EP1030109B1 - Fuel injector for injecting liquid and/or gas fuels in a combustion chamber - Google Patents
Fuel injector for injecting liquid and/or gas fuels in a combustion chamber Download PDFInfo
- Publication number
- EP1030109B1 EP1030109B1 EP00810118A EP00810118A EP1030109B1 EP 1030109 B1 EP1030109 B1 EP 1030109B1 EP 00810118 A EP00810118 A EP 00810118A EP 00810118 A EP00810118 A EP 00810118A EP 1030109 B1 EP1030109 B1 EP 1030109B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- passage
- liquid
- lance
- air
- 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
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Classifications
-
- 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
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
-
- 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
- F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
- F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
-
- 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
- F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
- F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2214/00—Cooling
Definitions
- the present invention relates to the field of burner technology as it is is used in particular in gas turbines. It affects a fuel lance for injecting liquid and / or gaseous fuels into a combustion chamber, which fuel lance is part of a combustion air jet in a secondary or tertiary burner with a flow around it, and a liquid fuel channel within an outer lance jacket Supply of liquid fuel, a surrounding the liquid fuel channel Gas channel for the supply of gaseous fuel and one the gas channel surrounding air duct for supplying cooling or atomizing air, and first means for radially injecting the liquid fuel from the liquid fuel channel into the combustion chamber and second means for radial injection of the gaseous fuel from the gas channel into the combustion chamber.
- Such a fuel lance is e.g. B. from a previous patent application DE-A1-43 26 802 known to the applicant.
- a fuel lance is known from the document DE-A1-43 26 802 mentioned at the beginning known that the applicant is currently using their gas turbines (see also the publications US-A-5,341,018, US-A-5,626,017 and EP-A1-0 620 362) is used.
- the nozzles for gaseous fuel and liquid fuel (Oil etc.) are combined.
- the liquid fuel is injected according to the so-called air blast principle, i.e. that as a film on an atomizer lip Applied fuel is in the shear field of the surrounding air flow atomized and mixed with the combustion air as a fuel mist. Does that happen Injection transverse to the direction of flow of the combustion air, so is the depth of penetration determined exclusively by the air pulse.
- the momentum of the liquid Fuel is only used for film production, but not to support the Fuel jet used.
- the object is achieved by the entirety of the features of claim 1.
- the essence of the invention is the liquid fuel by means of a suitable Guide tube arrangement as a plain jet radially to the main flow direction.
- This type of injection means that the liquid fuel stays in the vehicle for a while is reduced in the premixing section and thus less water must be added to prevent a flashback.
- Another advantage is the improved fuel-air mixture due to this arrangement.
- the existing one that has already been optimized for gas injection can be used Air flow field of the main flow also for atomization and mixing of the liquid fuel.
- the injection of the gaseous fuel and the surrounding air jacket turns out to be particularly favorable if according to a second preferred Embodiment, the second guide tube in the region of the air duct in the outer diameter tapered towards the mouth, and the first guide tube in the area of the gas channel tapers conically in the outside diameter towards the mouth.
- a preferred embodiment is one in longitudinal section Fuel lance reproduced according to the invention.
- the fuel lance 10 which extends along a lance axis 24, which in turn essentially parallel to the main flow direction 25 of a combustion air flow flowing around the lance is shown in the figure only with its head area.
- a liquid fuel tube 16 In the fuel lance 10 are located one inside the other concentrically to the lance axis 24 a liquid fuel tube 16, a gas tube 14 and a lance jacket 12 are arranged.
- the interior of the liquid fuel tube 16 forms a liquid fuel channel 17, through which liquid fuel, in particular oil or the like, for injection into Direction of the arrow shown is guided into the lance head 11.
- a gas duct 15 formed by which gaseous fuel in the direction of the drawn Arrow is injected into the lance head 11.
- an air duct 13 is formed through which Air is guided into the lance head 11 in the direction of the arrow shown becomes.
- the liquid fuel from the liquid fuel channel 17 radially injected into the combustion chamber in the form of a plain jet into which the Fuel lance 10 protrudes.
- a first guide tube 23 is provided for injection. which goes in the radial direction from the liquid fuel channel 17 and in Area of a (circular) jacket opening 22 in the lance jacket 12 ends.
- the gaseous fuel is also radially from the gas channel 15 to the lance axis 24 and thus injected into the main flow direction 25 into the combustion chamber.
- a second guide tube 21 is provided, which is in the radial direction starts from the gas channel 15 and also ends in the region of the jacket opening 22.
- Both guide tubes 21, 23 are arranged concentrically one inside the other at a distance, so that the gaseous fuel in the annular gap thus formed between the two Guide tubes 21, 23 is guided.
- the diameter of the jacket opening 22 is relative chosen for the outer diameter of the second guide tube 21 so that a annular gap for generating a protective surrounding the gas jet Air jacket remains free.
- the flow conditions are particularly favorable for the Air jacket flow when the two guide tubes 21, 23 - as shown in the figure flush end with the inner contour of the lance jacket 12.
- the deflection of the flows out of the gas duct 15 and the air duct 13 the axial direction in the radial direction and the formation of the desired Sheath flows can be further facilitated if the second guide tube 21 in the area of the air duct 14 in the outer diameter towards the mouth tapers, and the first guide tube 23 in the region of the gas duct 15 in the outer diameter tapered towards the mouth.
- air from the air duct can be made in a manner known per se 13 for cooling the head part 18 and for generating an axial air curtain be guided into the lance head. Do this on a concentric ring arranged around the lance axis 24 around axial bores 20, through the air in can emerge in the axial direction. The air required for this comes from the air duct 13 led over a head channel 19 which in the edge area through the lance head 11 runs. This ensures that the lance head 11 through the air flowing through it is cooled.
Description
Die vorliegende Erfindung bezieht sich auf das Gebiet der Brennertechnik, wie sie insbesondere bei Gasturbinen Anwendung findet. Sie betrifft eine Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer, welche Brennstofflanze Teil eines von einem Verbrennungsluftstrahl in einer Hauptströmungsrichtung umströmten sekundären oder tertiären Brenners ist, und innerhalb eines äusseren Lanzenmantels einen Flüssigbrennstoffkanal zur Zuführung von Flüssigbrennstoff, einen den Flüssigbrennstoffkanal umgebenden Gaskanal zur Zuführung von gasförmigen Brennstoff und einen den Gaskanal umgebenden Luftkanal zur Zuführung von Kühl- bzw. Zerstäuberluft umfasst, sowie erste Mittel zum radialen Eindüsen des Flüssigbrennstoffes aus dem Flüssigbrennstoffkanal in die Brennkammer sowie zweite Mittel zum radialen Eindüsen des gasförmigen Brennstoffes aus dem Gaskanal in die Brennkammer.The present invention relates to the field of burner technology as it is is used in particular in gas turbines. It affects a fuel lance for injecting liquid and / or gaseous fuels into a combustion chamber, which fuel lance is part of a combustion air jet in a secondary or tertiary burner with a flow around it, and a liquid fuel channel within an outer lance jacket Supply of liquid fuel, a surrounding the liquid fuel channel Gas channel for the supply of gaseous fuel and one the gas channel surrounding air duct for supplying cooling or atomizing air, and first means for radially injecting the liquid fuel from the liquid fuel channel into the combustion chamber and second means for radial injection of the gaseous fuel from the gas channel into the combustion chamber.
Eine solche Brennstofflanze ist z. B. aus einer früheren Patentanmeldung DE-A1-43 26 802 der Anmelderin bekannt.Such a fuel lance is e.g. B. from a previous patent application DE-A1-43 26 802 known to the applicant.
Aus der eingangs genannten Druckschrift DE-A1-43 26 802 ist eine Brennstofflanze bekannt, die von der Anmelderin derzeit bei ihren Gasturbinen (siehe dazu auch die Druckschriften US-A-5,341,018, US-A-5,626,017 und EP-A1-0 620 362) verwendet wird. Die Düsen für gasförmigen Brennstoff und Flüssigbrennstoff (Oel etc.) sind dabei kombiniert.A fuel lance is known from the document DE-A1-43 26 802 mentioned at the beginning known that the applicant is currently using their gas turbines (see also the publications US-A-5,341,018, US-A-5,626,017 and EP-A1-0 620 362) is used. The nozzles for gaseous fuel and liquid fuel (Oil etc.) are combined.
In der erwähnten Druckschrift erfolgt die Eindüsung des flüssigen Brennstoffes nach dem sogenannten Air-Blast-Prinzip, d.h. der als Film auf einer Zerstäuberlippe aufgebrachte Brennstoff wird im Scherfeld der umgebenden Luftströmung zerstäubt und als Brennstoffnebel der Verbrennungsluft beigemischt. Erfolgt die Eindüsung quer zur Strömungsrichtung der Verbrennungsluft, so wird die Eindringtiefe ausschliesslich vom Luftimpuls bestimmt. Der Eigenimpuls des flüssigen Brennstoffes wird lediglich zur Filmerzeugung, nicht aber zur Unterstützung des Brennstoffstrahles benutzt.In the mentioned publication, the liquid fuel is injected according to the so-called air blast principle, i.e. that as a film on an atomizer lip Applied fuel is in the shear field of the surrounding air flow atomized and mixed with the combustion air as a fuel mist. Does that happen Injection transverse to the direction of flow of the combustion air, so is the depth of penetration determined exclusively by the air pulse. The momentum of the liquid Fuel is only used for film production, but not to support the Fuel jet used.
Zur Erzeugung eines möglichst homogenen Brennstoff/Luft-Gemisches ist es erforderlich, dass der Brennstoff aus dem Nachlauf der Düse im Querschnitt der Verbrennungsluft verteilt wird. Bei hohen Querströmungen ist ein entsprechend hoher Strahlimpuls notwendig. Dieser hohe Strahlimpuls kann mit der Zerstäuberluft alleine nicht erreicht werden. Deshalb soll der Eigenimpuls des eingedüsten flüssigen Brennstoffes (bzw. des gasförmigen Brennstoffes) unterstützend ausgenützt werden. Der Zerfall des Brennstoffstrahles erfolgt durch Strahlinstabilitäten nach einigen Strahldurchmessern Lauflänge. To generate a fuel / air mixture that is as homogeneous as possible, it is necessary that the fuel from the wake of the nozzle in cross section of the Combustion air is distributed. In the case of high cross currents, an is appropriate high beam pulse necessary. This high jet impulse can with the atomizing air cannot be achieved alone. Therefore, the intrinsic impulse should be injected liquid fuel (or gaseous fuel) is used as a support become. The fuel jet decays due to jet instabilities after a few beam diameters.
Es ist daher Aufgabe der Erfindung, eine Brennstofflanze für die Eindüsung von Flüssigbrennstoff und/oder gasförmigem Brennstoff in einem sekundären oder tertiären Brenner zu schaffen, welche die geschilderten Nachteile bisheriger Lanzen vermeidet und insbesondere eine Verkürzung der Aufenthaltszeit des Flüssigbrennstoffes in der Vormischstrecke und damit eine Reduzierung des zugemischten Wasseranteils ermöglicht.It is therefore an object of the invention to provide a fuel lance for the injection of Liquid fuel and / or gaseous fuel in a secondary or to create tertiary burners, which have the disadvantages described previous lances avoids and in particular a shortening of the residence time of the liquid fuel in the premixing section and thus a reduction in the admixed Water share enabled.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, den Flüssigbrennstoff mittels einer geeigneten Leitrohranordnung als Plain-Jet radial zur Hauptströmungsrichtung einzudüsen. Diese Art der Eindüsung hat zur Folge, dass die Aufenthaltszeit des Flüssigbrennstoffes in der Vormischstrecke vermindert wird und somit weniger Wasser zur Verhinderung eines Flammenrückschlages zugegeben werden muss. Ein weiterer Vorteil ist die durch diese Anordnung verbesserte Brennstoff-Luft-Mischung. Insbesondere kann so das bereits für die Gaseindüsung optimierte, vorhandene Luftströmungsfeld der Hauptströmung auch für die Zerstäubung und Mischung des Flüssigbrennstoffs ausgenutzt werden.The object is achieved by the entirety of the features of claim 1. The essence of the invention is the liquid fuel by means of a suitable Guide tube arrangement as a plain jet radially to the main flow direction. This type of injection means that the liquid fuel stays in the vehicle for a while is reduced in the premixing section and thus less water must be added to prevent a flashback. On Another advantage is the improved fuel-air mixture due to this arrangement. In particular, the existing one that has already been optimized for gas injection can be used Air flow field of the main flow also for atomization and mixing of the liquid fuel.
Besonders günstige Strömungsverhältnisse ergeben sich, wenn gemäss einer ersten bevorzugten Ausführungsform der erfindungsgemässen Brennstofflanze die beiden Leitrohre bündig mit der Innenkontur des Lanzenmantels enden.Particularly favorable flow conditions result if according to a first preferred embodiment of the fuel lance according to the invention Both guide tubes end flush with the inner contour of the lance jacket.
Die Eindüsung des gasförmigen Brennstoffs und des umgebenden Luftmantels gestaltet sich besonders günstig, wenn sich gemäss eine zweiten bevorzugten Ausführungsform das zweite Leitrohr im Bereich des Luftkanals im Aussendurchmesser zur Mündung hin konisch verjüngt, und sich das erste Leitrohr im Bereich des Gaskanals im Aussendurchmesser zur Mündung hin konisch verjüngt. The injection of the gaseous fuel and the surrounding air jacket turns out to be particularly favorable if according to a second preferred Embodiment, the second guide tube in the region of the air duct in the outer diameter tapered towards the mouth, and the first guide tube in the area of the gas channel tapers conically in the outside diameter towards the mouth.
Die Erfindung soll nachfolgend anhand eines Ausführungsbeispiels im Zusammenhang mit der Zeichnung näher erläutert werden. Die einzige Figur zeigt im Längsschnitt den Kopfbereich einer Brennstofflanze gemäss einem bevorzugten Ausführungsbeispiel der Erfindung mit radialer Eindüsung des gasförmigen Brennstoffes und des Flüssigbrennstoffs durch zwei konzentrisch ineinander angeordnete Leitrohre.In the following, the invention will be described in connection with an exemplary embodiment be explained in more detail with the drawing. The only figure shows in Longitudinal section of the head region of a fuel lance according to a preferred one Embodiment of the invention with radial injection of the gaseous Fuel and liquid fuel by two concentrically arranged one inside the other Guide tubes.
In der einzigen Figur ist im Längsschnitt ein bevorzugtes Ausführungsbeispiel einer
Brennstofflanze nach der Erfindung wiedergegeben. Die Brennstofflanze 10,
die sich entlang einer Lanzenachse 24 erstreckt, die ihrerseits im wesentlichen
parallel zur Hauptströmungsrichtung 25 einer die Lanze umströmenden Verbrennungsluftströmung
liegt, ist in der Figur nur mit ihrem Kopfbereich dargestellt. In
der Brennstofflanze 10 sind konzentrisch zur Lanzenachse 24 ineinanderliegend
ein Flüssigbrennstoffrohr 16, ein Gasrohr 14 und ein Lanzenmantel 12 angeordnet.
Das Innere des Flüssigbrennstoffrohres 16 bildet einen Flüssigbrennstoffkanal
17, durch welchen Flüssigbrennstoff, insbesondere Oel oder dgl., zur Eindüsung in
Richtung des eingezeichneten Pfeiles in den Lanzenkopf 11 geführt wird. Zwischen
dem Flüssigbrennstoffrohr 16 und dem Gasrohr 14 ist ein Gaskanal 15
gebildet, durch welchen gasförmiger Brennstoff in Richtung des eingezeichneten
Pfeiles zum Eindüsen in den Lanzenkopf 11 geführt wird. Zwischen dem Gasrohr
14 und dem Lanzenmantel 12 schliesslich ist ein Luftkanal 13 gebildet, durch welchen
in Richtung des eingezeichneten Pfeiles Luft in den Lanzenkopf 11 geführt
wird. Anstelle der in der Figur gezeigten konzentrischen Anordnung der Rohre 12,
14 und 16 ist es in bestimmten Fällen denkbar und auch vorteilhaft, die Rohre so
anzuordnen, dass der Gaskanal 15 bzw. der Flüssigbrennstoffkanal 17 exzentrisch
angeordnet sind. In the single figure, a preferred embodiment is one in longitudinal section
Fuel lance reproduced according to the invention. The
Erfindungsgemäss wird der Flüssigbrennstoff aus dem Flüssigbrennstoffkanal 17
radial in Form eines Plain-Jets in die Brennkammer eingedüst, in welche die
Brennstofflanze 10 hineinragt. Zur Eindüsung ist ein erstes Leitrohr 23 vorgesehen,
welches in radialer Richtung vom Flüssigbrennstoffkanal 17 abgeht und im
Bereich einer (kreisförmigen) Mantelöffnung 22 im Lanzenmantel 12 endet. Der
gasförmige Brennstoff wird ebenfalls aus dem Gaskanal 15 radial zur Lanzenachse
24 und damit zur Hauptströmungsrichtung 25 in die Brennkammer eingedüst.
Dazu ist ein zweites Leitrohr 21 vorgesehen, welches in radialer Richtung
vom Gaskanal 15 ausgeht und ebenfalls im Bereich der Mantelöffnung 22 endet.
Beide Leitrohre 21, 23 sind mit Abstand konzentrisch ineinander angeordnet, so
dass der gasförmige Brennstoff im derart gebildeten Ringspalt zwischen den beiden
Leitrohren 21, 23 geführt wird. Der Durchmesser der Mantelöffnung 22 ist relativ
zum Aussendurchmesser des zweiten Leitrohres 21 so gewählt, dass ein
ringförmiger Spalt zur Erzeugung eines den Gasstrahl umgebenden, schützenden
Luftmantels frei bleibt. Besonders günstig sind die Strömungsverhältnisse für den
Luftmantelstrom, wenn die beiden Leitrohre 21, 23 - wie in der Figur gezeigtbündig
mit der Innenkontur des Lanzenmantels 12 enden.According to the invention, the liquid fuel from the
Die Umlenkung der Strömungen aus dem Gaskanal 15 und dem Luftkanal 13 aus
der axialen Richtung in die radiale Richtung und die Bildung der gewünschten
Mantelströmungen kann weiter erleichtert werden, wenn sich das zweite Leitrohr
21 im Bereich des Luftkanals 14 im Aussendurchmesser zur Mündung hin konisch
verjüngt, und sich das erste Leitrohr 23 im Bereich des Gaskanals 15 im Aussendurchmesser
zur Mündung hin konisch verjüngt.The deflection of the flows out of the
Weiterhin kann, falls notwendig, in an sich bekannter Weise Luft aus dem Luftkanal
13 zur Kühlung des Kopfteils 18 und zur Erzeugung eines axialen Luftschleiers
in den Lanzenkopf geführt werden. Dazu werden auf einem konzentrischen Ring
um die Lanzenachse 24 herum axiale Bohrungen 20 angeordnet, durch die Luft in
axialer Richtung austreten kann. Die dazu erforderliche Luft wird aus dem Luftkanal
13 über einen Kopfkanal 19 herangeführt, der im Randbereich durch den Lanzenkopf
11 verläuft. Damit wird erreicht, dass auch der Lanzenkopf 11 durch die
hindurchströmende Luft gekühlt wird.Furthermore, if necessary, air from the air duct can be made in a manner known per se
13 for cooling the
- 1010
- Brennstofflanzefuel lance
- 1111
- Lanzenkopflance head
- 1212
- Lanzenmantellance outer shell
- 1313
- Luftkanalair duct
- 1414
- Gasrohrgas pipe
- 1515
- Gaskanalgas channel
- 1616
- FlüssigbrennstoffrohrLiquid fuel pipe
- 1717
- FlüssigbrennstoffkanalLiquid fuel passage
- 1818
- Kopfteilheadboard
- 1919
- Kopfkanal (Luft)Head channel (air)
- 2020
- Bohrung (Luftschleier)Hole (air curtain)
- 2121
- Leitrohr (gasförmiger Brennstoff)Guide tube (gaseous fuel)
- 2222
- Mantelöffnungshell opening
- 2323
- Leitrohr (flüssiger Brennstoff)Guide tube (liquid fuel)
- 2424
- Lanzenachselance axis
- 2525
- HauptströmungsrichtungMain flow direction
Claims (6)
- Fuel lance (10) for spraying liquid and/or gaseous fuels into a combustion chamber, which fuel lance (10) is part of a secondary or tertiary burner, around which a combustion air jet flows in a main flow direction (25), and comprises inside an outer lance shell (12) a liquid-fuel passage (17) for supplying liquid fuel, a gas passage (15) surrounding the liquid-fuel passage (17) and intended for supplying gaseous fuel, and an air passage (13) surrounding the gas passage (15) and intended for supplying cooling or atomizing air, and first means (23) for the radial spraying of the liquid fuel from the liquid-fuel passage (17) into the combustion chamber, and second means (21) for the radial spraying of the gaseous fuel from the gas passage (15) into the combustion chamber, characterized in that the first means comprise a first guide tube (23), which, in the radial direction starting from the liquid-fuel passage (17), runs outward through the gas passage (15) and the air passage (13), in that the second means comprise a second guide tube (21), which, in the radial direction starting from the gas passage (15), runs outward through the air passage (13) and concentrically surrounds the first guide tube (23) at a distance, and in that the two guide tubes (21, 23) open in the region of a shell opening (22) in the lance shell (12) in such a way that the liquid-fuel jet discharging from the first guide tube (23) discharges as a plain jet into the combustion chamber, and the fuel jets discharging from the guide tubes (21, 23) are surrounded in a sheath-like manner by the air flowing out of the air passage (13) through the shell opening (22).
- Fuel lance according to Claim 1, characterized in that the two guide tubes (21, 23) end flush with the inner contour of the lance shell (12).
- Fuel lance according to either of Claims 1 or 2, characterized in that the second guide tube (21), in the region of the air passage (13), narrows conically in outside diameter toward the orifice.
- Fuel lance according to one of Claims 1 to 3, characterized in that the first guide tube (23), in the region of the gas passage (15), narrows conically in outside diameter toward the orifice.
- Fuel lance according to one of Claims 1 to 4, characterized in that the liquid-fuel passage (17) and the gas passage (15) are arranged concentrically to one another.
- Fuel lance according to one of Claims 1 to 4, characterized in that the liquid-fuel passage (17) or the gas passage (15) is arranged eccentrically.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19905996 | 1999-02-15 | ||
| DE19905996A DE19905996A1 (en) | 1999-02-15 | 1999-02-15 | Fuel lance for injecting liquid and / or gaseous fuels into a combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1030109A1 EP1030109A1 (en) | 2000-08-23 |
| EP1030109B1 true EP1030109B1 (en) | 2004-04-07 |
Family
ID=7897373
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP00810118A Expired - Lifetime EP1030109B1 (en) | 1999-02-15 | 2000-02-10 | Fuel injector for injecting liquid and/or gas fuels in a combustion chamber |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US6325618B1 (en) |
| EP (1) | EP1030109B1 (en) |
| JP (1) | JP4465076B2 (en) |
| CN (1) | CN1175202C (en) |
| DE (2) | DE19905996A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10050285C2 (en) * | 2000-10-10 | 2003-03-06 | Innovatherm Prof Dr Leisenberg Gmbh & Co Kg | Gas burner for a tunnel kiln |
| DE10056243A1 (en) | 2000-11-14 | 2002-05-23 | Alstom Switzerland Ltd | Combustion chamber and method for operating this combustion chamber |
| DE10330023A1 (en) * | 2002-07-20 | 2004-02-05 | Alstom (Switzerland) Ltd. | Vortex generator used in the swirling and mixing of fuel/air mixtures in pre-mixing combustion chambers comprises an outlet opening for targeted introduction of a secondary flow into the core flow of the wake produced |
| DE102004041272B4 (en) * | 2004-08-23 | 2017-07-13 | General Electric Technology Gmbh | Hybrid burner lance |
| FR2875584B1 (en) * | 2004-09-23 | 2009-10-30 | Snecma Moteurs Sa | EFFERVESCENCE INJECTOR FOR AEROMECHANICAL AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER |
| US8387390B2 (en) | 2006-01-03 | 2013-03-05 | General Electric Company | Gas turbine combustor having counterflow injection mechanism |
| GB0618196D0 (en) * | 2006-09-15 | 2006-10-25 | Pursuit Dynamics Plc | An improved mist generating apparatus and method |
| JP2008185254A (en) * | 2007-01-30 | 2008-08-14 | General Electric Co <Ge> | Reverse-flow injection mechanism having coaxial fuel-air passage |
| US7775791B2 (en) * | 2008-02-25 | 2010-08-17 | General Electric Company | Method and apparatus for staged combustion of air and fuel |
| EP2116766B1 (en) | 2008-05-09 | 2016-01-27 | Alstom Technology Ltd | Burner with fuel lance |
| ES2400247T3 (en) | 2008-12-19 | 2013-04-08 | Alstom Technology Ltd | Burner of a gas turbine that has a special lance configuration |
| US8434291B2 (en) * | 2009-01-08 | 2013-05-07 | General Electric Company | Systems and methods for detecting a flame in a fuel nozzle of a gas turbine |
| EP2211110B1 (en) | 2009-01-23 | 2019-05-01 | Ansaldo Energia Switzerland AG | Burner for a gas turbine |
| EP2236934A1 (en) * | 2009-03-18 | 2010-10-06 | Siemens Aktiengesellschaft | Burner assembly |
| US8087928B2 (en) * | 2009-03-25 | 2012-01-03 | Horn Wallace E | Laminar flow jets |
| US9587823B2 (en) | 2009-03-25 | 2017-03-07 | Wallace Horn | Laminar flow jets |
| US20110072823A1 (en) * | 2009-09-30 | 2011-03-31 | Daih-Yeou Chen | Gas turbine engine fuel injector |
| ES2611106T3 (en) * | 2010-05-20 | 2017-05-04 | General Electric Technology Gmbh | Lance of a gas turbine burner |
| CN101936527B (en) * | 2010-09-07 | 2012-10-10 | 西安航天远征流体控制股份有限公司 | Oil-oxygen burning pre-mixed type starting burner |
| EP2789915A1 (en) * | 2013-04-10 | 2014-10-15 | Alstom Technology Ltd | Method for operating a combustion chamber and combustion chamber |
| DE102018204741A1 (en) * | 2018-03-28 | 2019-10-02 | Siemens Aktiengesellschaft | fuel supply |
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| NL7515165A (en) * | 1975-12-30 | 1977-07-04 | Shell Int Research | PROCESS AND BURNER FOR PARTIAL COMBUSTION OF A LIQUID OR GAS FUEL, AND PROCESS FOR REDUCTION OF SULFUR COMPOUNDS CONTAINING GASES. |
| US4077761A (en) * | 1976-08-04 | 1978-03-07 | Sid Richardson Carbon & Gasoline Co. | Carbon black reactor with axial flow burner |
| JPS587800A (en) | 1981-07-07 | 1983-01-17 | 新明和工業株式会社 | Electrode interval adjusting device in high power pulse particle beam generator |
| JPS58198612A (en) * | 1982-05-13 | 1983-11-18 | Mitsubishi Heavy Ind Ltd | Fuel atomizer |
| CH672541A5 (en) * | 1986-12-11 | 1989-11-30 | Bbc Brown Boveri & Cie | |
| US4854127A (en) * | 1988-01-14 | 1989-08-08 | General Electric Company | Bimodal swirler injector for a gas turbine combustor |
| DE59000422D1 (en) * | 1989-04-20 | 1992-12-10 | Asea Brown Boveri | COMBUSTION CHAMBER ARRANGEMENT. |
| FR2667928B1 (en) * | 1990-10-16 | 1995-07-28 | Air Liquide | METHOD FOR HEATING A THERMAL ENCLOSURE. |
| US5341018A (en) | 1991-09-18 | 1994-08-23 | Nec Corporation | Semiconductor integrated circuit device having a plurality of input circuits each including differently sized transistors |
| EP0577862B1 (en) | 1992-07-03 | 1997-03-12 | Abb Research Ltd. | Afterburner |
| DE4237858A1 (en) * | 1992-11-10 | 1994-05-11 | Kraft Industriewaermetechnik D | Gas / oil burner |
| CH687269A5 (en) | 1993-04-08 | 1996-10-31 | Abb Management Ag | Gas turbine group. |
| DE4326802A1 (en) * | 1993-08-10 | 1995-02-16 | Abb Management Ag | Fuel lance for liquid and / or gaseous fuels and process for their operation |
| DE4426351B4 (en) | 1994-07-25 | 2006-04-06 | Alstom | Combustion chamber for a gas turbine |
| DE19535370B4 (en) * | 1995-09-25 | 2006-05-11 | Alstom | Process for low-emission premix combustion in gas turbine combustion chambers |
| GB2307980B (en) * | 1995-12-06 | 2000-07-05 | Europ Gas Turbines Ltd | A fuel injector arrangement; a method of operating a fuel injector arrangement |
| DE19618058B4 (en) * | 1996-05-06 | 2008-12-04 | Alstom | burner |
-
1999
- 1999-02-15 DE DE19905996A patent/DE19905996A1/en not_active Withdrawn
-
2000
- 2000-02-10 EP EP00810118A patent/EP1030109B1/en not_active Expired - Lifetime
- 2000-02-10 DE DE50005950T patent/DE50005950D1/en not_active Expired - Lifetime
- 2000-02-14 US US09/503,709 patent/US6325618B1/en not_active Expired - Lifetime
- 2000-02-15 JP JP2000037039A patent/JP4465076B2/en not_active Expired - Fee Related
- 2000-02-15 CN CNB001053930A patent/CN1175202C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN1175202C (en) | 2004-11-10 |
| JP2000234735A (en) | 2000-08-29 |
| US6325618B1 (en) | 2001-12-04 |
| DE50005950D1 (en) | 2004-05-13 |
| JP4465076B2 (en) | 2010-05-19 |
| EP1030109A1 (en) | 2000-08-23 |
| CN1265455A (en) | 2000-09-06 |
| DE19905996A1 (en) | 2000-08-17 |
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