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EP0956475B1 - Burner for fluid fuels - Google Patents

Burner for fluid fuels Download PDF

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Publication number
EP0956475B1
EP0956475B1 EP97951835A EP97951835A EP0956475B1 EP 0956475 B1 EP0956475 B1 EP 0956475B1 EP 97951835 A EP97951835 A EP 97951835A EP 97951835 A EP97951835 A EP 97951835A EP 0956475 B1 EP0956475 B1 EP 0956475B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
vortex element
air
duct
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
EP97951835A
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German (de)
French (fr)
Other versions
EP0956475A2 (en
Inventor
Gerwig Poeschl
Stefan Hoffmann
Ingo Ganzmann
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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Publication of EP0956475A2 publication Critical patent/EP0956475A2/en
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Publication of EP0956475B1 publication Critical patent/EP0956475B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to a burner for fluid fuels, especially for use in a gas turbine plant.
  • a burner for fluid fuels such as the one in particular used in a gas turbine plant is from the DE 42 12 810 A1 known. From this it can be seen that air passes through an air supply ring duct system and fuel through another Ring channel system are fed to the combustion. there fuel is injected from the fuel duct into the air duct, either directly or from hollow blades Swirl blades.
  • this is to ensure that the mixture of Fuel and air can be reached to be a low nitrogen oxide
  • the lowest possible nitrogen oxide production is for reasons of environmental protection and corresponding legal guidelines for pollutant emissions an essential Combustion requirements, especially the Combustion in the gas turbine plant of a power plant.
  • the formation of nitrogen oxides increases exponentially with that Flame temperature of the combustion. With an inhomogeneous mixture there is a certain amount of fuel and air Distribution of flame temperatures in the combustion area. Determine the maximum temperatures of such a distribution after the exponential relationship of nitrogen oxide formation and flame temperature determine the amount of the formed Nitrogen oxides.
  • the combustion of a homogeneous fuel-air mixture therefore achieved at the same mean flame temperature lower nitrogen oxide emissions than combustion of an inhomogeneous mixture.
  • the cited publication is a good mix of air and fuel.
  • EP 561 591 A2 there is a rotating grid for production a turbulent flow for use in a burner, especially in a premix burner of a gas turbine, disclosed.
  • the rotating grille serves two concentric, generate oppositely rotating currents, so that in the inner flow during a partial load operation of the Gas turbine plant a reduced amount of fuel in one reduced air volume due to the division into two flows burned and thus stable combustion even in partial load operation can be maintained. It also creates Rotating grid directly adjacent to the rotating grid Backflow areas, the combustion areas for a stable Represent combustion.
  • EP 619 134 A1 discloses a mixing chamber for mixing Fabrics, e.g. in chemistry, food or pharmaceutical production.
  • the substances to be mixed are in separate channels swirled by a vortex generator and then merged.
  • the vortex generator is called elongated half pyramids trained deflection elements formed.
  • DE 44 15 916 A1 describes a method and a device for the combustion of a flowable fuel, in particular in the burner of a gas turbine.
  • a burner generating a turbulence is used, so that combustion air is swirled.
  • Combustion air is admitted fuel so that a particularly good mixture of fuel and Combustion air results.
  • the swirl is represented by a number achieved obtuse flow obstacles, in particular through bars or discs.
  • a swirl element called a static mixer is known from DE 41 23 161 A1. It exhibits a variety of in relation to the diameter of a pipeline or one Flow channel in which or in which it can be used, small Deflection elements on the axis of the flow channel or the pipe are inclined. The inclination of the in Rows aligned deflection elements is within one Row in the same direction and from row to row in opposite directions.
  • On such a swirling element covers a simply coherent Area, e.g. B. a circular or rectangular Cross-section. It serves to flow a medium through swirling the pipeline or flow channel a thorough mixing with one introduced into the medium Substance is available.
  • large swirl elements are also in EP 0 634 207 B1 and in WO 95/26226 A1 described. The main area of application of such Swirling elements are the nitrogen oxide reduction of flue gas by admixing ammonia in flow channels of typically a few square meters of cross-sectional area.
  • the object of the invention is to provide a burner for fluid Provide fuels that have a good mixture of combustion air and fuel at the same time, at most, at the least Impairment of other combustion parameters.
  • a major advantage of the invention is that the turbulent flow of the combustion air is a special one good mixture of combustion air and fuel can be achieved is, at the same time by the swirling element caused pressure loss is low. It is through the Mixture of fuel and combustion air in the turbulent Flow improved spatial homogeneity of the mixture achieved.
  • the temporal Fluctuation of the mixing ratio in extensive tests determined. Locally occurring fluctuations in time of the Mixing ratio, as well as the spatial inhomogeneities, to a distribution of the flame temperature the adverse effects on the Nitrogen oxide emission. The results of the tests showed that the fuel / air mixture generated a short time Fluctuation in the mixing ratio.
  • the swirling element is preferably designed such that that the turbulent flow of combustion air generated on Swirling element essentially no areas flowing back Combustion air has. So that is achieved that no ignitable fuel-air mixture to the swirling element can flow back and therefore no combustion is stabilized on the swirling element, causing damage of the swirling element could result.
  • the burner is preferably designed such that the outflow side from the swirling element swirl blades in the air duct are arranged. This ensures that a swirl element with the advantageous described above Effects on the homogeneity of the mixture of fuel and combustion air used in conjunction with swirl blades that is favorable to the stability of the combustion act.
  • At least one of the swirl blades is preferably a hollow blade trained from which fuel is admitted.
  • this configuration makes it possible to achieve uniform injection of fuel from a hollow vane Swirl blade with a further homogenizing effect on the fuel / air mixture in combination with the above advantages explained.
  • the burner as one Premix or hybrid burners for use in gas turbine plants, with an air supply duct, especially one itself tapering ring channel, which at least three more, in particular Ring channels arranged concentrically to the air supply channel for the supply of fluidic media, wherein two of these channels serve to supply a pilot burner and wherein a pilot flame is maintained by the pilot burner the combustion can be generated.
  • the connecting area is preferably less than half of those enclosed by the larger perimeter ring Circular area. Also preferred is the diameter of the larger limiting ring smaller than one meter, in particular 40 cm to 60 cm. This is the swirl element for use in small flow channels, e.g. Air ducts of gas turbine burners.
  • they are one Circle-associated deflection elements are equally spaced from one another. This creates one over the entire interface even turbulence achieved.
  • each deflecting element is made of the connection surface to a tear-off edge to produce Whirls rejuvenated. It preferably has trapezoidal or Triangular shape. This configuration makes it special intense turbulence reached.
  • FIG. 1 shows a hybrid burner 1 which is approximately rotationally symmetrical with respect to an axis 12.
  • a pilot burner 9 directed along the axis 12 with a fuel supply channel 8 and an air supply ring channel 7 concentrically surrounding it is surrounded concentrically by a fuel ring channel 3.
  • This fuel ring channel 3 is at the bottom, ie partially concentrically enclosed by an air supply ring channel 2.
  • a ring of swirl blades 5, which is shown schematically, is installed in this air supply ring channel 2. At least one of these swirl blades 5 is designed as a hollow blade 5a. It has an inlet 6 formed by a plurality of openings for a fuel supply.
  • the fuel ring channel 3 opens into this hollow blade 5a.
  • a swirling element 4 - shown schematically - is installed in the air duct 2.
  • the hybrid burner 1 can be used as a diffusion burner via the pilot burner 9 operate. But usually it is called Premix burners used, that means fuel and air are mixed first and then fed to the combustion.
  • the pilot burner 9 serves to maintain a pilot flame, the combustion during premix burner operation with a possibly changing fuel-air ratio stabilized.
  • Combustion air 10 and fuel 11 mixed in the air duct 2 and then fed to the combustion.
  • the fuel 11 from the fuel channel 3 in a hollow blade 5a of the swirl blade ring 5 passed and from there via the inlet 6 into the combustion air 10 initiated in the air duct 2.
  • FIG. 2 is a top view of a swirling element 4 shown.
  • Fig. 3 shows the same with the same reference numerals Swirling element 4 in a side view.
  • From an inner Limiting ring 52 lead evenly distributed over the ring circumference a plurality of webs 54 to an outer boundary ring 53.
  • the center of the outer perimeter ring 53 lies on the symmetry axis 59 of the inner limiting ring 52 and the webs 54 are normal to the inner limiting ring 52 directed.
  • the connecting surface 56 provides the lateral surface of a truncated cone between the inner boundary ring 52 and outer limiting ring 53.
  • On each Web 54 are trapezoidal, pointing into the interior of the truncated cone, flat deflection elements 51 arranged.
  • each deflection element 51 is connected to a web 4.
  • the deflection elements 51 are along three, to the axis of symmetry 59 concentric circles 55a, 55b, 55c to each other equally spaced.
  • the deflection elements 51 are inclined to a normal of the connecting surface 56, wherein each of the deflection elements 51 along a circle 55a, 55b, 55c in the same direction, from a circle 55a, 55b, 55c to one adjacent circle 55a, 55b, 55c inclined in opposite directions are.
  • a flow of combustion air through the swirling element 4 10, normal to the interface 56 in the interior of the truncated cone has the consequence that on the narrow sides 51b of the deflection elements 51 form vertebrae 57.
  • introduced fuel 11 is caused by this turbulence intensively mixed with the combustion air 10.
  • the inclination the deflection elements 51 also characterize the main flow secondary flows 58 in addition to the locally good Mixing the swirling homogenizes the mixture over the entire cross-sectional area of an air supply ring duct, in which the swirling element is installed (see Fig 1), enable.
  • the design of the swirling element 4 has the consequence that the by the Swirling pressure loss is low.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

The invention concerns a burner (1), in particular for a gas turbine, combustion air (10) being swirled by means of a swirling element (4) and fuel (11) being admitted into the swirled combustion air (10). At the same time, the pressure loss caused by the swirling element (4) is low. As a result of the invention, NOx emission is low whilst the degree of efficiency is almost the same as with conventional burners.

Description

Die Erfindung betrifft einen Brenner für fluidische Brennstoffe, insbesondere für den Einsatz in einer Gasturbinenanlage.The invention relates to a burner for fluid fuels, especially for use in a gas turbine plant.

Ein Brenner für fluidische Brennstoffe, wie er insbesondere in einer Gasturbinenanlage eingesetzt wird, ist aus der DE 42 12 810 A1 bekannt. Hieraus geht hervor, daß Luft durch ein Luftzufuhr-Ringkanalsystem und Brennstoff durch ein weiteres Ringkanalsystem der Verbrennung zugeführt werden. Dabei wird Brennstoff aus dem Brennstoffkanal in den Luftkanal eingedüst, entweder direkt oder aus als Hohlschaufeln ausgebildeten Drallschaufeln.A burner for fluid fuels, such as the one in particular used in a gas turbine plant is from the DE 42 12 810 A1 known. From this it can be seen that air passes through an air supply ring duct system and fuel through another Ring channel system are fed to the combustion. there fuel is injected from the fuel duct into the air duct, either directly or from hollow blades Swirl blades.

Damit soll unter anderem eine möglichst homogene Mischung von Brennstoff und Luft erreicht werden, um eine stickoxidarme Verbrennung zu erzielen. Eine möglichst geringe Stickoxidproduktion ist aus Gründen des Umweltschutzes und entsprechenden gesetzlichen Richtlinien für Schadstoffemissionen eine wesentliche Anforderung an die Verbrennung, insbesondere an die Verbrennung in der Gasturbinenanlage eines Kraftwerks. Die Bildung von Stickoxiden erhöht sich exponentiell mit der Flammentemperatur der Verbrennung. Bei einer inhomogenen Mischung von Brennstoff und Luft ergibt sich eine bestimmte Verteilung der Flammentemperaturen im Verbrennungsbereich. Die Maximaltemperaturen einer solchen Verteilung bestimmen nach dem genannten exponentiellen Zusammenhang von Stickoxidbildung und Flammentemperatur maßgeblich die Menge der gebildeten Stickoxide. Die Verbrennung eines homogenen Brennstoff-Luft-Gemisch erzielt demnach bei gleicher mittlerer Flammentemperatur einen niedrigeren Stickoxidausstoß als die Verbrennung eines inhomogenen Gemisches. Bei der Brennerausführung der zitierten Druckschrift wird eine räumlich gute Mischung von Luft und Brennstoff erzielt.Among other things, this is to ensure that the mixture of Fuel and air can be reached to be a low nitrogen oxide To achieve combustion. The lowest possible nitrogen oxide production is for reasons of environmental protection and corresponding legal guidelines for pollutant emissions an essential Combustion requirements, especially the Combustion in the gas turbine plant of a power plant. The The formation of nitrogen oxides increases exponentially with that Flame temperature of the combustion. With an inhomogeneous mixture there is a certain amount of fuel and air Distribution of flame temperatures in the combustion area. Determine the maximum temperatures of such a distribution after the exponential relationship of nitrogen oxide formation and flame temperature determine the amount of the formed Nitrogen oxides. The combustion of a homogeneous fuel-air mixture therefore achieved at the same mean flame temperature lower nitrogen oxide emissions than combustion of an inhomogeneous mixture. In the burner version The cited publication is a good mix of air and fuel.

In der EP 561 591 A2 ist ein Rotationsgitter zur Erzeugung einer turbulenten Strömung für einen Einsatz in einem Brenner, insbesondere in einem Vormischbrenner einer Gasturbine, offenbart. Das Rotationsgitter dient dazu, zwei konzentrische, gegensinnig rotierende Strömungen zu erzeugen, so daß in der inneren Strömung während eines Teillastbetriebes der Gasturbinenanlage eine reduzierte Brennstoffmenge in einer durch die Aufteilung in zwei Strömungen reduzierten Luftmenge verbrannt und somit auch im Teillastbetrieb eine stabile Verbrennung aufrecht erhalten werden kann. Weiterhin erzeugt das Rotationsgitter direkt an das Rotationsgitter angrenzende Rückströmgebiete, die Verbrennungsgebiete für eine stabile Verbrennung darstellen.In EP 561 591 A2 there is a rotating grid for production a turbulent flow for use in a burner, especially in a premix burner of a gas turbine, disclosed. The rotating grille serves two concentric, generate oppositely rotating currents, so that in the inner flow during a partial load operation of the Gas turbine plant a reduced amount of fuel in one reduced air volume due to the division into two flows burned and thus stable combustion even in partial load operation can be maintained. It also creates Rotating grid directly adjacent to the rotating grid Backflow areas, the combustion areas for a stable Represent combustion.

Die EP 619 134 A1 offenbart eine Mischkammer zur Mischung von Stoffen, z.B. in der Chemie, Nahrungsmittel- oder Pharmaproduktion. Die zu mischenden Stoffe werden in getrennten Kanälen durch einen Wirbelgenerator verwirbelt und dann zusammengeführt. Der Wirbelgenerator wird durch als längliche Halbpyramiden ausgebildete Auslenkelemente gebildet.EP 619 134 A1 discloses a mixing chamber for mixing Fabrics, e.g. in chemistry, food or pharmaceutical production. The substances to be mixed are in separate channels swirled by a vortex generator and then merged. The vortex generator is called elongated half pyramids trained deflection elements formed.

In der DE 44 15 916 A1 sind ein Verfahren und eine Vorrichtung zur Verbrennung eines fließfähigen Brennstoffes, insbesondere im Brenner einer Gasturbine, beschrieben. Im Luftkanal des Brenners wird eine turbulenzerzeugende Anordnung eingesetzt, so daß Verbrennungsluft verwirbelt wird. In die verwirbelte Verbrennungsluft wird Brennstoff eingelassen, so daß sich eine besonders gute Durchmischung von Brennstoff und Verbrennungsluft ergibt. Die Verwirbelung wird durch eine Anzahl stumpfer Strömungshindernisse erzielt, insbesondere durch Stäbe oder Scheiben. DE 44 15 916 A1 describes a method and a device for the combustion of a flowable fuel, in particular in the burner of a gas turbine. In the air duct a burner generating a turbulence is used, so that combustion air is swirled. In the swirled Combustion air is admitted fuel so that a particularly good mixture of fuel and Combustion air results. The swirl is represented by a number achieved obtuse flow obstacles, in particular through bars or discs.

Ein als statischer Mischer bezeichnetes Verwirbelungselement ist aus der DE 41 23 161 A1 bekannt. Es weist eine Vielzahl von in Bezug zum Durchmesser einer Rohrleitung oder eines Strömungskanals, in der oder den es einsetzbar ist, kleinen Auslenkelementen auf, die gegenüber der Achse des Strömungskanals oder der Rohrleitung geneigt sind. Die Neigung der in Reihen ausgerichteten Auslenkelemente ist innerhalb einer Reihe gleichsinnig und von Reihe zu Reihe gegensinnig. Ein solches Verwirbelungselement überdeckt eine einfach zusammenhängende Fläche, z. B. einen kreisförmigen oder rechteckigen Querschnitt. Es dient dazu, eine Strömung eines Mediums durch die Rohrleitung oder den Strömungskanal zu verwirbeln, wodurch eine gute Durchmischung mit einem in das Medium eingebrachten Stoff erreichbar ist. Vergleichbare, große Verwirbelungselemente sind auch in der EP 0 634 207 B1 und in der WO 95/26226 A1 beschrieben. Das Haupteinsatzgebiet solcher Verwirbelungselemente ist die Stickoxidminderung von Rauchgas durch die Beimischung von Ammoniak in Strömungskanälen von typischerweise einigen Quadratmetern Querschnittsfläche.A swirl element called a static mixer is known from DE 41 23 161 A1. It exhibits a variety of in relation to the diameter of a pipeline or one Flow channel in which or in which it can be used, small Deflection elements on the axis of the flow channel or the pipe are inclined. The inclination of the in Rows aligned deflection elements is within one Row in the same direction and from row to row in opposite directions. On such a swirling element covers a simply coherent Area, e.g. B. a circular or rectangular Cross-section. It serves to flow a medium through swirling the pipeline or flow channel a thorough mixing with one introduced into the medium Substance is available. Comparable, large swirl elements are also in EP 0 634 207 B1 and in WO 95/26226 A1 described. The main area of application of such Swirling elements are the nitrogen oxide reduction of flue gas by admixing ammonia in flow channels of typically a few square meters of cross-sectional area.

Aufgabe der Erfindung ist es, einen Brenner für fluidische Brennstoffe bereitzustellen, der eine gute Mischung von Verbrennungsluft und Brennstoff bei gleichzeitig allenfalls geringfügiger Beeinträchtigung anderer Parameter der Verbrennung.The object of the invention is to provide a burner for fluid Provide fuels that have a good mixture of combustion air and fuel at the same time, at most, at the least Impairment of other combustion parameters.

Die Lösung der Aufgabe, die auf den Brenner gerichtet ist, erfolgt erfindungsgemäß durch einen Brenner für fluidische Brennstoffe, insbesondere für den Einsatz in einer Gasturbinenanlage, mit einem Luftkanal für die Zufuhr von Verbrennungsluft und einem Brennstoffkanal für die Zufuhr von Brennstoff, wobei ein Verwirbelungselement zur Erzeugung von stark turbulenter Verbrennungsluft und ein Einlaß von Brennstoff aus dem Brennstoffkanal in den Luftkanal abströmseitig vom Verwirbelungselement vorgesehen sind und wobei das Verwirbelungselement aufweist:

  • a) einen ersten Begrenzungsring mit einer Symmetrieachse,
  • b) einen zweiten, größeren Begrenzungsring (53), dessen Mittelpunkt auf der Symmetrieachse liegt,
  • c) eine Verbindungsfläche, die durch die beiden Begrenzungsringe aufgespannt ist,
  • d) entlang auf der Verbindungsfläche liegender Kreise, deren jeweiliger Mittelpunkt auf der Symmetrieachse liegt, eine Vielzahl von flächigen Auslenkelementen, die jeweils gegen eine Normale der Verbindungsfläche geneigt sind. Das Verwirbelungselement ist für einen Einsatz in einem ringförmigen Strömungskanal geeignet. Es sind mindestens zwei, vorzugsweise drei Kreise vorgesehen.
    • The object, which is directed to the burner, is achieved according to the invention by a burner for fluid fuels, in particular for use in a gas turbine system, with an air duct for the supply of combustion air and a fuel duct for the supply of fuel, with a swirling element for Generation of highly turbulent combustion air and an inlet of fuel from the fuel channel into the air channel on the downstream side of the swirling element are provided, and wherein the swirling element has:
  • a) a first limiting ring with an axis of symmetry,
  • b) a second, larger limiting ring (53), the center of which lies on the axis of symmetry,
  • c) a connecting surface which is spanned by the two limiting rings,
  • d) along circles lying on the connecting surface, the respective center point of which lies on the axis of symmetry, a multiplicity of flat deflection elements which are each inclined against a normal of the connecting surface. The swirling element is suitable for use in an annular flow channel. At least two, preferably three, circles are provided.

    • Ein wesentlicher Vorteil der Erfindung liegt darin, daß durch die turbulente Strömung der Verbrennungsluft eine besonders gute Mischung von Verbrennungsluft und Brennstoff erreichbar ist, wobei gleichzeitig ein durch das Verwirbelungselement hervorgerufener Druckverlust gering ist. Es wird durch die Mischung von Brennstoff und Verbrennungsluft in der turbulenten Strömung eine verbesserte räumliche Homogenität des Gemisches erzielt. Darüber hinaus wurde erstmalig die zeitliche Schwankung des Mischungsverhältnisses in umfangreichen Versuchen ermittelt. Lokal auftretende zeitliche Schwankungen des Mischungsverhältnisses führen, wie auch die räumlichen Inhomogenitäten, zu einer Verteilung der Flammentemperatur mit den oben ausgeführten nachteiligen Wirkungen auf die Stickoxidemission. Die Ergebnisse der Versuche zeigten, daß die erzeugte Brennstoff/Luft-Mischung eine geringe zeitliche Schwankung im Mischungsverhältnis aufweist. Es wird also eine räumlich und zeitlich weitgehend homogene Mischung von Brennstoff und Luft und damit eine reduzierte Stickoxidproduktion erreicht. Durch den gleichzeitig nur geringen Druckverlust bleibt der Wirkungsgrad des Brenners nahezu unbeeinträchtigt. Dies stellt eine erhebliche Verbesserung gegenüber bisher verwendeten Verwirbelungselementen dar, die als stumpfe Strömungshindernisse ausgeführt waren. Solche Strömungshindernisse haben einen erheblichen Druckverlust zur Folge, so daß eine verbesserte Mischung von Brennstoff und Verbrennungsluft durch einen deutlich verminderten Wirkungsgrad des Brenners erkauft werden mußte.A major advantage of the invention is that the turbulent flow of the combustion air is a special one good mixture of combustion air and fuel can be achieved is, at the same time by the swirling element caused pressure loss is low. It is through the Mixture of fuel and combustion air in the turbulent Flow improved spatial homogeneity of the mixture achieved. In addition, the temporal Fluctuation of the mixing ratio in extensive tests determined. Locally occurring fluctuations in time of the Mixing ratio, as well as the spatial inhomogeneities, to a distribution of the flame temperature the adverse effects on the Nitrogen oxide emission. The results of the tests showed that the fuel / air mixture generated a short time Fluctuation in the mixing ratio. So it will be one largely homogeneous mixture of fuel in terms of space and time and air and thus a reduced nitrogen oxide production reached. Due to the low pressure drop at the same time the efficiency of the burner remains almost unaffected. This represents a significant improvement over the previous one used swirling elements that act as obtuse flow obstacles were executed. Such flow obstacles result in a significant loss of pressure, so that an improved mixture of fuel and combustion air due to a significantly reduced burner efficiency had to be bought.

    Zur Vermeidung einer Flammenstabilisierung am Verwirbelungselement erfolgt der Einlaß des Brennstoffs abströmseitig vom Verwirbelungselement. Damit wird das Verwirbelungselement nur von Verbrennungsluft durchströmt, und die Gefahr einer Verbrennung im Bereich des Verwirbelungselementes, die dieses beschädigen könnte, ist reduziert.To avoid flame stabilization on the swirl element the fuel is admitted downstream of the Swirling element. So that the swirling element only of combustion air and the risk of burning in the area of the swirling element, this could damage is reduced.

    Vorzugsweise wird das Verwirbelungselement so ausgebildet, daß die erzeugte turbulente Strömung der Verbrennungsluft am Verwirbelungselement im wesentlichen keine Gebiete zurückströmender Verbrennungsluft aufweist. Damit wird erreicht, daß kein zündfähiges Brennstoff-Luft-Gemisch zum Verwirbelungselement zurückströmen kann und damit keine Verbrennung am Verwirbelungselement stabilisiert wird, die eine Beschädigung des Verwirbelungselementes zur Folge haben könnte.The swirling element is preferably designed such that that the turbulent flow of combustion air generated on Swirling element essentially no areas flowing back Combustion air has. So that is achieved that no ignitable fuel-air mixture to the swirling element can flow back and therefore no combustion is stabilized on the swirling element, causing damage of the swirling element could result.

    Bevorzugtermaßen ist der Brenner so ausgestaltet, daß abströmseitig vom Verwirbelungselement Drallschaufeln im Luftkanal angeordnet sind. Hierdurch wird erreicht, daß ein Verwirbelungselement mit den oben beschriebenen vorteilhaften Auswirkungen auf die Homogenität der Mischung von Brennstoff und Verbrennungsluft in Verbindung mit Drallschaufeln eingesetzt wird, die günstig auf die Stabilität der Verbrennung einwirken.The burner is preferably designed such that the outflow side from the swirling element swirl blades in the air duct are arranged. This ensures that a swirl element with the advantageous described above Effects on the homogeneity of the mixture of fuel and combustion air used in conjunction with swirl blades that is favorable to the stability of the combustion act.

    Vorzugsweise ist zumindest eine der Drallschaufeln als Hohlschaufel ausgebildet, aus der Brennstoff einlaßbar ist. Über diese Ausgestaltung ist es möglich, eine gleichmäßige Eindüsung von Brennstoff aus einer als Hohlschaufel ausgebildeten Drallschaufel mit einer weiter homogenisierenden Wirkung auf das Brennstoff/Luft-Gemisch in Kombination mit den oben erläuterten Vorteilen zu nutzen.At least one of the swirl blades is preferably a hollow blade trained from which fuel is admitted. about this configuration makes it possible to achieve uniform injection of fuel from a hollow vane Swirl blade with a further homogenizing effect on the fuel / air mixture in combination with the above advantages explained.

    Weiterhin bevorzugt ist die Ausbildung des Brenners als ein Vormisch- oder Hybridbrenner für den Einsatz in Gasturbinenanlagen, mit einem Luftzufuhrkanal, insbesondere ein sich verjüngender Ringkanal, welcher mindestens drei weitere, insbesondere konzentrisch zum Luftzufuhrkanal angeordnete Ringkanäle zur Zuführung von fluidischen Medien umschließt, wobei zwei dieser Kanäle zur Versorgung eines Pilotbrenners dienen und wobei durch den Pilotbrenner eine Pilotflamme zur Aufrechterhaltung der Verbrennung erzeugbar ist.Also preferred is the design of the burner as one Premix or hybrid burners for use in gas turbine plants, with an air supply duct, especially one itself tapering ring channel, which at least three more, in particular Ring channels arranged concentrically to the air supply channel for the supply of fluidic media, wherein two of these channels serve to supply a pilot burner and wherein a pilot flame is maintained by the pilot burner the combustion can be generated.

    Bevorzugtermaßen beträgt die Verbindungsfläche weniger als die Hälfte der durch den größeren Begrenzungsring umschlossenen Kreisfläche. Weiterhin bevorzugt ist der Durchmesser des größeren Begrenzungsringes kleiner als ein Meter, insbesondere 40 cm bis 60 cm. Damit ist das Verwirbelungselement für den Einsatz in kleinen Strömungskanälen, wie z.B. Luftkanälen von Gasturbinenbrennern, geeignet.The connecting area is preferably less than half of those enclosed by the larger perimeter ring Circular area. Also preferred is the diameter of the larger limiting ring smaller than one meter, in particular 40 cm to 60 cm. This is the swirl element for use in small flow channels, e.g. Air ducts of gas turbine burners.

    In einer weiter bevorzugten Ausgestaltung sind die einem Kreis zugeordneten Auslenkelemente untereinander gleich beabstandet. Damit wird eine über die ganze Verbindungsfläche gleichmäßige Verwirbelung erzielt.In a further preferred embodiment, they are one Circle-associated deflection elements are equally spaced from one another. This creates one over the entire interface even turbulence achieved.

    Weiterhin bevorzugt ist, daß sich jedes Auslenkelement aus der Verbindungsfläche zu einer Abrißkante zur Erzeugung von Wirbeln verjüngt. Vorzugsweise weist es etwa Trapez- oder Dreiecksform auf. Durch diese Ausgestaltung wird eine besonders intensive Verwirbelung erreicht.It is further preferred that each deflecting element is made of the connection surface to a tear-off edge to produce Whirls rejuvenated. It preferably has trapezoidal or Triangular shape. This configuration makes it special intense turbulence reached.

    Bevorzugtermaßen sind die einem jeweiligen Kreis zugeordneten Auslenkelemente gleichsinnig geneigt. Bevorzugt sind auf einander benachbarten Kreisen angeordnete Auslenkelemente gegensinnig geneigt. Diese Anordnung der Auslenkelemente bewirkt, daß zusätzlich zur lokal guten Durchmischung durch die Verwirbelung eine Homogenisierung über größere Bereiche der Strömung erfolgt.Preferred are those assigned to a respective circle Deflection elements inclined in the same direction. Are preferred to each other neighboring circles arranged in opposite directions inclined. This arrangement of the deflection elements causes that in addition to the good local mixing due to the swirling homogenization over larger areas of the Flow takes place.

    In der Zeichnung ist zur näheren Erläuterung ein Ausführungsbeispiel der Erfindung dargestellt. Es zeigen:

  • Fig 1 einen Längsschnitt durch einen Hybridbrenner,
  • Fig 2 ein Verwirbelungselement in Aufsicht,
  • Fig 3 ein Verwirbelungselement in Seitenansicht
    • In the drawing, an embodiment of the invention is shown for further explanation. Show it:
  • 1 shows a longitudinal section through a hybrid burner,
  • 2 a swirl element in supervision,
  • 3 shows a swirling element in a side view

    • Figur 1 zeigt einen Hybridbrenner 1, der in etwa rotationssymmetrisch bezüglich einer Achse 12 ist. Ein entlang der Achse 12 gerichteter Pilotbrenner 9 mit einem Brennstoff-Zufuhrkanal 8 und einem diesen konzentrisch umschließenden Luftzufuhr-Ringkanal 7 ist konzentrisch umgeben von einem Brennstoff-Ringkanal 3. Dieser Brennstoff-Ringkanal 3 ist unten, d.h. teilweise konzentrisch umschlossen von einem Luftzufuhr-Ringkanal 2. In diesem Luftzufuhr-Ringkanal 2 ist ein - schematisch dargestellter - Kranz von Drallschaufeln 5 eingebaut. Mindestens eine dieser Drallschaufeln 5 ist als Hohlschaufel 5a ausgebildet. Sie weist einen durch mehrere Öffnungen gebildeten Einlaß 6 für eine Brennstoffzuführung auf.
    Der Brennstoff-Ringkanal 3 mündet in diese Hohlschaufel 5a. Zuströmseitig vom Drallschaufelkranz 5 ist ein - schematisch dargestelltes - Verwirbelungselement 4 im Luftkanal 2 eingebaut.    FIG. 1 shows a hybrid burner 1 which is approximately rotationally symmetrical with respect to an axis 12. A pilot burner 9 directed along the axis 12 with a fuel supply channel 8 and an air supply ring channel 7 concentrically surrounding it is surrounded concentrically by a fuel ring channel 3. This fuel ring channel 3 is at the bottom, ie partially concentrically enclosed by an air supply ring channel 2. A ring of swirl blades 5, which is shown schematically, is installed in this air supply ring channel 2. At least one of these swirl blades 5 is designed as a hollow blade 5a. It has an inlet 6 formed by a plurality of openings for a fuel supply.
    The fuel ring channel 3 opens into this hollow blade 5a. On the inflow side of the swirl vane ring 5, a swirling element 4 - shown schematically - is installed in the air duct 2.

    Der Hybridbrenner 1 kann über den Pilotbrenner 9 als Diffusionsbrenner betrieben werden. Üblicherweise wird er aber als Vormischbrenner eingesetzt, daß heißt Brennstoff und Luft werden erst gemischt und dann der Verbrennung zugeführt. Dabei dient der Pilotbrenner 9 zur Aufrechterhaltung einer Pilotflamme, die die Verbrennung während des Vormischbrennerbetriebes bei einem eventuell wechselnden Brennstoff-Luft-Verhältnis stabilisiert. Für die eigentliche Verbrennung werden Verbrennungsluft 10 und Brennstoff 11 im Luftkanal 2 gemischt und anschließend der Verbrennung zugeführt. Im gezeigten Ausführungsbeispiel wird dabei der Brennstoff 11 aus dem Brennstoffkanal 3 in eine Hohlschaufel 5a des Drallschaufelkranzes 5 geleitet und von dort über den Einlaß 6 in die Verbrennungsluft 10 im Luftkanal 2 eingeleitet.The hybrid burner 1 can be used as a diffusion burner via the pilot burner 9 operate. But usually it is called Premix burners used, that means fuel and air are mixed first and then fed to the combustion. there the pilot burner 9 serves to maintain a pilot flame, the combustion during premix burner operation with a possibly changing fuel-air ratio stabilized. For the actual combustion Combustion air 10 and fuel 11 mixed in the air duct 2 and then fed to the combustion. In the embodiment shown the fuel 11 from the fuel channel 3 in a hollow blade 5a of the swirl blade ring 5 passed and from there via the inlet 6 into the combustion air 10 initiated in the air duct 2.

    Wie bereits erläutert, kommt es für eine stickoxidarme Verbrennung wesentlich darauf an, eine möglichst homogene Mischung von Verbrennungsluft 10 und Brennstoff 11 zu erreichen. Dies wird durch das Verwirbelungselement 4 erreicht, das die Verbrennungsluft 10 in eine turbulente Strömung überführt. Der in die turbulente Verbrennungsluft 10 eingebrachte Brennstoff 11 wird durch die Verwirbelung besonders gut mit der Verbrennungsluft 10 vermischt. Es wird eine räumlich und zeitlich homogene Mischung von Verbrennungsluft 10 und Brennstoff 11 erreicht. Gleichzeitig ist der durch das Verwirbelungselement 4 hervorgerufene Druckverlust gering, wodurch der Wirkungsgrad des Brenners 1 kaum beeinträchtigt wird.As already explained, there is combustion with low nitrogen oxides essential to ensure that the mixture is as homogeneous as possible to achieve combustion air 10 and fuel 11. This is achieved by the swirling element 4, that converts the combustion air 10 into a turbulent flow. The introduced into the turbulent combustion air 10 Fuel 11 is particularly good with the swirling the combustion air 10 mixed. It will be a spatial and temporally homogeneous mixture of combustion air 10 and fuel 11 reached. At the same time it is through the swirling element 4 caused pressure loss low, which the efficiency of the burner 1 is hardly affected.

    In Fig. 2 ist eine Aufsicht auf ein Verwirbelungselement 4 gezeigt. Fig. 3 zeigt mit gleichen Bezugszeichen das gleiche Verwirbelungselement 4 in einer Seitenansicht. Von einem inneren Begrenzungsring 52 führen gleichverteilt über den Ringumfang eine Vielzahl von Stegen 54 zu einem äußeren Begrenzungsring 53. Der Mittelpunkt des äußeren Begrenzungsringes 53 liegt auf der Symmmetrieachse 59 des inneren Begrenzungsringes 52 und die Stege 54 sind normal auf den inneren Begrenzungsring 52 gerichtet. Die Verbindungsfläche 56 stellt die Mantelfläche eines Kegelstumpfes zwischen innerem Begrenzungsring 52 und äußerem Begrenzungsring 53 dar. An jedem Steg 54 sind in das Innere des Kegelstumpfes weisende, trapezförmige, ebene Auslenkelemente 51 angeordnet. Die breite Seite 51a jedes Auslenkelementes 51 ist mit einem Steg 4 verbunden. Die Auslenkelemente 51 sind entlang dreier, zur Symmetrieachse 59 konzentrischer Kreise 55a, 55b, 55c zueinander gleich beabstandet angeordnet. Die Auslenkelemente 51 sind gegen eine Normale der Verbindungsfläche 56 geneigt, wobei jeweils die Auslenkelemente 51 entlang eines Kreises 55a, 55b, 55c gleichsinnig, von einem Kreis 55a, 55b, 55c zu einem benachbarten Kreis 55a, 55b, 55c gegensinnig geneigt sind.2 is a top view of a swirling element 4 shown. Fig. 3 shows the same with the same reference numerals Swirling element 4 in a side view. From an inner Limiting ring 52 lead evenly distributed over the ring circumference a plurality of webs 54 to an outer boundary ring 53. The center of the outer perimeter ring 53 lies on the symmetry axis 59 of the inner limiting ring 52 and the webs 54 are normal to the inner limiting ring 52 directed. The connecting surface 56 provides the lateral surface of a truncated cone between the inner boundary ring 52 and outer limiting ring 53. On each Web 54 are trapezoidal, pointing into the interior of the truncated cone, flat deflection elements 51 arranged. The width Side 51a of each deflection element 51 is connected to a web 4. The deflection elements 51 are along three, to the axis of symmetry 59 concentric circles 55a, 55b, 55c to each other equally spaced. The deflection elements 51 are inclined to a normal of the connecting surface 56, wherein each of the deflection elements 51 along a circle 55a, 55b, 55c in the same direction, from a circle 55a, 55b, 55c to one adjacent circle 55a, 55b, 55c inclined in opposite directions are.

    Eine Durchströmung des Verwirbelungselementes 4 mit Verbrennungsluft 10, normal zur Verbindungsfläche 56 in das Innere des Kegelstumpfes hat zur Folge, daß sich an den Schmalseiten 51b der Auslenkelemente 51 Wirbel 57 bilden. In das strömende Medium eingeleiteter Brennstoff 11 wird durch diese Verwirbelung intensiv mit der Verbrennungsluft 10 vermischt. Die Neigung der Auslenkelemente 51 prägt der Hauptströmung zudem Sekundärströmungen 58 auf, die zusätzlich zur lokal guten Durchmischung der Verwirbelung eine Homogenisierung des Gemisches über die gesamte Querschnittsfläche eines Luftzufuhr-Ringkanals, in dem das Verwirbelungselement eingebaut ist (s. Fig 1), ermöglichen. Die Ausgestaltung des Verwirbelungselementes 4 hat gleichzeitig zur Folge, daß der durch die Verwirbelung hervorgerufene Druckverlust gering ist.A flow of combustion air through the swirling element 4 10, normal to the interface 56 in the interior of the truncated cone has the consequence that on the narrow sides 51b of the deflection elements 51 form vertebrae 57. In the pouring Medium introduced fuel 11 is caused by this turbulence intensively mixed with the combustion air 10. The inclination the deflection elements 51 also characterize the main flow secondary flows 58 in addition to the locally good Mixing the swirling homogenizes the mixture over the entire cross-sectional area of an air supply ring duct, in which the swirling element is installed (see Fig 1), enable. The design of the swirling element 4 has the consequence that the by the Swirling pressure loss is low.

    Claims (11)

    1. Burner (1) for fluidic fuels, in particular for use in a gas-turbine plant, having an air duct (2) for the feed of combustion air (10), and a fuel duct (3) for the feed of fuel (11), in which a vortex element (4) for generating highly turbulent combustion air (10) and an inlet (6) for fuel (11) from the fuel duct (3) into the air duct (2) are provided on the downstream side of the vortex element (4), the vortex element (4) having
      a) a first boundary ring (52) having an axis of symmetry (59),
      b) a second, larger boundary ring (53), the centre of which lies on the axis of symmetry (59),
      c) a connecting area (56) which is stretched out by the two boundary rings (52, 53),
      d) along circles (55a, 55b, 55c) which lie on the connecting area (56) and whose respective centre lies on the axis of symmetry (59), a multiplicity of flat deflecting elements (51), which are each inclined relative to a normal of the connecting area (56).
    2. Burner (1) according to Claim 1, in which the vortex element (4) is designed in such a way that the turbulent flow of combustion air (10) which can be generated at the vortex element (4) has essentially no zones of backflowing combustion air (10).
    3. Burner (1) according to one of the preceding claims, in which swirl blades (5) are arranged in the air duct (2) on the downstream side of the vortex element (4).
    4. Burner (1) according to Claim 3, in which at least one of the swirl blades (5) is designed as a hollow blade (5a) from which the fuel (11) can be admitted.
    5. Burner (1) according to one of the preceding claims, which is designed as a premix or hybrid burner for use in a gas-turbine plant, having an air feed duct (2), in particular a narrowing annular duct, which encloses at least three further annular ducts arranged in particular concentrically to the air-feed duct (2) and intended for feeding fluidic media, in which case two of these ducts serve to supply a pilot burner (9), and a pilot flame for maintaining the combustion can be produced by the pilot burner (9).
    6. Burner (1) according to one of the preceding claims, in which the connecting area (56) of the vortex element (4) is less than half the circular area enclosed by the larger boundary ring (53).
    7. Burner (1) according to one of the preceding claims, in which the diameter of the larger boundary ring (53) of the vortex element (4) is less than one metre, preferably 40 cm to 60 cm.
    8. Burner (1) according to one of the preceding claims, in which the deflecting elements (51) of the vortex element (4) which are allocated to one circle (55a, 55b, 55c) are at an equal distance from one another.
    9. Burner (1) according to one of the preceding claims, each deflecting element (51) of the vortex element (4) narrowing from the connecting area (56) to a separation edge (51b) for generating vortices (57), in which case it has in particular an approximately trapezoidal or triangular shape.
    10. Burner (1) according to one of the preceding claims, the deflecting elements (51) of the vortex element (4) which are allocated to one circle (55a, 55b, 55c) being inclined in the same direction.
    11. Burner (1) according to Claim 10, the deflecting elements (51) arranged on circles (55a, 55b, 55c) of the vortex element (4) which are adjacent to one another being inclined in opposite directions.
    EP97951835A 1996-12-20 1997-12-08 Burner for fluid fuels Expired - Lifetime EP0956475B1 (en)

    Applications Claiming Priority (5)

    Application Number Priority Date Filing Date Title
    DE19653474 1996-12-20
    DE19653473 1996-12-20
    DE19653474 1996-12-20
    DE19653473 1996-12-20
    PCT/DE1997/002858 WO1998028574A2 (en) 1996-12-20 1997-12-08 Burner for liquid fuels, method of operating a burner, and swirling element

    Publications (2)

    Publication Number Publication Date
    EP0956475A2 EP0956475A2 (en) 1999-11-17
    EP0956475B1 true EP0956475B1 (en) 2001-09-26

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    EP (1) EP0956475B1 (en)
    JP (1) JP4127858B2 (en)
    DE (1) DE59704739D1 (en)
    WO (1) WO1998028574A2 (en)

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    Also Published As

    Publication number Publication date
    WO1998028574A2 (en) 1998-07-02
    WO1998028574A3 (en) 1998-09-17
    JP4127858B2 (en) 2008-07-30
    DE59704739D1 (en) 2001-10-31
    EP0956475A2 (en) 1999-11-17
    JP2001507115A (en) 2001-05-29
    US6189320B1 (en) 2001-02-20

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