Brennstoffeinlässen zur Verbesserung der Mischung ist gegebenenfalls möglich. Below the inlets, the air duct is free of internals, especially designed without a flame holder. The installation of turbulence generating elements in front of the fuel inlets it is possible to improve the mixture.

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 Einlässe 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 Einlässe 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 Strömungsgeschwindigkeit der im Luftkanal strömenden Luft und den geometrischen Verhältnissen im Luftkanal ab.According to a preferred embodiment of the invention the pilot burner's lance-like delivery system two or more ring channels arranged concentrically to each other, with an annular channel immediately inside and / or outside the air duct to supply fuel, in particular Fuel gas is used. Through inlets in the partition between Air duct and inner or outer ring duct comes under higher pressure than the combustion air Fuel in the air duct and is distributed there the swirl flow generated by the swirl generator very much evenly. The inlets should be with a certain Distance from the swirl generator to be arranged safely prevent flames from returning to the swirl generator can. The exact distance depends on the flow velocity 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 be axial and / or radial and / or generate tangential swirl, the swirl strength and the length of time for mixing with the fuel Available pre-mixing section should be chosen so that the meridional flow velocity is great to kick back to prevent the flames, and that no so-called Hub detachment can occur, that is the flow itself does not detach 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 Erfindung einen Diffusor auf, insbesondere gebildet durch eine in Strömungsrichtung zunehmende Erweiterung des Querschnittes im Endbereich.In order to largely increase the stability of the pilot flame, points the air duct at its opening into the furnace End area in a special embodiment of the invention a diffuser, in particular formed by an in Flow direction increasing expansion of the cross section in the End area.

Da die Pilotflamme anders als beim Stand der Technik nicht mehr durch einen Flammenhalter gehalten wird, besteht die Möglichkeit, daß sich die Wände des Luftkanals im Endbereich stark erhitzen, was durch eine Wandkühlung in Grenzen gehalten 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.Because the pilot flame does not differ from the state of the art is held by a flame holder Possibility that the walls of the air duct in the end area heat up strongly, which is limited by wall cooling can be. In particular, a concentric to Air duct arranged cooling system can be used, in which Air, air-fuel mixture or steam the end area of the air duct cools.

Bei einer besonders bevorzugten Ausführungsform sind die Einlässe 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 Luftkanal verteilen. Auch die Anordnung von zusätzlichen Drallerzeuger- schaufeln mit Einlaßöffnungen für Brennstoff ist möglich.In a particularly preferred embodiment, the inlets are for fuel as mixing elements in the air duct of the Pilot burner. You can, for example, in the Be formed in the form of small tubes with a. Large number of inlet openings in the fuel very fine Distribute air duct. Even the arrangement of additional Swirl generator blades with inlet openings for fuel is 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 however, it is not limited, is based on the following Drawing explained in more detail.

Die Zeichnung zeigt einen Brenner, wie er aus der EP 0 193 838 B1 vom prinzipiellen Aufbau her bekannt ist. Die aus dieser 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 möglichst selten benutzt werden soll, da der Betrieb des Pilotbrenners als Diffusionsbrenner zu viel NOx erzeugt. Um dies zu vermeiden, weist der Luftkanal 6 Einlässe 10, 11 auf, durch welche Brennstoff der Verbrennungsluft des Pilotbrenners zugemischt werden kann. Der konzentrische lanzenartige Aufbau des Brenners gibt dabei die Möglichkeit, diesen Brennstoff durch einen äußeren Brennstoffkanal 8 und äußere Einlässe 10 und/oder durch einen inneren Brennstoffkanal 9 und innere Einlässe 11 zuzuführen. Statt einfacher Einlaßöffnungen 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 entsprechenden Einlässe beziehungsweise Einmischelemente geeignet dimensioniert sein müssen.The drawing shows a burner as it comes from the The basic structure of EP 0 193 838 B1 is known. The Components known from this document are therefore only schematic shown and partially omitted. At the The main burner 1 becomes the load operation of such a burner with main combustion air 2, in which finely divided via a main fuel gas supply 3 and a main fuel gas injection 20 fuel gas and / or via a main fuel oil supply 4 and a main fuel oil injector 21 fuel oil is injected. 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 premixed with the main combustion air so that low-pollution combustion can be achieved. Downtown the main burner 1 is in a known per se Way a pilot burner to ignite and stabilize the Main flame, the combustion air through an air duct 6 is fed. For the operation of this pilot burner as a diffusion burner there is a central fuel channel 7 which but as far as possible according to the main idea of the present invention should rarely be used because of the operation of the pilot burner Generates too much NOx as a diffusion burner. To do this to avoid, the air duct has 6 inlets 10, 11, through which fuel the combustion air of the pilot burner can be added. The concentric lance-like Building the burner gives you the opportunity to use this fuel through an outer fuel channel 8 and outer inlets 10 and / or through an inner fuel channel 9 and to supply inner inlets 11. Instead of simple inlet openings Mixing elements can also be in the walls of the air duct 6 15 are used in the present exemplary embodiment in the form of small perforated tubes for more uniform Distribution of fuel. Basically come as fuel Fuel oil or fuel gas into consideration, for which the corresponding Inlets or mixing elements suitable must be dimensioned.

Ganz wesentlich für die vorliegende Erfindung ist die Anordnung eines Drallerzeugers 12 mit Abstand oberhalb der Einlässe 10, 11. Diese Anordnung erlaubt die Erzeugung eines Dralls schon vor dem Zumischen von Brennstoff, wodurch sich eine gleichmäßigere und schadstoffarme Verbrennung ergibt. Die Anordnung der Drallerzeuger in Strömungsrichtung vor den Einlässen für Brennstoff hat außerdem den Vorteil, daß bei Störungen die Flammen des Pilotbrenners keinesfalls weiter als bis zum Drallerzeuger 12 zurückschlagen können.The arrangement is very important for the present invention a swirl generator 12 at a distance above the inlets 10, 11. This arrangement allows the generation of a Swirls before adding fuel, which causes results in a more even and low-pollution combustion. The arrangement of the swirl generator in the flow direction before Inlets for fuel also have the advantage that Do not disturb the pilot burner flames under any circumstances than can strike back to the swirl generator 12.

Zur weiteren Stabilisierung der Pilotflamme kann der Luftkanal 6 in seinem Endbereich als Diffusor 13 ausgebildet werden. 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.The air duct can be used to further stabilize the pilot flame 6 are formed in its end region as a diffuser 13. To avoid overheating the walls of the diffuser 13, these can be particularly preferably with a cooling system 14 be equipped, especially with a concentric around the Diffuser lying system, which uses air, air-fuel mixture or steam is cooled.

Ein erfindungsgemäßer Brenner wird in an sich bekannter Weise über entsprechende Steuerventile mit seinem Lufteinlaß 16 an eine Luftversorgung angeschlossen und mit seinen Brennstoffeinlässen 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 made 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 one in wide load ranges stable and low-pollution operation and are suitable especially for combustion chambers of gas turbine plants.

Claims (9)

  1. Burner arrangement for a firing unit, in particular a gas-turbine combustion chamber, having a main burner (1) and a pilot burner, which serves to ignite and/or to stabilize the main burner (1), in which arrangement:
    the pilot burner can be operated constantly or from time to time as a premix burner,
    there is a feed system (6, 7, 8, 9) of lance-like construction surrounded concentrically by the main burner (1) for the feed of fuel and combustion air to the pilot burner, which feed system (6, 7, 8, 9) has at least one air duct (6) of approximately annular cross-section,
    inlets (10; 11) for fuel are arranged at the air duct (6),
    main swirl generators (5), in the region of which fuel can be let into the main burner (1), are arranged in an air duct of the main burner (1),
    characterized in that a swirl generator (12) is arranged in the air duct (6) in the air-flow direction upstream of the inlets (10; 11) for the fuel.
  2. Burner arrangement according to Claim 1,
    characterized in that, for fuel gas as the fuel, a plurality of inlets (10; 11), distributed approximately uniformly over the periphery, are present at the air duct (6).
  3. Burner arrangement according to Claim 1 or 2,
    characterized in that the air duct (6) is free of built-in components in the direction of flow below the inlets (10; 11).
  4. Burner arrangement according to Claim 1, 2 or 3,
    characterized in that an annular duct arranged approximately concentrically with respect to the air duct (6) on the inside (9) and/or on the outside (8) is present for the fuel feed and is connected to the air duct (6) by the inlets (11 and 10 resp.).
  5. Burner arrangement according to one of the preceding claims, characterized in that the inlets (10; 11) are arranged at a distance from the swirl generator (12), preferably at such a distance that a flashback of the flames into the swirl generator (12) is avoided.
  6. Burner arrangement according to one of the preceding claims, characterized in that the swirl generator (12) generates an axial and/or radial and/or tangential swirl, preferably while avoiding flow separations at the walls of the air duct (6).
  7. Burner arrangement according to one of the preceding claims, characterized in that the air duct (6), at its end region leading into the firing unit, is designed as a diffuser (13), in particular an end region (13) which widens increasingly in cross-section.
  8. Burner arrangement according to one of the preceding claims, characterized in that the end region (13) of the air duct (6) is provided with wall cooling (14), in particular by means of a concentrically arranged cooling system for air, air/fuel mixture and/or steam.
  9. Burner arrangement according to one of the preceding claims, characterized in that the inlets (10; 11) are designed as intermixing elements (15) arranged in the air duct (6), preferably as tubes or swirl-generator blades having a multiplicity 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 EP0995066A1 (en) 2000-04-26
EP0995066B1 true EP0995066B1 (en) 2001-09-26

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JP (1) JP2001510885A (en)
DE (1) DE59801583D1 (en)
WO (1) WO1999004196A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8474266B2 (en) 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle

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
JP4629945B2 (en) 1999-12-15 2011-02-09 大阪瓦斯株式会社 Fluid distributor and 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
US6363726B1 (en) * 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
US6367262B1 (en) * 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
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
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
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
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
US5467926A (en) * 1994-02-10 1995-11-21 Solar Turbines Incorporated Injector having low tip temperature
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
ES2169273T3 (en) * 1995-09-22 2002-07-01 Siemens Ag BURNER, ESPECIALLY FOR A GAS TURBINE.
GB9607010D0 (en) * 1996-04-03 1996-06-05 Rolls Royce Plc Gas turbine engine combustion equipment

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8474266B2 (en) 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle

Also Published As

Publication number Publication date
DE59801583D1 (en) 2001-10-31
WO1999004196A1 (en) 1999-01-28
JP2001510885A (en) 2001-08-07
EP0995066A1 (en) 2000-04-26

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