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EP1999409B1 - Burner arrangement - Google Patents

Burner arrangement Download PDF

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Publication number
EP1999409B1
EP1999409B1 EP07726463.8A EP07726463A EP1999409B1 EP 1999409 B1 EP1999409 B1 EP 1999409B1 EP 07726463 A EP07726463 A EP 07726463A EP 1999409 B1 EP1999409 B1 EP 1999409B1
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EP
European Patent Office
Prior art keywords
burner
fuel
lance
tip
stage
Prior art date
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Application number
EP07726463.8A
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German (de)
French (fr)
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EP1999409A1 (en
Inventor
Adnan Eroglu
Rudolf Lachner
Martin Zajadatz
James Robertson
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.)
Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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Publication of EP1999409A1 publication Critical patent/EP1999409A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • 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

Definitions

  • the present invention relates to the field of gas turbines. It relates to a burner assembly according to the preamble of claim 1.
  • FIG. 1 shows a burner assembly 10 in the form of a so-called double-cone burner, which has one of a double cone 11 enclosed swirl space 17 (for the operation of the double-cone burner, see for example the EP-A1-0 321 809 ).
  • a fuel lance 12 projects, from which liquid fuel 16, which is surrounded by shielding air 15, exits in the axial direction at the front end.
  • a premix fuel is injected into the burner in two stages 13 and 14.
  • the premix fuel is discharged from the central fuel lance 12 through a plurality of injection ports (indicated by the arrows in FIG Fig. 1 ) injected radially outwards.
  • the injection ports are formed and arranged to provide a predetermined distribution of the injected premix fuel.
  • the penetration depth of the fuel jets into the intersecting air flow must be sufficiently high.
  • the depth of penetration of a jet in a cross flow depends on the diameter of the jet and on the ratio of the momentum fluxes of jet and cross flow.
  • the object is solved by the entirety of the features of claim 1.
  • the decisive factor for the proposed solution is that in the first stage, the entire premix fuel is injected into the swirl space through two opposite injection openings with an enlarged opening diameter.
  • the injection ports combined in a pair with a large opening diameter enable operation both at idle and at full load with reduced gas pressure.
  • the solution is very simple and robust and can be implemented without difficulty in existing burner arrangements. In addition, fouling by dirt is reduced.
  • the two injection openings of the first stage have a diameter of about 5 mm and the two injection openings are arranged in the circumferential direction by an angle of about 65 degrees twisted out of a median plane, which is oriented parallel to the air flowing tangentially in the double cone.
  • a preferred embodiment of the invention is characterized in that the fuel lance so far protrudes into the swirl space, that the tip of the fuel lance is removed by a distance of 135 mm from the open end of the swirl space, and that the two injection openings in the axial Direction are arranged at a distance of about 115 mm from the top of the fuel lance.
  • liquid fuel can be injected into the swirl space in the axial direction at the tip of the burner lance, wherein the liquid fuel is surrounded by a jacket of shielding air.
  • the burner lance is bounded at the top by an end face perpendicular to the burner axis.
  • the burner lance may be rounded or streamlined at the top.
  • Fig. 2 is in a to Fig. 1 comparable representation of an embodiment of the invention reproduced.
  • the burner assembly 20 comprises a double cone 11, which encloses a swirl space 17, into which a fuel lance 12 projects from the apex of the cone in the axial direction.
  • premix fuel is injected through a plurality of injection openings in the tangent to the swirl chamber 17 air flow.
  • the first stage 18 instead of the many small injection orifices of the prior art, only two opposing injection orifices 19 having a significantly increased diameter are now provided, through which now the entire premix fuel of the first stage 18 is injected. How out Fig.
  • the two injection openings 19 of the first stage 18 are arranged at a distance a away from the tip of the fuel lance 12.
  • the tip of the fuel lance 12 in turn has a distance b from the open end of the swirl space 17.
  • the distance a is 115 mm +/- 10 mm.
  • the distance b is preferably 135 mm.
  • the diameter of the injection openings 19 is 5 mm +/- 0.5 mm.
  • the injection openings 19 are oriented in the radial direction and have relative to the double cone 11 an angular position in the circumferential direction, as is made Fig. 4 becomes clear.
  • a burner arrangement is shown in which the burner lance is delimited at the top by an end face perpendicular to the burner axis (rectangular geometry of the tip).
  • the burner lances are rounded off at the tip or have a streamlined design.

Landscapes

  • 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)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Gasturbinen. Sie betrifft eine Brenneranordnung gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbines. It relates to a burner assembly according to the preamble of claim 1.

STAND DER TECHNIKSTATE OF THE ART

Der abgestufte Betrieb eines Vormischbrenners vom Typ des Doppelkegelbrenners ist in der Druckschrift WO-A1-2001/096785 bzw. der äquivalenten US-B2-6,769,903 beschrieben worden. Das in diesen Druckschriften offenbarte Betriebsverfahren ermöglicht einen flexiblen Betrieb des Brenners mit niedrigen Emissionen und Pulsationen über einen weiten Bereich von Brennstoff- und Umgebungsparametern.The staged operation of a double cone burner type premix burner is described in the document WO-A1-2001 / 096785 or the equivalent US B2-6,769,903 been described. The operating method disclosed in these references enables flexible operation of the burner with low emissions and pulsations over a wide range of fuel and environmental parameters.

Eine in den Druckschriften beschriebene Brennerkonfiguration zur Durchführung des Verfahrens ist in Fig. 1 wiedergegeben. Die Fig. 1 zeigt eine Brenneranordnung 10 in Form eines sogenannten Doppelkegelbrenners, der einen von einem Doppelkegel 11 umschlossenen Drallraum 17 aufweist (zur Funktionsweise des Doppelkegelbrenners siehe z.B. die EP-A1-0 321 809 ). In den Drallraum 17 ragt in axialer Richtung zur Brennerachse 21 eine Brennstofflanze 12 hinein, aus der am vorderen Ende in axialer Richtung flüssiger Brennstoff 16 austritt, der von Abschirmluft 15 umgeben ist. Ein Vormischbrennstoff wird in zwei Stufen 13 und 14 in den Brenner eingedüst. In der ersten Stufe 13 wird der Vormischbrennstoff aus der zentralen Brennstofflanze 12 durch eine Vielzahl von Eindüsungsöffnungen (angedeutet durch die Pfeile in Fig. 1) radial nach aussen eingedüst. Die Eindüsungsöffnungen sind so ausgebildet und angeordnet, dass sich eine vorbestimmte Verteilung des eingedüsten Vormischbrennstoffs ergibt.A burner configuration described in the publications for carrying out the method is in Fig. 1 played. The Fig. 1 shows a burner assembly 10 in the form of a so-called double-cone burner, which has one of a double cone 11 enclosed swirl space 17 (for the operation of the double-cone burner, see for example the EP-A1-0 321 809 ). Into the swirl space 17, in the axial direction to the burner axis 21, a fuel lance 12 projects, from which liquid fuel 16, which is surrounded by shielding air 15, exits in the axial direction at the front end. A premix fuel is injected into the burner in two stages 13 and 14. In the first stage 13, the premix fuel is discharged from the central fuel lance 12 through a plurality of injection ports (indicated by the arrows in FIG Fig. 1 ) injected radially outwards. The injection ports are formed and arranged to provide a predetermined distribution of the injected premix fuel.

Um eine gute Durchmischung des Brennstoffs mit Luft zu erreichen, muss die Eindringtiefe der Brennstoffstrahlen in den kreuzenden Luftstrom ausreichend hoch sein. Die Eindringtiefe eines Strahls in einem Querstrom hängt vom Durchmesser des Strahls und vom Verhältnis der Impulsflüsse von Strahl und Querströmung ab. Um mit einer Vielzahl von Eindüsungsöffnungen mit kleinem Durchmesser eine ausreichend Eindringtiefe zu erzielen, werden ziemlich hohe Eindüsgeschwindigkeiten benötigt. Dies führt zu speziellen Anforderungen an die Höhe des Gasdrucks für die erste Stufe.In order to achieve good mixing of the fuel with air, the penetration depth of the fuel jets into the intersecting air flow must be sufficiently high. The depth of penetration of a jet in a cross flow depends on the diameter of the jet and on the ratio of the momentum fluxes of jet and cross flow. To achieve a sufficient penetration depth with a large number of small-diameter injection orifices, quite high injection speeds are required. This leads to special requirements for the level of the gas pressure for the first stage.

Hohe Gasdrücke in der ersten Stufe stellen für die bestehende Vormischbrenneranordnung ein erhebliches Problem dar. Dadurch werden dem Einsatz von mehrstufigen Vormischbrennern in Netzen mit niedrigem Gasdruck Grenzen gesetzt. Theoretisch ist es möglich, das Problem dadurch abzuschwächen, dass der Gasdruck mittels eines zusätzlichen Verdichters erhöht wird. Jedoch werden hierdurch die Kosten für die Installation und den Betrieb deutlich erhöht. Es ist deshalb wünschenswert, eine Lösung zu finden, bei welcher die Anforderungen an den Gasdruck für die erste Stufe durch die Gestaltung des Brenners verringert werden, ohne dass die Wirkung des Brenners massgeblich beeinträchtigt wird.High gas pressures in the first stage present a significant problem for the existing premix burner assembly. This limits the use of multi-stage premix burners in low gas pressure networks. Theoretically, it is possible to mitigate the problem by increasing the gas pressure by means of an additional compressor. However, this significantly increases the costs for installation and operation. It is therefore desirable to find a solution in which the requirements for the gas pressure for the first stage by the design of the Burner can be reduced without the effect of the burner is significantly impaired.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, eine mehrstufige Brenneranordnung mit einem Vormischbrenner zu schaffen, bei der durch konstruktive Vorkehrungen die Anforderungen an den Druck für die erste Stufe begrenzt werden.It is therefore an object of the invention to provide a multi-stage burner assembly with a premix burner, in which the requirements for the pressure for the first stage are limited by design precautions.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Massgeblich für die vorgeschlagene Lösung ist, dass in der ersten Stufe der gesamte Vormischbrennstoff durch zwei gegenüberliegende Eindüsungsöffnungen mit vergrössertem Öffnungsdurchmesser in den Drallraum eingedüst wird. Durch die in einem Paar mit grossem Öffnungsdurchmesser zusammengefassten Eindüsungsöffnungen wird ein Betrieb sowohl bei Leerlauf als auch bei Volllast mit reduziertem Gasdruck ermöglicht. Die Lösung ist sehr einfach und robust und kann ohne Schwierigkeiten bei vorhanden Brenneranordnungen implementiert werden. Zusätzlich wird ein Fouling durch Schmutz reduziert.The object is solved by the entirety of the features of claim 1. The decisive factor for the proposed solution is that in the first stage, the entire premix fuel is injected into the swirl space through two opposite injection openings with an enlarged opening diameter. The injection ports combined in a pair with a large opening diameter enable operation both at idle and at full load with reduced gas pressure. The solution is very simple and robust and can be implemented without difficulty in existing burner arrangements. In addition, fouling by dirt is reduced.

Erfindungsgemäß weisen die beiden Eindüsungsöffnungen der ersten Stufe einen Durchmesser von etwa 5 mm auf und die beiden Eindüsungsöffnungen sind in Umfangrichtung um einen Winkel von etwa 65 Grad aus einer Mittelebene heraus verdreht angeordnet sind, welche parallel zur im Doppelkegel tangential einströmenden Luft orientiert ist.According to the invention, the two injection openings of the first stage have a diameter of about 5 mm and the two injection openings are arranged in the circumferential direction by an angle of about 65 degrees twisted out of a median plane, which is oriented parallel to the air flowing tangentially in the double cone.

Eine bevorzugte Ausgestaltung der Erfindung ist dadurch gekennzeichnet, dass die Brennstofflanze soweit in den Drallraum hineinragt, dass die Spitze der Brennstofflanze etwa um einen Abstand von 135 mm vom offenen Ende des Drallraums entfernt ist, und dass die beiden Eindüsungsöffnungen in axialer Richtung in einem Abstand von etwa 115 mm von der Spitze der Brennstofflanze entfernt angeordnet sind.A preferred embodiment of the invention is characterized in that the fuel lance so far protrudes into the swirl space, that the tip of the fuel lance is removed by a distance of 135 mm from the open end of the swirl space, and that the two injection openings in the axial Direction are arranged at a distance of about 115 mm from the top of the fuel lance.

Insbesondere kann an der Spitze der Brennerlanze flüssiger Brennstoff in axialer Richtung in den Drallraum eingedüst werden, wobei der flüssige Brennstoff von einem Mantel von Abschirmluft umgeben ist.In particular, liquid fuel can be injected into the swirl space in the axial direction at the tip of the burner lance, wherein the liquid fuel is surrounded by a jacket of shielding air.

Weiterhin ist es denkbar, dass die Brennerlanze an der Spitze durch eine senkrecht zur Brennerachse stehenden Stirnfläche begrenzt ist.Furthermore, it is conceivable that the burner lance is bounded at the top by an end face perpendicular to the burner axis.

Ebenso kann die Brennerlanze an der Spitze abgerundet oder stromlinienförmig ausgebildet sein.Likewise, the burner lance may be rounded or streamlined at the top.

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
in einer stark vereinfachten Darstellung die Seitenansicht einer Brenneranordnung mit einem mehrstufigen Vormischbrenner nach dem Stand der Technik;
Fig. 2
in einer zu Fig. 1 vergleichbaren Darstellung einen mehrstufigen Vormischbrenner gemäss einem bevorzugten Ausführungsbeispiel der Erfindung;
Fig. 3
einige wesentliche Abmessungen beim Vormischbrenner aus Fig. 2; und
Fig. 4
den Vormischbrenner aus Fig. 2 in der Frontalansicht mit der Orientierung der Eindüsungsöffnungen der ersten Stufe in Umfangsrichtung.
The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. Show it
Fig. 1
in a highly simplified representation, the side view of a burner assembly with a multi-stage premix burner according to the prior art;
Fig. 2
in one too Fig. 1 comparable representation of a multi-stage premix burner according to a preferred embodiment of the invention;
Fig. 3
some essential dimensions in the premix burner Fig. 2 ; and
Fig. 4
the premix burner off Fig. 2 in the front view with the orientation of the injection ports of the first stage in the circumferential direction.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

In Fig. 2 ist in einer zur Fig. 1 vergleichbaren Darstellung ein Ausführungsbeispiel der Erfindung wiedergegeben. Die Brenneranordnung 20 umfasst einen Doppelkegel 11, der einen Drallraum 17 umschliesst, in den von der Kegelspitze her eine Brennstofflanze 12 in axialer Richtung hineinragt. In einer zweiten Stufe 14 wird Vormischbrennstoff durch eine Vielzahl von Eindüsungsöffnungen in den tangential in den Drallraum 17 einströmenden Luftstrom eingedüst. In der ersten Stufe 18 sind anstelle der vielen kleinen Eindüsungsöffnungen aus dem Stand der Technik nunmehr nur zwei gegenüberliegende Eindüsungsöffnungen 19 mit deutlich vergrössertem Durchmesser vorgesehen, durch die nunmehr der gesamte Vormischbrennstoff der ersten Stufe 18 eingedüst wird.
Wie aus Fig. 3 ersichtlich ist, sind die beiden Eindüsungsöffnungen 19 der ersten Stufe 18 um einen Abstand a entfernt von der Spitze der Brennstofflanze 12 angeordnet. Die Spitze der Brennstofflanze 12 ihrerseits hat von dem offenen Ende des Drallraums 17 einen Abstand b. Bevorzugt beträgt der Abstand a 115 mm +/- 10 mm. Der Abstand b beträgt vorzugsweise 135 mm. Der Durchmesser der Eindüsungsöffnungen 19 beträgt 5 mm +/- 0,5 mm. Die Eindüsungsöffnungen 19 sind in radialer Richtung orientiert und haben relativ zum Doppelkegel 11 eine Winkelstellung in Umfangsrichtung, wie dies aus Fig. 4 deutlich wird. Wenn man eine Mittelebene 22 definiert, die durch die Brennerachse 21 geht, und die parallel zu der Richtung ist, in welcher die Luft durch den Doppelkegel 11 tangential in den Drallraum 17 einströmt (kleine Pfeile in Fig. 4), sind die Eindüsungsöffnungen 19 um einen Winkel α von 65 Grad (+5 Grad/ -10 Grad) aus dieser Mittelebene 22 herausgedreht.In Fig. 2 is in a to Fig. 1 comparable representation of an embodiment of the invention reproduced. The burner assembly 20 comprises a double cone 11, which encloses a swirl space 17, into which a fuel lance 12 projects from the apex of the cone in the axial direction. In a second stage 14 premix fuel is injected through a plurality of injection openings in the tangent to the swirl chamber 17 air flow. In the first stage 18, instead of the many small injection orifices of the prior art, only two opposing injection orifices 19 having a significantly increased diameter are now provided, through which now the entire premix fuel of the first stage 18 is injected.
How out Fig. 3 it can be seen, the two injection openings 19 of the first stage 18 are arranged at a distance a away from the tip of the fuel lance 12. The tip of the fuel lance 12 in turn has a distance b from the open end of the swirl space 17. Preferably, the distance a is 115 mm +/- 10 mm. The distance b is preferably 135 mm. The diameter of the injection openings 19 is 5 mm +/- 0.5 mm. The injection openings 19 are oriented in the radial direction and have relative to the double cone 11 an angular position in the circumferential direction, as is made Fig. 4 becomes clear. Defining a median plane 22 passing through the burner axis 21, which is parallel to the direction in which the air flows in through the double cone 11 tangentially into the swirling space 17 (small arrows in FIG Fig. 4 ), the injection openings 19 are rotated out of this center plane 22 by an angle α of 65 degrees (+5 degrees / -10 degrees).

In den Fig. 2-4 ist eine Brenneranordnung gezeigt, bei der die Brennerlanze an der Spitze durch eine senkrecht zur Brennerachse stehenden Stirnfläche begrenzt ist (rechteckige Geometrie der Spitze). Es ist aber in Abhängigkeit von der Ausgestaltung der Düse für den flüssigen Brennstoff und der Abschirmluft auch denkbar, dass die Brennerlanze an der Spitze abgerundet oder stromlinienförmig ausgebildet sind.In the Fig. 2-4 a burner arrangement is shown in which the burner lance is delimited at the top by an end face perpendicular to the burner axis (rectangular geometry of the tip). However, it is also conceivable, depending on the configuration of the nozzle for the liquid fuel and the shielding air, that the burner lances are rounded off at the tip or have a streamlined design.

Der Betrieb der erfindungsgemässen Brenneranordnung kann nach den gleichen Prinzipien erfolgen, wie sie in der eingangs genannten Druckschrift erläutert worden ist.The operation of the burner assembly according to the invention can be carried out according to the same principles as has been explained in the document mentioned above.

Insgesamt ergibt sich mit der Erfindung eine Brenneranordnung, die sich auszeichnet durch

  • einen reduzierten Gasdruck sowohl bei Leerlauf- als auch bei Volllastbetrieb;
  • eine einfache und robuste Konstruktion; und
  • eine reduzierte Anfälligkeit für schmutzbedingtes Fouling.
Overall, with the invention results in a burner assembly, which is characterized by
  • a reduced gas pressure in both idle and full load operation;
  • a simple and robust construction; and
  • a reduced susceptibility to dirt-based fouling.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

10,2010.20
Brenneranordnung (Vormischbrenner)Burner arrangement (premix burner)
1111
Doppelkegeldouble cone
1212
Brennstofflanzefuel lance
13,1813.18
erste Stufefirst stage
1414
zweite Stufesecond step
1515
AbschirmluftAbschirmluft
1616
flüssiger Brennstoffliquid fuel
1717
Drallraumswirl space
1919
Eindüsungsöffnung erste StufeInjection opening first stage
2121
BrennerachseBrenner
2222
Mittelebenemidplane
a,bfrom
Abstanddistance
αα
Winkelangle

Claims (6)

  1. Burner arrangement (20) with a conical swirl body arranged concentrically to a burner axis (21), in the form of a double cone (11) which encloses a swirl space (17), and with a central fuel lance (12) which lies in the burner axis (21) and protrudes from the cone tip of the swirl body (11) into the swirl space (17);
    wherein a first stage (18) for injecting premix fuel is provided, in which the premix fuel is injected radially outward into the swirl space (17) through injection openings (19) arranged on the fuel lance (12); and
    wherein a second stage (14) for injecting premix fuel is provided, in which the premix fuel is injected through injection openings in the double cone (11) into an air flow guided in the double cone (11);
    wherein in the first stage (18), all the premix fuel is injected into the swirl space (17) through two opposite injection openings (19) of increased opening diameter; wherein the two injection openings (19) of the first stage (18) have a diameter of around 5 mm;
    characterised in that the two injection openings (19) are arranged twisted in the peripheral direction through an angle (α) of around 65° out of a central plane (22) which is oriented parallel to the air flowing tangentially into the double cone.
  2. Burner arrangement according to claim 1, characterised in that the fuel lance (12) protrudes into the swirl space (17) sufficiently far for the tip of the fuel lance (12) to be spaced by a distance (b) of around 135 mm from the open end of the swirl space (17), and that the two injection openings (19) are arranged spaced in the axial direction by a distance (a) of around 115 mm from the tip of the fuel lance (12).
  3. Burner arrangement according to claim 1 or 2, characterised in that liquid fuel (16) is injected in the axial direction into the swirl space (17) at the tip of the burner lance (12).
  4. Burner arrangement according to claim 3, characterised in that the liquid fuel (16) is surrounded by a casing of screening air (15).
  5. Burner arrangement according to any of claims 1 to 4, characterised in that at the tip, the burner lance (12) is delimited by an end face standing perpendicular to the burner axis (21).
  6. Burner arrangement according to any of claims 1 to 4, characterised in that the burner lance (12) is formed rounded or streamlined at the tip.
EP07726463.8A 2006-03-30 2007-02-22 Burner arrangement Active EP1999409B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH5322006 2006-03-30
PCT/EP2007/051705 WO2007113054A1 (en) 2006-03-30 2007-02-22 Burner arrangement

Publications (2)

Publication Number Publication Date
EP1999409A1 EP1999409A1 (en) 2008-12-10
EP1999409B1 true EP1999409B1 (en) 2018-05-02

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP07726463.8A Active EP1999409B1 (en) 2006-03-30 2007-02-22 Burner arrangement

Country Status (5)

Country Link
US (1) US8801429B2 (en)
EP (1) EP1999409B1 (en)
JP (1) JP2009531641A (en)
AU (1) AU2007233890B2 (en)
WO (1) WO2007113054A1 (en)

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US10571135B2 (en) 2012-04-09 2020-02-25 David Kreutzman Renewable energy hot water heater with heat pump
CN105650622B (en) * 2016-03-25 2018-05-18 宿元凯 A kind of cooking Chinese meal environmental protection and energy saving golden yellow flame burner
US10760793B2 (en) * 2017-07-21 2020-09-01 General Electric Company Jet in cross flow fuel nozzle for a gas turbine engine
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

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Also Published As

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US20090068609A1 (en) 2009-03-12
AU2007233890B2 (en) 2010-07-01
WO2007113054A1 (en) 2007-10-11
US8801429B2 (en) 2014-08-12
JP2009531641A (en) 2009-09-03
EP1999409A1 (en) 2008-12-10
AU2007233890A1 (en) 2007-10-11

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