EP0029619B1 - Gas-turbine combustor with premixing-prevaporizing elements - Google Patents

Gas-turbine combustor with premixing-prevaporizing elements Download PDF

Info

Publication number
EP0029619B1
EP0029619B1 EP80200979A EP80200979A EP0029619B1 EP 0029619 B1 EP0029619 B1 EP 0029619B1 EP 80200979 A EP80200979 A EP 80200979A EP 80200979 A EP80200979 A EP 80200979A EP 0029619 B1 EP0029619 B1 EP 0029619B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
orifices
elements
flame retention
flame
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
Application number
EP80200979A
Other languages
German (de)
French (fr)
Other versions
EP0029619A1 (en
Inventor
Eduard Brühwiler
Hans Koch
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=4363297&utm_source=***_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP0029619(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0029619A1 publication Critical patent/EP0029619A1/en
Application granted granted Critical
Publication of EP0029619B1 publication Critical patent/EP0029619B1/en
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback

Definitions

  • the invention relates to the combustion chamber of a gas turbine according to the preamble of claim 1.
  • Gas turbines are increasingly subject to the stringent environmental regulations in many countries regarding exhaust gas composition. Above all, compliance with the regulations on the maximum permitted NO x emissions is extremely difficult when operating a gas turbine.
  • a combustion chamber of the type mentioned at the outset for the purpose of reducing the pollutants liberated during combustion is known from US-A-4 100 733. It is aimed there that the emission values of pollutants without the injection of aids such as water or steam into the combustion chamber under the allowable values fall from the emission regulations. This is achieved by adding a pre-mixing / pre-evaporation phase to the actual combustion process. For this purpose, the pre-mixing / pre-evaporation is carried out in several tubular elements, the fuel being mixed with air from the compressor with a large excess of air.
  • This known combustion chamber is designed in two stages and is operated in such a way that the first stage is operated at low load, i. H. that about half of the tubular elements are used in terms of fuel. The second stage is only operated at higher loads. The aim here is that the mixture in the first stage is always rich enough to ensure stable combustion. This can be achieved either by changing the resistance at the air inlets on the distribution chamber side or by using fuel injectors of different sizes.
  • the present invention is based on the object of improving a combustion chamber of the type mentioned in such a way that first of all a reliable ignition of all elements is ensured and that then a re-ignition of the Flame from the combustion chamber into the interior of the tubular elements is prevented.
  • pilot elements are used in the present invention, it is expedient to distribute them geometrically evenly among the tubular elements used. If these are still put into operation by initial ignition, then one does not apply to the elements which are put into operation later: the flame jumps from the pilot elements to the surrounding ones, favored by the fact that the flame holders of these pilot elements are provided either with swirl bodies or with oblique holes, so that divergent tongues of flame are generated, which additionally promote good caloric and air-jet mixing, which is reflected in a more uniform temperature and speed distribution after the combustion chamber.
  • both the oblique openings and the openings in the flame holder parallel to the axis of the flame holder have a length of at least 1.5 opening diameters. Through this opening, the air-fuel oil vapor mixture or the air-fuel gas mixture flows to the combustion chamber at an increased speed, as a result of which flame back ignition is avoided.
  • a further embodiment in order to avoid a flashback, is to design the openings in the flame holder as injectors, so that air is introduced into the boundary layer of the openings.
  • Another configuration of the openings in the flame holder is to design them as diffusers. With this solution, a higher speed is possible with the same pressure loss. The higher speed offers more security against the flame reigniting from the combustion chamber. To ensure the safe operation of the diffuser, it is necessary to add a cylindrical section with a minimum length of 1.5 diameter.
  • FIG. 1 shows schematically the concept of such a combustion chamber.
  • a larger number of tubular elements 2 are arranged in the upper area of the combustion chamber casing 1, which optimally fill the available space.
  • FIG. 2 An example of such an arrangement is shown in FIG. 2, in which thirty-seven tubular elements 2 are arranged. However, this number is not mandatory, because it depends on the size of the combustion chamber, which in turn is dependent on the desired combustion output.
  • a support bridge 27, on which the tubular elements 2 are connected by means of end nuts 5, is anchored to a support rib 23. In order to connect the tubular elements 2 to the support bridge 27, other types of connection can of course also be used.
  • the tubular elements 2 are guided laterally in the lower region by means of a guide plate 6.
  • the tubular elements 2 can also be guided individually, as can be seen in FIG. 16, in which case no guide plate is then used, but individual guide rings 25 take on this task.
  • the guide rings 25 are also carried here by support elements 22 which are firmly connected to the support bridge 27.
  • the tubular elements 2 can also be anchored differently than with the support bridge 27 shown, but in such cases it will always be necessary to ensure that the chosen anchoring is placed as far away from the combustion chamber 7 as possible so that the thermal expansions cannot have a disruptive effect.
  • the greater part of the compressed air which is provided in the compressor (not shown), flows through the openings 9 into a distribution chamber 19 provided in the combustion chamber casing I, which distributes downwards through the support bridge 27 and upwards through the cover 35 flanged on the flange rib 38 is narrowed down. From this distribution chamber 19, the compressed air then flows through the air funnels 14 into the individual tubular elements 2.
  • the fuel supply is provided for each tubular element 2 by means of a fuel line 4, a fuel nozzle 15, which projects into the tubular element 2 and has one or more fuel openings (not shown), atomizing the fuel against the air inflow direction. The fuel does not necessarily have to be injected against the air flow.
  • fuel gas natural gas
  • the gas is blown in in the direction of air inflow. It is also possible to input and burn oil and gas at the same time.
  • fuel oil to achieve finer atomization, the smallest possible amount of compressed air can be added through the nozzle 15, which has an overpressure compared to the process pressure.
  • the fuel therefore mixes with the incoming compressed air in such a way that a pre-mixing nor evaporation process takes place in the tubular element 2.
  • This process can be intensified due to the turbulence which arises by inserting a flange 34 at the air inlet of the tubular element 2, as can be seen in FIG. 16.
  • the fuel injection or fuel injection through the fuel nozzle 15 must be carried out at an optimal distance from the mouth 34, but still in the region of the turbulence that has arisen.
  • the fuel evaporates and mixes with the air.
  • the degree of evaporation is stronger, the greater the temperature and the residence time and the smaller the drop size of the atomized fuel.
  • the critical time until the mixture self-ignites decreases, so that the length of the tubular elements 2 is coordinated in such a way that the best possible evaporation results for the shortest possible time.
  • gas there is no evaporation; the gas only needs to be distributed evenly with the air.
  • a remaining amount of compressed air does not flow into the distribution chamber 19, but into the combustion chamber casing I through the openings 26, is distributed between the tubular elements 2 and flows through the openings 18 recessed in the flame holder edge 13 (FIG. 2) to the combustion chamber, as a result of which the outer part of the flame holder 3 is cooled in such a way that the risk of burning, which is latent especially when producing divergent flame tongues, is counteracted.
  • the combustion of the mixture is aimed at with the largest possible excess of air, which is given by the fact that the flame is still burning and further by the fact that not too much CO is produced.
  • a good optimization can be present, for example, if the air content of the mixture is kept at 1.8 times the stoichiometric value.
  • the lower terminating rib 24 prevents free convection of the hot air from the combustion chamber 7, the terminating rib 24 also being cooled with the same residual air flowing in through the openings 26, which then flows out through the openings 18 of the adjacent flame shader edges 13 to the combustion chamber 7.
  • the flame holder 3 which forms the end of the downstream part of the tubular element 2, has the task of preventing the flame from reigniting from the combustion chamber 7 into the interior of the tubular element 2.
  • the inner wall of the combustion chamber casing 1 is provided with a cooling system (not shown) in the area of the combustion chamber 7, that is to say from the flame heater 3.
  • the flame holder 3 shown has a number of cylindrical holes 21 which run parallel to the axis of the tubular element 2. If additional divergent flame tongues are to be produced, as can be seen in FIGS. 4 and 5, the holes 30 in the flame holder 3, with the exception of the central hole, can be made obliquely in radial planes of the flame holder 3, the angle 38 from the center to the periphery of the flame holder 3 steadily increases or remains the same.
  • the length of both the parallel holes 21 and the oblique holes 30, 31 must be at least 1.5 hole diameter.
  • the resulting increased mixture speed in the holes 21, 30, 31 and the length of the holes counteract flame reignition from the combustion chamber 7.
  • the number of holes 21, 30, 31 must be adapted to the given conditions. In the example shown in FIG. 7, there are for example twenty-one holes 31.
  • the flame holder 3 consists of an upper plate 3a and a lower plate 3b, between which a channel 10 connected to the openings 8 runs.
  • the openings 8 provided in the flame holder 3 are each lined with two slightly conical bushes 11, 12, these overlapping in the region of the channel 10 telescopically and with play 16. Burning back of the flame from the combustion chamber 7, in particular in the boundary layer along the wall of the sleeve 12, is counteracted by introducing compressed air through the channel 10, which flows through the play 16 along the endangered wall of the sleeve 12 with the mixture . Flow separations, which would favor reignition, are prevented by the conical shape of the openings 8.
  • the flame holder 3 shown in FIG. 11 has sixteen openings 8, which are fed symmetrically from two channels 10 with compressed air.
  • the supply of the openings 8 made in the flame holder 3 with compressed air can be fulfilled by other channel configurations.
  • the openings 8 in the flame holder 3 are designed as diffusers 39.
  • an initial cylindrical bore 32 is followed by a section formed as a diffuser 40, which is followed by a cylindrical bore 33 of larger diameter than the inlet bore 32, which has a length of at least 1.5 bore diameter.
  • a higher speed at the narrowest point is possible with the same pressure loss, which is reflected in greater safety against flame reignition from the combustion chamber 7.
  • the beginning of the flame in the combustion chamber 7 is brought into a corresponding distance from the diffuser 40 through the cylindrical bore 33.
  • the flow in the subsequent cylindrical part 33 will again rest against the wall.
  • the flame holder 3 can, as shown in FIG. 9 10 and 10, can be provided with a swirl body 28, the mixture being directed to the combustion chamber 7 in a swirling manner through its openings 41, for example fourteen in number.
  • the swirl body 28 promotes good air-jet mixing of the fuel / air mixture and good heat distribution, which results in a homogeneous temperature and speed distribution after the combustion chamber 7, with the effect that the turbine, not shown, is acted upon uniformly.
  • tubular elements 2 and the individual flame holder 3 itself in combination according to Figures 3, 4/5, 6/7/8, 9/10, 11/15 or 14 can be formed.
  • the combustion chamber casing 1 is optimally filled with a larger number of tubular elements 2. As shown in FIG. 2, among the thirty-seven tubular elements 2 used, thirteen pilot elements 17 are geometrically evenly distributed. When the combustion chamber is started, pilot elements 17 are initially put into operation by an initial ignition unit (not shown). When the load increases, the flame jumps from the pilot elements 17 to the surrounding ones, which have just been put into operation.
  • the openings 8 in the flame holder 3 of the pilot elements 17 can optionally be formed after the holes 30 and / or after the holes 31.
  • the use of swirl bodies 28 can also be provided for the pilot elements 17, which, like the holes 30, 31, also produce divergent flame tongues and thus favor the ignition of the surrounding tubular elements 2.
  • the flame holder 3 is hexagonal 20 in the circumferential direction. From these figures it can also be seen that the openings 18 made in the flame holder base 13 are evenly distributed between the hexagonal shape 20 and the tubular element. A polygon game 29 absorbs the thermal expansion in this area.
  • an orifice 34 is used, which in this area, that is to say directly around the fuel nozzle 15, generates turbulence which is suitable for this purpose; to intensify the premixing, atomization and pre-evaporation process in addition to the measures described above, that is to say in particular by the fine injection of the fuel against the direction of air inflow.
  • turbulence amplifiers can also be used instead of the on-board mouth 34.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)

Description

Die Erfindung betrifft die Brennkammer einer Gasturbine gemäss Oberbegriff des Anspruchs 1.The invention relates to the combustion chamber of a gas turbine according to the preamble of claim 1.

Gasturbinen unterliegen zunehmend den strengen Umweltschutzvorschriften vieler Staaten bezüglich Abgaszusammensetzung. Aus dem Betrieb einer Gasturbine bereitet vor allem die Einhaltung der Vorschriften über die maximal erlaubten NOx-Emissionen grosse Schwierigkeiten.Gas turbines are increasingly subject to the stringent environmental regulations in many countries regarding exhaust gas composition. Above all, compliance with the regulations on the maximum permitted NO x emissions is extremely difficult when operating a gas turbine.

Eine Brennkammer der eingangs genannten Art zum Zwecke der Verringerung der bei der Verbrennung freiwerdenden Schadstoffe ist bekannt aus der US-A-4 100 733. Dort wird angestrebt, dass die Emissionswerte von Schadstoffen ohne Einspritzung von Hilfsmitteln wie Wasser oder Dampf in den Verbrennungsraum unter die von den Emissionsvorschriften erlaubten Werte fallen. Dies wird erreicht, indem dem eigentlichen Verbrennungsprozess eine Vormisch/Vorverdampfungsphase vorgeschaltet wird. Zu diesem Zweck wird das Vormischen/Vorverdampfen in mehreren rohrförmigen Elementen durchgeführt, wobei der Brennstoff mit Luft aus dem Verdichter bei grosser Luftüberschusszahl vermengt wird. Diese bekannte Brennkammer ist zweistufig ausgebildet und wird derart gefahren, dass bei niedriger Last zunächst die erste Stufe betrieben wird, d. h. dass etwa die Hälfte der rohrförmigen Elemente brennstoffmässig im Einsatz ist. Erst bei höherer Last wird die zweite Stufe betrieben. Hierbei wird angestrebt, dass das Gemisch in der ersten Stufe immer fett genug ist, um eine stabile Verbrennung zu gewährleisten. Dies kann entweder durch veränderbaren Widerstand an den Verteilkammer-seitigen Lufteinlässen erreicht werden oder durch unterschiedlich grosse Brennstoffeinspritzdüsen.A combustion chamber of the type mentioned at the outset for the purpose of reducing the pollutants liberated during combustion is known from US-A-4 100 733. It is aimed there that the emission values of pollutants without the injection of aids such as water or steam into the combustion chamber under the allowable values fall from the emission regulations. This is achieved by adding a pre-mixing / pre-evaporation phase to the actual combustion process. For this purpose, the pre-mixing / pre-evaporation is carried out in several tubular elements, the fuel being mixed with air from the compressor with a large excess of air. This known combustion chamber is designed in two stages and is operated in such a way that the first stage is operated at low load, i. H. that about half of the tubular elements are used in terms of fuel. The second stage is only operated at higher loads. The aim here is that the mixture in the first stage is always rich enough to ensure stable combustion. This can be achieved either by changing the resistance at the air inlets on the distribution chamber side or by using fuel injectors of different sizes.

Ausgehend von der Erkenntnis, dass die Verbrennung mit grösstmöglicher Luftüberschusszahl - einmal dadurch gegeben, dass die Flamme überhaupt noch brennt und im weiteren dadurch, dass nicht zuviel CO entsteht - nicht nur die Schadstoffmenge von NOx reduziert, sondern darüber hinaus auch eine konsistente Tiefhaltung anderer Schadstoffe wie z. B. CO und unverbrannte Kohlenwasserstoffe bewirkt, liegt der vorliegenden Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, die Aufgabe zugrunde, eine Brennkammer der eingangs genannten Art derart zu verbessern, dass zunächst ein sicheres Zünden aller Elemente gewährleistet ist und dass dann ein Rückzünden der Flamme vom Brennraum ins Innere der rohrförmigen Elemente unterbunden wird.Based on the knowledge that combustion with the largest possible excess of air - given that the flame is still burning at all and furthermore that not too much CO is produced - not only reduces the amount of NO x pollutants, but also a consistent maintenance of others Pollutants such as B. causes CO and unburned hydrocarbons, the present invention, as characterized in the claims, is based on the object of improving a combustion chamber of the type mentioned in such a way that first of all a reliable ignition of all elements is ensured and that then a re-ignition of the Flame from the combustion chamber into the interior of the tubular elements is prevented.

Von besonderem Vorteil ist hierbei, dass ohne Eingriff in das Luftverteilsystem oder das Brennstoffeinspritzsystem bei der Lastregelung jeweils nur soviele Elemente mit Brennstoff betrieben werden, dass sich für die jeweilige Betriebsphase (Start, Teillast usw.) immer die optimale Luftüberschusszahl ergibt.It is particularly advantageous here that without intervention in the air distribution system or the fuel injection system in the load control, only so many elements are operated with fuel that the optimum excess air number always results for the respective operating phase (start, partial load, etc.).

Zwar ist es aus der GB-A-2 012413 ebenfalls bereits bekannt, zwecks Vormischen des eingespritzten Brennstoffs mit der Brennluft eine Mehrzahl von rohrförmigen Elementen vorzusehen, wobei diese Elemente brennkammerseitig mit Unstetigkeiten in Form von Verengungen versehen sind. Jedoch dienen diese Verengungen ausschliesslich der Brennstoffzufuhr zwischen den bündelartig zusammengefassten Rohren. Eine flammenabhaltende Funktion können sie nicht erfüllen.It is also already known from GB-A-2 012413 to provide a plurality of tubular elements for premixing the injected fuel with the combustion air, these elements being provided on the combustion chamber side with discontinuities in the form of constrictions. However, these constrictions only serve to supply fuel between the bundled tubes. They cannot fulfill a flame-retardant function.

Sofern bei der vorliegenden Erfindung mehrere Pilot-elemente zum Einsatz gelangen, ist es zweckmässig, diese geometrisch gleichmässig unter den eingesetzten rohrförmigen Elementen zu verteilen. Wenn jene noch durch Initialzündung in Betrieb genommen werden, so entfällt eine solche für die später in Betrieb genommenen Elemente : Von den Pilotelementen springt die Flamme zu den umliegenden über, dadurch begünstigt, dass die Flammenhalter dieser Pilotelemente entweder mit Drallkörpern oder mit Schräglöchern versehen werden, so dass divergierende Flammenzungen erzeugt werden, welche zusätzlich eine gute kalorische und luftstrahlige Durchmischung begünstigen, was sich in einer gleichmässigeren Temperatur und Geschwindigkeitsverteilung nach dem Brennraum niederschlägt.If several pilot elements are used in the present invention, it is expedient to distribute them geometrically evenly among the tubular elements used. If these are still put into operation by initial ignition, then one does not apply to the elements which are put into operation later: the flame jumps from the pilot elements to the surrounding ones, favored by the fact that the flame holders of these pilot elements are provided either with swirl bodies or with oblique holes, so that divergent tongues of flame are generated, which additionally promote good caloric and air-jet mixing, which is reflected in a more uniform temperature and speed distribution after the combustion chamber.

Von Vorteil ist es, wenn sowohl die schrägen als auch die zur Achse des Flammenhalters parallelen Oeffnungen im Flammenhalter eine Länge von mindestens 1,5 Oeffnungsdurchmesser besitzen. Durch diese Oeffnung strömt das Luft-Brennöldampfgemisch bzw. das Luft-Brenngasgemisch mit erhöhter Geschwindigkeit zum Brennraum, wodurch eine Flammenrückzündung vermieden wird.It is advantageous if both the oblique openings and the openings in the flame holder parallel to the axis of the flame holder have a length of at least 1.5 opening diameters. Through this opening, the air-fuel oil vapor mixture or the air-fuel gas mixture flows to the combustion chamber at an increased speed, as a result of which flame back ignition is avoided.

Eine weitere Ausgestaltung, um ein Flammenrückschlagen zu vermeiden, besteht darin, die Oeffnungen im Flammenhalter als Injektoren auszubilden, so dass Luft in die Grenzschicht der Oeffnungen eingeführt wird.A further embodiment, in order to avoid a flashback, is to design the openings in the flame holder as injectors, so that air is introduced into the boundary layer of the openings.

Eine weitere Ausgestaltung der Oeffnungen im Flammenhalter besteht darin, sie als Diffusoren auszubilden. Mit dieser Lösung ist bei gleichem Druckverlust eine höhere Geschwindigkeit möglich. Die höhere Geschwindigkeit bietet mehr Sicherheit gegen die Rückzündung der Flamme aus dem Brennraum. Zur sicheren Funktionsweise des Diffusors ist es notwendig eine zylindrische Partie mit einer Mindestlänge von 1,5 Durchmesser nachzuschalten.Another configuration of the openings in the flame holder is to design them as diffusers. With this solution, a higher speed is possible with the same pressure loss. The higher speed offers more security against the flame reigniting from the combustion chamber. To ensure the safe operation of the diffuser, it is necessary to add a cylindrical section with a minimum length of 1.5 diameter.

Von Vorteil ist es auch, wenn die Einspritzung des Brennstoffes gegen die Lufteinströmungsrichtung gerichtet ist. Dadurch wird der VormischNorverdampfungsprozess soweit begünstigt, dass die Länge des rohrförmigen Elementes gegenüber einer anderen Brennstoffzufuhrsart erheblich kürzer gehalten werden kann. Hierdurch wird die Verweilzeit des Gemisches im rohrförmigen Element reduziert und die Selbstzündungsgefahr unterbunden.It is also advantageous if the injection of the fuel is directed against the air inflow direction. This favors the pre-mixing nor evaporation process to such an extent that the length of the tubular element can be kept considerably shorter compared to another type of fuel supply. This reduces the residence time of the mixture in the tubular element and the self ignition danger prevented.

Durch den Einsatz einer Bordamündung am Lufteingang des rohrförmigen Elementes wird in diesem Bereich eine Turbulenz erzeugt, welche den Vormischungs-, Zerstäubungs- und Vorverdampfungsprozess zusätzlich intensiviert.By using an on-board mouth at the air inlet of the tubular element, turbulence is generated in this area, which additionally intensifies the pre-mixing, atomization and pre-evaporation process.

Es ist zweckmässig, den Umfang des Flammenhalterrandes als Polygon auszubilden, so dass sich die rohrförmigen Elemente platzsparend ineinanderfügen.It is expedient to design the circumference of the flame holder edge as a polygon, so that the tubular elements fit into one another in a space-saving manner.

Es empfiehlt sich, im Flammenhalterrand, um den Aussenmantel des rohrförmigen Elementes herum, mehrere Oeffnungen auszunehmen, durch welche eine Teilmenge der Verdichterluft durchströmt und so den Flammenhalterrand kühlt.It is advisable to cut out several openings in the flame holder edge around the outer jacket of the tubular element, through which a portion of the compressor air flows and thus cools the flame holder edge.

Im folgenden ist anhand der Figuren ein Ausführungsbeispiel der erfindungsgemässen Brennkammer schematisch dargestellt und näher erläutert. Alle für das Verständnis der Erfindung unwesentlichen Elemente sind nicht dargestellt. Gleiche Elemente sind in den verschiedenen Figuren mit gleichen Bezugsziffern versehen.An exemplary embodiment of the combustion chamber according to the invention is shown schematically and explained in more detail below with reference to the figures. All elements that are not essential for understanding the invention are not shown. The same elements are provided with the same reference numbers in the different figures.

Es zeigt :

  • Figur 1 Eine Schnittdarstellung einer Brennkammer,
  • Figur 2 Eine Anordnung der rohrförmigen Elemente in der Brennkammer,
  • Figur 3 Eine Schnittdarstellung eines Flammenhalters mit parallelen Löchern,
  • Figuren 4 und 5 Eine Darstellung eines weiteren Flammenhalters mit schrägen Löchern,
  • Figuren 6, 7 und 8 Eine Darstellung eines weiteren Flammenhalters mit schrägen Löchern,
  • Figuren 9 und 10 Eine Darstellung eines weiteren Flammenhalters mit Drallkörper versehen,
  • Figur 11 Eine Schnittdarstellung eines weiteren Flammenhalters mit Oeffnungen als Injektoren ausgebildet,
  • Figuren 12 und 13 Eine Darstellung eines Pilotelementes mit Diffusionsflamme,
  • Figur 14 Eine Schnittdarstellung eines weiteren Flammenhalters mit Oeffnungen als Diffusoren ausgebildet,
  • Figur 15 Eine Ansicht des Flammenhalters von Fig. 11 einschliesslich Ausgestaltung des Luftzuführungskanals,
  • Figur 16 Eine Darstellung der mittels Ringe geführten rohrförmigen Elemente mit Bordamündung.
It shows :
  • FIG. 1 shows a sectional illustration of a combustion chamber,
  • FIG. 2 shows an arrangement of the tubular elements in the combustion chamber,
  • FIG. 3 shows a sectional illustration of a flame holder with parallel holes,
  • FIGS. 4 and 5 an illustration of a further flame holder with oblique holes,
  • FIGS. 6, 7 and 8 an illustration of a further flame holder with oblique holes,
  • FIGS. 9 and 10 show a representation of a further flame holder with swirl body,
  • FIG. 11 shows a sectional illustration of a further flame holder with openings designed as injectors,
  • FIGS. 12 and 13 an illustration of a pilot element with a diffusion flame,
  • FIG. 14 shows a sectional illustration of a further flame holder with openings designed as diffusers,
  • FIG. 15 shows a view of the flame holder from FIG. 11, including the configuration of the air supply duct,
  • Figure 16 A representation of the tubular elements guided by rings with mouth.

Fig. 1 zeigt schematisch die Konzeption einer solchen Brennkammer. Im oberen Bereich der Brennkammerhülle 1 sind eine grössere Anzahl rohrförmiger Elemente 2 angeordnet, welche den zur Verfügung stehenden Raum optimal ausfüllen. Ein Beispiel einer solchen Anordnung geht aus Fig. 2 hervor, in der siebenunddreissig rohrförmige Elemente 2 angeordnet sind. Diese Anzahl ist indessen nicht zwingend, denn sie hängt von der Grösse der Brennkammer ab, welche wiederum in Abhängigkeit zur gewünschten Brennleistung steht. Eine Tragbrücke 27, an der die rohrförmigen Elemente 2 mittels Abschluss-' muttern 5 verbunden sind, ist an einer Tragrippe 23 verankert. Um die rohrförmigen Elemente 2 mit der Tragbrücke 27 zu verbinden, können selbstverständlich auch andere Verbindungsarten herangezogen werden. Die rohrförmigen Elemente 2 sind im unteren Bereich mittels einer Führungsplatte 6 seitlich geführt. Mehrere Tragelemente 22, welche ihrerseits mit der Tragbrücke 27 fest verbunden sind, tragen die Führungsplatte 6. Selbstverständlich können die rohrförmigen Elemente 2 auch einzeln geführt werden, wie dies aus Fig. 16 hervorgeht, wobei dann nicht mehr eine Führungsplatte eingesetzt wird, sondern einzelne Führungsringe 25 diese Aufgabe übernehmen. Die Führungsringe 25 werden auch hier von Tragelementen 22 getragen, die mit der Tragbrücke 27 fest verbunden sind. Selbstverständlich können die rohrförmigen Elemente 2 auch anders als mit der dargestellten Tragbrücke 27 verankert werden, immer wird man aber in solchen Fällen darauf achten müssen, dass die gewählte Verankerung möglichst weit weg vom Brennraum 7 plaziert ist, damit die Wärmedehnungen keine störende Wirkung entfalten können.Fig. 1 shows schematically the concept of such a combustion chamber. A larger number of tubular elements 2 are arranged in the upper area of the combustion chamber casing 1, which optimally fill the available space. An example of such an arrangement is shown in FIG. 2, in which thirty-seven tubular elements 2 are arranged. However, this number is not mandatory, because it depends on the size of the combustion chamber, which in turn is dependent on the desired combustion output. A support bridge 27, on which the tubular elements 2 are connected by means of end nuts 5, is anchored to a support rib 23. In order to connect the tubular elements 2 to the support bridge 27, other types of connection can of course also be used. The tubular elements 2 are guided laterally in the lower region by means of a guide plate 6. A plurality of support elements 22, which in turn are firmly connected to the support bridge 27, carry the guide plate 6. Of course, the tubular elements 2 can also be guided individually, as can be seen in FIG. 16, in which case no guide plate is then used, but individual guide rings 25 take on this task. The guide rings 25 are also carried here by support elements 22 which are firmly connected to the support bridge 27. Of course, the tubular elements 2 can also be anchored differently than with the support bridge 27 shown, but in such cases it will always be necessary to ensure that the chosen anchoring is placed as far away from the combustion chamber 7 as possible so that the thermal expansions cannot have a disruptive effect.

Der grössere Teil der verdichteten Luft, die im nicht dargestellten Verdichter bereitgestellt wird, strömt durch die Oeffnungen 9 in eine in der Brennkammerhülle I vorgesehene Verteilkammer 19 ein, welche nach unten durch die Tragbrücke 27 und nach oben durch den an der Flanschrippe 38 geflanschten Deckel 35 eingegrenzt ist. Von dieser Verteilkammer 19 aus strömt dann die verdichtete Luft durch die Lufttrichter 14 in die einzelnen rohrförmigen Elemente 2 ein. Die Brennstoffzuführung wird je rohrförmiges Element 2 durch eine Brennstoffleitung 4 beigestellt, wobei eine Brennstoffdüse 15, welche ins rohrförmige Element 2 hineinragt und eine oder mehrere nicht dargestellte Brennstofföffnungen aufweist, die Zerstäubung des Brennstoffes gegen die Lufteinströmungsrichtung besorgt. Der Brennstoff muss aber nicht notwendigerweise gegen den Luftstrom eingespritzt werden. Im Falle eines Einsatzes von Brenngas (Erdgas) beispielsweise wird das Gas in Lufteinströmungsrichtung eingeblasen. Es ist auch möglich, Oel und Gas gleichzeitig einzugeben und zu verbrennen. Auch kann bei Einsatz von Brennöl, zur Erzielung einer feineren Zerstäubung, durch die Düse 15 eine kleinstmögliche Menge Druckluft beigegeben werden, welche gegenüber dem Prozessdruck einen Ueberdruck aufweist. Der Brennstoff vermischt sich demnach mit der einströmenden verdichteten Luft, dergestalt, dass im rohrförmigen Element 2 ein VormischNorverdampfungsprozess abläuft. Dieser Prozess kann durch die Einsetzung einer Bordamündung 34 am Lufteingang des rohrförmigen Elementes 2, wie dies aus Fig. 16 hervorgeht, auf Grund der entstehenden Turbulenz intensiviert werden. In einem solchen Falle muss die Brennstoffeinspritzung bzw. Brennstoffeinblasung durch die Brennstoffdüse 15 in optimalem Abstand von der Bordamündung 34, aber noch im Bereich der entstandenen Turbulenz vorgenommen werden.The greater part of the compressed air, which is provided in the compressor (not shown), flows through the openings 9 into a distribution chamber 19 provided in the combustion chamber casing I, which distributes downwards through the support bridge 27 and upwards through the cover 35 flanged on the flange rib 38 is narrowed down. From this distribution chamber 19, the compressed air then flows through the air funnels 14 into the individual tubular elements 2. The fuel supply is provided for each tubular element 2 by means of a fuel line 4, a fuel nozzle 15, which projects into the tubular element 2 and has one or more fuel openings (not shown), atomizing the fuel against the air inflow direction. The fuel does not necessarily have to be injected against the air flow. If fuel gas (natural gas) is used, for example, the gas is blown in in the direction of air inflow. It is also possible to input and burn oil and gas at the same time. When using fuel oil to achieve finer atomization, the smallest possible amount of compressed air can be added through the nozzle 15, which has an overpressure compared to the process pressure. The fuel therefore mixes with the incoming compressed air in such a way that a pre-mixing nor evaporation process takes place in the tubular element 2. This process can be intensified due to the turbulence which arises by inserting a flange 34 at the air inlet of the tubular element 2, as can be seen in FIG. 16. In such a case, the fuel injection or fuel injection through the fuel nozzle 15 must be carried out at an optimal distance from the mouth 34, but still in the region of the turbulence that has arisen.

In der Zeit, in der das Gemisch durch das rohrförmige Element 2 bis zum Ausgang durch die im Flammenhalter 3 ausgenommenen Oeffnungen 8 strömt, verdampft der Brennstoff und vermischt sich mit der Luft. Der Grad der Verdampfung ist umso stärker, je grösser die Temperatur und die Verweilzeit und je kleiner die Tropfengrösse des zerstäubten Brennstoffes sind. Mit der Zunahme von Druck und Temperatur verringert sich jedoch die kritische Zeitdauer bis zur Selbstzündung des Gemisches, so dass die Länge der rohrförmigen Elemente 2 derart abgestimmt ist, dass eine möglichst gute Verdampfung während einer möglichst kurzen Zeit resultiert. Im Falle von Gas entfällt die Verdampfung ; das Gas muss mit der Luft nur gleichmässig verteilt werden.During the time in which the mixture flows through the tubular element 2 to the outlet through the openings 8 recessed in the flame holder 3, the fuel evaporates and mixes with the air. The degree of evaporation is stronger, the greater the temperature and the residence time and the smaller the drop size of the atomized fuel. With the increase in pressure and temperature, however, the critical time until the mixture self-ignites decreases, so that the length of the tubular elements 2 is coordinated in such a way that the best possible evaporation results for the shortest possible time. In the case of gas, there is no evaporation; the gas only needs to be distributed evenly with the air.

Eine restliche Menge verdichteter Luft strömt nicht in die Verteilkammer 19, sondern durch die Oeffnungen 26 in die Brennkammerhülle I ein, verteilt sich zwischen den rohrförmigen Elementen 2 und strömt durch die im Flammenhalterrand 13 (Fig. 2) ausgenommenen Oeffnungen 18 dem Brennraum zu, wodurch der äussere Teil des Flammenhalters 3 gekühlt wird, dermassen, dass der Abbrandgefahr, die insbesondere bei Erzeugung von divergierenden Flammenzungen latent vorhanden ist, entgegengewirkt wird.A remaining amount of compressed air does not flow into the distribution chamber 19, but into the combustion chamber casing I through the openings 26, is distributed between the tubular elements 2 and flows through the openings 18 recessed in the flame holder edge 13 (FIG. 2) to the combustion chamber, as a result of which the outer part of the flame holder 3 is cooled in such a way that the risk of burning, which is latent especially when producing divergent flame tongues, is counteracted.

Die Verbrennung des Gemisches wird, wie bereits erwähnt, mit dem grösstmöglichen Luftüberschuss angestrebt, wobei dieser einmal dadurch gegeben ist, dass die Flamme überhaupt noch brennt und im weiteren dadurch, dass nicht zuviel CO entsteht. Eine gute Optimierung kann beispeilsweise vorliegen, wenn der Luftanteil des Gemisches auf das 1,8-fache des stöchiometrischen Wertes gehalten wird. Die untere Abschlussrippe 24 verhindert eine freie Konvektion der heissen Luft aus dem Brennraum 7, wobei die Abschlussrippe 24 mit der gleichen durch die Oeffnungen 26 einströmenden Restluft, die dann durch die Oeffnungen 18 der benachbarten Flammenhatterränder 13 zum Brennraum 7 abströmt, mitgekühlt wird.As already mentioned, the combustion of the mixture is aimed at with the largest possible excess of air, which is given by the fact that the flame is still burning and further by the fact that not too much CO is produced. A good optimization can be present, for example, if the air content of the mixture is kept at 1.8 times the stoichiometric value. The lower terminating rib 24 prevents free convection of the hot air from the combustion chamber 7, the terminating rib 24 also being cooled with the same residual air flowing in through the openings 26, which then flows out through the openings 18 of the adjacent flame hatter edges 13 to the combustion chamber 7.

Der Flammenhalter 3, welcher den Abschluss des Strömungsabwärts gelegenen Teils des rohrförmigen Elementes 2 bildet, hat die Aufgabe, eine Rückzündung der Flamme vom Brennraum 7 ins Innere des rohrförmigen Elementes 2 zu verhindern. Die innere Wandung der Brennkammerhülle 1 ist im Bereich des Brennraumes 7, also ab Flammenhatter 3, mit einem nicht dargestellten Kühlungssystem versehen.The flame holder 3, which forms the end of the downstream part of the tubular element 2, has the task of preventing the flame from reigniting from the combustion chamber 7 into the interior of the tubular element 2. The inner wall of the combustion chamber casing 1 is provided with a cooling system (not shown) in the area of the combustion chamber 7, that is to say from the flame heater 3.

Wie aus Fig. 3 hervorgeht, weist der dargestellte Flammenhalter 3 eine Anzahl zylindrische und parallel zur Achse des rohrförmigen Elementes 2 verlaufende Löcher 21 auf. Sollen zusätzlich divergierende Flammenzungen erzeugt werden, so können, wie auf Fig. 4 und Fig. 5 hervorgeht, die Löcher 30 im Flammenhalter 3, mit Ausnahme des zentralen Loches, schräg in Radialebenen des Flammenhalters 3 angebracht werden, wobei der Winkel 38 von der Mitte zur Peripherie des Flammenhalters 3 hin stetig zunimmt oder gleichbleibt. Wie aus Fig. 6, 7 und 8 hervorgeht, können die Löcher 31 im Flammenhalter 3, mit Ausnahme des zentralen Loches, auch schräg in Tangentialebenen des Flammenhalters 3 angebracht werden, wobei der Winkel 37, ähnlich wie oben, von der Mitte zur Peripherie des Flammenhalters 3 hin stetig zunimmt oder gleichbleibt. Die Länge sowohl der parallelen Löcher 21 als auch der schrägen Löcher 30, 31 muss mindestens 1,5 Lochdurchmesser betragen. Durch die sich daraus ergebende erhöhte Gemischgeschwindigkeit in den Löchern 21, 30, 31 und die Länge der Löcher wird einer Flammenrückzündung aus dem Brennraum 7 entgegengewirkt. Die Anzahl der Löcher 21, 30, 31 muss jeweils den gegebenen Verhältnissen angepasst werden. Im dargestellten Beispiel aus Fig. 7 sind es beispielsweise einundzwanzig Löcher 31.As can be seen from FIG. 3, the flame holder 3 shown has a number of cylindrical holes 21 which run parallel to the axis of the tubular element 2. If additional divergent flame tongues are to be produced, as can be seen in FIGS. 4 and 5, the holes 30 in the flame holder 3, with the exception of the central hole, can be made obliquely in radial planes of the flame holder 3, the angle 38 from the center to the periphery of the flame holder 3 steadily increases or remains the same. 6, 7 and 8, the holes 31 in the flame holder 3, with the exception of the central hole, can also be made obliquely in tangential planes of the flame holder 3, the angle 37, similar to the above, from the center to the periphery of the Flame holder 3 increases steadily or remains the same. The length of both the parallel holes 21 and the oblique holes 30, 31 must be at least 1.5 hole diameter. The resulting increased mixture speed in the holes 21, 30, 31 and the length of the holes counteract flame reignition from the combustion chamber 7. The number of holes 21, 30, 31 must be adapted to the given conditions. In the example shown in FIG. 7, there are for example twenty-one holes 31.

In der in Fig. 11 gezeigten Anordnung, besteht der Flammenhalter 3 aus einer Oberplatte 3a und einer Unterplatte 3b, zwischen denen ein mit den Oeffnungen 8 in Verbindung stehender Kanal 10 verläuft. Die im Flammenhalter 3 angebrachten Oeffnungen 8 sind mit je zwei leicht konischen Büchsen 11, 12 ausgekleidet, wobei diese im Bereich des Kanals 10 sich teleskopartig und mit Spiel 16 überlappen. Ein Rückbrennen der Flamme aus dem Brennraum 7, insbesondere in der Grenzschicht entlang der Wandung der Büchse 12, wird entgegengewirkt, indem durch den Kanal 10 Druckluft herangeführt wird, welche durch das Spiel 16, entlang der gefährdeten Wandung der Büchse 12, mit dem Gemisch abströmt. Strömungsablösungen, die ein Rückzünden begünstigen würden, werden durch die konische Form der Oeffnungen 8 verhindert.In the arrangement shown in FIG. 11, the flame holder 3 consists of an upper plate 3a and a lower plate 3b, between which a channel 10 connected to the openings 8 runs. The openings 8 provided in the flame holder 3 are each lined with two slightly conical bushes 11, 12, these overlapping in the region of the channel 10 telescopically and with play 16. Burning back of the flame from the combustion chamber 7, in particular in the boundary layer along the wall of the sleeve 12, is counteracted by introducing compressed air through the channel 10, which flows through the play 16 along the endangered wall of the sleeve 12 with the mixture . Flow separations, which would favor reignition, are prevented by the conical shape of the openings 8.

Aus Fig. 15 geht hervor, dass der in Fig. 11 dargestellte Flammenhalter 3 sechzehn Oeffnungen 8 aufweist, welche symmetrisch aus zwei Kanälen 10 mit Druckluft gespeist werden. Selbstverständlich kann die Speisung der im Flammenhalter 3 angebrachten Oeffnungen 8 mit Druckluft durch andere Kanalkonfigurationen erfüllt werden.15 shows that the flame holder 3 shown in FIG. 11 has sixteen openings 8, which are fed symmetrically from two channels 10 with compressed air. Of course, the supply of the openings 8 made in the flame holder 3 with compressed air can be fulfilled by other channel configurations.

Wie in Fig. 14 dargestellt ist, werden die Oeffnungen 8 im Flammenhalter 3 als Diffusoren 39 ausgebildet. In Strömungsrichtung des Gemisches zum Brennraum 7 folgt einer anfänglichen zylindrischen Bohrung 32 eine Partie als Diffusor 40 ausgebildet, welchem eine zylindrische Bohrung 33 grösseren Durchmessers als die Eingangsbohrung 32 folgt, wobei jene eine Länge von mindestens 1,5 Bohrungsdurchmesser aufweist. Mit dieser Ausbildung ist bei gleichem Druckverlust eine höhere Geschwindigkeit an der engsten Stelle möglich, was sich in mehr Sicherheit gegen eine Flammenrückzündung aus dem Brennraum 7 niederschlägt. Durch die zylindrische Bohrung 33 wird der Flammenanfang im Brennraum 7 in eine entsprechende Distanz zum Diffusor 40 gebracht. Dadurch wird bei momentanen Strömungsablösungen im Diffusor 40 die Strömung im nachfolgenden zylindrischen Teil 33 wieder an die Wandung anliegen.As shown in FIG. 14, the openings 8 in the flame holder 3 are designed as diffusers 39. In the direction of flow of the mixture to the combustion chamber 7, an initial cylindrical bore 32 is followed by a section formed as a diffuser 40, which is followed by a cylindrical bore 33 of larger diameter than the inlet bore 32, which has a length of at least 1.5 bore diameter. With this design, a higher speed at the narrowest point is possible with the same pressure loss, which is reflected in greater safety against flame reignition from the combustion chamber 7. The beginning of the flame in the combustion chamber 7 is brought into a corresponding distance from the diffuser 40 through the cylindrical bore 33. As a result, in the event of current flow separations in the diffuser 40, the flow in the subsequent cylindrical part 33 will again rest against the wall.

Der Flammenhalter 3 kann, wie dies aus Fig. 9 und 10 hervorgeht, mit einem Drallkörper 28 versehen werden, wobei durch dessen Oeffnungen 41, beispielsweise mit vierzehn an der Zahl, das Gemisch drallförmig zum Brennraum 7 geleitet wird. Der Drallkörper 28 begünstigt eine gute luftstrahlige Durchmischung des Brennstoff/Luftgemisches und eine gute Wärmeverteilung, wodurch daraus eine homogene Temperatur- und Geschwindigkeitsverteilung nach dem Brennraum 7 resultiert mit dem Effekt, dass die nicht dargestellte Turbine gleichmässig beaufschlagt wird.The flame holder 3 can, as shown in FIG. 9 10 and 10, can be provided with a swirl body 28, the mixture being directed to the combustion chamber 7 in a swirling manner through its openings 41, for example fourteen in number. The swirl body 28 promotes good air-jet mixing of the fuel / air mixture and good heat distribution, which results in a homogeneous temperature and speed distribution after the combustion chamber 7, with the effect that the turbine, not shown, is acted upon uniformly.

Selbstverständlich können die rohrförmigen Elemente 2 und der einzelne Flammenhalter 3 selbst, kombinationsweise nach Figuren 3, 4/5, 6/7/8, 9/10, 11/15 oder 14 ausgebildet werden.Of course, the tubular elements 2 and the individual flame holder 3 itself, in combination according to Figures 3, 4/5, 6/7/8, 9/10, 11/15 or 14 can be formed.

Wie vorne bereits angedeutet, wird die Brennkammerhülle 1 mit einer grösseren Anzahl rohrförmiger Elemente 2 optimal ausgefüllt. Wie in Fig. 2 gezeigt ist, sind unter den eingesetzten siebenunddreissig rohrförmigen Elementen 2 dreizehn Pilotelemente 17 geometrisch gleichmässig verteilt. Beim Start der Brennkammer werden vorerst die Pilotelemente 17 durch ein nicht dargestelltes Initialzündungsaggregat in. Betrieb genommen. Bei Lasterhöhung springt die Flamme von den Pilotelementen 17 zu den umliegenden, die soeben in Betrieb genommen wurden, über.As already indicated above, the combustion chamber casing 1 is optimally filled with a larger number of tubular elements 2. As shown in FIG. 2, among the thirty-seven tubular elements 2 used, thirteen pilot elements 17 are geometrically evenly distributed. When the combustion chamber is started, pilot elements 17 are initially put into operation by an initial ignition unit (not shown). When the load increases, the flame jumps from the pilot elements 17 to the surrounding ones, which have just been put into operation.

Die Oeffnungen 8 im Flammenhalter 3 der Pilotelemente 17 können wahlweise nach den Löchern 30 und/oder nach den Löchern 31 ausgebildet werden. Für die Pilotelemente 17 kann auch der Einsatz von Drallkörpern 28 vorgesehen werden, welche ebenfalls wie die Löcher 30, 31 divergierende Flammenzungen erzeugen und so die Zündung der umliegenden rohrförmigen Elemente 2 begünstigen.The openings 8 in the flame holder 3 of the pilot elements 17 can optionally be formed after the holes 30 and / or after the holes 31. The use of swirl bodies 28 can also be provided for the pilot elements 17, which, like the holes 30, 31, also produce divergent flame tongues and thus favor the ignition of the surrounding tubular elements 2.

Die Anordnung wie sie aus Fig. 12 und 13 hervorgeht, also mit Drallkörper 28, ist als weitere Variante für die Pilotelemente 17 gedacht. Da hierbei die Brennstoffdüse 15 in den Brennraum 7 hineinragt, findet im rohrförmigen Element 2 kein VormischNorverdampfungsprozess statt. Diese Variante eignet sich dementsprechend auch nur als Starthilfe, womit gesagt ist, dass nur wenige Pilotelemente 17 nach dieser Ausführung vorgesehen zu werden brauchen.The arrangement as shown in FIGS. 12 and 13, that is, with swirl body 28, is intended as a further variant for the pilot elements 17. Since the fuel nozzle 15 projects into the combustion chamber 7, there is no pre-mixing nor evaporation process in the tubular element 2. Accordingly, this variant is only suitable as a starting aid, which means that only a few pilot elements 17 need to be provided according to this embodiment.

Wie aus Fig. 2, 5, 7, 10, 13 und 15 hervorgeht, ist der Flammenhalter 3 in Umfangsrichtung sechskantförmig 20 ausgebildet. Aus diesen Figuren geht ferner hervor, dass die im Flammenhalterboden 13 angebrachten Oeffnungen 18 zwischen sechskantförmigem Umfang 20 und rohrförmigen Element gleichmässig verteilt sind. Ein Polygonspiel 29 fängt die Wärmedehnungen in diesem Bereich auf.2, 5, 7, 10, 13 and 15, the flame holder 3 is hexagonal 20 in the circumferential direction. From these figures it can also be seen that the openings 18 made in the flame holder base 13 are evenly distributed between the hexagonal shape 20 and the tubular element. A polygon game 29 absorbs the thermal expansion in this area.

Wie bereits angedeutet geht aus Fig. 16 hervor, dass am Lufteingang des rohrförmigen Elementes 2, nach dem Lufttrichter 14, eine Bordamündung 34 eingesetzt ist, welche in diesem Bereich, also unmittelbar um die Brennstoffdüse 15, eine Turbulenz erzeugt, die dazu geeignet ist; den Vormischungs-, Zerstäubungs- und Vorverdampfungsprozess zusätzlich zu den weiter oben beschriebenen Massnahmen, also insbesondere durch die feine Einspritzung des Brennstoffes gegen die Lufteinströmungsrichtung, zu intensivieren. Selbstverständlich können auch andere Turbulenzverstärker an Stelle der Bordamündung 34 zum Einsatz gelangen.As already indicated in FIG. 16, it can be seen from FIG. 16 that, at the air inlet of the tubular element 2, after the air funnel 14, an orifice 34 is used, which in this area, that is to say directly around the fuel nozzle 15, generates turbulence which is suitable for this purpose; to intensify the premixing, atomization and pre-evaporation process in addition to the measures described above, that is to say in particular by the fine injection of the fuel against the direction of air inflow. Of course, other turbulence amplifiers can also be used instead of the on-board mouth 34.

Claims (12)

1. Combustion chamber of a gas turbine, in which the air distribution chamber (19) and the combustion space (7) are separated locally from one another within the combustion-chamber casing (1), and in which are arranged between the distribution chamber (19) and the combustion space (7) several tubular elements (2) in which take place the pre-mixing and pre-vaporisation of the fuel oil supplied through nozzles (15) at the end on the same side as the distribution chamber and/or the pre-mixing of the fuel gas, supplied through nozzles (15) at the end on the same side as the distribution chamber, with the compressor air, in the case of a high air excess number, characterised in that one or more pilot elements (17) are located between the tubular elements (2), and in that each tubular element (2) and the pilot element or elements (17) are closed at their end on the same side as the combustion space by a flame retention baffle (3) provided with one or more orifices (8).
2. Combustion chamber according to Claim 1, characterised in that, in the case of several pilot elements (17), these are arranged geometrically uniformly under the tubular elements (2), so that when the individual tubular elements (2) are started up in a sequence staggered as a function of the machine load a flash-over of the flame to the particular surrounding elements takes place.
3. Combustion chamber according to Claim 1, characterised in that the injection of the fuel supplied through nozzles (15) is directed against the air inflow direction.
4. Combustion chamber according to Claim 1, characterised in that the orifices (8) in the flame retention baffle (3) are cylindrical holes (21) which extend parallel to the axis of the tubular element (2) and the length of which is at least equal to 1.5 hole diameters.
5. Combustion chamber according to Claim 1, characterised in that the orifices (8) in the flame retention baffle (3) are holes (30) extending obliquely in radial planes of the flame retention baffle (3), the angle (36) increasing constantly from the centre to the periphery of the flame retention baffle (3) or remaining the same, and the length of the holes (30) being at least equal to 1.5 hole diameters.
6. Combustion chamber according to Claim 1, characterised in that the orifices (8) in the flame retention baffle (3) are holes (31) extending obliquely in tangential planes of the flame retention baffle (3), the angle (37) increasing constantly from the centre to the periphery of the flame retention baffle (3) or remaining the same, and the length of the holes (31) being at least equal to 1.5 hole diameters.
7. Combustion chamber according to Claim 1, characterised in that the orifices (8) in the flame retention baffle (3) are provided with swirl bodies (28).
8. Combustion chamber according to Claim 1, characterised in that the flame retention baffle (3) consists of a top plate (3a) and a bottom plate (3b), between which extends a channel (10) connected to the orifices (8), and in that the orifices (8) are each lined with two conical bushes (11, 12) which overlap one another telescopically and with play (16) in the region of the channel (10), with the result that the medium flowing through the channel (10) flows off together with the mixture from the tubular element (2).
9. Combustion chamber according to Claim 1, characterised in that the orifices (8) in the flame retention baffle (3) are designed as diffusors (40) with adjoining cylindrical orifices (33), the length of which amounts to at least 1.5 times their diameter.
10. Combustion chamber according to Claim 1, characterised in that several orifices (18) are made, round the outer shell of the tubular element (2), in the edge (13) of the flame retention baffle.
11. Combustion chamber according to Claim 1, characterised in that the outer periphery of the flame retention baffle (3) is designed as a polygon (20).
12. Combustion chamber according to Claim 1, characterised in that each tubular element (2) is provided at the end on the same side as the distribution chamber with a choke tube (14) and adjoining a sharp-edged orifice (34).
EP80200979A 1979-11-23 1980-10-16 Gas-turbine combustor with premixing-prevaporizing elements Expired EP0029619B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH10444/79 1979-11-23
CH1044479 1979-11-23

Publications (2)

Publication Number Publication Date
EP0029619A1 EP0029619A1 (en) 1981-06-03
EP0029619B1 true EP0029619B1 (en) 1983-06-01

Family

ID=4363297

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80200979A Expired EP0029619B1 (en) 1979-11-23 1980-10-16 Gas-turbine combustor with premixing-prevaporizing elements

Country Status (5)

Country Link
US (1) US4408461A (en)
EP (1) EP0029619B1 (en)
JP (1) JPS5691132A (en)
CA (1) CA1157280A (en)
DE (2) DE2950535A1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0095788A1 (en) * 1982-05-28 1983-12-07 BBC Aktiengesellschaft Brown, Boveri & Cie. Gas turbine combustion chamber and method of operating it
US4539811A (en) * 1982-01-27 1985-09-10 The United States Of America As Represented By The Secretary Of The Navy Multi-port dump combustor
EP0526152A1 (en) * 1991-08-01 1993-02-03 General Electric Company Flashback resistant fuel staged premixed combustor
FR2695460A1 (en) * 1992-09-09 1994-03-11 Snecma Gas annular turbine combustion chamber with several injectors - includes injectors in tubular base domes for idling, with full gas take off injectors alternating circumferentially and domes being interconnected
US5412938A (en) * 1992-06-29 1995-05-09 Abb Research Ltd. Combustion chamber of a gas turbine having premixing and catalytic burners
US5713206A (en) * 1993-04-15 1998-02-03 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor

Families Citing this family (123)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57207711A (en) * 1981-06-15 1982-12-20 Hitachi Ltd Premixture and revolving burner
DE3241162A1 (en) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim PRE-MIXING BURNER WITH INTEGRATED DIFFUSION BURNER
DE3318863A1 (en) * 1983-05-25 1984-12-13 Erich 8480 Weiden Bielefeldt Power engine with gas turbine
US5165241A (en) * 1991-02-22 1992-11-24 General Electric Company Air fuel mixer for gas turbine combustor
US5805973A (en) * 1991-03-25 1998-09-08 General Electric Company Coated articles and method for the prevention of fuel thermal degradation deposits
US5891584A (en) * 1991-03-25 1999-04-06 General Electric Company Coated article for hot hydrocarbon fluid and method of preventing fuel thermal degradation deposits
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
US5261226A (en) * 1991-08-23 1993-11-16 Westinghouse Electric Corp. Topping combustor for an indirect fired gas turbine
JPH0579631A (en) * 1991-09-19 1993-03-30 Hitachi Ltd Combustion device facility
JPH05203146A (en) * 1992-01-29 1993-08-10 Hitachi Ltd Gas turbine combustion apparatus and gas turbine power generator
US5274991A (en) * 1992-03-30 1994-01-04 General Electric Company Dry low NOx multi-nozzle combustion liner cap assembly
DE4223828A1 (en) * 1992-05-27 1993-12-02 Asea Brown Boveri Method for operating a combustion chamber of a gas turbine
US5247792A (en) * 1992-07-27 1993-09-28 General Electric Company Reducing thermal deposits in propulsion systems
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
EP0592717B1 (en) * 1992-10-16 1998-02-25 Asea Brown Boveri Ag Gas-operated premix burner
US5444982A (en) * 1994-01-12 1995-08-29 General Electric Company Cyclonic prechamber with a centerbody
DE4408136A1 (en) * 1994-03-10 1995-09-14 Bmw Rolls Royce Gmbh Method for fuel preparation for gas turbine combustion chamber
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
DE4444125A1 (en) * 1994-12-12 1996-06-13 Abb Research Ltd Process for clean combustion of pre=mixed gaseous or liquid fuels
WO1997040316A1 (en) * 1996-04-19 1997-10-30 Westinghouse Electric Corporation Premixed combustor with flashback arrestors
US5797268A (en) * 1996-07-05 1998-08-25 Westinghouse Electric Corporation Partially swirled multi-swirl combustor plate and chimneys
JP3448190B2 (en) * 1997-08-29 2003-09-16 三菱重工業株式会社 Gas turbine combustor
US6298667B1 (en) * 2000-06-22 2001-10-09 General Electric Company Modular combustor dome
US6672073B2 (en) * 2002-05-22 2004-01-06 Siemens Westinghouse Power Corporation System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate
US6996991B2 (en) * 2003-08-15 2006-02-14 Siemens Westinghouse Power Corporation Fuel injection system for a turbine engine
US6923002B2 (en) * 2003-08-28 2005-08-02 General Electric Company Combustion liner cap assembly for combustion dynamics reduction
CA2630721C (en) * 2005-12-14 2012-06-19 Rolls-Royce Power Engineering Plc Gas turbine engine premix injectors
JP4854613B2 (en) * 2007-07-09 2012-01-18 株式会社日立製作所 Combustion apparatus and gas turbine combustor
JP4922878B2 (en) * 2007-09-19 2012-04-25 株式会社日立製作所 Gas turbine combustor
JP4872992B2 (en) * 2008-09-12 2012-02-08 株式会社日立製作所 Combustor, fuel supply method for combustor, and modification method for combustor
US7886991B2 (en) * 2008-10-03 2011-02-15 General Electric Company Premixed direct injection nozzle
US9140454B2 (en) 2009-01-23 2015-09-22 General Electric Company Bundled multi-tube nozzle for a turbomachine
WO2010128882A1 (en) * 2009-05-07 2010-11-11 General Electric Company Multi-premixer fuel nozzle
US8522555B2 (en) * 2009-05-20 2013-09-03 General Electric Company Multi-premixer fuel nozzle support system
US8402763B2 (en) * 2009-10-26 2013-03-26 General Electric Company Combustor headend guide vanes to reduce flow maldistribution into multi-nozzle arrangement
EP2436983A1 (en) * 2010-10-04 2012-04-04 Siemens Aktiengesellschaft Jet burner
EP2442029A1 (en) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Impingement cooled head plate with thermal decoupling for a jet pilot
EP2442030A1 (en) * 2010-10-13 2012-04-18 Siemens Aktiengesellschaft Axial stage for a burner with a stabilised jet
US9506654B2 (en) * 2011-08-19 2016-11-29 General Electric Company System and method for reducing combustion dynamics in a combustor
US9243803B2 (en) * 2011-10-06 2016-01-26 General Electric Company System for cooling a multi-tube fuel nozzle
US9004912B2 (en) * 2011-11-11 2015-04-14 General Electric Company Combustor and method for supplying fuel to a combustor
US9033699B2 (en) * 2011-11-11 2015-05-19 General Electric Company Combustor
US20140311151A1 (en) * 2011-11-16 2014-10-23 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US9366440B2 (en) * 2012-01-04 2016-06-14 General Electric Company Fuel nozzles with mixing tubes surrounding a liquid fuel cartridge for injecting fuel in a gas turbine combustor
US9134023B2 (en) * 2012-01-06 2015-09-15 General Electric Company Combustor and method for distributing fuel in the combustor
US20130199190A1 (en) * 2012-02-08 2013-08-08 Jong Ho Uhm Fuel injection assembly for use in turbine engines and method of assembling same
US20130199189A1 (en) * 2012-02-08 2013-08-08 Jong Ho Uhm Fuel injection assembly for use in turbine engines and method of assembling same
US20130219899A1 (en) * 2012-02-27 2013-08-29 General Electric Company Annular premixed pilot in fuel nozzle
US9121612B2 (en) * 2012-03-01 2015-09-01 General Electric Company System and method for reducing combustion dynamics in a combustor
US9366445B2 (en) * 2012-04-05 2016-06-14 General Electric Company System and method for supporting fuel nozzles inside a combustor
US20130283802A1 (en) * 2012-04-27 2013-10-31 General Electric Company Combustor
US20130283810A1 (en) * 2012-04-30 2013-10-31 General Electric Company Combustion nozzle and a related method thereof
US9267690B2 (en) * 2012-05-29 2016-02-23 General Electric Company Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
US20130318976A1 (en) * 2012-05-29 2013-12-05 General Electric Company Turbomachine combustor nozzle and method of forming the same
US9291103B2 (en) * 2012-12-05 2016-03-22 General Electric Company Fuel nozzle for a combustor of a gas turbine engine
US10571124B2 (en) 2013-02-14 2020-02-25 Clearsign Combustion Corporation Selectable dilution low NOx burner
CA2892234A1 (en) 2013-02-14 2014-08-21 Clearsign Combustion Corporation Perforated flame holder and burner including a perforated flame holder
CN104903647B (en) 2013-02-14 2018-02-02 克利尔赛恩燃烧公司 Fuel combustion system with perforation stable reaction device
US10386062B2 (en) 2013-02-14 2019-08-20 Clearsign Combustion Corporation Method for operating a combustion system including a perforated flame holder
US10125983B2 (en) 2013-02-14 2018-11-13 Clearsign Combustion Corporation High output porous tile burner
US11460188B2 (en) 2013-02-14 2022-10-04 Clearsign Technologies Corporation Ultra low emissions firetube boiler burner
US10119704B2 (en) 2013-02-14 2018-11-06 Clearsign Combustion Corporation Burner system including a non-planar perforated flame holder
US20140251483A1 (en) * 2013-03-07 2014-09-11 General Electric Company Tube assembly for use in fuel injection assemblies and methods of assembling same
US9534787B2 (en) 2013-03-12 2017-01-03 General Electric Company Micromixing cap assembly
US9528444B2 (en) 2013-03-12 2016-12-27 General Electric Company System having multi-tube fuel nozzle with floating arrangement of mixing tubes
US9651259B2 (en) 2013-03-12 2017-05-16 General Electric Company Multi-injector micromixing system
US9347668B2 (en) * 2013-03-12 2016-05-24 General Electric Company End cover configuration and assembly
US9765973B2 (en) 2013-03-12 2017-09-19 General Electric Company System and method for tube level air flow conditioning
US9671112B2 (en) 2013-03-12 2017-06-06 General Electric Company Air diffuser for a head end of a combustor
US9650959B2 (en) 2013-03-12 2017-05-16 General Electric Company Fuel-air mixing system with mixing chambers of various lengths for gas turbine system
US9759425B2 (en) 2013-03-12 2017-09-12 General Electric Company System and method having multi-tube fuel nozzle with multiple fuel injectors
US9366439B2 (en) 2013-03-12 2016-06-14 General Electric Company Combustor end cover with fuel plenums
DE102013204309A1 (en) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft jet burner
US10190767B2 (en) 2013-03-27 2019-01-29 Clearsign Combustion Corporation Electrically controlled combustion fluid flow
WO2014183135A1 (en) 2013-05-10 2014-11-13 Clearsign Combustion Corporation Combustion system and method for electrically assisted start-up
US9322555B2 (en) 2013-07-01 2016-04-26 General Electric Company Cap assembly for a bundled tube fuel injector
US9371997B2 (en) * 2013-07-01 2016-06-21 General Electric Company System for supporting a bundled tube fuel injector within a combustor
US9273868B2 (en) * 2013-08-06 2016-03-01 General Electric Company System for supporting bundled tube segments within a combustor
CN105531540B (en) 2013-09-23 2018-04-06 克利尔赛恩燃烧公司 Using multiple buner systems and operating method for having hole flame holder
CN105556210B (en) 2013-09-23 2018-07-24 克利尔赛恩燃烧公司 For low NOXThe porous flame holder of burning
WO2015057740A1 (en) 2013-10-14 2015-04-23 Clearsign Combustion Corporation Flame visualization control for electrodynamic combustion control
CN105705864B (en) 2013-11-08 2017-10-03 克利尔赛恩燃烧公司 It is equipped with the combustion system of flame location actuating
EP3097365A4 (en) 2014-01-24 2017-10-25 Clearsign Combustion Corporation LOW NOx FIRE TUBE BOILER
CN106103338B (en) 2014-02-14 2018-04-20 克利尔赛恩燃烧公司 With the top burning type burner for having hole flame holder
US9885496B2 (en) 2014-07-28 2018-02-06 Clearsign Combustion Corporation Fluid heater with perforated flame holder
US9828288B2 (en) 2014-08-13 2017-11-28 Clearsign Combustion Corporation Perforated burner for a rotary kiln
CN107110496A (en) * 2014-12-24 2017-08-29 克利尔赛恩燃烧公司 Flameholder with fuel and oxidant recirculation includes the combustion system of such flameholder, and associated method
US10006715B2 (en) 2015-02-17 2018-06-26 Clearsign Combustion Corporation Tunnel burner including a perforated flame holder
WO2016134068A1 (en) * 2015-02-17 2016-08-25 Clearsign Combustion Corporation Burner system with a perforated flame holder and a plurality of fuel sources
US11473774B2 (en) 2015-02-17 2022-10-18 Clearsign Technologies Corporation Methods of upgrading a conventional combustion system to include a perforated flame holder
WO2016133936A1 (en) 2015-02-17 2016-08-25 Clearsign Combustion Corporation Prefabricated integrated combustion assemblies and methods of installing the same into a combustion system
WO2016134061A1 (en) 2015-02-17 2016-08-25 Clearsign Combustion Corporation Perforated flame holder with adjustable fuel nozzle
US20180051883A1 (en) * 2015-04-01 2018-02-22 Siemens Energy, Inc. Pre-mixing based fuel nozzle for use in a combustion turbine engine
RU2015156419A (en) 2015-12-28 2017-07-04 Дженерал Электрик Компани The fuel injector assembly made with a flame stabilizer pre-mixed mixture
US10088153B2 (en) 2015-12-29 2018-10-02 Clearsign Combustion Corporation Radiant wall burner including perforated flame holders
EP3403026B1 (en) 2016-01-13 2021-12-15 ClearSign Technologies Corporation Combustion system comprising a first and a second perforated flame holder, separated by a gap
US10551058B2 (en) 2016-03-18 2020-02-04 Clearsign Technologies Corporation Multi-nozzle combustion assemblies including perforated flame holder, combustion systems including the combustion assemblies, and related methods
WO2017190080A1 (en) 2016-04-29 2017-11-02 Clearsign Combustion Corporation Burner system with discrete transverse flame stabilizers
US10408455B2 (en) * 2016-06-14 2019-09-10 General Electric Company Fuel nozzle assembly with fuel inlet slots
US10514165B2 (en) 2016-07-29 2019-12-24 Clearsign Combustion Corporation Perforated flame holder and system including protection from abrasive or corrosive fuel
US10539326B2 (en) 2016-09-07 2020-01-21 Clearsign Combustion Corporation Duplex burner with velocity-compensated mesh and thickness
US10724740B2 (en) 2016-11-04 2020-07-28 General Electric Company Fuel nozzle assembly with impingement purge
US10295190B2 (en) 2016-11-04 2019-05-21 General Electric Company Centerbody injector mini mixer fuel nozzle assembly
US10393382B2 (en) 2016-11-04 2019-08-27 General Electric Company Multi-point injection mini mixing fuel nozzle assembly
US10465909B2 (en) 2016-11-04 2019-11-05 General Electric Company Mini mixing fuel nozzle assembly with mixing sleeve
US10352569B2 (en) 2016-11-04 2019-07-16 General Electric Company Multi-point centerbody injector mini mixing fuel nozzle assembly
US10634353B2 (en) 2017-01-12 2020-04-28 General Electric Company Fuel nozzle assembly with micro channel cooling
US10669942B2 (en) * 2017-02-23 2020-06-02 General Electric Company Endcover assembly for a combustor
US10273913B2 (en) 2017-05-25 2019-04-30 The United States Of America, As Represented By The Secretary Of The Navy Multi-mode thermoacoustic actuator
US11525578B2 (en) * 2017-08-16 2022-12-13 General Electric Company Dynamics-mitigating adapter for bundled tube fuel nozzle
KR102046455B1 (en) * 2017-10-30 2019-11-19 두산중공업 주식회사 Fuel nozzle, combustor and gas turbine having the same
JP2019128125A (en) * 2018-01-26 2019-08-01 川崎重工業株式会社 Burner device
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
JP7044669B2 (en) * 2018-09-05 2022-03-30 三菱重工業株式会社 Gas turbine combustor
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
EP4027059A1 (en) * 2021-01-12 2022-07-13 Crosstown Power GmbH Burner, combustor, and method for retrofitting a combustion appliance
US20230135396A1 (en) * 2021-11-03 2023-05-04 Power Systems Mfg., Llc Multitube pilot injector having a split airflow for a gas turbine engine
WO2023122177A1 (en) * 2021-12-21 2023-06-29 Spark Thermionics, Inc. Burner system and method of operation
US20230204213A1 (en) * 2021-12-29 2023-06-29 General Electric Company Engine fuel nozzle and swirler
US20230266003A1 (en) * 2022-02-22 2023-08-24 Honeywell International Inc. Ultra-low nox multi-port burner apparatus

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1020491B (en) * 1941-01-24 1957-12-05 Bayerische Motoren Werke Ag Jet engine with rechargeable combustion chamber and downstream gas turbine or propulsion jet nozzle or gas turbine and propulsion jet nozzle
DE805463C (en) * 1946-12-04 1951-05-21 Armstrong Siddeley Motors Ltd Combustion chamber for liquid fuel
DE806613C (en) * 1947-02-24 1951-06-14 Cem Comp Electro Mec Arrangement of the combustion chambers of gas turbines
GB657789A (en) * 1949-01-13 1951-09-26 Rolls Royce Improvements relating to liquid fuel combustion equipment for gas-turbine engines
US2565843A (en) * 1949-06-02 1951-08-28 Elliott Co Multiple tubular combustion chamber
DE1855295U (en) * 1961-03-06 1962-07-19 David Budworth Ltd FUEL EVAPORATIVE BURNER.
CH577627A5 (en) * 1974-04-03 1976-07-15 Bbc Sulzer Turbomaschinen
GB1559779A (en) * 1975-11-07 1980-01-23 Lucas Industries Ltd Combustion assembly
US4052144A (en) * 1976-03-31 1977-10-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Fuel combustor
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4262482A (en) * 1977-11-17 1981-04-21 Roffe Gerald A Apparatus for the premixed gas phase combustion of liquid fuels
GB2012413B (en) * 1977-12-05 1982-03-24 Secr Defence Evaproative fuel injectors
GB2012415B (en) * 1978-01-04 1982-03-03 Secr Defence Fuel mixers
US4215535A (en) * 1978-01-19 1980-08-05 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors
US4226083A (en) * 1978-01-19 1980-10-07 United Technologies Corporation Method and apparatus for reducing nitrous oxide emissions from combustors

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4539811A (en) * 1982-01-27 1985-09-10 The United States Of America As Represented By The Secretary Of The Navy Multi-port dump combustor
EP0095788A1 (en) * 1982-05-28 1983-12-07 BBC Aktiengesellschaft Brown, Boveri & Cie. Gas turbine combustion chamber and method of operating it
US4967561A (en) * 1982-05-28 1990-11-06 Asea Brown Boveri Ag Combustion chamber of a gas turbine and method of operating it
EP0526152A1 (en) * 1991-08-01 1993-02-03 General Electric Company Flashback resistant fuel staged premixed combustor
US5412938A (en) * 1992-06-29 1995-05-09 Abb Research Ltd. Combustion chamber of a gas turbine having premixing and catalytic burners
FR2695460A1 (en) * 1992-09-09 1994-03-11 Snecma Gas annular turbine combustion chamber with several injectors - includes injectors in tubular base domes for idling, with full gas take off injectors alternating circumferentially and domes being interconnected
US5713206A (en) * 1993-04-15 1998-02-03 Westinghouse Electric Corporation Gas turbine ultra low NOx combustor

Also Published As

Publication number Publication date
CA1157280A (en) 1983-11-22
DE2950535A1 (en) 1981-06-11
DE3063624D1 (en) 1983-07-07
US4408461A (en) 1983-10-11
JPS5691132A (en) 1981-07-23
JPH0130055B2 (en) 1989-06-15
EP0029619A1 (en) 1981-06-03

Similar Documents

Publication Publication Date Title
EP0029619B1 (en) Gas-turbine combustor with premixing-prevaporizing elements
EP2156095B1 (en) Swirling-free stabilising of the flame of a premix burner
DE3222347C2 (en)
DE60007946T2 (en) A combustion chamber
DE69828916T2 (en) Low emission combustion system for gas turbine engines
DE69822984T2 (en) Fuel line
DE60215351T2 (en) PREAMBLE CHAMBER FOR TURBINE COMBUSTION CHAMBER
EP0918191B1 (en) Burner for the operation of a heat generator
EP0924470B1 (en) Premix combustor for a gas turbine
EP1730448B1 (en) Multiple burner arrangement for operating a combustion chamber, and method for operating the multiple burner arrangement
EP0059490A1 (en) Annular combustion chamber with an annular burner for gas turbines
CH698007A2 (en) Stepped Mehrringdüse with radial intake for lean premix and two-material ring tube combustor.
DE2731562A1 (en) BURNERS FOR LIQUID AND / OR GASEOUS FUELS
EP1645802A2 (en) Premix Burner
DE69910106T2 (en) combustion chamber
EP1436546A1 (en) Burner for synthesis gas
DE2417147A1 (en) GAS TURBINE COMBUSTION DEVICE AND METHOD OF OPERATING THE DEVICE
WO2003098110A1 (en) Premix burner
EP0481111A1 (en) Gas-turbine combustion chamber
EP0394800A1 (en) Premix burner for generating a hot gas
EP0483554B1 (en) Method for minimising the NOx emissions from a combustion
DE60028127T2 (en) Combustion chamber for gas turbines
DE4409918A1 (en) Low calorific value fuel burner for combustion chamber
EP0882932B1 (en) Combustor
DE4422535A1 (en) Process for operating a furnace

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

Designated state(s): CH DE FR GB NL SE

17P Request for examination filed

Effective date: 19810725

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: BBC AKTIENGESELLSCHAFT BROWN, BOVERI & CIE.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Designated state(s): CH DE FR GB LI NL SE

REF Corresponds to:

Ref document number: 3063624

Country of ref document: DE

Date of ref document: 19830707

ET Fr: translation filed
PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

26 Opposition filed

Opponent name: KRAFTWERK UNION AKTIENGESELLSCHAFT

Effective date: 19840301

PLBN Opposition rejected

Free format text: ORIGINAL CODE: 0009273

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: OPPOSITION REJECTED

27O Opposition rejected

Effective date: 19850502

NLR2 Nl: decision of opposition
PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 19930127

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 19930915

Year of fee payment: 14

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19931031

Ref country code: CH

Effective date: 19931031

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19941017

EAL Se: european patent in force in sweden

Ref document number: 80200979.5

EUG Se: european patent has lapsed

Ref document number: 80200979.5

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 19970919

Year of fee payment: 18

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 NON-PAYMENT OF DUE FEES

Effective date: 19990501

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 19990501

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19990913

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: 19990927

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: 19990929

Year of fee payment: 20

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: 20001015

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Effective date: 20001015

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO