EP2864706B1 - Local improvement of the mixture of air and fuel in burners comprising swirl generators having blade ends that are crossed in the outer region - Google Patents

Local improvement of the mixture of air and fuel in burners comprising swirl generators having blade ends that are crossed in the outer region Download PDF

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Publication number
EP2864706B1
EP2864706B1 EP13729697.6A EP13729697A EP2864706B1 EP 2864706 B1 EP2864706 B1 EP 2864706B1 EP 13729697 A EP13729697 A EP 13729697A EP 2864706 B1 EP2864706 B1 EP 2864706B1
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Prior art keywords
flow
fuel
burner
air
blades
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Not-in-force
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EP13729697.6A
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German (de)
French (fr)
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EP2864706A1 (en
Inventor
Bernd Prade
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Siemens AG
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Siemens AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—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
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors

Definitions

  • the invention relates to a burner with fuel mixing swirl generators and in particular the local improvement of the mixture of air and fuel.
  • the even mixing of fuel into the combustion air is the central design task in the development of burners, which are operated in the field of so-called lean premix combustion.
  • the temperature range of lean premix combustion is particularly useful in gas turbines because of the material-related limitation of the combustion chamber outlet temperature for controlling nitrogen oxide emissions.
  • the difficulty of premix combustion, especially under pressure, is the avoidance of uncontrollable combustion phenomena / auto-ignition within the premix, which is usually associated with the destruction of the premix. As a rule of thumb, it can be assumed that the most homogeneous premix possible also results in minimal NO x emissions.
  • the object of the invention is to provide a burner of the type mentioned, which allows an improved mixture of air and fuel, in particular in radially outer regions of the premix.
  • the invention solves this problem by providing that in such a burner with a substantially annular in cross-section, in the operation of air and fuel flow through the air supply and Vormischkanal, which is formed by an outer shell and a hub and in the plurality of swirl vanes are arranged, which extend from the hub to the outer shell in the radial direction and have a deflection surface, wherein exclusively in a radial outer region of the Swirl blades at least one time and once decreases a flow angle to a main flow direction at an outflow end of the deflection in the radial direction.
  • the invention is based on the recognition that the locally present turbulence intensity represents an additional influencing parameter on the mixing of the fuel into the air.
  • An increase in the turbulence intensity has a mixing-promoting effect.
  • an outflow angle ⁇ 1 lies at a radially inward outflow end of the deflection surface between an outflow angle ⁇ 3 of a radially outer outflow end and an outflow angle ⁇ 2 of an outflow end located therebetween.
  • the turbulence is then locally increased in the form of a vortex street because of the shear.
  • the swirl blades are at least partially designed as hollow blades with outlet openings for fuel.
  • burner 1 which may optionally be used in conjunction with several similar burners, for example in the combustion chamber of a gas turbine plant comprises an inner pilot burner system 2 and the pilot burner system 2 concentrically surrounding the main burner system 3.
  • Both pilot burner system 2 and main burner system 3 can optionally with gaseous and / or liquid fuels, such as, for example, natural gas or fuel oil operated.
  • the main burner system 3 comprises a radial outer air supply and premixing duct 4, also called annular air duct, which is formed by an outer jacket 5 and a hub 6 and through which swirl vanes 7 extend a swirl blading. These swirl blades 7 have outlet openings 8 for fuel, through which fuel gas can be injected into the air flowing in through the radial air supply and premixing channel 4.
  • FIG. 2 shows a developed portion of the main burner system 3 in the plan view with the swirl blades 7 and illustrates the areas of good 9 and bad interference 10 of the fuel in air.
  • the blades 7 Radially inside, ie in the vicinity of the hub 6, the blades 7 are comparatively close to each other, so that the fuel sufficiently far into the gap can be injected between two blades 7 in order to achieve the best possible mixing.
  • FIG. 3 shows the view of the deflection surface 11 of a swirl blade 7 of a burner 1 according to the invention.
  • the swirl blade 7 extends in the burner 1 from the radially inner hub 6 (right, not shown) to the radially outer outer jacket 5 (left, not shown).
  • the swirl blade 7 in the embodiment of FIG. 3 designed as hollow blades with outlet openings 8 for fuel.
  • three regions 101, 102 and 103 are marked in the region of the outflow end 12 of the deflection surface 11, the regions 102 and 103 being attributable to the radial outer region of the blade 7.
  • FIG. 4 shows three successive cuts through the areas 101, 102 and 103 of the swirl blade 7 of the FIG. 3 Viewing from the hub 6 to the outer jacket 5. It can be seen that at a radially inner outflow end 12 of the deflection 11, ie in section through the region 101, the outflow angle ⁇ 1 to a main flow direction 13 between a discharge angle ⁇ 3 of a radially outer Outflowing 12, that is, in section through the region 103, and an outflow angle ⁇ 2 of an intervening outflow end, ie in section through the region 102, is located.

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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)

Description

Die Erfindung betrifft einen Brenner mit Brennstoff einmischenden Drallerzeugern und insbesondere die lokale Verbesserung der Mischung von Luft und Brennstoff.The invention relates to a burner with fuel mixing swirl generators and in particular the local improvement of the mixture of air and fuel.

Die gleichmäßige Einmischung von Brennstoff in die Verbrennungsluft ist die zentrale Designaufgabe bei der Entwicklung von Brennern, die im Bereich der sogenannten mageren Vormischverbrennung betrieben werden. Der Temperaturbereich der mageren Vormischverbrennung bietet sich in Gasturbinen wegen der materialbedingten Beschränkung der Brennkammeraustrittstemperatur zur Kontrolle von Stickoxidemissionen besonders an. Die Schwierigkeit der Vormischverbrennung, insbesondere unter Druck, ist die Vermeidung von unkontrollierbaren Verbrennungserscheinungen/Selbstzündungen innerhalb der Vormischstrecke, welche in der Regel mit der Zerstörung der Vormischstrecke verbunden sind.
Als Faustregel kann angenommen werden, dass eine möglichst homogene Vormischung auch in minimalen NOx-Emissionen resultiert.The even mixing of fuel into the combustion air is the central design task in the development of burners, which are operated in the field of so-called lean premix combustion. The temperature range of lean premix combustion is particularly useful in gas turbines because of the material-related limitation of the combustion chamber outlet temperature for controlling nitrogen oxide emissions. The difficulty of premix combustion, especially under pressure, is the avoidance of uncontrollable combustion phenomena / auto-ignition within the premix, which is usually associated with the destruction of the premix.
As a rule of thumb, it can be assumed that the most homogeneous premix possible also results in minimal NO x emissions.

In der Regel sind technische Brenner annähernd rotationssymmetrisch aufgebaut und haben häufig einen oder mehrere konzentrisch umeinander angeordnete Drallerzeuger. Stand der Technik ist es mittlerweile, die Drallerzeugerschaufeln als Hohlschaufeln auszuführen und gleichzeitig als Brennstoffeindüseelemente zu nutzen, siehe beispielsweise WO 2011/023669 . Derartige Anordnungen führen meist dazu, dass es einen deutlichen Unterschied des Abstands von zwei benachbarten Schaufel auf der Nabe gegenüber dem Außenschnitt gibt, d.h. die Schaufeln stehen nabenseitig in der Regel deutlich näher zusammen als außen. Damit ergibt sich das Problem, den Brennstoff vor allem radial außen hinreichend weit in den Zwischenraum zwischen zwei Schaufeln einzudüsen, um eine möglichst gute Mischung zu erreichen, während das auf der Nabenseite deutlich leichter zu erreichen ist.As a rule, industrial burners are constructed approximately rotationally symmetrical and frequently have one or more swirl generators arranged concentrically around one another. In the meantime, the prior art has been to make the swirl generator blades as hollow blades and at the same time to use them as fuel injector elements, see, for example WO 2011/023669 , Such arrangements usually lead to the fact that there is a significant difference in the distance between two adjacent blades on the hub relative to the outer cut, ie the blades are generally much closer together on the hub side than on the outside. This results in the problem of the fuel, especially radially outside sufficiently far in the Injecting space between two blades to achieve the best possible mixture, while on the hub side is much easier to achieve.

Es gibt Vorschläge, dieses Problem zu lösen. In der Regel fällt die Verbesserung aber nicht übermäßig groß aus. Beispiele sind:

  • Vergrößerung der Brennstoff-Bohrungsdurchmesser von innen nach außen. Damit lässt sich zwar eine partielle, wenn auch nicht völlig ausreichende Verbesserung der Eindringtiefe der Brennstoffstrahlen erreichen, gleichzeitig nimmt aber die erforderliche Mischungsstrecke zu (skaliert etwa mit dem Durchmesser der Brennstoffbohrung).
  • Erhöhung der Anzahl der Schaufelzahl. Dies ist konstruktiv und aerodynamisch begrenzt durch den verfügbaren Platz auf der Nabe und die zunehmende Blockierung der Luftströmung nabenseitig.
  • Verwendung stark 3-dimensionaler Schaufelprofile mit zunehmender Schaufelstärke mit steigendem Abstand von der Nabe. Auch hierdurch kommt es zu Problemen hinsichtlich der aerodynamischen Kontur der Schaufel, diesmal im Außenschnitt, um von der großen Schaufelstärke in der Ebene der Brennstoffbohrungen wieder auf ein sehr dünnes Schaufelende zu kommen, d.h. die Schaufeln würden dann außen sehr lang.
There are suggestions to solve this problem. In general, the improvement is not overly large. Examples are:
  • Enlargement of the fuel bore diameter from inside to outside. Thus, although a partial, albeit not completely sufficient improvement in the penetration depth of the fuel jets can be achieved, but at the same time increases the required mixing distance (scales approximately with the diameter of the fuel bore).
  • Increase the number of blades. This is constructive and aerodynamically limited by the available space on the hub and the increasing blockage of air flow on the hub side.
  • Use of strong 3-dimensional blade profiles with increasing blade thickness with increasing distance from the hub. This also causes problems with respect to the aerodynamic contour of the blade, this time in the outer section, in order to get back to a very thin blade end from the large blade thickness in the plane of the fuel holes, ie the blades would then be very long outside.

Des Weiteren ist aus der DE 4406399 eine Schaufelverschränkung der Drallschaufeln bekannt.Furthermore, from the DE 4406399 a blade entanglement of the swirl blades known.

Aufgabe der Erfindung ist es, einen Brenner der eingangs genannten Art bereitzustellen, der eine verbesserte Mischung von Luft und Brennstoff, insbesondere in radial außen liegenden Bereichen der Vormischstrecke, ermöglicht.The object of the invention is to provide a burner of the type mentioned, which allows an improved mixture of air and fuel, in particular in radially outer regions of the premix.

Die Erfindung löst diese Aufgabe, indem sie vorsieht, dass bei einem derartigen Brenner mit einem im Querschnitt im Wesentlichen ringförmigen, im Betrieb von Luft und Brennstoff durchströmten Luftzufuhr-und-Vormischkanal, der durch einen Außenmantel und eine Nabe gebildet ist und in dem mehrere Drallschaufeln angeordnet sind, die sich von der Nabe bis zum Außenmantel in radialer Richtung erstrecken und eine Umlenkfläche aufweisen, wobei ausschließlich in einem radialen Außenbereich der Drallschaufeln ein Abströmwinkel zu einer Hauptströmungsrichtung an einem Abströmende der Umlenkfläche in radialer Richtung mindestens einmal zu- und einmal abnimmt.The invention solves this problem by providing that in such a burner with a substantially annular in cross-section, in the operation of air and fuel flow through the air supply and Vormischkanal, which is formed by an outer shell and a hub and in the plurality of swirl vanes are arranged, which extend from the hub to the outer shell in the radial direction and have a deflection surface, wherein exclusively in a radial outer region of the Swirl blades at least one time and once decreases a flow angle to a main flow direction at an outflow end of the deflection in the radial direction.

Die Erfindung geht von der Erkenntnis aus, dass die lokal vorliegende Turbulenzintensität einen zusätzlichen Einflussparameter auf die Einmischung des Brennstoffs in die Luft darstellt. Eine Erhöhung der Turbulenzintensität wirkt mischungsfördernd.The invention is based on the recognition that the locally present turbulence intensity represents an additional influencing parameter on the mixing of the fuel into the air. An increase in the turbulence intensity has a mixing-promoting effect.

Es wird daher vorgeschlagen im Außenschnitt, die Turbulenzintensität zu erhöhen, bzw. mischungsfördernde Wirbelstraßen zu erzeugen.It is therefore proposed in the outer section to increase the turbulence intensity, or to produce mixing-promoting vortex streets.

In einer vorteilhaften Ausführungsform liegt ein Abströmwinkel α1 an einem radial innen liegenden Abströmende der Umlenkfläche zwischen einem Abströmwinkel α3 eines radial außen liegenden Abströmendes und einem Abströmwinkel α2 eines dazwischen liegenden Abströmendes. In den Scherzonen der Bereiche mit unterschiedlichen Abströmwinkeln wird dann wegen der Scherung die Turbulenz lokal in Form einer Wirbelstraße erhöht.In an advantageous embodiment, an outflow angle α 1 lies at a radially inward outflow end of the deflection surface between an outflow angle α 3 of a radially outer outflow end and an outflow angle α 2 of an outflow end located therebetween. In the shear zones of the regions with different outflow angles, the turbulence is then locally increased in the form of a vortex street because of the shear.

Dabei kann es zweckmäßig sein, wenn benachbarte Drallschaufeln unterschiedliche radiale Verläufe ihrer Abströmwinkel α aufweisen.It may be expedient if adjacent swirl blades have different radial courses of their outflow angle α.

Bevorzugtermaßen sind die Drallschaufeln zumindest zum Teil als Hohlschaufeln mit Auslassöffnungen für Brennstoff ausgeführt.Preferably, the swirl blades are at least partially designed as hollow blades with outlet openings for fuel.

Es ist zweckmäßig, wenn der Luftzufuhr-und-Vormischkanal ein zentrales Pilotbrennersystem konzentrisch umgibt.It is useful if the air supply and premixing channel concentrically surrounds a central pilot burner system.

Die lokale Anwendung mischungsfördernder Turbulenz durch gegeneinander "verschränkte" Schaufelenden verbessert die Mischungsqualität im Außenschnitt, ohne die innen liegenden Bereiche stark zu beeinflussen. Weiterhin wird die Mischungsqualität unabhängiger von den Betriebsbedingungen.The local application of mixture-promoting turbulence through mutually "entangled" blade ends improves the quality of the mixture in the outer section, without the internal areas strongly influence. Furthermore, the mixing quality is more independent of the operating conditions.

Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen nicht maßstäblich:

Figur 1
einen Brenner in einer stark schematisierten Prinzipskizze,
Figur 2
eine Draufsicht auf einen abgewickelten Teil des Hauptbrennersystems,
Figur 3
eine Draufsicht auf eine Drallschaufel und
Figur 4
in radialer Richtung von der Nabe zum Außenmantel versetzte Schnitte durch eine Drallschaufel.
The invention will be explained in more detail by way of example with reference to the drawings. It does not show to scale:
FIG. 1
a burner in a very schematized schematic diagram,
FIG. 2
a top view of a developed part of the main burner system,
FIG. 3
a plan view of a swirl blade and
FIG. 4
in the radial direction from the hub to the outer shell staggered cuts through a swirl blade.

Der in Figur 1 gezeigte Brenner 1, der ggf. in Verbindung mit mehreren gleichartigen Brennern beispielsweise in der Brennkammer einer Gasturbinenanlage eingesetzt werden kann, umfasst ein inneres Pilotbrennersystem 2 und ein das Pilotbrennersystem 2 konzentrisch umgebendes Hauptbrennersystem 3. Sowohl Pilotbrennersystem 2 als auch Hauptbrennersystem 3 können wahlweise mit gasförmigen und/oder flüssigen Brennstoffen, wie bspw. Erdgas oder Heizöl, betrieben werden.The in FIG. 1 shown burner 1, which may optionally be used in conjunction with several similar burners, for example in the combustion chamber of a gas turbine plant comprises an inner pilot burner system 2 and the pilot burner system 2 concentrically surrounding the main burner system 3. Both pilot burner system 2 and main burner system 3 can optionally with gaseous and / or liquid fuels, such as, for example, natural gas or fuel oil operated.

Das Hauptbrennersystem 3 umfasst einen radialen äußeren Luftzufuhr-und-Vormischkanal 4, auch Ringluftkanal genannt, der durch einen Außenmantel 5 und eine Nabe 6 gebildet ist und durch den sich Drallschaufeln 7 einer Drallbeschaufelung erstrecken. Diese Drallschaufeln 7 weisen Auslassöffnungen 8 für Brennstoff auf, durch die Brenngas in die durch den radialen Luftzufuhr-und-Vormischkanal 4 einströmende Luft eingedüst werden kann.The main burner system 3 comprises a radial outer air supply and premixing duct 4, also called annular air duct, which is formed by an outer jacket 5 and a hub 6 and through which swirl vanes 7 extend a swirl blading. These swirl blades 7 have outlet openings 8 for fuel, through which fuel gas can be injected into the air flowing in through the radial air supply and premixing channel 4.

Figur 2 zeigt einen abgewickelten Teil des Hauptbrennersystems 3 in der Draufsicht mit den Drallschaufeln 7 und verdeutlicht die Bereiche guter 9 und schlechter Einmischung 10 des Brennstoffs in Luft. Radial innen, also in Nähe der Nabe 6, stehen die Schaufeln 7 vergleichsweise dicht beieinander, so dass der Brennstoff hinreichend weit in den Zwischenraum zwischen zwei Schaufeln 7 eingedüst werden kann, um eine möglichst gute Durchmischung zu erzielen. Radial außen, in der Nähe des Außenmantels 5, sind die Schaufeln 7 entsprechend weiter voneinander entfernt, wodurch eine hinreichend weite Eindüsung des Brennstoffs in die Luft erschwert ist. FIG. 2 shows a developed portion of the main burner system 3 in the plan view with the swirl blades 7 and illustrates the areas of good 9 and bad interference 10 of the fuel in air. Radially inside, ie in the vicinity of the hub 6, the blades 7 are comparatively close to each other, so that the fuel sufficiently far into the gap can be injected between two blades 7 in order to achieve the best possible mixing. Radially outside, in the vicinity of the outer shell 5, the blades 7 are correspondingly farther apart, whereby a sufficiently wide injection of the fuel into the air is difficult.

Figur 3 zeigt die Ansicht der Umlenkfläche 11 einer Drallschaufel 7 eines Brenners 1 nach der Erfindung. Die Drallschaufel 7 erstreckt sich im Brenner 1 von der radial innen liegenden Nabe 6 (rechts, nicht gezeigt) bis zum radial außen liegenden Außenmantel 5 (links, nicht gezeigt). Ferner ist die Drallschaufel 7 im Ausführungsbeispiel der Figur 3 als Hohlschaufeln mit Auslassöffnungen 8 für Brennstoff ausgeführt. Zum besseren Verständnis der Erfindung sind im Bereich des Abströmendes 12 der Umlenkfläche 11 drei Bereiche 101, 102 und 103 gekennzeichnet, wobei die Bereiche 102 und 103 dem radialen Außenbereich der Schaufel 7 zuzurechnen sind. FIG. 3 shows the view of the deflection surface 11 of a swirl blade 7 of a burner 1 according to the invention. The swirl blade 7 extends in the burner 1 from the radially inner hub 6 (right, not shown) to the radially outer outer jacket 5 (left, not shown). Furthermore, the swirl blade 7 in the embodiment of FIG. 3 designed as hollow blades with outlet openings 8 for fuel. For a better understanding of the invention, three regions 101, 102 and 103 are marked in the region of the outflow end 12 of the deflection surface 11, the regions 102 and 103 being attributable to the radial outer region of the blade 7.

Figur 4 zeigt drei hintereinander gelegte Schnitte durch die Bereiche 101, 102 und 103 der Drallschaufel 7 der Figur 3 mit Blickrichtung von der Nabe 6 zum Außenmantel 5. Man erkennt, dass an einem radial innen liegenden Abströmende 12 der Umlenkfläche 11, d.h. im Schnitt durch den Bereich 101, der Abströmwinkel α1 zu einer Hauptströmungsrichtung 13 zwischen einem Abströmwinkel α3 eines radial außen liegenden Abströmendes 12, d.h. im Schnitt durch den Bereich 103, und einem Abströmwinkel α2 eines dazwischen liegenden Abströmendes, d.h. im Schnitt durch den Bereich 102, liegt. Andere Ausführungsformen der Drallschaufel 7, bei der in einem radialen Außenbereich ein Abströmwinkel α zu einer Hauptströmungsrichtung 13 an einem Abströmende 12 der Umlenkfläche 11 in radialer Richtung mindestens einmal zu- und einmal abnimmt, sind ebenso möglich, solange im Außenbereich der Drallschaufel 7, d.h. in der Nähe des Außenmantels 5, am Schaufelende eine Art Verschränkung geschaffen wird, so dass dort in der im Betrieb entstehenden Scherzone eine mischende Wirbelstraße erzeugt wird. FIG. 4 shows three successive cuts through the areas 101, 102 and 103 of the swirl blade 7 of the FIG. 3 Viewing from the hub 6 to the outer jacket 5. It can be seen that at a radially inner outflow end 12 of the deflection 11, ie in section through the region 101, the outflow angle α 1 to a main flow direction 13 between a discharge angle α 3 of a radially outer Outflowing 12, that is, in section through the region 103, and an outflow angle α 2 of an intervening outflow end, ie in section through the region 102, is located. Other embodiments of the swirl vane 7, in which in a radial outer region an outflow angle α to a main flow direction 13 at a discharge end 12 of the deflection 11 in the radial direction at least once and decreases, are also possible, as long as in the outer region of the swirl blade 7, ie in near the outer shell 5, a kind of entanglement is created at the blade end, so that a mixing vortex street is generated there in the shear zone produced during operation.

Claims (5)

  1. Burner (1) with an air supply and premix duct (4) which is of substantially annular cross section, through which, in operation, air and fuel flow, which is formed by an outer shell (5) and a hub (6) and in which multiple swirl blades (7) are arranged which extend radially from the hub (6) to the outer shell (5) and have a deflection surface (11), characterized in that, exclusively in a radial outer region of the swirl blades (7), a flow-off angle (α) with respect to a main flow direction (13) at a flow-off end (12) of the deflection surface (11) increases at least once and decreases at least once in the radial direction.
  2. Burner (1) according to Claim 1, wherein, at a radially inner flow-off end (12) of the deflection surface (11), a flow-off angle (α1) is between a flow-off angle (α3) of a radially outer flow-off end (12) and a flow-off angle (α2) of a flow-off end (12) therebetween.
  3. Burner (1) according to either of Claims 1 and 2, wherein the flow-off angles (α) of adjacent swirl blades (7) exhibit different radial profiles.
  4. Burner (1) according to one of the preceding claims, wherein the swirl blades (7) are at least partially embodied as hollow blades with outlet openings (8) for fuel.
  5. Burner (1) according to one of the preceding claims, wherein the air supply and premix duct (4) concentrically surrounds a central pilot burner system (2).
EP13729697.6A 2012-08-06 2013-06-13 Local improvement of the mixture of air and fuel in burners comprising swirl generators having blade ends that are crossed in the outer region Not-in-force EP2864706B1 (en)

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DE102012213853 2012-08-06
PCT/EP2013/062248 WO2014023462A1 (en) 2012-08-06 2013-06-13 Local improvement of the mixture of air and fuel in burners comprising swirl generators having blade ends that are crossed in the outer region

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EP2864706A1 EP2864706A1 (en) 2015-04-29
EP2864706B1 true EP2864706B1 (en) 2016-11-02

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KR (1) KR20150039763A (en)
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WO (1) WO2014023462A1 (en)

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Also Published As

Publication number Publication date
EP2864706A1 (en) 2015-04-29
CN104471317A (en) 2015-03-25
CN104471317B (en) 2016-09-07
RU2633475C2 (en) 2017-10-12
US20150285499A1 (en) 2015-10-08
KR20150039763A (en) 2015-04-13
RU2015107562A (en) 2016-09-27
US10012386B2 (en) 2018-07-03
WO2014023462A1 (en) 2014-02-13

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