EP0849533A2 - Burner arrangement for a gas turbine - Google Patents

Burner arrangement for a gas turbine Download PDF

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Publication number
EP0849533A2
EP0849533A2 EP97810834A EP97810834A EP0849533A2 EP 0849533 A2 EP0849533 A2 EP 0849533A2 EP 97810834 A EP97810834 A EP 97810834A EP 97810834 A EP97810834 A EP 97810834A EP 0849533 A2 EP0849533 A2 EP 0849533A2
Authority
EP
European Patent Office
Prior art keywords
burner
lance
axis
compressed air
outlet openings
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
EP97810834A
Other languages
German (de)
French (fr)
Other versions
EP0849533A3 (en
EP0849533B1 (en
Inventor
Jakob Prof. Dr. Keller
Paul Marlow
Robin Mc Millan
Martin Dr. Valk
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.)
Alstom SA
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0849533A2 publication Critical patent/EP0849533A2/en
Publication of EP0849533A3 publication Critical patent/EP0849533A3/en
Application granted granted Critical
Publication of EP0849533B1 publication Critical patent/EP0849533B1/en
Anticipated expiration legal-status Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/76—Protecting flame and burner parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention relates to the field of Burner technology for gas turbines. It relates to a burner arrangement for a gas turbine, comprising at least one in Plenum of the gas turbine arranged burner, which with a internal injection chamber opens into a combustion chamber and outside with compressed air from a compressor stage of the gas turbine is acted upon, as well as a fuel lance assigned to the burner for the optional supply of liquid and / or gaseous fuels, which fuel lance is a central Liquid fuel pipe and a the liquid fuel pipe Has concentrically surrounding pilot gas pipe, the Tubes in a lance head at the top of the fuel lance end in associated outlet openings, and which fuel lance with the lance head in with the injection chamber in Connected inner tube of the burner is insertable.
  • Such a burner arrangement is e.g. from the German Publication DE-A1-43 06 956 known.
  • the burner lance is usually a two-fuel lance ("dual fuel lance"), i.e. in the fuel lance can optionally use gaseous fuel (pilot gas) and liquid fuel (usually an oil-water mixture) be fed.
  • dual fuel lance a two-fuel lance
  • gaseous fuel pilot gas
  • liquid fuel usually an oil-water mixture
  • These are concentric in the lance appropriate pipes (liquid fuel pipe, pilot gas pipe) arranged, the channels for the gas and the liquid fuel form.
  • the channels end at the tip of the lance (in the lance head) in associated outlet openings for the respective fuel.
  • the lance is in a corresponding position with the lance head Inner tube of the burner, so that the exiting Fuel in the injection chamber adjoining the inner tube reached.
  • the inner liquid fuel pipe flows (Liquid fuel channel) of the fuel lance an oil-water mixture.
  • Flows in the start phase in contrast, in gas operation, pilot gas in the ring-shaped pilot gas channel between the liquid fuel pipe and the pilot gas pipe.
  • pilot gas in the ring-shaped pilot gas channel between the liquid fuel pipe and the pilot gas pipe A the two fuel channels are always out of operation. Sometimes even both channels are not used at the same time.
  • the task is the one mentioned in your burner arrangement Kind of solved by protecting against intrusion of hot gases and / or hot liquid fuel into the outlet openings of the pipes when not in use Pipes in the lance head in the immediate vicinity of the outlet openings an additional opening is provided for the pipes is through which compressed air flows into the injection chamber, and that means are provided which compressed air the plenum surrounding the burner to the additional opening to lead. This will immediately on the lance head An air screen is located near the outlet openings of the fuel pipes generates a backflow into the outlet openings safely prevented. Because the compressed air required for this is direct taken from the surrounding plenum on the burner, there are no additional lines in the lance and to the lance and associated connections, valves and the like.
  • a first preferred embodiment of the burner arrangement according to the invention is characterized in that the means include an intermediate space for guiding the compressed air, which in the flow direction in front of the lance head between the pilot gas pipe and the inner tube of the burner is arranged, that the space with the plenum surrounding the burner via at least one from the outside through the burner the inner tube leading inlet bore is connected to that of the Gap with the additional opening over at least a compressed air duct led through the lance head stands, and that the space is annular and concentrically surrounds the pilot gas pipe.
  • the gap can be easily formed by that the (outer) pilot gas pipe of the lance in the direction of flow in front of the lance head in the outside diameter compared to the Inner tube of the burner is significantly reduced.
  • the inlet holes and compressed air ducts require very little change on the burner or lance head.
  • Burner arrangement is characterized in that several Inlet holes around the burner axis or lance axis are distributed that several compressed air channels around the Burner axis or lance axis are distributed around and that the compressed air channels are inclined in the direction of flow Run the burner axis or lance axis.
  • the outlet opening for the liquid fuel in the lance head is preferably arranged centrally, and the additional The opening in the lance head is preferably designed as a ring opening, which is the central outlet for the liquid fuel concentrically surrounds. This creates an air jacket generates the central outlet for the liquid fuel encloses and shields in a ring.
  • the burner arrangement 1 is a first general embodiment in longitudinal section for a burner arrangement according to the present Invention reproduced.
  • the burner arrangement 1 comprises a burner 2, in the present case as a double-cone burner is trained.
  • the burner 2 encloses an injection chamber 8, in a combustion chamber, not shown opens (see DE-A1-43 06 956).
  • the burner is outside surrounded by the plenum 7 of the gas turbine, which with compressed air from the compressor stage of the gas turbine.
  • An inner tube 6 is arranged in the center of the burner 2, in which has a fuel lance 9 with an outer tube 10 and a lance tip is inserted, which is the end of a pilot gas pipe 11 and the adjoining lance head 12 includes.
  • the burner 2 further comprises two external ones Main gas channels 3 and 4 (see also Fig. 2) through which the Main gas introduced and through a variety of inflow openings 5 (of which in FIG. 1 for the sake of clarity only five are shown as examples) in the injection chamber 8 is injected.
  • the outside diameter of the pilot gas pipe 11 is opposite to that Inner diameter of the inner tube 6 (at least immediately behind the lance head 12) significantly reduced, so that between the pilot gas pipe 11 and the inner pipe 6 an annular space 13 results.
  • This space 13 can - as from the cross section in Fig. 2 is clear - by two opposite Inlet holes 14 and 15 compressed air from the inflow surrounding plenum 7 and is there to form a Air screen in the exit area of the lance head 12 for Available.
  • the formation of the air screen can be different This is done and is to follow two exemplary embodiments 3 and 4 are explained, the show the inner structure in the area of the lance head 12.
  • Fig. 3 shows a first embodiment in longitudinal section (Partial figure (b)) and in cross section (partial figure (a)) along level B-B from sub-figure (b).
  • the in the inner tube 6 of the burner 2 stuck fuel lance 9 includes next to that already mentioned pilot gas pipe 11 and the lance head 12 a concentric Liquid fuel tube arranged in the pilot gas tube 11 19.
  • the liquid fuel brought up and through an associated outlet opening 20 in Lance head 12 injected into the injection space 8.
  • With gas operation becomes pilot gas in the pilot gas channel 16 between the liquid fuel pipe 19 and the pilot gas pipe 11 and through several outlet openings 23 and 23a-c in the lance head injected into the injection chamber 8.
  • the outlet openings 23a-c are formed by the liquid fuel pipe 19 at the tip 21 a cross section in the form of a circular bore of the pilot gas pipe 11 inscribed Triangle (see Fig. 3 (a)).
  • annular opening 17 is provided, which is the central Outlet opening 22 of the liquid fuel channel 20 concentrically surrounds.
  • the ring opening 17 is by several (three) compressed air ducts distributed around the lance axis 18 or 18a-c with compressed air from the space 13 supplied.
  • the compressed air channels 18 and 18a-c are located in the radial direction outside the outlet openings 23 or 23a-c, which open into the ring opening 17.
  • the compressed air channels 18 or 18a-c and the inner wall of the ring opening 17th are preferably at an angle to the burner axis or lance axis trained to run. This forms the emerging Compressed air a conically tapered air screen that a backflow of hot gases and / or hot oil from Injection chamber 8 in one of the (just not used) outlet openings 22 and 23, 23a-c effectively prevented.
  • FIG. 4 A second exemplary embodiment is shown in FIG. 4.
  • the one in the inner tube 6 of the burner 2 comprises Fuel lance 9 an outer pilot gas tube 24, which is concentric surrounds a central liquid fuel tube 31.
  • the liquid fuel formed by the two pipes 24 and 31 and pilot gas channels 32 and 25 correspond to the channels 20 and 16 from FIG. 3.
  • the tubes 24 and 31 also end here the lance head 12, which also has an annular opening 27, which is the central outlet opening 33 for the liquid fuel channel 32 concentrically surrounds.
  • the compressed air for the ring opening 27 is made of the annular space 26, which in connection with the plenum via the inlet bores 14, 15 stands radially inward over a plurality of (six) directed compressed air channels 28 brought up.
  • the pilot gas is not in this embodiment in the Ring opening 27 injected, but by a plurality of (Six) separate outlet openings 29, which are connected to the pilot gas channel 25 via corresponding pilot gas bores 30 in connection stand.
  • the outlet openings 29 are outside the ring opening 27.
  • the air screen generated with the ring opening 27 not only shields the lance head 12 as a whole but also separates between the outlet openings 29 for the pilot gas and the outlet opening 33 for the Liquid fuel, which in particular causes a backflow effective between the different outlet openings of the lance is prevented.
  • the limited space in the lance head 12 is used particularly well when the outlet openings 29 for the pilot gas or pilot gas bores 30 and the compressed air channels 28 around the burner axis or lance axis are arranged alternately around.
  • the invention results in a burner arrangement, effective in a simple manner with little effort it prevents hot gases and / or hot oil from escaping the burner into the unused channels of the burner lance can flow back.

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

Abstract

The combustion assembly has an additional opening (17) near the outlet openings (22,23,23a-23c) of the tubes (11,19), to prevent the entry of hot gases and/or hot liquid fuel entering the outlet openings of the tubes when they are not in use in the lance head (12). Compressed air flows through the additional opening (17) into the fuel injection zone. Compressed air is fed from the plenum round the burner to the additional opening. The gas turbine assembly has a lance head for the selective feed of an injected liquid and/or gas fuel.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Brennertechnik für Gasturbinen. Sie betrifft eine Brenneranordnung für eine Gasturbine, umfassend wenigstens einen im Plenum der Gasturbine angeordneten Brenner, welcher mit einem innenliegenden Einspritzraum in eine Brennkammer mündet und aussen mit Druckluft von einer Kompressorstufe der Gasturbine beaufschlagt ist, sowie eine dem Brenner zugeordnete Brennstofflanze für die wahlweise Zufuhr von flüssigen und/oder gasförmigen Brennstoffen, welche Brennstofflanze ein zentrales Flüssigbrennstoffrohr und ein das Flüssigbrennstoffrohr konzentrisch umgebendes Pilotgasrohr aufweist, wobei die Rohre in einem Lanzenkopf an der Spitze der Brennstofflanze in zugehörigen Austrittsöffnungen enden, und welche Brennstofflanze mit dem Lanzenkopf in ein mit dem Einspritzraum in Verbindung stehendes Innenrohr des Brenners einführbar ist.The present invention relates to the field of Burner technology for gas turbines. It relates to a burner arrangement for a gas turbine, comprising at least one in Plenum of the gas turbine arranged burner, which with a internal injection chamber opens into a combustion chamber and outside with compressed air from a compressor stage of the gas turbine is acted upon, as well as a fuel lance assigned to the burner for the optional supply of liquid and / or gaseous fuels, which fuel lance is a central Liquid fuel pipe and a the liquid fuel pipe Has concentrically surrounding pilot gas pipe, the Tubes in a lance head at the top of the fuel lance end in associated outlet openings, and which fuel lance with the lance head in with the injection chamber in Connected inner tube of the burner is insertable.

Eine derartige Brenneranordnung ist z.B. aus der Deutschen Offenlegungschrift DE-A1-43 06 956 bekannt. Such a burner arrangement is e.g. from the German Publication DE-A1-43 06 956 known.

STAND DER TECHNIKSTATE OF THE ART

Für stationäre Gasturbinen in Kraftwerken haben sich seit längerem Brennkammern mit sogenannten Doppelkegelbrennern bewährt, denen von aussen durch einsteckbare Brennerlanzen Brennstoff zugeführt wird (siehe die eingangs genannte Druckschrift). Die Brennerlanze ist dabei meist als Zwei-Brennstoff-Lanze ("dual fuel lance") ausgelegt, d.h. in der Brennstofflanze kann wahlweise gasförmiger Brennstoff (Pilotgas) und flüssiger Brennstoff (üblicherweise ein Oel-Wasser-Mischung) zugeführt werden. Dazu sind in der Lanze konzentrisch entsprechende Rohre (Flüssigbrennstoffrohr, Pilotgasrohr) angeordnet, die Kanäle für das Gas und den Flüssigbrennstoff bilden. Die Kanäle enden an der Lanzenspitze (im Lanzenkopf) in zugehörigen Austrittsöffnungen für den jeweiligen Brennstoff. Die Lanze steckt mit dem Lanzenkopf in einem entsprechenden Innenrohr des Brenners, so dass der austretende Brennstoff in den an das Innenrohr anschliessenden Einspritzraum gelangt.For stationary gas turbines in power plants have been around Proven longer combustion chambers with so-called double-cone burners, those from the outside by insertable burner lances Fuel is supplied (see the publication mentioned above). The burner lance is usually a two-fuel lance ("dual fuel lance"), i.e. in the fuel lance can optionally use gaseous fuel (pilot gas) and liquid fuel (usually an oil-water mixture) be fed. These are concentric in the lance appropriate pipes (liquid fuel pipe, pilot gas pipe) arranged, the channels for the gas and the liquid fuel form. The channels end at the tip of the lance (in the lance head) in associated outlet openings for the respective fuel. The lance is in a corresponding position with the lance head Inner tube of the burner, so that the exiting Fuel in the injection chamber adjoining the inner tube reached.

Während des normalen Oelbetriebs fliesst in dem inneren Flüssigbrennstoffrohr (Flüssigbrennstoffkanal) der Brennstofflanze ein Oel-Wasser-Gemisch. In der Startphase fliesst dagegen im Gasbetrieb Pilotgas im ringförmigen Pilotgaskanal zwischen dem Flüssigbrennstoffrohr und dem Pilotgasrohr. Eine der beiden Brennstoffkanäle ist dabei immer ausser Betrieb. Manchmal werden sogar beide Kanäle gleichzeitig nicht benutzt.During normal oil operation, the inner liquid fuel pipe flows (Liquid fuel channel) of the fuel lance an oil-water mixture. Flows in the start phase in contrast, in gas operation, pilot gas in the ring-shaped pilot gas channel between the liquid fuel pipe and the pilot gas pipe. A the two fuel channels are always out of operation. Sometimes even both channels are not used at the same time.

Da in den nicht benutzten Kanälen der notwendige Ueberdruck gegenüber dem Einspritzraum des Brenners fehlt, kann es vorkommen, dass heisse Gase oder heisses Oel vom Brenner her in die nicht benutzten Kanäle eindringen und zu einer zeitweisen oder dauerhaften Beeinträchtigung der Funktion der Brennstofflanze führen. Es wäre daher wünschenswert, die Brenneranordnung so auszubilden, dass ein solches Eindringen auf einfache Weise sicher verhindert wird.Because the necessary overpressure in the unused channels compared to the burner's injection chamber, it can happen that hot gases or hot oil from the burner the unused channels penetrate and at times or permanent impairment of the function of the Guide the fuel lance. It would therefore be desirable that Form the burner arrangement so that such penetration is safely prevented in a simple manner.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, eine Brenneranordnung anzugeben, bei welcher mit geringem Aufwand das Eindringen von heissen Gasen oder heissem Oel aus dem Brenner in einen nicht benutzten Brennstoffkanal der Brennerlanze sicher vermieden wird.It is therefore an object of the invention to provide a burner arrangement at which the penetration of hot gases or hot oil from the burner into one used fuel channel of the burner lance safely avoided becomes.

Die Aufgabe wird bei deiner Brenneranordnung der eingangs genannten Art dadurch gelöst, dass zum Schutz vor einem Eindringen von heissen Gasen und/oder heissem Flüssigbrennstoff in die Austrittsöffnungen der Rohre bei Nichtbenutzung dieser Rohre im Lanzenkopf in unmittelbarer Nähe der Austrittsöffnungen der Rohre eine zusätzliche Oeffnung vorgesehen ist, durch welche Druckluft in den Einspritzraum ausströmt, und dass Mittel vorgesehen sind, welche Druckluft aus dem den Brenner umgebenden Plenum zu der zusätzlichen Oeffnung führen. Hierdurch wird am Lanzenkopf in unmittelbarer Nähe der Austrittsöffnungen der Brennstoffrohre ein Luftschirm erzeugt, der ein Rückströmen in die Austrittsöffnungen sicher unterbindet. Da die dazu erforderliche Druckluft direkt am Brenner aus dem umgebenden Plenum entnommen wird, entfallen zusätzliche Leitungen in der Lanze und zur Lanze hin, sowie zugehörige Anschlüsse, Ventile und dgl..The task is the one mentioned in your burner arrangement Kind of solved by protecting against intrusion of hot gases and / or hot liquid fuel into the outlet openings of the pipes when not in use Pipes in the lance head in the immediate vicinity of the outlet openings an additional opening is provided for the pipes is through which compressed air flows into the injection chamber, and that means are provided which compressed air the plenum surrounding the burner to the additional opening to lead. This will immediately on the lance head An air screen is located near the outlet openings of the fuel pipes generates a backflow into the outlet openings safely prevented. Because the compressed air required for this is direct taken from the surrounding plenum on the burner, there are no additional lines in the lance and to the lance and associated connections, valves and the like.

Eine erste bevorzugte Ausführungsform der Brenneranordnung nach der Erfindung zeichnet sich dadurch aus, dass die Mittel zur Führung der Druckluft einen Zwischenraum umfassen, welcher in Strömungsrichtung vor dem Lanzenkopf zwischen dem Pilotgasrohr und dem Innenrohr des Brenners angeordnet ist, dass der Zwischenraum mit dem den Brenner umgebenden Plenum über wenigstens eine von aussen durch den Brenner hindurch in das Innenrohr führende Einlassbohrung verbunden ist, dass der Zwischenraum mit der zusätzlichen Oeffnung über wenigstens einen durch den Lanzenkopf geführten Druckluftkanal in Verbindung steht, und dass der Zwischenraum ringförmig ausgebildet ist und das Pilotgasrohr konzentrisch umgibt. Der Zwischenraum kann auf einfache Weise dadurch gebildet werden, dass das (äussere) Pilotgasrohr der Lanze in Strömungsrichtung vor dem Lanzenkopf im Aussendurchmesser gegenüber dem Innenrohr des Brenners deutlich reduziert wird. Die Einlassbohrungen und Druckluftkanäle erfordern nur sehr geringe Aenderungen am Brenner bzw. dem Lanzenkopf.A first preferred embodiment of the burner arrangement according to the invention is characterized in that the means include an intermediate space for guiding the compressed air, which in the flow direction in front of the lance head between the pilot gas pipe and the inner tube of the burner is arranged, that the space with the plenum surrounding the burner via at least one from the outside through the burner the inner tube leading inlet bore is connected to that of the Gap with the additional opening over at least a compressed air duct led through the lance head stands, and that the space is annular and concentrically surrounds the pilot gas pipe. The gap can be easily formed by that the (outer) pilot gas pipe of the lance in the direction of flow in front of the lance head in the outside diameter compared to the Inner tube of the burner is significantly reduced. The inlet holes and compressed air ducts require very little change on the burner or lance head.

Eine weitere bevorzugte Ausführungsform der erfindungsgemässen Brenneranordnung ist dadurch gekennzeichnet, dass mehrere Einlassbohrungen um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind, dass mehrere Druckluftkanäle um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind, und dass die Druckluftkanäle in Strömungsrichtung schräg zur Brennerachse bzw. Lanzenachse hin verlaufen. Durch diese Art der Anordnung wird ein besonders gleichmässiger und stabiler Luftschirm erzeugt.Another preferred embodiment of the invention Burner arrangement is characterized in that several Inlet holes around the burner axis or lance axis are distributed that several compressed air channels around the Burner axis or lance axis are distributed around and that the compressed air channels are inclined in the direction of flow Run the burner axis or lance axis. By this way the arrangement becomes a particularly uniform and stable Air screen generated.

Die Austrittsöffnung für den Flüssigbrennstoff im Lanzenkopf ist vorzugsweise zentral angeordnet, und die zusätzliche Oeffnung im Lanzenkopf ist vorzugsweise als Ringöffnung ausgebildet, welche die zentrale Austrittsöffnung für den Flüssigbrennstoff konzentrisch umgibt. Dadurch wird ein Luftmantel erzeugt, der den zentralen Austritt für den Flüssigbrennstoff ringförmig umschliesst und abschirmt. The outlet opening for the liquid fuel in the lance head is preferably arranged centrally, and the additional The opening in the lance head is preferably designed as a ring opening, which is the central outlet for the liquid fuel concentrically surrounds. This creates an air jacket generates the central outlet for the liquid fuel encloses and shields in a ring.

In einer ersten alternativen Weiterbildung dieser Ausführungsform sind mehrere Austrittsöffnungen für das Pilotgas um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet, und die Austrittsöffnungen münden in die Ringöffnung. Hierdurch werden die nicht benutzten Austrittsöffnungen für beide Brennstoffe einfach abgeschirmt.In a first alternative development of this embodiment there are several outlet openings for the pilot gas the burner axis or lance axis distributed around and the outlet openings open into the ring opening. Hereby the unused outlet openings for both Simply shielded fuels.

In einer zweiten alternativen Weiterbildung dieser Ausführungsform sind mehrere Austrittsöffnungen für das Pilotgas um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet, und die Austrittsöffnungen liegen ausserhalb der Ringöffnung. Hierdurch wird zusätzlich zu der Abschirmung der nicht benutzten Austrittsöffnungen eine Trennung mittels des Luftvorhangs zwischen der innenliegenden Austrittsöffnung für den Flüssigbrennstoff und den aussenliegenden Austrittsöffnungen für das Pilotgas erreicht.In a second alternative development of this embodiment there are several outlet openings for the pilot gas the burner axis or lance axis distributed around and the outlet openings are outside the ring opening. This will, in addition to shielding the unused Outlet openings a separation by means of the air curtain between the inside outlet for the Liquid fuel and the external outlet openings reached for the pilot gas.

Weitere Ausführungsformen ergeben sich aus den abhängigen Ansprüchen.Further embodiments result from the dependent claims.

KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES

Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen

Fig. 1
im Längsschnitt ein erstes allgemeines Ausführungsbeispiel für eine Brenneranordnung gemäss vorliegender Erfindung;
Fig. 2
den Querschnitt durch die Brenneranordnung gemäss Fig. 1 entlang der Ebene A-A mit den Einlassbohrungen für die abschirmende Druckluft;
Fig. 3
im Längsschnitt (Teilfigur (b)) und im Querschnitt (Teilfigur (a)) entlang der Ebene B-B aus Teilfigur (b) ein zweites bevorzugtes Ausführungsbeispiel für eine erfindungsgemässe Brenneranordnung mit gemeinsamer Ringöffnung für die Druckluft und das Pilotgas; und
Fig. 4
in der Frontalansicht (Teilfigur (a)), im Längsschnitt (Teilfigur(b)) und im Querschnitt (Teilfigur(c)) entlang der Ebene C-C in Teilfigur (b) ein drittes bevorzugtes Ausführungsbeispiel für eine erfindungsgemässe Brenneranordnung mit einer Plazierung des Luftschirms zwischen dem Flüssigbrennstoffaustritt und dem Pilotgasaustritt.
The invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing. Show it
Fig. 1
in longitudinal section a first general embodiment for a burner arrangement according to the present invention;
Fig. 2
the cross section through the burner arrangement of Figure 1 along the plane AA with the inlet holes for the shielding compressed air.
Fig. 3
in longitudinal section (partial figure (b)) and in cross section (partial figure (a)) along plane BB from partial figure (b) a second preferred exemplary embodiment of a burner arrangement according to the invention with a common ring opening for the compressed air and the pilot gas; and
Fig. 4
in the frontal view (partial figure (a)), in longitudinal section (partial figure (b)) and in cross section (partial figure (c)) along the plane CC in partial figure (b) a third preferred exemplary embodiment of a burner arrangement according to the invention with a placement of the air screen between the liquid fuel outlet and the pilot gas outlet.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS OF CARRYING OUT THE INVENTION

In der Fig. 1 ist im Längsschnitt ein erstes allgemeines Ausführungsbeispiel für eine Brenneranordnung gemäss vorliegender Erfindung wiedergegeben. Die Brenneranordnung 1 umfasst einen Brenner 2, der im vorliegenden Fall als Doppelkegelbrenner ausgebildet ist. Der Brenner 2 umschliesst einen Einspritzraum 8, der in eine nicht eingezeichnet Brennkammer mündet (siehe dazu die DE-A1-43 06 956). Der Brenner ist aussen vom Plenum 7 der Gasturbine umgeben, welches mit Druckluft aus der Kompressorstufe der Gasturbine beaufschlagt ist. Im Zentrum des Brenners 2 ist ein Innenrohr 6 angeordnet, in welches eine Brennstofflanze 9 mit einem Aussenrohr 10 und einer Lanzenspitze eingesteckt ist, welche das Ende eines Pilotgasrohres 11 und den daran anschliessenden Lanzenkopf 12 umfasst. Der Brenner 2 umfasst weiterhin zwei aussenliegende Hauptgaskanäle 3 und 4 (siehe auch Fig. 2), durch welche das Hauptgas herangeführt und durch eine Vielzahl von Einströmöffnungen 5 (von denen in Fig. 1 der Uebersichtlichkeit halber nur fünf beispielhaft eingezeichnet sind) in den Einspritzraum 8 eingedüst wird.1 is a first general embodiment in longitudinal section for a burner arrangement according to the present Invention reproduced. The burner arrangement 1 comprises a burner 2, in the present case as a double-cone burner is trained. The burner 2 encloses an injection chamber 8, in a combustion chamber, not shown opens (see DE-A1-43 06 956). The burner is outside surrounded by the plenum 7 of the gas turbine, which with compressed air from the compressor stage of the gas turbine. An inner tube 6 is arranged in the center of the burner 2, in which has a fuel lance 9 with an outer tube 10 and a lance tip is inserted, which is the end of a pilot gas pipe 11 and the adjoining lance head 12 includes. The burner 2 further comprises two external ones Main gas channels 3 and 4 (see also Fig. 2) through which the Main gas introduced and through a variety of inflow openings 5 (of which in FIG. 1 for the sake of clarity only five are shown as examples) in the injection chamber 8 is injected.

Der Aussendurchmesser des Pilotgasrohres 11 ist gegenüber dem Innendurchmesser des Innenrohres 6 (zumindest gleich hinter dem Lanzenkopf 12) deutlich reduziert, so dass sich zwischen dem Pilotgasrohr 11 und dem Innenrohr 6 ein ringförmiger Zwischenraum 13 ergibt. In diesen Zwischenraum 13 kann - wie aus dem Querschnitt in Fig. 2 deutlich wird - durch zwei sich gegenüberliegende Einlassbohrungen 14 und 15 Druckluft aus dem umgebenden Plenum 7 einströmen und steht dort zur Bildung eines Luftschirms im Austrittsbereich des Lanzenkopfes 12 zur Verfügung. Die Bildung des Luftschirms kann auf unterschiedliche Weise erfolgen und soll nachfolgend an zwei Ausführungsbeispielen gemäss den Fig. 3 und 4 erläutert werden, die dazu den inneren Aufbau im Bereich des Lanzenkopfes 12 zeigen.The outside diameter of the pilot gas pipe 11 is opposite to that Inner diameter of the inner tube 6 (at least immediately behind the lance head 12) significantly reduced, so that between the pilot gas pipe 11 and the inner pipe 6 an annular space 13 results. In this space 13 can - as from the cross section in Fig. 2 is clear - by two opposite Inlet holes 14 and 15 compressed air from the inflow surrounding plenum 7 and is there to form a Air screen in the exit area of the lance head 12 for Available. The formation of the air screen can be different This is done and is to follow two exemplary embodiments 3 and 4 are explained, the show the inner structure in the area of the lance head 12.

Fig. 3 zeigt ein erstes Ausführungsbeispiel im Längsschnitt (Teilfigur (b)) und im Querschnitt (Teilfigur (a)) entlang der Ebene B-B aus Teilfigur (b). Die im Innenrohr 6 des Brenners 2 steckende Brennstofflanze 9 umfasst neben dem bereits erwähnten Pilotgasrohr 11 und dem Lanzenkopf 12 ein konzentrisch im Pilotgasrohr 11 angeordnetes Flüssigbrennstoffrohr 19. Im zentralen Flüssigbrennstoffkanal 20 des Flüssigbrennstoffrohres wird beim Betrieb des Brenners mit Flüssigbrennstoff (meist eine Oel-Wasser-Mischung) der Flüssigbrennstoff herangeführt und durch eine zugehörige Austrittsöffnung 20 im Lanzenkopf 12 in den Einspritzraum 8 eingespritzt. Beim Gasbetrieb wird Pilotgas im Pilotgaskanal 16 zwischen dem Flüssigbrennstoffrohr 19 und dem Pilotgasrohr 11 herangeführt und durch mehrere Austrittsöffnungen 23 bzw. 23a-c im Lanzenkopf in die Einspritzkammer 8 eingedüst. Die Austrittsöffnungen 23a-c werden dadurch gebildet, dass das Flüssigbrennstoffrohr 19 an der Spitze 21 einen Querschnitt in Form eines in die kreisförmige Bohrung des Pilotgasrohres 11 einbeschriebenen Dreiecks aufweist (siehe Fig. 3(a)).Fig. 3 shows a first embodiment in longitudinal section (Partial figure (b)) and in cross section (partial figure (a)) along level B-B from sub-figure (b). The in the inner tube 6 of the burner 2 stuck fuel lance 9 includes next to that already mentioned pilot gas pipe 11 and the lance head 12 a concentric Liquid fuel tube arranged in the pilot gas tube 11 19. In the central liquid fuel channel 20 of the liquid fuel pipe when operating the burner with liquid fuel (usually an oil-water mixture) the liquid fuel brought up and through an associated outlet opening 20 in Lance head 12 injected into the injection space 8. With gas operation becomes pilot gas in the pilot gas channel 16 between the liquid fuel pipe 19 and the pilot gas pipe 11 and through several outlet openings 23 and 23a-c in the lance head injected into the injection chamber 8. The outlet openings 23a-c are formed by the liquid fuel pipe 19 at the tip 21 a cross section in the form of a circular bore of the pilot gas pipe 11 inscribed Triangle (see Fig. 3 (a)).

Zur Bildung des Luftschirmes ist nun im Frontbereich des Lanzenkopfes 12 eine Ringöffnung 17 vorgesehen, welche die zentrale Austrittsöffnung 22 des Flüssigbrennstoffkanals 20 konzentrisch umgibt. Die Ringöffnung 17 wird durch mehrere (drei) um die Lanzenachse herum verteilt angeordnete Druckluftkanäle 18 bzw. 18a-c mit Druckluft aus dem Zwischenraum 13 versorgt. Die Druckluftkanäle 18 bzw. 18a-c liegen dabei in radialer Richtung ausserhalb der Austrittsöffnungen 23 bzw. 23a-c, welche in die Ringöffnung 17 münden. Die Druckluftkanäle 18 bzw. 18a-c und die Innenwand der Ringöffnung 17 sind vorzugsweise schräg zur Brennerachse bzw. Lanzenachse hin verlaufend ausgebildet. Dadurch bildet die austretende Druckluft einen sich konisch verjüngenden Luftschirm, der eine Rückströmung von heissen Gasen und/oder heissem Oel vom Einspritzraum 8 in eine der (gerade nicht benutzten) Austrittsöffnungen 22 bzw. 23, 23a-c wirksam unterbindet.To form the air screen is now in the front area of the lance head 12 an annular opening 17 is provided, which is the central Outlet opening 22 of the liquid fuel channel 20 concentrically surrounds. The ring opening 17 is by several (three) compressed air ducts distributed around the lance axis 18 or 18a-c with compressed air from the space 13 supplied. The compressed air channels 18 and 18a-c are located in the radial direction outside the outlet openings 23 or 23a-c, which open into the ring opening 17. The compressed air channels 18 or 18a-c and the inner wall of the ring opening 17th are preferably at an angle to the burner axis or lance axis trained to run. This forms the emerging Compressed air a conically tapered air screen that a backflow of hot gases and / or hot oil from Injection chamber 8 in one of the (just not used) outlet openings 22 and 23, 23a-c effectively prevented.

Ein zweites Ausführungsbeispiel ist in Fig. 4 wiedergegeben. Auch hier umfasst die im Innenrohr 6 des Brenners 2 steckende Brennstofflanze 9 ein äusseres Pilotgasrohr 24, welches konzentrisch ein zentrales Flüssigbrennstoffrohr 31 umgibt. Die durch die beiden Rohre 24 und 31 gebildeten Flüssigbrennstoff- und Pilotgaskanäle 32 bzw. 25 entsprechen den Kanälen 20 und 16 aus Fig. 3. Die Rohre 24 und 31 enden auch hier in dem Lanzenkopf 12, der ebenfalls eine Ringöffnung 27 aufweist, welche die zentrale Austrittsöffnung 33 für den Flüssigbrennstoffkanal 32 konzentrisch umgibt. Die Druckluft für die Ringöffnung 27 wird aus dem ringförmigen Zwischenraum 26, der über die Einlassbohrungen 14, 15 mit dem Plenum in Verbindung steht, über eine Mehrzahl von (sechs) radial nach innen gerichteten Druckluftkanälen 28 herangeführt. Das Pilotgas wird in diesem Ausführungsbeispiel jedoch nicht in die Ringöffnung 27 eingedüst, sondern durch eine Mehrzahl von (sechs) separaten Austrittsöffnungen 29, die mit dem Pilotgaskanal 25 über entsprechende Pilotgasbohrungen 30 in Verbindung stehen.A second exemplary embodiment is shown in FIG. 4. Here too, the one in the inner tube 6 of the burner 2 comprises Fuel lance 9 an outer pilot gas tube 24, which is concentric surrounds a central liquid fuel tube 31. The liquid fuel formed by the two pipes 24 and 31 and pilot gas channels 32 and 25 correspond to the channels 20 and 16 from FIG. 3. The tubes 24 and 31 also end here the lance head 12, which also has an annular opening 27, which is the central outlet opening 33 for the liquid fuel channel 32 concentrically surrounds. The compressed air for the ring opening 27 is made of the annular space 26, which in connection with the plenum via the inlet bores 14, 15 stands radially inward over a plurality of (six) directed compressed air channels 28 brought up. The pilot gas is not in this embodiment in the Ring opening 27 injected, but by a plurality of (Six) separate outlet openings 29, which are connected to the pilot gas channel 25 via corresponding pilot gas bores 30 in connection stand.

Die Austrittsöffnungen 29 liegen in diesem Fall ausserhalb der Ringöffnung 27. Der mit der Ringöffnung 27 erzeugte Luftschirm schirmt damit nicht nur den Lanzenkopf 12 als Ganzes ab, sondern liegt auch trennend zwischen den Austrittsöffnungen 29 für das Pilotgas und der Austrittsöffnung 33 für den Flüssigbrennstoff, wodurch insbesondere eine Rückströmung zwischen den verschiedenen Austrittsöffnungen der Lanze wirksam verhindert wird. Der beschränkte Platz im Lanzenkopf 12 wird dabei besonders gut ausgenutzt, wenn die Austrittsöffnungen 29 für das Pilotgas bzw. die Pilotgasbohrungen 30 und die Druckluftkanäle 28 um die Brennerachse bzw. Lanzenachse herum alternierend angeordnet sind.In this case, the outlet openings 29 are outside the ring opening 27. The air screen generated with the ring opening 27 not only shields the lance head 12 as a whole but also separates between the outlet openings 29 for the pilot gas and the outlet opening 33 for the Liquid fuel, which in particular causes a backflow effective between the different outlet openings of the lance is prevented. The limited space in the lance head 12 is used particularly well when the outlet openings 29 for the pilot gas or pilot gas bores 30 and the compressed air channels 28 around the burner axis or lance axis are arranged alternately around.

Insgesamt ergibt sich mit der Erfindung eine Brenneranordnung, bei der mit geringem Aufwand auf einfache Weise wirksam verhindert wird, dass heisse Gase und/oder heisses Oel aus dem Brenner in die nicht benutzten Kanäle der Brennerlanze zurückströmen können.Overall, the invention results in a burner arrangement, effective in a simple manner with little effort it prevents hot gases and / or hot oil from escaping the burner into the unused channels of the burner lance can flow back.

BEZEICHNUNGSLISTELIST OF DESIGNATIONS

11
BrenneranordnungBurner arrangement
22nd
Brenner (insb. Doppelkegelbrenner) Burner (esp. Double cone burner)
3,43.4
HauptgaskanalMain gas duct
55
EinströmöffnungInflow opening
66
Innenrohr (Brenner)Inner tube (burner)
77
Plenumplenum
88th
EinspritzraumInjection chamber
99
BrennstofflanzeFuel lance
1010th
AussenrohrOuter tube
1111
PilotgasrohrPilot gas pipe
1212th
LanzenkopfLance head
1313
Zwischenraum (ringförmig)Space (ring-shaped)
14,1514.15
Einlassbohrung (Druckluft)Inlet bore (compressed air)
1616
PilotgaskanalPilot gas duct
1717th
RingöffnungRing opening
18, 18a-c18, 18a-c
DruckluftkanalCompressed air duct
1919th
FlüssigbrennstoffrohrLiquid fuel pipe
2020th
FlüssigbrennstoffkanalLiquid fuel channel
2121
Spitze (Flüssigbrennstoffrohr)Tip (liquid fuel tube)
2222
Austrittsöffnung (Flüssigbrennstoffkanal)Outlet opening (liquid fuel channel)
23,23a-c23.23a-c
Austrittsöffnung (Pilotgaskanal)Outlet opening (pilot gas channel)
2424th
PilotgasrohrPilot gas pipe
2525th
PilotgaskanalPilot gas duct
2626
Zwischenraum (ringförmig)Space (ring-shaped)
2727
RingöffnungRing opening
2828
DruckluftkanalCompressed air duct
2929
Austrittsöffnung (Pilotgaskanal)Outlet opening (pilot gas channel)
3030th
PilotgasbohrungPilot gas well
3131
FlüssigbrennstoffrohrLiquid fuel pipe
3232
FlüssigbrennstoffkanalLiquid fuel channel
3333
Austrittsöffnung (Flüssigbrennstoffkanal)Outlet opening (liquid fuel channel)

Claims (10)

Brenneranordnung (1) für eine Gasturbine, umfassend wenigstens einen im Plenum (7) der Gasturbine angeordneten Brenner (2), welcher mit einem innenliegenden Einspritzraum (8) in eine Brennkammer mündet und aussen mit Druckluft von einer Kompressorstufe der Gasturbine beaufschlagt ist, sowie eine dem Brenner (2) zugeordnete Brennstofflanze (9) für die wahlweise Zufuhr von flüssigen und/oder gasförmigen Brennstoffen, welche Brennstofflanze (9) ein zentrales Flüssigbrennstoffrohr (19, 31) und ein das Flüssigbrennstoffrohr (19, 31) konzentrisch umgebendes Pilotgasrohr (11, 24) aufweist, wobei die Rohre (11, 19, 24, 31) in einem Lanzenkopf (12) an der Spitze der Brennstofflanze (9) in zugehörigen Austrittsöffnungen (22, 23, 23a-c, 29, 33) enden, und welche Brennstofflanze (9) mit dem Lanzenkopf (12) in ein mit dem Einspritzraum (8) in Verbindung stehendes Innenrohr (6) des Brenners (2) einführbar ist. dadurch gekennzeichnet, dass zum Schutz vor einem Eindringen von heissen Gasen und/oder heissem Flüssigbrennstoff in die Austrittsöffnungen (22, 23, 23a-c, 29, 33) der Rohre (11, 19, 24, 31) bei Nichtbenutzung dieser Rohre im Lanzenkopf (12) in unmittelbarer Nähe der Austrittsöffnungen (22, 23, 23a-c, 29, 33) der Rohre (11, 19, 24, 31) eine zusätzliche Oeffnung (17, 27) vorgesehen ist, durch welche Druckluft in den Einspritzraum (8) ausströmt, und dass Mittel vorgesehen sind, welche Druckluft aus dem den Brenner (2) umgebenden Plenum (7) zu der zusätzlichen Oeffnung (17, 27) führen.Combustion arrangement (1) for a gas turbine, comprising at least one arranged in the plenum (7) of the gas turbine Burner (2), which has an internal injection space (8) opens into a combustion chamber and outside with compressed air from a compressor stage of the gas turbine is applied, and a fuel lance (9) assigned to the burner (2) for the optional supply of liquid and / or gaseous fuels, which fuel lance (9) is a central liquid fuel pipe (19, 31) and a the liquid fuel pipe (19, 31) has a concentrically surrounding pilot gas pipe (11, 24), the tubes (11, 19, 24, 31) in a lance head (12) at the tip of the fuel lance (9) in associated Exit openings (22, 23, 23a-c, 29, 33) end, and which Fuel lance (9) with the lance head (12) in one with the Injection chamber (8) related inner tube (6) of the Burner (2) is insertable. characterized in that at Protection against the penetration of hot gases and / or hot liquid fuel into the outlet openings (22, 23, 23a-c, 29, 33) of the tubes (11, 19, 24, 31) when not in use of these tubes in the lance head (12) in the immediate vicinity of the Outlet openings (22, 23, 23a-c, 29, 33) of the tubes (11, 19, 24, 31) an additional opening (17, 27) is provided, through which compressed air flows into the injection chamber (8), and that means are provided which compressed air from the Burner (2) surrounding plenum (7) to the additional opening (17, 27) lead. Brenneranordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Mittel zur Führung der Druckluft einen Zwischenraum (13, 26) umfassen, welcher in Strömungsrichtung vor dem Lanzenkopf (12) zwischen dem Pilotgasrohr (11) und dem Innenrohr (6) des Brenners (2) angeordnet ist, dass der Zwischenraum (13, 26) mit dem den Brenner (2) umgebenden Plenum (7) über wenigstens eine von aussen durch den Brenner (2) hindurch in das Innenrohr (6) führende Einlassbohrung (14, 15) verbunden ist, und dass der Zwischenraum (13, 26) mit der zusätzlichen Oeffnung (17, 27) über wenigstens einen durch den Lanzenkopf (12) geführten Druckluftkanal (18, 18a-c, 28) in Verbindung steht.Burner arrangement according to claim 1, characterized in that the means for guiding the compressed air have a gap (13, 26), which in the direction of flow the lance head (12) between the pilot gas pipe (11) and the Inner tube (6) of the burner (2) is arranged that the space (13, 26) with the plenum surrounding the burner (2) (7) via at least one from the outside through the burner (2) inlet bore (14,) leading into the inner tube (6) 15) and that the space (13, 26) with the additional opening (17, 27) through at least one the lance head (12) guided compressed air duct (18, 18a-c, 28) communicates. Brenneranordnung nach Anspruch 2, dadurch gekennzeichnet, dass der Zwischenraum (13, 26) ringförmig ausgebildet ist und das Pilotgasrohr (11) konzentrisch umgibt.Burner arrangement according to claim 2, characterized in that the space (13, 26) is annular and concentrically surrounds the pilot gas pipe (11). Brenneranordnung nach einem der Ansprüche 2 und 3, dadurch gekennzeichnet, dass mehrere Einlassbohrungen (14, 15) um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind.Burner arrangement according to one of claims 2 and 3, characterized characterized in that several inlet bores (14, 15) distributed around the burner axis or lance axis are. Brenneranordnung nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, dass mehrere Druckluftkanäle (18, 18a-c, 28) um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind.Burner arrangement according to one of claims 2 to 4, characterized characterized in that several compressed air channels (18, 18a-c, 28) distributed around the burner axis or lance axis are arranged. Brenneranordnung nach Anspruch 5, dadurch gekennzeichnet, dass die Druckluftkanäle (18, 18a-c, 28) in Strömungsrichtung schräg zur Brennerachse bzw. Lanzenachse hin verlaufen.Burner arrangement according to claim 5, characterized in that the compressed air channels (18, 18a-c, 28) in the direction of flow run at an angle to the burner axis or lance axis. Brenneranordnung nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Austrittsöffnung (22, 33) für den Flüssigbrennstoff im Lanzenkopf (12) zentral angeordnet ist, und dass die zusätzliche Oeffnung im Lanzenkopf (12) als Ringöffnung (17, 27) ausgebildet ist, welche die zentrale Austrittsöffnung (22, 33) für den Flüssigbrennstoff konzentrisch umgibt.Burner arrangement according to one of claims 1 to 6, characterized characterized in that the outlet opening (22, 33) for the liquid fuel is arranged centrally in the lance head (12) and that the additional opening in the lance head (12) as Ring opening (17, 27) is formed, which is the central Outlet opening (22, 33) for the liquid fuel concentric surrounds. Brenneranordnung nach Anspruch 7, dadurch gekennzeichnet. dass mehrere Austrittsöffnungen (23, 23a-c) für das Pilotgas um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind, und dass die Austrittsöffnungen (23, 23a-c) in die Ringöffnung (17) münden.Burner arrangement according to claim 7, characterized. that several outlet openings (23, 23a-c) for the pilot gas distributed around the burner axis or lance axis are arranged, and that the outlet openings (23, 23a-c) open into the ring opening (17). Brenneranordnung nach Anspruch 7, dadurch gekennzeichnet, dass mehrere Austrittsöffnungen (29) für das Pilotgas um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind, und dass die Austrittsöffnungen (29) ausserhalb der Ringöffnung (27) liegen.Burner arrangement according to claim 7, characterized in that several outlet openings (29) for the pilot gas around the burner axis or lance axis is distributed around are, and that the outlet openings (29) outside the Ring opening (27). Brenneranordnung nach Anspruch 9, dadurch gekennzeichnet, dass mehrere Druckluftkanäle (28) um die Brennerachse bzw. Lanzenachse herum verteilt angeordnet sind, und dass die Austrittsöffnungen (29) bzw. die Pilotgasbohrungen (30) und die Druckluftkanäle (28) um die Brennerachse bzw. Lanzenachse herum alternierend angeordnet sind.Burner arrangement according to claim 9, characterized in that several compressed air channels (28) around the burner axis or lance axis are distributed around, and that the outlet openings (29) or the pilot gas holes (30) and the compressed air channels (28) around the burner axis or Lance axis are arranged alternately around.
EP97810834A 1996-12-19 1997-11-06 Burner arrangement for a gas turbine Expired - Lifetime EP0849533B1 (en)

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DE19652899A DE19652899A1 (en) 1996-12-19 1996-12-19 Burner arrangement for a gas turbine
DE19652899 1996-12-19

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DE4306956A1 (en) 1993-03-05 1994-09-08 Abb Management Ag Fuel feed for a gas turbine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7082768B2 (en) 2001-12-20 2006-08-01 Alstom Technology Ltd Method for injecting a fuel-air mixture into a combustion chamber
US7406827B2 (en) 2001-12-20 2008-08-05 Alstom Technology Ltd Apparatus for injecting a fuel-air mixture into a combustion chamber
EP2693124A1 (en) * 2012-08-02 2014-02-05 Siemens Aktiengesellschaft Pilot burner, burner, combustor and gas turbine engine
EP3366999A1 (en) * 2017-02-22 2018-08-29 Delavan, Inc. Passive purge injectors

Also Published As

Publication number Publication date
DE19652899A1 (en) 1998-06-25
EP0849533A3 (en) 1999-08-11
US6038863A (en) 2000-03-21
EP0849533B1 (en) 2003-06-04
DE59710217D1 (en) 2003-07-10
CN1103024C (en) 2003-03-12
CN1185565A (en) 1998-06-24
JP3995067B2 (en) 2007-10-24
JPH10185194A (en) 1998-07-14

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