EP1344002B1 - Burner with progressive fuel injection - Google Patents

Burner with progressive fuel injection Download PDF

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Publication number
EP1344002B1
EP1344002B1 EP01970076A EP01970076A EP1344002B1 EP 1344002 B1 EP1344002 B1 EP 1344002B1 EP 01970076 A EP01970076 A EP 01970076A EP 01970076 A EP01970076 A EP 01970076A EP 1344002 B1 EP1344002 B1 EP 1344002B1
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EP
European Patent Office
Prior art keywords
fuel
burner
combustion air
swirl
group
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EP01970076A
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German (de)
French (fr)
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EP1344002A1 (en
Inventor
Adnan Eroglu
Douglas Pennell
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General Electric Technology GmbH
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Alstom Technology AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—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
    • F23R3/02—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

Definitions

  • the present invention relates to a staged fuel injection combustor composed of a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, wherein the means for introducing fuel into the combustion air stream comprises at least a first fuel supply having a first group Fuel outlet openings and a second fuel supply to a second group of fuel outlet openings downstream of the first group of fuel outlet openings and the first and second group of fuel outlet openings and inlet openings for the combustion air flow along the swirl space formed by the swirl generator are arranged.
  • a preferred field of application for such a burner is the use in steam and gas turbine technology.
  • a multi-shell cone-shaped burner known as a double-cone burner. Due to the conical multi-shell vortex generator, which forms a swirl space in the interior, a closed swirl flow is generated in the conical head, which becomes unstable due to the increasing swirl along the conical tip and into an annular Swirl flow merges with backflow in the core.
  • the shells of the swirl generator are assembled in such a way that tangential air inlet slots for combustion air are formed along the burner axis. Feed lines for the premix gas, ie the gaseous fuel, are provided on the inflow edge of the conical shells, which have outlet openings for the premix gas distributed along the swirl space in the direction of the burner axis.
  • the gas is injected through the outlet openings or bores transversely to the air inlet gap. This injection, in conjunction with the swirl generated in the swirl space of the combustion air-fuel gas flow to a good mixing of the fuel or premixed gas with the combustion air. Good mixing in such premix burners is the prerequisite for low NO x values during the combustion process.
  • a burner for a heat generator known, which has an additional mixing section for further mixing of fuel and combustion air following the swirl generator.
  • This mixing section can be designed, for example, as a downstream tube, into which the flow emerging from the swirl generator is transferred without appreciable flow losses. Through this additional mixing section, the degree of mixing can be further increased and thus the pollutant emissions can be reduced.
  • Fig. 1 shows schematically an example of such a burner, in which the fuel over Outlet openings in along the burner axis arranged in the swirl body 1 supply channels with the incoming combustion air is mixed.
  • the conical swirl body 1 of the burner is shown with the swirl space 1a enclosed by the latter, along which the fuel feeds to the outlet openings 2 - in the figure indicated by arrows for injected fuel - run.
  • These fuel feeds are generally formed as individual channels, which have a fixed distribution of the fuel outlet openings 2 along the burner axis.
  • a piloting lance 5 via which the fuel is injected directly into the swirl chamber 1a when starting the burner.
  • a switchover from this pilot stage to the premix mode takes place in which the fuel is mixed with the inflowing combustion air via the aforementioned fuel outlet openings 2.
  • WO 93/17279 Another known burner geometry of a premix burner is known from WO 93/17279 known.
  • a cylindrical swirl generator is used with an additional conical inner body.
  • the premix gas is also injected via feeders with corresponding outlet openings in the swirl space, which are arranged along the axially extending air inlet slots.
  • the piloting supply of this burner is provided at the end of the conical inner body.
  • the piloting leads to increased NO x emissions, since in this mode of operation only an insufficient mixing with the combustion air can take place.
  • a burner assembly in which the means for introducing fuel into the combustion air stream at least a first fuel supply to a first group of fuel outlet openings for a first premix fuel quantity and a second fuel supply to a second group of fuel Outlet openings downstream of the first group of fuel outlet openings for a second Premix fuel quantity include.
  • the fuel feeds with the fuel outlet openings are in this case arranged on the swirl body along the swirl space in the longitudinal direction of the burner and divided into at least two mutually independent channels for the fuel.
  • the operation of the burner can be optimally adapted to the respective operating load in terms of emissions.
  • a fuel supply via the piloting lance is no longer necessary because the sole operation with fuel outlet openings of the first stage (eg 2a in Fig. 2 ) causes sufficiently high local temperatures on the burner axis, while the total adiabatic temperature is still low.
  • the extinction limit of a burner with a fully premixed fuel-air mixture has an extinguishing limit above 1600 K.
  • Modern AAP gas turbines are operated at idle and at low load with a fuel-air mixture, the combustion of an adiabatic temperature of 900 produced up to 1600 Kelvin. It is therefore impossible to burn the fuel in the entire available combustion air, so that an enrichment of the core air in the burner by piloting in the region of the burner neck is required.
  • This relates in particular to the abovementioned burners of the prior art with single-stage fuel injection.
  • Applicant's multi-stage fuel injection burners by splitting the fuel feeds into two separate regions, show a reduction in NO x emissions and in the magnitude of combustion pulsations at higher flame temperatures above 1650K.
  • the problem of pulsations still occurs Temperatures below 1500 K, when the first stage is operated essentially alone and thus performs a function similar to a piloting stage.
  • the object of the present invention is to provide a burner which generates a low level of pulsations even at lower combustion temperatures below 1600K.
  • the present staged fuel injection burner is essentially composed of a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream.
  • the means for introducing fuel into the combustion air stream include at least a first fuel supply having a first group of fuel discharge ports and a second fuel supply having a second group of fuel discharge ports remote from the first group of fuel discharge ports.
  • the two groups of fuel outlets as well Inlet openings for combustion air, as a rule air inlet slots, are hereby arranged along the swirl space formed by the swirl body, as is also the case with single-stage burner systems of the type mentioned at the beginning. This is inevitably required to inject the fuel into the combustion air entering through the inlet slots in order to achieve the best possible mixing in this way.
  • the present burner is characterized in that in the transition region between the first group and the second group of fuel outlet openings, a separating element is arranged in the swirl space, which extends in the direction of the combustion chamber and the combustion air flow entering in the region of the first group via the air inlet openings separates from the entering in the second group of fuel-discharge openings combustion air flow.
  • This separation takes place here at least over a region of the swirl space, ie, starting from the transition region in the direction of the combustion chamber into the region of the swirl space into which the second group of fuel outlet openings is arranged.
  • the separating element can be constructed in one piece as well as in several parts. It is preferably composed of a burner axis enclosing the partition.
  • the partition wall is preferably tubular in adaptation to the geometric shape of the swirl generator over at least one subregion.
  • This embodiment of the present burner allows a stronger pulsation even at low load of the system, ie at low burner power and low total adiabatic combustion temperatures.
  • the inventors have recognized that the flame during operation of the first stage without such a separator on the one hand can perform relatively free axial pulsations and on the other hand these pulsations are supported due to the cooling effect of flowing in the second stage through the air inlet openings combustion air.
  • By inserting the separating element between the air streams which flow into the swirl space in the region of the first stage and the air streams which flow in the region of the second stage an interaction between these can be prevented at low burner power. This in turn leads advantageously to a reduction of the combustion pulsations.
  • the burner comprises a fuel lance which extends into the region of the separating element or of the volume formed by the separating element.
  • This burner lance is thus extended compared to the known from the prior art in connection with the burners with single-stage fuel injection fuel or pilot lances.
  • an additional stabilization point for the fuel-air mixture is created by the "increment" over the lance tip of the first stage and the axial pulsation of the combustion is further reduced.
  • the walls of the separating element on cooling channels, which combustion air is supplied from upstream of the swirl generator.
  • the cooling channels extend in the direction of the combustion chamber.
  • the cooling air exits through corresponding openings at the combustion chamber end of the separating element in the swirl space.
  • the separating element is preferably formed integrally with or attached to the swirl body or shells forming it.
  • the present embodiment of the burner makes it possible to provide existing burner designs without expensive redesign with the separating element.
  • Fig. 1 shows a single-stage burner system, as is known from the prior art and has already been explained in the introduction to the description.
  • a burner geometry is used, as in principle from the above-mentioned prior art, in particular from EP 0 321 809 B1 is known.
  • the burner consists of the swirl body 1, which includes a swirl space 1a for mixing the fuel with the combustion air entering via the air inlet slots in the swirl body 1 (indicated by arrows).
  • the combustion chamber 3 connects.
  • the swirl generator 1 is conical in a known manner and consists of several subshells. In these subshells, the channel-shaped feeds 4a and 4b are arranged for the injection of the fuel in the swirl space 1a.
  • a two-stage fuel injection is used, in which a first stage is formed by the fuel supply 4a and a second stage by the fuel supply 4b.
  • the first group of fuel outlet openings 2a in the first fuel channel 4a and the second group of fuel outlet openings 2b in the second fuel channel 4b can be seen schematically.
  • outlet openings 2a, 2b are shown only schematically in the present example, wherein the number, distribution and geometry of these outlet openings is adapted to the respective conditions.
  • the feed line 6 of the fuel to the second stage 4b is guided along the outer wall of the swirl body 1 in this example.
  • the feeder for the first stage 4a is not explicitly shown in this example.
  • a fuel lance 5 can be seen, which extends on the longitudinal axis 7 of the burner.
  • a separating element 8 is provided, that surrounds the longitudinal axis 7 of the burner in the swirling space 1a and is substantially cylindrical or cup-shaped.
  • This separating element 8 separates the combustion air flow entering through the air inlet slots in the region of the first step 4a from the combustion air flow which enters the outer zone of the swirl space 1a in the region of the second step 4b.
  • the flow pattern of the incoming combustion air can be recognized by the two arrows.
  • the separating element 8 in this case forms a kind of can open to the combustion chamber 3.
  • the fuel lance 5 is opposite in this example known arrangements extended and extends to about halfway into the volume formed by the partition 8.
  • the fuel is directed mainly through the fuel outlet openings 2a of the first stage 4a into the inner zone of the swirl space 1a, i. into the entering into the swirl space in this area combustion air, injected.
  • a combustion zone forms on the combustion chamber side edge of the separating element 8, which is shown schematically by the reference numeral 9 in the figure.
  • This combustion of the fuel of the first stage 4a in the said mode of operation is not disturbed by the combustion air flow entering in the region of the second stage 4b, since the flame root is located inside the separating element. Possible pulsations of the combustion are thereby significantly reduced and the stability of the flame is improved, in particular by the extended fuel lance 5, which generates a step backwards facing step.
  • cooling system for the separating element 8 in the form of cooling channels 11 can also be seen very well. These cooling channels 11 are connected to the combustion air entering the swirl generator 1 upstream of the second stage and have their outlet openings at the combustion chamber end of the walls of the separating element 8. The exiting combustion air is indicated in this area by the arrows.
  • the present invention is also applicable to other burner geometries, which are operated via an at least two-stage injection of the fuel into the combustion air.
  • the essential element here is the separating element which separates the combustion air flow entering in the region of the two stages. This separation is required at least in a portion of the swirl space.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)

Description

Technisches AnwendungsgebietTechnical application

Die vorliegende Erfindung betrifft einen Brenner mit gestufter Brennstoff-Eindüsung, der sich aus einem Drallerzeuger für einen Verbrennungsluftstrom und Mitteln zum Einbringen von Brennstoff in den Verbrennungsluftstrom zusammensetzt, wobei die Mittel zum Einbringen von Brennstoff in den Verbrennungsluftstrom wenigstens eine erste Brennstoffzuführung mit einer ersten Gruppe von Brennstoff-Austrittsöffnungen und eine zweite Brennstoffzuführung mit einer zweiten Gruppe von Brennstoff-Austrittsöffnungen stromab der ersten Gruppe von Brennstoff-Austrittsöffnungen umfassen und die erste und zweite Gruppe von Brennstoff-Austrittsöffnungen sowie Eintrittsöffnungen für den Verbrennungsluftstrom entlang des durch den Drallerzeuger gebildeten Drallraums angeordnet sind. Ein bevorzugtes Anwendungsgebiet für einen derartigen Brenner ist der Einsatz in der Dampf- und Gasturbinentechnik.The present invention relates to a staged fuel injection combustor composed of a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, wherein the means for introducing fuel into the combustion air stream comprises at least a first fuel supply having a first group Fuel outlet openings and a second fuel supply to a second group of fuel outlet openings downstream of the first group of fuel outlet openings and the first and second group of fuel outlet openings and inlet openings for the combustion air flow along the swirl space formed by the swirl generator are arranged. A preferred field of application for such a burner is the use in steam and gas turbine technology.

Stand der TechnikState of the art

Aus der EP 0 321 809 B1 ist ein aus mehreren Schalen bestehender kegelförmiger Brenner, ein so genannter Doppelkegelbrenner bekannt. Durch den kegelförmigen aus mehreren Schalen zusammengesetzten Drallerzeuger, der einen Drallraum im Innern bildet, wird eine geschlossene Drallströmung im Kegelkopf erzeugt, welche aufgrund des zunehmenden Dralls entlang der Kegelspitze instabil wird und in eine annulare Drallströmung mit Rückströmung im Kern übergeht. Die Schalen des Drallerzeugers sind derart zusammengesetzt, dass entlang der Brennerachse tangentiale Lufteintrittsschlitze für Verbrennungsluft gebildet werden. An der hierdurch entstehenden Einströmkante der Kegelschalen sind Zuführungen für das Vormischgas, d.h. den gasförmigen Brennstoff, vorgesehen, die in Richtung der Brennerachse entlang des Drallraums verteilte Austrittsöffnungen für das Vormischgas aufweisen. Das Gas wird durch die Austrittsöffnungen bzw. Bohrungen quer zum Lufteintrittsspalt eingedüst. Diese Eindüsung führt in Verbindung mit dem im Drallraum erzeugten Drall der Verbrennungsluft-Brenngas-Strömung zu einer guten Durchmischung des Brenn- bzw. Vormischgases mit der Verbrennungsluft. Eine gute Durchmischung ist bei derartigen Vormischbrennern die Voraussetzung für niedrige NOx-Werte beim Verbrennungsvorgang.From the EP 0 321 809 B1 is a multi-shell cone-shaped burner known as a double-cone burner. Due to the conical multi-shell vortex generator, which forms a swirl space in the interior, a closed swirl flow is generated in the conical head, which becomes unstable due to the increasing swirl along the conical tip and into an annular Swirl flow merges with backflow in the core. The shells of the swirl generator are assembled in such a way that tangential air inlet slots for combustion air are formed along the burner axis. Feed lines for the premix gas, ie the gaseous fuel, are provided on the inflow edge of the conical shells, which have outlet openings for the premix gas distributed along the swirl space in the direction of the burner axis. The gas is injected through the outlet openings or bores transversely to the air inlet gap. This injection, in conjunction with the swirl generated in the swirl space of the combustion air-fuel gas flow to a good mixing of the fuel or premixed gas with the combustion air. Good mixing in such premix burners is the prerequisite for low NO x values during the combustion process.

Zur weiteren Verbesserung eines derartigen Brenners ist aus der EP 0 280 629 A2 ein Brenner für einen Wärmeerzeuger bekannt, der im Anschluss an den Drallerzeuger eine zusätzliche Mischstrecke zur weiteren Vermischung von Brennstoff und Verbrennungsluft aufweist. Diese Mischstrecke kann beispielsweise als nachgeschaltetes Rohr ausgeführt sein, in das die aus dem Drallerzeuger austretende Strömung ohne nennenswerte Strömungsverluste überführt wird. Durch diese zusätzliche Mischstrecke können der Vermischungsgrad weiter erhöht und damit die Schadstoffemissionen verringert werden.To further improve such a burner is from the EP 0 280 629 A2 a burner for a heat generator known, which has an additional mixing section for further mixing of fuel and combustion air following the swirl generator. This mixing section can be designed, for example, as a downstream tube, into which the flow emerging from the swirl generator is transferred without appreciable flow losses. Through this additional mixing section, the degree of mixing can be further increased and thus the pollutant emissions can be reduced.

Fig. 1 zeigt schematisch ein Beispiel für derartige Brenner, bei denen der Brennstoff über Austrittsöffnungen in entlang der Brennerachse im Drallkörper 1 angeordneten Zuführungskanälen mit der eintretenden Verbrennungsluft gemischt wird. In der Figur ist hierbei der kegelförmige Drallkörper 1 des Brenners mit dem von diesem umschlossenen Drallraum 1a dargestellt, entlang dem die Brennstoffzuführungen mit den Austrittsöffnungen 2 - in der Figur durch Pfeile für eingedüsten Brennstoff angedeutet - verlaufen. Diese Brennstoffzuführungen sind in der Regel als einzelne Kanäle ausgebildet, die eine feste Verteilung der Brennstoff-Austrittsöffnungen 2 entlang der Brennerachse aufweisen. Weiterhin ist in der Figur 1 eine Pilotierungslanze 5 zu erkennen, über die beim Anfahren des Brenners der Brennstoff direkt in den Drallraum 1a eingespritzt wird. Bei steigender Last erfolgt dann ein Umschalten von dieser Pilotierungsstufe zum Vormisch-Betrieb, bei dem der Brennstoff über die genannten Brennstoff-Austrittsöffnungen 2 mit der zuströmenden Verbrennungsluft vermischt wird. Fig. 1 shows schematically an example of such a burner, in which the fuel over Outlet openings in along the burner axis arranged in the swirl body 1 supply channels with the incoming combustion air is mixed. In the figure, in this case, the conical swirl body 1 of the burner is shown with the swirl space 1a enclosed by the latter, along which the fuel feeds to the outlet openings 2 - in the figure indicated by arrows for injected fuel - run. These fuel feeds are generally formed as individual channels, which have a fixed distribution of the fuel outlet openings 2 along the burner axis. Furthermore, in the FIG. 1 to detect a piloting lance 5, via which the fuel is injected directly into the swirl chamber 1a when starting the burner. When the load increases, a switchover from this pilot stage to the premix mode takes place in which the fuel is mixed with the inflowing combustion air via the aforementioned fuel outlet openings 2.

Eine weitere bekannte Brennergeometrie eines Vormisch-Brenners ist aus der WO 93/17279 bekannt. Bei dieser Anordnung wird ein zylindrischer Drallerzeuger mit einem zusätzlichen konischen Innenkörper eingesetzt. Das Vormischgas wird ebenfalls über Zuführungen mit entsprechenden Austrittsöffnungen in den Drallraum eingedüst, die entlang der axial verlaufenden Lufteintrittsschlitze angeordnet sind. Die Pilotierungszuführung dieses Brenners ist am Ende des konischen Innenkörpers vorgesehen. Die Pilotierung führt jedoch zu erhöhten NOx-Emissionen, da bei dieser Betriebsweise nur eine unzureichende Vermischung mit der Verbrennungsluft stattfinden kann.Another known burner geometry of a premix burner is known from WO 93/17279 known. In this arrangement, a cylindrical swirl generator is used with an additional conical inner body. The premix gas is also injected via feeders with corresponding outlet openings in the swirl space, which are arranged along the axially extending air inlet slots. The piloting supply of this burner is provided at the end of the conical inner body. However, the piloting leads to increased NO x emissions, since in this mode of operation only an insufficient mixing with the combustion air can take place.

Bei allen bekannten Brennersystemen ist eine einstufige Zuführung des Brennstoffes im Vormisch-betrieb vorgesehen. Die Größe, Verteilung, Anordnung, der Abstand sowie die Anzahl der Austrittsöffnungen der Brennstoffzuführung entlang der Brennerachse müssen hierbei optimiert werden, um die Anforderungen an geringe Emissionen, die Extinktionsgrenze, die Rückschlaggrenze sowie die Anforderungen an die Stabilität der Verbrennung zu erfüllen. Hierbei ist es nahezu unmöglich, alle diese Anforderungen mit einer festen Verteilung der Austrittsöffnungen auch unter wechselnden Betriebs- und Umgebungsbedingungen zu erfüllen.In all known burner systems, a one-stage supply of the fuel is provided in premix operation. The size, distribution, arrangement, the distance and the number of outlets of the fuel supply along the burner axis must be optimized in this case to meet the requirements of low emissions, the Absinktionsgrenze, the setback limit and the requirements for the stability of the combustion. It is almost impossible to meet all these requirements with a fixed distribution of the outlet openings even under changing operating and environmental conditions.

Ein weiterer Nachteil der bekannten Verfahren zum Betrieb von Vormisch-Brennern liegt darin, dass diese für niedrige Emissionen und niedrige Verbrennungsoszillationen unter Volllastbedingungen optimiert sind. Um den Brenner anzufahren und die Gasturbine zu starten, wird eine zusätzliche Pilotierungsstufe benötigt, die jedoch die Emissionswerte deutlich ansteigen lässt.Another disadvantage of the known methods for operating premix burners is that they are optimized for low emissions and low combustion oscillations under full load conditions. In order to start the burner and start the gas turbine, an additional piloting stage is needed, which however increases the emission values significantly.

In einer parallelen Patentanmeldung der Anmelderin ( US-5 699 667-A ) wurde zur Lösung dieser Problematik eine Brenneranordnung vorgeschlagen, bei der die Mittel zum Einbringen von Brennstoff in den Verbrennungsluftstrom wenigstens eine erste Brennstoffzuführung mit einer ersten Gruppe von Brennstoff-Austrittsöffnungen für eine erste Vormisch-Brennstoffmenge und eine zweite Brennstoffzuführung mit einer zweiten Gruppe von Brennstoff-Austrittsöffnungen stromab der ersten Gruppe von Brennstoff-Austrittsöffnungen für eine zweite Vormisch-Brennstoffmenge umfassen. Die Brennstoffzuführungen mit den Brennstoff-Austrittsöffnungen sind hierbei am Drallkörper entlang des Drallraums in Längsrichtung des Brenners angeordnet und in zumindest zwei voneinander unabhängige Kanäle für den Brennstoff unterteilt. Durch den Einsatz eines derartigen Brennersystems mit gestufter Brennstoff-Eindüsung wird ein gegenüber einstufigen Brennersystemen deutlich erweiterter Betriebsbereich ermöglicht. Insbesondere kann die Betriebsweise des Brenners hinsichtlich der Emissionen optimal an die jeweilige Betriebslast angepasst werden. Weiterhin ist eine Brennstoffzuführung über die Pilotierungslanze nicht mehr erforderlich, da der alleinige Betrieb mit Brennstoff-Austrittsöffnungen der ersten Stufe (z.B. 2a in Fig. 2) ausreichend hohe lokale Temperaturen auf der Brennerachse hervorruft, während die gesamtadiabatische Temperatur weiterhin niedrig ist.In a parallel patent application of the Applicant ( US-5,699,667-A ) has been proposed to solve this problem, a burner assembly in which the means for introducing fuel into the combustion air stream at least a first fuel supply to a first group of fuel outlet openings for a first premix fuel quantity and a second fuel supply to a second group of fuel Outlet openings downstream of the first group of fuel outlet openings for a second Premix fuel quantity include. The fuel feeds with the fuel outlet openings are in this case arranged on the swirl body along the swirl space in the longitudinal direction of the burner and divided into at least two mutually independent channels for the fuel. The use of such a burner system with staged fuel injection enables a significantly extended operating range compared to single-stage burner systems. In particular, the operation of the burner can be optimally adapted to the respective operating load in terms of emissions. Furthermore, a fuel supply via the piloting lance is no longer necessary because the sole operation with fuel outlet openings of the first stage (eg 2a in Fig. 2 ) causes sufficiently high local temperatures on the burner axis, while the total adiabatic temperature is still low.

Die Löschgrenze eines Brenners mit einem vollständig vorgemischten Brennstoff-Luft-Gemisch hat eine Löschgrenze oberhalb von 1600 K. Moderne AAP-Gasturbinen werden im Leerlauf und bei niedriger Last mit einem Brennstoff-Luft-Gemisch betrieben, das bei der Verbrennung eine adiabatische Temperatur von 900 bis 1600 Kelvin erzeugt. Es ist daher unmöglich, den Brennstoff in der gesamten verfügbaren Verbrennungsluft zu verbrennen, so dass eine Anreicherung der Kernluft im Brenner durch Pilotierung im Bereich des Brennerhalses erforderlich ist. Dies betrifft insbesondere die oben genannten Brenner des Standes der Technik mit einstufiger Brennstoff-Eindüsung.The extinction limit of a burner with a fully premixed fuel-air mixture has an extinguishing limit above 1600 K. Modern AAP gas turbines are operated at idle and at low load with a fuel-air mixture, the combustion of an adiabatic temperature of 900 produced up to 1600 Kelvin. It is therefore impossible to burn the fuel in the entire available combustion air, so that an enrichment of the core air in the burner by piloting in the region of the burner neck is required. This relates in particular to the abovementioned burners of the prior art with single-stage fuel injection.

Die von der Anmelderin entwickelten Brenner mit mehrstufiger Brennstoff-Eindüsung durch Aufteilung der Brennstoffzuführungen in zwei getrennte Bereiche zeigen insbesondere eine Verringerung der NOX-Emissionen und der Stärke der Verbrennungspulsationen bei höheren Flammentemperaturen oberhalb von 1650 K. Das Problem der Pulsationen tritt jedoch noch immer bei Temperaturen unterhalb von 1500 K auf, wenn die erste Stufe im Wesentlichen alleine betrieben wird und somit eine Funktion ähnlich einer Pilotierungsstufe erfüllt.In particular, Applicant's multi-stage fuel injection burners, by splitting the fuel feeds into two separate regions, show a reduction in NO x emissions and in the magnitude of combustion pulsations at higher flame temperatures above 1650K. However, the problem of pulsations still occurs Temperatures below 1500 K, when the first stage is operated essentially alone and thus performs a function similar to a piloting stage.

Die Aufgabe der vorliegenden Erfindung besteht darin, einen Brenner bereitzustellen, der auch bei niedrigeren Verbrennungstemperaturen unterhalb von 1600 K ein geringes Maß an Pulsationen erzeugt.The object of the present invention is to provide a burner which generates a low level of pulsations even at lower combustion temperatures below 1600K.

Darstellung der ErfindungPresentation of the invention

Die Aufgabe wird mit dem Brenner gemäß Patentanspruch 1 gelöst. Vorteilhafte Ausgestaltungen des Brenners sind Gegenstand der Unteransprüche.The object is achieved with the burner according to claim 1. Advantageous embodiments of the burner are the subject of the dependent claims.

Der vorliegende Brenner mit gestufter Brennstoff-Eindüsung setzt sich im Wesentlichen aus einem Drallerzeuger für einen Verbrennungsluftstrom und Mitteln zum Einbringen von Brennstoff in den Verbrennungsluftstrom zusammen. Die Mittel zum Einbringen von Brennstoff in den Verbrennungsluftstrom umfassen wenigstens eine erste Brennstoffzuführung mit einer ersten Gruppe von Brennstoff-Austrittsöffnungen und eine zweite Brennstoffzuführung mit einer zweiten Gruppe von Brennstoff-Austrittsöffnungen abgesetzt von der ersten Gruppe von Brennstoff-Austrittsöffnungen. Die beiden Gruppen von Brennstoff-Austrittsöffnungen sowie Eintrittsöffnungen für Verbrennungsluft, in der Regel Lufteintrittsschlitze, sind hierbei entlang des durch den Drallkörper gebildeten Drallraums angeordnet, wie dies auch bei einstufigen Brennersystemen der eingangs genannten Art der Fall ist. Dies ist zwangsläufig erforderlich, um den Brennstoff in die durch die Eintrittsschlitze eintretende Verbrennungsluft einzudüsen, um auf diese Weise eine möglichst gute Vermischung zu erreichen. Der vorliegende Brenner zeichnet sich dadurch aus, dass im Übergangsbereich zwischen der ersten Gruppe und der zweiten Gruppe von Brennstoff-Austrittsöffnungen ein Trennelement im Drallraum angeordnet ist, das sich in Richtung der Brennkammer erstreckt und das den im Bereich der ersten Gruppe über die Lufteintrittsöffnungen eintretenden Verbrennungsluftstrom von dem im Bereich der zweiten Gruppe von Brennstoff-Austrittsöffnungen eintretenden Verbrennungsluftstrom trennt. Diese Trennung erfolgt hierbei zumindest über einen Bereich des Drallraums, d.h. ausgehend vom Übergangsbereich in Richtung der Brennkammer bis in den Bereich des Drallraums hinein, in dem die zweite Gruppe von Brennstoff-Austrittsöffnungen angeordnet ist.The present staged fuel injection burner is essentially composed of a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream. The means for introducing fuel into the combustion air stream include at least a first fuel supply having a first group of fuel discharge ports and a second fuel supply having a second group of fuel discharge ports remote from the first group of fuel discharge ports. The two groups of fuel outlets as well Inlet openings for combustion air, as a rule air inlet slots, are hereby arranged along the swirl space formed by the swirl body, as is also the case with single-stage burner systems of the type mentioned at the beginning. This is inevitably required to inject the fuel into the combustion air entering through the inlet slots in order to achieve the best possible mixing in this way. The present burner is characterized in that in the transition region between the first group and the second group of fuel outlet openings, a separating element is arranged in the swirl space, which extends in the direction of the combustion chamber and the combustion air flow entering in the region of the first group via the air inlet openings separates from the entering in the second group of fuel-discharge openings combustion air flow. This separation takes place here at least over a region of the swirl space, ie, starting from the transition region in the direction of the combustion chamber into the region of the swirl space into which the second group of fuel outlet openings is arranged.

Das Trennelement kann sowohl einstückig als auch mehrteilig aufgebaut sein. Es setzt sich vorzugsweise aus einer die Brennerachse umschließenden Trennwand zusammen. Die Trennwand ist hierbei in Anpassung an die geometrische Form des Drallerzeugers vorzugsweise über zumindest einen Teilbereich rohrförmig ausgebildet. Durch dieses Trennelement bzw. diese Trennwand innerhalb des Drallraums wird ein gesondertes Volumen geschaffen, das eine Art verkleinerter Brennkammer für die erste Stufe, d.h. den über die erste Gruppe von Brennstoff-Austrittsöffnungen in den Drallraum eintretenden Brennstoff und das daraus resultierende Brennstoff-Luft-Gemisch, bildet.The separating element can be constructed in one piece as well as in several parts. It is preferably composed of a burner axis enclosing the partition. In this case, the partition wall is preferably tubular in adaptation to the geometric shape of the swirl generator over at least one subregion. By this separating element or this partition within the swirl space a separate volume is created, which is a kind of reduced combustion chamber for the first stage, ie the fuel entering the swirl space via the first group of fuel outlets, and the resulting fuel-air mixture.

Bei einer Betriebsweise des Brenners, bei der im Wesentlichen der Brennstoff durch diese erste Stufe zugeführt wird, wie dies zum Anfahren, im Leerlaufbetrieb und bei niedriger Last der durch den Brenner betriebenen Anlage, insbesondere einer Gasturbine, in Art einer Pilotierung der Fall ist, wird die Flamme bereits innerhalb des durch das Trennelement gebildeten Volumens erzeugt.In an operation of the burner in which substantially the fuel is supplied through this first stage, as is the case for starting, idling and low load of the burner operated by the plant, in particular a gas turbine, in the manner of piloting is the flame already generated within the volume formed by the partition.

Durch diese Ausgestaltung des vorliegenden Brenners wird eine stärkere Pulsation auch bei niedriger Last der Anlage, d.h. bei niedriger Brennerleistung und niedrigen gesamt adiabaten Verbrennungstemperaturen ermöglicht. Die Erfinder haben hierbei erkannt, dass die Flamme beim Betrieb der ersten Stufe ohne ein derartiges Trennelement einerseits relativ freie axiale Pulsationen ausführen kann und andererseits diese Pulsationen aufgrund des Kühlungseffektes der im Bereich der zweiten Stufe durch die Lufteintrittsöffnungen einströmenden Verbrennungsluft unterstützt werden. Durch die Einfügung des Trennelementes zwischen den Luftströmen, die im Bereich der ersten Stufe in den Drallraum einströmen und den Luftströmen, die im Bereich der zweiten Stufe einströmen, kann eine Wechselwirkung zwischen diesen bei niedriger Brennerleistung verhindert werden. Dies wiederum führt in vorteilhafter Weise zu einer Verringerung der Verbrennungspulsationen.This embodiment of the present burner allows a stronger pulsation even at low load of the system, ie at low burner power and low total adiabatic combustion temperatures. The inventors have recognized that the flame during operation of the first stage without such a separator on the one hand can perform relatively free axial pulsations and on the other hand these pulsations are supported due to the cooling effect of flowing in the second stage through the air inlet openings combustion air. By inserting the separating element between the air streams which flow into the swirl space in the region of the first stage and the air streams which flow in the region of the second stage, an interaction between these can be prevented at low burner power. This in turn leads advantageously to a reduction of the combustion pulsations.

In einer vorteilhaften Ausführungsform umfasst der Brenner eine Brennstofflanze, die sich bis in den Bereich des Trennelementes bzw. des durch das Trennelement gebildeten Volumens erstreckt. Diese Brennerlanze ist somit gegenüber den aus dem Stand der Technik in Zusammenhang mit den Brennern mit einstufiger Brennstoff-Eindüsung bekannten Brennstoff- oder Pilotierungslanzen verlängert. Durch diese Verlängerung der Brennstofflanze bis in das Volumen des Trennelementes wird ein zusätzlicher Stabilisierungspunkt für das Brennstoff-Luft-Gemisch durch den "Stufensprung" über die Lanzenspitze der ersten Stufe geschaffen und die axiale Pulsation der Verbrennung weiter verringert.In an advantageous embodiment, the burner comprises a fuel lance which extends into the region of the separating element or of the volume formed by the separating element. This burner lance is thus extended compared to the known from the prior art in connection with the burners with single-stage fuel injection fuel or pilot lances. As a result of this extension of the fuel lance into the volume of the separating element, an additional stabilization point for the fuel-air mixture is created by the "increment" over the lance tip of the first stage and the axial pulsation of the combustion is further reduced.

Vorzugsweise weisen die Wände des Trennelementes Kühlkanäle auf, denen Verbrennungsluft von stromauf des Drallerzeugers zugeführt wird. Die Kühlkanäle erstrecken sich hierbei in Richtung der Brennkammer. Die Kühlluft tritt durch entsprechende Öffnungen am brennkammerseitigen Ende des Trennelementes in den Drallraum aus.Preferably, the walls of the separating element on cooling channels, which combustion air is supplied from upstream of the swirl generator. The cooling channels extend in the direction of the combustion chamber. The cooling air exits through corresponding openings at the combustion chamber end of the separating element in the swirl space.

Das Trennelement ist vorzugsweise integral mit dem Drallkörper bzw. den diesen bildenden Schalen ausgebildet oder daran befestigt. Die vorliegende Ausgestaltung des Brenners ermöglicht es, bereits bestehende Brennerkonstruktionen ohne aufwendige Neukonstruktion mit dem Trennelement zu versehen.The separating element is preferably formed integrally with or attached to the swirl body or shells forming it. The present embodiment of the burner makes it possible to provide existing burner designs without expensive redesign with the separating element.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Der vorliegende Brenner wird nachfolgend anhand eines Ausführungsbeispiels in Verbindung mit den Figuren nochmals kurz erläutert. Hierbei zeigen:

Fig. 1
einen einstufigen Brenner gemäß dem Stand der Technik; und
Fig. 2
ein Beispiel für einen vorliegenden Brenner in schematischer Darstellung.
The present burner will be briefly explained again with reference to an embodiment in conjunction with the figures. Hereby show:
Fig. 1
a single-stage burner according to the prior art; and
Fig. 2
an example of a present burner in a schematic representation.

Wege zur Ausführung der ErfindungWays to carry out the invention

Fig. 1 zeigt ein einstufiges Brennersystem, wie dies aus dem Stand der Technik bekannt ist und in der Beschreibungseinleitung bereits erläutert wurde. Fig. 1 shows a single-stage burner system, as is known from the prior art and has already been explained in the introduction to the description.

Im vorliegenden Ausführungsbeispiel wird eine Brennergeometrie eingesetzt, wie sie prinzipiell aus dem eingangs genannten Stand der Technik, insbesondere aus der EP 0 321 809 B1 bekannt ist. Der Brenner besteht aus dem Drallkörper 1, der einen Drallraum 1a zur Vermischung des Brennstoffes mit der über Lufteintrittsschlitze im Drallkörper 1 eintretende Verbrennungsluft (durch Pfeile angedeutet) umfasst. Im Anschluss an den Drallraum 1a schließt sich die Brennkammer 3 an. Der Drallerzeuger 1 ist in bekannter Weise kegelförmig ausgebildet und besteht aus mehreren Teilschalen. In diesen Teilschalen sind die kanalförmigen Zuführungen 4a bzw. 4b für die Eindüsung des Brennstoffes in den Drallraum 1a angeordnet. Beim vorliegenden Brennersystem wird eine zweistufige Brennstoff-Eindüsung eingesetzt, bei der eine erste Stufe durch die Brennstoffzuführung 4a und eine zweite Stufe durch die Brennstoffzuführung 4b gebildet wird. In der Figur ist hierbei schematisch die erste Gruppe von Brennstoff-Austrittsöffnungen 2a im ersten Brennstoffkanal 4a sowie die zweite Gruppe von Brennstoff-Austrittsöffnungen 2b im zweiten Brennstoffkanal 4b zu erkennen.In the present embodiment, a burner geometry is used, as in principle from the above-mentioned prior art, in particular from EP 0 321 809 B1 is known. The burner consists of the swirl body 1, which includes a swirl space 1a for mixing the fuel with the combustion air entering via the air inlet slots in the swirl body 1 (indicated by arrows). Following the swirl chamber 1a, the combustion chamber 3 connects. The swirl generator 1 is conical in a known manner and consists of several subshells. In these subshells, the channel-shaped feeds 4a and 4b are arranged for the injection of the fuel in the swirl space 1a. In the present burner system, a two-stage fuel injection is used, in which a first stage is formed by the fuel supply 4a and a second stage by the fuel supply 4b. In the figure, the first group of fuel outlet openings 2a in the first fuel channel 4a and the second group of fuel outlet openings 2b in the second fuel channel 4b can be seen schematically.

Selbstverständlich sind diese Austrittsöffnungen 2a, 2b im vorliegenden Beispiel nur schematisch dargestellt, wobei die Anzahl, Verteilung und Geometrie dieser Austrittsöffnungen an die jeweiligen Bedingungen angepasst ist.Of course, these outlet openings 2a, 2b are shown only schematically in the present example, wherein the number, distribution and geometry of these outlet openings is adapted to the respective conditions.

Die Zuführungsleitung 6 des Brennstoffes zur zweiten Stufe 4b wird in diesem Beispiel an der Aussenwandung des Drallkörpers 1 entlanggeführt. Die Zuführung für die erste Stufe 4a ist in diesem Beispiel nicht explizit gezeigt.The feed line 6 of the fuel to the second stage 4b is guided along the outer wall of the swirl body 1 in this example. The feeder for the first stage 4a is not explicitly shown in this example.

Im zentralen Bereich des Drallerzeugers 1 ist eine Brennstofflanze 5 zu erkennen, die auf der Längsachse 7 des Brenners verläuft.In the central region of the swirl generator 1 is a fuel lance 5 can be seen, which extends on the longitudinal axis 7 of the burner.

Bei diesem Ausführungsbeispiel des erfindungsgemäßen Brenners ist ein Trennelement 8 vorgesehen, dass die Längsachse 7 des Brenners im Drallraum 1a umschließt und im Wesentlichen zylinder- bzw. topfförmig ausgebildet ist. Dieses Trennelement 8 trennt die durch die Lufteintrittsschlitze im Bereich der ersten Stufe 4a eintretende Verbrennungsluftströmung von der Verbrennungsluftströmung, die im Bereich der zweiten Stufe 4b in die äußere Zone des Drallraums 1a eintritt. Der Strömungsverlauf der eintretenden Verbrennungsluft ist durch die beiden Pfeile erkennbar. Das Trennelement 8 bildet hierbei eine Art von zur Brennkammer 3 hin offene Dose. Die Brennstofflanze 5 ist in diesem Beispiel gegenüber bekannten Anordnungen verlängert und erstreckt sich bis etwa auf halbe Höhe in das durch das Trennelement 8 gebildete Volumen. Durch diese Anordnung wird eine Trennung der im Bereich der beiden Stufen 4a und 4b eintretenden Verbrennungsluftströmung erreicht, so dass zwischen beiden Strömungen keine Wechselwirkung stattfindet. Das Trennelement 8 erstreckt sich hierbei nicht bis an den brennkammerseitigen Rand des Drallerzeugers 1, sondern nur über einen Teilbereich.In this embodiment of the burner according to the invention, a separating element 8 is provided, that surrounds the longitudinal axis 7 of the burner in the swirling space 1a and is substantially cylindrical or cup-shaped. This separating element 8 separates the combustion air flow entering through the air inlet slots in the region of the first step 4a from the combustion air flow which enters the outer zone of the swirl space 1a in the region of the second step 4b. The flow pattern of the incoming combustion air can be recognized by the two arrows. The separating element 8 in this case forms a kind of can open to the combustion chamber 3. The fuel lance 5 is opposite in this example known arrangements extended and extends to about halfway into the volume formed by the partition 8. By this arrangement, a separation of the combustion air flow entering in the region of the two stages 4a and 4b is achieved, so that there is no interaction between the two flows. The separator 8 does not extend to the combustion chamber side edge of the swirl generator 1, but only over a partial area.

Bei niedriger Last bzw. geringer Leistung des Brenners wird der Brennstoff hauptsächlich durch die Brennstoff-Austrittsöffnungen 2a der ersten Stufe 4a in die innere Zone des Drallraums 1a, d.h. in die in den Drallraum in diesem Bereich eintretende Verbrennungsluft, eingedüst. Hierdurch bildet sich eine Verbrennungszone am brennkammerseitigen Rand des Trennelementes 8, die mit dem Bezugszeichen 9 in der Figur schematisch dargestellt ist. Diese Verbrennung des Brennstoffes der ersten Stufe 4a in der genannten Betriebsweise wird nicht durch die im Bereich der zweiten Stufe 4b eintretende Verbrennungsluftströmung gestört, da sich die Flammenwurzel innerhalb des Trennelementes befindet. Mögliche Pulsationen der Verbrennung werden hierdurch deutlich vermindert und die Stabilität der Flamme insbesondere durch die verlängerte Brennstofflanze 5 verbessert, die einen Stufensprung (backwards facing step) erzeugt.At low load of the burner, the fuel is directed mainly through the fuel outlet openings 2a of the first stage 4a into the inner zone of the swirl space 1a, i. into the entering into the swirl space in this area combustion air, injected. As a result, a combustion zone forms on the combustion chamber side edge of the separating element 8, which is shown schematically by the reference numeral 9 in the figure. This combustion of the fuel of the first stage 4a in the said mode of operation is not disturbed by the combustion air flow entering in the region of the second stage 4b, since the flame root is located inside the separating element. Possible pulsations of the combustion are thereby significantly reduced and the stability of the flame is improved, in particular by the extended fuel lance 5, which generates a step backwards facing step.

Hierbei ist nicht beabsichtigt, gasförmigen Brennstoff über die Lanze einzubringen. Die beiden in Figur 2 in der Lanze erkennbaren Kanäle sind für Lanzen-Kühlluft und die Möglichkeit des Einbringens von flüssigem Brennstoff für einen Doppel-Brennstoff-Betrieb über die zental angeordnete Flachstrahldüse.This is not intended to introduce gaseous fuel over the lance. The two in FIG. 2 Channels recognizable in the lance are for lance cooling air and the possibility of introducing liquid fuel for dual fuel operation via the centrally located fan jet nozzle.

Bei höherer Brennerleistung werden zusätzlich durch die zweite Stufe 4b größere Brennstoffmengen eingedüst, wodurch sich am Ende die Verbrennungszone in den mit dem Bezugszeichen 10 schematisch angedeuteten Bereich verlagert. Bei den in dieser Betriebsweise bereits auftretenden höheren Verbrennungstemperaturen tritt die Problematik der Pulsationen nicht mehr in dem bei niedrigen Leistungen vorliegenden Maße auf. Durch die Trennwand ist auch die Flammenwurzel der Flamme, die durch den über die zweite Stufe 4b eingebrachten Brennstoff erzeugt wird, immer noch mit der Flamme 9 im bzw. am Trennwandaustritt verankert.With a higher burner output, larger amounts of fuel are additionally injected by the second stage 4b, whereby at the end the combustion zone is displaced into the region indicated schematically by the reference numeral 10. In the already occurring in this mode of operation higher combustion temperatures, the problem of pulsations no longer occurs in the present at low power levels. Through the partition wall and the flame root of the flame, which is generated by the introduced via the second stage 4b fuel, is still anchored to the flame 9 in or on the partition wall exit.

In der Figur ist auch sehr gut das Kühlungssystem für das Trennelement 8 in Form von Kühlkanälen 11 zu erkennen. Diese Kühlkanäle 11 sind mit der in den Drallerzeuger 1 stromauf der zweiten Stufe eintretenden Verbrennungsluft verbunden und haben ihre Austrittsöffnungen an dem brennkammerseitigen Ende der Wände des Trennelementes 8. Die austretende Verbrennungsluft ist in diesem Bereich durch die Pfeile angedeutet.In the figure, the cooling system for the separating element 8 in the form of cooling channels 11 can also be seen very well. These cooling channels 11 are connected to the combustion air entering the swirl generator 1 upstream of the second stage and have their outlet openings at the combustion chamber end of the walls of the separating element 8. The exiting combustion air is indicated in this area by the arrows.

Es versteht sich von selbst, dass die vorliegende Erfindung auch auf andere Brennergeometrien anwendbar ist, die über eine zumindest zweistufige Eindüsung des Brennstoffes in die Verbrennungsluft betrieben werden. Das wesentliche Element ist hierbei das Trennelement, das die im Bereich der beiden Stufen eintretende Verbrennungsluftströmung voneinander trennt. Diese Trennung ist zumindest in einem Teilbereich des Drallraums erforderlich.It goes without saying that the present invention is also applicable to other burner geometries, which are operated via an at least two-stage injection of the fuel into the combustion air. The essential element here is the separating element which separates the combustion air flow entering in the region of the two stages. This separation is required at least in a portion of the swirl space.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

11
Drallerzeugerswirl generator
1a1a
Drallraumswirl space
22
Brennstoff-AustrittsöffnungenFuel outlet openings
2a2a
Brennstoff-Austrittsöffnungen der ersten StufeFirst stage fuel exit ports
2b2 B
Brennstoff-Austrittsöffnungen der zweiten StufeSecond stage fuel exit ports
33
Brennkammercombustion chamber
4a4a
Brennstoffzuführung der ersten StufeFuel supply of the first stage
4a4a
Brennstoffzuführung der zweiten StufeFuel supply of the second stage
55
Brennstofflanzefuel lance
66
Brennstoffleitungfuel line
77
Längsachse des BrennersLongitudinal axis of the burner
88th
Trennelementseparating element
99
Verbrennungszone 1Combustion zone 1
1010
Verbrennungszone 2Combustion zone 2
1111
Kühlkanälecooling channels

Claims (6)

  1. Burner with staged fuel injection, essentially consisting of a swirl generator (1) for a combustion air stream and means for the introduction of fuel into the combustion air stream, the means for the introduction of fuel into the combustion air stream comprising at least one first fuel supply (4a) with a first group of fuel outlet orifices (2a) and a second fuel supply (4b) with a second group of fuel outlet orifices (2b) downstream of the first group of fuel outlet orifices (2a), and the first and second group of fuel outlet orifices (2a, 2b) and also inlet orifices for the combustion air stream being arranged along a swirl space (1a) formed by the swirl generator (1), characterized in that, in the transitional region between the first and the second group of fuel outlet orifices (2a, 2b), a separating element (8) is arranged in the swirl space (1a), said separating element separating, at least over a portion of a longitudinal axis (7) of the burner, a first combustion air stream, which enters the swirl space (1a) in the region of the first group of fuel outlet orifices (2a), from a second combustion air stream which flows into the swirl space (1a) in the region of the second group of fuel outlet orifices (2b).
  2. Burner according to Claim 1, characterized in that the separating element (8) is formed by one or more partitions which surround the longitudinal axis (7) of the burner.
  3. Burner according to Claim 1 or 2, characterized in that the separating element (8) is of essentially tubular or bowl-shaped design.
  4. The burner system as claimed in one of Claims 1 to 3, characterized in that the separating element (8) has cooling ducts (11) passing through it.
  5. The burner system as claimed in Claim 4, characterized in that the cooling ducts (11) have outlet orifices toward the combustion chamber (3).
  6. The burner system as claimed in one of Claims 1 to 5, characterized in that the burner has a central fuel lance (5) which extends into the volume formed by the separating element (8).
EP01970076A 2000-10-16 2001-10-03 Burner with progressive fuel injection Expired - Lifetime EP1344002B1 (en)

Applications Claiming Priority (3)

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DE10051221A DE10051221A1 (en) 2000-10-16 2000-10-16 Burner with staged fuel injection
DE10051221 2000-10-16
PCT/IB2001/001817 WO2002033324A1 (en) 2000-10-16 2001-10-03 Burner with progressive fuel injection

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EP1344002B1 true EP1344002B1 (en) 2008-02-27

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EP (1) EP1344002B1 (en)
JP (1) JP4143404B2 (en)
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DE (2) DE10051221A1 (en)
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EP2538139A2 (en) 2011-06-20 2012-12-26 Alstom Technology Ltd Method for operating a combustion device and combustion device for implementing the method

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JP3940705B2 (en) * 2003-06-19 2007-07-04 株式会社日立製作所 Gas turbine combustor and fuel supply method thereof
EP1510755B1 (en) * 2003-09-01 2016-09-28 General Electric Technology GmbH Burner with lance and staged fuel supply.
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CN1232762C (en) 2005-12-21
JP2004514867A (en) 2004-05-20
AU2001290189A1 (en) 2002-04-29
US7189073B2 (en) 2007-03-13
WO2002033324A1 (en) 2002-04-25
US20050175948A1 (en) 2005-08-11
DE10051221A1 (en) 2002-07-11
EP1344002A1 (en) 2003-09-17
US20040053181A1 (en) 2004-03-18
DE50113673D1 (en) 2008-04-10
CN1524172A (en) 2004-08-25
JP4143404B2 (en) 2008-09-03

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