EP0321809B1 - Process for combustion of liquid fuel in a burner - Google Patents
Process for combustion of liquid fuel in a burner Download PDFInfo
- Publication number
- EP0321809B1 EP0321809B1 EP88120667A EP88120667A EP0321809B1 EP 0321809 B1 EP0321809 B1 EP 0321809B1 EP 88120667 A EP88120667 A EP 88120667A EP 88120667 A EP88120667 A EP 88120667A EP 0321809 B1 EP0321809 B1 EP 0321809B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- fuel
- liquid fuel
- interior
- cone
- 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
Images
Classifications
-
- 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
- F23C1/00—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air
-
- 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
- F23D11/402—Mixing chambers downstream of the nozzle
-
- 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
- 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
- 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
- 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
Definitions
- the present invention relates to a method for the combustion of liquid fuel in a burner without a premix section according to the preamble of claim 1. It also relates to a burner for carrying out this method.
- a burner is known from EP-A1-0 210 462, which is formed from at least two double-curved hollow partial cone bodies acted upon with tangential air entry. These bodies are folded in the direction of flow along diagonals that open outwards in the shape of a cone. One curved fold side forms an inner cone with an increasing cone inclination in the outflow direction, while the other curved fold side forms an outer cone with a decreasing cone inclination in the outflow direction. At their ends, the inner cones each carry a fuel line along their entire axial extent for the supply of the gaseous fuel which flows through several fuel nozzles into the interior of the burner in order to mix there with the tangentially flowing combustion air.
- the burner also has a separate supply of a liquid fuel, which is a dual burner.
- the injection of the liquid fuel is directed axially onto the outer cone in such a way that, depending on the strength of the injection, a different length of fuel film is formed.
- weighty mixing is carried out by the tangentially introduced combustion air, which rolls up the fuel film in layers due to its swirling movement in the axial direction, making the generation of a strong mixture superfluous. Because the impulse of the injection of liquid fuel is adapted to the load of the machine, the mixture is never too lean or too rich.
- this burner results in a vortex flow which is low in swirl in the center but has an excess of axial speed. Because the number of swirls increases strongly in the axial direction and reaches the breakdown value or the critical value at the end of the burner, this results in a positionally stable vortex backflow.
- the oil injection is structurally relatively complex. But the design of the folded cone sections and their coordination with each other is not easy to handle.
- the object of the invention is to simplify the physical configuration of the burner in a method and a burner of the types mentioned at the beginning and at the same time to minimize the NO x emission values from the premixed combustion of liquid fuel, without changing the flow field in the burner with the stable vortex backflow zone.
- Another advantage of the invention results from the possibility that the burner according to the invention can also be used in gas turbines, the pressure ratio of which is so high over approximately 12 that, due to the principle, no pre-evaporation of the liquid fuel is possible because the fuel has previously ignited would. Finally, the burner according to the invention can also be used in those cases in which no or only insufficient air preheating for evaporation can be achieved.
- an essential advantage of the invention is that the burner according to the invention consists of a few components that are easy to manufacture and assemble.
- FIGS. 2-4 In order to better understand the structure of the burner, it is advantageous if the reader uses the individual sections according to FIGS. 2-4 simultaneously with FIG. 1. Furthermore, in order not to make Fig. 1 unnecessarily confusing, the baffles 21a, 21b shown schematically according to Figs. 2-4 have only been hinted at. In the description of FIG. 1 below, the remaining FIGS. 2-4 are optionally referred to as required.
- the burner according to FIG. 1 consists of two half hollow tapered bodies 1, 2 which are offset from one another.
- the offset of the respective central axis 1b, 2b of the partial cone bodies 1, 2 to each other creates a tangential air inlet slot 19, 20 on both sides in a mirror-image arrangement (FIGS. 2-4), through which the combustion air 15 enters the interior of the burner, ie flows into the cone cavity 14.
- the two partial cone bodies 1, 2 each have a cylindrical initial part 1 a, 2 a, which likewise run offset from one another analogously to the partial cone bodies 1, 2, so that the tangential air inlet slots 19, 20 are present from the beginning.
- a nozzle 3 is accommodated, the fuel injection 4 of which coincides with the narrowest cross section of the conical cavity 14 formed by the two partial cone bodies 1, 2.
- the burner can be made purely conical, that is to say without cylindrical initial parts 1a, 2a.
- Both partial cone bodies 1, 2 each have a fuel line 8, 9, which are provided with openings 17 through which the gaseous fuel 13 is mixed with the combustion air 15 flowing through the tangential air inlet slots 19, 20. The position of these fuel lines 8, 9 is shown schematically in FIGS.
- the fuel lines 8, 9 are attached to the end of the tangential air inlet slots 19, 20, so that the admixture 16 of the gaseous fuel 13 with the incoming combustion air 15 also takes place there .
- the burner On the combustion chamber side 22, the burner has a collar-shaped anchoring for the partial cone body 1, 2 serving end plate 10 with a number of holes 11 through which, if necessary, dilution air or cooling air 18 can be supplied to the front part of the combustion chamber 22 or its wall.
- the liquid fuel 12 flowing through the nozzle 3 is injected into the cone cavity 14 at an acute angle, in such a way that the most homogeneous conical fuel spray is obtained in the burner outlet plane, it being very important to ensure that the inner walls of the partial cone bodies 1, 2 injected liquid fuel 12 are not wetted.
- the fuel injector 4 can be an air-assisted nozzle or a pressure atomizer.
- the conical liquid fuel profile 5 is enclosed by a rotating combustion air stream 15 flowing in tangentially. In the axial direction, the concentration of the liquid fuel 12 is continuously reduced by the mixed-in combustion air 15. If gaseous fuel 13/16 is burned, the mixture is formed with the combustion air 15 directly at the end of the air inlet slots 19, 20.
- the nitrogen oxide and carbon monoxide emissions are low if the excess air is at least 60%. In the case of complete evaporation before entering the combustion zone, the pollutant emission values are lowest. The same also applies to near-stoichiometric operation when the excess air is replaced by recirculating exhaust gas.
- the partial cone bodies 1, 2 with regard to the taper inclination and the width of the tangential air inlet slots 19, 20, narrow limits must be observed so that the desired flow field of the air with its return flow zone 6 is established in the area of the burner mouth for flame stabilization.
- the backflow zone 6 which is once geometrically fixed, is inherently position-stable, because the swirl number increases in the direction of flow in the region of the cone shape of the burner.
- the design of the burner is particularly suitable, given the given overall length of the burner, of changing the size of the tangential air inlet slots 19, 20 by fixing the partial cone bodies 1, 2 to the end plate 10 by means of a releasable connection.
- the distance between the two central axes 1b, 2b decreases or increases as a result of radial displacement of the two partial cone bodies 1, 2 to and from one another, and the gap size of the tangential air inlet slots 19, 20 changes accordingly, as can be seen particularly well from FIGS. 2-4 emerges.
- the partial cone bodies 1, 2 can also be displaced relative to one another in another plane, as a result of which even an overlap thereof can be controlled. Yes, it is even possible to spirally move the partial cone bodies 1, 2 with one another by means of a counter-rotating movement. It is therefore in your hand to vary the shape and size of the tangential air inlets 19, 20 as desired, so that the burner can be used universally without changing its overall length.
- 2-4 also shows the position of the guide plates 21a, 21b. They have flow introduction functions, whereby they, of different lengths, extend the respective end of the partial cone bodies 1 and 2 in the direction of flow of the combustion air 15.
- the channeling of the combustion air into the cone cavity 14 can be optimized by opening or closing the guide plates 21a, 21b around the pivot point 23, in particular this is necessary if the original gap size of the tangential air inlet slots 19, 20 is changed.
Abstract
Description
Die vorliegende Erfindung betrifft ein Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner ohne Vormischstrecke gemäss Oberbegriff des Anspruchs 1. Sie betrifft auch ein Brenner zur Durchführung dieses Verfahrens.The present invention relates to a method for the combustion of liquid fuel in a burner without a premix section according to the preamble of
Aus EP-A1-0 210 462 ist ein Brenner bekannt geworden, welcher aus mindestens zwei mit tangentialem Lufteintritt beaufschlagten doppelgekrümmten hohlen Teilkegelkörpern gebildet ist. Diese Körper sind in Strömungsrichtung entlang von kegelstrahlig nach aussen hin sich öffnenden Diagonalen gefalzt. Dabei bildet die eine gekrümmte Falzseite einen Innenkegel mit in Abströmungsrichtung zunehmender Kegelneigung, während die andere gekrümmte Falzseite einen Aussenkegel bildet, mit in Abströmungsrichtung abnehmender Kegelneigung. Die Innenkegel tragen endseitig, auf ihrer ganzen axialen Ausdehnung, je eine Brennstoffleitung für die Zuführung des gasförmigen Brennstoffes, der durch mehrere Brennstoffdüsen in den Innenraum des Brenners strömt, um sich dort mit der tangential einströmenden Verbrennungsluft zu vermischen. Der Brenner weist des weiteren eine separate Zuführung eines flüssigen Brennstoffes auf, womit man hier mit einem Dualbrenner zu tun. Die Eindüsung des flüssigen Brennstoffes ist axial auf die Aussenkegel gerichtet, dergestalt, dass sich dort, je nach Stärke der Eindüsung, einen verschieden langen Brennstoffilm bildet. Nebst der natürlichen Verdampfung des flüssigen Brennstoffes durch die dort herrschende Strahlungswärme, wird eine gewichtige Vermischung durch die tangential herangeführte Verbrennungsluft übernommen, welche durch ihre Drallbewegung in axialer Richtung den Brennstoffilm schichtenweise aufrollt, wodurch die Erzeugung einer starken Vermischung überflüssig wird. Dadurch, dass der Impuls der Eindüsung von flüssigem Brennstoff der Last der Maschine angepasst wird, ist das Gemisch nie zu mager oder zu fett.A burner is known from EP-A1-0 210 462, which is formed from at least two double-curved hollow partial cone bodies acted upon with tangential air entry. These bodies are folded in the direction of flow along diagonals that open outwards in the shape of a cone. One curved fold side forms an inner cone with an increasing cone inclination in the outflow direction, while the other curved fold side forms an outer cone with a decreasing cone inclination in the outflow direction. At their ends, the inner cones each carry a fuel line along their entire axial extent for the supply of the gaseous fuel which flows through several fuel nozzles into the interior of the burner in order to mix there with the tangentially flowing combustion air. The burner also has a separate supply of a liquid fuel, which is a dual burner. The injection of the liquid fuel is directed axially onto the outer cone in such a way that, depending on the strength of the injection, a different length of fuel film is formed. In addition to the natural evaporation of the liquid fuel due to the radiant heat prevailing there, weighty mixing is carried out by the tangentially introduced combustion air, which rolls up the fuel film in layers due to its swirling movement in the axial direction, making the generation of a strong mixture superfluous. Because the impulse of the injection of liquid fuel is adapted to the load of the machine, the mixture is never too lean or too rich.
Zwei Ziele lassen sich damit unmittelbar erreichen:
- Die Vorzüge eines Vormischbrenners, nämlich wenig NOx und CO, stellen sich ein.
- Eine gute Flammenstabilität in einem weiteren Betriebsbereich ist gewährleistet.
- The advantages of a premix burner, namely little NO x and CO, come about.
- Good flame stability is guaranteed in another operating area.
Des weiteren ergibt sich aus der konstruktiven Gestaltung dieses Brenners eine Wirbelströmung, welche im Zentrum drallarm ist, aber einen Axialgeschwindigkeitsüberschuss aufweist. Weil nun die Drallzahl in axialer Richtung stark zunimmt und am Ende des Brenners den Breakdown-Wert bzw. den kritischen Wert erreicht, ergibt dies eine positionsstabile Wirbelrückströmung.Furthermore, the structural design of this burner results in a vortex flow which is low in swirl in the center but has an excess of axial speed. Because the number of swirls increases strongly in the axial direction and reaches the breakdown value or the critical value at the end of the burner, this results in a positionally stable vortex backflow.
Obwohl die Vorteile des hier gewürdigten Brenners nicht wegzuleugnen sind, hat es sich doch gezeigt, dass die NOx- und CO-Emissionswerte, obwohl sie durch seinen Einsatz bereits tiefer liegen gegenüber den gesetzlichen Grenzwerten, zukünftig substantiell vermindert werden müssen. Des weiteren hat es sich auch gezeigt, dass Verkokungsprobleme des Aussenkegels aus der Oelverbrennung nicht auszuschliessen sind, und die Brennstoffeindüsung nicht einfach zu handhaben ist.Although the advantages of the burner recognized here cannot be denied, it has been shown that the NO x and CO emission values, although their use is already lower than the legal limit values, will have to be substantially reduced in the future. Furthermore it has It has also been shown that coking problems of the outer cone cannot be ruled out from the oil combustion and that the fuel injection is not easy to handle.
Des weiteren ist die Oeleindüsung konstruktiv relativ aufwendig gelöst. Aber auch die Gestaltung der gefalzten Kegelabschnitte und deren Abstimmung zueinander ist nicht einfach zu handhaben.Furthermore, the oil injection is structurally relatively complex. But the design of the folded cone sections and their coordination with each other is not easy to handle.
Hier greift die Erfindung ein. Der Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, liegt die Aufgabe zugrunde, bei einem Verfahren sowie einem Brenner der eingangs genannten Arten die körperliche Ausgestaltung des Brenners zu vereinfachen und gleichzeitig die NOx-Emissionswerte aus der vormischartigen Verbrennung von flüssigem Brennstoff zu minimieren, ohne das Strömungsfeld im Brenner mit der stabilen Wirbelrückströmzone zu verändern.This is where the invention intervenes. The object of the invention, as characterized in the claims, is to simplify the physical configuration of the burner in a method and a burner of the types mentioned at the beginning and at the same time to minimize the NO x emission values from the premixed combustion of liquid fuel, without changing the flow field in the burner with the stable vortex backflow zone.
Die wesentlichen Vorteile der Erfindung hinsichtlich der Ausgestaltung sind darin zu sehen, dass im Fehlen der sonst üblichen Vormischzone keine Gefahr eines Rückzündens in den Brenner zu befürchten ist. Des weiteren entfallen die wohlbekannten Probleme bei der Einsetzung von Drallerzeugern im Gemischstrom, beispielsweise jene Unzulänglichkeiten, die durch Abbrennen von Belägen mit Zerstörung der Drallschaufeln entstehen.The essential advantages of the invention with regard to the configuration are to be seen in the fact that, in the absence of the otherwise usual premixing zone, there is no fear of reignition in the burner. Furthermore, the well-known problems in the use of swirl generators in the mixture flow, for example those inadequacies which arise from the burning off of deposits with destruction of the swirl vanes, are eliminated.
Der wesentliche Vorteil der Erfindung hinsichtlich der NOx-Emissionswerte ist darin zu sehen, dass diese schlagartig auf einen Bruchteil dessen sinken, was man bis heute als maximal erreichbar betrachtet hat. Die Verbesserung weist also nicht bloss ein paar Prozentpunkte auf, sondern man bewegt sich nun in der Grössenordnung von verschwindend kleinen 10 - 15 % der gesetzlichen Grenzwerte, womit eine ganz neue Qualitätsstufe erreicht ist.The main advantage of the invention with regard to the NO x emission values can be seen in the fact that these suddenly drop to a fraction of what has hitherto been considered to be attainable to the maximum. So the improvement is not just a few percentage points, but you are now in the order of a tiny 10 - 15% of the legal limit values, which has reached a whole new level of quality.
Ein weiterer Vorteil der Erfindung ergibt sich aus der Möglichkeit heraus, dass der erfindungsgemässe Brenner auch in Gasturbinen eingesetzt werden kann, deren Druckverhältnis _ über etwa 12 _ so hoch ist, dass prinzipbedingt keine Vorverdampfung des Flüssigbrennstoffes mehr möglich ist, weil zuvor Selbstzündung des Brennstoffes einsetzen würde. Schliesslich ist der erfindungsgemässe Brenner auch noch in solchen Fällen einsetzbar, in denen keine oder nur eine für die Verdampfung unzureichende Luftvorerwärmung erreicht werden kann.Another advantage of the invention results from the possibility that the burner according to the invention can also be used in gas turbines, the pressure ratio of which is so high over approximately 12 that, due to the principle, no pre-evaporation of the liquid fuel is possible because the fuel has previously ignited would. Finally, the burner according to the invention can also be used in those cases in which no or only insufficient air preheating for evaporation can be achieved.
Nicht zuletzt ist ein wesentlicher Vorteil der Erfindung auch darin zu sehen, dass der erfindungsgemässe Brenner aus wenigen Bestandteilen besteht, die einfach herzustellen und zu montieren sind.Last but not least, an essential advantage of the invention is that the burner according to the invention consists of a few components that are easy to manufacture and assemble.
Vorteilhafte und zweckmässige Weiterbildungen der erfindungsgemässen Aufgabenlösung sind in den abhängigen Ansprüchen gekennzeichnet.Advantageous and expedient developments of the task solution according to the invention are characterized in the dependent claims.
Im folgenden wird anhand der Zeichnung ein Ausführungsbeispiel der Erfindung erläutert. Alle für das unmittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind fortgelassen. Die Strömungsrichtungen der verschiedenen Medien sind mit Pfeilen angegeben. In den verschiedenen Figuren sind jeweils gleiche Elemente mit den gleichen Bezugszeichen versehen.In the following an embodiment of the invention will be explained with reference to the drawing. All elements not necessary for the immediate understanding of the invention have been omitted. The flow directions of the different media are indicated by arrows. In the various figures, the same elements are provided with the same reference symbols.
Es zeigt:
- Fig. 1 einen Brenner in perspektivischer Darstellung, entsprechend aufgeschnitten und
- Fig. 2, 3, 4 entsprechende Schnitte durch die Ebenen II-II (Fig. 2), III-III (Fig. 3) und IV-IV (Fig. 4), wobei diese Schnitte nur eine schematische, vereinfachte Darstellung des Brenners sind.
- Fig. 1 a burner in a perspective view, cut accordingly and
- Fig. 2, 3, 4 corresponding sections through the planes II-II (Fig. 2), III-III (Fig. 3) and IV-IV (Fig. 4), these sections only a schematic, simplified representation of the burner are.
Um den Aufbau des Brenners besser zu verstehen, ist es von Vorteil, wenn der Leser gleichzeitig zu Fig. 1 die einzelnen Schnitte nach Fig. 2-4 heranzieht. Des weiteren, um Fig. 1 nicht unnötig unübersichtlich zu gestalten, sind in ihr die nach Fig. 2-4 schematisch gezeigten Leitbleche 21a, 21b nur andeutungsweise aufgenommen worden. Im folgenden werden auch bei der Beschreibung von Fig. 1 wahlweise, nach Bedarf, auf die restlichen Fig. 2-4 hingewiesen.In order to better understand the structure of the burner, it is advantageous if the reader uses the individual sections according to FIGS. 2-4 simultaneously with FIG. 1. Furthermore, in order not to make Fig. 1 unnecessarily confusing, the
Der Brenner gemäss Fig. 1 besteht aus zwei halben hohlen Teikegelkörpern 1, 2, die versetzt zueinander aufeinander liegen. Die Versetzung der jeweiligen Mittelachse 1b, 2b der Teilkegelkörper 1, 2 zueinander schafft auf beiden Seiten in spiegelbildlicher Anordnung jeweils einen tangentialen Lufteintrittsschlitz 19, 20 frei, (Fig. 2-4), durch welche die Verbrennungsluft 15 in den Innenraum des Brenners, d.h. in den Kegelhohlraum 14 strömt. Die beiden Teilkegelkörper 1, 2 haben je einen zylindrischen Anfangsteil 1a, 2a, die ebenfalls analog den Teilkegelkörpern 1, 2 versetzt zueinander verlaufen, so dass die tangentialen Lufteintrittsschlitze 19, 20 vom Anfang an vorhanden sind. In diesem zylindrischen Anfangsteil 1a, 2a ist eine Düse 3 untergebracht, deren Brennstoffeindüsung 4 mit dem engsten Querschnitt des durch die zwei Teilkegelkörper 1, 2 gebildeten kegeligen Hohlraumes 14 zusammenfällt. Sebstverständlich kann der Brenner rein kegelig, also ohne zylindrische Anfangsteile 1a, 2a, ausgeführt sein. Beide Teilkegelkörper 1, 2 weisen je eine Brennstoffleitung 8, 9 auf, die mit Oeffnungen 17 versehen sind, durch welche der gasförmige Brennstoff 13, der durch die tangentialen Lufteintrittsschlitze 19, 20 strömenden Verbrennungsluft 15 zugemischt wird. Die Lage dieser Brennstoffleitungen 8, 9 geht schematisch aus Fig. 2-4 hervor: Die Brennstoffleitungen 8, 9 sind am Ende der tangentialen Lufteintrittsschlitze 19, 20 angebracht, so dass dort auch die Zumischung 16 des gasförmigen Brennstoffes 13 mit der einströmenden Verbrennungsluft 15 stattfindet. Brennraumseitig 22 weist der Brenner eine kragenförmige als Verankerung für die Teilkegelkörper 1, 2 dienende Abschlussplatte 10 mit einer Anzahl Bohrungen 11 auf, durch welche nötigenfalls Verdünnungsluft bzw. Kühlluft 18 dem vorderen Teil des Brennraumes 22 bzw. dessen Wand zugeführt werden kann. Der durch die Düse 3 strömende flüssige Brennstoff 12 wird in einem spitzen Winkel in den Kegelhohlraum 14 eingedüst, dergestalt, dass sich in der Brenneraustrittsebene ein möglichst homogener kegeliger Brennstoffspray einstellt, wobei streng darauf zu achten ist, dass die Innenwände der Teilkegelkörper 1, 2 vom eingedüsten flüssigen Brennstoff 12 nicht benetzt werden. Bei der Brennstoffeindüsung 4 kann es sich um eine luftunterstützte Düse oder um einen Druckzerstäuber handeln. Das kegelige Flüssigbrennstoffprofil 5 wird von einem tangential einströmenden rotierenden Verbrennungsluftstrom 15 umschlossen. In axialer Richtung wird die Konzentration des Flüssigbrennstoffes 12 fortlaufend durch die eingemischte Verbrennungsluft 15 abgebaut. Wird gasförmiger Brennstoff 13/16 verbrannt, geschieht die Gemischbildung mit der Verbrennungsluft 15 direkt am Ende der Lufteintrittsschlitze 19, 20. Bei der Eindüsung von flüssigem Brennstoff 12 wird im Bereich des Wirbelaufplatzens, also im Bereich der Rückströmzone 6, die optimale, homogene Brennstoffkonzentration über den Querschnitt erreicht. Die Zündung erfolgt an der Spitze der Rückströmzone 6. Erst an dieser Stelle kann eine stabile Flammenfront 7 entstehen. Ein Rückschlag der Flamme ins Innere des Brenners, wie dies bei Vormischstrecken latent der Fall ist, wogegen dort mit komplizierten Flammenhaltern Abhilfe gesucht wird, ist hier nicht zu befürchten. Ist die Verbrennungsluft 15 vorgeheizt, so stellt sich eine natürliche Verdampfung des flüssigen Brennstoffes 12 ein, bevor der Punkt am Ausgang des Brenners erreicht ist, an dem die Zündung des Gemisches stattfinden kann. Der Grad der Verdampfung ist selbstverständlich von der Grösse des Brenners, der Tropfengrössenverteilung und der Temperatur der Verbrennungsluft 15 abhängig. Unabhängig aber davon, ob neben der homogenen Tropfenvormischung durch Verbrennungsluft 15 niedriger Temperatur oder zusätzlich nur eine partielle oder die vollständige Tropfenverdampfung durch vorgeheizte Verbrennungsluft 15 erreicht wird, fallen die Stickoxid- und Kohlenmonoxidemissionen niedrig aus, wenn der Luftüberschuss mindestens 60 % beträgt. Im Falle der vollständigen Verdampfung vor dem Eintritt in die Verbrennungszone sind die Schadstoffemissionswerte am niedrigsten. Gleiches gilt auch für den nahstöchiometrischen Betrieb, wenn die Ueberschussluft durch rezirkulierendes Abgas ersetzt wird. Bei der Gestaltung der Teilkegelkörper 1, 2 hinsichtlich Kegelneigung und der Breite der tangentialen Lufteintrittsschlitze 19, 20 sind enge Grenzen einzuhalten, damit sich das gewünschte Strömungsfeld der Luft mit ihrer Rückströmzone 6 im Bereich der Brennermündung zur Flammenstabilisierung einstellt. Allgemein ist zu sagen, dass eine Verkleinerung der Lufteintrittsschlitze 19, 20 die Rückströmzone 6 weiter stromaufwärts verschiebt, wodurch dann allerdings das Gemisch früher zur Zündung käme. Immerhin ist hier zu sagen, dass die einmal geometrisch fixierte Rückströmzone 6 an sich positionsstabil ist, denn die Drallzahl nimmt in Strömungsrichtung im Bereich der Kegelform des Brenners zu. Die Konstruktion des Brenners eignet sich vorzüglich, bei vorgegebener Baulänge des Brenners, die Grösse der tangentialen Lufteintrittsschllitze 19, 20 zu verändern, indem die Teilkegelkörper 1, 2 anhand einer lösbaren Verbindung mit der Abschlussplatte 10 fixiert sind. Durch radiale Verschiebung der beiden Teilkegelkörper 1, 2 zu- oder auseinander verkleinert bzw. vergrössert sich der Abstand der beiden Mittelachsen 1b, 2b, und dementsprechend verändert sich die Spaltgrösse der tangentialen Lufteintrittsschlitze 19, 20, wie dies aus Fig. 2-4 besonders gut hervorgeht. Selbstverständlich sind die Teilkegelkörper 1, 2 auch in einer anderen Ebene zueinander verschiebbar, wodurch sogar eine Ueberlappung derselben angesteuert werden kann. Ja, es ist sogar möglich, die Teilkegelkörper 1, 2 durch eine gegenläufige drehende Bewegung spiralartig eineinander zu verschieben. Somit hat man es in der Hand, die Form und die Grösse der tangentialen Lufteintritte 19, 20 beliebig zu variieren, womit der Brenner ohne Veränderung seiner Baulänge universell einsetzbar ist.The burner according to FIG. 1 consists of two half hollow
Aus Fig. 2-4 geht auch die Lage der Leitbleche 21a, 21b hervor. Sie haben Strömungseinleitungsfunktionen, wobei sie, verschieden lang, das jeweilige Ende der Teilkegelkörper 1 und 2 in Anströmungsrichtung der Verbrennungsluft 15 verlängern. Die Kanalisierung der Verbrennungsluft in den Kegelhohlraum 14 kann durch Oeffnung bzw. Schliessung der Leitbleche 21a, 21b um den Drehpunkt 23 optimiert werden, insbesondere ist dies dann vonnöten, wenn die ursprüngliche Spaltgrösse der tangentialen Lufteintrittsschlitze 19, 20 verändert wird.2-4 also shows the position of the
Claims (8)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT88120667T ATE63628T1 (en) | 1987-12-21 | 1988-12-10 | PROCESS FOR COMBUSTION OF LIQUID FUEL IN A BURNER. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4980/87 | 1987-12-21 | ||
CH4980/87A CH674561A5 (en) | 1987-12-21 | 1987-12-21 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0321809A1 EP0321809A1 (en) | 1989-06-28 |
EP0321809B1 true EP0321809B1 (en) | 1991-05-15 |
Family
ID=4285866
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP88120667A Expired - Lifetime EP0321809B1 (en) | 1987-12-21 | 1988-12-10 | Process for combustion of liquid fuel in a burner |
Country Status (8)
Country | Link |
---|---|
US (1) | US4932861A (en) |
EP (1) | EP0321809B1 (en) |
JP (1) | JP2608320B2 (en) |
KR (1) | KR0129752B1 (en) |
AT (1) | ATE63628T1 (en) |
CA (1) | CA1312816C (en) |
CH (1) | CH674561A5 (en) |
DE (1) | DE3862854D1 (en) |
Cited By (135)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0298386A2 (en) | 1987-07-06 | 1989-01-11 | University Of Waterloo | Polymer hydrogenation process |
EP0394911A1 (en) * | 1989-04-27 | 1990-10-31 | Asea Brown Boveri Ag | Combustion installation |
EP0394800A1 (en) * | 1989-04-24 | 1990-10-31 | Asea Brown Boveri Ag | Premix burner for generating a hot gas |
EP0433790A1 (en) * | 1989-12-22 | 1991-06-26 | Asea Brown Boveri Ag | Burner |
EP0433789A1 (en) * | 1989-12-19 | 1991-06-26 | Asea Brown Boveri Ag | Method for a premix burning of a liquid fuel |
EP0436113A1 (en) * | 1989-12-01 | 1991-07-10 | Asea Brown Boveri Ag | Method for operating a combustion plant |
EP0461447A1 (en) * | 1990-06-07 | 1991-12-18 | Asea Brown Boveri Ag | Pressurised atomising nozzle |
EP0483554A1 (en) * | 1990-11-02 | 1992-05-06 | Asea Brown Boveri Ag | Method for minimising the NOx emissions from a combustion |
EP0491079A1 (en) * | 1990-12-19 | 1992-06-24 | Asea Brown Boveri Ag | Burner head for premix combustion of a liquid fuel in an atmospheric combustion installation |
EP0503319A2 (en) * | 1991-03-12 | 1992-09-16 | Asea Brown Boveri Ag | Burner for a premixing combustion of a liquid and/or a gaseous fuel |
EP0518072A1 (en) * | 1991-06-14 | 1992-12-16 | Asea Brown Boveri Ag | Burner for an internal combustion engine, a combustion chamber of a gas turbine plant or a furnace |
EP0521325A1 (en) * | 1991-07-03 | 1993-01-07 | Asea Brown Boveri Ag | Combustion chamber |
EP0548396A1 (en) * | 1991-12-23 | 1993-06-30 | Asea Brown Boveri Ag | Device for mixing of two gaseous components and burner in which this device is applied |
EP0561011A1 (en) * | 1992-03-16 | 1993-09-22 | Asea Brown Boveri Ag | Intercooled compressor |
DE4223828A1 (en) * | 1992-05-27 | 1993-12-02 | Asea Brown Boveri | Method for operating a combustion chamber of a gas turbine |
EP0576697A1 (en) * | 1992-06-29 | 1994-01-05 | Abb Research Ltd. | Combustor chamber for a gas turbine |
EP0592717A1 (en) * | 1992-10-16 | 1994-04-20 | Asea Brown Boveri Ag | Gas-operated premix burner |
EP0593816A1 (en) * | 1992-10-23 | 1994-04-27 | Asea Brown Boveri Ag | Burner with electric ignition device |
EP0619457A1 (en) * | 1993-04-08 | 1994-10-12 | ABB Management AG | Premix burner |
EP0641971A2 (en) * | 1993-09-06 | 1995-03-08 | Abb Research Ltd. | Method for operating a premix burner |
EP0675322A2 (en) * | 1994-04-02 | 1995-10-04 | ABB Management AG | Premix burner |
EP0697507A2 (en) | 1994-08-19 | 1996-02-21 | ABB Management AG | Gasturbine speed control method for sudden load loss |
EP0713058A1 (en) | 1994-11-19 | 1996-05-22 | ABB Management AG | Multi-stage combustion chamber |
EP0714001A2 (en) | 1994-11-23 | 1996-05-29 | ABB Management AG | Combustion chamber with premix burners |
EP0719983A1 (en) | 1994-12-27 | 1996-07-03 | ABB Management AG | Method and device for feeding gaseous fuel in a premix burner |
US5562441A (en) * | 1994-07-25 | 1996-10-08 | Abb Research Ltd. | Burner |
US5569020A (en) * | 1994-11-05 | 1996-10-29 | Abb Research Ltd. | Method and device for operating a premixing burner |
US5573392A (en) * | 1994-07-13 | 1996-11-12 | Abb Research Ltd. | Method and device for distributing fuel in a burner suitable for both liquid and gaseous fuels |
US5573395A (en) * | 1994-04-02 | 1996-11-12 | Abb Management Ag | Premixing burner |
US5586878A (en) * | 1994-11-12 | 1996-12-24 | Abb Research Ltd. | Premixing burner |
US5588826A (en) * | 1994-10-01 | 1996-12-31 | Abb Management Ag | Burner |
US5593302A (en) * | 1994-05-19 | 1997-01-14 | Abb Management Ag | Combustion chamber having self-ignition |
US5609017A (en) * | 1994-05-19 | 1997-03-11 | Abb Management Ag | Method and apparatus for operating a combustion chamber for autoignition of a fuel |
US5617718A (en) * | 1994-05-26 | 1997-04-08 | Asea Brown Boveri Ag | Gas-turbine group with temperature controlled fuel auto-ignition |
US5626017A (en) * | 1994-07-25 | 1997-05-06 | Abb Research Ltd. | Combustion chamber for gas turbine engine |
EP0778445A2 (en) | 1995-12-05 | 1997-06-11 | Asea Brown Boveri Ag | Premix burner |
EP0780630A2 (en) | 1995-12-21 | 1997-06-25 | Abb Research Ltd. | Burner for a heat generator |
EP0780629A2 (en) | 1995-12-21 | 1997-06-25 | ABB Research Ltd. | Burner for a heat generator |
EP0780628A2 (en) | 1995-12-21 | 1997-06-25 | Abb Research Ltd. | Premix burner for a heat generator |
EP0783089A2 (en) | 1995-12-27 | 1997-07-09 | Abb Research Ltd. | Cone-shaped burner |
US5661967A (en) * | 1995-04-24 | 1997-09-02 | Asea Brown Boveri Ag | Method of operating a sequentially fired gas-turbine group |
US5664943A (en) * | 1994-07-13 | 1997-09-09 | Abb Research Ltd. | Method and device for operating a combined burner for liquid and gaseous fuels |
US5673551A (en) * | 1993-05-17 | 1997-10-07 | Asea Brown Boveri Ag | Premixing chamber for operating an internal combustion engine, a combustion chamber of a gas turbine group or a firing system |
US5674066A (en) * | 1995-01-30 | 1997-10-07 | Asea Brown Boveri Ag | Burner |
US5685705A (en) * | 1994-03-11 | 1997-11-11 | Asea Brown Boveri Ag | Method and appliance for flame stabilization in premixing burners |
US5687571A (en) * | 1995-02-20 | 1997-11-18 | Asea Brown Boveri Ag | Combustion chamber with two-stage combustion |
US5689948A (en) * | 1995-03-07 | 1997-11-25 | Asea Brown Boveri Ag | Method of operating a reheat power plant with steam injection |
US5699667A (en) * | 1994-12-28 | 1997-12-23 | Asea Brown Boveri Ag | Gas-operated premixing burner for gas turbine |
US5738509A (en) * | 1995-05-08 | 1998-04-14 | Asea Brown Boveri Ag | Premix burner having axial or radial air inflow |
US5737912A (en) * | 1995-10-10 | 1998-04-14 | Asea Brown Boveri Ag | Method for starting gas turbine in combined cycle power station |
US5738508A (en) * | 1995-04-25 | 1998-04-14 | Abb Research Ltd. | Burner |
US5755166A (en) * | 1993-12-21 | 1998-05-26 | Abb Carbon Ab | Method and device for after-burning of particulate fuel in a power plant |
US5765366A (en) * | 1995-07-03 | 1998-06-16 | Asea Brown Boveri Ag | Fuel feed for gas turbines having an annular combustion chamber |
EP0851176A2 (en) | 1996-12-30 | 1998-07-01 | Abb Research Ltd. | Boiler for a heat generator |
EP0851172A2 (en) | 1996-12-23 | 1998-07-01 | Abb Research Ltd. | Burner for operating a combustion chamber with a liquid and/or gaseous fuel |
US5782627A (en) * | 1996-06-29 | 1998-07-21 | Abb Research Ltd. | Premix burner and method of operating the burner |
US5791892A (en) * | 1995-11-23 | 1998-08-11 | Abb Research Ltd. | Premix burner |
US5791891A (en) * | 1995-09-30 | 1998-08-11 | Abb Research Ltd. | Method and device for burning fuels |
US5829967A (en) * | 1995-03-24 | 1998-11-03 | Asea Brown Boveri Ag | Combustion chamber with two-stage combustion |
EP0877156A2 (en) | 1997-05-09 | 1998-11-11 | Abb Research Ltd. | Method and device to vaporize liquid fuel for use in a gas turbine combustor |
US5839269A (en) * | 1995-10-02 | 1998-11-24 | Asea Brown Boveri Ag | Method of operating a combined gas and power steam plant |
DE19726975A1 (en) * | 1997-06-26 | 1999-01-07 | Asea Brown Boveri | Jet engine |
EP0902233A1 (en) | 1997-09-15 | 1999-03-17 | Abb Research Ltd. | Combined pressurised atomising nozzle |
US5884470A (en) * | 1996-04-22 | 1999-03-23 | Asea Brown Boveri Ag | Method of operating a combined-cycle plant |
US5884471A (en) * | 1996-05-10 | 1999-03-23 | Asea Brown Boveri Ag | Device for operating an annular combustion chamber equipped with combined burners for liquid and gaseous fuels |
US5885068A (en) * | 1996-04-09 | 1999-03-23 | Abb Research Ltd. | Combustion chamber |
EP0913630A1 (en) | 1997-10-31 | 1999-05-06 | Abb Research Ltd. | Burner for the operation of a heat generator |
EP0919768A1 (en) | 1997-11-25 | 1999-06-02 | Abb Research Ltd. | Burner for the operation of a heat generator |
US5921766A (en) * | 1996-05-17 | 1999-07-13 | Abb Research Ltd. | Burner |
US5934555A (en) * | 1996-03-05 | 1999-08-10 | Abb Research Ltd. | Pressure atomizer nozzle |
US5961313A (en) * | 1997-03-18 | 1999-10-05 | Abb Research Ltd. | Method of operating a swirl stabilized burner and burner for carrying out the method |
US5980240A (en) * | 1997-12-22 | 1999-11-09 | Asea Brown Boveri Ag | Burner |
US5984670A (en) * | 1996-12-21 | 1999-11-16 | Asea Brown Boveri Ag | Burner |
US5983643A (en) * | 1996-04-22 | 1999-11-16 | Asea Brown Boveri Ag | Burner arrangement with interference burners for preventing pressure pulsations |
US6027331A (en) * | 1997-11-13 | 2000-02-22 | Abb Research Ltd. | Burner for operating a heat generator |
US6045351A (en) * | 1997-12-22 | 2000-04-04 | Abb Alstom Power (Switzerland) Ltd | Method of operating a burner of a heat generator |
US6045058A (en) * | 1997-07-17 | 2000-04-04 | Abb Research Ltd. | Pressure atomizer nozzle |
US6050078A (en) * | 1996-11-29 | 2000-04-18 | Abb Research Ltd. | Gas turbine combustion chamber with two stages and enhanced acoustic properties |
US6055813A (en) * | 1997-08-30 | 2000-05-02 | Asea Brown Boveri Ag | Plenum |
EP1001214A1 (en) | 1998-11-09 | 2000-05-17 | Asea Brown Boveri AG | Process to prevent the formation of flow instabilities in a burner |
EP1004821A1 (en) | 1998-11-25 | 2000-05-31 | Asea Brown Boveri AG | Method and device for pulverising liquid fuel for a combustion plant |
EP1010939A1 (en) | 1998-12-15 | 2000-06-21 | ABB Alstom Power (Schweiz) AG | Combustion chamber with acoustic damped fuel supply system |
WO2000039503A1 (en) | 1998-12-23 | 2000-07-06 | Alstom (Schweiz) Ag | Burner for heat generator |
US6098406A (en) * | 1996-12-21 | 2000-08-08 | Asea Brown Boveri Ag | Premix Burner for operating a combustion chamber with a liquid and/or gaseous fuel |
US6126439A (en) * | 1996-09-30 | 2000-10-03 | Abb Alstom Power (Switzerland) Ltd | Premix burner |
US6132202A (en) * | 1997-10-27 | 2000-10-17 | Asea Brown Boveri Ag | Method and device for operating a premix burner |
US6141954A (en) * | 1998-05-18 | 2000-11-07 | United Technologies Corporation | Premixing fuel injector with improved flame disgorgement capacity |
US6189211B1 (en) | 1998-05-15 | 2001-02-20 | Asea Brown Boveri Ag | Method and arrangement for carrying out repair and/or maintenance work in the inner casing of a multishell turbomachine |
US6192669B1 (en) | 1997-03-20 | 2001-02-27 | Asea Brown Boveri Ag | Combustion chamber of a gas turbine |
US6210152B1 (en) | 1998-09-16 | 2001-04-03 | Abb Research Ltd. | Burner for a heat generator and method for operating the same |
US6263676B1 (en) | 1998-08-19 | 2001-07-24 | Asea Brown Boveri Ag | Burner having a frame for operating an internal combustion machine |
US6331109B1 (en) | 1999-07-22 | 2001-12-18 | Alstom (Switzerland) Ltd. | Premix burner |
US6336806B1 (en) * | 1999-07-14 | 2002-01-08 | Alstom (Switzerland) Ltd. | Method for combustion of a liquid fuel in a combustion system, and a combustion system for carrying out the method |
US6343927B1 (en) | 1999-07-23 | 2002-02-05 | Alstom (Switzerland) Ltd | Method for active suppression of hydrodynamic instabilities in a combustion system and a combustion system for carrying out the method |
DE10049204A1 (en) * | 2000-10-05 | 2002-04-11 | Alstom Switzerland Ltd | Device and method for the electrostatic atomization of a liquid medium |
WO2002033324A1 (en) | 2000-10-16 | 2002-04-25 | Alstom (Switzerland) Ltd. | Burner with progressive fuel injection |
US6390805B1 (en) | 1998-09-16 | 2002-05-21 | Asea Brown Boveri Ag | Method of preventing flow instabilities in a burner |
US6402059B1 (en) | 1999-02-15 | 2002-06-11 | Alstom (Switzerland) Ltd | Fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, and method of operating such a fuel lance |
EP1262714A1 (en) | 2001-06-01 | 2002-12-04 | ALSTOM (Switzerland) Ltd | Burner with exhausts recirculation |
US6558154B2 (en) | 2000-11-13 | 2003-05-06 | Alstom (Switzerland) Ltd | Burner system with staged fuel injection and method for its operation |
US6584775B1 (en) | 1999-09-20 | 2003-07-01 | Alstom | Control of primary measures for reducing the formation of thermal nitrogen oxides in gas turbines |
EP1336800A1 (en) | 2002-02-13 | 2003-08-20 | ALSTOM (Switzerland) Ltd | Method for reducing the oscillations induced by the combustion in combustion systems and premix burner for carrying out the method |
US6640545B2 (en) | 2000-12-22 | 2003-11-04 | Alstom Ltd. | Burner with high flame stability |
US6679060B2 (en) | 2000-12-16 | 2004-01-20 | Alstom Technology Ltd | Method for operating a premix burner |
EP1389713A1 (en) | 2002-08-12 | 2004-02-18 | ALSTOM (Switzerland) Ltd | Premixed exit ring pilot burner |
US6705857B2 (en) | 2000-11-09 | 2004-03-16 | Alstom Technology Ltd. | Method for injecting fuel into a burner |
US6834504B2 (en) | 2001-07-26 | 2004-12-28 | Alstom Technology Ltd | Premix burner with high flame stability having a net-like structure within the mixing section |
DE19507088B4 (en) * | 1995-03-01 | 2005-01-27 | Alstom | premix |
US6901760B2 (en) | 2000-10-11 | 2005-06-07 | Alstom Technology Ltd | Process for operation of a burner with controlled axial central air mass flow |
US6969251B2 (en) | 2002-10-12 | 2005-11-29 | Alstom Technology Ltd | Burner |
DE4412315B4 (en) * | 1994-04-11 | 2005-12-15 | Alstom | Method and device for operating the combustion chamber of a gas turbine |
US7003957B2 (en) | 2001-10-19 | 2006-02-28 | Alstom Technology Ltd | Burner for synthesis gas |
US7069727B2 (en) | 2003-02-11 | 2006-07-04 | Alstom Technology Ltd. | Method for operating a gas turbo group |
DE19545310B4 (en) * | 1995-12-05 | 2008-06-26 | Alstom | premix |
US7424804B2 (en) | 2003-03-07 | 2008-09-16 | Alstom Technology Ltd | Premix burner |
US7428817B2 (en) | 2004-02-12 | 2008-09-30 | Alstom Technology Ltd | Premix burner with a swirl generator delimiting a conical swirl space and having sensor monitoring |
US7445445B2 (en) | 2003-09-01 | 2008-11-04 | Alstom Technology Ltd. | Burner having a burner lance and staged fuel injection |
DE19721937B4 (en) * | 1997-05-26 | 2008-12-11 | Alstom | Premix burner for operating a unit for generating a hot gas |
DE19542644B4 (en) * | 1995-11-17 | 2008-12-11 | Alstom | premixed |
EP2058590A1 (en) | 2007-11-09 | 2009-05-13 | 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 |
US7568335B2 (en) | 2005-09-09 | 2009-08-04 | Alstom Technology Ltd | Gas turbogroup |
DE19914666B4 (en) * | 1999-03-31 | 2009-08-20 | Alstom | Burner for a heat generator |
DE102008012794B3 (en) * | 2008-03-05 | 2009-08-20 | Auerhahn Bestecke Gmbh | firing |
US7584616B2 (en) | 2004-12-23 | 2009-09-08 | Alstom Technology Ltd | Method for the operation of a gas turbo group |
EP2299178A1 (en) | 2009-09-17 | 2011-03-23 | Alstom Technology Ltd | A method and gas turbine combustion system for safely mixing H2-rich fuels with air |
WO2011032935A2 (en) | 2009-09-17 | 2011-03-24 | Alstom Technology Ltd. | Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method |
EP2796788A1 (en) | 2013-04-24 | 2014-10-29 | Alstom Technology Ltd | Swirl generator |
EP2848865A1 (en) | 2013-09-12 | 2015-03-18 | Alstom Technology Ltd | Thermoacoustic stabilization method |
EP2933559A1 (en) | 2014-04-16 | 2015-10-21 | Alstom Technology Ltd | Fuel mixing arragement and combustor with such a fuel mixing arrangement |
EP3062019A1 (en) | 2015-02-27 | 2016-08-31 | General Electric Technology GmbH | Method and device for flame stabilization in a burner system of a stationary combustion engine |
CN107270285A (en) * | 2016-04-08 | 2017-10-20 | 安萨尔多能源瑞士股份公司 | Method and burner for burning fuel |
US9829200B2 (en) | 2013-08-16 | 2017-11-28 | Ansaldo Energia Switzerland AG | Burner arrangement and method for operating a burner arrangement |
DE102005011287B4 (en) | 2004-03-31 | 2018-07-19 | Ansaldo Energia Ip Uk Limited | Method and an apparatus for operating at least one burner for firing the combustion chamber of a heat engine or gas turbine |
DE102006059532B4 (en) | 2006-02-20 | 2020-07-09 | Ansaldo Energia Ip Uk Limited | Method for operating a gas turbine arrangement with sequential combustion |
Families Citing this family (143)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5193995A (en) * | 1987-12-21 | 1993-03-16 | Asea Brown Boveri Ltd. | Apparatus for premixing-type combustion of liquid fuel |
CH678757A5 (en) * | 1989-03-15 | 1991-10-31 | Asea Brown Boveri | |
CH678568A5 (en) * | 1989-03-15 | 1991-09-30 | Asea Brown Boveri | |
CH680084A5 (en) * | 1989-06-06 | 1992-06-15 | Asea Brown Boveri | |
US5165241A (en) * | 1991-02-22 | 1992-11-24 | General Electric Company | Air fuel mixer for gas turbine combustor |
AU2923792A (en) * | 1991-10-28 | 1993-06-07 | Irvin Glassman | Asymmetric whirl combustion |
US5307634A (en) * | 1992-02-26 | 1994-05-03 | United Technologies Corporation | Premix gas nozzle |
US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
DE4237187A1 (en) * | 1992-11-04 | 1994-05-05 | Raimund Prof Dr Ruderich | Turbulence-generator for burner or mixer - has spiral surfaces for guidance of fuel and air |
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 |
DE4306956A1 (en) * | 1993-03-05 | 1994-09-08 | Abb Management Ag | Fuel feed for a gas turbine |
CH687269A5 (en) * | 1993-04-08 | 1996-10-31 | Abb Management Ag | Gas turbine group. |
US5623826A (en) * | 1993-07-30 | 1997-04-29 | Hitachi, Ltd. | Combustor having a premix chamber with a blade-like structural member and method of operating the combustor |
DE4325802B4 (en) * | 1993-07-31 | 2005-07-07 | Alstom | Method for operating a gas turbine plant with liquid or gaseous fuel |
SE9304194L (en) * | 1993-12-17 | 1995-06-18 | Abb Stal Ab | fuel spreader |
US5444982A (en) * | 1994-01-12 | 1995-08-29 | General Electric Company | Cyclonic prechamber with a centerbody |
US5461865A (en) * | 1994-02-24 | 1995-10-31 | United Technologies Corporation | Tangential entry fuel nozzle |
DE4409918A1 (en) * | 1994-03-23 | 1995-09-28 | Abb Management Ag | Low calorific value fuel burner for combustion chamber |
DE4416650A1 (en) * | 1994-05-11 | 1995-11-16 | Abb Management Ag | Combustion process for atmospheric combustion plants |
DE4446543A1 (en) | 1994-12-24 | 1996-06-27 | Abb Management Ag | Power plant |
DE4446610A1 (en) | 1994-12-24 | 1996-06-27 | Abb Management Ag | Process for operating a gas turbine group |
DE19510743A1 (en) * | 1995-02-20 | 1996-09-26 | Abb Management Ag | Combustion chamber with two stage combustion |
DE19527453B4 (en) * | 1995-07-27 | 2009-05-07 | Alstom | premix |
US5772422A (en) * | 1996-08-27 | 1998-06-30 | Pvi Industries, Inc. | Burner array for water heating apparatus |
DE19721936A1 (en) | 1997-05-26 | 1998-12-03 | Abb Research Ltd | Burner for operating a unit for generating a hot gas |
EP0915232B1 (en) | 1997-07-25 | 2003-02-26 | ALSTOM (Switzerland) Ltd | Process for operating a power plant |
DE19736902A1 (en) * | 1997-08-25 | 1999-03-04 | Abb Research Ltd | Burners for a heat generator |
DE19737998A1 (en) | 1997-08-30 | 1999-03-04 | Abb Research Ltd | Burner device |
ATE234444T1 (en) * | 1997-10-27 | 2003-03-15 | Alstom Switzerland Ltd | METHOD FOR OPERATING A PREMIX BURNER |
US6176087B1 (en) * | 1997-12-15 | 2001-01-23 | United Technologies Corporation | Bluff body premixing fuel injector and method for premixing fuel and air |
EP0978635B1 (en) | 1998-08-05 | 2003-05-28 | ALSTOM (Switzerland) Ltd | Process for cooling the thermally stressed structures of a power plant |
EP0981019A1 (en) | 1998-08-20 | 2000-02-23 | Asea Brown Boveri AG | Method and burner for combustion of liquid fuels |
EP0995891B1 (en) | 1998-10-20 | 2005-06-15 | ALSTOM Technology Ltd | Turbomachine and method for its operation |
EP0995910A1 (en) | 1998-10-20 | 2000-04-26 | Abb Research Ltd. | Vortex valve |
DE19851636A1 (en) * | 1998-11-10 | 2000-05-11 | Asea Brown Boveri | Damping device for reducing vibration amplitude of acoustic waves for burner for internal combustion engine operation is preferably for driving gas turbo-group, with mixture area for air and fuel |
EP1065346A1 (en) | 1999-07-02 | 2001-01-03 | Asea Brown Boveri AG | Gas-turbine engine combustor |
EP1070915B1 (en) | 1999-07-22 | 2004-05-19 | ALSTOM Technology Ltd | Premix burner |
IT1313774B1 (en) | 1999-10-06 | 2002-09-17 | Rft Spa | DETECTION SYSTEM FOR THE ROTATION SPEED OF A SHAFT OF AN INTERNAL COMBUSTION ENGINE. |
DE19948674B4 (en) * | 1999-10-08 | 2012-04-12 | Alstom | Combustion device, in particular for the drive of gas turbines |
DE19948673B4 (en) * | 1999-10-08 | 2009-02-26 | Alstom | Method for producing hot gases in a combustion device and combustion device for carrying out the method |
DE19948956A1 (en) * | 1999-10-11 | 2001-04-12 | Asea Brown Boveri | Mounting system for burner duct in gas turbine cylinder comprises internal groove in cylinder into which lugs on top and bottom retaining components fit, side pieces being fitted between retaining components and bolted into place |
EP1292795B1 (en) * | 2000-06-15 | 2005-05-04 | ALSTOM Technology Ltd | Method for operating a burner with staged premix gas injection |
DE10040869A1 (en) | 2000-08-21 | 2002-03-07 | Alstom Power Nv | Method and device for suppressing flow vortices within a fluid power machine |
US6474071B1 (en) * | 2000-09-29 | 2002-11-05 | General Electric Company | Multiple injector combustor |
DE10049205A1 (en) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Process for supplying fuel to a premix burner for operating a gas turbine comprises introducing premix gas separately via two axially divided regions along the burner shell |
US6360776B1 (en) | 2000-11-01 | 2002-03-26 | Rolls-Royce Corporation | Apparatus for premixing in a gas turbine engine |
WO2003038253A1 (en) * | 2001-10-31 | 2003-05-08 | Alstom Technology Ltd | Sequentially-fired gas turbine unit |
ES2295423T3 (en) * | 2001-12-20 | 2008-04-16 | Alstom Technology Ltd | PROCEDURE FOR INJECTION OF A FUEL / AIR MIXTURE IN A COMBUSTION CHAMBER. |
DE10164099A1 (en) | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Burner with staged fuel injection |
AU2003238524A1 (en) | 2002-05-16 | 2003-12-02 | Alstom Technology Ltd | Premix burner |
DE10233805B4 (en) | 2002-07-25 | 2013-08-22 | Alstom Technology Ltd. | Annular combustion chamber for a gas turbine |
CN101793393B (en) * | 2002-08-09 | 2012-09-05 | 杰富意钢铁株式会社 | Tubular flame burner and combustion control method |
KR20040015644A (en) * | 2002-08-13 | 2004-02-19 | 주식회사 제이에이치에너지 | Sprayer and mixer of oxygen, hydrogen and liquid fuel for burner |
GB0305025D0 (en) | 2003-03-05 | 2003-04-09 | Alstom Switzerland Ltd | Method and device for efficient usage of cooling air for acoustic damping of combustion chamber pulsations |
JP3940705B2 (en) * | 2003-06-19 | 2007-07-04 | 株式会社日立製作所 | Gas turbine combustor and fuel supply method thereof |
DE102004002631A1 (en) * | 2004-01-19 | 2005-08-11 | Alstom Technology Ltd | A method of operating a gas turbine combustor |
US7896646B2 (en) | 2004-01-20 | 2011-03-01 | Alstom Technology Ltd | Premixing burner arrangement for operating a combustion chamber in addition to a method for operating a combustion chamber |
ATE389852T1 (en) | 2004-03-30 | 2008-04-15 | Alstom Technology Ltd | DEVICE AND METHOD FOR FLAME STABILIZATION IN A BURNER |
EP1730447A1 (en) * | 2004-03-31 | 2006-12-13 | Alstom Technology Ltd | Burner |
DE102004049491A1 (en) | 2004-10-11 | 2006-04-20 | Alstom Technology Ltd | premix |
WO2006048405A1 (en) | 2004-11-03 | 2006-05-11 | Alstom Technology Ltd | Premix burner |
CN101069039B (en) | 2004-11-30 | 2011-10-19 | 阿尔斯托姆科技有限公司 | Method and device for burning hydrogen in a premix burner |
WO2006069861A1 (en) | 2004-12-23 | 2006-07-06 | Alstom Technology Ltd | Premix burner comprising a mixing section |
ATE479054T1 (en) | 2005-03-09 | 2010-09-15 | Alstom Technology Ltd | PREMIX BURNER FOR GENERATING AN IGNITIBLE FUEL-AIR MIXTURE |
CN101137869A (en) | 2005-03-09 | 2008-03-05 | 阿尔斯托姆科技有限公司 | Premix burner for operating a combustion chamber |
JP2008534896A (en) | 2005-03-23 | 2008-08-28 | アルストム テクノロジー リミテッド | Method and apparatus for burning hydrogen in a premix burner |
EP1734306B1 (en) | 2005-06-17 | 2010-09-08 | Alstom Technology Ltd | Burner for premix-type combustion |
EP1943464A1 (en) * | 2005-11-04 | 2008-07-16 | ALSTOM Technology Ltd | Fuel lance |
EP1999410B1 (en) | 2006-03-27 | 2015-12-02 | Alstom Technology Ltd | Burner for the operation of a heat generator |
EP1999409B1 (en) | 2006-03-30 | 2018-05-02 | Ansaldo Energia IP UK Limited | Burner arrangement |
EP1843098A1 (en) * | 2006-04-07 | 2007-10-10 | Siemens Aktiengesellschaft | Gas turbine combustor |
WO2008091801A2 (en) * | 2007-01-22 | 2008-07-31 | Rolls-Royce Fuel Cell Systems Inc. | Multistage combustor and method for starting a fuel cell system |
WO2009019113A2 (en) | 2007-08-07 | 2009-02-12 | Alstom Technology Ltd | Burner for a combustion chamber of a turbo group |
WO2009019114A2 (en) * | 2007-08-07 | 2009-02-12 | Alstom Technology Ltd | Burner for a combustion chamber of a turbine group |
EP2225488B1 (en) | 2007-11-27 | 2013-07-17 | Alstom Technology Ltd | Premix burner for a gas turbine |
WO2009068427A1 (en) | 2007-11-27 | 2009-06-04 | Alstom Technology Ltd | Device and method for operating a gas turbine system using a second, hydrogen-rich fuel |
EP2071156B1 (en) | 2007-12-10 | 2013-11-06 | Alstom Technology Ltd | Fuel distribution system for a gas turbine with multistage burner arrangement |
WO2009083456A2 (en) | 2007-12-29 | 2009-07-09 | Alstom Technology Ltd | Gas turbine |
EP2090830B1 (en) | 2008-02-13 | 2017-01-18 | General Electric Technology GmbH | Fuel supply arrangement |
WO2009103636A1 (en) | 2008-02-20 | 2009-08-27 | Alstom Technology Ltd. | Thermal machine |
MY161317A (en) | 2008-02-20 | 2017-04-14 | General Electric Technology Gmbh | Gas turbine |
EP2242915B1 (en) * | 2008-02-20 | 2018-06-13 | General Electric Technology GmbH | Gas turbine having an improved cooling architecture |
WO2009103658A1 (en) * | 2008-02-20 | 2009-08-27 | Alstom Technology Ltd | Gas turbine having an annular combustion chamber |
EP2252831B1 (en) | 2008-03-07 | 2013-05-08 | Alstom Technology Ltd | Burner arrangement, and use of such a burner arrangement |
WO2009109454A1 (en) | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Method and burner arrangement for the production of hot gas, and use of said method |
WO2009109448A1 (en) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Burner arrangement, and use of such a burner arrangement |
JP5490091B2 (en) | 2008-03-28 | 2014-05-14 | アルストム テクノロジー リミテッド | Gas turbine guide vanes |
JP2011515618A (en) | 2008-03-28 | 2011-05-19 | アルストム テクノロジー リミテッド | Gas turbine stationary blade and gas turbine equipped with such a stationary blade |
EP2268900A1 (en) * | 2008-03-28 | 2011-01-05 | Alstom Technology Ltd | Blade for a rotating thermal engine |
JP2011516269A (en) * | 2008-03-31 | 2011-05-26 | アルストム テクノロジー リミテッド | Blade for gas turbine |
EP2300686B1 (en) | 2008-05-26 | 2013-08-07 | Alstom Technology Ltd | Gas turbine comprising a guide vane |
CH700799A1 (en) | 2009-04-11 | 2010-10-15 | Alstom Technology Ltd | Combustor with Helmholtz damper for a gas turbine. |
JP5462527B2 (en) * | 2009-05-19 | 2014-04-02 | 大阪瓦斯株式会社 | Tubular flame burner |
CH701803A1 (en) | 2009-09-03 | 2011-03-15 | Alstom Technology Ltd | Gas turbine group and method for operating such a gas turbine group. |
WO2011054757A2 (en) | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | Reheat burner injection system with fuel lances |
WO2011054760A1 (en) | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | A cooling scheme for an increased gas turbine efficiency |
EP2496883B1 (en) | 2009-11-07 | 2016-08-10 | Alstom Technology Ltd | Premixed burner for a gas turbine combustor |
WO2011054739A2 (en) | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | Reheat burner injection system |
WO2011054766A2 (en) | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | Reheat burner injection system |
JP5448762B2 (en) * | 2009-12-02 | 2014-03-19 | 三菱重工業株式会社 | Combustion burner for gas turbine |
CH702594A1 (en) | 2010-01-28 | 2011-07-29 | Alstom Technology Ltd | Helmholtz damper for incorporation in the combustor of a gas turbine and method of installation of such a Helmholtz damper. |
CH703655A1 (en) * | 2010-08-27 | 2012-02-29 | Alstom Technology Ltd | Premix FOR A GAS TURBINE. |
US20120255472A1 (en) * | 2011-04-06 | 2012-10-11 | Gordon Norman R | Burner assembly and method for reducing nox emissions |
CH704829A2 (en) | 2011-04-08 | 2012-11-15 | Alstom Technology Ltd | Gas turbine group and associated operating method. |
RU2550370C2 (en) | 2011-05-11 | 2015-05-10 | Альстом Текнолоджи Лтд | Centrifugal nozzle with projecting parts |
EP2522912B1 (en) | 2011-05-11 | 2019-03-27 | Ansaldo Energia Switzerland AG | Flow straightener and mixer |
JP5203489B2 (en) * | 2011-06-15 | 2013-06-05 | 中外炉工業株式会社 | Combustion device |
WO2014001230A1 (en) | 2012-06-29 | 2014-01-03 | Alstom Technology Ltd | Method for a part load co reduction operation for a sequential gas turbine |
RU2561956C2 (en) | 2012-07-09 | 2015-09-10 | Альстом Текнолоджи Лтд | Gas-turbine combustion system |
CN104541104A (en) | 2012-08-24 | 2015-04-22 | 阿尔斯通技术有限公司 | Sequential combustion with dilution gas mixer |
RU2570480C2 (en) * | 2012-08-24 | 2015-12-10 | Альстом Текнолоджи Лтд | Mixing of diluting air in gas turbine sequential combustion system |
AU2013219140B2 (en) | 2012-08-24 | 2015-10-08 | Ansaldo Energia Switzerland AG | Method for mixing a dilution air in a sequential combustion system of a gas turbine |
EP2703721B1 (en) | 2012-08-31 | 2019-05-22 | Ansaldo Energia IP UK Limited | Premix burner |
CA2830031C (en) | 2012-10-23 | 2016-03-15 | Alstom Technology Ltd. | Burner for a can combustor |
KR20150074155A (en) | 2012-10-24 | 2015-07-01 | 알스톰 테크놀러지 리미티드 | Sequential combustion with dilution gas mixer |
EP2725302A1 (en) | 2012-10-25 | 2014-04-30 | Alstom Technology Ltd | Reheat burner arrangement |
EP2796789B1 (en) | 2013-04-26 | 2017-03-01 | General Electric Technology GmbH | Can combustor for a can-annular combustor arrangement in a gas turbine |
EP2837888A1 (en) | 2013-08-15 | 2015-02-18 | Alstom Technology Ltd | Sequential combustion with dilution gas mixer |
JP2013228207A (en) * | 2013-08-15 | 2013-11-07 | Osaka Gas Co Ltd | Tubular flame burner |
EP2857658A1 (en) | 2013-10-01 | 2015-04-08 | Alstom Technology Ltd | Gas turbine with sequential combustion arrangement |
EP2863018B1 (en) | 2013-10-17 | 2018-03-21 | Ansaldo Energia Switzerland AG | Combustor of a gas turbine with a transition piece having a cooling structure |
EP2894405B1 (en) | 2014-01-10 | 2016-11-23 | General Electric Technology GmbH | Sequential combustion arrangement with dilution gas |
EP2921779B1 (en) | 2014-03-18 | 2017-12-06 | Ansaldo Energia Switzerland AG | Combustion chamber with cooling sleeve |
EP2960436B1 (en) | 2014-06-27 | 2017-08-09 | Ansaldo Energia Switzerland AG | Cooling structure for a transition piece of a gas turbine |
EP2993314B1 (en) | 2014-09-05 | 2017-11-08 | Ansaldo Energia Switzerland AG | Device and method for mounting or dismantling, replacement and maintenance of a can-combustor |
EP2993315B8 (en) | 2014-09-05 | 2017-07-19 | Ansaldo Energia Switzerland AG | Apparatus for an assembly tool for mounting or dismantling, replacement and maintenance of a component of an engine |
EP2993404B1 (en) | 2014-09-08 | 2019-03-13 | Ansaldo Energia Switzerland AG | Dilution gas or air mixer for a combustor of a gas turbine |
EP3015772B1 (en) | 2014-10-31 | 2020-01-08 | Ansaldo Energia Switzerland AG | Combustor arrangement for a gas turbine |
EP3015771B1 (en) | 2014-10-31 | 2020-01-01 | Ansaldo Energia Switzerland AG | Combustor arrangement for a gas turbine |
EP3023696B1 (en) | 2014-11-20 | 2019-08-28 | Ansaldo Energia Switzerland AG | Lobe lance for a gas turbine combustor |
EP3026347A1 (en) | 2014-11-25 | 2016-06-01 | Alstom Technology Ltd | Combustor with annular bluff body |
EP3037725B1 (en) | 2014-12-22 | 2018-10-31 | Ansaldo Energia Switzerland AG | Mixer for admixing a dilution air to the hot gas flow |
EP3037728B1 (en) | 2014-12-22 | 2020-04-29 | Ansaldo Energia Switzerland AG | Axially staged mixer with dilution air injection |
EP3037726B1 (en) | 2014-12-22 | 2018-09-26 | Ansaldo Energia Switzerland AG | Separate feedings of cooling and dilution air |
EP3067622B1 (en) | 2015-03-12 | 2018-12-26 | Ansaldo Energia Switzerland AG | Combustion chamber with double wall and method of cooling the combustion chamber |
EP3130848B1 (en) | 2015-08-12 | 2019-01-16 | Ansaldo Energia Switzerland AG | Sequential combustion arrangement with cooling gas for dilution |
EP3133343A1 (en) | 2015-08-18 | 2017-02-22 | General Electric Technology GmbH | Gas turbine with diluted liquid fuel |
EP3135880B1 (en) | 2015-08-25 | 2020-07-08 | Ansaldo Energia IP UK Limited | Gas turbine with a sequential combustion arrangement and fuel composition control |
EP3228939B1 (en) | 2016-04-08 | 2020-08-05 | Ansaldo Energia Switzerland AG | Method for combusting a fuel, and combustion appliance |
EP3306194B1 (en) | 2016-10-06 | 2019-04-24 | Ansaldo Energia IP UK Limited | Combustor wall element and method for manufacturing the same |
EP3354984B1 (en) | 2017-01-31 | 2020-09-09 | Ansaldo Energia Switzerland AG | Lobed injector for a gas turbine combustor |
KR102134354B1 (en) * | 2020-04-16 | 2020-07-15 | 국방과학연구소 | Device for preventing projection, device for flame protection, and guided weapons comprising thereof |
CN114110582B (en) * | 2022-01-25 | 2022-04-19 | 烟台市大昌燃气器具有限责任公司 | Combustion-supporting combustor |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1910735A (en) * | 1927-02-14 | 1933-05-23 | Buttnerwerke A G | Burner for coal dust firing |
US2800093A (en) * | 1951-06-13 | 1957-07-23 | Pollopas Patents Ltd | Apparatus for burning pulverized fuel |
FR2316540A2 (en) * | 1975-02-28 | 1977-01-28 | Heurtey Efflutherm | METHOD AND DEVICE FOR THE EVAPORATION AND THERMAL OXIDATION OF LIQUID EFFLUENTS AND SOLID WASTE IN PULVERULENT FORM |
US4120640A (en) * | 1977-02-18 | 1978-10-17 | Infern-O-Therm Corporation | Burner for liquid fuel |
DE3662462D1 (en) * | 1985-07-30 | 1989-04-20 | Bbc Brown Boveri & Cie | Dual combustor |
-
1987
- 1987-12-21 CH CH4980/87A patent/CH674561A5/de not_active IP Right Cessation
-
1988
- 1988-12-10 DE DE8888120667T patent/DE3862854D1/en not_active Expired - Lifetime
- 1988-12-10 EP EP88120667A patent/EP0321809B1/en not_active Expired - Lifetime
- 1988-12-10 AT AT88120667T patent/ATE63628T1/en not_active IP Right Cessation
- 1988-12-12 US US07/282,736 patent/US4932861A/en not_active Expired - Lifetime
- 1988-12-13 CA CA000585788A patent/CA1312816C/en not_active Expired - Lifetime
- 1988-12-20 JP JP63319709A patent/JP2608320B2/en not_active Expired - Lifetime
- 1988-12-21 KR KR1019880017141A patent/KR0129752B1/en not_active IP Right Cessation
Cited By (190)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0298386A2 (en) | 1987-07-06 | 1989-01-11 | University Of Waterloo | Polymer hydrogenation process |
CH679692A5 (en) * | 1989-04-24 | 1992-03-31 | Asea Brown Boveri | |
EP0394800A1 (en) * | 1989-04-24 | 1990-10-31 | Asea Brown Boveri Ag | Premix burner for generating a hot gas |
US5127821A (en) * | 1989-04-24 | 1992-07-07 | Asea Brown Boveri Ltd. | Premixing burner for producing hot gas |
EP0394911A1 (en) * | 1989-04-27 | 1990-10-31 | Asea Brown Boveri Ag | Combustion installation |
US5147200A (en) * | 1989-12-01 | 1992-09-15 | Asea Brown Boveri, Ltd. | Method of operating a firing installation |
EP0436113A1 (en) * | 1989-12-01 | 1991-07-10 | Asea Brown Boveri Ag | Method for operating a combustion plant |
CH680157A5 (en) * | 1989-12-01 | 1992-06-30 | Asea Brown Boveri | |
CH680946A5 (en) * | 1989-12-19 | 1992-12-15 | Asea Brown Boveri | |
US5085575A (en) * | 1989-12-19 | 1992-02-04 | Asea Brown Boveri | Method for premixed combustion of a liquid fuel |
EP0433789A1 (en) * | 1989-12-19 | 1991-06-26 | Asea Brown Boveri Ag | Method for a premix burning of a liquid fuel |
US5169302A (en) * | 1989-12-22 | 1992-12-08 | Asea Brown Boveri Ltd. | Burner |
CH680467A5 (en) * | 1989-12-22 | 1992-08-31 | Asea Brown Boveri | |
EP0433790A1 (en) * | 1989-12-22 | 1991-06-26 | Asea Brown Boveri Ag | Burner |
CH681480A5 (en) * | 1990-06-07 | 1993-03-31 | Asea Brown Boveri | |
US5165606A (en) * | 1990-06-07 | 1992-11-24 | Asea Brown Boveri, Ltd. | Method for operating a pressure atomization nozzle |
EP0461447A1 (en) * | 1990-06-07 | 1991-12-18 | Asea Brown Boveri Ag | Pressurised atomising nozzle |
US5284437A (en) * | 1990-11-02 | 1994-02-08 | Asea Brown Boveri Ag | Method of minimizing the NOx emissions from a combustion |
EP0483554A1 (en) * | 1990-11-02 | 1992-05-06 | Asea Brown Boveri Ag | Method for minimising the NOx emissions from a combustion |
CH682009A5 (en) * | 1990-11-02 | 1993-06-30 | Asea Brown Boveri | |
EP0491079A1 (en) * | 1990-12-19 | 1992-06-24 | Asea Brown Boveri Ag | Burner head for premix combustion of a liquid fuel in an atmospheric combustion installation |
US5244380A (en) * | 1991-03-12 | 1993-09-14 | Asea Brown Boveri Ltd. | Burner for premixing combustion of a liquid and/or gaseous fuel |
EP0503319A3 (en) * | 1991-03-12 | 1993-02-24 | Asea Brown Boveri Ag | Burner for a premixing combustion of a liquid and/or a gaseous fuel |
EP0503319A2 (en) * | 1991-03-12 | 1992-09-16 | Asea Brown Boveri Ag | Burner for a premixing combustion of a liquid and/or a gaseous fuel |
EP0518072A1 (en) * | 1991-06-14 | 1992-12-16 | Asea Brown Boveri Ag | Burner for an internal combustion engine, a combustion chamber of a gas turbine plant or a furnace |
US5249955A (en) * | 1991-07-03 | 1993-10-05 | Asea Brown Boveri Ltd. | Burner and ignitor arrangement |
EP0521325A1 (en) * | 1991-07-03 | 1993-01-07 | Asea Brown Boveri Ag | Combustion chamber |
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. |
US5340306A (en) * | 1991-12-23 | 1994-08-23 | Asea Brown Boveri Ltd. | Device for mixing two gaseous components and burner in which this device is employed |
EP0548396A1 (en) * | 1991-12-23 | 1993-06-30 | Asea Brown Boveri Ag | Device for mixing of two gaseous components and burner in which this device is applied |
EP0561011A1 (en) * | 1992-03-16 | 1993-09-22 | Asea Brown Boveri Ag | Intercooled compressor |
DE4223828A1 (en) * | 1992-05-27 | 1993-12-02 | Asea Brown Boveri | Method for operating a combustion chamber of a gas turbine |
US5361576A (en) * | 1992-05-27 | 1994-11-08 | Asea Brown Boveri Ltd. | Method for operating a combustion chamber of a gas turbine |
EP0576697A1 (en) * | 1992-06-29 | 1994-01-05 | Abb Research Ltd. | Combustor chamber for a gas turbine |
US5412938A (en) * | 1992-06-29 | 1995-05-09 | Abb Research Ltd. | Combustion chamber of a gas turbine having premixing and catalytic burners |
US5482457A (en) * | 1992-10-16 | 1996-01-09 | Asea Brown Boveri Ltd. | Gas-operated premixing burner |
EP0592717A1 (en) * | 1992-10-16 | 1994-04-20 | Asea Brown Boveri Ag | Gas-operated premix burner |
EP0593816A1 (en) * | 1992-10-23 | 1994-04-27 | Asea Brown Boveri Ag | Burner with electric ignition device |
US5413478A (en) * | 1992-10-23 | 1995-05-09 | Asea Brown Boveri Ltd. | Burner with an electric ignition device |
US5433596A (en) * | 1993-04-08 | 1995-07-18 | Abb Management Ag | Premixing burner |
EP0619457A1 (en) * | 1993-04-08 | 1994-10-12 | ABB Management AG | Premix burner |
CH687831A5 (en) * | 1993-04-08 | 1997-02-28 | Asea Brown Boveri | Premix burner. |
US5673551A (en) * | 1993-05-17 | 1997-10-07 | Asea Brown Boveri Ag | Premixing chamber for operating an internal combustion engine, a combustion chamber of a gas turbine group or a firing system |
EP0641971A2 (en) * | 1993-09-06 | 1995-03-08 | Abb Research Ltd. | Method for operating a premix burner |
US5755166A (en) * | 1993-12-21 | 1998-05-26 | Abb Carbon Ab | Method and device for after-burning of particulate fuel in a power plant |
US5685705A (en) * | 1994-03-11 | 1997-11-11 | Asea Brown Boveri Ag | Method and appliance for flame stabilization in premixing burners |
US5558515A (en) * | 1994-04-02 | 1996-09-24 | Abb Management Ag | Premixing burner |
EP0675322A2 (en) * | 1994-04-02 | 1995-10-04 | ABB Management AG | Premix burner |
US5573395A (en) * | 1994-04-02 | 1996-11-12 | Abb Management Ag | Premixing burner |
DE4412315B4 (en) * | 1994-04-11 | 2005-12-15 | Alstom | Method and device for operating the combustion chamber of a gas turbine |
US5609017A (en) * | 1994-05-19 | 1997-03-11 | Abb Management Ag | Method and apparatus for operating a combustion chamber for autoignition of a fuel |
US5593302A (en) * | 1994-05-19 | 1997-01-14 | Abb Management Ag | Combustion chamber having self-ignition |
US5617718A (en) * | 1994-05-26 | 1997-04-08 | Asea Brown Boveri Ag | Gas-turbine group with temperature controlled fuel auto-ignition |
US5664943A (en) * | 1994-07-13 | 1997-09-09 | Abb Research Ltd. | Method and device for operating a combined burner for liquid and gaseous fuels |
US5573392A (en) * | 1994-07-13 | 1996-11-12 | Abb Research Ltd. | Method and device for distributing fuel in a burner suitable for both liquid and gaseous fuels |
US5562441A (en) * | 1994-07-25 | 1996-10-08 | Abb Research Ltd. | Burner |
US5626017A (en) * | 1994-07-25 | 1997-05-06 | Abb Research Ltd. | Combustion chamber for gas turbine engine |
DE4429539C2 (en) * | 1994-08-19 | 2002-10-24 | Alstom | Process for speed control of a gas turbine when shedding loads |
US5680753A (en) * | 1994-08-19 | 1997-10-28 | Asea Brown Boveri Ag | Method of regulating the rotational speed of a gas turbine during load disconnection |
EP0697507A2 (en) | 1994-08-19 | 1996-02-21 | ABB Management AG | Gasturbine speed control method for sudden load loss |
US5588826A (en) * | 1994-10-01 | 1996-12-31 | Abb Management Ag | Burner |
US5569020A (en) * | 1994-11-05 | 1996-10-29 | Abb Research Ltd. | Method and device for operating a premixing burner |
US5586878A (en) * | 1994-11-12 | 1996-12-24 | Abb Research Ltd. | Premixing burner |
EP0713058A1 (en) | 1994-11-19 | 1996-05-22 | ABB Management AG | Multi-stage combustion chamber |
EP0714001A2 (en) | 1994-11-23 | 1996-05-29 | ABB Management AG | Combustion chamber with premix burners |
US5655903A (en) * | 1994-11-23 | 1997-08-12 | Asea Brown Boveri Ag | Combustion chamber with premixing burners |
EP0719983A1 (en) | 1994-12-27 | 1996-07-03 | ABB Management AG | Method and device for feeding gaseous fuel in a premix burner |
DE4446945B4 (en) * | 1994-12-28 | 2005-03-17 | Alstom | Gas powered premix burner |
US5699667A (en) * | 1994-12-28 | 1997-12-23 | Asea Brown Boveri Ag | Gas-operated premixing burner for gas turbine |
US5674066A (en) * | 1995-01-30 | 1997-10-07 | Asea Brown Boveri Ag | Burner |
US5687571A (en) * | 1995-02-20 | 1997-11-18 | Asea Brown Boveri Ag | Combustion chamber with two-stage combustion |
DE19507088B4 (en) * | 1995-03-01 | 2005-01-27 | Alstom | premix |
US5689948A (en) * | 1995-03-07 | 1997-11-25 | Asea Brown Boveri Ag | Method of operating a reheat power plant with steam injection |
US5829967A (en) * | 1995-03-24 | 1998-11-03 | Asea Brown Boveri Ag | Combustion chamber with two-stage combustion |
US5661967A (en) * | 1995-04-24 | 1997-09-02 | Asea Brown Boveri Ag | Method of operating a sequentially fired gas-turbine group |
US5738508A (en) * | 1995-04-25 | 1998-04-14 | Abb Research Ltd. | Burner |
US5738509A (en) * | 1995-05-08 | 1998-04-14 | Asea Brown Boveri Ag | Premix burner having axial or radial air inflow |
US5765366A (en) * | 1995-07-03 | 1998-06-16 | Asea Brown Boveri Ag | Fuel feed for gas turbines having an annular combustion chamber |
US5791891A (en) * | 1995-09-30 | 1998-08-11 | Abb Research Ltd. | Method and device for burning fuels |
US5839269A (en) * | 1995-10-02 | 1998-11-24 | Asea Brown Boveri Ag | Method of operating a combined gas and power steam plant |
US5737912A (en) * | 1995-10-10 | 1998-04-14 | Asea Brown Boveri Ag | Method for starting gas turbine in combined cycle power station |
DE19542644B4 (en) * | 1995-11-17 | 2008-12-11 | Alstom | premixed |
US5791892A (en) * | 1995-11-23 | 1998-08-11 | Abb Research Ltd. | Premix burner |
US5833451A (en) * | 1995-12-05 | 1998-11-10 | Asea Brown Boveri Ag | Premix burner |
EP0778445A2 (en) | 1995-12-05 | 1997-06-11 | Asea Brown Boveri Ag | Premix burner |
DE19545310B4 (en) * | 1995-12-05 | 2008-06-26 | Alstom | premix |
EP0780630A2 (en) | 1995-12-21 | 1997-06-25 | Abb Research Ltd. | Burner for a heat generator |
EP0780628A2 (en) | 1995-12-21 | 1997-06-25 | Abb Research Ltd. | Premix burner for a heat generator |
EP0780629A2 (en) | 1995-12-21 | 1997-06-25 | ABB Research Ltd. | Burner for a heat generator |
US5876196A (en) * | 1995-12-21 | 1999-03-02 | Abb Research Ltd. | Burner for a heat generator |
US5800160A (en) * | 1995-12-21 | 1998-09-01 | Abb Research Ltd. | Premix burner for a heat generator |
US5735687A (en) * | 1995-12-21 | 1998-04-07 | Abb Research Ltd. | Burner for a heat generator |
US5807097A (en) * | 1995-12-27 | 1998-09-15 | Abb Research Ltd. | Cone burner |
EP0783089A2 (en) | 1995-12-27 | 1997-07-09 | Abb Research Ltd. | Cone-shaped burner |
US5934555A (en) * | 1996-03-05 | 1999-08-10 | Abb Research Ltd. | Pressure atomizer nozzle |
US5885068A (en) * | 1996-04-09 | 1999-03-23 | Abb Research Ltd. | Combustion chamber |
US5884470A (en) * | 1996-04-22 | 1999-03-23 | Asea Brown Boveri Ag | Method of operating a combined-cycle plant |
US5983643A (en) * | 1996-04-22 | 1999-11-16 | Asea Brown Boveri Ag | Burner arrangement with interference burners for preventing pressure pulsations |
US5884471A (en) * | 1996-05-10 | 1999-03-23 | Asea Brown Boveri Ag | Device for operating an annular combustion chamber equipped with combined burners for liquid and gaseous fuels |
DE19618856B4 (en) * | 1996-05-10 | 2006-04-13 | Alstom | Device for operating an annular combustion chamber equipped with combined burners for liquid and gaseous fuels |
US5921766A (en) * | 1996-05-17 | 1999-07-13 | Abb Research Ltd. | Burner |
US5782627A (en) * | 1996-06-29 | 1998-07-21 | Abb Research Ltd. | Premix burner and method of operating the burner |
US6126439A (en) * | 1996-09-30 | 2000-10-03 | Abb Alstom Power (Switzerland) Ltd | Premix burner |
US6050078A (en) * | 1996-11-29 | 2000-04-18 | Abb Research Ltd. | Gas turbine combustion chamber with two stages and enhanced acoustic properties |
US6098406A (en) * | 1996-12-21 | 2000-08-08 | Asea Brown Boveri Ag | Premix Burner for operating a combustion chamber with a liquid and/or gaseous fuel |
US5984670A (en) * | 1996-12-21 | 1999-11-16 | Asea Brown Boveri Ag | Burner |
DE19654008B4 (en) * | 1996-12-21 | 2006-08-10 | Alstom | burner |
DE19654009B4 (en) * | 1996-12-21 | 2006-05-18 | Alstom | Premix burner for operating a combustion chamber with a liquid and / or gaseous fuel |
EP0851172A2 (en) | 1996-12-23 | 1998-07-01 | Abb Research Ltd. | Burner for operating a combustion chamber with a liquid and/or gaseous fuel |
US5921770A (en) * | 1996-12-23 | 1999-07-13 | Abb Research Ltd. | Burner for operating a combustion chamber with a liquid and/or gaseous fuel |
EP0851176A2 (en) | 1996-12-30 | 1998-07-01 | Abb Research Ltd. | Boiler for a heat generator |
US5961313A (en) * | 1997-03-18 | 1999-10-05 | Abb Research Ltd. | Method of operating a swirl stabilized burner and burner for carrying out the method |
US6192669B1 (en) | 1997-03-20 | 2001-02-27 | Asea Brown Boveri Ag | Combustion chamber of a gas turbine |
US6067789A (en) * | 1997-05-09 | 2000-05-30 | Abb Research Ltd. | Method and appliance for operating a gas turbine installation combustion chamber with liquid fuel |
US6230482B1 (en) | 1997-05-09 | 2001-05-15 | Abb Research Ltd. | Appliance for operating a gas turbine installation combustion chamber with liquid fuel |
EP0877156A2 (en) | 1997-05-09 | 1998-11-11 | Abb Research Ltd. | Method and device to vaporize liquid fuel for use in a gas turbine combustor |
DE19721937B4 (en) * | 1997-05-26 | 2008-12-11 | Alstom | Premix burner for operating a unit for generating a hot gas |
DE19726975A1 (en) * | 1997-06-26 | 1999-01-07 | Asea Brown Boveri | Jet engine |
US6045058A (en) * | 1997-07-17 | 2000-04-04 | Abb Research Ltd. | Pressure atomizer nozzle |
US6055813A (en) * | 1997-08-30 | 2000-05-02 | Asea Brown Boveri Ag | Plenum |
US6378787B1 (en) | 1997-09-15 | 2002-04-30 | Alstom | Combined pressure atomizing nozzle |
EP0902233A1 (en) | 1997-09-15 | 1999-03-17 | Abb Research Ltd. | Combined pressurised atomising nozzle |
US6132202A (en) * | 1997-10-27 | 2000-10-17 | Asea Brown Boveri Ag | Method and device for operating a premix burner |
US6059565A (en) * | 1997-10-31 | 2000-05-09 | Abb Alstom Power (Switzereland) Ltd | Burner for operating a heat generator |
EP0913630A1 (en) | 1997-10-31 | 1999-05-06 | Abb Research Ltd. | Burner for the operation of a heat generator |
US6027331A (en) * | 1997-11-13 | 2000-02-22 | Abb Research Ltd. | Burner for operating a heat generator |
US5954490A (en) * | 1997-11-25 | 1999-09-21 | Abb Research Ltd. | Burner for operating a heat generator |
EP0919768A1 (en) | 1997-11-25 | 1999-06-02 | Abb Research Ltd. | Burner for the operation of a heat generator |
US6045351A (en) * | 1997-12-22 | 2000-04-04 | Abb Alstom Power (Switzerland) Ltd | Method of operating a burner of a heat generator |
US5980240A (en) * | 1997-12-22 | 1999-11-09 | Asea Brown Boveri Ag | Burner |
US6189211B1 (en) | 1998-05-15 | 2001-02-20 | Asea Brown Boveri Ag | Method and arrangement for carrying out repair and/or maintenance work in the inner casing of a multishell turbomachine |
US6141954A (en) * | 1998-05-18 | 2000-11-07 | United Technologies Corporation | Premixing fuel injector with improved flame disgorgement capacity |
US6263676B1 (en) | 1998-08-19 | 2001-07-24 | Asea Brown Boveri Ag | Burner having a frame for operating an internal combustion machine |
US6390805B1 (en) | 1998-09-16 | 2002-05-21 | Asea Brown Boveri Ag | Method of preventing flow instabilities in a burner |
US6210152B1 (en) | 1998-09-16 | 2001-04-03 | Abb Research Ltd. | Burner for a heat generator and method for operating the same |
EP1001214A1 (en) | 1998-11-09 | 2000-05-17 | Asea Brown Boveri AG | Process to prevent the formation of flow instabilities in a burner |
US6360971B1 (en) | 1998-11-25 | 2002-03-26 | Alstom | Method and appliance for atomizing liquid fuel for a firing installation |
EP1004821A1 (en) | 1998-11-25 | 2000-05-31 | Asea Brown Boveri AG | Method and device for pulverising liquid fuel for a combustion plant |
DE19854382B4 (en) * | 1998-11-25 | 2009-01-02 | Alstom | Method and device for atomizing liquid fuel for a firing plant |
US6305927B1 (en) | 1998-12-15 | 2001-10-23 | Abb Alstom Power (Schweiz) Ag | Burner with acoustically damped fuel supply system |
EP1010939A1 (en) | 1998-12-15 | 2000-06-21 | ABB Alstom Power (Schweiz) AG | Combustion chamber with acoustic damped fuel supply system |
WO2000039503A1 (en) | 1998-12-23 | 2000-07-06 | Alstom (Schweiz) Ag | Burner for heat generator |
US6402059B1 (en) | 1999-02-15 | 2002-06-11 | Alstom (Switzerland) Ltd | Fuel lance for spraying liquid and/or gaseous fuels into a combustion chamber, and method of operating such a fuel lance |
DE19914666B4 (en) * | 1999-03-31 | 2009-08-20 | Alstom | Burner for a heat generator |
US6336806B1 (en) * | 1999-07-14 | 2002-01-08 | Alstom (Switzerland) Ltd. | Method for combustion of a liquid fuel in a combustion system, and a combustion system for carrying out the method |
US6331109B1 (en) | 1999-07-22 | 2001-12-18 | Alstom (Switzerland) Ltd. | Premix burner |
EP1070917B1 (en) * | 1999-07-23 | 2003-09-17 | ALSTOM (Switzerland) Ltd | Process for active suppression of fluidic instabilities in a combustion system and combustion system for carrying out the process |
US6343927B1 (en) | 1999-07-23 | 2002-02-05 | Alstom (Switzerland) Ltd | Method for active suppression of hydrodynamic instabilities in a combustion system and a combustion system for carrying out the method |
US6584775B1 (en) | 1999-09-20 | 2003-07-01 | Alstom | Control of primary measures for reducing the formation of thermal nitrogen oxides in gas turbines |
DE10049204A1 (en) * | 2000-10-05 | 2002-04-11 | Alstom Switzerland Ltd | Device and method for the electrostatic atomization of a liquid medium |
US6901760B2 (en) | 2000-10-11 | 2005-06-07 | Alstom Technology Ltd | Process for operation of a burner with controlled axial central air mass flow |
WO2002033324A1 (en) | 2000-10-16 | 2002-04-25 | Alstom (Switzerland) Ltd. | Burner with progressive fuel injection |
US6705857B2 (en) | 2000-11-09 | 2004-03-16 | Alstom Technology Ltd. | Method for injecting fuel into a burner |
US6558154B2 (en) | 2000-11-13 | 2003-05-06 | Alstom (Switzerland) Ltd | Burner system with staged fuel injection and method for its operation |
US6679060B2 (en) | 2000-12-16 | 2004-01-20 | Alstom Technology Ltd | Method for operating a premix burner |
US6817188B2 (en) | 2000-12-16 | 2004-11-16 | Alstom (Switzerland) Ltd | Method for operating a premix burner |
US6640545B2 (en) | 2000-12-22 | 2003-11-04 | Alstom Ltd. | Burner with high flame stability |
US6672863B2 (en) | 2001-06-01 | 2004-01-06 | Alstom Technology Ltd | Burner with exhaust gas recirculation |
EP1262714A1 (en) | 2001-06-01 | 2002-12-04 | ALSTOM (Switzerland) Ltd | Burner with exhausts recirculation |
US6834504B2 (en) | 2001-07-26 | 2004-12-28 | Alstom Technology Ltd | Premix burner with high flame stability having a net-like structure within the mixing section |
US7003957B2 (en) | 2001-10-19 | 2006-02-28 | Alstom Technology Ltd | Burner for synthesis gas |
EP1336800A1 (en) | 2002-02-13 | 2003-08-20 | ALSTOM (Switzerland) Ltd | Method for reducing the oscillations induced by the combustion in combustion systems and premix burner for carrying out the method |
US6918256B2 (en) | 2002-02-13 | 2005-07-19 | Alstom Technology Ltd | Method for the reduction of combustion-driven oscillations in combustion systems and premixing burner for carrying out the method |
DE10205839B4 (en) * | 2002-02-13 | 2011-08-11 | Alstom Technology Ltd. | Premix burner for reducing combustion-driven vibrations in combustion systems |
EP1389713A1 (en) | 2002-08-12 | 2004-02-18 | ALSTOM (Switzerland) Ltd | Premixed exit ring pilot burner |
US6969251B2 (en) | 2002-10-12 | 2005-11-29 | Alstom Technology Ltd | Burner |
US7069727B2 (en) | 2003-02-11 | 2006-07-04 | Alstom Technology Ltd. | Method for operating a gas turbo group |
US7424804B2 (en) | 2003-03-07 | 2008-09-16 | Alstom Technology Ltd | Premix burner |
US7445445B2 (en) | 2003-09-01 | 2008-11-04 | Alstom Technology Ltd. | Burner having a burner lance and staged fuel injection |
US7428817B2 (en) | 2004-02-12 | 2008-09-30 | Alstom Technology Ltd | Premix burner with a swirl generator delimiting a conical swirl space and having sensor monitoring |
DE102005011287B4 (en) | 2004-03-31 | 2018-07-19 | Ansaldo Energia Ip Uk Limited | Method and an apparatus for operating at least one burner for firing the combustion chamber of a heat engine or gas turbine |
US7584616B2 (en) | 2004-12-23 | 2009-09-08 | Alstom Technology Ltd | Method for the operation of a gas turbo group |
US7568335B2 (en) | 2005-09-09 | 2009-08-04 | Alstom Technology Ltd | Gas turbogroup |
DE102006059532B4 (en) | 2006-02-20 | 2020-07-09 | Ansaldo Energia Ip Uk Limited | Method for operating a gas turbine arrangement with sequential combustion |
EP2058590A1 (en) | 2007-11-09 | 2009-05-13 | 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 |
DE102008012794B3 (en) * | 2008-03-05 | 2009-08-20 | Auerhahn Bestecke Gmbh | firing |
EP2299178A1 (en) | 2009-09-17 | 2011-03-23 | Alstom Technology Ltd | A method and gas turbine combustion system for safely mixing H2-rich fuels with air |
US8549860B2 (en) | 2009-09-17 | 2013-10-08 | Alstom Technology Ltd | Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method |
WO2011032935A2 (en) | 2009-09-17 | 2011-03-24 | Alstom Technology Ltd. | Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method |
WO2011032839A1 (en) | 2009-09-17 | 2011-03-24 | Alstom Technology Ltd | A method and gas turbine combustion system for safely mixing h2-rich fuels with air |
DE112010003677B4 (en) | 2009-09-17 | 2023-10-26 | Ansaldo Energia Switzerland AG | METHOD FOR BURNING HYDROGEN-RICH, GASEOUS FUELS IN A BURNER AND BURNER FOR CARRYING OUT THE METHOD |
EP2796788A1 (en) | 2013-04-24 | 2014-10-29 | Alstom Technology Ltd | Swirl generator |
US9829200B2 (en) | 2013-08-16 | 2017-11-28 | Ansaldo Energia Switzerland AG | Burner arrangement and method for operating a burner arrangement |
EP2848865A1 (en) | 2013-09-12 | 2015-03-18 | Alstom Technology Ltd | Thermoacoustic stabilization method |
EP2933559A1 (en) | 2014-04-16 | 2015-10-21 | Alstom Technology Ltd | Fuel mixing arragement and combustor with such a fuel mixing arrangement |
EP3062019A1 (en) | 2015-02-27 | 2016-08-31 | General Electric Technology GmbH | Method and device for flame stabilization in a burner system of a stationary combustion engine |
US11313559B2 (en) | 2015-02-27 | 2022-04-26 | Ansaldo Energia Switzerland AG | Method and device for flame stabilization in a burner system of a stationary combustion engine |
CN107270285A (en) * | 2016-04-08 | 2017-10-20 | 安萨尔多能源瑞士股份公司 | Method and burner for burning fuel |
CN107270285B (en) * | 2016-04-08 | 2020-08-28 | 安萨尔多能源瑞士股份公司 | Method for burning fuel and combustion device |
Also Published As
Publication number | Publication date |
---|---|
ATE63628T1 (en) | 1991-06-15 |
US4932861A (en) | 1990-06-12 |
KR890010487A (en) | 1989-08-09 |
DE3862854D1 (en) | 1991-06-20 |
JP2608320B2 (en) | 1997-05-07 |
EP0321809A1 (en) | 1989-06-28 |
KR0129752B1 (en) | 1998-04-09 |
CH674561A5 (en) | 1990-06-15 |
JPH01203809A (en) | 1989-08-16 |
CA1312816C (en) | 1993-01-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0321809B1 (en) | Process for combustion of liquid fuel in a burner | |
EP0387532B1 (en) | Gas turbine combustion chamber | |
EP0704657B1 (en) | Burner | |
EP0777081B1 (en) | Premix burner | |
EP0436113B1 (en) | Method for operating a combustion plant | |
EP0918191B1 (en) | Burner for the operation of a heat generator | |
EP0401529B1 (en) | Gas turbine combustion chamber | |
EP0481111B1 (en) | Gas-turbine combustion chamber | |
DE19547913A1 (en) | Burners for a heat generator | |
CH680467A5 (en) | ||
EP0641971B1 (en) | Method for operating a premix burner and premix burner for execution of the method | |
DE19640198A1 (en) | Premix burner | |
EP0394800B1 (en) | Premix burner for generating a hot gas | |
DE19547912A1 (en) | Burners for a heat generator | |
EP0816759B1 (en) | Premix burner and method of operating the burner | |
EP0994300A1 (en) | Burner for operating a heat generator | |
EP0742411B1 (en) | Air supply for a premix combustor | |
EP0483554B1 (en) | Method for minimising the NOx emissions from a combustion | |
EP0694730B1 (en) | Burner | |
DE19537636B4 (en) | Power plant | |
DE4412315A1 (en) | Method of operating gas turbine combustion chamber | |
EP0807787B1 (en) | Burner | |
EP0740108A2 (en) | Burner | |
EP0780628A2 (en) | Premix burner for a heat generator | |
DE19505614A1 (en) | Operating method for pre-mixing burner |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT CH DE FR GB IT LI NL SE |
|
17P | Request for examination filed |
Effective date: 19891211 |
|
17Q | First examination report despatched |
Effective date: 19900319 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT CH DE FR GB IT LI NL SE |
|
REF | Corresponds to: |
Ref document number: 63628 Country of ref document: AT Date of ref document: 19910615 Kind code of ref document: T |
|
REF | Corresponds to: |
Ref document number: 3862854 Country of ref document: DE Date of ref document: 19910620 |
|
ET | Fr: translation filed | ||
ITF | It: translation for a ep patent filed |
Owner name: DE DOMINICIS & MAYER S.R.L. |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed | ||
EAL | Se: european patent in force in sweden |
Ref document number: 88120667.6 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PUE Owner name: BBC BROWN BOVERI AG TRANSFER- ABB ALSTOM POWER (SC |
|
NLS | Nl: assignments of ep-patents |
Owner name: ABB ALSTOM POWER (SCHWEIZ) AG |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: TP |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PFA Free format text: ABB ALSTOM POWER (SCHWEIZ) AG TRANSFER- ALSTOM (SWITZERLAND) LTD |
|
NLT1 | Nl: modifications of names registered in virtue of documents presented to the patent office pursuant to art. 16 a, paragraph 1 |
Owner name: ALSTOM POWER (SCHWEIZ) AG Owner name: ALSTOM (SWITZERLAND) LTD |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CA Ref country code: FR Ref legal event code: CD |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NL Payment date: 20071213 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20071217 Year of fee payment: 20 Ref country code: AT Payment date: 20071221 Year of fee payment: 20 Ref country code: IT Payment date: 20071222 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20071213 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20071218 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20071221 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20071217 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20081209 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20081210 |
|
EUG | Se: european patent has lapsed | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20081209 |