EP1125087B1 - Burner assembly - Google Patents

Burner assembly Download PDF

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Publication number
EP1125087B1
EP1125087B1 EP99952393A EP99952393A EP1125087B1 EP 1125087 B1 EP1125087 B1 EP 1125087B1 EP 99952393 A EP99952393 A EP 99952393A EP 99952393 A EP99952393 A EP 99952393A EP 1125087 B1 EP1125087 B1 EP 1125087B1
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EP
European Patent Office
Prior art keywords
combustion chamber
burner
flow
outlet
combustion
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EP99952393A
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German (de)
French (fr)
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EP1125087A1 (en
Inventor
Carsten Tiemann
Martin Lenze
Manfred Lenz
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Siemens AG
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Siemens AG
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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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • 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 arrangement with a burner, which opens into a combustion chamber. In particular, it's about a burner assembly for a gas turbine.
  • thermoacoustic Exciting vibrations also called combustion oscillations become. These are not just an unwanted one Sound source, but may be too high mechanical Burdens of the combustion chamber lead.
  • thermoacoustic Vibration is actively damped by the fact that Injecting a fluid is the place of incineration Heat release fluctuation is controlled.
  • EP A 0 931 979 discloses a device for suppression of flame / pressure oscillations in a furnace in particular a gas turbine.
  • this device is a flame through a gas jacket flow of a higher flow rate enclosed.
  • a ring vortex formation prevented.
  • a screen is provided, which surrounds the gas outlet openings of the burner and runs at a distance around the burner, so that one with the Combustion chamber related flue gas recirculation area from the outlet of the gas jacket flow and thus the gas jacket flow is separated. It is also suggested Such devices in an annular combustion chamber of a gas turbine to use with every burner.
  • US-A 4,373,342 discloses a combustor chamber of a gas turbine engine.
  • the entrance area of the gas turbine combustor is provided with a screen which enters the combustion chamber protrudes. This screen reduces a Köhlstoffablagerung in the head of the combustion chamber and also reduces the smoke emissions.
  • the object of the invention is to provide a burner arrangement, in particular with regard to the avoidance of thermoacoustic Vibrations has a favorable behavior.
  • this object is achieved by a burner assembly with a variety of burners in a common Combustion chamber, with each burner at a mouth in a combustion chamber opens, with some of the burner the Each mouth at least partially by a in the combustion chamber protruding flow guide for guiding a the burner in the combustion chamber leaking fuel gas stream is formed.
  • the fuel gas stream may be a mixture of combustion air with e.g. Be oil or natural gas.
  • the flow guide serves the Guidance of emerging from the mouth fuel gas flow. This becomes the area of combustion of the fuel gas flow moved further into the combustion chamber inside.
  • the Flame shape of combustion affected.
  • the burner assembly i. the system of burner and Combustion chamber, acoustically detuned. This acoustic detuning prevents combustion vibrations or weakens them at least from.
  • For a variety of burners in a common Combustion chamber are not combustion oscillations predictable and therefore very difficult to control.
  • the complex system can be the plurality of burners in the common combustion chamber in simple way and efficiently detune acoustically so that Combustion vibrations possibly with low amplitude occur.
  • Flow guide is also a tear edge for vortex provided from the fuel gas stream. Through this vortex results a remindström capable for at least a portion of the Fuel gas stream. This has a favorable effect on stabilization the flame and a reduction in nitrogen oxide emissions out. The reduction of nitrogen oxide emissions results from a homogenization of the flame temperatures by the mixing vortex.
  • the flow guide is one along a Flow guide element axis directed hollow cylinder or hollow truncated cone. More preferably, the hollow cylinder or the end Hollow truncated cone on an imaginary top surface, wherein the Top surface not oriented perpendicular to the flow guide axis is. In other words: the hollow cylinder or the Hollow truncated cone ends on a bevelled top surface. Of the Fuel gas stream is thus at a long side of the hollow cylinder or hollow truncated cone over a longer distance than on a long side opposite short side.
  • the flow guide is about the Half of the estuary arranged around.
  • the natural gas flow on one side offered a contact area.
  • the Fuel gas flow deflected a little way to the open area This in turn has a shift of the location of the combustion result. This makes a particularly efficient one acoustic detuning and thus the suppression of a combustion vibration reached.
  • the flow guide is a sheet of a heat-resistant metal, preferably of a steel.
  • the combustion chamber is an annular combustion chamber of a Gas turbine.
  • a gas turbine especially in a Stationary gas turbine, it comes to a very large release of power when burning.
  • combustion oscillations not only can be annoying acoustically, but even mechanically harmful. A suppression of combustion vibrations is therefore of particular importance here.
  • the mouth has a mouth diameter and Flow guide along the element axis a longest Extension to, with the longest extension between a Sixth and half of the mouth diameter is long.
  • the value of the longest extent lies between one and ten centimeters.
  • FIG. 1 shows a longitudinal section through a partial view shown burner assembly 1.
  • a combustion chamber 11 On a combustion chamber wall. 9 a combustion chamber 11, not shown, is a burner 3 arranged.
  • the burner 3 is a hybrid burner, i. H. it can act as a diffusion burner or as a premix burner operate.
  • the burner 3 indicates as a premixing stage an annular channel 5.
  • the annular channel 5 surrounds concentrically a pilot burner 7.
  • a fuel-air mixture 14a led In the annular channel 5 is a fuel-air mixture 14a led. This unites with one Fuel-air mixture 14 b from the pilot burner 7 to a Fuel gas stream 14.
  • the fuel gas stream 14 emerges from a Mouth 13 along a mouth direction 15 from the burner 3 off.
  • the mouth 13 is of a hollow cylindrical Flow guide 17 surrounded.
  • the flow guide 17 ends at an imaginary top surface 16.
  • the flow guide 17 is directed along a flow guide axis 17b.
  • the top surface 16 is not perpendicular to Flow guiding element axis 17b oriented.
  • the flow guide 17 thus ends at an inclined top surface 16.
  • the flow guide 17 thereby has a long side 17c and a short side 17d.
  • the fuel gas flow 14 is on the long side 17c led over a slightly larger distance than on the short side 17d. This opens the fuel gas flow 14 towards the short side 17d.
  • This has a shift the combustion area perpendicular to the mouth direction 15 result.
  • By the mouth 13 surrounding flow guide 17 also results in such a shift of the Combustion area along the direction of the mouth 15.
  • the shape of the combustion area affected.
  • the displacement of the combustion area and the influence on the shape of the combustion area have the consequence that the acoustic system of burner 3 and combustion chamber 11 is acoustically detuned. Thereby a combustion vibration is avoided or
  • the flow guide 17 terminates at a tear-off edge 18.
  • An this tear-off edge 18 rupture vortex 20 from the fuel gas flow 14 off.
  • a sudström for fuel gas is generated.
  • FIG. 2 shows a burner assembly 1 in longitudinal section accordingly the burner assembly 1 of Figure 1.
  • the flow guide 17 is a hollow truncated cone executed.
  • the flow guide 17 expands ie in the direction of the fuel gas flow 14. Through this flow guide 17 will again be the place of burning of the Shifted fuel gas stream 14. Also the form of combustion is influenced by the flow guide 17. It will also achieved here that the acoustic system of burner. 3 and combustion chamber 11 is acoustically detuned. This has, like above, suppression of combustion vibrations result.
  • FIG 3 is a perspective and partially broken one Ring combustion chamber for a gas turbine shown.
  • the combustion chamber 11 is rotationally symmetrical about a combustion chamber axis 25 and has an outer wall 21 and an inner wall 23.
  • the outer wall 21 and the inner wall 23 enclose one annular combustion chamber 24.
  • the inner surface of the outer wall 21st and the outer surface of the inner wall 23 are refractory Interior lining 27 provided.
  • a plurality of burners. 3 arranged.
  • At some of the burners 3 are flow guide 17 arranged.
  • the flow guide 17 is the system of burners 3 and combustion chamber 11 acoustically detuned so that a Suppression of combustion vibrations results. This is especially with the high geometric complexity of a Ring combustion chamber with a variety of burners required because the acoustic properties of such an annular combustion chamber 11 are virtually unpredictable.

Abstract

The invention relates to a burner assembly (1) comprising a burner (3) which ends into a combustion chamber (11) in an area at least partially formed by a flow-guiding element (17) extending in the combustion chamber (11). The inventive burner assembly allows combustion vibrations to be avoided.

Description

Die Erfindung betrifft eine Brenneranordnung mit einem Brenner, der in eine Brennkammer mündet. Insbesondere geht es um eine Brenneranordnung für eine Gasturbine.The invention relates to a burner arrangement with a burner, which opens into a combustion chamber. In particular, it's about a burner assembly for a gas turbine.

In der DE 43 39 094 A1 ist ein Verfahren zur Dämpfung von thermoakustischen Schwingungen in der Brennkammer einer Gasturbine beschrieben. Bei der Verbrennung von Brennstoffen in der Brennkammer einer stationären Gasturbine, eines Flugzeugtriebwerks oder dergleichen kann es aufgrund der Verbrennungsvorgänge zu Instabilitäten oder Druckschwankungen kommen, die unter ungünstigen Verhältnissen thermoakustische Schwingungen anregen, die auch Verbrennungsschwingungen genannt werden. Diese stellen nicht nur eine unerwünschte Schallquelle dar, sondern können zu unzulässig hohen mechanischen Belastungen der Brennkammer führen. Eine solche thermoakustische Schwingung wird aktiv dadurch gedämpft, daß durch Eindüsen eines Fluides der Ort der mit der Verbrennung verbundenen Wärmefreisetzungsschwankung gesteuert wird.In DE 43 39 094 A1 discloses a method for damping of thermoacoustic oscillations in the combustion chamber of a gas turbine described. When burning fuels in the combustion chamber of a stationary gas turbine, an aircraft engine or the like may be due to the combustion processes come to instabilities or pressure fluctuations, under unfavorable conditions thermoacoustic Exciting vibrations, also called combustion oscillations become. These are not just an unwanted one Sound source, but may be too high mechanical Burdens of the combustion chamber lead. Such a thermoacoustic Vibration is actively damped by the fact that Injecting a fluid is the place of incineration Heat release fluctuation is controlled.

Die EP A 0 931 979 offenbart eine Vorrichtung zur Unterdrückung von Flammen-/Druckschwingungen bei einer Feuerung insbesondere einer Gasturbine. Bei dieser Vorrichtung wird eine Flamme durch eine Gasmantelströmung einer höheren Strömungsgeschwindigkeit umschlossen. Hierdurch wird eine Ringwirbelbildung unterbunden. Um für die Gasmantelströmung geringere Gasvolumina erreichen zu können, wird ein Schirm vorgesehen, der die Gasaustrittsöffnungen des Brenners umfängt und mit Abstand um den Brenner verläuft, so dass ein mit dem Brennraum in Verbindung stehender Rauchgas-Rezirkulationsbereich von dem Austrittsort der Gasmantelströmung und damit der Gasmantelströmung getrennt wird. Es wird auch vorgeschlagen, solche Vorrichtungen in einer Ringbrennkammer einer Gasturbine bei jedem Brenner zu verwenden.EP A 0 931 979 discloses a device for suppression of flame / pressure oscillations in a furnace in particular a gas turbine. In this device is a flame through a gas jacket flow of a higher flow rate enclosed. As a result, a ring vortex formation prevented. To lower for the gas jacket flow To reach gas volumes, a screen is provided, which surrounds the gas outlet openings of the burner and runs at a distance around the burner, so that one with the Combustion chamber related flue gas recirculation area from the outlet of the gas jacket flow and thus the gas jacket flow is separated. It is also suggested Such devices in an annular combustion chamber of a gas turbine to use with every burner.

Die US-A 4,373,342 offenbart eine Brennerkammer eines Gasturbinentriebwerks. Der Eintrittsbereich der Gasturbinenbrennkammer ist mit einem Schirm versehen, der in die Brennkammer hineinragt. Dieser Schirm reduziert eine Köhlenstoffablagerung im Kopfbereich der Brennkammer und reduziert ebenfalls die Rauchemissionen.US-A 4,373,342 discloses a combustor chamber of a gas turbine engine. The entrance area of the gas turbine combustor is provided with a screen which enters the combustion chamber protrudes. This screen reduces a Köhlstoffablagerung in the head of the combustion chamber and also reduces the smoke emissions.

Aufgabe der Erfindung ist es, eine Brenneranordnung anzugeben, die insbesondere hinsichtlich der Vermeidung thermoakustischer Schwingungen ein günstiges Verhalten aufweist.The object of the invention is to provide a burner arrangement, in particular with regard to the avoidance of thermoacoustic Vibrations has a favorable behavior.

Erfindungsgemäß wird diese Aufgabe gelöst durch eine Brenneranordnung mit einer Vielzahl von Brennern in einer gemeinsamen Brennkammer, wobei jeder Brenner an einer Mündung in eine Brennkammer mündet, wobei bei einigen der Brenner die Mündung jeweils zumindest teilweise durch ein in die Brennkammer ragendes Strömungsleitelement zur Führung eines aus dem Brenner in die Brennkammer austretenden Brenngasstromes gebildet ist.According to the invention this object is achieved by a burner assembly with a variety of burners in a common Combustion chamber, with each burner at a mouth in a combustion chamber opens, with some of the burner the Each mouth at least partially by a in the combustion chamber protruding flow guide for guiding a the burner in the combustion chamber leaking fuel gas stream is formed.

Der Brenngasstrom kann ein Gemisch aus Verbrennungsluft mit z.B. Öl oder Erdgas sein. Das Strömungsleitelement dient der Führung des aus der Mündung austretenden Brenngasstroms. Hierdurch wird das Gebiet der Verbrennung des Brenngasstroms weiter in die Brennkammer hinein verlagert. Außerdem wird die Flammenform der Verbrennung beeinflußt. Durch den Einfluß auf die Form und den Ort der Verbrennung bei einigen der Brenner wird die Brenneranordnung, d.h. das System aus Brenner und Brennkammer, akustisch verstimmt. Diese akustische Verstimmung verhindert Verbrennungsschwingungen oder schwächt diese zumindest ab. Bei einer Vielzahl von Brennern in einer gemeinsamen Brennkammer sind Verbrennungsschwingungen nicht vorhersagbar und damit besonders schwer kontrollierbar. Durch den Einsatz eines Strömungsleitelements an einem Brenner oder auch an mehreren Brennern läßt sich das komplexe System aus der Vielzahl von Brennern in der gemeinsamen Brennkammer in einfacher Weise und effizient akustisch so verstimmen, daß Verbrennungsschwingungen allenfalls noch mit geringer Amplitude auftreten. Durch das in die Brennkammer hineinragende Strömungsleitelement wird außerdem eine Abrißkante für Wirbel aus dem Brenngasstrom bereitgestellt. Durch diese Wirbel ergibt sich ein Rückströmgebiet für zumindest einen Teil des Brenngasstroms. Dies wirkt sich günstig auf eine Stabilisierung der Flamme und auf eine Reduzierung der Stickoxidemissionen aus. Die Reduzierung der Stickoxidemission resultiert aus einer Vergleichmäßigung der Flammtemperaturen durch die mischenden Wirbel.The fuel gas stream may be a mixture of combustion air with e.g. Be oil or natural gas. The flow guide serves the Guidance of emerging from the mouth fuel gas flow. This becomes the area of combustion of the fuel gas flow moved further into the combustion chamber inside. In addition, the Flame shape of combustion affected. By the influence on the shape and location of combustion in some of the burners the burner assembly, i. the system of burner and Combustion chamber, acoustically detuned. This acoustic detuning prevents combustion vibrations or weakens them at least from. For a variety of burners in a common Combustion chamber are not combustion oscillations predictable and therefore very difficult to control. By the use of a flow guide on a burner or even at several burners, the complex system can be the plurality of burners in the common combustion chamber in simple way and efficiently detune acoustically so that Combustion vibrations possibly with low amplitude occur. By the projecting into the combustion chamber Flow guide is also a tear edge for vortex provided from the fuel gas stream. Through this vortex results a Rückströmgebiet for at least a portion of the Fuel gas stream. This has a favorable effect on stabilization the flame and a reduction in nitrogen oxide emissions out. The reduction of nitrogen oxide emissions results from a homogenization of the flame temperatures by the mixing vortex.

Bevorzugt ist das Strömungsleitelement ein entlang einer Strömungsleitelementachse gerichteter Hohlzylinder oder Hohlkegelstumpf. Weiter bevorzugt enden der Hohlzylinder oder der Hohlkegelstumpf an einer gedachten Deckfläche, wobei die Deckfläche nicht senkrecht zur Strömungsleitelementachse orientiert ist. Mit anderen Worten: Der Hohlzylinder oder der Hohlkegelstumpf enden an einer abgeschrägten Deckfläche. Der Brenngasstrom wird somit an einer Langseite des Hohlzylinders oder Hohlkegelstumpfes über eine längere Strecke geführt als auf einer der Langseite gegenüberliegenden Kurzseite.Preferably, the flow guide is one along a Flow guide element axis directed hollow cylinder or hollow truncated cone. More preferably, the hollow cylinder or the end Hollow truncated cone on an imaginary top surface, wherein the Top surface not oriented perpendicular to the flow guide axis is. In other words: the hollow cylinder or the Hollow truncated cone ends on a bevelled top surface. Of the Fuel gas stream is thus at a long side of the hollow cylinder or hollow truncated cone over a longer distance than on a long side opposite short side.

Bevorzugtermaßen ist das Strömungsleitelement etwa um die Hälfte der Mündung herum angeordnet. Somit wird dem Erenngasstrom einseitig eine Anlagefläche geboten. Zusätzlich zu dem Einfluß auf die Form der Verbrennung wird dadurch der Brenngasstrom ein Stück weit zur offenen Fläche hin abgelenkt. Dies hat wiederum eine Verlagerung des Orts der Verbrennung zur Folge. Dadurch wird besonders effizient eine akustische Verstimmung und damit die Unterdrückung einer Verbrennungsschwingung erreicht. Preferred dimensions, the flow guide is about the Half of the estuary arranged around. Thus, the natural gas flow on one side offered a contact area. In addition to the influence on the form of combustion is thereby the Fuel gas flow deflected a little way to the open area. This in turn has a shift of the location of the combustion result. This makes a particularly efficient one acoustic detuning and thus the suppression of a combustion vibration reached.

Bevorzugt ist das Strömungsleitelement ein Blech aus einem hochwarmfesten Metall, vorzugsweise aus einem Stahl.Preferably, the flow guide is a sheet of a heat-resistant metal, preferably of a steel.

Bevorzugtermaßen ist die Brennkammer eine Ringbrennkammer einer Gasturbine. Bei einer Gasturbine, insbesondere bei einer stationären Gasturbine, kommt es zu einer sehr großen Leistungsfreisetzung bei der Verbrennung. Verbrennungsschwingungen können hier nicht nur akustisch störend, sondern sogar mechanisch schädigend wirken. Eine Unterdrückung von Verbrennungsschwingungen ist hier somit von besonderer Bedeutung.Preferably, the combustion chamber is an annular combustion chamber of a Gas turbine. In a gas turbine, especially in a Stationary gas turbine, it comes to a very large release of power when burning. combustion oscillations not only can be annoying acoustically, but even mechanically harmful. A suppression of combustion vibrations is therefore of particular importance here.

Bevorzugt weist die Mündung einen Mündungsdurchmesser und das Strömungsleitelement entlang der Elementachse eine längste Erstreckung auf, wobei die längste Erstreckung zwischen einem Sechstel und der Hälfte des Mündungsdurchmessers lang ist. Vorzugsweise liegt der Wert der längsten Erstreckung zwischen einem und zehn Zentimeter.Preferably, the mouth has a mouth diameter and Flow guide along the element axis a longest Extension to, with the longest extension between a Sixth and half of the mouth diameter is long. Preferably, the value of the longest extent lies between one and ten centimeters.

Die Erfindung wird anhand der Zeichnung teilweise schematisch und beispielhaft näher erläutert. Es zeigen:

Figur 1
einen Längsschnitt durch eine ausschnittsweise dargestellte Brenneranordnung,
Figur 2
einen Längsschnitt durch eine ausschnittsweise dargestellte Brenneranordnung mit einem gegenüber Figur 1 geänderten Strömungsleitelement.
Figur 3
eine Ringbrennkammer einer Gasturbine.
The invention will be explained in more detail partially and schematically by way of example with reference to the drawing. Show it:
FIG. 1
a longitudinal section through a fragmentary burner assembly,
FIG. 2
a longitudinal section through a partially shown burner assembly with a comparison with Figure 1 changed flow guide.
FIG. 3
an annular combustion chamber of a gas turbine.

Gleiche Bezugszeichen haben in den verschiedenen Figuren die gleiche Bedeutung.The same reference numerals have in the various figures same meaning.

Figur 1 zeigt einen Längsschnitt durch eine ausschnittsweise dargestellte Brenneranordnung 1. An einer Brennkammerwand 9 einer nicht näher dargestellten Brennkammer 11 ist ein Brenner 3 angeordnet. Der Brenner 3 ist ein Hybridbrenner, d. h. er kann als ein Diffusionsbrenner oder als ein Vormischbrenner betrieben werden. Der Brenner 3 weist als eine Vormischstufe einen Ringkanal 5 auf. Der Ringkanal 5 umgibt konzentrisch einen Pilotbrenner 7. Im Ringkanal 5 wird ein Brennstoff-Luft-Gemisch 14a geführt. Dieses vereinigt sich mit einem Brennstoff-Luft-Gemisch 14b aus dem Pilotbrenner 7 zu einem Brenngasstrom 14. Der Brenngasstrom 14 tritt aus einer Mündung 13 entlang einer Mündungsrichtung 15 aus dem Brenner 3 aus. Die Mündung 13 ist von einem hohlzylinderförmigen Strömungsleitelement 17 umgeben. Das Strömungsleitelement 17 endet an einer gedachten Deckfläche 16. Das Strömungsleitelement 17 ist entlang einer Strömungsleitelementachse 17b gerichtet. Die Deckfläche 16 ist dabei nicht senkrecht zur Strömungsleitelementachse 17b orientiert. Das Strömungsleitelement 17 endet also an einer schräg gestellten Deckfläche 16. Das Strömungsleitelement 17 weist dadurch eine Langseite 17c und eine Kurzseite 17d auf. Der Brenngasstrom 14 wird an der Langseite 17c über eine etwas größere Strecke geführt als an der Kurzseite 17d. Dadurch öffnet sich der Brenngasstrom 14 in Richtung auf die Kurzseite 17d. Dies hat eine Verlagerung des Verbrennungsgebietes senkrecht zur Mündungsrichtung 15 zur Folge. Durch das die Mündung 13 umgebende Strömungsleitelement 17 ergibt sich auch eine solche Verlagerung des Verbrennungsgebietes entlang der Mündungsrichtung 15. Außerdem wird durch das Strömungsleitelement 17 die Form des Verbrennungsgebietes beeinflußt. Die Verlagerung des Verbrennungsgebietes und der Einfluß auf die Form des Verbrennungsgebietes haben zur Folge, daß das akustische System aus Brenner 3 und Brennkammer 11 akustisch verstimmt wird. Dadurch wird eine Verbrennungsschwingung vermieden oder zumindest abgeschwächt.FIG. 1 shows a longitudinal section through a partial view shown burner assembly 1. On a combustion chamber wall. 9 a combustion chamber 11, not shown, is a burner 3 arranged. The burner 3 is a hybrid burner, i. H. it can act as a diffusion burner or as a premix burner operate. The burner 3 indicates as a premixing stage an annular channel 5. The annular channel 5 surrounds concentrically a pilot burner 7. In the annular channel 5 is a fuel-air mixture 14a led. This unites with one Fuel-air mixture 14 b from the pilot burner 7 to a Fuel gas stream 14. The fuel gas stream 14 emerges from a Mouth 13 along a mouth direction 15 from the burner 3 off. The mouth 13 is of a hollow cylindrical Flow guide 17 surrounded. The flow guide 17 ends at an imaginary top surface 16. The flow guide 17 is directed along a flow guide axis 17b. The top surface 16 is not perpendicular to Flow guiding element axis 17b oriented. The flow guide 17 thus ends at an inclined top surface 16. The flow guide 17 thereby has a long side 17c and a short side 17d. The fuel gas flow 14 is on the long side 17c led over a slightly larger distance than on the short side 17d. This opens the fuel gas flow 14 towards the short side 17d. This has a shift the combustion area perpendicular to the mouth direction 15 result. By the mouth 13 surrounding flow guide 17 also results in such a shift of the Combustion area along the direction of the mouth 15. In addition becomes through the flow guide 17, the shape of the combustion area affected. The displacement of the combustion area and the influence on the shape of the combustion area have the consequence that the acoustic system of burner 3 and combustion chamber 11 is acoustically detuned. Thereby a combustion vibration is avoided or at least mitigated.

Das Strömungsleitelement 17 endet an einer Abrißkante 18. An dieser Abrißkante 18 reißen Wirbel 20 aus dem Brenngasstrom 14 ab. Hierdurch wird ein Rückströmgebiet für Brenngas erzeugt. Durch ein solches Rückströmgebiet kommt es zu einer Stabilisierung der Verbrennung und zu einer geringeren Stickoxidbildung durch eine Vergleichmäßigung der Verbrennung.The flow guide 17 terminates at a tear-off edge 18. An this tear-off edge 18 rupture vortex 20 from the fuel gas flow 14 off. As a result, a Rückströmgebiet for fuel gas is generated. By such Rückströmgebiet it comes to a Stabilization of combustion and to a lesser extent Nitrogen oxide formation by equalizing the combustion.

Figur 2 zeigt eine Brenneranordnung 1 im Längsschnitt entsprechend der Brenneranordnung 1 aus Figur 1. Im Unterschied zu Figur 1 ist das Strömungsleitelement 17 als Hohlkegelstumpf ausgeführt. Das Strömungsleitelement 17 erweitert sich also in Richtung des Brenngasstroms 14. Durch dieses Strömungsleitelement 17 wird wiederum der Ort der Verbrennung des Brenngasstroms 14 verlagert. Auch die Form der Verbrennung wird durch das Strömungsleitelement 17 beeinflußt. Es wird auch hier erreicht, daß das akustische System aus Brenner 3 und Brennkammer 11 akustisch verstimmt wird. Dies hat, wie oben ausgeführt, eine Unterdrückung von Verbrennungsschwingungen zur Folge.Figure 2 shows a burner assembly 1 in longitudinal section accordingly the burner assembly 1 of Figure 1. In difference to Figure 1, the flow guide 17 is a hollow truncated cone executed. The flow guide 17 expands ie in the direction of the fuel gas flow 14. Through this flow guide 17 will again be the place of burning of the Shifted fuel gas stream 14. Also the form of combustion is influenced by the flow guide 17. It will also achieved here that the acoustic system of burner. 3 and combustion chamber 11 is acoustically detuned. This has, like above, suppression of combustion vibrations result.

In Figur 3 ist perspektivisch und teilweise aufgebrochen eine Ringbrennkammer für eine Gasturbine dargestellt. Die Brennkammer 11 liegt rotationssymmetrisch um eine Brennkammerachse 25 und weist eine äußere Wand 21 und eine innere Wand 23 auf. Die äußere Wand 21 und die innere Wand 23 umschließen einen ringförmigen Brennraum 24. Die Innenfläche der Außenwand 21 und die Außenfläche der Innenwand 23 sind mit einer feuerfesten Innenauskleidung 27 versehen. Entlang einer Umfangsrichtung sind in der Brennkammer 11 eine Vielzahl von Brennern 3 angeordnet. An einigen der Brenner 3 sind Strömungsleitelement 17 angeordnet. Durch geeignete Orientierung und Anordnung der Strömungsleitelement 17 wird das System aus Brennern 3 und Brennkammer 11 akustisch so verstimmt, daß sich eine Unterdrückung von Verbrennungsschwingungen ergibt. Dies ist insbesondere bei der hohen geometrischen Komplexität einer Ringbrennkammer mit einer Vielzahl von Brennern erforderlich, da die akustischen Eigenschaften einer solchen Ringbrennkammer 11 praktisch nicht vorhersagbar sind.In Figure 3 is a perspective and partially broken one Ring combustion chamber for a gas turbine shown. The combustion chamber 11 is rotationally symmetrical about a combustion chamber axis 25 and has an outer wall 21 and an inner wall 23. The outer wall 21 and the inner wall 23 enclose one annular combustion chamber 24. The inner surface of the outer wall 21st and the outer surface of the inner wall 23 are refractory Interior lining 27 provided. Along a circumferential direction are in the combustion chamber 11, a plurality of burners. 3 arranged. At some of the burners 3 are flow guide 17 arranged. By suitable orientation and arrangement the flow guide 17 is the system of burners 3 and combustion chamber 11 acoustically detuned so that a Suppression of combustion vibrations results. This is especially with the high geometric complexity of a Ring combustion chamber with a variety of burners required because the acoustic properties of such an annular combustion chamber 11 are virtually unpredictable.

Claims (7)

  1. Burner arrangement (1) comprising a multiplicity of burners (3) in a common combustion chamber (11), each burner (3) opening into a combustion chamber (11) at an outlet (13), characterized in that the outlet (13), only at some of the burners (3), is formed in each case at least partly by a flow-guidance element (17) which projects into the combustion chamber (11) and is intended for directing a fuel-gas flow (14) discharging from the burner (3) into the combustion chamber (11).
  2. Burner arrangement (1) according to Claim 1, characterized in that the flow-guidance element (17) is directed along an element axis (17B) and is a hollow cylinder or hollow truncated cone surrounding the outlet (13).
  3. Burner arrangement (1) according to Claim 2, characterized in that the hollow cylinder (17) or the hollow truncated cone (17) ends at a top surface (16) sloping relative to the element axis (17B).
  4. Burner arrangement (1) according to Claim 1, characterized in that the flow-guidance element (17) is a wall element drawn partly around the outlet (13), in particular around approximately half the outlet (13).
  5. Burner arrangement (1) according to Claim 1, characterized in that the flow-guidance element (17) is a sheet made of a high-temperature-resistant metal, in particular a steel.
  6. Burner arrangement (1) according to one of the preceding claims, the combustion chamber (11) being an annular combustion chamber of a gas turbine.
  7. Burner arrangement (1) according to one of the preceding claims in which the outlet (13) has an outlet diameter (d) and the flow-guidance element (17) has a longest extent (1) along the element axis (17B), the longest extent (1) being of a length which is between one sixth of and half the outlet diameter (d).
EP99952393A 1998-08-31 1999-08-13 Burner assembly Expired - Lifetime EP1125087B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19839639 1998-08-31
DE19839639 1998-08-31
PCT/DE1999/002541 WO2000012939A1 (en) 1998-08-31 1999-08-13 Burner assembly

Publications (2)

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EP1125087A1 EP1125087A1 (en) 2001-08-22
EP1125087B1 true EP1125087B1 (en) 2005-05-18

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EP99952393A Expired - Lifetime EP1125087B1 (en) 1998-08-31 1999-08-13 Burner assembly

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JP (1) JP4472181B2 (en)
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EP1284391A1 (en) * 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Combustion chamber for gas turbines
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EP1764553A1 (en) * 2005-09-14 2007-03-21 Enel Produzione S.p.A. High-stability premix burner for gas turbines
FR2958014B1 (en) * 2010-03-23 2013-12-13 Snecma COMBUSTION CHAMBER WITH INJECTORS SHIFTING LONGITUDINALLY ON THE SAME CROWN
US9909755B2 (en) * 2013-03-15 2018-03-06 Fives North American Combustion, Inc. Low NOx combustion method and apparatus
DE102015222661A1 (en) * 2015-11-17 2017-05-18 Siemens Aktiengesellschaft Flow sleeve for fuel injection with time delay

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Publication number Publication date
US6536204B2 (en) 2003-03-25
US20010025491A1 (en) 2001-10-04
DE59912076D1 (en) 2005-06-23
EP1125087A1 (en) 2001-08-22
JP4472181B2 (en) 2010-06-02
WO2000012939A1 (en) 2000-03-09
JP2002523722A (en) 2002-07-30

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