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EP2171354B1 - Burner - Google Patents

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Publication number
EP2171354B1
EP2171354B1 EP08775346A EP08775346A EP2171354B1 EP 2171354 B1 EP2171354 B1 EP 2171354B1 EP 08775346 A EP08775346 A EP 08775346A EP 08775346 A EP08775346 A EP 08775346A EP 2171354 B1 EP2171354 B1 EP 2171354B1
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EP
European Patent Office
Prior art keywords
inlet
burner
fuel
section
channel
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EP08775346A
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German (de)
French (fr)
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EP2171354A2 (en
Inventor
Harald Schütz
Guido Schmitz
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Deutsches Zentrum fuer Luft und Raumfahrt eV
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Deutsches Zentrum fuer Luft und Raumfahrt eV
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Publication of EP2171354A2 publication Critical patent/EP2171354A2/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2203/00—Gaseous fuel burners
    • F23D2203/007—Mixing tubes, air supply regulation

Definitions

  • the invention relates to a burner with an inlet, which has inlets for fuel and air, and a mixing section adjoining the inlet.
  • EP 1 096 202 A describes a mixing device for a burner with an inlet with inlets for exhaust gas and for fuel and a fuel lance.
  • the inlet is adjoined by a mixing section arranged along the burner axis, which opens into a combustion chamber to form a flame.
  • the inlet has a substantially rectangular cross-section, the mixing section forms a round channel.
  • a burner which has an inlet with coaxial inlets for fuel and air.
  • the burner inlet is followed by a mixing section in which fuel and air mix before the mixture enters a combustion chamber.
  • Fuel and air have such a flow impulse that combustion takes place only in the combustion chamber.
  • DE 23 52 204 A1 describes a cylindrical combustion chamber surrounded by a gas inlet annular chamber and a heat exchanger. The combustion gases leaving the combustion chamber are passed through the heat exchanger.
  • a rectangular burner and flame tube member having a cylindrical main combustion chamber or a cylindrical burner and flame tube member having a rectangular main combustion chamber may be combined to form an overall plant.
  • EP 1 112 972 A1 describes a burner with a rectangular or round burner block, which is surrounded by a nozzle ring, from which an inert gas emerges.
  • the inert gas generates an annular protective gas jacket of rectangular cross-section around the flame.
  • a pulverized coal combustion apparatus is disclosed in US Pat EP 0 672 863 A2 described.
  • a throttle point is provided through the fuel-air mixture to concentrate the flow.
  • the combustion temperature is regulated by an excess of combustion air through the burner.
  • the mixing behavior of a burner can now be characterized by the extent to which occurring ⁇ inhomogeneities in the burner are reduced before entering the combustion chamber. In the best case one obtains a homogeneous profile with the ⁇ -value of the assigned global mixture.
  • the corresponding adiabatic combustion temperature of the global mixture may thus be considered to be the lower limit of the optimum maximum combustion temperature to be achieved, provided there is no additional heat extraction.
  • the degree of approximation to this ideal state characterizes the quality of mixing of each burner.
  • the invention has for its object to provide a burner with improved mixing behavior to reduce nitrogen oxide formation.
  • the burner according to the invention is defined by the patent claim 1. It has an inlet with a substantially rectangular cross-section, wherein two parallel walls define a clear width:
  • the mixing section forms a round channel whose width is greater than the clear width between the parallel walls, so that in the flow direction widening transition stages are formed.
  • transverse flows are initiated at the transition stages, by means of which the mixing process is greatly improved by increasing the turbulently diffused transport and the induction of a convective secondary transport.
  • This is achieved by the combustion air is transferred from a rectangular channel into a channel with a round cross-section. Rectangular channel and round channel are "inline", d. H. arranged on the same burner axis and form on its transition surface two mutually parallel stages (transition stages).
  • the result is a convective-diffusive transport of the fuel-air mixture and a strong and uniform spread of the fuel in the radial direction.
  • the maximum fuel concentration at the outlet of the mixing section is thus low and the distribution of the fuel over the cross section of the mixing channel is improved.
  • the transition stages between square and round cross-section cause the induction of four secondary vortices, each rotating about a parallel to the burner axis, but radially offset, extending vortex axis.
  • the rotations of adjacent secondary vortices have opposite directions of rotation.
  • the dimension of the inlet is rectangular to the clear width greater than the width of the channel. This means that the inlet overhangs the round channel laterally.
  • the aspect ratio of the round channel-congruent portion of the face of the inlet should be about 2/3 of the area of the round channel.
  • the cross sections of the surface of the inlet and the surface of the round channel should be about the same size.
  • the ratio of the lengths of the mutually perpendicular sides of the inlet is preferably 2.5 to 3.5.
  • the inlet contains a fuel lance that ends at a distance in front of the mixing section.
  • the burner after the Figures 1-5 has an inlet 10, which consists of a tube of substantially rectangular cross-section.
  • the inlet 10 has two pairs of parallel walls.
  • a fuel lance 12 is arranged along the longitudinal axis of the inlet 10, which forms the burner axis 11, a fuel lance 12 is arranged. This consists of a tube of round cross-section.
  • the fuel lance 12 is supplied with fuel 13, while the space surrounding the fuel lance 12 of the inlet 10 is supplied with air 14.
  • fuel for example, methane (CH 4 ) is used. Both the fuel and the air are supplied at high pressures.
  • the fuel lance 12 terminates at a distance in front of the outlet end 15 of the inlet 10.
  • a mixing section 20 connects. This consists of a tube 21 of round cross section, which forms the channel.
  • the cylindrical tube 21 is arranged coaxially with the burner axis 17 and sealingly connected to the outlet end of the inlet 10.
  • the outlet end 22 of the mixing section 20 is open.
  • the mixing section opens here into a combustion chamber 23, in which a flame 24 is formed.
  • the inner diameter D of the tube 21 is greater than the clear width W of the inlet 10, which is defined by the mutual distance between two parallel walls of the inlet. Therefore, at each of the four parallel walls of the inlet 10 at the outlet end 15, a transition stage 25 is formed in which the respective side wall recedes in the flow path of the gas mixture.
  • the walls of the inlet 10 project beyond the contour of the channel 17 on opposite sides.
  • the surfaces of the inlet 10 and the channel 17 behave approximately like 1: 1.
  • the area ratio of the inlet 10 is approximately 2/3 of the area of the round channel 17.
  • the dimension W r of the inlet 10 at right angles to the clear width W is greater than the width D of the channel 17
  • This channel design results in a radial pulse on the mixture flow behind the outlet end 15 of the inlet 10.
  • a total of four vortices are distributed around the circumference in the mixing tube, which will be explained below.
  • the total length L1 of the inlet 10 is 14 mm and the length of the fuel lance 12 is 11 mm, so that the fuel lance ends at a distance of 3 mm in front of the outlet end 15.
  • the length of the mixing section 20 in this example is 30-40 mm.
  • FIGS. 4 and 5 the flow conditions in the mixing section 20 are shown.
  • the air temperature is 720K, bringing the adiabatic flame temperature to about 1750K. With ideal, ie complete mixing, this results in a NO x emission of about 2 ppm.
  • the streamline in FIG. 5 shows that the flow from the rectangular inlet preferably flows in the region of the largest step height. In the further course of the flow in the mixing section this is compensated for continuity reasons by the formation of four axisymmetric secondary vortices W1 - W4.
  • the secondary vortices W1 - W4 are each located in a quadrant of the cross section of the mixing section 20.
  • the directions of rotation of two adjacent secondary vortices are opposite.
  • the secondary vortex carries the fuel outwards and makes the fuel distribution even.
  • the transition stages 25 cause a velocity component in the transverse direction.
  • FIG. 6 shows an annular burner system, as used for example in stationary gas turbines.
  • Numerous burners B of the type described above are arranged in a ring, so that they are in a common Open combustion chamber 23.
  • the inlets 10 of the individual burners B are delimited from one another. They are curved to give the overall ring structure.
  • the burner according to the invention is particularly suitable for gas turbines both for energy production and in aircraft. But it can also be used for heating purposes.

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

Abstract

A burner having an inlet (10) and a mixing path (20) is designed such that the inlet (10) has a rectangular cross section. The mixing path (20) adjacent thereto has a round cross section and a larger diameter, thus forming four transitional stages (25). The transitional stages (25) form two secondary vortices, thus improving the distribution of the fuel in the radial direction. The burner provides combustion with low emissions of hazardous substances, and with low emission of nitrogen oxides.

Description

Die Erfindung betrifft einen Brenner mit einem Einlauf, der Einlässe für Brennstoff und Luft aufweist und einer sich an den Einlauf anschließenden Mischstrecke.The invention relates to a burner with an inlet, which has inlets for fuel and air, and a mixing section adjoining the inlet.

EP 1 096 202 A , als nächstliegender Stand der Technik, beschreibt eine Mischeinrichtung für einen Brenner mit einem Einlauf mit Einlässen für Abgas und für Brennstoff und einer Brennstofflanze. An den Einlauf schließt sich eine längs der Brennerachse angeordnete Mischstrecke an, die in eine Brennkammer zur Ausbildung einer Flamme mündet. Der Einlauf hat einen im wesentlichen rechteckigen Querschnitt, die Mischstrecke bildet einen runden Kanal. EP 1 096 202 A , as the closest prior art, describes a mixing device for a burner with an inlet with inlets for exhaust gas and for fuel and a fuel lance. The inlet is adjoined by a mixing section arranged along the burner axis, which opens into a combustion chamber to form a flame. The inlet has a substantially rectangular cross-section, the mixing section forms a round channel.

In EP 0 463 218 B1 ist ein Brenner beschrieben, der einen Einlauf mit koaxialen Einlässen für Brennstoff und Luft aufweist. An den Brennereinlauf schließt sich eine Mischstrecke an, in der Brennstoff und Luft sich mischen bevor das Gemisch in eine Brennkammer eintritt. Treibstoff und Luft haben einen solchen Strömungsimpuls, dass eine Verbrennung erst in der Brennkammer stattfindet.In EP 0 463 218 B1 a burner is described which has an inlet with coaxial inlets for fuel and air. The burner inlet is followed by a mixing section in which fuel and air mix before the mixture enters a combustion chamber. Fuel and air have such a flow impulse that combustion takes place only in the combustion chamber.

In DE 43 29 237 A1 ist eine Anordnung zur Vergleichmäßigung der Staubbeladung eines Gasstromes in einem Kanal beschrieben. Hierbei wird ein Kohlenstaub-Trägergas-Gemischstrom einem Brenner zugeführt. In einem Fall ist eine rechteckige Anströmleitung vorgesehen, die Seitenprallelemente sowie Lenk- und Leitelemente zur Führung des Staubstromes und zur Ableitung in die Mitte der Anströmleitung aufweist. Die Anströmleitung mündet in einen Konus, der mit seinem rückwärtigen Ende die Anströmleitung umgibt und dort Lufteinlässe aufweist. Das Staub-Luft-Gemisch durchläuft einen Luftring und wird in einer Brennkammer verbrannt.In DE 43 29 237 A1 an arrangement for equalizing the dust loading of a gas stream in a channel is described. Here, a coal dust-carrier gas mixture stream is fed to a burner. In one case is a rectangular Anströmleitung provided, the side impact elements and steering and guiding elements for guiding the dust flow and for discharge into the middle of the Anströmleitung has. The inflow line opens into a cone which surrounds the inflow line with its rear end and has air inlets there. The dust-air mixture passes through an air ring and is burned in a combustion chamber.

DE 23 52 204 A1 beschreibt eine zylindrische Brennkammer, die von einer Gaseintritts-Ringkammer und von einem Wärmetauscher umgeben ist. Die aus der Brennkammer austretenden Verbrennungsgase werden durch den Wärmetauscher geleitet. In einer Ausführungsform kann ein rechteckiger Brenner- und Flammrohrteil mit einem zylindrischen Hauptbrennraum oder ein zylindrischer Brenner- und Flammrohrteil mit einem rechteckigen Hauptbrennraum zu einer Gesamtanlage kombiniert werden. DE 23 52 204 A1 describes a cylindrical combustion chamber surrounded by a gas inlet annular chamber and a heat exchanger. The combustion gases leaving the combustion chamber are passed through the heat exchanger. In one embodiment, a rectangular burner and flame tube member having a cylindrical main combustion chamber or a cylindrical burner and flame tube member having a rectangular main combustion chamber may be combined to form an overall plant.

EP 1 112 972 A1 beschreibt eine Brennvorrichtung mit einem rechteckigen oder runden Brennerblock, der von einem Düsenring umgeben ist, aus welchem ein Inertgas austritt. Das Inertgas erzeugt einen ringförmigen Schutzgasmantel von rechteckigem Querschnitt um die Flamme herum. EP 1 112 972 A1 describes a burner with a rectangular or round burner block, which is surrounded by a nozzle ring, from which an inert gas emerges. The inert gas generates an annular protective gas jacket of rectangular cross-section around the flame.

Eine Verbrennungsvorrichtung für pulverisierte Kohle ist in EP 0 672 863 A2 beschrieben. Hierin ist eine Drosselstelle im Wege des Brennstoff-Luft-Gemisches vorgesehen, um die Strömung zu konzentrieren.A pulverized coal combustion apparatus is disclosed in US Pat EP 0 672 863 A2 described. Herein, a throttle point is provided through the fuel-air mixture to concentrate the flow.

Bei der Verbrennung ist es im Sinne einer Reduzierung des NOx-Ausstoßes wichtig, eine gute Durchmischung des Brennstoffs mit der Luft und eine möglichst niedrige maximale Verbrennungstemperatur zu erreichen. Der Grad der Mischung im Austritt der Brennerdüse hat einen ganz wesentlichen Einfluss auf die nachfolgenden Verbrennungsvorgänge in der Brennkammer. Dies gilt insbesondere im Hinblick auf die Stickoxidbildung (NOx), die ihrerseits maßgeblich durch die lokale Verbrennungstemperatur (Zeldovich oder thermisches NO) bestimmt ist. Das Ziel einer bestmöglichen Reduktion der Stickoxidemission lässt sich folglich dadurch erreichen, indem man durch geeignete Kontrolle der Mischungs- und Verbrennungsprozesse die Verbrennungstemperatur so gering wie möglich hält (Tmax < 1750 - 1800 K). Dies lässt sich entweder durch starken Wärmeentzug im Brennraum mittels Wärmetauscher oder durch Zumischung von inerten, an den chemischen Reaktionen nur als Drittkörper beteiligter Gase (Luft, N2, Ar, ... usw.) erreichen. Im Falle von Gasturbinenbrennkammern wird die Verbrennungstemperatur durch einen Überschuss an Verbrennungsluft durch den Brenner reguliert. Die maßgebliche Kennzahl ist hierbei die Luftzahl λ, gebildet aus dem molaren Verhältnis von Luft zu Brennstoff bezogen auf die stöchiometrische Zusammensetzung (λ=1). Für doppelten Luftüberschuss beispielsweise gilt dann λ=2. Im Brenner selbst werden Brennstoff und Luft zusammengeführt und es entstehen zunächst auch bei hohem Luftüberschuss stöchiometrische Bereiche. Das Mischungsverhalten eines Brenners lässt sich nun dadurch charakterisieren, in welchem Maße auftretende λ -Inhomogenitäten im Brenner vor Eintritt in die Brennkammer abgebaut werden. Im besten Fall erreicht man ein homogenes Profil mit dem λ-Wert der zugeordneten globalen Mischung. Die entsprechende adiabate Verbrennungstemperatur der globalen Mischung kann somit als die untere Grenze der optimaler Weise zu erreichenden maximalen Verbrennungstemperatur angesehen werden, vorausgesetzt, es findet kein zusätzlicher Wärmeentzug statt. Der Grad der Annäherung an diesen Idealzustand charakterisiert die Mischungsgüte eines jeden Brenners.When burning, it is important to achieve a good mixing of the fuel with the air and a lowest possible maximum combustion temperature in order to reduce the NO x emissions. The degree of mixing in the outlet of the burner nozzle has a very significant influence on the subsequent combustion processes in the combustion chamber. This is especially true with regard to the formation of nitrogen oxides (NO x ), which in turn significantly by the local combustion temperature (Zeldovich or thermal NO) is determined. The aim of the best possible reduction of nitrogen oxide emissions can thus be achieved by keeping the combustion temperature as low as possible by suitable control of the mixing and combustion processes (T max <1750 - 1800 K). This can be achieved either by strong heat extraction in the combustion chamber by means of heat exchangers or by admixing inert gases (air, N 2 , Ar,... Etc.) which are only involved as third-party in the chemical reactions. In the case of gas turbine combustors, the combustion temperature is regulated by an excess of combustion air through the burner. The relevant characteristic here is the air ratio λ, formed from the molar ratio of air to fuel based on the stoichiometric composition (λ = 1). For example, for double excess air, λ = 2. In the burner itself, fuel and air are brought together and initially stoichiometric areas are formed even with high excess air. The mixing behavior of a burner can now be characterized by the extent to which occurring λ inhomogeneities in the burner are reduced before entering the combustion chamber. In the best case one obtains a homogeneous profile with the λ-value of the assigned global mixture. The corresponding adiabatic combustion temperature of the global mixture may thus be considered to be the lower limit of the optimum maximum combustion temperature to be achieved, provided there is no additional heat extraction. The degree of approximation to this ideal state characterizes the quality of mixing of each burner.

Der Erfindung liegt die Aufgabe zugrunde, einen Brenner mit verbessertem Mischungsverhalten zur Verringerung der Stickoxidbildung zu schaffen.The invention has for its object to provide a burner with improved mixing behavior to reduce nitrogen oxide formation.

Der erfindungsgemäße Brenner ist durch den Patentanspruch 1 definiert. Er weist einen Einlauf mit im wesentlichen rechteckigem Querschnitt auf, wobei zwei parallele Wände eine lichte Weite begrenzen: Die Mischstrecke bildet einen runden Kanal, dessen Weite größer ist als die lichte Weite zwischen den parallelen Wänden, so dass dadurch in Strömungsrichtung sich erweiternde Übergangsstufen gebildet werden.The burner according to the invention is defined by the patent claim 1. It has an inlet with a substantially rectangular cross-section, wherein two parallel walls define a clear width: The mixing section forms a round channel whose width is greater than the clear width between the parallel walls, so that in the flow direction widening transition stages are formed.

Durch die Erfindung wird erreicht, dass an den Übergangsstufen Querströmungen initiiert werden, durch die der Mischungsvorgang durch Erhöhung des turbulent diffusen Transportes sowie der Induktion eines konvektiven Sekundärtransportes stark verbessert wird. Dies wird dadurch erzielt, dass die Verbrennungsluft aus einem Rechteckkanal in einen Kanal mit rundem Querschnitt überführt wird. Rechteckkanal und Rundkanal sind "inline", d. h. auf derselben Brennerachse angeordnet und bilden auf ihrer Übergangsfläche zwei zueinander parallele Stufen (Übergangsstufen) aus. Es entsteht ein konvektiv-diffusiver Transport des Brennstoff-Luft-Gemisches und eine starke und gleichmäßige Ausbreitung des Brennstoffs auch in radialer Richtung. Die maximale Brennstoffkonzentration am Ausgang der Mischstrecke ist somit gering und die Verteilung des Brennstoffs über den Querschnitt des Mischkanals wird verbessert. Die Folge ist eine Reduktion der thermischen Stickoxidbildung. Die Übergangsstufen zwischen eckigem und rundem Querschnitt bewirken die Induktion von vier Sekundärwirbeln, die jeweils um eine parallel zu der Brennerachse, jedoch radial versetzt, verlaufende Wirbelachse rotieren. Die Rotationen benachbarter Sekundärwirbel haben entgegengesetzten Drehsinn.By means of the invention it is achieved that transverse flows are initiated at the transition stages, by means of which the mixing process is greatly improved by increasing the turbulently diffused transport and the induction of a convective secondary transport. This is achieved by the combustion air is transferred from a rectangular channel into a channel with a round cross-section. Rectangular channel and round channel are "inline", d. H. arranged on the same burner axis and form on its transition surface two mutually parallel stages (transition stages). The result is a convective-diffusive transport of the fuel-air mixture and a strong and uniform spread of the fuel in the radial direction. The maximum fuel concentration at the outlet of the mixing section is thus low and the distribution of the fuel over the cross section of the mixing channel is improved. The result is a reduction of thermal nitrogen oxide formation. The transition stages between square and round cross-section cause the induction of four secondary vortices, each rotating about a parallel to the burner axis, but radially offset, extending vortex axis. The rotations of adjacent secondary vortices have opposite directions of rotation.

Vorzugsweise ist die Abmessung des Einlaufs rechteckig zu der lichten Weite größer als die Weite des Kanals. Dies bedeutet, dass der Einlauf den runden Kanal seitlich überragt. Das Querschnittsverhältnis des mit dem runden Kanal deckungsgleichen Anteils der Fläche des Einlaufs sollte etwa 2/3 der Fläche des runden Kanals betragen. Die Querschnitte der Fläche des Einlaufs und der Fläche des runden Kanals sollten etwa gleich groß sein. Das Verhältnis der Längen der zueinander rechtwinklig verlaufenden Seiten des Einlaufs beträgt vorzugsweise 2,5 bis 3,5.Preferably, the dimension of the inlet is rectangular to the clear width greater than the width of the channel. This means that the inlet overhangs the round channel laterally. The aspect ratio of the round channel-congruent portion of the face of the inlet should be about 2/3 of the area of the round channel. The cross sections of the surface of the inlet and the surface of the round channel should be about the same size. The ratio of the lengths of the mutually perpendicular sides of the inlet is preferably 2.5 to 3.5.

Gemäß einer bevorzugten Ausführungsform der Erfindung enthält der Einlauf eine Brennstofflanze, die im Abstand vor der Mischstrecke endet.According to a preferred embodiment of the invention, the inlet contains a fuel lance that ends at a distance in front of the mixing section.

Im Folgenden wird unter Bezugnahme auf die Zeichnungen ein Ausführungsbeispiel der Erfindung näher erläutert.In the following an embodiment of the invention will be explained in more detail with reference to the drawings.

Es zeigen:

Fig. 1
einen Längsschnitt durch einen Brenner nach der Erfindung,
Fig. 2
einen Schnitt entlang der Linie II-II von Figur 1,
Fig. 3
einen Schnitt entlang der Linie III-III von Figur 1,
Fig. 4
eine perspektivische Darstellung der vier sich in der Mischkammer ausbildenden und in dieser fortschreitenden Sekundärwirbel,
Fig. 5
eine Darstellung der Strömungsvektoren in einer Querebene des runden Kanals und
Fig. 6
eine Stirnansicht in die Brennkammer eines Ringbrennersystems mit zahlreichen Brennern.
Show it:
Fig. 1
a longitudinal section through a burner according to the invention,
Fig. 2
a section along the line II-II of FIG. 1 .
Fig. 3
a section along the line III-III of FIG. 1 .
Fig. 4
a perspective view of the four forming in the mixing chamber and in this progressive secondary vortex,
Fig. 5
a representation of the flow vectors in a transverse plane of the round channel and
Fig. 6
an end view into the combustion chamber of a ring burner system with numerous burners.

Der Brenner nach den Figuren 1-5 weist einen Einlauf 10 auf, der aus einem Rohr von im wesentlichen rechteckigem Querschnitt besteht. Der Einlauf 10 hat zwei Paare jeweils paralleler Wände. Entlang der Längsachse des Einlaufs 10, welche die Brennerachse 11 bildet, ist eine Brennstofflanze 12 angeordnet. Diese besteht aus einem Rohr von rundem Querschnitt. Die Brennstofflanze 12 wird mit Brennstoff 13 versorgt, während der die Brennstofflanze 12 umgebende Raum des Einlaufs 10 mit Luft 14 versorgt wird. Als Brennstoff wird beispielsweise Methan (CH4) benutzt. Sowohl der Brennstoff als auch die Luft werden mit hohen Drücken zugeführt. Die Brennstofflanze 12 endet in einem Abstand vor dem Auslassende 15 des Einlaufs 10.The burner after the Figures 1-5 has an inlet 10, which consists of a tube of substantially rectangular cross-section. The inlet 10 has two pairs of parallel walls. Along the longitudinal axis of the inlet 10, which forms the burner axis 11, a fuel lance 12 is arranged. This consists of a tube of round cross-section. The fuel lance 12 is supplied with fuel 13, while the space surrounding the fuel lance 12 of the inlet 10 is supplied with air 14. As fuel, for example, methane (CH 4 ) is used. Both the fuel and the air are supplied at high pressures. The fuel lance 12 terminates at a distance in front of the outlet end 15 of the inlet 10.

An den Einlauf 10 schließt sich eine Mischstrecke 20 an. Diese besteht aus einem Rohr 21 von rundem Querschnitt, das den Kanal bildet. Das zylindrische Rohr 21 ist koaxial zur Brennerachse 17 angeordnet und abdichtend mit dem Auslassende des Einlaufs 10 verbunden. Das Auslassende 22 der Mischstrecke 20 ist offen. Die Mischstrecke mündet hier in eine Brennkammer 23, in der sich eine Flamme 24 ausbildet.At the inlet 10, a mixing section 20 connects. This consists of a tube 21 of round cross section, which forms the channel. The cylindrical tube 21 is arranged coaxially with the burner axis 17 and sealingly connected to the outlet end of the inlet 10. The outlet end 22 of the mixing section 20 is open. The mixing section opens here into a combustion chamber 23, in which a flame 24 is formed.

Der Innendurchmesser D des Rohres 21 ist größer als die lichte Weite W des Einlaufs 10, welche durch den gegenseitigen Abstand zweier paralleler Wände des Einlaufs definiert wird. Daher ist an jeder der vier parallelen Wände des Einlaufs 10 am Auslassende 15 eine Übergangsstufe 25 ausgebildet, bei der im Strömungsweg des Gasgemisches die betreffende Seitenwand zurückweicht. Die Wände des Einlaufs 10 überragen nach entgegengesetzten Seiten hin die Kontur des Kanals 17. Die Flächen des Einlaufs 10 und des Kanals 17 verhalten sich etwa wie 1:1. Wie aus den Figuren 3 und 5 ergibt, beträgt das Querschnittsverhältnis des mit dem runden Kanal 17 deckungsgleichen Anteils der Fläche des Einlaufs 10 etwa 2/3 der Fläche des runden Kanals 17. Die Abmessung Wr des Einlaufs 10 rechtwinklig der lichten Weite W ist größer als die Weite D des Kanals 17. Durch diese Kanalgestaltung ergibt sich hinter dem Auslassende 15 des Einlaufs 10 ein radialer Impuls auf die Gemischströmung. Infolge der vier Übergangsstufen 25 ergeben sich um den Umfang verteilt im Mischrohr insgesamt vier Wirbel, die nachfolgend noch erläutert werden.The inner diameter D of the tube 21 is greater than the clear width W of the inlet 10, which is defined by the mutual distance between two parallel walls of the inlet. Therefore, at each of the four parallel walls of the inlet 10 at the outlet end 15, a transition stage 25 is formed in which the respective side wall recedes in the flow path of the gas mixture. The walls of the inlet 10 project beyond the contour of the channel 17 on opposite sides. The surfaces of the inlet 10 and the channel 17 behave approximately like 1: 1. Like from the Figures 3 and 5 the area ratio of the inlet 10 is approximately 2/3 of the area of the round channel 17. The dimension W r of the inlet 10 at right angles to the clear width W is greater than the width D of the channel 17 This channel design results in a radial pulse on the mixture flow behind the outlet end 15 of the inlet 10. As a result of the four transition stages 25, a total of four vortices are distributed around the circumference in the mixing tube, which will be explained below.

Bei einem praktisch ausgeführten Ausführungsbeispiel beträgt die Gesamtlänge L1 des Einlaufs 10 14 mm und die Länge der Brennstofflanze 12 beträgt 11 mm, so dass die Brennstofflanze im Abstand von 3 mm vor dem Auslassende 15 endet. Die Länge der Mischstrecke 20 beträgt bei diesem Beispiel 30 - 40 mm.In a practical embodiment, the total length L1 of the inlet 10 is 14 mm and the length of the fuel lance 12 is 11 mm, so that the fuel lance ends at a distance of 3 mm in front of the outlet end 15. The length of the mixing section 20 in this example is 30-40 mm.

In den Figuren 4 und 5 sind die Strömungsverhältnisse in der Mischstrecke 20 dargestellt. Bei einer gasturbinenrelevanten Anwendung sei eine Luftzahl der globalen Mischung von λ=2,16 vorgegeben. Die Lufttemperatur beträgt 720K, womit sich die adiabate Flammentemperatur zu ca. 1.750K ergibt. Bei idealer, d.h. vollständiger Durchmischung, ergibt sich daraus eine NOx-Emission von ca. 2 ppm. Der Stromlinienverlauf in Figur 5 zeigt, dass die Strömung aus dem Rechteckeinlauf bevorzugt in den Bereich der größten Stufenhöhe strömt. Im weiteren Verlauf der Strömung in der Mischstrecke wird dies aus Kontinuitätsgründen durch die Bildung von vier achsensymmetrischen Sekundärwirbeln W1 - W4 ausgeglichen. Der Brennstoff wird über die auf der Brennerachse angeordnete Brennstofflanze 12 axial in Höhe der Übergangsstufen direkt in die Symmetrieachse dieser vier Sekundärwirbel eingedüst. Der beschriebene konvektiv/diffusive Transport bewirkt eine relative starke und gleichmäßige Ausbreitung des Brennstoffes in radialer Richtung. Figur 4 zeigt weiterhin, dass die anfänglich 100%-ige CH4-Konzentration am Brennstoffeinlass bis auf einen maximalen Wert von 8% (λ=1.2) auf der Brennerachse im Brenneraustrittsquerschnitt verdünnt wird. Demgegenüber zeigt ein kommerziell verfügbarer Vergleichsbrenner eine relativ hohe CH4-Konzentration von ca. 13% (λ=0.7). Der höhere minimale λ-Wert im Bereich der maximalen Brennstoffkonzentration führt schließlich zu lokal erheblich niedrigeren Maximaltemperaturen in der Brennkammer. Damit wird durch den Einsatz des vorgestellten neuen Brennerkonzepts das Potential zur Reduktion der thermischen Stickoxidbildung deutlich gesteigert.In the FIGS. 4 and 5 the flow conditions in the mixing section 20 are shown. For a gas turbine-relevant application, an air ratio of the global mixture of λ = 2.16 is given. The air temperature is 720K, bringing the adiabatic flame temperature to about 1750K. With ideal, ie complete mixing, this results in a NO x emission of about 2 ppm. The streamline in FIG. 5 shows that the flow from the rectangular inlet preferably flows in the region of the largest step height. In the further course of the flow in the mixing section this is compensated for continuity reasons by the formation of four axisymmetric secondary vortices W1 - W4. The fuel is injected via the arranged on the burner axis fuel lance 12 axially at the level of the transition stages directly into the axis of symmetry of these four secondary vortices. The described convective / diffusive transport causes a relatively strong and uniform spread of the fuel in the radial direction. FIG. 4 further shows that the initially 100% CH 4 concentration at the fuel inlet is diluted to a maximum value of 8% (λ = 1.2) on the burner axis in the burner outlet section. In contrast, a commercially available comparison burner shows a relatively high CH 4 concentration of about 13% (λ = 0.7). The higher minimum λ value in the region of the maximum fuel concentration ultimately leads to locally much lower maximum temperatures in the combustion chamber. This significantly increases the potential for reducing thermal nitrogen oxide formation through the use of the new burner concept presented.

Die Sekundärwirbel W1 - W4 befinden sich jeweils in einem Quadranten des Querschnitts der Mischstrecke 20. Die Drehrichtungen zweier benachbarter Sekundärwirbel sind entgegengesetzt. Durch die Sekundärwirbel wird der Brennstoff nach außen getragen und die Brennstoffverteilung wird vergleichmäßigt. Die Übergangsstufen 25 bewirken eine Geschwindigkeitskomponente in Querrichtung.The secondary vortices W1 - W4 are each located in a quadrant of the cross section of the mixing section 20. The directions of rotation of two adjacent secondary vortices are opposite. The secondary vortex carries the fuel outwards and makes the fuel distribution even. The transition stages 25 cause a velocity component in the transverse direction.

Figur 6 zeigt ein Ringbrennersystem, wie es beispielsweise in stationären Gasturbinen zur Anwendung kommt. Zahlreiche Brenner B der oben beschriebenen Art sind ringförmig angeordnet, so dass sie in eine gemeinsame Brennkammer 23 einmünden. Die Einläufe 10 der einzelnen Brenner B sind gegeneinander abgegrenzt. Sie sind gekrümmt, um insgesamt die Ringstruktur zu ergeben. FIG. 6 shows an annular burner system, as used for example in stationary gas turbines. Numerous burners B of the type described above are arranged in a ring, so that they are in a common Open combustion chamber 23. The inlets 10 of the individual burners B are delimited from one another. They are curved to give the overall ring structure.

Der erfindungsgemäße Brenner eignet sich insbesondere für Gasturbinen sowohl zur Energiegewinnung als auch in Flugzeugen. Er kann aber auch für Heizungszwecke eingesetzt werden.The burner according to the invention is particularly suitable for gas turbines both for energy production and in aircraft. But it can also be used for heating purposes.

Claims (6)

  1. A burner comprising an inlet (10), said inlet (10) comprising intake ducts for air and for fuel and said intake duct for fuel comprising a fuel lance (12), said burner further comprising a mixing path (20) following said inlet (10) along a burner axis (11) and extending along said burner axis, said mixing path entering a combustion chamber (23) for generating a flame, said inlet (10) having a substantially rectangular cross section wherein two parallel walls delimit a clear width (W), and said mixing path (20) forming a round channel (17) of a width (D) larger than said clear width (W) between said parallel walls, and said mixing path (20) being sealingly connected to said inlet (10) to thereby form transitional steps (25) widening in the flow direction.
  2. The burner according to claim 1, characterized in that the size (Wr) of the inlet (10) rectangularly to said clear width (W) is larger than the width (D) of the channel (17).
  3. The burner according to claim 1 or 2, characterized in that the cross-section ratio of that portion the area of the inlet (10) which is congruent with the round channel (17) is about 2/3 of the area of the round channel (17).
  4. The burner according to any one of claims 1-3, characterized in that the cross-section ratio of the area of the inlet relative to the area of the round channel is about 1:1.
  5. The burner according to any one of claims 1-4, characterized in that the ratio between the lengths of the sides of the inlet (10) is 2.5 to 3.5.
  6. The burner according to any one of claims 1-5, characterized in that said fuel lancet (12) terminates at a distance upstream of the mixing path (20).
EP08775346A 2007-08-04 2008-07-24 Burner Active EP2171354B1 (en)

Applications Claiming Priority (2)

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DE102007036953A DE102007036953B3 (en) 2007-08-04 2007-08-04 burner
PCT/EP2008/059744 WO2009019140A2 (en) 2007-08-04 2008-07-24 Burner

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EP2171354A2 EP2171354A2 (en) 2010-04-07
EP2171354B1 true EP2171354B1 (en) 2012-06-20

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DE102008032265B4 (en) 2008-07-09 2010-06-10 Deutsches Zentrum für Luft- und Raumfahrt e.V. incinerator
US9587823B2 (en) * 2009-03-25 2017-03-07 Wallace Horn Laminar flow jets
GB2533293A (en) * 2014-12-15 2016-06-22 Edwards Ltd Inlet assembly
FR3031771B1 (en) * 2015-01-20 2017-03-03 Commissariat Energie Atomique COMBUSTION SYSTEM HAVING ENHANCED TEMPERATURE
PL422320A1 (en) * 2017-07-24 2019-01-28 Instytut Lotnictwa Injector of over-rich air-fuel mixture into the combustion engine combustion chamber
DE102021103800B4 (en) 2021-02-18 2024-10-17 Viessmann Climate Solutions Se Method for operating a gas burner

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DE2352204B2 (en) * 1973-10-18 1976-01-22 Katec Katalytische Lufttechnik Betz & Co, 6461 Neuenhaßlau COMBUSTION DEVICE FOR COMBUSTION OF NUMBERS IN EXHAUST GASES
US4383820A (en) * 1980-10-10 1983-05-17 Technology Application Services Corporation Fuel gas burner and method of producing a short flame
ATE114364T1 (en) * 1990-06-29 1994-12-15 Wuenning Joachim METHOD AND DEVICE FOR BURNING FUEL IN A COMBUSTION ROOM.
DE4329237C2 (en) * 1993-08-24 1998-04-16 Ver Energiewerke Ag Method and arrangement for equalizing the dust loading of a coal dust / carrier gas mixture flow in the duct in front of a coal dust burner
JPH07260106A (en) * 1994-03-18 1995-10-13 Hitachi Ltd Pulverized coal combustion burner and pulverized coal combustion device
US6383462B1 (en) * 1999-10-26 2002-05-07 John Zink Company, Llc Fuel dilution methods and apparatus for NOx reduction
US6383461B1 (en) 1999-10-26 2002-05-07 John Zink Company, Llc Fuel dilution methods and apparatus for NOx reduction
US6367288B1 (en) * 1999-12-29 2002-04-09 Corning Incorporated Method and apparatus for preventing burner-hole build-up in fused silica processes
DE10128063A1 (en) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd burner system
US6652268B1 (en) * 2003-01-31 2003-11-25 Astec, Inc. Burner assembly

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WO2009019140A3 (en) 2009-05-28
US8246345B2 (en) 2012-08-21
WO2009019140A2 (en) 2009-02-12
DE102007036953B3 (en) 2009-04-02
US20110229836A1 (en) 2011-09-22
EP2171354A2 (en) 2010-04-07

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