EP1534997A2 - Burner - Google Patents

Burner

Info

Publication number
EP1534997A2
EP1534997A2 EP03794901A EP03794901A EP1534997A2 EP 1534997 A2 EP1534997 A2 EP 1534997A2 EP 03794901 A EP03794901 A EP 03794901A EP 03794901 A EP03794901 A EP 03794901A EP 1534997 A2 EP1534997 A2 EP 1534997A2
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
longitudinal axis
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.)
Granted
Application number
EP03794901A
Other languages
German (de)
French (fr)
Other versions
EP1534997B1 (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
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP03794901.3A priority Critical patent/EP1534997B1/en
Publication of EP1534997A2 publication Critical patent/EP1534997A2/en
Application granted granted Critical
Publication of EP1534997B1 publication Critical patent/EP1534997B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 claims 1 and 2.
  • Such combustion instabilities can be suppressed actively, for example by increasing the power of the pilot flame, or passively, for example by resonators.
  • FIG. 2 shows an enlarged detail from FIG. 1,
  • FIG. 3 shows a swirl vane for a burner designed according to the invention
  • FIG. 4 shows a swirl vane for a burner designed according to the invention
  • Figure 5 velocity vectors of a flowing fuel air-gas mixture
  • 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.
  • a diffusion or pilot burner 43 is arranged centrally along the longitudinal axis 46 of the burner. In the premix mode, the pilot burner 43 is operated to support the burner 1.
  • fuel 7 and / or air 4 is fed to a premixing section 10 and / or a combustion chamber 19 via a channel 13 (FIG. 6) that is annular, for example, to the longitudinal axis 46.
  • a channel 13 annular, for example, to the longitudinal axis 46.
  • oxygen or another gas can also be supplied, which together with fuel 7 results in a combustible fuel-gas mixture.
  • air 4 is first supplied to channel 13 and then fuel 7.
  • the air 4 flows in the channel 13, for example, at least on one
  • the swirl blades 16 are arranged, for example, in a ring shape, in particular equidistantly, around the longitudinal axis 46 of the burner (FIG. 6).
  • the air 4 and the fuel 7 mix in the premixing section 10, which is indicated by dashed lines.
  • FIG. 2 shows the radial end 49 of the diffusion / pilot burner 43 with the annular channel 13.
  • the fuel 7 is fed to the channel 13 via at least two fuel nozzles 31 and flows there in a flow direction 88.
  • the fuel is preferably supplied 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.
  • the concentration of the fuel is approximately the same.
  • the operating range for burner 1 can thus be expanded.
  • the fuel concentration changes, for example, in a radial direction
  • Fuel concentration for example, linearly from or to.
  • FIG. 3 shows a swirl vane 16 with which this can be achieved.
  • the operating range can also be expanded if a discharge angle ⁇ of a medium, ie the angle between the resulting speed and peripheral speed (FIG. 5), for example the air / fuel / 7 mixture, has a distribution similar to the concentration of the fuel 7 has, ie seen from the burner longitudinal axis 46, the outflow angle ⁇ decreases, for example, in a radial direction 55 from a maximum value to a minimum value or vice versa. This is done, for example, by twisting the swirl blade 16 as described in FIG. 4.
  • 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.
  • the distribution 52 of the fuel concentration and the outflow angle ⁇ can also be combined with one another in order to expand and improve the operating range of the burner 1.
  • FIG. 3 shows a swirl vane 16 for a burner 1 according to the invention.
  • the swirl vane 16 has a leading edge 67 and a trailing edge 70.
  • the medium flows in in channel 13
  • Flow direction 88 first past the leading edge 67 and then past the trailing edge 70.
  • FIG. 4 shows a further swirl vane 16 for a burner 1 according to the invention.
  • the swirl vane 16 is designed, for example, with respect to the size and distribution of the fuel nozzles 31, like the swirl vane in FIG. 3.
  • the airfoil 61 can still be wound around a winding axis 76.
  • the winding axis 76 forms a non-zero cutting angle with the flow direction 88 and is in particular 90 °.
  • ⁇ 1 At one end of the swirl vane 16 in the region of the trailing edge 70, a different outflow angle ⁇ 1 is generated than at the other end, an outflow angle ⁇ 2 (not equal to ⁇ l), 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 ⁇ likewise suppresses combustion instabilities, so that the operating range for the burner 1 is expanded.
  • the flowing medium on the swirl vane 16 with the flow direction 88 in the channel 13 forms the outflow angle ⁇ .
  • the swirl vane 16 can be both twisted and have different diameters for the fuel nozzles.
  • FIG. 5 shows the arrangement of the different flow vectors of the gas flowing in the channel 13.
  • the vector 79 represents the meridional speed component.
  • the vector 82 represents the peripheral speed, so that a resulting speed sector 85 results.
  • 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 direction of flow of the flowing medium and a plane which is perpendicular to the longitudinal axis 46 of the burner.

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)

Abstract

Burners in prior art exhibit combustion instabilities in certain operation ranges. The operating range of burners is restricted by said instabilities. In an inventive burner (1), the combustible (7) has a concentration distribution, whereby the concentration of the combustible (7) reduces in a radial direction (55) from the interior to the exterior.

Description

Brenner burner
Die Erfindung betrifft einen Brenner gemäß dem Oberbegriff des Anspruchs 1 und 2.The invention relates to a burner according to the preamble of claims 1 and 2.
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 vibrations.
Solche Verbrennungsinstabilitäten können aktiv, beispielsweise durch Erhöhung der Leistung der Pilotflamme, oder passiv, beispielsweise durch Resonatoren, unterdrückt werden.Such combustion instabilities can be suppressed actively, for example by increasing the power of the pilot flame, or passively, for example by resonators.
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 show a burner in which a stable area for the combustion is expanded in a simple manner.
Die Aufgabe wird gelöst durch einen Brenner gemäß Anspruch 1 und 2. Weitere vorteilhafte Ausgestaltungen des Brenners sind in den Unteransprüchen aufgelistet.The object is achieved by a burner according to claims 1 and 2. Further advantageous refinements of the burner are listed in the subclaims.
Es zeigenShow it
Figur 1 einen Brenner,1 shows a burner,
Figur 2 einen vergrößerten Ausschnitt aus Figur 1,FIG. 2 shows an enlarged detail from FIG. 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, und3 shows a swirl vane for a burner designed according to the invention, FIG. 4 shows a swirl vane for a burner designed according to the invention, Figure 5 velocity vectors of a flowing fuel air-gas mixture, and
Figur 6 einen Schnitt entlang der Linie VI-VI der Figur 2.6 shows 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. For example, a diffusion or pilot burner 43 is arranged centrally along the longitudinal axis 46 of the burner. In the premix mode, 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 . Die Luft 4 strömt im Kanal 13 bspw. zumindest an einerAt a radial end 49 of the diffusion burner 43, fuel 7 and / or air 4 is fed to a premixing section 10 and / or a combustion chamber 19 via a channel 13 (FIG. 6) that is annular, for example, to the longitudinal axis 46. Instead of air, oxygen or another gas can also be supplied, which together with fuel 7 results in a combustible fuel-gas mixture. For example, air 4 is first supplied to channel 13 and then fuel 7. The air 4 flows in the channel 13, for example, at least on one
Drallschaufel 16 vorbei, wobei die Drallschaufel 16 bspw. Brennstoff 7 dem Kanal 13 zuführt.Swirl vane 16 past, the swirl vane 16 supplying fuel 7 to the channel 13, for example.
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 blades 16 are arranged, for example, in a ring shape, in particular equidistantly, around the longitudinal axis 46 of the burner (FIG. 6). The air 4 and the fuel 7 mix in the premixing section 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. Figur 2 zeigt das radiale Ende 49 des Diffusions- /Pilotbrenners 43 mit dem ringförmigen Kanal 13. Der Brennstoff 7 wird über zumindest zwei Brennstoffdüsen 31 dem Kanal 13 zugeführt und strömt dort in einer Strömungsrichtung 88.However, the fuel 7 and then the air 4 can also be supplied in the channel 13 first. FIG. 2 shows the radial end 49 of the diffusion / pilot burner 43 with the annular channel 13. The fuel 7 is fed 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.The fuel is preferably supplied 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.e. perpendicular to a longitudinal axis 46, the concentration of the fuel is approximately the same.
Durch eine erfindungsgemäße Verteilung 52 für dieBy a distribution 52 according to the invention for the
Brennstoffkonzentration, die in radialer Richtung 55 zu zumindest einem Zeitpunkt während des Betriebes des BrennersFuel concentration that is in the radial direction 55 at least at one time during the operation of the burner
1 nicht konstant ist, werden die Stärke der1 is not constant, the strength of the
Verbrennungsschwingungen reduziert .Burning vibrations reduced.
Somit kann der Betriebsbereich für den Brenner 1 erweitert werden. Die Brennstoffkonzentration verändert sich bspw. in radialerThe operating range for burner 1 can thus be expanded. The fuel concentration changes, for example, in a radial direction
Richtung 55 gesehen ausgehend von der Mitte, d.h. von derDirection 55 seen from the center, i.e. of the
Brennerlängsachse 46, nach außen, insbesondere nimmt dieBurner longitudinal axis 46, outwards, in particular takes the
Brennstoffkonzentration bspw. linear ab oder zu.Fuel concentration, for example, linearly from 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 increase or decrease. FIG. 3 shows a swirl vane 16 with which this can be achieved.
Der Betriebsbereich kann auch erweitert werden, wenn ein Abströmwinkel α eines Mediums, d.h. der Winkel zwischen resultierender Geschwindigkeit und Umfangsgeschwindigkeit (Fig. 5), bspw. des Luft- 4 /Brennstoff- 7 Gemisches, eine ähnliche Verteilung wie die Konzentration des Brennstoffes 7 aufweist, d.h. von der Brennerlängsachse 46 aus gesehen, nimmt der Abströmwinkel α bspw. in einer radialen Richtung 55 von einem maximalen Wert zu einem minimalen Wert ab oder umgekehrt. Dies geschieht bspw. durch eine Verwindung der Drallschaufel 16 wie in Figur 4 beschrieben. 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 operating range can also be expanded if a discharge angle α of a medium, ie the angle between the resulting speed and peripheral speed (FIG. 5), for example the air / fuel / 7 mixture, has a distribution similar to the concentration of the fuel 7 has, ie seen from the burner longitudinal axis 46, the outflow angle α decreases, for example, in a radial direction 55 from a maximum value to a minimum value or vice versa. This is done, for example, by twisting the swirl blade 16 as described in FIG. 4. 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.
Es kann auch gleichzeitig die Verteilung 52 der Brennstoffkonzentration und des Abströmwinkels α miteinander kombiniert werden, um den Betriebsbereich des Brenners 1 zu erweitern und verbessern.The distribution 52 of the fuel concentration and the outflow angle α can also be combined with one another in order to expand and improve the operating range of the burner 1.
Figur 3 zeigt eine Drallschaufel 16 für einen erfindungsgemäßen Brenner 1.FIG. 3 shows a swirl vane 16 for a burner 1 according to the invention.
Die Drallschaufel 16 weist eine Anströmkante 67 und eine Abströmkante 70 auf. Im Kanal 13 strömt das Medium inThe swirl vane 16 has a leading edge 67 and a trailing edge 70. The medium flows in in channel 13
Strömungsrichtung 88 zuerst an der Anströmkante 67 und dann an der Abströmkante 70 vorbei.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. Das Medium, das an der Drallschaufel 16 vorbeiströmt, erfährt einen Abströmwinkel α. Figur 4 zeigt eine weitere Drallschaufel 16 für einen erfindungsgemäßen Brenner 1.In the area of the leading edge 67 there is a core 73 in which there is a supply 64 for fuel 7. The feed 64 is, for example, a blind hole. Viewed in the radial direction 55, parallel to the trailing edge 70, there are 64 holes in the feed, which represent the fuel nozzles 31. The fuel 7 enters the channel 13 through these fuel nozzles 31. The diameter of the holes in the fuel nozzles 31 of the swirl vane 1 installed in the burner change in the radial direction 55 in accordance with the concentration distribution 52 and decreases, for example, in the radial direction 55 as seen from the inside out , The medium that flows past the swirl vane 16 experiences an outflow angle α. FIG. 4 shows a further swirl vane 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 vane 16 is designed, for example, with respect to the size and distribution of the fuel nozzles 31, like the swirl vane in FIG. 3.
Darüber hinaus kann das Schaufelblatt 61 um eine Windungsachse 76 noch gewunden sein.In addition, the airfoil 61 can still be 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 a non-zero cutting angle with the flow direction 88 and is in particular 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 αl erzeugt als an dem anderen Ende, einem Abströmwinkel α2 (ungleich αl) , 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 on the swirl vane 16 from the leading edge 67 to the trailing edge 70 experiences different outflow angles α, i.e. in radial direction 55. At one end of the swirl vane 16 in the region of the trailing edge 70, a different outflow angle α1 is generated than at the other end, an outflow angle α2 (not equal to αl), 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 likewise suppresses combustion instabilities, so that the operating range for the burner 1 is expanded.
Im Kanal 13 bildet das strömende Medium an der Drallschaufel 16 mit der Strömungsrichtung 88 in dem Kanal 13 den Abströmwinkel α. Die Drallschaufel 16 kann sowohl verwunden sein als auch verschiedene Durchmesser für die Brennstoffdüsen aufweisen.In the channel 13, the flowing medium on the swirl vane 16 with the flow direction 88 in the channel 13 forms the outflow angle α. The swirl vane 16 can be both twisted and 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 .FIG. 5 shows the arrangement of the different flow vectors of the gas flowing in the channel 13. The vector 79 represents the meridional speed component. The vector 82 represents the peripheral speed, so that a resulting speed sector 85 results. 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.
Der Abströmwinkel α ist auch der Winkel zwischen der Strömungsrichtung des strömenden Mediums und einer Ebene, die senkrecht zur Brennerlängsachse 46 verläuft. The outflow angle α is also the angle between the direction of flow of the flowing medium and a plane which is perpendicular to the longitudinal axis 46 of the burner.

Claims

Patentansprüche claims
1. Brenner (1) , bei dem zumindest ein Brennstoff (7) zugeführt wird, der in einer Strömungsrichtung (88) strömt, wobei der Brennstoff (7) in einer Ebene senkrecht zur Strömungsrichtung (88) eine Konzentrationsverteilung (58) aufweist,1. burner (1) in which at least one fuel (7) is supplied which flows in a flow direction (88), the fuel (7) having a concentration distribution (58) in a plane perpendicular to the flow direction (88),
d a d u r c h g e k e n n z e i c h n e t, dassd a d u r c h g e k e n n z e i c h n e t that
die Konzentrationsverteilung (52) nicht konstant ist, um Verbrennungsinstabilitäten beim Betrieb des Brenners (1) zu vermeiden.the concentration distribution (52) is not constant in order to avoid combustion instabilities when operating the burner (1).
2. Brenner (1) , bei dem Luft und/oder Sauerstoff (4) zugeführt wird, das in einer Strömungsrichtung (88) strömt, wobei die Luft und/oder der Sauerstoff (4) in einer Ebene senkrecht zur Strömungsrichtung (88) eine Verteilung eines Abströmwinkels aufweist,2. Burner (1), in which air and / or oxygen (4) is supplied, which flows in a direction of flow (88), the air and / or oxygen (4) in a plane perpendicular to the direction of flow (88) Distribution of an outflow angle,
d a d u r c h g e k e n n z e i c h n e t, dassd a d u r c h g e k e n n z e i c h n e t that
die Verteilung des Abströmwinkels nicht konstant ist, um Verbrennungsinstabilitäten beim Betrieb des Brenners (1) zu vermeiden.the distribution of the outflow angle is not constant in order to avoid combustion instabilities when operating the burner (1).
3. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t,3. Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, dass der Brenner (1) eine zur Brennerlängsachse (46) senkrecht angeordnete radiale Richtung (55) aufweist, und dass sich die Konzentrationsverteilung (52) des Brennstoffs (7) in der radialen Richtung (55) verändert. that the burner (1) has a burner longitudinal axis (46), that the burner (1) has a radial direction (55) arranged perpendicular to the burner longitudinal axis (46), and that the concentration distribution (52) of the fuel (7) is in the radial direction Direction (55) changed.
4. Brenner nach Anspruch 3, d a d u r c h g e k e n n z e i c h n e t,4. Burner according to claim 3, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, die den inneren Bereich des Brenners (1) darstellt, und dass die Konzentrationsverteilung (52) des Brennstoffs (7) von innen nach außen abnimmt.that the burner (1) has a burner longitudinal axis (46) which represents the inner region of the burner (1) and that the concentration distribution (52) of the fuel (7) decreases from the inside to the outside.
5. Brenner nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t,5. Burner according to claim 1, d a d u r c h g e k e n n z e i c h n e t,
dass der Brennstoff (7) in einem Kanal (13) zuführbar ist, und dass Luft (4) und/oder Sauerstoff in den Kanal (13) zuführbar ist.that the fuel (7) can be fed in a channel (13) and that air (4) and / or oxygen can be fed into the channel (13).
6. Brenner nach Anspruch 2, d a d u r c h g e k e n n z e i c h n e t,6. Burner according to claim 2, d a d u r c h g e k e n n z e i c h n e t,
dass die Luft und/oder Sauerstoff (4) in einem Kanal (13) zuführbar ist, und dass Brennstoff (7) in den Kanal (13) zuführbar ist.that the air and / or oxygen (4) can be supplied in a channel (13) and that fuel (7) can be supplied in the channel (13).
7. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t,7. Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, dass der Brennstoff (7) oder die Luft oder der Sauerstoffthat the burner (1) has a burner longitudinal axis (46), that the fuel (7) or the air or the oxygen
(4) einem Kanal (13) zuführbar ist, und dass der Kanal (13) ringförmig um die Brennerlängsachse(4) a channel (13) can be fed, and that the channel (13) is annular around the longitudinal axis of the burner
(46) ausgebildet ist. (46) is formed.
. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t,, Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, dass der Brenner (1) eine zur Brennerlängsachse (46) senkrecht angeordnete radiale Richtung (55) aufweist, dass der Brenner (1) einen Kanal (13) aufweist, in dem ein Medium strömt, und dass das strömende Medium einen Abströmwinkel (α) zwischen seiner Strömungsrichtung und einer Ebene senkrecht zur Brennerlängsachse (46) aufweist, der sich in radialer Richtung (55) verändert.that the burner (1) has a burner longitudinal axis (46), that the burner (1) has a radial direction (55) arranged perpendicular to the burner longitudinal axis (46), that the burner (1) has a channel (13) in which a Medium flows, and that the flowing medium has an outflow angle (α) between its flow direction and a plane perpendicular to the longitudinal axis (46) of the burner, which changes in the radial direction (55).
9. Brenner nach Anspruch 8, d a d u r c h g e k e n n z e i c h n e t,9. Burner according to claim 8, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, die den inneren Bereich des Brenners (1) darstellt, und dass der Abströmwinkel (α) in radialer Richtung (55) von innen nach aussen abnimmt.that the burner (1) has a burner longitudinal axis (46) which represents the inner region of the burner (1), and that the outflow angle (α) decreases in the radial direction (55) from the inside to the outside.
10. Brenner nach Anspruch 5 oder 6, d a d u r c h g e k e n n z e i c h n e t, dass10. Burner according to claim 5 or 6, d a d u r c h g e k e n n z e i c h n e t that
in dem Kanal (13) ein Brennstoff -Gasgemisch strömt.a fuel-gas mixture flows in the channel (13).
11. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, dass11. Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t that
der Brenner (1) ein Gasturbinenbrenner ist. the burner (1) is a gas turbine burner.
12. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, dass12. Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t that
der Brenner (1) einen Diffusions- oder Pilotbrenner (43) aufweist .the burner (1) has a diffusion or pilot burner (43).
13. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, dass13. Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t that
der Brenner (1) ein Vormischbrenner ist.the burner (1) is a premix burner.
14. Brenner nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t,14. Burner according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) einen Kanal (13) aufweist, und dass in dem Kanal (13) zumindest eine Drallschaufel (16) angeordnet ist.that the burner (1) has a channel (13) and that at least one swirl blade (16) is arranged in the channel (13).
15. Brenner nach Anspruch 14, d a d u r c h g e k e n n z e i c h n e t, dass15. Burner according to claim 14, d a d u r c h g e k e n n z e i c h n e t that
der Brennstoff (7) über zumindest eine Brennstoffdüse (31) in der Drallschaufel (16) in den Kanal (13) zuführbar ist.the fuel (7) can be fed into the channel (13) via at least one fuel nozzle (31) in the swirl vane (16).
16. Brenner nach Anspruch 15, d a d u r c h g e k e n n z e i c h n e t,16. Burner according to claim 15, d a d u r c h g e k e n n z e i c h n e t,
dass die Drallschaufel (16) Brennstoffdüsen (31) aufweist, deren Durchmesser unterschiedlich ist, so dass die Konzentrationsverteilung (52) des Brennstoffs (7) nicht konstant ist. that the swirl vane (16) has fuel nozzles (31), the diameter of which is different, so that the concentration distribution (52) of the fuel (7) is not constant.
17. Brenner nach Anspruch 16, d a d u r c h g e k e n n z e i c h n e t,17. Burner according to claim 16, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, die den inneren Bereich des Brenners (1) darstellt, dass der Brenner (1) eine zur Brennerlängsachse (46) senkrecht angeordnete radiale Richtung (55) aufweist, und dass der Durchmesser der Brennstoffdüsen (31) der eingebauten Drallschaufel (16) in der radialen Richtung (55) von innen nach aussen abnimmt.that the burner (1) has a burner longitudinal axis (46) which represents the inner region of the burner (1), that the burner (1) has a radial direction (55) arranged perpendicular to the burner longitudinal axis (46), and that the diameter of the Fuel nozzles (31) of the installed swirl vane (16) decreases in the radial direction (55) from the inside to the outside.
18. Brenner (1) nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, dass18. Burner (1) according to claim 1 or 2, d a d u r c h g e k e n n z e i c h n e t that
der Brenner (1) zumindest eine Drallschaufel (16) aufweist, wobei die Drallschaufel (16) ein Schaufelblatt (61) aufweist, das um eine Windungsachse (76) verwunden ist, so dass das in der Strömungsrichtung (88) an derthe burner (1) has at least one swirl vane (16), the swirl vane (16) having an airfoil (61) which is twisted about a winding axis (76), so that in the flow direction (88) on the
Drallschaufel (16) vorbeiströmende Gas längs einer Kante des Schaufelblatts (61), die mit der Strömungsrichtung (88) einen von null verschiedenen Schnittwinkel aufweist, verschiedene Abströmwinkel (α) aufweist. Swirl vane (16) gas flowing past along an edge of the vane (61), which has a non-zero cutting angle with the flow direction (88), has different outflow angles (α).
9. Brenner (1) nach Anspruch 18, d a d u r c h g e k e n n z e i c h n e t,9. burner (1) according to claim 18, d a d u r c h g e k e n n z e i c h n e t,
dass der Brenner (1) eine Brennerlängsachse (46) aufweist, die den inneren Bereich des Brenners (1) darstellt, dass der Brenner (1) eine zur Brennerlängsachse (46) senkrecht angeordnete radiale Richtung (55) aufweist, dass der Abströmwinkel (α) eines an einer Drallschaufel (16) vorbeiströmenden Gases in radialer Richtung (55) an der Drallschaufel (16) verschiedene Abströmwinkel (α) aufweist, wobei der Abströmwinkel (α) in radialer Richtung (55) von innen nach außen abnimmt. that the burner (1) has a burner longitudinal axis (46) which represents the inner region of the burner (1), that the burner (1) has a radial direction (55) arranged perpendicular to the burner longitudinal axis (46), that the outflow angle (α ) of a gas flowing past a swirl vane (16) in the radial direction (55) at the swirl vane (16) has different outflow angles (α), the outflow angle (α) decreasing in the radial direction (55) from the inside to the outside.
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
EP02019530 2002-09-02
EP02019530A EP1394471A1 (en) 2002-09-02 2002-09-02 Burner
EP03794901.3A EP1534997B1 (en) 2002-09-02 2003-08-20 Gas turbine burner
PCT/EP2003/009222 WO2004025183A2 (en) 2002-09-02 2003-08-20 Burner

Publications (2)

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

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Family Applications (2)

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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

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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
JP4841587B2 (en) 2011-12-21
CN100432531C (en) 2008-11-12
WO2004025183A2 (en) 2004-03-25
EP1394471A1 (en) 2004-03-03
EP1534997B1 (en) 2015-07-29
WO2004025183A3 (en) 2005-01-20
CN1678871A (en) 2005-10-05
US7753677B2 (en) 2010-07-13
JP2008256357A (en) 2008-10-23
ES2550096T3 (en) 2015-11-04
JP2006507466A (en) 2006-03-02
JP4369370B2 (en) 2009-11-18
US20060035188A1 (en) 2006-02-16

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