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EP0210462B1 - Dual combustor - Google Patents

Dual combustor Download PDF

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Publication number
EP0210462B1
EP0210462B1 EP86109039A EP86109039A EP0210462B1 EP 0210462 B1 EP0210462 B1 EP 0210462B1 EP 86109039 A EP86109039 A EP 86109039A EP 86109039 A EP86109039 A EP 86109039A EP 0210462 B1 EP0210462 B1 EP 0210462B1
Authority
EP
European Patent Office
Prior art keywords
fuel
dual burner
cones
dual
burner according
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.)
Expired
Application number
EP86109039A
Other languages
German (de)
French (fr)
Other versions
EP0210462A1 (en
Inventor
Jean Dr. Hellat
Jakob Dr. Keller
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.)
BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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Publication date
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Publication of EP0210462A1 publication Critical patent/EP0210462A1/en
Application granted granted Critical
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Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising 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
    • F23R3/36—Supply of different fuels
    • 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

Definitions

  • the present invention relates to a dual burner according to the preamble of claim 1. It also relates to a method for mixing air with the liquid fuel flowing into the dual burner.
  • a spiral vortex burner is described in GB-A-817936.
  • a known way of building a detachable swirl body is to provide a tubular jacket with tangential entry slots. This creates a potential vortex that flows axially.
  • vortex breakdown zones in a potential vortex have very poor stability properties.
  • the invention seeks to remedy this.
  • the object of the invention is to produce a stable vortex backflow zone in a dual burner of the type mentioned at the outset.
  • the conditions must be met, according to which the axial profile of the vortex flow generated by the swirl body in the vicinity of the axis has a speed increase, while the swirl must decrease sharply towards the axis.
  • the objectives of the invention are basically achieved in that slotted cones are provided with suitable opening angles; this gives you an optimal opportunity to combine the advantages of a potential vortex tube and a fluid-mechanically perfect swirl body.
  • a vortex flow is obtained which is low in swirl in the center and has an axial speed excess. Because the number of swirls of this burner increases strongly in the axial direction and reaches the breakdown value or the critical value at the end of the burner, this results in a positionally stable vortex backflow zone.
  • Fig. 1 shows a dual burner in the direction of flow to the media used there.
  • the dual burner which is placed in front of the combustion chamber 13 of the combustion chamber, which is only hinted at, is essentially composed of a structure formed into a swirl body, an oil line and a gas line 3.
  • the swirl body structure itself consists of two double-curved plates which are produced by bending flat plates can. The sheets are folded on a certain diagonal and stiffened with a rib (see FIGS. 2, 3, 4). Because the diagonals diverge from each other in the central plane of the flow direction, an arrangement of inner cones is created 4b, 5b, which expand in the flow direction and an arrangement of outer cones 4a, 5a, which taper in the flow direction.
  • the fuels introduced - fuel gas and fuel oil - are introduced individually into the swirl body 1 and thus meet the requirements placed on a dual burner.
  • the oil line 2 divides in front of the swirl body 1 into two oil nozzles 2a, 2b in such a way that their injection is directed axially onto the outer cone 4a, 5a.
  • the pulse of the oil injection at full load is selected so that the oil film 6 penetrates to the end of an outer cone 4a or 5a. With a reduced load, the penetration depth decreases accordingly, so that the outer areas of the vortex flow remain free of fuel. This results in self-regulation, which means that the fuel / air mixture 7a in the vortex center never becomes too lean or too rich.
  • the swirl strength of the vortex flow is dependent on the selected width of the slot that results between the outer cone 4a, 5a and the inner cone 4b, 5b.
  • the outer cones 4a, 5a tapering in the direction of flow thus fulfill various functions. On the one hand, they serve as carriers of the oil film 6 released by the oil nozzles 2a, 2b; Furthermore, the outer cones 4a, 5a serve to guide the flow of the working mixture, which rolls in the axial direction due to the swirl movement.
  • the radiant heat which the sheets receive from the combustion chamber 13 can be partially transferred to the oil film 6 here.
  • the inner cones 4b, 5b which widen in the direction of flow, have fuel lines 8 on the bend end, as a continuation of the gas line 3, which serve to supply a gaseous fuel.
  • the fuel lines 8, which are supplemented with nozzles, also serve to stiffen the swirl body 1. This is closed on the combustion chamber side with a perforated plate 11, through which cooling air or dilution air for the first part of the combustion chamber wall or the combustion chamber 13 can be supplied.
  • the slot widths 14 which are not visible in FIG.
  • the backflow zone 12 begins at the downstream end of the inner cones 4b, 5b.
  • the backflow zone 12 is inherently positionally stable.
  • the taper and expansion rates of the cones 4a, 4b and. 4b, 5b depend on the properties of the combustion chamber, as does the overall length of the swirl body 1.
  • the fuel lines 8 are provided with fuel nozzles 9 which inject the fuel gas towards the center of the swirl body 1.
  • the tangentially flowing air 7 is thus homogeneously enriched with the available fuel gas.
  • the fuel is “rolled in” by the tangentially flowing air 7 between relatively thin layers of air, as a result of which subsequent mixing is unnecessary.
  • the swirl body 1 is closed on the combustion chamber side, as can be seen in FIG. 4, with the perforated plate 11, through which, as already explained, cooling air or dilution air can reach the combustion chamber 13.
  • FIG. 5 shows an expanded variant of the swirl body 1 already shown in FIG. 1.
  • the local version is supplemented with a pilot burner 15.
  • the gas line 3 is extended in the flow direction via the fuel lines 8.
  • the pilot burner version is particularly suitable if the swirl body 1 has more than two pairs of cones.
  • FIGS. 6, 7, 8, 9 - which views can be seen through the planes VI, VII, VIII, IX according to FIG. 5 - the swirl body 1 constructed here from four pairs of cones does not differ conceptually from the one already explained , variant consisting of two pairs of cones.
  • the mixing of the fuels with the tangentially flowing air 7 is easier here, however, because it has to “roll in” smaller fuel rates.
  • the injection of the fuel via the four oil nozzles 2a, 2b, 2c, 2d is also directed axially onto the outer cones 4a, 5a, 16a, 17a.
  • the swirl body 1 now consists of four double-curved sheets 4, 5, 16, 17, which are folded into double cones in the planes of the diagonals 10a, 10b, 10c, 10d. These diagonals run outwards in the direction of flow in a cone-shaped manner, so that the outer cones 4a, 5a, 16a, 17a taper, while the inner cones 4b, 5b, 16b, 17b expand.
  • the inner cones 4b, 5b, 16b, 17b each carry at the end a fuel line 8 provided with fuel nozzles 9, which in cooperation with the rib 10 serves to increase the rigidity of the folded sheets 4, 5, 16, 17.

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

Description

Die vorliegende Erfindung betrifft einen Dualbrenner nach dem Oberbegriff des Anspruchs 1. Sie betrifft auch ein Verfahren zur Vermischung von Luft mit dem in den Dualbrenner einströmenden flüssigen Brennstoff.The present invention relates to a dual burner according to the preamble of claim 1. It also relates to a method for mixing air with the liquid fuel flowing into the dual burner.

Die meisten Drallkörper von Dualbrennern erfordern wegen ihrer relativ komplizierten Geometrie eine aufwendige und teure Fertigung. Insbesondere bei Vormischbrennern dürfen durch die dort als Bestandteil von Dualbrennern eingebauten Drallkörper keine Ablösungszonen auftreten, weil diese die Gefahr der Rückzündung stark erhöhen würden.Most swirl bodies of dual burners require complex and expensive production because of their relatively complicated geometry. Particularly in the case of premix burners, the swirl bodies installed there as a component of dual burners must not cause any separation zones because these would greatly increase the risk of reignition.

Ein Spiralwirbelbrenner ist in der GB-A-817936 beschrieben.A spiral vortex burner is described in GB-A-817936.

Eine bekannte Möglichkeit, einen ablösungsfreien Drallkorper zu bauen, besteht darin, einen Rohrmantel mit tangentialen Eintrittsschlitzen zu versehen. Auf diese Weise entsteht ein Potentialwirbel, der axial abströmt. Es zeigt sich nun aber, dass Wirbelrückströmzonen (Vortex Breakdown) in einem Potentialwirbel sehr schlechte Stabilitätseigenschaften aufweisen.A known way of building a detachable swirl body is to provide a tubular jacket with tangential entry slots. This creates a potential vortex that flows axially. However, it can now be seen that vortex breakdown zones in a potential vortex have very poor stability properties.

Hier will die Erfindung Abhilfe schaffen. Der Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, liegt die Aufgabe zugrunde, bei einem Dualbrenner der eingangs genannten Art die Erzeugung einer stabilen Wirbelrückströmzone zu bewerkstelligen.The invention seeks to remedy this. The object of the invention, as characterized in the claims, is to produce a stable vortex backflow zone in a dual burner of the type mentioned at the outset.

Zu diesem Zweck müssen die Bedingungen erfüllt werden, wonach das axiale Profil der vom Drallkörper erzeugten Wirbelströmung in der Nähe der Achse eine Geschwindigkeitsüberhöhung aufweisen, während der Drall gegen die Achse hin stark abnehmen muss.For this purpose, the conditions must be met, according to which the axial profile of the vortex flow generated by the swirl body in the vicinity of the axis has a speed increase, while the swirl must decrease sharply towards the axis.

Die Ziele der Erfindung werden grundsätzlich dadurch erreicht, dass geschlitzte Kegel mit geeigneten Oeffnungswinkeln vorgesehen werden ; damit erhält man eine optimale Möglichkeit, die Vorzüge eines Potentialwirbelrohres und eines strömungsmechanisch perfekten Drallkörpers zu kombinieren. In diesem Fall erhält man eine Wirbelströmung, die im Zentrum drallarm ist und einen Axialgeschwindigkeitsüberschuss aufweist. Weil die Drallzahl dieses Brenners nun in axialer Richtung stark zunimmt und am Brennerende den Breakdown-Wert bzw. den kritischen Wert erreicht, ergibt dies eine positionsstabile Wirbelrückströmzone.The objectives of the invention are basically achieved in that slotted cones are provided with suitable opening angles; this gives you an optimal opportunity to combine the advantages of a potential vortex tube and a fluid-mechanically perfect swirl body. In this case, a vortex flow is obtained which is low in swirl in the center and has an axial speed excess. Because the number of swirls of this burner increases strongly in the axial direction and reaches the breakdown value or the critical value at the end of the burner, this results in a positionally stable vortex backflow zone.

Abgesehen von seiner äusserst einfachen Konstruktion, welche die Erzeugung einer Vielfalt von Wirbelströmungstypen erlaubt, weist dieser Dualbrenner weitere Vorteile auf :

  • - Durch den tangentialen Lufteintritt in die Kegel wird der dort eingedüste Brennstoff zwischen relativ dünnen Luftschichten « eingerollt •, wodurch die Erzeugung einer starken Vermischung überflüssig wird.
  • - Die Vorzüge des Vormischbrenners (wenig NOX und CO) stellen sich ein : Der Impuls der Eindüsung von flüssigem Brennstoff wird bei Vollast so gewählt, dass der Flüssig-Brennstofffilm bis ans Ende eines Aussenkegels eindringt. Bei kleinerer Last verkleinert sich die Eindringtiefe, so dass die Aussenbereiche der Wirbelströmung von Brennstoff frei bleiben. Dadurch stellt sich eine Selbstregulierung ein, welche bewirkt, dass das Brennstoff/Luft-Gemisch im Wirbelzentrum nie zu mager oder zu fett wird. Damit wird eine gute Flammenstabilität in einem weiten Betriebsbereich gewährleistet.
  • - Es besteht keine Rückzündgefahr. Flammenfetzen, die bei Störungen in die Aussenkegel gelangen könnten, werden von der Strömung sofort wieder in den Innenkegel hineingespült.
  • - Flüssige Brennstoffe müssen nicht zerstäubt werden.
  • - Die Bauweise dieses Dualbrenners ist sehr viel kompakter als diejenige eines Vormischbrenners (keine Vormischstrecke).
Apart from its extremely simple construction, which allows the generation of a variety of vortex flow types, this dual burner has other advantages:
  • - Due to the tangential air entry into the cone, the fuel injected there is “rolled in” between relatively thin layers of air, making the generation of strong mixing unnecessary.
  • - The advantages of the premix burner (little NO X and CO) set in: The pulse of the injection of liquid fuel is selected at full load so that the liquid fuel film penetrates to the end of an outer cone. With a lower load, the penetration depth decreases so that the outer areas of the vortex flow remain free of fuel. This results in self-regulation, which means that the fuel / air mixture in the vortex center never becomes too lean or too rich. This ensures good flame stability over a wide operating range.
  • - There is no risk of reignition. Scraps of flame that could get into the outer cone in the event of faults are immediately flushed back into the inner cone by the flow.
  • - Liquid fuels do not have to be atomized.
  • - The design of this dual burner is much more compact than that of a premix burner (no premix section).

Vorteilhafte und zweckmässige Weiterbildungen der erfindungsgemässen Aufgabenlösung sind in den Unteransprüchen gekennzeichnet.Advantageous and expedient developments of the task solution according to the invention are characterized in the subclaims.

In der Zeichnung sind Ausführungsbeispiele der Erfindung schematisch dargestellt.Exemplary embodiments of the invention are shown schematically in the drawing.

Es zeigt :

  • Fig. 1 einen Dualbrenner,
  • Fig. 2 eine Ansicht des Dualbrenners aus Fig. 1 durch Ebene II,
  • Fig. 3 eine Ansicht des Dualbrenners aus Fig. 1 durch Ebene 111,
  • Fig. 4 eine Ansicht des Dualbrenners aus Fig. 1 durch Ebene IV,
  • Fig. 5 eine weitere Ausführung des Dualbrenners,
  • Fig. 6 eine Ansicht des Dualbrenners aus Fig. 5 durch Ebene IV,
  • Fig. 7 eine Ansicht des Dualbrenners aus Fig. 5 durch Ebene VII,
  • Fig. 8 eine Ansicht des Dualbrenners aus Fig. 5 durch Ebene VIII und
  • Fig. 9 eine Ansicht des Dualbrenners aus Fig. 5 durch Ebene IX.
It shows :
  • 1 shows a dual burner,
  • 2 shows a view of the dual burner from FIG. 1 through plane II,
  • 3 shows a view of the dual burner from FIG. 1 through plane 111,
  • 4 shows a view of the dual burner from FIG. 1 through plane IV,
  • 5 shows a further embodiment of the dual burner,
  • 6 is a view of the dual burner from FIG. 5 through plane IV,
  • 7 is a view of the dual burner from FIG. 5 through plane VII,
  • 8 is a view of the dual burner from FIG. 5 through plane VIII and
  • FIG. 9 is a view of the dual burner from FIG. 5 through plane IX.

Alle für das unmittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind fortgelassen. Die Strömungsrichtung der Medien ist mit Pfeilen bezeichnet. In den verschiedenen Figuren sind jeweils gleiche Elemente mit den gleichen Bezugszeichen versehen.All elements not necessary for the immediate understanding of the invention have been omitted. The direction of flow of the media is indicated by arrows. In the various figures, the same elements are provided with the same reference symbols.

Fig. 1 zeigt einen Dualbrenner in Strömungsrichtung zu den dort zum Einsatz gelangenden Medien. Der Dualbrenner, der vor dem nur andeutungsweise markierten Brennraum 13 einer Brennkammer plaziert ist, besteht im wesentlichen aus einem zu einem Drallkörper geformten Gebilde, einer Oelleitung und einer Gasleitung 3. Das Drallkörpergebilde selbst besteht aus zwei doppeltgekrümmten Blechen, die durch Biegen ebener Bleche erzeugt werden können. Auf einer bestimmten Diagonale sind die Bleche gefalzt und mit einer Rippe versteift (siehe Fig. 2, 3, 4). Weil die Diagonalen in der Mittelebene der Strömungsrichtung kegelstrahlig auseinandergehen, entsteht jeweils eine Anordnung von Innenkegeln 4b, 5b, die sich in Strömungsrichtung erweitern und eine Anordnung von Aussenkegeln 4a, 5a, die sich in Strömungsrichtung verjüngen.Fig. 1 shows a dual burner in the direction of flow to the media used there. The dual burner, which is placed in front of the combustion chamber 13 of the combustion chamber, which is only hinted at, is essentially composed of a structure formed into a swirl body, an oil line and a gas line 3. The swirl body structure itself consists of two double-curved plates which are produced by bending flat plates can. The sheets are folded on a certain diagonal and stiffened with a rib (see FIGS. 2, 3, 4). Because the diagonals diverge from each other in the central plane of the flow direction, an arrangement of inner cones is created 4b, 5b, which expand in the flow direction and an arrangement of outer cones 4a, 5a, which taper in the flow direction.

Die herangeführten Brennstoffe - Brenngas und Brennoel - werden individuell in den Drallkörper 1 eingeleitet und erfüllen somit die an einen Dualbrenner gestellten Anforderungen. Die Oelleitung 2 teilt sich vor dem Drallkörper 1 in zwei Oeldüsen 2a, 2b auf, dergestalt, dass deren Eindüsung axial auf die Aussenkegel 4a, 5a gerichtet ist. Der Impuls der Oeleindüsung bei Vollast wird so gewählt, dass der Oelfilm 6 bis ans Ende eines Aussenkegels 4a bzw. 5a eindringt. Bei reduzierter Last verkleinert sich die Eindringtiefe entsprechend, so dass die Aussenbezirke der Wirbelströmung von Brennstoff frei bleiben. Dadurch ergibt sich eine Selbstregulierung, die bewirkt, dass das Brennstoff/Luft-Gemisch 7a im Wirbelzentrum nie zu mager oder zu fett wird. Die Drallstärke der Wirbelströmung ist von der gewählten Weite des Schlitzes, der sich zwischen dem Aussenkegel 4a, 5a und dem Innenkegel 4b, 5b ergibt, abhängig. Die in Strömungsrichtung sich verjüngenden Aussenkegel 4a, 5a erfüllen somit verschiedene Funktionen. Sie dienen einerseits als Träger des von den Oeldüsen 2a, 2b freigegebenen Oelfilms 6 ; des weiteren dienen die Aussenkegel 4a, 5a der Strömungsführung des Arbeitsgemisches, das sich durch die Drallbewegung in axialer Richtung abrollt. Die Strahlungswärme, welche die Bleche vom Brennraum 13 erhalten, kann hier zum Teil auf den Oelfilm 6 übertragen werden. Somit findet die herangeführte Luft 7 mindestens teilweise verdampftes Oel vor, wodurch die Vermischung optimal vonstatten geht. Selbst wenn Anteile des Oelfilms 6 allenfalls nicht vollständig verdampfen, bietet dies weiter keine Nachteile, denn die tangential herangeführte Luft ist in der Lage den verbleibenden Oelfilm 6 schichtweise « einzurollen ». Die in Strömungsrichtung sich erweiternden Innenkegel 4b, 5b weisen krümmungsendseitig, als Fortsetzung der Gasleitung 3, Brennstoffleitungen 8 auf, die der Zuführung eines gasförmigen Brennstoffes dienen. Die Brennstoffleitungen 8, die mit Düsen ergänzt sind, dienen danebst auch der Versteifung des Drallkörpers 1. Dieser wird brennkammerseitig mit einem Lochblech 11 abgeschlossen, durch welches Kühlluft bzw. Verdünnungsluft für den ersten Teil der Brennkammerwand bzw. des Brennraumes 13 zugeführt werden kann. Die in Fig. 1 nicht ersichtlichen Schlitzbreiten 14 sind so gewählt, dass die Rückströmzone 12 am stromabgelegenen Ende der Innenkegel 4b, 5b beginnt. Für gewisse Anwendungen kann es allerdings von Vorteil sein, schmälere Luftschlitze zu wählen. In diesem Falle würde sich die Rückströmzone 12 stromaufwärts verschieben und das Gemisch käme dann entsprechend früher zur Zün- ' dung.The fuels introduced - fuel gas and fuel oil - are introduced individually into the swirl body 1 and thus meet the requirements placed on a dual burner. The oil line 2 divides in front of the swirl body 1 into two oil nozzles 2a, 2b in such a way that their injection is directed axially onto the outer cone 4a, 5a. The pulse of the oil injection at full load is selected so that the oil film 6 penetrates to the end of an outer cone 4a or 5a. With a reduced load, the penetration depth decreases accordingly, so that the outer areas of the vortex flow remain free of fuel. This results in self-regulation, which means that the fuel / air mixture 7a in the vortex center never becomes too lean or too rich. The swirl strength of the vortex flow is dependent on the selected width of the slot that results between the outer cone 4a, 5a and the inner cone 4b, 5b. The outer cones 4a, 5a tapering in the direction of flow thus fulfill various functions. On the one hand, they serve as carriers of the oil film 6 released by the oil nozzles 2a, 2b; Furthermore, the outer cones 4a, 5a serve to guide the flow of the working mixture, which rolls in the axial direction due to the swirl movement. The radiant heat which the sheets receive from the combustion chamber 13 can be partially transferred to the oil film 6 here. Thus, the air 7 that is brought in finds at least partially evaporated oil, as a result of which the mixing takes place optimally. Even if portions of the oil film 6 do not evaporate completely at all, this does not offer any further disadvantages, since the air which is brought in tangentially is able to "roll up" the remaining oil film 6 in layers. The inner cones 4b, 5b, which widen in the direction of flow, have fuel lines 8 on the bend end, as a continuation of the gas line 3, which serve to supply a gaseous fuel. The fuel lines 8, which are supplemented with nozzles, also serve to stiffen the swirl body 1. This is closed on the combustion chamber side with a perforated plate 11, through which cooling air or dilution air for the first part of the combustion chamber wall or the combustion chamber 13 can be supplied. The slot widths 14 which are not visible in FIG. 1 are selected such that the backflow zone 12 begins at the downstream end of the inner cones 4b, 5b. For certain applications, however, it can be advantageous to choose narrower louvers. In this case, the backflow zone 12 would shift upstream and the mixture would then ignite accordingly earlier.

Weil die Drallzahl in Strömungsrichtung zunimmt und den Breakdown-Wert bzw. den kritischen Wert am Ende der Innenkegel 4b, 5b erreicht wird, ist die Rückströmzone 12 an sich positionsstabil. Die Verjüngungs- und Erweiterungsraten der Kegel 4a, 4b resp. 4b, 5b sind von den Eigenschaften der Brennkammer abhängig, ebenso die Baulänge des Drallkörpers 1.Because the swirl number increases in the direction of flow and the breakdown value or the critical value is reached at the end of the inner cone 4b, 5b, the backflow zone 12 is inherently positionally stable. The taper and expansion rates of the cones 4a, 4b and. 4b, 5b depend on the properties of the combustion chamber, as does the overall length of the swirl body 1.

Fig. 2, 3, 4 sind Ansichten durch die Ebenen 11, 111, IV gemäss Fig. 1. Daraus ist gut ersichtlich, wie die Kegel 4a, 5a und 4b, 5b sich verjüngen resp. erweitern. In den Ebenen der Diagonalen 10a, 10b sind die Bleche 4, 5 gefalzt und jeweils mit einer Rippe 10 versteift. Auch ist aus diesen Figuren gut ersichtlich, wie die Luft 7 tangential in die Kegel einströmt und durch deren Krümmung die Drallbewegung initiert wird. Die Anteile des Oelfilms 6, die nicht unmittelbar verdampfen, werden von der verdrallten Luft 7 schichtweise « eingerollt », wodurch gewährleistet wird, dass das Brennstoff/Luft-Gemisch eine homogene Konzentration aufweist. In Strömungsrichtung nehmen die Schlitzbreiten 14 zwischen Innen- und Aussenkegeln zu, während die Einströmungsöffnungen 14a zwischen Brennstoffleitungen 8 und Aussenkegeln 4a, 5b abnehmen.2, 3, 4 are views through the planes 11, 111, IV according to FIG. 1. This clearly shows how the cones 4a, 5a and 4b, 5b taper respectively. expand. The plates 4, 5 are folded in the planes of the diagonals 10a, 10b and each stiffened with a rib 10. These figures also clearly show how the air 7 flows tangentially into the cone and how the swirl movement is initiated by its curvature. The portions of the oil film 6 that do not evaporate immediately are "rolled up" in layers by the swirled air 7, which ensures that the fuel / air mixture has a homogeneous concentration. In the direction of flow, the slot widths 14 between the inner and outer cones increase, while the inflow openings 14a between fuel lines 8 and outer cones 4a, 5b decrease.

Es ist aus diesen Figuren des weiteren ersichtlich, dass die Brennstoffleitungen 8 mit Brennstoffdüsen 9 versehen sind, welche das Brenngas gegen die Mitte des Drallkörpers 1 eindüsen. Die tangential einströmende Luft 7 wird dadurch mit dem zur Verfügung stehenden Brenngas homogen angereichert. Auch hier wird der Brennstoff von der tangential einströmenden Luft 7 zwischen relativ dünnen Luftschichten « eingerollt », wodurch eine nachträgliche Vermischung überflüssig wird. Der Drallkörper 1 wird brennkammerseitig, wie aus Fig. 4 hervorgeht, mit dem Lochblech 11 abgeschlossen, durch welches, wie bereits erläutert, Kühlluft bzw. Verdünnungsluft zum Brennraum 13 gelangen kann.It can further be seen from these figures that the fuel lines 8 are provided with fuel nozzles 9 which inject the fuel gas towards the center of the swirl body 1. The tangentially flowing air 7 is thus homogeneously enriched with the available fuel gas. Here, too, the fuel is “rolled in” by the tangentially flowing air 7 between relatively thin layers of air, as a result of which subsequent mixing is unnecessary. The swirl body 1 is closed on the combustion chamber side, as can be seen in FIG. 4, with the perforated plate 11, through which, as already explained, cooling air or dilution air can reach the combustion chamber 13.

Fig. 5 zeigt eine erweiterte Variante des bereits unter Fig. 1 dargestellten Drallkörpers 1. Die hiesige Ausführung ist mit einem Pilotbrenner 15 ergänzt. Dazu wird die Gasleitung 3 über die Brennstoffleitungen 8 in Strömungsrichtung verlängert. Die Pilotbrenner-Ausführung eignet sich insbesondere gut, wenn der Drallkörper 1 mehr als zwei Kegelpaare aufweist.FIG. 5 shows an expanded variant of the swirl body 1 already shown in FIG. 1. The local version is supplemented with a pilot burner 15. For this purpose, the gas line 3 is extended in the flow direction via the fuel lines 8. The pilot burner version is particularly suitable if the swirl body 1 has more than two pairs of cones.

Wie aus Fig. 6, 7, 8, 9 - welche Ansichten durch die Ebenen VI, VII, VIII, IX gemäss Fig. 5 sind - ersichtlich ist, unterscheidet sich der hier aus vier Paar Kegeln aufgebaute Drallkörper 1 konzeptionsmässig nicht von der bereits erläuterten, aus zwei Paar Kegeln bestehenden Variante. Die Vermischung der Brennstoffe mit der tangential einströmenden Luft 7 gestaltet sich hier indessen einfacher, weil diese jeweils kleinere Brennstoffraten « einzurollen » hat. Die Eindüsung des Brennstoffes über die vier Oeldüsen 2a, 2b, 2c, 2d ist auch hier axial auf die Aussenkegel 4a, 5a, 16a, 17a gerichtet.As can be seen from FIGS. 6, 7, 8, 9 - which views can be seen through the planes VI, VII, VIII, IX according to FIG. 5 - the swirl body 1 constructed here from four pairs of cones does not differ conceptually from the one already explained , variant consisting of two pairs of cones. The mixing of the fuels with the tangentially flowing air 7 is easier here, however, because it has to “roll in” smaller fuel rates. The injection of the fuel via the four oil nozzles 2a, 2b, 2c, 2d is also directed axially onto the outer cones 4a, 5a, 16a, 17a.

Der Drallkörper 1 besteht nun aus vier doppeltgekrümmten Blechen 4, 5, 16, 17, die in den Ebenen der Diagonalen 10a, 10b, 10c, 10d zu Doppelkegeln gefalzt sind. Dabei verlaufen diese Diagonalen in Strömungsrichtung kegelstrahlig nach aussen, so dass sich die Aussenkegel 4a, 5a, 16a, 17a verjüngen, während die Innenkegel 4b, 5b, 16b, 17b sich erweitern. Die Innenkegel 4b, 5b, 16b, 17b tragen endseitig je eine mit Brennstoffdüsen 9 versehene Brennstoffleitung 8, welche im Zusammenwirken mit der Rippe 10 dazu dient, die Steifigkeit der gefalzten Bleche 4, 5, 16, 17 zu erhöhen.The swirl body 1 now consists of four double-curved sheets 4, 5, 16, 17, which are folded into double cones in the planes of the diagonals 10a, 10b, 10c, 10d. These diagonals run outwards in the direction of flow in a cone-shaped manner, so that the outer cones 4a, 5a, 16a, 17a taper, while the inner cones 4b, 5b, 16b, 17b expand. The inner cones 4b, 5b, 16b, 17b each carry at the end a fuel line 8 provided with fuel nozzles 9, which in cooperation with the rib 10 serves to increase the rigidity of the folded sheets 4, 5, 16, 17.

Brennkammerseitig ist die verbleibende Oeffnung des Drallkörpers 1 durch ein Lochblech 11 abgeschlossen.On the combustion chamber side, the remaining opening of the swirl body 1 is closed by a perforated plate 11.

Die Wirkungsweise dieses erweiterten Drallkörpers 1 unterscheidet sich nicht von derjenigen Ausführung, die unter Fig. 1, 2, 3, 4 erläutert wurde.The mode of operation of this expanded swirl body 1 does not differ from that embodiment which was explained under FIGS. 1, 2, 3, 4.

Claims (6)

1. A dual burner of a gas turbine or a hot gas generator, consisting substantially of swirl chamber and inlets for gaseous and liquid fuels, characterized in that the swirl chamber (1) consists of at least two doubly-curved sheets (4, 5) impinged on by tangential air entry, which are folded along diagonals (10a, 10b) which extend divergently in the downstream direction, in such a way that one of the curved panels beside the fold forms an inner cone (4b, 5b) expanding in the downstream direction, while the other curved panel beside the fold forms an outer cone (4a, 5a) which contracts in the downstream direction, while the curved panels of the inner cones (4b, 5b) expanding in the downstream direction are fitted at the boundary with a fuel passage (8), having fuel nozzles (9).
2. A dual burner according to Claim 1, characterized in that the fuel nozzles (9) are directed towards the interior of the swirl chamber (1).
3. A dual burner according to Claim 1, characterized in that a pilot burner (15) is placed centrally in relation to the double-folded sheets (4, 5, 16, 17).
4. A dual burner according to Claim 1, characterized in that the remaining downstream areas of cross section between the external outline of the swirl chamber (1) and the cone openings (4a, 4b ; 5a, 5b ; 16a, 16b ; 17a, 17b) are closed by a perforated sheet (11).
5. A dual burner according to Claim 1, characterized in that the fold diagonals (10a, 10b, 10c, 10d) are reinforced by a rib (10).
6. A method of mixing air with the liquid fuel entering the dual burner according to Claim 1, characterized in that the injection of the liquid fuel (2a, 2b, 2c, 2d) is directed at the outer cones (4a, 5a, 16a, 17a), while the film (6) which forms there is rolled up by the air (7) flowing tangentially into the outer cones (4a, 5a, 16a, 17a).
EP86109039A 1985-07-30 1986-07-02 Dual combustor Expired EP0210462B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3289/85 1985-07-30
CH328985 1985-07-30

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EP0210462A1 EP0210462A1 (en) 1987-02-04
EP0210462B1 true EP0210462B1 (en) 1989-03-15

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US (1) US4781030A (en)
EP (1) EP0210462B1 (en)
JP (1) JPH06103085B2 (en)
CA (1) CA1286886C (en)
DE (1) DE3662462D1 (en)
IN (1) IN167458B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108224473A (en) * 2017-12-28 2018-06-29 中国航发四川燃气涡轮研究院 A kind of integrated after-burner of sudden expansion inner cone flame stabilization structure

Families Citing this family (55)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5193995A (en) * 1987-12-21 1993-03-16 Asea Brown Boveri Ltd. Apparatus for premixing-type combustion of liquid fuel
CH674561A5 (en) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
CH678757A5 (en) * 1989-03-15 1991-10-31 Asea Brown Boveri
CH678568A5 (en) * 1989-03-15 1991-09-30 Asea Brown Boveri
CH679692A5 (en) * 1989-04-24 1992-03-31 Asea Brown Boveri
CH680816A5 (en) * 1989-04-27 1992-11-13 Asea Brown Boveri
CH680084A5 (en) * 1989-06-06 1992-06-15 Asea Brown Boveri
CH680157A5 (en) * 1989-12-01 1992-06-30 Asea Brown Boveri
CH680467A5 (en) * 1989-12-22 1992-08-31 Asea Brown Boveri
DE59009353D1 (en) * 1990-10-17 1995-08-03 Asea Brown Boveri Combustion chamber of a gas turbine.
CH684962A5 (en) * 1991-07-03 1995-02-15 Asea Brown Boveri Burner for operating an internal combustion engine, a combustor of a gas turbine group or a firing.
US5307634A (en) * 1992-02-26 1994-05-03 United Technologies Corporation Premix gas nozzle
EP0592717B1 (en) * 1992-10-16 1998-02-25 Asea Brown Boveri Ag Gas-operated premix burner
EP0593816B1 (en) * 1992-10-23 1997-04-16 Asea Brown Boveri Ag Burner with electric ignition device
SE9304194L (en) * 1993-12-17 1995-06-18 Abb Stal Ab fuel spreader
US5461865A (en) * 1994-02-24 1995-10-31 United Technologies Corporation Tangential entry fuel nozzle
DE4424639A1 (en) * 1994-07-13 1996-01-18 Abb Research Ltd Method and device for fuel distribution in a burner suitable for both liquid and gaseous fuels
DE4426353A1 (en) * 1994-07-25 1996-02-01 Abb Research Ltd burner
DE4435473A1 (en) * 1994-10-04 1996-04-11 Abb Management Ag Flame stabilised, premix burner for liq. fuel
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
DE4440558A1 (en) * 1994-11-12 1996-05-15 Abb Research Ltd Premix burner
DE4441235A1 (en) * 1994-11-19 1996-05-23 Abb Management Ag Combustion chamber with multi-stage combustion
DE4446842B4 (en) * 1994-12-27 2006-08-10 Alstom Method and device for feeding a gaseous fuel into a premix burner
DE19502796B4 (en) * 1995-01-30 2004-10-28 Alstom burner
CA2209672C (en) * 1995-02-03 2006-06-06 Bmw Rolls-Royce Gmbh Flow guiding body for gas turbine combustion chambers
DE19512645A1 (en) * 1995-04-05 1996-10-10 Bmw Rolls Royce Gmbh Fuel preparation device for gas turbine combustion chamber
DE19515082B4 (en) * 1995-04-25 2005-02-03 Alstom premix
DE19545309A1 (en) * 1995-12-05 1997-06-12 Asea Brown Boveri Premix burner
DE19547914A1 (en) * 1995-12-21 1997-06-26 Abb Research Ltd Premix burner for a heat generator
DE19548851A1 (en) * 1995-12-27 1997-07-03 Asea Brown Boveri Premix burner
DE19619873A1 (en) * 1996-05-17 1997-11-20 Abb Research Ltd burner
DE19626240A1 (en) * 1996-06-29 1998-01-02 Abb Research Ltd Premix burner and method of operating the burner
DE19654008B4 (en) * 1996-12-21 2006-08-10 Alstom burner
DE19721937B4 (en) * 1997-05-26 2008-12-11 Alstom Premix burner for operating a unit for generating a hot gas
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
US6141954A (en) * 1998-05-18 2000-11-07 United Technologies Corporation Premixing fuel injector with improved flame disgorgement capacity
EP1262714A1 (en) 2001-06-01 2002-12-04 ALSTOM (Switzerland) Ltd Burner with exhausts recirculation
DE10164099A1 (en) 2001-12-24 2003-07-03 Alstom Switzerland Ltd Burner with staged fuel injection
GB0219461D0 (en) * 2002-08-21 2002-09-25 Rolls Royce Plc Fuel injection arrangement
GB0305025D0 (en) 2003-03-05 2003-04-09 Alstom Switzerland Ltd Method and device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations
EP1601913A1 (en) * 2003-03-07 2005-12-07 Alstom Technology Ltd Premixing burner
US20060283181A1 (en) * 2005-06-15 2006-12-21 Arvin Technologies, Inc. Swirl-stabilized burner for thermal management of exhaust system and associated method
ATE414874T1 (en) 2004-01-20 2008-12-15 Alstom Technology Ltd PREMIX BURNER ARRANGEMENT AND METHOD FOR OPERATING A COMBUSTION CHAMBER
WO2005078341A1 (en) 2004-02-12 2005-08-25 Alstom Technology Ltd Premixing burner comprising a vortex generator defining a tapered vortex space, and sensor monitoring
DE102005011287B4 (en) 2004-03-31 2018-07-19 Ansaldo Energia Ip Uk Limited Method and an apparatus for operating at least one burner for firing the combustion chamber of a heat engine or gas turbine
DE102004015904A1 (en) * 2004-03-31 2005-10-20 Alstom Technology Ltd Baden Method of liquid fuel atomization in a premix burner and premix burner
EP1856442B1 (en) 2005-03-09 2010-08-25 Alstom Technology Ltd Premix burner for producing an ignitable fuel/air mixture
WO2006094939A1 (en) 2005-03-09 2006-09-14 Alstom Technology Ltd Burner comprising a premix for combustion chamber
EP2116766B1 (en) * 2008-05-09 2016-01-27 Alstom Technology Ltd Burner with fuel lance
JP5462527B2 (en) * 2009-05-19 2014-04-02 大阪瓦斯株式会社 Tubular flame burner
EP2685160B1 (en) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Premix burner of the multi-cone type for a gas turbine
EP2685161B1 (en) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Combustor arrangement, especially for a gas turbine
JP2013228207A (en) * 2013-08-15 2013-11-07 Osaka Gas Co Ltd Tubular flame burner
JP6190670B2 (en) * 2013-08-30 2017-08-30 三菱日立パワーシステムズ株式会社 Gas turbine combustion system
JP6123720B2 (en) * 2014-03-26 2017-05-10 Ｊｆｅスチール株式会社 Multi-tube tubular flame burner

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB305072A (en) * 1927-10-29 1929-01-29 Lilian Farrow Improvements in or relating to internal combustion turbines
GB675092A (en) * 1949-01-25 1952-07-02 Rolls Royce Improvements relating to combustion systems of gas-turbine engines
GB817936A (en) * 1956-08-03 1959-08-06 Power Jets Res & Dev Ltd Vortex flow reaction chambers
FR1168777A (en) * 1957-03-01 1958-12-16 Snecma Vaporization burner device
FR74185E (en) * 1958-09-19 1960-11-07 Snecma Vaporization burner device
US4428191A (en) * 1964-10-01 1984-01-31 Rolls Royce Limited Fuel combustion in ducted flow
GB1179023A (en) * 1966-03-17 1970-01-28 Wingaersheek Turbine Co Inc Gas Combustion Apparatus
US3691762A (en) * 1970-12-04 1972-09-19 Caterpillar Tractor Co Carbureted reactor combustion system for gas turbine engine
DE2452178C3 (en) * 1974-11-02 1981-05-07 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Combustion chamber for gas turbine engines
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
DE2511172A1 (en) * 1975-03-14 1976-09-30 Daimler Benz Ag FILM EVAPORATION COMBUSTION CHAMBER
US4478045A (en) * 1980-03-07 1984-10-23 Solar Turbines Incorporated Combustors and gas turbine engines employing same
EP0059490B1 (en) * 1981-03-04 1984-12-12 BBC Aktiengesellschaft Brown, Boveri & Cie. Annular combustion chamber with an annular burner for gas turbines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108224473A (en) * 2017-12-28 2018-06-29 中国航发四川燃气涡轮研究院 A kind of integrated after-burner of sudden expansion inner cone flame stabilization structure

Also Published As

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IN167458B (en) 1990-10-27
DE3662462D1 (en) 1989-04-20
US4781030A (en) 1988-11-01
CA1286886C (en) 1991-07-30
EP0210462A1 (en) 1987-02-04
JPH06103085B2 (en) 1994-12-14
JPS6338812A (en) 1988-02-19

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