EP1534997B1 - Gas turbine burner - Google Patents

Gas turbine burner Download PDF

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Publication number
EP1534997B1
EP1534997B1 EP03794901.3A EP03794901A EP1534997B1 EP 1534997 B1 EP1534997 B1 EP 1534997B1 EP 03794901 A EP03794901 A EP 03794901A EP 1534997 B1 EP1534997 B1 EP 1534997B1
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EP
European Patent Office
Prior art keywords
burner
fuel
swirl blade
channel
radial direction
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 - Lifetime
Application number
EP03794901.3A
Other languages
German (de)
French (fr)
Other versions
EP1534997A2 (en
Inventor
Peter Berenbrink
Malte Blomeyer
Werner Krebs
Bernd Prade
Holger Streb
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.)
Siemens AG
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Siemens AG
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Publication date
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Priority to EP03794901.3A priority Critical patent/EP1534997B1/en
Publication of EP1534997A2 publication Critical patent/EP1534997A2/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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a burner according to the preamble of claim 1.
  • Such combustion instabilities can be actively suppressed, for example by increasing the power of the pilot flame, or passively, for example by resonators.
  • the EP 0 870 989 discloses differently sized fuel outlets for stabilizing the flame at low load conditions, with the openings being smallest in an upstream region.
  • the EP 1 207 350 discloses for magnification of the operating range of a combustion chamber, the injection of differently controlled fuel / air mixture jets into different target spaces within a mixing zone.
  • the DE 199 48 673 discloses a method for preventing thermoacoustic combustion instabilities, in which regions of different average flow velocity are generated in the gas flow and the fuel is injected into these regions.
  • the EP 0 672 865 describes a fuel nozzle for diffusion and premixing operation.
  • the US 6,092,363 discloses a low NOx burner suitable for operation with various fuels.
  • the burner includes concentrically arranged cylindrical passages with annular fuel nozzle channels at the respective upstream end.
  • the US 5,511,375 shows a device for mixing fuel with air for a gas turbine combustor, in which extending for the radial fuel distribution through the hollow blades of a diagonal grid fuel passages.
  • FIG. 1 shows a burner 1, in particular a premix burner 1, in particular for a gas turbine.
  • the burner 1 has a burner longitudinal axis 46. Along the burner longitudinal axis 46, for example, a diffusion or pilot burner 43 is arranged centrally. In the pre-mixing operation, the pilot burner 43 is operated to support the burner 1.
  • a Vormisch zone 10 and / or a combustion chamber 19 is supplied to the longitudinal axis 46 .
  • oxygen or other gas can be supplied, which results in the fuel 7, a combustible fuel-gas mixture.
  • air 4 is first supplied to the duct 13 and then the fuel 7.
  • the air 4 flows in the channel 13, for example, past at least one swirl blade 16, the swirl blade 16, for example, supplying fuel 7 to the channel 13.
  • the swirl vanes 16 are, for example, annular, in particular equidistant, arranged around the burner longitudinal axis 46 (FIG. Fig. 6 ).
  • the air 4 and the fuel 7 mix in the premix 10, which is indicated by dashed lines.
  • FIG. 2 shows the radial end 49 of the diffusion / pilot burner 43 with the annular channel 13th
  • the fuel 7 is supplied to the channel 13 via at least two fuel nozzles 31 and flows there in a flow direction 88.
  • the fuel supply via fuel nozzles 31, which are arranged in the swirl vane 16.
  • the fuel 7 can also be supplied to the channel 13 via other distribution units.
  • the combustion instabilities result from a distribution of the fuel concentration 58 according to the prior art.
  • concentration of the fuel is approximately equal.
  • the operating range is extended according to the invention, in that an outflow angle ⁇ of a medium, ie the angle between resulting speed and peripheral speed ( Fig. 5 ), for example of the air / fuel mixture 7, in a radial direction 55 from a maximum value to a minimum Value decreases from the inside out. This is done by a twist of the swirl blade 16 as in FIG. 4 described.
  • the outflow angle ⁇ is also the angle between the flow direction of the medium flowing in the channel (air, oxygen, fuel, mixtures thereof) and a plane whose normal is the burner longitudinal axis 46.
  • an additional fuel concentration distribution 52 which is not constant in the radial direction 55 at least at a point in time during the operation of the burner 1, the intensity of the combustion oscillations is reduced. In this way, the operating range for the burner 1 can be extended.
  • the fuel concentration changes, for example, in the radial direction 55 as viewed from the center, i. from the burner longitudinal axis 46, to the outside, in particular, the fuel concentration, for example, decreases linearly or to.
  • FIG. 3 shows a swirl blade 16, with which this can be realized.
  • FIG. 3 shows a swirl blade 16 for a burner.
  • the swirl blade 16 has a leading edge 67 and a trailing edge 70.
  • the medium flows in the flow direction 88 first past the leading edge 67 and then past the trailing edge 70.
  • a core 73 is present, in which a feed 64 for fuel 7 is present.
  • the feeder 64 is, for example, a blind hole.
  • 64 holes are present in the supply, which constitute the fuel nozzles 31. Through these fuel nozzles 31, the fuel 7 enters the channel 13.
  • the diameter of the holes of the fuel nozzles 31 of the built-in burner swirl blade 1 change in the radial direction 55 according to the concentration distribution 52 and takes, for example. In the radial direction 55 seen from the inside outwards.
  • the medium which flows past the swirl blade 16, experiences an outflow angle ⁇ .
  • FIG. 4 shows a swirl blade 16 for a burner 1 according to the invention.
  • the swirl blade 16 is, for example, with respect to the size and distribution of the fuel nozzles 31 as the swirl blade in FIG. 3 educated.
  • the airfoil 61 is still wound around a winding axis 76.
  • the winding axis 76 forms with the flow direction 88 a non-zero cutting angle and is in particular at 90 °.
  • a gas or a fuel-air mixture which flows at the swirl blade 16 from the leading edge 67 to the outflow edge 70, experiences in the radial direction 55 different outflow angles ⁇ , i.
  • a different outflow angle ⁇ 1 is generated than at the other end, an outflow angle ⁇ 2 (not equal to ⁇ 1), viewed in the direction of a longitudinal axis of the feed 64.
  • the outflow angle ⁇ decreases linearly. There may also be a non-linear increase or decrease.
  • This distribution in the radial direction 55 of the outflow angle ⁇ also suppresses combustion instabilities, so that the operating range for the burner 1 is widened.
  • the flowing medium forms at the swirl blade 16 with the flow direction 88 in the channel 13 the outflow angle ⁇ .
  • the swirl blade 16 is wound according to the invention and may also have different diameters for the fuel nozzles.
  • FIG. 5 shows the arrangement of the various flow vectors of the gas flowing in the channel 13.
  • the vector 79 represents the meridional velocity component.
  • the vector 82 represents the peripheral velocity, resulting in a resulting velocity sector 85.
  • the angle between the resulting speed 85 and the peripheral speed 82 represents the outflow angle ⁇ .
  • the angle 90 ° - ⁇ is the complementary angle.
  • the outflow angle ⁇ is also the angle between the flow direction of the flowing medium and a plane which is perpendicular to the burner longitudinal axis 46.

Landscapes

  • 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)
  • Spray-Type Burners (AREA)
  • Air Supply (AREA)

Description

Die Erfindung betrifft einen Brenner gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a burner according to the preamble of claim 1.

Der Betriebsbereich von Brennern mit Vormischungen, insbesondere in Gasturbinen, wird durch selbsterregte Flammenschwingungen begrenzt.The operating range of burners with premixes, especially in gas turbines, is limited by self-excited flame oscillations.

Solche Verbrennungsinstabilitäten können aktiv, beispielsweise durch Erhöhung der Leistung der Pilotflamme, oder passiv, beispielsweise durch Resonatoren, unterdrückt werden.Such combustion instabilities can be actively suppressed, for example by increasing the power of the pilot flame, or passively, for example by resonators.

Die EP 0 870 989 offenbart Brennstoffauslässe in unterschiedlicher Größe zur Stabilisierung der Flamme bei Niederlastbedingungen, wobei die Öffnungen in einem stromaufwärtigen Bereich am kleinsten sind.The EP 0 870 989 discloses differently sized fuel outlets for stabilizing the flame at low load conditions, with the openings being smallest in an upstream region.

Die EP 1 207 350 offenbart zur Vergößerung des Betriebsbereichs einer Brennkammer das Eindüsen von unterschiedlich angesteuerten Brennstoff/Luft-Gemisch-Strahlen in verschiedene Zielräume innerhalb einer Mischzone.The EP 1 207 350 discloses for magnification of the operating range of a combustion chamber, the injection of differently controlled fuel / air mixture jets into different target spaces within a mixing zone.

Die DE 199 48 673 offenbart ein Verfahren zur Vermeidung von thermoakustischen Verbrennungsinstabilitäten, bei dem in der Gasströmung Bereiche mit unterschiedlicher mittlerer Strömungsgeschwindigkeit erzeugt werden und der Brennstoff in diese Bereiche eingedüst wird.The DE 199 48 673 discloses a method for preventing thermoacoustic combustion instabilities, in which regions of different average flow velocity are generated in the gas flow and the fuel is injected into these regions.

Die EP 0 672 865 beschreibt eine Brennstoffdüse für Diffusions- und Vormischbetrieb.The EP 0 672 865 describes a fuel nozzle for diffusion and premixing operation.

Die US 6,092,363 offenbart einen Brenner für niedriege NOx-Emissionen, der für den Betrieb mit verschiedenen Brennstoffen geeignet ist. Der Brenner umfasst konzentrisch angeordnete zylinderförmige Passagen mit ringförmigen Brennstoffdüsenkanälen am jeweiligen stromaufwärtigen Ende.The US 6,092,363 discloses a low NOx burner suitable for operation with various fuels. The burner includes concentrically arranged cylindrical passages with annular fuel nozzle channels at the respective upstream end.

Die US 5,511,375 zeigt eine Vorrichtung zum Mischen von Brennstoff mit Luft für einen Gasturbinenbrenner, bei der sich zur radialen Brennstoffverteilung durch die hohlen Schaufeln eines Diagonalgitters Brennstoffpassagen erstrecken.The US 5,511,375 shows a device for mixing fuel with air for a gas turbine combustor, in which extending for the radial fuel distribution through the hollow blades of a diagonal grid fuel passages.

Es ist daher Aufgabe der Erfindung, einen Brenner aufzuzeigen, bei dem auf einfache Art und Weise ein stabiler Bereich für die Verbrennung erweitert wird.It is therefore an object of the invention to provide a burner in which a simple way a stable range for the combustion is extended.

Die Aufgabe wird gelöst durch einen Brenner gemäß Anspruch 1. Weitere vorteilhafte Ausgestaltungen des Brenners sind in den Unteransprüchen aufgelistet.The object is achieved by a burner according to claim 1. Further advantageous embodiments of the burner are listed in the subclaims.

Es zeigen

Figur 1
einen Brenner,
Figur 2
einen vergrößerten Ausschnitt aus Figur 1,
Figur 3
eine Drallschaufel für einen erfindungsgemäß ausgebildeten Brenner,
Figur 4
eine Drallschaufel für einen erfindungsgemäß ausgebildeten Brenner,
Figur 5
Geschwindigkeitsvektoren eines strömenden Brennstoffs Luft-Gasgemisches, und
Figur 6
einen Schnitt entlang der Linie VI-VI der Figur 2.
Show it
FIG. 1
a burner,
FIG. 2
an enlarged section FIG. 1 .
FIG. 3
a swirl blade for a burner designed according to the invention,
FIG. 4
a swirl blade for a burner designed according to the invention,
FIG. 5
Velocity vectors of a flowing fuel air-gas mixture, and
FIG. 6
a section along the line VI-VI of Figure 2.

Figur 1 zeigt einen Brenner 1, insbesondere einen Vormischbrenner 1, insbesondere für eine Gasturbine. FIG. 1 shows a burner 1, in particular a premix burner 1, in particular for a gas turbine.

Der Brenner 1 weist eine Brennerlängsachse 46 auf. Längs der Brennerlängsachse 46 ist mittig beispielsweise ein Diffusions- oder Pilotbrenner 43 angeordnet. Im Vormischbetrieb wird der Pilotbrenner 43 zur Unterstützung des Brenners 1 betrieben.The burner 1 has a burner longitudinal axis 46. Along the burner longitudinal axis 46, for example, a diffusion or pilot burner 43 is arranged centrally. In the pre-mixing operation, the pilot burner 43 is operated to support the burner 1.

An einem radialen Ende 49 des Diffusionsbrenners 43 wird über einen bspw. zur Längsachse 46 ringförmigen Kanal 13 (Fig. 6) Brennstoff 7 und/oder Luft 4 einer Vormischstrecke 10 und/oder einem Brennraum 19 zugeführt. Anstatt Luft kann auch Sauerstoff oder ein anderes Gas zugeführt werden, das mit dem Brennstoff 7 ein brennbares Brennstoff-Gasgemisch ergibt. Beispielsweise wird zuerst Luft 4 dem Kanal 13 und dann der Brennstoff 7 zugeführt.At a radial end 49 of the diffusion burner 43 is via an example. To the longitudinal axis 46 annular channel 13 (FIG. Fig. 6 ) Fuel 7 and / or air 4 a Vormischstrecke 10 and / or a combustion chamber 19 is supplied. Instead of air also oxygen or other gas can be supplied, which results in the fuel 7, a combustible fuel-gas mixture. For example, air 4 is first supplied to the duct 13 and then the fuel 7.

Die Luft 4 strömt im Kanal 13 bspw. zumindest an einer Drallschaufel 16 vorbei, wobei die Drallschaufel 16 bspw. Brennstoff 7 dem Kanal 13 zuführt.The air 4 flows in the channel 13, for example, past at least one swirl blade 16, the swirl blade 16, for example, supplying fuel 7 to the channel 13.

Die Drallschaufeln 16 sind bspw. ringförmig, insbesondere äquidistant, um die Brennerlängsachse 46 angeordnet (Fig. 6). Die Luft 4 und der Brennstoff 7 vermischen sich in der Vormischstrecke 10, die gestrichelt angedeutet ist.The swirl vanes 16 are, for example, annular, in particular equidistant, arranged around the burner longitudinal axis 46 (FIG. Fig. 6 ). The air 4 and the fuel 7 mix in the premix 10, which is indicated by dashed lines.

Es kann aber auch zuerst der Brennstoff 7 und dann die Luft 4 in dem Kanal 13 zugeführt werden.But it may also first the fuel 7 and then the air 4 are supplied in the channel 13.

Figur 2 zeigt das radiale Ende 49 des Diffusions/Pilotbrenners 43 mit dem ringförmigen Kanal 13. FIG. 2 shows the radial end 49 of the diffusion / pilot burner 43 with the annular channel 13th

Der Brennstoff 7 wird über zumindest zwei Brennstoffdüsen 31 dem Kanal 13 zugeführt und strömt dort in einer Strömungsrichtung 88.The fuel 7 is supplied to the channel 13 via at least two fuel nozzles 31 and flows there in a flow direction 88.

Vorzugsweise erfolgt die Brennstoffzuführung über Brennstoffdüsen 31, die in der Drallschaufel 16 angeordnet sind.Preferably, the fuel supply via fuel nozzles 31, which are arranged in the swirl vane 16.

Der Brennstoff 7 kann auch über andere Verteilungseinheiten dem Kanal 13 zugeführt werden.The fuel 7 can also be supplied to the channel 13 via other distribution units.

Die Verbrennungsinstabilitäten entstehen durch eine Verteilung der Brennstoffkonzentration 58 nach dem Stand der Technik. In radialer Richtung 55, d.h. senkrecht zur einer Längsachse 46 ist die Konzentration des Brennstoffes ungefähr gleich groß.The combustion instabilities result from a distribution of the fuel concentration 58 according to the prior art. In the radial direction 55, i. perpendicular to a longitudinal axis 46, the concentration of the fuel is approximately equal.

Der Betriebsbereich wird erfindungsgemäß erweitert, dadurch, dass ein Abströmwinkel α eines Mediums, d.h. der Winkel zwischen resultierender Geschwindigkeit und Umfangsgeschwindigkeit (Fig. 5), bspw. des Luft- 4 /Brennstoff- 7 Gemisches, in einer radialen Richtung 55 von einem maximalen Wert zu einem minimalen Wert von innen nach außen abnimmt. Dies geschieht durch eine Verwindung der Drallschaufel 16 wie in Figur 4 beschrieben.The operating range is extended according to the invention, in that an outflow angle α of a medium, ie the angle between resulting speed and peripheral speed ( Fig. 5 ), for example of the air / fuel mixture 7, in a radial direction 55 from a maximum value to a minimum Value decreases from the inside out. This is done by a twist of the swirl blade 16 as in FIG. 4 described.

Der Abströmwinkel α ist auch der Winkel zwischen der Strömungsrichtung des im Kanal strömenden Mediums (Luft, Sauerstoff, Brennstoff, Gemische davon) und einer Ebene, deren Normale die Brennerlängsachse 46 ist.The outflow angle α is also the angle between the flow direction of the medium flowing in the channel (air, oxygen, fuel, mixtures thereof) and a plane whose normal is the burner longitudinal axis 46.

Durch eine erfindungsgemäße zusätzliche Verteilung 52 für die Brennstoffkonzentration, die in radialer Richtung 55 zu zumindest einem Zeitpunkt während des Betriebes des Brenners 1 nicht konstant ist, wird die Stärke der Verbrennungsschwingungen reduziert. Auch auf diese Weise kann der Betriebsbereich für den Brenner 1 erweitert werden.By means of an additional fuel concentration distribution 52 according to the invention, which is not constant in the radial direction 55 at least at a point in time during the operation of the burner 1, the intensity of the combustion oscillations is reduced. In this way, the operating range for the burner 1 can be extended.

Die Brennstoffkonzentration verändert sich bspw. in radialer Richtung 55 gesehen ausgehend von der Mitte, d.h. von der Brennerlängsachse 46, nach außen, insbesondere nimmt die Brennstoffkonzentration bspw. linear ab oder zu.The fuel concentration changes, for example, in the radial direction 55 as viewed from the center, i. from the burner longitudinal axis 46, to the outside, in particular, the fuel concentration, for example, decreases linearly or to.

Es kann auch eine nichtlineare Ab- oder Zunahme vorliegen. Figur 3 zeigt eine Drallschaufel 16, mit der dies realisiert werden kann.There may also be a non-linear decrease or increase. FIG. 3 shows a swirl blade 16, with which this can be realized.

Figur 3 zeigt eine Drallschaufel 16 für einen Brenner. Die Drallschaufel 16 weist eine Anströmkante 67 und eine Abströmkante 70 auf. Im Kanal 13 strömt das Medium in Strömungsrichtung 88 zuerst an der Anströmkante 67 und dann an der Abströmkante 70 vorbei. FIG. 3 shows a swirl blade 16 for a burner. The swirl blade 16 has a leading edge 67 and a trailing edge 70. In the channel 13, the medium flows in the flow direction 88 first past the leading edge 67 and then past the trailing edge 70.

Im Bereich der Anströmkante 67 ist ein Kern 73 vorhanden, in dem eine Zufuhr 64 für Brennstoff 7 vorhanden ist. Die Zufuhr 64 ist beispielsweise ein Sackloch. In radialer Richtung 55 gesehen, parallel zur Abströmkante 70, sind in der Zufuhr 64 Löcher vorhanden, die die Brennstoffdüsen 31 darstellen. Durch diese Brennstoffdüsen 31 gelangt der Brennstoff 7 in den Kanal 13. Die Durchmesser der Löcher der Brennstoffdüsen 31 der im Brenner eingebauten Drallschaufel 1 verändern sich in radialer Richtung 55 entsprechend der Konzentrationsverteilung 52 und nimmt bspw. in radialer Richtung 55 von innen nach außen gesehen ab.In the region of the leading edge 67, a core 73 is present, in which a feed 64 for fuel 7 is present. The feeder 64 is, for example, a blind hole. Seen in the radial direction 55, parallel to the trailing edge 70, 64 holes are present in the supply, which constitute the fuel nozzles 31. Through these fuel nozzles 31, the fuel 7 enters the channel 13. The diameter of the holes of the fuel nozzles 31 of the built-in burner swirl blade 1 change in the radial direction 55 according to the concentration distribution 52 and takes, for example. In the radial direction 55 seen from the inside outwards.

Das Medium, das an der Drallschaufel 16 vorbeiströmt, erfährt einen Abströmwinkel α.The medium, which flows past the swirl blade 16, experiences an outflow angle α.

Figur 4 zeigt eine Drallschaufel 16 für einen erfindungsgemäßen Brenner 1. FIG. 4 shows a swirl blade 16 for a burner 1 according to the invention.

Die Drallschaufel 16 ist bspw. bezüglich der Größe und Verteilung der Brennstoffdüsen 31 wie die Drallschaufel in Figur 3 ausgebildet.The swirl blade 16 is, for example, with respect to the size and distribution of the fuel nozzles 31 as the swirl blade in FIG. 3 educated.

Darüber hinaus ist das Schaufelblatt 61 um eine Windungsachse 76 noch gewunden.In addition, the airfoil 61 is still wound around a winding axis 76.

Die Windungsachse 76 bildet mit der Strömungsrichtung 88 einen von null verschiedenen Schnittwinkel und liegt insbesondere bei 90°.The winding axis 76 forms with the flow direction 88 a non-zero cutting angle and is in particular at 90 °.

Ein Gas oder ein Brennstoff-Luftgemisch, das an der Drallschaufel 16 von der Anströmkante 67 zur Abströmkante 70 strömt, erfährt in radialer Richtung 55 gesehen verschiedene Abströmwinkel α, d.h. an einem Ende der Drallschaufel 16 im Bereich der Abströmkante 70 wird ein anderer Abströmwinkel α1 erzeugt als an dem anderen Ende, einem Abströmwinkel α2 (ungleich α1), in Richtung einer Längsachse der Zufuhr 64 betrachtet. Insbesondere nimmt der Abströmwinkel α linear ab. Es kann auch eine nichtlineare Zu- oder Abnahme vorliegen.A gas or a fuel-air mixture, which flows at the swirl blade 16 from the leading edge 67 to the outflow edge 70, experiences in the radial direction 55 different outflow angles α, i. At one end of the swirl blade 16 in the region of the outflow edge 70, a different outflow angle α1 is generated than at the other end, an outflow angle α2 (not equal to α1), viewed in the direction of a longitudinal axis of the feed 64. In particular, the outflow angle α decreases linearly. There may also be a non-linear increase or decrease.

Diese Verteilung in radialer Richtung 55 des Abströmwinkels α unterdrückt ebenso Verbrennungsinstabilitäten, so dass der Betriebsbereich für den Brenner 1 erweitert wird.This distribution in the radial direction 55 of the outflow angle α also suppresses combustion instabilities, so that the operating range for the burner 1 is widened.

Im Kanal 13 bildet das strömende Medium an der Drallschaufel 16 mit der Strömungsrichtung 88 in dem Kanal 13 den Abströmwinkel α.In the channel 13, the flowing medium forms at the swirl blade 16 with the flow direction 88 in the channel 13 the outflow angle α.

Die Drallschaufel 16 ist nach der Erfindung verwunden und kann auch verschiedene Durchmesser für die Brennstoffdüsen aufweisen.The swirl blade 16 is wound according to the invention and may also have different diameters for the fuel nozzles.

Figur 5 zeigt die Anordnung der verschiedenen Strömungsvektoren des in dem Kanal 13 strömenden Gases. Der Vektor 79 stellt die meridionale Geschwindigkeitskomponente dar. Der Vektor 82 stellt die Umfangsgeschwindigkeit dar, so dass sich eine resultierender Geschwindigkeitssektor 85 ergibt. Der Winkel zwischen der resultierenden Geschwindigkeit 85 und der Umfangsgeschwindigkeit 82 stellt den Abströmwinkel α dar. Der Winkel 90°- α ist der komplementäre Winkel. Der Abströmwinkel α ist auch der Winkel zwischen der Strömungsrichtung des strömenden Mediums und einer Ebene, die senkrecht zur Brennerlängsachse 46 verläuft. FIG. 5 shows the arrangement of the various flow vectors of the gas flowing in the channel 13. The vector 79 represents the meridional velocity component. The vector 82 represents the peripheral velocity, resulting in a resulting velocity sector 85. The angle between the resulting speed 85 and the peripheral speed 82 represents the outflow angle α. The angle 90 ° -α is the complementary angle. The outflow angle α is also the angle between the flow direction of the flowing medium and a plane which is perpendicular to the burner longitudinal axis 46.

Claims (8)

  1. Burner (1),
    wherein air and/or oxygen (4) is supplied which flows in a flow direction (88), wherein the burner (1) has a channel (13) in which a medium flows, wherein at least one swirl blade (16) is disposed in the channel (13), wherein the swirl blade (16) has a bladed disk (61) which is wound around a winding axis (76) such that the gas flowing past the swirl blade (16) in the flow direction (88) along an edge of the bladed disk (61) which forms an intersecting angle not equal to zero with the flow direction (88) has different outflow angles (α), so that the air and/or oxygen (4) have a distribution of an outflow angle in a plane perpendicular to the flow direction (88), and the distribution of the outflow angle is not constant in order to avoid combustion instabilities during operation of the burner (1), wherein the burner (1) has a burner longitudinal axis (46), which represents the interior area of the burner (1), wherein the burner (1) has a radial direction (55) disposed perpendicularly to the burner longitudinal axis (46),
    wherein the outflow angle (α) between its flow direction (88) and a plane perpendicular to the burner longitudinal axis (46) of a gas flowing past the swirl blade (16) has different outflow angles (α) in the radial direction (55) on the swirl blade (16), characterised in that the outflow angle (α) decreases in the radial direction (55) from the interior to the exterior.
  2. Burner according to claim 1,
    characterised in that fuel (7) can be supplied into the channel (13) via at least one fuel nozzle (31) in the swirl blade (16), that the swirl blade (16) has fuel nozzles (31) whose diameters vary, with the result that the concentration distribution (52) of the fuel (7) is not constant and varies in the radial direction (55).
  3. Burner according to claim 2,
    characterised in that the diameter of the fuel nozzles (31) of the installed swirl blade (16) decreases in the radial direction (55) from the interior to the exterior, so that the concentration distribution (52) of the fuel (7) varies from the interior to the exterior.
  4. Burner according to claim 1,
    characterised in that
    the fuel (7) or the air or the oxygen (4) can be supplied to the channel (13), and
    the channel (13) is embodied annularly around the burner longitudinal axis (46).
  5. Burner according to claim 4,
    characterised in that a fuel-gas mixture flows in the channel (13).
  6. Burner according to claim 1,
    characterised in that the burner (1) is a gas turbine burner.
  7. Burner according to claim 1,
    characterised in that the burner (1) has a diffusion or pilot burner (43).
  8. Burner according to claim 1,
    characterised in that the burner (1) is a premix burner.
EP03794901.3A 2002-09-02 2003-08-20 Gas turbine burner Expired - Lifetime EP1534997B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03794901.3A EP1534997B1 (en) 2002-09-02 2003-08-20 Gas turbine burner

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02019530A EP1394471A1 (en) 2002-09-02 2002-09-02 Burner
EP02019530 2002-09-02
PCT/EP2003/009222 WO2004025183A2 (en) 2002-09-02 2003-08-20 Burner
EP03794901.3A EP1534997B1 (en) 2002-09-02 2003-08-20 Gas turbine burner

Publications (2)

Publication Number Publication Date
EP1534997A2 EP1534997A2 (en) 2005-06-01
EP1534997B1 true EP1534997B1 (en) 2015-07-29

Family

ID=31197882

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02019530A Withdrawn EP1394471A1 (en) 2002-09-02 2002-09-02 Burner
EP03794901.3A Expired - Lifetime EP1534997B1 (en) 2002-09-02 2003-08-20 Gas turbine burner

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP02019530A Withdrawn EP1394471A1 (en) 2002-09-02 2002-09-02 Burner

Country Status (6)

Country Link
US (1) US7753677B2 (en)
EP (2) EP1394471A1 (en)
JP (2) JP4369370B2 (en)
CN (1) CN100432531C (en)
ES (1) ES2550096T3 (en)
WO (1) WO2004025183A2 (en)

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Also Published As

Publication number Publication date
EP1534997A2 (en) 2005-06-01
WO2004025183A3 (en) 2005-01-20
CN100432531C (en) 2008-11-12
CN1678871A (en) 2005-10-05
EP1394471A1 (en) 2004-03-03
US7753677B2 (en) 2010-07-13
JP4369370B2 (en) 2009-11-18
JP2008256357A (en) 2008-10-23
WO2004025183A2 (en) 2004-03-25
US20060035188A1 (en) 2006-02-16
JP4841587B2 (en) 2011-12-21
ES2550096T3 (en) 2015-11-04
JP2006507466A (en) 2006-03-02

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