EP0029619A1 - Gas-turbine combustor with premixing-prevaporizing elements - Google Patents

Gas-turbine combustor with premixing-prevaporizing elements Download PDF

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Publication number
EP0029619A1
EP0029619A1 EP80200979A EP80200979A EP0029619A1 EP 0029619 A1 EP0029619 A1 EP 0029619A1 EP 80200979 A EP80200979 A EP 80200979A EP 80200979 A EP80200979 A EP 80200979A EP 0029619 A1 EP0029619 A1 EP 0029619A1
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EP
European Patent Office
Prior art keywords
combustion chamber
flame holder
openings
chamber according
air
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Granted
Application number
EP80200979A
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German (de)
French (fr)
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EP0029619B1 (en
Inventor
Eduard Brühwiler
Hans Koch
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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, in which the air distribution chamber and combustion chamber are spatially separated from one another within the combustion chamber shell.
  • the invention has for its object to provide a combustion chamber of a gas turbine in which the pollutants released by the combustion fall below the values permitted by the emission regulations.
  • the advantage of the invention can be seen in particular in the fact that the emission values of pollutants fall below the values permitted by the emission regulations without the injection of expensive aids into the combustion chamber. This is achieved by adding a pre-mixing / pre-evaporation phase to the actual combustion process.
  • the pre-mixing / pre-evaporation in performed several tubular elements the fuel being premixed / pre-evaporated with air from the compressor with a large excess of air.
  • This optimization process in the present combustion chamber can be driven in the direction of even lower NO x values by keeping the space for combustion and after-reactions much longer than would be necessary for the actual combustion.
  • pilot elements it is expedient to distribute them geometrically evenly among the tubular elements used. If those are still put into operation by initial ignition, this does not apply to the elements that 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 either provided with swirl bodies or with oblique holes so that divergent tongues of flame are generated, which additionally promote a 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. For the safe functioning of the diffuser, it is necessary to have a cylindrical section with a minimum length of 1.5 diameter.
  • the injection of the fuel is directed against the air inflow direction.
  • the pre-mixing / pre-evaporation process is promoted to such an extent that the length of the tubular element can be kept considerably shorter compared to another type of fuel supply.
  • the residence time of the mixture in the tubular element is reduced and the risk of auto-ignition is prevented.
  • 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 depends 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 illustrated support bridge 27, but in such cases it will always be necessary to ensure that the selected anchoring is placed as far away from the combustion chamber 7 as possible. so that the thermal expansion 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 1, which is down through the support bridge 27 and up 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 through 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 direction of air inflow.
  • 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.
  • 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 accordingly mixes with the inflowing compressed air in such a way that a pre-mixing / pre-evaporation process takes place in the tubular element 2.
  • This process can be carried out by inserting a flange 34 at the air inlet of the tubular element 2, as can be seen in FIG resulting turbulence can be intensified.
  • 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 such that the best possible evaporation results for the shortest possible time.
  • the 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 1 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 aims for the largest possible excess of air, which is given by the fact that the flame is still burning and then 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 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 holder 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 holder 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 diverging flame tongues are to be produced, as can be seen from 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 36 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 can be 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 rest against the wall.
  • the flame holder 3 can, as can be seen from FIGS. 9 and 10, be provided with a swirl body 28, the mixture being passed through the openings 41, for example fourteen in number, to the combustion chamber 7 in a swirling manner.
  • 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 applied evenly.
  • 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.
  • the pilot elements 17 are initially put into operation by an initial ignition unit (not shown).
  • 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.
  • a bord mouth 34 is used, which in this area, that is to say directly around the fuel nozzle 15, generates turbulence which is suitable for 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. long.

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

Abstract

Brennkammer einer Gasturbine, versehen mit einer Anzahl rohrförmiger Elemente (2), in denen zwischen Brennstoff und Verdichterluft ein Vormisch/Vorverdampfungsprozess abläuft, wobei jedes rohrförmige Element (2) an seinem Brennraum-seitigen Ende durch einen mit einer oder mehreren Oeffnungen (8) versehenen Flammenhalter (3) verschlossen ist, so dass die Verbrennung erst stromabwärts von dem Flammenhalter (3) stattfinden kann, wodurch die Emissionswerte an Schadstoffen aus der Verbrennung erheblich reduziert werden.Combustion chamber of a gas turbine, provided with a number of tubular elements (2), in which a pre-mixing / pre-evaporation process takes place between fuel and compressor air, each tubular element (2) at its combustion chamber end by one or more openings (8) Flame holder (3) is closed, so that the combustion can only take place downstream of the flame holder (3), whereby the emission values of pollutants from the combustion are considerably reduced.

Description

Die Erfindung betrifft die Brennkammer einer Gasturbine, in welcher innerhalb der Brennkammerhülle Luftverteilkammer und Brennraum örtlich voneinander getrennt sind.The invention relates to the combustion chamber of a gas turbine, in which the air distribution chamber and combustion chamber are spatially separated from one another within the combustion chamber shell.

Gasturbinen unterliegen zunehmend den strengen Umweltschutzvorschriften vieler Staaten bezüglich Abgaszusammensetzung. Aus dem Betrieb einer Gasturbine bereitet vor allem die Einhaltung der Vorschriften über die max. erlaubten NOx-Emissionen grosse Schwierigkeiten. So sind gegenwärtig rechtsgültige Vorschriften in Kraft, namentlich in USA, wonach der Gehalt an NOx-Emissionen 75 ppm bei 15 Vol.% 02 nicht überschritten werden darf. Aehnliche Vorschriften gilt es in den meisten Industriestaaten zu beachten, wobei eher zu erwarten ist, dass in Zukunft die zulässigen Emissionswerte eine Korrektur nach unter erfahren werden. Diese Vorschriften konnten bis anhin nur unter Zuhilfenahme grosser Wasser- oder Dampfeinspritzungen in den Verbrennungsraum eingehalten werden. Die für die Herabsetzung der Emissionswerte eingesetzten Hilfsmittel, also Wasser oder Dampf, bringen aber einige bedeutende Nachteile mit sich.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 max. allowed NO x emissions to be very difficult. For example, currently valid regulations are in force, especially in the USA, according to which the content of NO x emissions may not exceed 75 ppm at 15% by volume 0 2 . Similar regulations must be observed in most industrialized countries, although it is more likely that the permissible emission values will be corrected in the future. Until now, these regulations could only be met with the help of large water or steam injections into the combustion chamber. The tools used to reduce the emission values, i.e. water or steam, have some significant disadvantages.

Wird Wasser in den Verbrennungsraum eingespritzt, so ist mit einer Einbusse des Wirkungsgrades zu rechnen. Darüber hinaus ist Wasser nicht immer und überall in verfügbarer Menge vorhanden, so z.B. in niederschlagsarmen Ländern. Ferner muss das Wasser vor dessen Einsatz einer Aufbereitung unterzogen werden, denn viele im Wasser vertretene Mineralien, so z.B. Natrium, Kochsalz etc., wirken sich auf ihre Umgebung stark korrosiv aus. Diese Aufbereitung ist indessen kostspielig und energieintensiv.If water is injected into the combustion chamber, a loss in efficiency can be expected. In addition, water is not always and everywhere available, e.g. in low-precipitation countries. Furthermore, the water must be treated before it is used, because many minerals represented in the water, e.g. Sodium, table salt etc. have a highly corrosive effect on their surroundings. However, this processing is expensive and energy-intensive.

Führt man hingegen Dampf dem Verbrennungsraum zu, so umgeht man die oben erwähnte Wirkungsgradeinbusse. Die Dampferzeugung setzt aber auch Wasser voraus und die Bereitstellung ist nicht minder energieintensiv.If, on the other hand, steam is fed into the combustion chamber, then the efficiency loss mentioned above is avoided. However, steam generation also requires water and the provision is no less energy-intensive.

Der Erfindung liegt die Aufgabe zugrunde, eine Brennkammer einer Gasturbine zu schaffen, in welcher die durch die Verbrennung freiwerdenden Schadstoffe unter die von den Emissionsvorschriften erlaubten Werte fallen.The invention has for its object to provide a combustion chamber of a gas turbine in which the pollutants released by the combustion fall below the values permitted by the emission regulations.

Diese Aufgabe wird erfindungsgemäss mit den kennzeichnenden Merkmalen des Patentanspruchs 1 gelöst.This object is achieved according to the invention with the characterizing features of patent claim 1.

Der Vorteil der Erfindung ist insbesondere darin zu sehen, dass die Emissionswerte von Schadstoffen ohne Einspritzung kostspieliger Hilfsmittel in den Verbrennungsraum unter die von den Emissionsvorschriften erlaubten Werte fallen. Dies wird erreicht, indem dem eigentlichen Verbrennungsprozess eine Vormisch/Vorverdampfungs-phase vorgeschaltet wird.The advantage of the invention can be seen in particular in the fact that the emission values of pollutants fall below the values permitted by the emission regulations without the injection of expensive aids into the combustion chamber. This is achieved by adding a pre-mixing / pre-evaporation phase to the actual combustion process.

Zu diesem Zweck wird das Vormischen/Vorverdampfen in mehreren rohrförmigen Elementen durchgeführt, wobei der Brennstoff mit Luft aus dem Verdichter bei grosser Luftüberschusszahl vorgemischt/vorverdampft wird. Die Verbrennung mit der grösstmöglichen Luftüberschusszahl - einmal dadurch gegeben, dass die Flamme überhaupt noch brennt und im weiteren dadurch, dass nicht zuviel CO entsteht - vermindert indessen nicht nur die Schadstoffmenge von NO , sondern bewirkt darüber hinaus auch eine konsistente Tiefhaltung anderer Schadstoffe, nämlich, wie bereits erwähnt, von CO und von unverbrannten Kohlenwasserstoffen. Dieser Optimierungsprozess kann bei der vorliegenden Brennkammer dadurch in Richtung noch tieferer NOX-Werte getrieben werden, dass der Raum für Verbrennung und Nachreaktionen viel länger gehalten wird als für die eigentliche Verbrennung notwendig wäre. Dies erlaubt die Wahl einer grösseren Luftüberschusszahl, wobei dann zwar zunächst grössere Mengen CO entstehen, diese aber zu C02 weiterreagieren können, so dass schliesslich die CO-Emissionen klein bleiben. Auf der anderen Seite bildet sich aber, wegen des grossen Luftüberschusses, nur wenig zusätzliches NO.For this purpose the pre-mixing / pre-evaporation in performed several tubular elements, the fuel being premixed / pre-evaporated with air from the compressor with a large excess of air. 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 pollutants, but also causes a consistent deepening of other pollutants, namely, as already mentioned, of CO and unburned hydrocarbons. This optimization process in the present combustion chamber can be driven in the direction of even lower NO x values by keeping the space for combustion and after-reactions much longer than would be necessary for the actual combustion. This allows a larger excess air number to be selected, with larger quantities of CO initially being produced, but these being able to react further to C0 2 , so that ultimately the CO emissions remain small. On the other hand, due to the large excess of air, only a little additional NO is formed.

Da mehrere rohrförmige Elemente das Vormischen/Vorverdampfen übernehmen, ergibt sich daraus der Verteil, dass bei der Lastregelung jeweils nur soviele Elemente mit Brennstoff betrieben werden, dass sich für die jeweilige Betriebsphase (Start, Teillast etc.) die optimale Luftüberschusszahl ergibt.Since several tubular elements take over the pre-mixing / pre-evaporation, this results in the distribution that with the load control only so many elements are operated with fuel that the optimum excess air number results for the respective operating phase (start, partial load etc.).

Sofern mehrere Pilotelemente 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, it is expedient to distribute them geometrically evenly among the tubular elements used. If those are still put into operation by initial ignition, this does not apply to the elements that 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 either provided with swirl bodies or with oblique holes so that divergent tongues of flame are generated, which additionally promote a 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 Brenn- raum. 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. For the safe functioning of the diffuser, it is necessary to have 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 Vormisch/Vorverdampfungsprozess 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. As a result, the pre-mixing / pre-evaporation process is promoted to such an extent that the length of the tubular element can be kept considerably shorter compared to another type of fuel supply. As a result, the residence time of the mixture in the tubular element is reduced and the risk of auto-ignition is 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:

  • Fig. l: Eine Schnittdarstellung einer Brennkammer,
  • Fig. 2: Eine Anordnung der rohrförmigen Elemente in der Brennkammer,
  • Fig. 3: Eine Schnittdarstellung eines Flammenhalters mit parallelen Löchern,
  • Fig. 4 Eine Darstellung eines weiteren Flammenhalters
  • Fig. 5 mit schrägen Löchern,
  • Fig. 6 Eine Darstellung eines weiteren Flammenhalters
  • Fig. 7 mit schrägen Löchern,
  • Fig. 8
  • Fig. 9 Eine Darstellung eines weiteren Flammenhalters
  • Fig. 10 mit Drallkörper versehen,
  • Fig. ll: Eine Schnittdarstellung eines weiteren Flammenhalters mit Oeffnungen als Injektoren ausgebildet,
  • Fig. 12 Eine Darstellung eines Pilotelementes mit
  • Fig. 13 Diffusionsflamme,
  • Fig. 14: Eine Schnittdarstellung eines weiteren Flammenhalters mit Oeffnungen als Diffusoren ausgebildet,
  • Fig. 15: Eine Ansicht des Flammenhalters von Fig. 11 einschliesslich Ausgestaltung des Luftzuführungskanals,
  • Fig. 16: Eine Darstellung der mittels Ringe geführten rohrförmigen Elemente mit Bordamündung.
It shows:
  • 1: a sectional view of a combustion chamber,
  • 2: an arrangement of the tubular elements in the combustion chamber,
  • 3: A sectional view of a flame holder with parallel holes,
  • Fig. 4 shows a further flame holder
  • 5 with oblique holes,
  • Fig. 6 shows a further flame holder
  • 7 with oblique holes,
  • Fig. 8
  • Fig. 9 shows a further flame holder
  • 10 provided with swirl body,
  • 11: shows a sectional illustration of a further flame holder with openings as injectors,
  • Fig. 12 shows a pilot element with
  • 13 diffusion flame,
  • 14: a sectional view of a further flame holder with openings designed as diffusers,
  • 15: a view of the flame holder of FIG. 11 including the configuration of the air supply duct,
  • Fig. 16: A representation of the tubular elements guided by means of rings with a 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 Abschlussmuttern 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 depends 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 illustrated support bridge 27, but in such cases it will always be necessary to ensure that the selected anchoring is placed as far away from the combustion chamber 7 as possible. so that the thermal expansion 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 1 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 Brennstoff- öffnungen 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 Vormisch/Vorverdampfungsprozess 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 1, which is down through the support bridge 27 and up 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 through 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 direction of air inflow. 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 accordingly mixes with the inflowing compressed air in such a way that a pre-mixing / pre-evaporation process takes place in the tubular element 2. This process can be carried out by inserting a flange 34 at the air inlet of the tubular element 2, as can be seen in FIG resulting turbulence can be intensified. 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 such 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 1 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 1 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 beispielsweise 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 Flammenhalterränder 13 zum Brennraum 7 abströmt, mitgekühlt wird.The combustion of the mixture, as already mentioned, aiming for the largest possible excess of air, which is given by the fact that the flame is still burning and then 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 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 holder 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 Flammenhalter 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 holder 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 aus 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 36 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 diverging flame tongues are to be produced, as can be seen from 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 36 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 attached obliquely in the tangential planes of the flame holder 3, the angle 37, similarly to the above, increasing or remaining constant from the center to the periphery of the flame holder 3. 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 that the flame holder 3 shown in FIG. 11 has sixteen openings 8, which can be 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 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 can be seen from FIGS. 9 and 10, be provided with a swirl body 28, the mixture being passed through the openings 41, for example fourteen in number, to the combustion chamber 7 in a swirling manner. 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 applied evenly.

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, the 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 Vormisch/Vorverdampfungsprozess 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 / pre-evaporation process in the tubular element 2. This variant Accordingly, it is also 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 rohrförmigem 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 ge- . langen.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, a bord mouth 34 is used, which in this area, that is to say directly around the fuel nozzle 15, generates turbulence which is suitable for 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. long.

B e z e i c h n u n g s l i s t eB e z e i c h n u n g s l i s t e

  • 1 = Brennkammerhülle1 = combustion chamber shell
  • 2 = Rohrförmiges Element2 = tubular element
  • 3 = Flammenhalter3 = flame holder
  • 3a = Flammenhalteroberplatte3a = flame holder top plate
  • 3b = Flammenhalterunterplatte3b = flame holder lower plate
  • 4 = Brennstoffleitung4 = fuel line
  • 5 = Abschlussmutter5 = final nut
  • 6 = Führungsplatte6 = guide plate
  • 7 = Brennraum7 = combustion chamber
  • 8 = Oeffnungen im Flammenhalter8 = openings in the flame holder
  • 9 = Oeffnungen in Brennkammerhülle9 = openings in the combustion chamber shell
  • 10 = Kanal10 = channel
  • 11 = Büchse Oberplatte11 = top plate sleeve
  • 12 = Büchse Unterplatte12 = bush lower plate
  • 13 = Flammenhalterrand13 = flame holder edge
  • 14 = Lufttrichter14 = air funnel
  • 15 = Brennstoffdüse im rohrförmigen Element15 = fuel nozzle in the tubular element
  • 16 = Spiel zwischen den Büchsen16 = game between the cans
  • 17 = Pilotbrenner17 = pilot burner
  • 18 = Oeffnungen im Flammenhalterrand18 = openings in the flame holder edge
  • 19 = Verteilkammer19 = distribution chamber
  • 20 = Polygon20 = polygon
  • 21 = Parallele Löcher21 = parallel holes
  • 22 = Tragelemente22 = support elements
  • 23 = Tragrippe23 = support rib
  • 24 = Untere Abschlussrippe24 = lower end rib
  • 25 = Führungsring25 = guide ring
  • 26 = Kühllufteinlass26 = K u h llufteinlass
  • 27 = Tragbrücke27 = support bridge
  • 28 = Drallkörper28 = D rallkörper
  • 29 Polygonspiel29 polygon game
  • 30 = Schräge Löcher in.Radialebene30 = oblique holes in radial plane
  • 31 = Schräge Löcher in Tangentialebene3 1 = Oblique holes in the tangential plane
  • 32 = Zylindrische Bohrung32 = cylindrical bore
  • 33 = Zylindrische Bohrung33 = cylindrical bore
  • 34 = Bordamündung34 = B mouth
  • 35 = Deckel35 = lid
  • 36 = Winkel36 = angle
  • 37 = Winkel37 = angle
  • 38 Flanschrippe38 flange rib
  • 39 = Löcher als Diffusoren39 = holes as diffusers
  • 40 = Diffusor40 = diffuser
  • 41 = Oeffnungen im Drallkörner41 = openings in the swirl grains

Claims (12)

1. Brennkammer einer Gasturbine, in welcher, innerhalb der Brennkammerhülle, Luftverteilkammer und Brennraum örtlich voneinander getrennt sind, dadurch gekennzeichnet, dass zwischen Verteilkammer (19) und Brennraum (7) mehrere rohrförmige Elemente (2) eingeordnet sind, in denen das Vormischen und das Vorverdampfen des am Verteilkammer-seitigen Ende durch Düsen (15) zugeführten Brennöls und/oder das Vormischen des am Verteilkammerseitigen Ende durch Düsen (15) zugeführten Brenngases mit der Verdichterluft bei grosser Luftüberschusszahl abläuft, wobei jedes rohrförmige Element (2) an seinem Brennraum-seitigen Ende durch einen mit einer oder mehreren Oeffnungen (8) versehenen Flammenhalter (3) verschlossen ist und wobei sich zwischen den rohrförmigen Elementen (2) ein oder mehrere Pilotelemente (17) befinden.1. Combustion chamber of a gas turbine, in which, within the combustion chamber casing, air distribution chamber and combustion chamber are spatially separated from one another, characterized in that several tubular elements (2) are arranged between the distribution chamber (19) and combustion chamber (7), in which the premixing and the Pre-evaporation of the fuel oil supplied at the end of the distribution chamber through nozzles (15) and / or the premixing of the fuel gas supplied at the end of the distribution chamber through nozzles (15) with the compressor air takes place with a large excess of air, with each tubular element (2) on its combustion chamber side End is closed by a flame holder (3) provided with one or more openings (8) and one or more pilot elements (17) are located between the tubular elements (2). 2. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass bei mehreren Pilotelementen (17) diese unter den rohrförmigen Elementen (2) so geometrisch gleichmässig angeordnet sind, dass bei in Abhängigkeit zur Maschinenlast gestaffelter Inbetriebnahme der einzelnen rohrförmigen Elemente (2) ein Ueberspringen der Flamme zu den jeweils umliegenden stattfindet.2. Combustion chamber according to claim 1, characterized in that in the case of a plurality of pilot elements (17), these are arranged geometrically uniformly under the tubular elements (2) in such a way that when the individual tubular elements (2) are staggered depending on the machine load, the flame leaps over to the each surrounding takes place. 3. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass die Einspritzung des durch Düsen (15) zugeführten Brennstoffes gegen die Lufteinströmungsrichtung gerichtet ist.3. Combustion chamber according to claim 1, characterized in that the injection of the fuel supplied through nozzles (15) is directed against the air inflow direction. 4. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass die Oeffnungen (8) im Flammenhalter (3) zylindrische und parallel zur Achse des rohrförmigen Elementes (2) verlaufende Löcher (21) sind,-deren Länge ≥ 1,5 Lochdurchmesser ist.4. Combustion chamber according to claim 1, characterized in that the openings (8) in the flame holder (3) are cylindrical and parallel to the axis of the tubular element (2) holes (21) whose length is ≥ 1.5 hole diameter. 5. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass die Oeffnungen (8) im Flammenhalter (3) schräg in Radialebenen des Flammenhalters (3) verlaufende Löcher (30) sind, wobei der Winkel (36) von der Mitte zur Peripherie des Flammenhalters (3) hin stetig zunimmt oder gleichbleibt und wobei die Länge der Löcher (30)≥ 1,5 Lochdurchmesser ist.5. Combustion chamber according to claim 1, characterized in that the openings (8) in the flame holder (3) obliquely in radial planes of the flame holder (3) are holes (30), the angle (36) from the center to the periphery of the flame holder ( 3) increases steadily or remains the same and the length of the holes (30) is ≥ 1.5 hole diameter. 6. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass die Oeffnungen (8) im Flammenhalter (3) schräg in Tangentialebenen des Flammenhalters (3) verlaufende Löcher (31) sind, wobei der Winkel (37) von der Mitte zur Peripherie des Flammenhalters (3) hin stetig zunimmt oder gleichbleibt und wobei die Länge der Löcher (31) ≥ 1,5 Lochdurchmesser ist.6. Combustion chamber according to claim 1, characterized in that the openings (8) in the flame holder (3) obliquely in tangential planes of the flame holder (3) are holes (31), the angle (37) from the center to the periphery of the flame holder ( 3) increases steadily or remains the same and the length of the holes (31) is ≥ 1.5 hole diameter. 7. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass die Oeffnungen (8) im Flammenhalter (3) mit Drallkörpern (28) versehen sind.7. Combustion chamber according to claim 1, characterized in that the openings (8) in the flame holder (3) with swirl bodies (28) are provided. 8. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass der Flammenhalter (3) aus einer Oberplatte (3a) und einer Unterplatte (3b) besteht, zwischen denen ein mit den Oeffnungen (8) in Verbindung stehender Kanal (10) verläuft und dass die Oeffnungen (8) mit je zwei konischen Büchsen (11, 12) ausgekleidet sind, welche sich im Bereich des Kanals (10) teleskopartig und mit Spiel (16) überlappen, wodurch das durch den Kanal (10) herströmende Medium mit dem Gemisch aus dem rohrförmigen Element (2) abströmt.8. Combustion chamber according to claim 1, characterized in that the flame holder (3) consists of an upper plate (3a) and a lower plate (3b), between which a channel (10) communicating with the openings (8) runs and that Openings (8) are lined with two conical sleeves (11, 12) which overlap telescopically and with play (16) in the region of the channel (10), so that the medium flowing through the channel (10) with the mixture of the flows out tubular element (2). 9. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass die Oeffnungen (8) im Flammenhalter (3) als Diffusoren (40) mit anschliessend zylindrischen Oeffnungen (33) ausgebildet sind, deren Länge mindestens das 1,5-fache ihres Durchmessers beträgt.9. Combustion chamber according to claim 1, characterized in that the openings (8) in the flame holder (3) as diffusers (40) with subsequent cylindrical openings (33) are formed, the length of which is at least 1.5 times its diameter. 10. Brennkammer nach Patentanspruch l, dadurch gekennzeichnet, dass im Flammenhalterrand (13), um den Aussenmantel des rohrförmigen Elementes (2) herum, mehrere Oeffnungen (18) ausgenommen sind.10. Combustion chamber according to claim 1, characterized in that in the flame holder edge (13), around the outer jacket of the tubular element (2), several openings (18) are excluded. 11. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass der Aussenumfang des Flammenhalters (3) als Polygon (20) ausgebildet ist.11. Combustion chamber according to claim 1, characterized in that the outer circumference of the flame holder (3) is designed as a polygon (20). 12. Brennkammer nach Patentanspruch 1, dadurch gekennzeichnet, dass jedes rohrförmige Element (2) am Verteilkammerseitigen Ende mit einem Lufttrichter (14) und einer anschliessenden Bordamündung (34) versehen ist.12. Combustion chamber according to claim 1, characterized in that each tubular element (2) is provided at the end of the distribution chamber with an air funnel (14) and a subsequent mouth (34).
EP80200979A 1979-11-23 1980-10-16 Gas-turbine combustor with premixing-prevaporizing elements Expired EP0029619B1 (en)

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CH10444/79 1979-11-23
CH1044479 1979-11-23

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US2565843A (en) * 1949-06-02 1951-08-28 Elliott Co Multiple tubular combustion chamber
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
GB2012413A (en) * 1977-12-05 1979-07-25 Secr Defence Fuel injector
GB2012415A (en) * 1978-01-04 1979-07-25 Secr Defence Fuel Mixer
DE2901099A1 (en) * 1978-01-19 1979-07-26 United Technologies Corp FUEL EVAPORATION DEVICE, COMBUSTION CHAMBER EQUIPPED WITH IT, AND METHOD OF OPERATING THE SAME
FR2415203A1 (en) * 1978-01-19 1979-08-17 United Technologies Corp FUEL VAPORIZATION DEVICE FOR COMBUSTION CHAMBER

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0620402A1 (en) * 1993-04-15 1994-10-19 Westinghouse Electric Corporation Premix combustor with concentric annular passages
EP0766045A1 (en) * 1993-04-15 1997-04-02 Westinghouse Electric Corporation Working method for a premix combustor
WO1997040316A1 (en) * 1996-04-19 1997-10-30 Westinghouse Electric Corporation Premixed combustor with flashback arrestors
EP2163819A3 (en) * 2008-09-12 2011-04-20 Hitachi Ltd. Combustor, method of supplying fuel to same, and method of modifying same
US8468832B2 (en) 2008-09-12 2013-06-25 Hitachi, Ltd. Combustor, method of supplying fuel to same, and method of modifying same
EP3620719A1 (en) * 2018-09-05 2020-03-11 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
EP4230909A1 (en) * 2022-02-22 2023-08-23 Honeywell International Inc. Ultra-low nox multi-port burner apparatus

Also Published As

Publication number Publication date
CA1157280A (en) 1983-11-22
EP0029619B1 (en) 1983-06-01
DE2950535A1 (en) 1981-06-11
DE3063624D1 (en) 1983-07-07
JPH0130055B2 (en) 1989-06-15
US4408461A (en) 1983-10-11
JPS5691132A (en) 1981-07-23

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