EP2288852A1 - Method for operating a premix burner, and a premix burner for carrying out the method - Google Patents

Method for operating a premix burner, and a premix burner for carrying out the method

Info

Publication number
EP2288852A1
EP2288852A1 EP08873895A EP08873895A EP2288852A1 EP 2288852 A1 EP2288852 A1 EP 2288852A1 EP 08873895 A EP08873895 A EP 08873895A EP 08873895 A EP08873895 A EP 08873895A EP 2288852 A1 EP2288852 A1 EP 2288852A1
Authority
EP
European Patent Office
Prior art keywords
diffusion
nozzles
fuel
premix burner
flame chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08873895A
Other languages
German (de)
French (fr)
Other versions
EP2288852B1 (en
Inventor
Eric Norster
Holger Huitenga
Reiner Brinkmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN Energy Solutions SE
Original Assignee
MAN Diesel and Turbo SE
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Publication date
Application filed by MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2288852A1 publication Critical patent/EP2288852A1/en
Application granted granted Critical
Publication of EP2288852B1 publication Critical patent/EP2288852B1/en
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—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
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14003—Special features of gas burners with more than one nozzle

Definitions

  • the invention relates to a method for operating a premix burner according to claim 1 and a premix burner for carrying out such a method according to claim 5.
  • the pilot flame In addition to stabilizing the combustion process, the pilot flame often also serves to ignite the respective combustion process, so that it is consequently positioned in the vicinity of an ignition orifice of the premix burner. Pollutant emissions take a back seat compared to the stabilization of the combustion process.
  • a premix burner for gaseous fuels and a method for controlling this premix burner is shown in DE 10 2005 054 442 A1.
  • This premix burner has a multi-stage main injection with a large number of main nozzles for injecting a gas-air mixture into a flame chamber and a central pilot gas system.
  • a pilot flame of unmixed main fuel is formed via the pilot gas system. From start up to a predetermined load ratio only a certain number of main nozzles are turned on. If a predetermined load ratio exceeds or exceeds is stepped on, more main nozzles are switched on or already operated main nozzles are fed.
  • This premix burner for gaseous fuels has a main injection and a central multi-stage pilot gas system.
  • the main injection has a nozzle group of main nozzles for injecting a premixed main fuel.
  • the central multi-stage pilot gas system has a nozzle group of diffusion nozzles for blowing in unmixed diffusion fuel and an independently controllable nozzle group of premix nozzles for additional injection of the premixed main fuel.
  • the premix burner When the premix burner is ignited, the largest fuel fraction is introduced via the diffusion stages of the pilot gas system. As the load increases, the premix nozzles of the pilot gas system and main nozzles of the main injection are switched on. The diffusion nozzles are moved back. At full load, the premix nozzles and main nozzles are fully operational and the diffuser nozzles are reduced to a minimum of the total fuel mass flow.
  • a disadvantage of this method is that the stability range of the combustion process, despite the multi-stage pilot gas system is not significantly disseminated. Furthermore, a complex control of the fuel supply is necessary. Furthermore, the premix burner is sensitive to changing fuel compositions.
  • the object of the present invention is to provide a method for operating a premix burner for gaseous fuels, which is more stable to changing environmental conditions and can be easily adapted to changing fuel compositions and fuel qualities, and a premix burner for carrying out such a method.
  • a method according to the invention provides for injecting a gas-air mixture as main fuel via a swirl generator into a flame chamber via a main injection.
  • a diffusion fuel of a central pilot gas system is injected into the flame chamber in the form of at least two partial streams with different directions or orientations.
  • the injection of the diffusion fuel according to the invention as at least two partial streams with different orientations effects a similar effect as a premix.
  • a combustion process with the injection according to the invention shows a substantially improved stability as well as an increased flexibility compared to varying fuel compositions and fuel qualities.
  • the first partial flow is injected transversely or perpendicularly to the flow direction of a main fuel stream forming in the flame chamber.
  • the second partial flow is injected in the flow direction of the main fuel flow.
  • the first partial flow transverse to the flow direction of the main fuel flow causes a similar effect as a premix.
  • the second partial flow in the direction of flow of the main fuel flow shows less turbulence and less mixing than the first partial flow transversely to the flow direction, whereby the diffusion fuel fraction in the flow direction is less sensitive to changes and the respective combustion process is more stable.
  • the gas-air mixture of the main injection is introduced radially into the flame chamber.
  • the gas-air ratio of the main fuel is controlled by the air supply and not by the main fuel nozzles.
  • An inventive premix burner for gaseous fuels has a flame chamber, a Hauptsindüsung for injecting a gas-air mixture as Main fuel in the flame chamber, a swirl generator for swirling the main fuel and arranged in the burner bottom central pilot gas system for injecting a diffusion fuel.
  • the pilot gas system has a multi-stage design with at least one axial diffusion nozzle for injecting a first partial flow of the diffusion fuel and one or more diffusion nozzles arranged obliquely to the longitudinal axis of the burner for feeding in a second partial flow of the diffusion fuel.
  • the at least one employed diffusion nozzle is set in the direction of flow of the main fuel stream.
  • a plurality of axial and annealed diffusion nozzles are provided.
  • the axial diffusion nozzles are located radially on the outside and the employed diffusion nozzles are positioned radially in the interior of the burner bottom.
  • the axial and annealed diffusion nozzles may form two or more concentric circles, the common center being on the burner longitudinal axis.
  • the diffusion nozzles can have different geometries.
  • the diffusion nozzles are formed as bores, grooves or longitudinal slots.
  • the pilot gas system preferably has more axial diffusion nozzles than employed diffusion nozzles. In particular, twice as many axial diffusion nozzles as employed diffusion nozzles can be provided.
  • the premix burner is formed as a can burner with an at least partially cylindrical flame tube which is spaced from the burner bottom via the swirl generator.
  • FIG. 1 shows a longitudinal section through a premix burner according to the invention in the burner bottom region
  • FIG. 2 shows a plan view of the burner bottom from FIG. 1.
  • FIG. 1 shows a greatly simplified partial longitudinal section through a premix burner 2 according to the invention for a gas turbine.
  • the premix burner 2 is designed as a can burner with a cylindrical flame chamber 4 for gaseous or liquid fuel. It has a main injection 6 and a central multi-stage pilot gas system 8 according to the invention.
  • the flame chamber 4 is bounded on one side in the axial direction by a burner base 10 and radially by a flame tube 12.
  • An end section 14 of the flame tube 12 facing away from the burner base 10 is widened in the shape of a funnel.
  • the main injection 6 is used to inject a gas-air mixture as a premixed main fuel 16.
  • the injection takes place radially to the burner longitudinal axis 18 via unspecified main nozzles, which open into a radial swirl generator 20.
  • the main injection has 24 main nozzles.
  • the radial swirl generator 20 is arranged between the burner base 10 and the flame tube 12. It causes the main fuel 16 to be acted upon by a swirl pulse and swirled into the flame chamber 4 occurs. In the flame chamber 4, a main fuel flow whose direction is indicated by the respective arrows.
  • the pilot gas system 8 is used for injecting a non-premixed diffusion fuel and has a multiplicity of axial diffusion nozzles 22a, 22b and a multiplicity of diffusion nozzles 24a, 24b set obliquely to the burner longitudinal axis 18.
  • the diffusion fuel is injected into the flame chamber 4 via the axial diffusion nozzles 22a, 22b and the employed diffusion nozzles 24a, 24b as two partial streams 26, 28.
  • the axial and employed diffusion nozzles 22a, 22b, 24a, 24b are arranged in the burner bottom 10, so that an injection of the partial streams 26, 28 takes place downstream of the entry of the main fuel stream 16.
  • the axial diffusion nozzles 22a, 22b transverse or perpendicular to the flow direction of the main fuel 16 in the flame chamber 4 cause the first partial flow 26 to be intensively mixed with the main fuel 16.
  • the employed diffusion nozzles 24a, 24b are oriented such that the second partial stream 28 is injected into the flame chamber 4 in the flow direction of the main turbulence fuel 16 and the mixing is thus minimized, which promotes the stability of the combustion process.
  • the axial diffusion nozzles 22a, 22b,... And the employed diffusion nozzles 24a, 24b,... Form two concentric circles whose common center point 30 lies on the burner longitudinal axis 18.
  • the axial diffusion nozzles 22a, 22b,... Are located radially outward and the employed diffusion nozzles 24a, 24b,... Are positioned radially inward.
  • the diffusion nozzles 22a, 22b,..., 24a, 24b,... are uniformly distributed over the respective circle, with 24 axial diffusion nozzles 22a, 22b,... And 12 employed diffusion nozzles 24a, 24b,. are provided.
  • the number of axial diffusion nozzles 22a, 22b,... Corresponds here to the number of main nozzles.
  • the axial diffusion nozzles 22 and the employed diffusion nozzles 24 are formed in this embodiment as bores.
  • a swirled gas-air mixture of the main injection 6 is injected radially into the flame chamber 4 via the radial swirl generator 20.
  • a diffusion fuel as a first partial flow 26 and a second partial flow 28 is injected into the flame chamber 4.
  • the first partial stream 26 is injected via the axial diffusion nozzles 22a, 22b,...
  • the second partial stream 28 into the flame chamber 4 via the employed diffusion nozzles 24a, 24b,.
  • the geometry of the diffusion nozzles 22a, 22b,..., 24a, 24b,... is not limited to bores, but that grooves or longitudinal slots are also conceivable.
  • the geometry of the axial or employed diffusion nozzles can vary with each other.
  • the arrangement of the diffusion nozzles 22a, 22b 24a, 24b,... Is not limited to a circular arrangement, but other arrangements such as, for example, a stem positioning are also conceivable. An uneven distribution of the diffusion nozzles is also possible.
  • a method of operating a premix burner for gaseous fuels with a multi-stage pilot gas system the diffusion fuel is injected as at least two partial streams with different orientations in a flame chamber of the premix burner, and a premix burner for performing the method.

Abstract

The invention discloses a method for operating a premix burner for gaseous fuels, having a multi-stage pilot gas system (8), the diffusion fuel of which is injected into a flame chamber (4) of the premix burner as at least two partial flows (26,28) with different orientations, and a premix burner for carrying out the method.

Description

Verfahren zum Betreiben eines Vormischbrenners und ein Vormischbrenner zur Durchführung des Verfahrens Method for operating a premix burner and a premix burner for carrying out the method
Die Erfindung betrifft ein Verfahren zum Betreiben eines Vormischbrenners nach Anspruch 1 und einen Vormischbrenner zur Durchführung eines derartigen Verfahrens nach Anspruch 5.The invention relates to a method for operating a premix burner according to claim 1 and a premix burner for carrying out such a method according to claim 5.
Fremdgezϋndete aber dann selbstlaufende Verbrennungsprozesse werden bei Gasturbinen häufig zur Reduzierung von Schadstoffemissionen über ein Hauptstrombrennstoffsystem bzw. eine Haupteindüsung mit einem mageren außerhalb der jeweiligen Flammkammer erzeugten Gas-Luftgemisch betrieben. Das magere Gas- Luftgemisch führt jedoch dazu, dass der jeweilige Verbrennungsprozess einen entsprechend engen Stabilitätsbereich aufweist. Je enger der Stabilitätsbereich ist, desto anfälliger wird der Verbrennungsprozess gegenüber sich ändernden Betriebsbedingungen, was in einem ungewollten Erlöschen des Verbrennungsprozesses resultieren kann. Zur Stabilisierung des Verbrennungsprozesses weisen bekannte Vor- mischbrenner ein Pilotgassystem auf, über welches eine Pilotflamme aus einem nicht vorgemischten Brennstoff in der Flammkammer aufgebaut wird. Die Pilotflamme dient neben der Stabilisierung des Verbrennungsprozesses häufig ebenfalls zum Zünden des jeweiligen Verbrennungsprozesses, so dass sie konsequenterweise in der Nähe einer Zündmündung des Vormischbrenners positioniert ist. Schadstoff- emissionen treten dabei im Vergleich zur Stabilisierung des Verbrennungsprozesses in den Hintergrund.Foreign ignited but then self-running combustion processes are often operated in gas turbines to reduce pollutant emissions via a main stream fuel system or a Hauptsindüsung with a lean outside the respective flame chamber generated gas-air mixture. The lean gas-air mixture, however, means that the respective combustion process has a correspondingly narrow stability range. The narrower the stability range, the more susceptible the combustion process to changing operating conditions, which can result in an unwanted extinction of the combustion process. To stabilize the combustion process, known premix burners have a pilot gas system, via which a pilot flame of a non-premixed fuel is built up in the flame chamber. In addition to stabilizing the combustion process, the pilot flame often also serves to ignite the respective combustion process, so that it is consequently positioned in the vicinity of an ignition orifice of the premix burner. Pollutant emissions take a back seat compared to the stabilization of the combustion process.
Ein Vormischbrenner für gasförmige Brennstoffe sowie ein Verfahren zur Ansteuerung dieses Vormischbrenners ist in der DE 10 2005 054 442 A1 gezeigt. Dieser Vor- mischbrenner hat eine mehrstufige Haupteindüsung mit einer Vielzahl von Hauptdüsen zur Eindüsung eines Gas-Luftgemisches in eine Flammkammer und ein zentrales Pilotgassystem. Zur Zündung des Gas-Luftgemisches wird über das Pilotgassystem eine Pilotflamme aus unvermischtem Hauptbrennstoff ausgebildet. Vom Anfahren bis zu einem vorbestimmten Lastverhältnis sind nur eine bestimmte Anzahl der Hauptdüsen aufgesteuert. Wenn ein vorbestimmte Lastverhältnis unter- bzw. über- schritten wird, werden weitere Hauptdüsen zugeschaltet oder bereits betriebene Hauptdüsen werden zugesteuert.A premix burner for gaseous fuels and a method for controlling this premix burner is shown in DE 10 2005 054 442 A1. This premix burner has a multi-stage main injection with a large number of main nozzles for injecting a gas-air mixture into a flame chamber and a central pilot gas system. To ignite the gas-air mixture, a pilot flame of unmixed main fuel is formed via the pilot gas system. From start up to a predetermined load ratio only a certain number of main nozzles are turned on. If a predetermined load ratio exceeds or exceeds is stepped on, more main nozzles are switched on or already operated main nozzles are fed.
Ein weiterer Vormischbrenner für Gasturbinen sowie ein Verfahren zum Betreiben eines derartigen Vormischbrenners ist in der DE 103 34 228 A1 beschrieben. Dieser Vormischbrenner für gasförmige Brennstoffe hat eine Haupteindüsung und ein zentrales mehrstufiges Pilotgassystem. Die Haupteindüsung weist eine Düsengruppe von Hauptdüsen zum Eindüsen eines vorgemischten Hauptbrennstoffs auf. Das zentrale mehrstufige Pilotgassystem hat eine Düsengruppe von Diffusionsdüsen zum Eindü- sen von unvermischtem Diffusionsbrennstoff und eine unabhängig ansteuerbare Düsengruppe von Vormischdüsen zum zusätzlichen Eindüsen des vorgemischten Hauptbrennstoffs.Another premix burner for gas turbines and a method for operating such a premix burner is described in DE 103 34 228 A1. This premix burner for gaseous fuels has a main injection and a central multi-stage pilot gas system. The main injection has a nozzle group of main nozzles for injecting a premixed main fuel. The central multi-stage pilot gas system has a nozzle group of diffusion nozzles for blowing in unmixed diffusion fuel and an independently controllable nozzle group of premix nozzles for additional injection of the premixed main fuel.
Bei Zündung des Vormischbrenners wird über die Diffusionsstufen des Pilotgassys- tems der größte Brennstoffteil eingebracht. Mit zunehmender Last werden die Vormischdüsen des Pilotgassystems und Hauptdüsen der Haupteindüsung zugeschaltet. Die Diffusionsdüsen werden zurückgefahren. Bei Volllast sind die Vormischdüsen und Hauptdüsen vollständig im Betrieb und die Diffusionsdüsen sind auf ein Minimum des Gesamtbrennstoffmassenstroms zurückgefahren.When the premix burner is ignited, the largest fuel fraction is introduced via the diffusion stages of the pilot gas system. As the load increases, the premix nozzles of the pilot gas system and main nozzles of the main injection are switched on. The diffusion nozzles are moved back. At full load, the premix nozzles and main nozzles are fully operational and the diffuser nozzles are reduced to a minimum of the total fuel mass flow.
Nachteilig an diesem Verfahren ist, dass der Stabilitätsbereich des Verbrennungs- prozess trotz der mehrstufigen Pilotgassystems nicht wesentlich verbreitet wird. Ferner ist eine aufwendige Steuerung der Brennstoffzufuhr notwendig. Weiterhin reagiert der Vormischbrenner empfindlich auf sich ändernde Brennstoffzusammenset- zungen.A disadvantage of this method is that the stability range of the combustion process, despite the multi-stage pilot gas system is not significantly disseminated. Furthermore, a complex control of the fuel supply is necessary. Furthermore, the premix burner is sensitive to changing fuel compositions.
Aufgabe der vorliegenden Erfindung ist es, ein Verfahren zum Betreiben eines Vormischbrenners für gasförmige Brennstoffe zu schaffen, das sich stabiler gegenüber sich ändernden Umgebungsbedingungen zeigt und einfach auf an sich ändernde Brennstoffzusammensetzungen und Brennstoffqualitäten angepasst werden kann, sowie einen Vormischbrenner zur Durchführung eines derartigen Verfahrens.The object of the present invention is to provide a method for operating a premix burner for gaseous fuels, which is more stable to changing environmental conditions and can be easily adapted to changing fuel compositions and fuel qualities, and a premix burner for carrying out such a method.
Diese Aufgabe wird gelöst durch ein Verfahren mit den Merkmalen des Anspruchs 1 und durch einen Vormischbrenner mit den Merkmalen des Anspruchs 5. Ein erfindungsgemäßes Verfahren sieht vor, über eine Haupteindüsung ein Gas- Luftgemisch als Hauptbrennstoff über einen Drallerzeuger in eine Flammkammer einzudüsen. Ein Diffusionsbrennstoff eines zentralen Pilotgassystems wird in Form von zumindest zwei Teilströmen mit unterschiedlichen Richtungen bzw. Orientierungen in die Flammkammer eingedüst.This object is achieved by a method having the features of claim 1 and by a premix burner having the features of claim 5. A method according to the invention provides for injecting a gas-air mixture as main fuel via a swirl generator into a flame chamber via a main injection. A diffusion fuel of a central pilot gas system is injected into the flame chamber in the form of at least two partial streams with different directions or orientations.
Die erfindungsgemäße Eindüsung des Diffusionsbrennstoffs als zumindest zwei Teilströme mit unterschiedlichen Orientierungen bewirkt einen ähnlichen Effekt wie eine Vormischung. Gleichzeitig zeigt ein Verbrennungsprozess mit der erfindungsgemäßen Eindüsung eine wesentlich verbesserter Stabilität sowie eine erhöhter Flexibilität gegenüber variierenden Brennstoffzusammensetzungen und Brennstoffqualitäten.The injection of the diffusion fuel according to the invention as at least two partial streams with different orientations effects a similar effect as a premix. At the same time, a combustion process with the injection according to the invention shows a substantially improved stability as well as an increased flexibility compared to varying fuel compositions and fuel qualities.
Bei einem bevorzugten Ausführungsbeispiel wird der erste Teilstrom quer bzw. senk- recht zur Strömungsrichtung eines sich in der Flammkammer ausbildenden Hauptbrennstoffstroms eingedüst. Der zweite Teilstrom wird in Strömungsrichtung des Hauptbrennstoffstroms eingedüst. Der erste Teilstrom quer zur Strömungsrichtung des Hauptbrennstoffstroms bewirkt einen ähnlichen Effekt wie eine Vormischung. Der zweite Teilstrom in Strömungsrichtung des Hauptbrennstoffstroms zeigt weniger Verwirbelungen und eine geringere Vermischung als der erste Teilstrom quer zur Strömungsrichtung, wodurch der Diffusionsbrennstoffanteil in Strömungsrichtung unempfindlicher gegenüber Veränderungen ist und der jeweilige Verbrennungsprozesses stabiler abläuft.In a preferred embodiment, the first partial flow is injected transversely or perpendicularly to the flow direction of a main fuel stream forming in the flame chamber. The second partial flow is injected in the flow direction of the main fuel flow. The first partial flow transverse to the flow direction of the main fuel flow causes a similar effect as a premix. The second partial flow in the direction of flow of the main fuel flow shows less turbulence and less mixing than the first partial flow transversely to the flow direction, whereby the diffusion fuel fraction in the flow direction is less sensitive to changes and the respective combustion process is more stable.
Vorzugsweise wird das Gas-Luftgemisch der Haupteindüsung radial in die Flammkammer eingebracht.Preferably, the gas-air mixture of the main injection is introduced radially into the flame chamber.
Bei einem Ausführungsbeispiel wird das Gas-Luftverhältnis des Hauptbrennstoffs über die Luftzufuhr und nicht über das Auf- bzw. Zusteuern von Hauptbrennstoffdü- sen geregelt.In one embodiment, the gas-air ratio of the main fuel is controlled by the air supply and not by the main fuel nozzles.
Ein erfindungsgemäßer Vormischbrenner für gasförmige Brennstoffe hat eine Flammkammer, eine Haupteindüsung zum Eindüsen eines Gas-Luftgemisches als Hauptbrennstoff in die Flammkammer, einen Drallerzeuger zur Verwirbelung des Hauptbrennstoffs und ein im Brennerboden angeordnetes zentrales Pilotgassystem zum Eindüsen eines Diffusionsbrennstoffs. Erfindungsgemäß ist das Pilotgassystem mehrstufig mit zumindest einer axialen Diffusionsdüse zum Eindüsen eines ersten Teilstroms des Diffusionsbrennstoffs und einer oder mehrerer schräg zur Brennerlängsachse angestellten Diffusionsdüse zum Einspeisen eines zweiten Teilstroms des Diffusionsbrennstoffs ausgeführt.An inventive premix burner for gaseous fuels has a flame chamber, a Hauptsindüsung for injecting a gas-air mixture as Main fuel in the flame chamber, a swirl generator for swirling the main fuel and arranged in the burner bottom central pilot gas system for injecting a diffusion fuel. According to the invention, the pilot gas system has a multi-stage design with at least one axial diffusion nozzle for injecting a first partial flow of the diffusion fuel and one or more diffusion nozzles arranged obliquely to the longitudinal axis of the burner for feeding in a second partial flow of the diffusion fuel.
Bei einem Ausführungsbeispiel ist die zumindest eine angestellte Diffusionsdüse in Strömungsrichtung des Hauptbrennstoffstroms angestellt.In one embodiment, the at least one employed diffusion nozzle is set in the direction of flow of the main fuel stream.
Bevorzugterweise sind eine Vielzahl von axialen und angestellten Diffusionsdüsen vorgesehen. Dabei sind die axialen Diffusionsdüsen radial außenliegend und die angestellten Diffusionsdüsen radial innenliegend im Brennerboden positioniert.Preferably, a plurality of axial and annealed diffusion nozzles are provided. In this case, the axial diffusion nozzles are located radially on the outside and the employed diffusion nozzles are positioned radially in the interior of the burner bottom.
Die axialen und angestellten Diffusionsdüsen können zwei oder mehr zueinander konzentrische Kreise bilden, deren gemeinsamer Mittelpunkt auf der Brennerlängsachse liegt.The axial and annealed diffusion nozzles may form two or more concentric circles, the common center being on the burner longitudinal axis.
Die Diffusionsdüsen können unterschiedliche Geometrien aufweisen. Beispielsweise sind die Diffusionsdüsen als Bohrungen, Nuten oder Längsschlitze ausgebildet.The diffusion nozzles can have different geometries. For example, the diffusion nozzles are formed as bores, grooves or longitudinal slots.
Bevorzugterweise weist das Pilotgassystem mehr axiale Diffusionsdüsen als angestellte Diffusionsdüsen auf. Insbesondere können doppelt so viele axiale Diffusions- düsen wie angestellte Diffusionsdüsen vorgesehen sein.The pilot gas system preferably has more axial diffusion nozzles than employed diffusion nozzles. In particular, twice as many axial diffusion nozzles as employed diffusion nozzles can be provided.
Bei einem Ausführungsbeispiel ist der Vormischbrenner als ein Dosenbrenner mit einem zumindest abschnittsweise zylindrischen Flammrohr ausgebildet, das über den Drallerzeuger vom Brennerboden beabstandet ist.In one embodiment, the premix burner is formed as a can burner with an at least partially cylindrical flame tube which is spaced from the burner bottom via the swirl generator.
Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche. Im Folgenden wird ein bevorzugtes Ausführungsbeispiel der Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigenOther advantageous embodiments of the invention are the subject of further subclaims. In the following, a preferred embodiment of the invention is explained in more detail with reference to schematic representations. Show it
Fig. 1 einen Längsschnitt durch einen erfindungsgemäßen Vormischbrenner im Brennerbodenbereich, und Fig. 2 eine Draufsicht auf den Brennerboden aus Figur 1.1 shows a longitudinal section through a premix burner according to the invention in the burner bottom region, and FIG. 2 shows a plan view of the burner bottom from FIG. 1.
Figur 1 zeigt einen stark vereinfachten Teillängsschnitt durch einen erfindungsgemäßen Vormischbrenner 2 für eine Gasturbine. Der Vormischbrenner 2 ist als ein Dosenbrenner mit einer zylindrischen Flammkammer 4 für gasförmigen oder flüssigen Brennstoff ausgebildet. Er weist eine Haupteindüsung 6 und ein erfindungsgemäßen zentrales mehrstufigen Pilotgassystem 8 auf.FIG. 1 shows a greatly simplified partial longitudinal section through a premix burner 2 according to the invention for a gas turbine. The premix burner 2 is designed as a can burner with a cylindrical flame chamber 4 for gaseous or liquid fuel. It has a main injection 6 and a central multi-stage pilot gas system 8 according to the invention.
Die Flammkammer 4 wird in axialer Richtung einseitig von einem Brennerboden 10 und radial von einem Flammrohr 12 begrenzt. Ein vom Brennerboden 10 abgewand- ter Endabschnitt 14 des Flammrohrs 12 ist trichterförmig erweitert.The flame chamber 4 is bounded on one side in the axial direction by a burner base 10 and radially by a flame tube 12. An end section 14 of the flame tube 12 facing away from the burner base 10 is widened in the shape of a funnel.
Die Haupteindüsung 6 dient zum Eindüsen eines Gas-Luftgemisches als vorgemischter Hauptbrennstoff 16. Das Eindüsen erfolgt radial zur Brennerlängsachse 18 über nicht bezeichnete Hauptdüsen, die in einen radialen Drallerzeuger 20 münden. Vorzugsweise weist die Haupteindüsung 24 Hauptdüsen auf.The main injection 6 is used to inject a gas-air mixture as a premixed main fuel 16. The injection takes place radially to the burner longitudinal axis 18 via unspecified main nozzles, which open into a radial swirl generator 20. Preferably, the main injection has 24 main nozzles.
Der radiale Drallerzeuger 20 ist zwischen dem Brennerboden 10 und dem Flammrohr 12 angeordnet. Er bewirkt, dass der Hauptbrennstoff 16 mit einem Drallimpuls beaufschlagt wird und verwirbelt in die Flammkammer 4 eintritt. In der Flammkammer 4 bildet sich ein Hauptbrennstoffstrom dessen Richtung durch die jeweiligen Pfeile angedeutet ist.The radial swirl generator 20 is arranged between the burner base 10 and the flame tube 12. It causes the main fuel 16 to be acted upon by a swirl pulse and swirled into the flame chamber 4 occurs. In the flame chamber 4, a main fuel flow whose direction is indicated by the respective arrows.
Das Pilotgassystem 8 dient zum Eindüsen eines nicht vorgemischten Diffusionsbrennstoffs und weist eine Vielzahl von axialen Diffusionsdüsen 22a, 22b und eine Vielzahl von zur Brennerlängsachse 18 schräg angestellten Diffusionsdüsen 24a, 24b auf. Der Diffusionsbrennstoff wird über die axialen Diffusionsdüsen 22a, 22b und die angestellten Diffusionsdüsen 24a, 24b als zwei Teilströme 26, 28 in die Flammkammer 4 eingedüst. Die axialen und angestellten Diffusionsdüsen 22a, 22b, 24a, 24b sind im Brennerboden 10 angeordnet, so dass eine Eindüsung der Teilströme 26, 28 stromabwärts dem Eintritt des Hauptbrennstoffstroms 16 erfolgt. Die axialen Diffusionsdüsen 22a, 22b quer bzw. senkrecht zur Strömrichtung des Hauptbrennstoffs 16 in der Flamm- kammer 4 bewirken, dass der erste Teilstrom 26 besonders intensiv mit dem Hauptbrennstoff 16 durchmischt wird. Die angestellte Diffusionsdüsen 24a, 24b sind derart orientiert, dass der zweite Teilstrom 28 in Strömungsrichtung des verwirbelten Hauptbrennstoffs 16 in die Flammkammer 4 eingedüst wird und die Vermischung somit minimiert ist, was die Stabilität des Verbrennungsprozesses fördert.The pilot gas system 8 is used for injecting a non-premixed diffusion fuel and has a multiplicity of axial diffusion nozzles 22a, 22b and a multiplicity of diffusion nozzles 24a, 24b set obliquely to the burner longitudinal axis 18. The diffusion fuel is injected into the flame chamber 4 via the axial diffusion nozzles 22a, 22b and the employed diffusion nozzles 24a, 24b as two partial streams 26, 28. The axial and employed diffusion nozzles 22a, 22b, 24a, 24b are arranged in the burner bottom 10, so that an injection of the partial streams 26, 28 takes place downstream of the entry of the main fuel stream 16. The axial diffusion nozzles 22a, 22b transverse or perpendicular to the flow direction of the main fuel 16 in the flame chamber 4 cause the first partial flow 26 to be intensively mixed with the main fuel 16. The employed diffusion nozzles 24a, 24b are oriented such that the second partial stream 28 is injected into the flame chamber 4 in the flow direction of the main turbulence fuel 16 and the mixing is thus minimized, which promotes the stability of the combustion process.
Gemäß der Stirnansicht des Brennerbodens 10 in Figur 2 bilden die axialen Diffusionsdüsen 22a, 22b,... und die angestellten Diffusionsdüsen 24a, 24b,... zwei konzentrische Kreise, deren gemeinsamer Mittelpunkt 30 auf der Brennerlängsachse 18 liegt. Dabei sind die axialen Diffusionsdüsen 22a, 22b,... radial außenliegend und die angestellten Diffusionsdüsen 24a, 24b,... radial innenliegend positioniert. Die Diffusionsdüsen 22a, 22b,..., 24a, 24b,... sind gleichmäßig über den jeweiligen Kreis verteilt, wobei in dem dargestellten Ausführungsbeispiel 24 axiale Diffusionsdüsen 22a, 22b, ... und 12 angestellte Diffusionsdüsen 24a, 24b,... vorgesehen sind. Somit gibt es doppelt so viele axiale Diffusionsdüsen 22a, 22b,... wir angestellte Diffusionsdü- sen 24a, 24b Die Anzahl der axialen Diffusionsdüsen 22a, 22b, ...entspricht hier der Anzahl der Hauptdüsen.According to the end view of the burner base 10 in FIG. 2, the axial diffusion nozzles 22a, 22b,... And the employed diffusion nozzles 24a, 24b,... Form two concentric circles whose common center point 30 lies on the burner longitudinal axis 18. In this case, the axial diffusion nozzles 22a, 22b,... Are located radially outward and the employed diffusion nozzles 24a, 24b,... Are positioned radially inward. The diffusion nozzles 22a, 22b,..., 24a, 24b,... Are uniformly distributed over the respective circle, with 24 axial diffusion nozzles 22a, 22b,... And 12 employed diffusion nozzles 24a, 24b,. are provided. Thus, there are twice as many axial diffusion nozzles 22a, 22b, ... we employed diffusion nozzles 24a, 24b The number of axial diffusion nozzles 22a, 22b,... Corresponds here to the number of main nozzles.
Die axialen Diffusionsdüsen 22 und die angestellten Diffusionsdüsen 24 sind in diesem Ausführungsbeispiel als Bohrungen ausgebildet.The axial diffusion nozzles 22 and the employed diffusion nozzles 24 are formed in this embodiment as bores.
Bei einem bevorzugten erfindungsgemäßen Verfahren zum Betreiben des Vormisch- brenners 2 wird über den radialen Drallerzeuger 20 ein verwirbeltes Gas-Luft- Gemisch der Haupteindüsung 6 in die Flammkammer 4 radial eingedüst. Mittels des mehrstufigen Pilotgassystems 8 wird ein Diffusionsbrennstoff als ein erster Teilstrom 26 und ein zweiter Teilstrom 28 in die Flammkammer 4 eingedüst. Der erste Teilstrom 26 wird über die axialen Diffusionsdüsen 22a, 22b,... und der zweite Teilstrom 28 über die angestellten Diffusionsdüsen 24a, 24b,... in die Flammkammer 4 eingedüst. Eine Anpassung des Gas-Luftverhältnisses des Hauptrennstoffs 16 an den jeweiligen Lastzustand erfolgt über eine Änderung der Luftzufuhr des Hauptbrennstoffs 16. Eine Anpassung des Gas-Luftgemisches über ein bekanntes Auf- bzw. Zusteuerung der Hauptdüsen ist somit nicht vorgesehen.In a preferred method according to the invention for operating the premix burner 2, a swirled gas-air mixture of the main injection 6 is injected radially into the flame chamber 4 via the radial swirl generator 20. By means of the multi-stage pilot gas system 8, a diffusion fuel as a first partial flow 26 and a second partial flow 28 is injected into the flame chamber 4. The first partial stream 26 is injected via the axial diffusion nozzles 22a, 22b,... And the second partial stream 28 into the flame chamber 4 via the employed diffusion nozzles 24a, 24b,. An adjustment of the gas-air ratio of the main fuel 16 to the respective load state via a change in the air supply of the main fuel 16. An adaptation of the gas-air mixture on a known up or Zusteuerung the main nozzles is thus not provided.
Es sei erwähnt, dass auch eine Aufteilung des Diffusionsbrennstoffs auf mehr als zwei Teilströme 26, 28 vorstellbar ist. Ebenso ist diese Anmeldung nicht auf zwei gleichgroße bzw. zwei unterschiedliche Teilströme 26, 28 des Diffusionsbrennstoffstroms begrenzt.It should be mentioned that it is also conceivable to divide the diffusion fuel into more than two partial flows 26, 28. Likewise, this application is not limited to two equal or two different part streams 26, 28 of the diffusion fuel stream.
Weiterhin sei erwähnt, dass die Geometrie der Diffusionsdüsen 22a, 22b, ..., 24a, 24b,... nicht auf Bohrungen beschränkt ist, sondern dass auch Nuten oder Längsschlitze vorstellbar sind. Ebenso kann die Geometrie der axialen bzw. angestellten Diffusionsdüsen untereinander variieren. Ferner ist die Anordnung der Diffusionsdüsen 22a, 22b 24a, 24b,... nicht auf eine kreisförmige Anordnung begrenzt ist, sondern es sind ebenfalls andere Anordnungen wie zum Beispiel eine Stempositio- nierung vorstellbar. Eine ungleichmäßige Verteilung der Diffusionsdüsen ist ebenfalls möglich.It should also be mentioned that the geometry of the diffusion nozzles 22a, 22b,..., 24a, 24b,... Is not limited to bores, but that grooves or longitudinal slots are also conceivable. Likewise, the geometry of the axial or employed diffusion nozzles can vary with each other. Furthermore, the arrangement of the diffusion nozzles 22a, 22b 24a, 24b,... Is not limited to a circular arrangement, but other arrangements such as, for example, a stem positioning are also conceivable. An uneven distribution of the diffusion nozzles is also possible.
Offenbart ist ein Verfahren zum Betreiben eines Vormischbrenners für gasförmige Brennstoffe mit einem mehrstufigen Pilotgassystem, dessen Diffusionsbrennstoff als zumindest zwei Teilströme mit unterschiedlichen Orientierungen in eine Flammkammer des Vormischbrenners eingedüst wird, und ein Vormischbrenner zur Durchführung des Verfahrens. Disclosed is a method of operating a premix burner for gaseous fuels with a multi-stage pilot gas system, the diffusion fuel is injected as at least two partial streams with different orientations in a flame chamber of the premix burner, and a premix burner for performing the method.
l CVCV
BezuαszeichenlisteLIST OF REFERENCE NUMERALS
Vormischbrennerpremix
4 Flammkammer4 flame chamber
6 Haupteindüsung6 main injection
8 Pilotgassystem8 pilot gas system
10 Brennerboden10 burner bottom
12 Flammrohr12 flame tube
14 Endabschnitt14 end section
16 Hauptbrennstoff16 main fuel
18 Brennerlängsachse18 burner longitudinal axis
20 Drallerzeuger20 swirl generator
22a, 22b, ... axiale Diffusionsdüse22a, 22b, ... axial diffusion nozzle
24a, 24b, ... angestellte Diffusionsdüse24a, 24b, ... Employed diffusion nozzle
26 erster Teilstrom des Diffusionsbrennstoffs26 first partial flow of the diffusion fuel
28 zweiter Teilstrom des Diffusionsbrennstoffs28 second partial flow of the diffusion fuel
30 Mittelpunkt 30 midpoint

Claims

Ansprüche claims
1. Verfahren zum Betreiben eines Vormischbrenners (2) für Gasturbinen mit den Schritten: • Eindüsen eines Gas-Luftgemisches als Hauptbrennstoff (16) über einen1. A method for operating a premix burner (2) for gas turbines, comprising the steps of: • injecting a gas-air mixture as the main fuel (16) via a
Drallerzeuger (20) in eine Flammkammer (4),Swirl generator (20) in a flame chamber (4),
• zentrales Eindüsen eines ersten Teilstroms (26) eines Diffusionsbrennstoffs in die Flammkammer (4), undCentral injection of a first partial stream (26) of a diffusion fuel into the flame chamber (4), and
• zentrales Eindüsen eines zweiten Teilstroms (28) des Diffusionsbrenn- Stoffs in die Flammkammer (4), wobei die Teilströme (26, 28) unterschiedliche Orientierungen aufweisen.Central injection of a second partial flow (28) of the diffusion fuel into the flame chamber (4), wherein the partial flows (26, 28) have different orientations.
2. Verfahren nach Anspruch 1 , wobei der erste Teilstrom (26) im Wesentlichen quer zum einen sich in der Flammkammer (4) ausbildenden Hauptbrennstoffstroms5 eingedüst wird und der zweite Teilstrom (28) im Wesentlichen in Strömungsrichtung des Hauptbrennstoffstroms eingedüst wird.2. The method of claim 1, wherein the first partial flow (26) is injected substantially transversely to a in the flame chamber (4) forming Hauptbrennstoffstroms5 and the second partial stream (28) is injected substantially in the flow direction of the main fuel flow.
3. Verfahren nach Anspruch 1 oder 2, wobei der Hauptbrennstoff (16) radial eingedüst wird. 03. The method of claim 1 or 2, wherein the main fuel (16) is injected radially. 0
4. Verfahren nach Anspruch 1 , 2 oder 3, wobei das Gas-Luftverhältnis des Hauptbrennstoffs (16) über die Luftzufuhr geregelt wird.4. The method of claim 1, 2 or 3, wherein the gas-air ratio of the main fuel (16) is regulated by the air supply.
5. Vormischbrenner für Gasturbinen zur Durchführung des Verfahrens nach An-5 spruch 1 mit einer Flammkammer (4), einer Haupteindüsung (6) zum Eindüsen eines Gas-Luftgemisches als Hauptbrennstoff (16) in die Flammkammer (4), einem Drallerzeuger (20) zum Verwirbeln des Hauptbrennstoff (16) und einem im Brennerboden (10) ausgebildeten zentralen Pilotgassystems (8) zum Eindüsen eines Diffusionsbrennstoffs, dadurch gekennzeichnet, dass im Brennerboden (10)0 zumindest eine axiale Diffusionsdüse (22a, 22b,...) zum Einspeisen eines ersten Teilstroms (26) des Diffusionsbrennstoffs quer zum sich in der Flammkammer (4) ausbildenden Hauptbrennstoffstroms und optional zumindest eine schräg zur Brennerlängsachse (18) angestellte Diffusionsdüse (24a, 24b,...) zum Eindüsen eines zweiten Teilstroms (28) des Diffusionsbrennstoffs angeordnet sind. R 5. Premix burner for gas turbines for carrying out the method according to An-5, claim 1 with a flame chamber (4), a Haupteindüsung (6) for injecting a gas-air mixture as the main fuel (16) in the flame chamber (4), a swirl generator (20). for swirling the main fuel (16) and a central pilot gas system (8) for injecting a diffusion fuel formed in the burner bottom (10), characterized in that at least one axial diffusion nozzle (22a, 22b, ...) for feeding in the burner bottom (10) a first partial flow (26) of the diffusion fuel transverse to the main fuel flow forming in the flame chamber (4) and optionally at least one diffusion nozzle (24a, 24b, ...) positioned obliquely to the burner longitudinal axis (18) for injecting a second partial flow (28) of the diffusion fuel are arranged. R
6. Vormischbrenner nach Anspruch 5, wobei die zumindest eine angestellte Diffusionsdüse (22a, 22b,...) in Strömungsrichtung des Hauptbrennstoffstroms angestellt ist.6. premix burner according to claim 5, wherein the at least one employee employed diffusion nozzle (22a, 22b, ...) is set in the direction of flow of the main fuel stream.
7. Vormischbrenner nach Anspruch 6, wobei eine Vielzahl von radial außenliegenden axialen Diffusionsdüsen (22a, 22b,...) und eine Vielzahl von radial innenliegenden angestellten Diffusionsdüsen (24a, 24b,...) vorgesehen sind.7. premix burner according to claim 6, wherein a plurality of radially outer axial diffusion nozzles (22a, 22b, ...) and a plurality of radially inwardly employed annulus diffusion nozzles (24a, 24b, ...) are provided.
8. Vormischbrenner nach Anspruch 6 oder 7, wobei die axialen Diffusionsdüsen (22a, 22b,...) und die angestellten Diffusionsdüsen (24a, 24b,...) zumindest zwei zueinander konzentrische Kreise bilden, deren gemeinsamer Mittelpunkt (30) auf der Brennerlängsachse (18) liegt.8. premix burner according to claim 6 or 7, wherein the axial diffusion nozzles (22a, 22b, ...) and the employed diffuser nozzles (24a, 24b, ...) form at least two concentric circles whose common center (30) on the Burner longitudinal axis (18) is located.
9. Vormischbrenner nach einem der Ansprüche 5 bis 8, wobei die axialen Diffusi- onsdüsen (22a, 22b,...) eine andere Geometrie als die angestellten Diffusionsdüsen (24a, 24b,...) aufweisen.9. premix burner according to one of claims 5 to 8, wherein the axial diffusion onsdüsen (22a, 22b, ...) have a different geometry than the employed diffuser nozzles (24a, 24b, ...).
10. Vormischbrenner nach Anspruch 9, wobei die axialen Diffusionsdüsen (22a, 22b,...) und die angestellten Diffusionsdüsen (24a, 24b,...) Bohrungen sind.10. premix burner according to claim 9, wherein the axial diffusion nozzles (22a, 22b, ...) and the employed diffuser nozzles (24a, 24b, ...) are bores.
11. Vormischbrenner nach einem der Ansprüche 5 bis 10, wobei das Pilotgassystem (8) mehr axiale Diffusionsdüsen (22a, 22b,...) als angestellte Diffusionsdüsen (24a, 24b,...), insbesondere doppelt so viele axiale Diffusionsdüsen (22a, 22b,...) wie angestellte Diffusionsdüsen(24a, 24b,...), aufweist.11. premix burner according to one of claims 5 to 10, wherein the pilot gas system (8) more axial diffusion nozzles (22a, 22b, ...) than employed diffusion nozzles (24a, 24b, ...), in particular twice as many axial diffusion nozzles (22a , 22b, ...) as employed diffusion nozzles (24a, 24b, ...), has.
12. Vormischbrenner nach einem der Ansprüche 5 bis 11 , wobei die Flammkammer (4) in der Nähe des Brennerbodens (10) von dem Drallerzeuger (20) und einem zylindrischen Flammrohr (12) radial begrenzt ist. 12. premix burner according to one of claims 5 to 11, wherein the flame chamber (4) in the vicinity of the burner bottom (10) of the swirl generator (20) and a cylindrical flame tube (12) is radially limited.
EP08873895.0A 2008-04-16 2008-11-03 Method for operating a premix burner, and a premix burner for carrying out the method Active EP2288852B1 (en)

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PCT/EP2008/009256 WO2009127240A1 (en) 2008-04-16 2008-11-03 Method for operating a premix burner, and a premix burner for carrying out the method

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009054669A1 (en) 2009-12-15 2011-06-16 Man Diesel & Turbo Se Burner for a turbine
EP2400222A1 (en) * 2010-06-28 2011-12-28 Siemens Aktiengesellschaft A combustion apparatus
EP2629008A1 (en) * 2012-02-15 2013-08-21 Siemens Aktiengesellschaft Inclined fuel injection of fuel into a swirler slot

Family Cites Families (19)

* 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
CH672541A5 (en) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
US5452574A (en) * 1994-01-14 1995-09-26 Solar Turbines Incorporated Gas turbine engine catalytic and primary combustor arrangement having selective air flow control
DE69617290T2 (en) * 1995-01-13 2002-06-13 Europ Gas Turbines Ltd Combustion device for gas turbine engine
GB2333832A (en) * 1998-01-31 1999-08-04 Europ Gas Turbines Ltd Multi-fuel gas turbine engine combustor
FR2788109B1 (en) * 1998-12-30 2001-06-08 Total Raffinage Distribution DEVICE FOR IMPROVING THE BURNING OF GASEOUS FUELS
NO312379B1 (en) * 2000-02-14 2002-04-29 Ulstein Turbine As Burner for gas turbines
FR2811410B1 (en) * 2000-07-10 2002-10-04 Gaz De France INCREASED GAS AND AIR MIXTURE BURNER
JP3590594B2 (en) * 2001-04-25 2004-11-17 川崎重工業株式会社 Liquid fuel-fired low NOx combustor for gas turbine engine
DE10334228A1 (en) 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Operating premix burner involves selecting second, third further fuel nozzle opening groups, applying fuel to them independently of each other so second, third groups form premixing, diffusion stages
EP1614967B1 (en) 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Method and premixed combustion system
DE102004049491A1 (en) * 2004-10-11 2006-04-20 Alstom Technology Ltd premix
JP4015656B2 (en) 2004-11-17 2007-11-28 三菱重工業株式会社 Gas turbine combustor
US20060191268A1 (en) 2005-02-25 2006-08-31 General Electric Company Method and apparatus for cooling gas turbine fuel nozzles
DE102005015152A1 (en) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Premix burner for a gas turbine combustor
ATE480737T1 (en) * 2005-06-17 2010-09-15 Alstom Technology Ltd BURNER FOR PREMIXED COMBUSTION
US20070234735A1 (en) * 2006-03-28 2007-10-11 Mosbacher David M Fuel-flexible combustion sytem and method of operation
EP1890083A1 (en) * 2006-08-16 2008-02-20 Siemens Aktiengesellschaft Fuel injector for a gas turbine engine
GB2443431B (en) * 2006-11-02 2008-12-03 Siemens Ag Fuel-injector nozzle

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009127240A1 *

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CA2717487C (en) 2013-01-29
DE102008019117A1 (en) 2009-10-22
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US10557634B2 (en) 2020-02-11
US20110167832A1 (en) 2011-07-14

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