EP0625673B1 - Premixing burner for operating an internal combustion engine, a combustion chamber of a gas turbo group or a combustion plant - Google Patents
Premixing burner for operating an internal combustion engine, a combustion chamber of a gas turbo group or a combustion plant Download PDFInfo
- Publication number
- EP0625673B1 EP0625673B1 EP94105929A EP94105929A EP0625673B1 EP 0625673 B1 EP0625673 B1 EP 0625673B1 EP 94105929 A EP94105929 A EP 94105929A EP 94105929 A EP94105929 A EP 94105929A EP 0625673 B1 EP0625673 B1 EP 0625673B1
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- EP
- European Patent Office
- Prior art keywords
- fuel
- throat
- premixing burner
- operating
- fuels
- 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
Links
- 238000002485 combustion reaction Methods 0.000 title claims description 27
- 239000000446 fuel Substances 0.000 claims description 48
- 239000007788 liquid Substances 0.000 claims description 8
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 3
- 238000010304 firing Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 description 7
- 230000015556 catabolic process Effects 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 239000003345 natural gas Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
- F23D11/40—Mixing tubes or chambers; Burner heads
-
- 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
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
-
- 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
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
-
- 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
-
- 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
- F23R3/36—Supply of different fuels
-
- 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
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
-
- 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
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Definitions
- the invention relates to a premix burner for operation an internal combustion engine, a combustion chamber of a gas turbine group or furnace and an associated process, which are used to burn fuels with very different Properties are suitable.
- Premix burners ie burners in which the premix zone is an integrated component of the burner itself and which are characterized by low NO x emissions, are known (EP-A1 0 321 809, 0 521 325 and US-A-3 982 392).
- the invention tries to avoid all these disadvantages. It is based on the task of creating a premix burner for the operation of an internal combustion engine, a combustion chamber of a gas turbine group or a combustion system and an associated method which have low NO x emissions, in which fuels with very different properties can be burned without problems and the function the burner is also ensured outside the design point or in the event of partial failure.
- this is the case with a premix burner from a swirl generator for the combustion air, a subsequent convergent part, one Narrowing point for the addition of liquid fuel a central lance and a downstream one Diffuser achieved in that the swirl generator is a double-cone burner with adjusted slot width and missing Fuel injection is, and that in the throat supply openings are arranged for further fuels, one Part of these feed openings are aligned radially and for the Supply of gaseous, dusty or liquid fuel is provided and at least a further part of the Feed openings aligned tangentially and for feeding provided by at least one other gaseous fuel is.
- this is the case with the method for operating the Premix burner achieved in that when operating with gaseous Fuels that have a high flame speed have the fuel through the openings in the constriction opposite to the direction of swirl of the combustion air be injected that when operating with gaseous fuels, which has a low flame speed and a have low calorific value, the fuel through the openings in the constriction in the same direction as the swirl direction of the combustion air be injected, and that when operating with liquid or dusty fuel the fuel in the constriction perpendicular to the direction of flow or just before Constriction with a central lance in the swirled combustion air is injected.
- the advantages of the invention include that when burning fuels with very different Properties the mixture before reaching the Flame front is complete and the flame does not reach the May interfere with the place of interference.
- the main reaction zone becomes purely aerodynamic without touching the burner wall, stabilized. There are also no backflow zones, Steps or sudden expansion in the flame zone.
- the burner also functions outside the design point and secured in the event of partial failure. Furthermore, the burner in an air or fuel graded combustion process applicable.
- cross-sectional profile is like this is adapted that no flow separation on the wall is possible is.
- the premix burner, in particular the diffuser is convectively coolable. This is even if the flame is applied to the end area of the diffuser safe burner operation guaranteed.
- the premix burner shown in Fig. 1 which for combustion of fuels with very different properties is used, consists of a swirl generator 1 for the combustion air 10, a subsequent one convergent part 2, a constriction 3 and a diffuser 4.
- a flow field with a possible constant total pressure generated Because of the vortex generated you can also the premix burner according to the invention as Designate vortex diffuser burner.
- the convergent part 2, the constriction 3 and the diffuser 4 are to avoid Secondary flows are rotationally symmetrical and in adapted to their cross-sectional course so that the extension is just so strong that there is no flow separation from the Wall.
- To the friction losses and, if necessary Keeping the surface to be cooled small is the length of the rotationally symmetrical parts as short as possible. With it result small mixed lengths.
- the size of the burner can be sufficient under the condition of one high Reynolds number in the burner and under the boundary conditions the desired thermal output and the desired Total length can be chosen arbitrarily.
- the swirl generator 1 is a double-cone burner with adjusted slot width of the air inlet slots 12 provided without the usual fuel injection.
- mixing zone i.e. where the fuel-air mixture is present (premix section 6, main reaction zone 7) no internals, e.g. Swirl generator or flame holder, available. Changes in swirl number are dependent on Fuel 9 possible without moving parts in the burner. It are also no backflow zones, steps or sudden extensions the flame zone in place, so that good flame stability (low pulsations) is reached.
- the main reaction zone 7 is due to the bursting swirl flow (Vortex Breakdown 5) purely aerodynamic, without the Touching the burner wall stabilized.
- the premix burner is operated with gaseous fuels, which has a high flame speed (short ignition delay times) the fuels must be in opposite directions to the swirl direction of the combustion air 10 in the narrow point 3 be injected (Fig. 2). This will cause the vortex breakdown 5 greatly weakened.
- gaseous fuels with low flame speed and low calorific value flame stabilization is used by the same direction Injection in relation to the swirl direction of the combustion air and thus by reinforcing the vortex breakdown 5 improved.
- the burner is a multifunctional system, because of how Fig. 2 shows, for example, low calorie Fuels 9a, natural gas 9b and hydrogen-containing gases 9c be used.
Description
Die Erfindung betrifft einen Vormischbrenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage und ein dazugehörendes Verfahren, welche zur Verbrennung von Brennstoffen mit stark unterschiedlichen Eigenschaften geeignet sind.The invention relates to a premix burner for operation an internal combustion engine, a combustion chamber of a gas turbine group or furnace and an associated process, which are used to burn fuels with very different Properties are suitable.
Vormischbrenner, also Brenner, bei denen die Vormischzone ein integrierter Bestandteil des Brenners selbst ist und die sich durch geringe NOx-Emissionen auszeichnen, sind bekannt (EP-A1 0 321 809, 0 521 325 und US-A-3 982 392).Premix burners, ie burners in which the premix zone is an integrated component of the burner itself and which are characterized by low NO x emissions, are known (EP-A1 0 321 809, 0 521 325 and US-A-3 982 392).
Bei diesen Brennern wird sichergestellt, dass die Zündung des Brennstoff-/Luftgemisches an einem Ort vonstatten geht, an dem keine zu grosse Strömungsgeschwindigkeit des Mediums vorherrscht. Zugleich wird dafür gesorgt, dass die Fortpflanzung der Flammenfont in Richtung des Brennerausganges, wo sich die Flammenfront einstellt, definiert erfolgt.These burners ensure that the ignition of the Fuel / air mixture takes place in one place which does not have too high a flow velocity of the medium. At the same time, it ensures that reproduction the flame font towards the burner exit, where the Flame front sets, defined takes place.
Bei den bekannten Vormischbrennern ergeben sich Probleme, wenn Brennstoffe mit stark unterschiedlichen Eigenschaften verbrannt werden sollen. Dann muss das Strömungsfeld so gestaltet sein, dass bei allen Brennstoffen sichergestellt ist, dass die Mischung vor dem Erreichen der Flammenzone abgeschlossen ist und die Flammen unter keinen Umständen an den Ort der Einmischung zurückschlagen. Zusätzlich dürfen in den Gebieten, die von der Flamme unter bestimmten Betriebsbedingungen erreicht werden, d.h. überall dort, wo ein Brennstoff-Luftgemisch vorhanden ist, keine ungekühlten Einbauten, wie Drallerzeuger oder Flammenhalter, vorhanden sein. Wenn z.B. im Gemischstrom Drallerzeuger angeordnet sind, ergeben sich die bekannten Nachteile, wie z.B. Belagsbildung oder Zerstörung der Drallschaufel durch Überhitzung.There are problems with the known premix burners, if fuels with very different properties to be burned. Then the flow field must be designed in this way be sure that all fuels are guaranteed that the mixture is completed before reaching the flame zone is and the flames under no circumstances to the Knock back the place of interference. In addition, in the Areas affected by the flame under certain operating conditions be achieved, i.e. wherever there is a fuel-air mixture is present, no uncooled internals, such as Swirl generator or flame holder. If e.g. Swirl generators are arranged in the mixture flow the known disadvantages, e.g. Formation of deposits or destruction the swirl vane due to overheating.
Ein weiterer Nachteil der bekannten Vormischbrenner besteht darin, dass ihr Betrieb ausserhalb des Auslegungspunktes und bei Teilversagen, z.B. bei Leckagen im Kühlluftsystem, problematisch ist. Versucht man nämlich, bei Teillastbetrieb magerer zu fahren, verschlechtert sich bei den bekannten Brennern der Ausbrand und die CO/UHC-Emissionen steigen stark an (CO/UHC-NOx-Schere).Another disadvantage of the known premix burners is that their operation outside the design point and in the event of partial failure, for example in the case of leaks in the cooling air system, is problematic. If you try to drive leaner at partial load, the burnout deteriorates with the known burners and the CO / UHC emissions increase sharply (CO / UHC-NO x scissors).
Die Erfindung versucht, all diese Nachteile zu vermeiden. Ihr liegt die Aufgabe zugrunde, einen Vormischbrenner für den Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder einer Feuerungsanlage und ein dazugehörendes Verfahren zu schaffen, die niedrige NOx-Emissionen aufweisen, bei denen Brennstoffe mit stark unterschiedlichen Eigenschaften problemlos verbrannt werden können und die Funktion des Brenners auch ausserhalb des Auslegungspunktes bzw. bei Teilversagen sichergestellt ist.The invention tries to avoid all these disadvantages. It is based on the task of creating a premix burner for the operation of an internal combustion engine, a combustion chamber of a gas turbine group or a combustion system and an associated method which have low NO x emissions, in which fuels with very different properties can be burned without problems and the function the burner is also ensured outside the design point or in the event of partial failure.
Erfindungsgemäss wird dies bei einem Vormischbrenner, bestehend aus einem Drallerzeuger für die Verbrennungsluft, einem sich daran anschliessenden konvergenten Teil, einer Engstelle für die Zugabe von flüssigem Brennstoff mittels einer zentralen Lanze und einem stromabwärts angeordneten Diffusor dadurch erreicht, dass der Drallerzeuger ein Doppelkegelbrenner mit angepasster Schlitzweite und fehlender Brennstoffeindüsung ist, und dass in der Engstelle Zufuhröffnungen für weitere Brennstoffe angeordnet sind, wobei ein Teil dieser Zufuhröffnungen radial ausgerichtet und für die Zufuhr von gasförmigem, staubförmigem oder flüssigem Brennstoff vorgesehen ist und mindestens ein weiterer Teil der Zufuhröffnungen tangential ausgerichtet und für die Zufuhr von mindestens einem weiteren gasförmigen Brennstoff vorgesehen ist.According to the invention, this is the case with a premix burner from a swirl generator for the combustion air, a subsequent convergent part, one Narrowing point for the addition of liquid fuel a central lance and a downstream one Diffuser achieved in that the swirl generator is a double-cone burner with adjusted slot width and missing Fuel injection is, and that in the throat supply openings are arranged for further fuels, one Part of these feed openings are aligned radially and for the Supply of gaseous, dusty or liquid fuel is provided and at least a further part of the Feed openings aligned tangentially and for feeding provided by at least one other gaseous fuel is.
Erfindungsgemäss wird dies bei dem Verfahren zum Betrieb des Vormischbrenners dadurch erreicht, dass beim Betrieb mit gasförmigen Brennstoffen, welche eine hohe Flammengeschwindigkeit haben, die Brennstoffe über die Öffnungen in der Engstelle gegensinnig zur Drallrichtung der Verbrennungsluft eingedüst werden, dass beim Betrieb mit gasförmigen Brennstoffen, welche eine geringe Flammengeschwindigkeit und einen geringen Heizwert haben, die Brennstoffe über die Öffnungen in der Engstelle gleichsinnig zur Drallrichtung der Verbrennungsluft eingedüst werden, und dass beim Betrieb mit flüssigem oder staubförmigem Brennstoff der Brennstoff in der Engstelle senkrecht zur Strömungsrichtung oder kurz vor der Engstelle mit einer zentralen Lanze in die verdrallte Verbrennungsluft eingedüst wird.According to the invention, this is the case with the method for operating the Premix burner achieved in that when operating with gaseous Fuels that have a high flame speed have the fuel through the openings in the constriction opposite to the direction of swirl of the combustion air be injected that when operating with gaseous fuels, which has a low flame speed and a have low calorific value, the fuel through the openings in the constriction in the same direction as the swirl direction of the combustion air be injected, and that when operating with liquid or dusty fuel the fuel in the constriction perpendicular to the direction of flow or just before Constriction with a central lance in the swirled combustion air is injected.
Die Vorteile der Erfindung sind unter anderem darin zu sehen, dass bei der Verbrennung von Brennstoffen mit stark unterschiedlichen Eigenschaften die Mischung vor dem Erreichen der Flammenfront abgeschlossen ist und die Flamme nicht an den Ort der Einmischung zurückschlagen kann. Die Hauptreaktionszone wird rein aerodynamisch, ohne die Brennerwand zu berühren, stabilisiert. Ausserdem gibt es keine Rückströmzonen, Stufen oder plötzliche Erweiterungen in der Flammenzone. Die Funktion des Brenners ist auch ausserhalb des Auslegungspunktes und bei Teilversagen gesichert. Weiterhin ist der Brenner in einem luft- oder brennstoffgestuften Verbrennungsprozess einsetzbar.The advantages of the invention include that when burning fuels with very different Properties the mixture before reaching the Flame front is complete and the flame does not reach the May interfere with the place of interference. The main reaction zone becomes purely aerodynamic without touching the burner wall, stabilized. There are also no backflow zones, Steps or sudden expansion in the flame zone. The The burner also functions outside the design point and secured in the event of partial failure. Furthermore, the burner in an air or fuel graded combustion process applicable.
Es ist besonders zweckmässig, wenn der konvergente Teil, die Engstelle und der Diffusor rotationssymmetrisch ausgebildet sind, weil dann Sekundärströmungen vermieden werden und vor dem Vortex Breakdown nur kleine Turbulenzen vorhanden sind.It is particularly useful if the convergent part, the Constriction and the diffuser are rotationally symmetrical are because then secondary flows are avoided and before there is only little turbulence after the vortex breakdown.
Ferner ist es vorteilhaft, wenn der Querschnittsverlauf so angepasst ist, dass keine Strömungsablösung an der Wand möglich ist.It is also advantageous if the cross-sectional profile is like this is adapted that no flow separation on the wall is possible is.
Weiterhin ist vorteilhaft, wenn der Vormischbrenner, insbesondere der Diffusor, konvektiv kühlbar ist. Dadurch ist selbst bei einem Anlegen der Flamme im Endbereich des Diffusors ein sicherer Brennerbetrieb gewährleistet.It is also advantageous if the premix burner, in particular the diffuser is convectively coolable. This is even if the flame is applied to the end area of the diffuser safe burner operation guaranteed.
In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt.In the drawing is an embodiment of the invention shown.
Es zeigen:
- Fig. 1
- einen Längsschnitt des Vormischbrenners;
- Fig. 2
- einen Schnitt durch den engsten Querschnitt (Eindüsungsstelle) des Vormischbrenners.
- Fig. 1
- a longitudinal section of the premix burner;
- Fig. 2
- a section through the narrowest cross-section (injection point) of the premix burner.
Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Die Strömungsrichtung der Arbeitsmittel ist mit Pfeilen bezeichnet. It is only essential for understanding the invention Elements shown. The flow direction of the work equipment is marked with arrows.
Der in Fig. 1 dargestellte Vormischbrenner, welcher zur Verbrennung
von Brennnstoffen mit stark unterschiedlichen Eigenschaften
eingesetzt wird, besteht aus einem Drallerzeuger 1
für die Verbrennungsluft 10, einem sich daran anschliessenden
konvergenten Teil 2, einer Engstelle 3 und einem Diffusor 4.
Im Drallerzeuger 1 wird ein Strömungfeld mit einem möglichst
konstanten Totaldruck erzeugt. Aufgrund der erzeugten Wirbel
kann man den erfindungsgemässen Vormischbrenner auch als
Wirbeldiffusor-Brenner bezeichnen. Der konvergente Teil 2,
die Engstelle 3 und der Diffusor 4 sind zur Vermeidung von
Sekundärströmungen rotationssymmetrisch ausgebildet und in
ihrem Querschnittsverlauf so angepasst, dass die Erweiterung
gerade so stark ist, dass keine Strömungsablösung von der
Wand erfolgt. Um die Reibungsverluste und die gegebenenfalls
zu kühlende Oberfläche klein zu halten, ist die Länge der
rotationssymmetrischen Teile möglichst kurz. Damit ergeben
sich kleine Mischlängen.The premix burner shown in Fig. 1, which for combustion
of fuels with very different properties
is used, consists of a
Die Baugrösse des Brenners kann unter der Bedingung einer genügend hohen Reynoldszahl im Brenner und unter den Randbedingungen der gewünschten thermischen Leistung und der gewünschten Gesamtlänge beliebig gewählt werden.The size of the burner can be sufficient under the condition of one high Reynolds number in the burner and under the boundary conditions the desired thermal output and the desired Total length can be chosen arbitrarily.
Der Drallerzeuger 1 ist erfindunggemäss ein Doppelkegelbrenner
mit angepasster Schlitzweite der Lufteintrittsschlitze 12
ohne die sonst übliche Brennstoffeindüsung vorgesehen.According to the invention, the
Im konvergenten Teil 2 erhöht sich die Strömungsgeschwindigkeit,
bis sie an der Engstelle 3 ihren höchsten Wert hat.
Dort an der Engstelle 3, dem Ort der höchsten Strömungsgeschwindigkeit,
erfolgt die Einmischung des Brennstoffes 9.
Damit wird erreicht, dass sich der Brennstoff 9 schnell mit
der Verbrennungsluft 10 mischt, die Mischung vor dem Erreichen
der Flammenzone abgeschlossen ist und die Flamme unter
keinen Umständen an den Ort der Brennstoffeinmischung zurückschlagen
kann. Der zur Mischung erforderliche Brennstoffvordruck
ist nur gering. Öffnungnen 13 dienen dabei der Zufuhr
von gasförmigem Brennstoff 9, während eine zentral angeordnete
Lanze 11 zur Zufuhr von staubförmigem oder flüssigem
Brennstoff 9 vorgesehen ist. Die Zuführöffnungen 13 sind radial
oder tangential ausgerichtet.In
In der Mischzone, also dort, wo das Brennstoff-Luftgemisch
vorhanden ist (Vormischstrecke 6, Hauptreaktionszone 7) sind
keine Einbauten, wie z.B. Drallerzeuger oder Flammenhalter,
vorhanden. Drallzahländerungen sind in Abhängigkeit vom
Brennstoff 9 möglich ohne bewegliche Teile im Brenner. Es
sind auch keine Rückströmzonen, Stufen oder plötzliche Erweiterungen
der Flammenzone vorhanden, so dass eine gute Flammenstabilität
(geringe Pulsationen) erreicht wird.In the mixing zone, i.e. where the fuel-air mixture
is present (
Wegen der axialsymmetrischen Geometrie sind vor dem Vortex
Breakdown 5 nur kleine Turbulenzen vorhanden.Because of the axially symmetric geometry are in front of the
Die Hauptreaktionszone 7 wird durch die aufplatzende Drallströmung
(Vortex Breakdown 5) rein aerodynamisch, ohne die
Brennerwand zu berühren, stabilisiert.The
In dem in Fig. 1 dargestellten Ausführungsbeispiel wird der
divergente Teil der Brenners konvektiv gekühlt. Durch die
kombinierte Brenner- und Brennkammerkühlung 8 wird erreicht,
dass selbst bei einem Anlegen der Flamme im Endbereich des
Diffusors 4 noch ein sicherer Brennerbetrieb gewährleistet
wird. Selbstverständlich kann in einem anderen Ausführungsbeispiel
der gesamte Brenner durch konvektive Kühlung relativ
einfach vollständig gekühlt sein, deshalb ist er auch für den
Betrieb als Stufenbrenner in einem luft- oder brennstoffgestuften
System, z.B. als erste, zweite oder dritte Stufe geeignet. In the embodiment shown in Fig. 1 the
divergent part of the burner cooled convectively. Through the
combined burner and
Wird der Vormischbrenner mit gasförmigen Brennstoffen betrieben,
welche eine hohe Flammengeschwindigkeit (kurze Zündverzugszeiten)
haben, so müssen die Brennstoffe gegensinnig
zur Drallrichtung der Verbrennungsluft 10 in der Engstelle 3
eingedüst werden (Fig. 2). Dadurch wird der Vortex Breakdown
5 stark abgeschwächt. Werden dagegen gasförmige Brennstoffe
mit geringer Flammengeschwindigkeit und geringem Heizwert
verwendet, wird die Flammenstabilisierung durch gleichsinniges
Eindüsen in Bezug auf die Drallrichtung der Verbrennungsluft
und damit durch Verstärkung des Vortex Breakdowns 5
verbessert.If the premix burner is operated with gaseous fuels,
which has a high flame speed (short ignition delay times)
the fuels must be in opposite directions
to the swirl direction of the
Beim Betrieb des Brenners mit flüssigem oder staubförmigen
Brennstoff wird dieser im engsten Querschnitt, also an der
Engstelle 3, senkrecht zur Strömungsrichtung bzw. kurz vor
dem engsten Querschnitt mittels der zentralen Lanze 11 eingedüst.When operating the burner with liquid or dust
This becomes fuel in the narrowest cross-section, i.e. at the
Narrow 3, perpendicular to the flow direction or just before
the narrowest cross section injected by means of the
Der Brenner ist ein multifuelfähiges System, denn wie aus
Fig. 2 hervorgeht, können beispielsweise niederkalorige
Brennstoffe 9a, Erdgas 9b und wasserstoffhaltige Gase 9c
verwendet werden.The burner is a multifunctional system, because of how
Fig. 2 shows, for example,
Ein weiterer Vorteil besteht darin, dass er auch ausserhalb des Auslegungspunktes und bei Teilversagen, wenn beispielsweise im Kühlluftsystem Leckagen vorhanden sind, voll funktionsfähig ist. Schliesslich sind noch die geringen NOx-Emissionen hervorzuheben. Another advantage is that it is fully functional even outside the design point and in the event of partial failure, for example if there are leaks in the cooling air system. Finally, the low NO x emissions should be emphasized.
- 11
- DrallerzeugerSwirl generator
- 22nd
- konvergenter Teilconvergent part
- 33rd
- EngstelleConstriction
- 44th
- DiffusorDiffuser
- 55
- Vortex BreakdownVortex breakdown
- 66
- VormischstreckePremixing section
- 77
- HauptreaktionszoneMain reaction zone
- 88th
- kombinierte Brenner- und Brennkammerkühlungcombined burner and combustion chamber cooling
- 99
- Brennstofffuel
- 9a9a
- niederkaloriger Brennstofflow calorific fuel
- 9b9b
- Erdgasnatural gas
- 9c9c
- wasserstoffhaltige Gasehydrogen-containing gases
- 1010th
- VerbrennungsluftCombustion air
- 1111
- zentrale Brennstofflanzecentral fuel lance
- 1212th
- LufteintrittsschlitzeAir inlet slots
- 1313
- Zufuhröffnungen für BrennstoffFeed openings for fuel
Claims (6)
- Premixing burner for the operation of an internal combustion engine, a combustion chamber of a gas turbine group or a firing system, comprising a swirl generator (1) for combustion air (10), a convergent part (2) adjoining it, a throat (3) for the supply of liquid fuel (9) by means of a central lance (11) and a diffuser (4) arranged downstream, in that the swirl generator (1) is a double-cone burner with an adapted slot width and with the injection of fuel missing, and in that supply openings (13) for further fuels (9) are arranged in the throat (3), some of the supply openings (13) being radially aligned and intended for the supply of gaseous, pulverized or liquid fuel (9) and at least some of the supply openings (13) being tangentially aligned and intended for the supply of at least one further gaseous fuel (9).
- Premixing burner according to Claim 1, characterized in that the convergent part (2), the throat (3) and the diffuser (4) have a rotationally symmetrical configuration.
- Premixing burner according to Claim 1 and 2, characterized in that the variation in cross section is adapted in such a way that no flow separation is possible at the wall.
- Premixing burner according to Claim 1 and 2, characterized in that the premixing burner can be completely cooled convectively.
- Premixing burner according to Claim 1 and 2, characterized in that it is mainly the diffuser (4) which can be cooled convectively.
- Method for operating a premixing burner according to Claim 1, characterized in that, when operating with gaseous fuels which have a high flame speed, the fuels are introduced via the openings (13) in the throat (3) in the opposite direction to the swirl direction of the combustion air (10), in that when operating with gaseous fuels which have a low flame speed and a low calorific value, the fuels are introduced via the openings (13) in the throat (3) in the same direction as the swirl direction of the combustion air (10) and in that, when operating with liquid or pulverized fuel, the fuel is introduced into the swirled combustion air (10) in the throat at right angles to the flow direction or shortly before the throat (3) by means of the central lance (11).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE4316474A DE4316474A1 (en) | 1993-05-17 | 1993-05-17 | Premix burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or a combustion system |
| DE4316474 | 1993-05-17 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP0625673A2 EP0625673A2 (en) | 1994-11-23 |
| EP0625673A3 EP0625673A3 (en) | 1995-05-17 |
| EP0625673B1 true EP0625673B1 (en) | 1999-03-24 |
Family
ID=6488294
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP94105929A Expired - Lifetime EP0625673B1 (en) | 1993-05-17 | 1994-04-16 | Premixing burner for operating an internal combustion engine, a combustion chamber of a gas turbo group or a combustion plant |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US5673551A (en) |
| EP (1) | EP0625673B1 (en) |
| JP (1) | JPH06341617A (en) |
| DE (2) | DE4316474A1 (en) |
Families Citing this family (30)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4435266A1 (en) * | 1994-10-01 | 1996-04-04 | Abb Management Ag | burner |
| DE19527453B4 (en) * | 1995-07-27 | 2009-05-07 | Alstom | premix |
| DE19545309A1 (en) * | 1995-12-05 | 1997-06-12 | Asea Brown Boveri | Premix burner |
| DE19548853A1 (en) * | 1995-12-27 | 1997-07-03 | Abb Research Ltd | Cone burner |
| DE19610930A1 (en) * | 1996-03-20 | 1997-09-25 | Abb Research Ltd | Burners for a heat generator |
| DE19757189B4 (en) * | 1997-12-22 | 2008-05-08 | Alstom | Method for operating a burner of a heat generator |
| US6585784B1 (en) * | 1999-12-13 | 2003-07-01 | Exxonmobil Chemical Patents Inc. | Method for utilizing gas reserves with low methane concentrations for fueling gas turbines |
| US6769903B2 (en) | 2000-06-15 | 2004-08-03 | Alstom Technology Ltd | Method for operating a burner and burner with stepped premix gas injection |
| DE10029607A1 (en) * | 2000-06-15 | 2001-12-20 | Alstom Power Nv | Method to operate burner; involves operating burner with two groups of fuel outlets to supply different amounts of same fuel, where outlet groups are supplied independently and controlled separately |
| DE10056243A1 (en) * | 2000-11-14 | 2002-05-23 | Alstom Switzerland Ltd | Combustion chamber and method for operating this combustion chamber |
| DE10340826A1 (en) * | 2003-09-04 | 2005-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Homogeneous mixture formation by twisted injection of the fuel |
| DE10348604A1 (en) | 2003-10-20 | 2005-07-28 | Rolls-Royce Deutschland Ltd & Co Kg | Fuel injector with filmy fuel placement |
| EP1568942A1 (en) * | 2004-02-24 | 2005-08-31 | Siemens Aktiengesellschaft | Premix Burner and Method for Combusting a Low-calorific Gas |
| CN101243287B (en) * | 2004-12-23 | 2013-03-27 | 阿尔斯托姆科技有限公司 | Premix burner with mixing section |
| DE102007043626A1 (en) * | 2007-09-13 | 2009-03-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity |
| EP2058590B1 (en) * | 2007-11-09 | 2016-03-23 | Alstom Technology Ltd | Method for operating a burner |
| WO2009068424A1 (en) * | 2007-11-27 | 2009-06-04 | Alstom Technology Ltd | Method and device for burning hydrogen in a premix burner |
| JP5449205B2 (en) * | 2008-03-07 | 2014-03-19 | アルストム テクノロジー リミテッド | Burner device and method of using such a burner device |
| WO2009109452A1 (en) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Burner arrangement, and use of such a burner arrangement |
| EP2257736B1 (en) * | 2008-03-07 | 2015-11-25 | Alstom Technology Ltd | Method for the production of hot gas |
| EP2107313A1 (en) * | 2008-04-01 | 2009-10-07 | Siemens Aktiengesellschaft | Fuel staging in a burner |
| EP2299178B1 (en) * | 2009-09-17 | 2015-11-04 | Alstom Technology Ltd | A method and gas turbine combustion system for safely mixing H2-rich fuels with air |
| EP2420730B1 (en) * | 2010-08-16 | 2018-03-07 | Ansaldo Energia IP UK Limited | Reheat burner |
| ES2462974T3 (en) * | 2010-08-16 | 2014-05-27 | Alstom Technology Ltd | Reheating burner |
| TWI435978B (en) * | 2011-10-31 | 2014-05-01 | Atomic Energy Council | Hydrogen-rich gas burner |
| EP2703721B1 (en) | 2012-08-31 | 2019-05-22 | Ansaldo Energia IP UK Limited | Premix burner |
| US9194583B2 (en) * | 2013-02-20 | 2015-11-24 | Jorge DE LA SOVERA | Mixed fuel vacuum burner-reactor |
| WO2014181951A1 (en) * | 2013-05-07 | 2014-11-13 | 한국기계연구원 | Premixing type combustor of venturi tube structure for reducing emissions |
| CN111520764A (en) * | 2020-03-25 | 2020-08-11 | 西北工业大学 | Combustion chamber with tail cooling structure |
| US20220333783A1 (en) * | 2021-03-07 | 2022-10-20 | CPS-Holding Limited | Hydrogen-Fueled Combustor for Gas Turbines |
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| CH291617A (en) * | 1949-06-29 | 1953-06-30 | Canadian Patents Dev | Combustion chamber for gas turbine. |
| US2671313A (en) * | 1952-03-07 | 1954-03-09 | Emile A Laramee | Jet engine vacuum expansion nozzle |
| DE1013467B (en) * | 1955-07-30 | 1957-08-08 | Daimler Benz Ag | Combustion chamber for gas turbines and jet engines with atomization device |
| US3752634A (en) * | 1970-08-18 | 1973-08-14 | Mitsubishi Heavy Ind Ltd | Burner |
| US3638865A (en) * | 1970-08-31 | 1972-02-01 | Gen Electric | Fuel spray nozzle |
| US3736746A (en) * | 1971-08-13 | 1973-06-05 | Gen Electric | Recirculating annular slot fuel/air carbureting system for gas turbine combustors |
| US3820320A (en) * | 1971-12-15 | 1974-06-28 | Phillips Petroleum Co | Combustion method with controlled fuel mixing |
| US3915619A (en) * | 1972-03-27 | 1975-10-28 | Phillips Petroleum Co | Gas turbine combustors and method of operation |
| US3866413A (en) * | 1973-01-22 | 1975-02-18 | Parker Hannifin Corp | Air blast fuel atomizer |
| GB1465785A (en) * | 1973-03-12 | 1977-03-02 | Tokyo Gas Co Ltd | Burner and method of combustion- |
| US3872664A (en) * | 1973-10-15 | 1975-03-25 | United Aircraft Corp | Swirl combustor with vortex burning and mixing |
| US3982392A (en) * | 1974-09-03 | 1976-09-28 | General Motors Corporation | Combustion apparatus |
| SU571615A2 (en) * | 1975-08-13 | 1977-09-05 | Всесоюзный научно-исследовательский институт горноспасательного дела | Inert gas generator |
| US3984528A (en) * | 1975-12-01 | 1976-10-05 | Phillips Petroleum Company | Carbon black reactor and process |
| US4144313A (en) * | 1976-06-04 | 1979-03-13 | Bayer Aktiengesellschaft | Method of purifying gases by combustion |
| US4120640A (en) * | 1977-02-18 | 1978-10-17 | Infern-O-Therm Corporation | Burner for liquid fuel |
| GB2055187B (en) * | 1979-08-01 | 1983-12-14 | Rolls Royce | Gaseous fuel injector for a gas turbine engine |
| US4373325A (en) * | 1980-03-07 | 1983-02-15 | International Harvester Company | Combustors |
| US4425755A (en) * | 1980-09-16 | 1984-01-17 | Rolls-Royce Limited | Gas turbine dual fuel burners |
| GB2150277B (en) * | 1983-11-26 | 1987-01-28 | Rolls Royce | Combustion apparatus for a gas turbine engine |
| GB2175684B (en) * | 1985-04-26 | 1989-12-28 | Nippon Kokan Kk | Burner |
| US4845952A (en) * | 1987-10-23 | 1989-07-11 | General Electric Company | Multiple venturi tube gas fuel injector for catalytic combustor |
| CH674561A5 (en) * | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
| JPH0792213B2 (en) * | 1988-03-16 | 1995-10-09 | 高茂産業株式会社 | Ejector burner device |
| JPH02118890U (en) * | 1989-03-10 | 1990-09-25 | ||
| CH679692A5 (en) * | 1989-04-24 | 1992-03-31 | Asea Brown Boveri | |
| US5156002A (en) * | 1990-03-05 | 1992-10-20 | Rolf J. Mowill | Low emissions gas turbine combustor |
| US5228283A (en) * | 1990-05-01 | 1993-07-20 | General Electric Company | Method of reducing nox emissions in a gas turbine engine |
| CH682952A5 (en) * | 1991-03-12 | 1993-12-15 | Asea Brown Boveri | Burner for a premixing combustion of a liquid and / or gaseous fuel. |
| CH684962A5 (en) * | 1991-07-03 | 1995-02-15 | Asea Brown Boveri | Burner for operating an internal combustion engine, a combustor of a gas turbine group or a firing. |
| US5295352A (en) * | 1992-08-04 | 1994-03-22 | General Electric Company | Dual fuel injector with premixing capability for low emissions combustion |
| US5303554A (en) * | 1992-11-27 | 1994-04-19 | Solar Turbines Incorporated | Low NOx injector with central air swirling and angled fuel inlets |
| DE4304213A1 (en) * | 1993-02-12 | 1994-08-18 | Abb Research Ltd | Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or a combustion system |
| US5345768A (en) * | 1993-04-07 | 1994-09-13 | General Electric Company | Dual-fuel pre-mixing burner assembly |
| US5477685A (en) * | 1993-11-12 | 1995-12-26 | The Regents Of The University Of California | Lean burn injector for gas turbine combustor |
-
1993
- 1993-05-17 DE DE4316474A patent/DE4316474A1/en not_active Withdrawn
-
1994
- 1994-04-16 DE DE59407984T patent/DE59407984D1/en not_active Expired - Fee Related
- 1994-04-16 EP EP94105929A patent/EP0625673B1/en not_active Expired - Lifetime
- 1994-05-16 JP JP6101148A patent/JPH06341617A/en not_active Ceased
-
1996
- 1996-09-17 US US08/714,890 patent/US5673551A/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| DE4316474A1 (en) | 1994-11-24 |
| US5673551A (en) | 1997-10-07 |
| EP0625673A2 (en) | 1994-11-23 |
| DE59407984D1 (en) | 1999-04-29 |
| EP0625673A3 (en) | 1995-05-17 |
| JPH06341617A (en) | 1994-12-13 |
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