EP0401529A1 - Gas turbine combustion chamber - Google Patents

Gas turbine combustion chamber Download PDF

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Publication number
EP0401529A1
EP0401529A1 EP90108684A EP90108684A EP0401529A1 EP 0401529 A1 EP0401529 A1 EP 0401529A1 EP 90108684 A EP90108684 A EP 90108684A EP 90108684 A EP90108684 A EP 90108684A EP 0401529 A1 EP0401529 A1 EP 0401529A1
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EP
European Patent Office
Prior art keywords
combustion chamber
burners
burner
premix burners
air
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP90108684A
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German (de)
French (fr)
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EP0401529B1 (en
Inventor
Jakob Dr. Keller
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.)
ABB Asea Brown Boveri Ltd
ABB AB
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ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the present invention relates to a combustion chamber according to the preamble of claim 1.
  • premix burners With regard to the prescribed, extremely low NO x emissions when operating a gas turbine, many manufacturers are adopting premix burners.
  • One of the disadvantages of premix burners is that they extinguish at very low air numbers, depending on the temperature of the compressor of the gas turbine, at around 2. For this reason, such premix burners must be supported by one or more pilot burners in the partial load operation of a gas turbine. Diffusion burners are usually used for this.
  • This technology enables very low No x emissions in the area of full load. In contrast, this auxiliary burner system leads at partial load operation at significantly higher NO x emissions.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object of providing a combustion chamber which, with minimized exhaust gas emissions, enables a wide operating range, while optimizing the quality factor for the temperature profile at the turbine inlet, in the technical term "pattern factor".
  • main burners are related to the small premix burners, hereinafter referred to as pilot burners, with regard to the flow through them
  • the pilot burners work as independent premix burners in the entire load range of the combustion chamber, with the air ratio remaining almost constant. Because the pilot burners can now be operated in the entire load range with an ideal mixture (premix burner), the NO x emissions are very low even at partial load. It also shows that, in the interest of "up-prizing" potential for gas turbines with higher turbine inlet temperatures, the proportion of air that cannot be formed by the burners (lean blowoff limit, CO / UHC) is not, because of the pattern factor, should only be used for cooling purposes.
  • a certain proportion of air is introduced via the air nozzles provided here, preferably after the primary combustion zone of the combustion chamber, and there it is ensured that perfect mixing takes place.
  • This has the advantage that the proportion of air that ensures “up-rating” and is therefore blown directly into the secondary combustion zone prevents the undesirable "thinning" of the primary zone. Since the air nozzles are located at a point with a very low air velocity and only occupy a limited width of the front wall, their influence on the main flow field in the primary area is only very weak. In particular, the air nozzles do not interfere with the cross-ignition between primary burners and main burners. Another advantage of these air nozzles results from their position on the front wall; this zone would become very hot there without the cooling effect of the air jets.
  • main burners and the pilot burners consist of so-called double-cone burners of different sizes, and if these are integrated in an annular combustion chamber. Because the circulating streamlines in the annular combustion chamber come very close to the vortex centers of the pilot burners in such a constellation, ignition is only possible with these pilot burners.
  • the amount of fuel that is supplied via the pilot burner is increased until the pilot burner is activated, i.e. until the full amount of fuel is available.
  • the configuration is chosen so that this point corresponds to the load shedding condition of the gas turbine.
  • the further increase in output then takes place via the main burner.
  • the main burners are also fully controlled at the peak load of the system.
  • FIG. 1 shows a section of a sector of the front wall 10. This shows the placement of the individual main burners B and pilot burners C. These are evenly and alternately distributed over the circumference of the annular combustion chamber A.
  • the size difference shown between main burners B and pilot burners C is only of a qualitative nature.
  • the effective size of the individual burners and their distribution and number on the circumference of the front wall 10 of the annular combustion chamber A, as already explained above, depends on the power and size of the combustion chamber itself.
  • the main burners B and pilot burners C which are arranged alternately, open out all at the same height in a uniform annular front wall 10, which forms the entry surface of the annular combustion chamber A.
  • a number of air nozzles D are provided, which occupy approximately half the width of the front wall 10 in the radial direction.
  • a circulating flow that surrounds the burners B and C is created above and below them.
  • the role of the roles is here through the co-rotating burner taken over.
  • a vortex center is also created around the respective burner; around the pilot burner C, the vortex centers are small and hot, and inherently unstable. These come to rest between the large, cooler vortex centers originating from the main burners B.
  • the air nozzles F act, which decisively improve the stabilization of the two, as has already been appreciated in the foregoing. Even if the main burners B are operated lean, as is the case in part-load operation, a very good burnout with low CO / UHC emissions can be expected.
  • FIGS. 2 and 3 show a schematic section through an annular combustion chamber A, respectively in the plane of a pilot burner C and. of a main burner B.
  • the annular combustion chamber A shown here is tapered in the direction of the turbine inlet D, as can be seen from the central axis E of the annular combustion chamber A shown.
  • An individual nozzle 3 is allocated to each burner B, C.
  • the burners B, C are at the same time premix burners, that is to say they do without the otherwise usual premix zone.
  • these premix burners B, C regardless of their specific design, must be designed in such a way that there is no fear of re-ignition into the premix zone via the respective front panel 10.
  • a premix burner which excellently fulfills this condition is shown comprehensively in FIGS. 6-9 and explained in more detail there, the structure being able to be the same for both burner types (main burner B / pilot burner C), only their size will be different.
  • the size ratio between main burner B and pilot burner C is selected such that about 23% of the burner air flows through the pilot burner C and about 77% through the main burner B.
  • FIG. 4 and 5 schematically show a main burner B, according to section IV-IV from FIG. 1, and the air nozzles F, according to section V-V from FIG. 1, in a positionally coordinated axial section.
  • the structure for the air nozzles F which extends far into the combustion chamber with respect to the front wall 10 and which causes the air to act further downstream of the flame front of the burners B and C must be observed.
  • FIGS. 7-9 are used simultaneously with FIG. 6. Furthermore, in order not to make FIG. 6 unnecessarily confusing, the guide plates 21a, 21b shown schematically according to FIGS. 7-9 have only been hinted at in it. In the following, the description of FIG. 6 will optionally refer to the remaining FIGS. 7-9 as required.
  • the burner B / C according to FIG. 6, which can be both a pilot burner C and a main burner B in terms of structure, consists of two half-hollow partial cone bodies 1, 2 which are offset from one another.
  • the offset of the respective central axis 1b, 2b of the partial cone bodies 1, 2 to each other creates a tangential air inlet slot 19, 20 on both sides in a mirror-image arrangement (FIGS. 7-9), through which the combustion air 15 enters the interior of the burner, ie flows into the cone cavity 14.
  • the two partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a which is also analogous to that Partial cone bodies 1, 2 run offset from one another, so that the tangential air inlet slots 19, 20 are present from the beginning.
  • a nozzle 3 is accommodated, the fuel injection 4 of which coincides with the narrowest cross section of the conical cavity 14 formed by the two partial cone bodies 1, 2.
  • the size of this nozzle 3 depends on the type of burner, ie whether it is a pilot burner C or main burner B. Of course, the burner can be made purely conical, that is to say without cylindrical starting parts 1a, 2a.
  • Both partial cone bodies 1, 2 each have a fuel line 8, 9, which are provided with openings 17 through which the gaseous fuel 13, which is mixed with the combustion air 15 flowing through the tangential air inlet slots 19, 20.
  • the position of these fuel lines 8, 9 are provided at the end of the tangential air inlet slots 19, 20, so that the admixture 16 of this fuel 13 with the inflowing combustion air 15 also takes place there.
  • the burner B / C has a plate which forms the front wall 10.
  • the liquid fuel 12 flowing through the nozzle 3 is injected into the cone cavity 14 at an acute angle such that a cone-shaped fuel spray which is as homogeneous as possible occurs in the burner outlet plane.
  • the fuel injector 4 can be an air-assisted nozzle or a pressure atomizer.
  • it can also be a dual burner with gaseous and liquid fuel supply, as is described, for example, in EP-A1 210 462.
  • the conical liquid fuel profile 5 from the nozzle 3 is enclosed by a rotating combustion air stream 15 flowing in tangentially.
  • the concentration of the liquid fuel 12 is continuously reduced in the direction by the mixed-in combustion air 15. If gaseous fuel 13/16 is burned, the mixture is formed with the combustion air 15 directly at the end of the air inlet slots 19, 20.
  • the optimal, homogeneous fuel concentration is in the area of the vortex bursting, that is to say in the area of the backflow zone 6 reached the cross section.
  • the ignition takes place at the top of the return flow zone 6. Only at this point can a stable flame front 7 arise.
  • the nitrogen oxide and carbon monoxide emissions are low if the excess air is at least 60%, which is one of them additional precaution to minimize NO x emissions is available.
  • the pollutant emission values are lowest. The same also applies to near-stoichiometric operation when the excess air is replaced by recirculating exhaust gas.
  • the design of the burner is particularly suitable for changing the size of the tangential air inlet slots 19, 20 for a given overall length of the burner by fixing the partial cone bodies 1, 2 to the end plate 10 by means of a releasable connection.
  • the distance between the two central axes 1b, 2b decreases or increases as a result of radial displacement of the two partial cone bodies 1, 2 to and from one another, and the gap size of the tangential air inlet slots 19, 20 changes accordingly, as is particularly well shown in FIGS. 7-9 emerges.
  • the partial cone bodies 1, 2 can also be displaced relative to one another in another plane, as a result of which even an overlap thereof can be controlled.
  • 7-9 also shows the position of the guide plates 21a, 21b. They have flow introduction functions, whereby, depending on their length, they extend the respective end of the partial cone bodies 1 and 2 in the flow direction of the combustion air 15.
  • the channeling of the combustion air into the cone cavity 14 can be optimized by opening or closing the guide plates 21a, 21b about the pivot point 23, in particular this is necessary if the original gap size of the tangential air inlet slots 19, 20 is changed.
  • the burner can also be operated without baffles.

Abstract

In a combustion chamber (A) having the shape of an annular combustion chamber, a series of large and small premix burners (B, C) is arranged along the annular front wall (10). The large premix burners (B), which are the main burners of the combustion chamber (A), and the small premix burners (C), which are the pilot burners of the combustion chamber (A), follow each other in alternating sequence and regularly along the front wall (10), where they also open into the combustion space of the combustion chamber (A). A plurality of air nozzles (D) are positioned between the large premix burners (B) and the small premix burners (C), their injection being directed into the combustion space of the combustion chamber (A). <IMAGE>

Description

Technisches GebietTechnical field

Die vorliegende Erfindung betrifft eine Brennkammer gemäss Oberbegriff des Anspruchs 1.The present invention relates to a combustion chamber according to the preamble of claim 1.

Stand der TechnikState of the art

Im Hinblick auf die vorgeschriebenen, extrem niedrige NOx-­Emissionen beim Betrieb einer Gasturbine gehen viele Hersteller dazu über, Vormischbrenner einzusetzen. Einer der Nachteile von Vormischbrennern besteht darin, dass sie bereits bei sehr niedrigen Luftzahlen, je nach Temperatur nach dem Verdichter der Gasturbine bei einer von ca. 2, löschen. Aus diesem Grund müssen solche Vormischbrenner im Teillastbetrieb einer Gasturbine von einem oder mehreren Pilotbrennern gestützt werden. In der Regel werden hierfür Diffussionsbrenner eingesetzt. Diese Technik ermöglicht zwar sehr niedrige Nox-Emissionen im Bereich der Vollast. Demgegenüber führt dieses Stützbrennersystem bei Teillast­ betrieb zu wesentlich höheren NOx-Emissionen. Der ver­schiedentlich bekannt gewordene Versuch, die Diffusions-­Stützbrenner magerer zu fahren oder kleinere Stützbrenner zu verwenden, muss daran scheitern, weil sich der Ausbrand verschlechtert und die C0/UHC-Emissionen sehr stark ansteigen. In der Fachsprache ist dieser Zustand unter der Bezeichnung CO/UHC-NOx-Schere bekannt geworden.With regard to the prescribed, extremely low NO x emissions when operating a gas turbine, many manufacturers are adopting premix burners. One of the disadvantages of premix burners is that they extinguish at very low air numbers, depending on the temperature of the compressor of the gas turbine, at around 2. For this reason, such premix burners must be supported by one or more pilot burners in the partial load operation of a gas turbine. Diffusion burners are usually used for this. This technology enables very low No x emissions in the area of full load. In contrast, this auxiliary burner system leads at partial load operation at significantly higher NO x emissions. The attempt, which has become known variously, to run the diffusion auxiliary burners leaner or to use smaller auxiliary burners must fail because the burnout deteriorates and the C0 / UHC emissions increase very sharply. In technical terms, this condition is known as CO / UHC-NO x scissors.

Aufgabe der ErfindungObject of the invention

Hier will die Erfindung Abhilfe schaffen. Der Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, liegt die Aufgabe zugrunde, eine Brennkammer bereitzustellen, welche bei minimierten Abgasemissionen einen breiten Betriebsbereich ermöglicht, unter Optimierung des Quali­tätsfaktors für das Temperaturprofil am Turbineneintritt, in der Fachsprache "Pattern Factor" benannt.The invention seeks to remedy this. The invention, as characterized in the claims, is based on the object of providing a combustion chamber which, with minimized exhaust gas emissions, enables a wide operating range, while optimizing the quality factor for the temperature profile at the turbine inlet, in the technical term "pattern factor".

Dazu wird entlang der ganzen Frontwand der Brennkammer vorgesehen, abwechslungsweise einen grossen und einen kleinen Vormischbrenner zu plazieren, d.h. zwischen zwei grossen Vormischbrennern ist jeweils ein kleiner Vormischbrenner zu finden. Des weiteren werden jeweils zwischen einem grossen und einen kleinen Vormischbrenner Luftdüsen vorgesehen, welche einen gewissen Luftanteil in den Brennraum einbringen. Diese Konfiguration ist für eine Ringbrennkammer optimal, wobei hier, demgemäss, die Front­wand dann ringförmig ist.For this purpose, it is provided along the entire front wall of the combustion chamber to alternately place a large and a small premix burner, i.e. A small premix burner can be found between two large premix burners. Furthermore, air nozzles are provided between a large and a small premix burner, which bring a certain amount of air into the combustion chamber. This configuration is optimal for an annular combustion chamber, with the front wall then being annular.

Die grossen Vormischbrenner, im folgenden Hauptbrenner ge­nannt, stehen zu den kleinen Vormischbrennern, im folgenden Pilotbrenner genannt, bezüglich der dort durchströmtenThe large premix burners, hereinafter referred to as main burners, are related to the small premix burners, hereinafter referred to as pilot burners, with regard to the flow through them

Brennerluft in einem Grössenverhältnis, das fallweise fest­gelegt wird. Im gesamten Lastbereich der Brennkammer ar­beiten die Pilotbrenner als selbstgängige Vormischbrenner, wobei die Luftzahl fast konstant bleibt. Weil nun die Pi­lotbrenner im ganzen Lastbereich bei idealem Gemisch (Vormischbrenner) gefahren werden können, sind die NOx-­Emissionen auch bei Teillast sehr gering. Es zeigt sich darüber hinaus, dass im Interesse eines "Uprating"-Poten­tials für Gasturbinen mit höheren Turbinenein­trittstemperaturen der Anteil der Luft, der nicht durch die Brenner gebildet werden kann (Lean Blowoff Limit, CO/UHC), nicht, wegen des Pattern Factors, ausschliesslich für Kühl­zwecke verwendet werden sollte. Über die hier vorgesehenen Luftdüsen wird ein gewisser Luftanteil vorzugsweise nach der Primärverbrennungszone des Brennraumes eingebracht, und dort wird dafür gesorgt, dass eine perfekte Einmischung zu­standekommt. Dies hat den Vorteil, dass der Luftanteil, der ein "Uprating" gewährleistet und der demnach direkt in die sekundäre Verbrennungszone geblasen wird, die unerwünschte "Ausmagerung" der Primärzone verhindert. Da sich die Luft­düsen an einer Stelle mit sehr kleiner Luftgeschwindigkeit befinden und ohnehin nur eine beschränkte Breite der Front­wand einnehmen, ist ihr Einfluss auf das Hauptströmungsfeld im Primärbereich nur sehr schwach. Im besonderen führen die Luftdüsen nicht zu einer Beeinträchtigung der Querzündung zwischen Primärbrennern und Hauptbrennern. Ein weiterer Vorteil dieser Luftdüsen ergibt sich aus ihrer Stellung auf der Frontwand; dort würde diese Zone ohne die kühlende Wirkung der Luftdüsen sehr heiss werden. Der Hauptvorteil dieser Luftdüsen ist indessen darin zu sehen, dass die zwischen Hauptbrennern und Pilotbrennern auftretenden Scherschichten stabilisiert werden. Aus diesem Grund wird das "Lean Stability Limit" der Brennkammer, bei welchem nur die Pilotbrenner selbstgängig brennen, duch die Luftdüsen entscheidend verbessert.Burner air in a size ratio that is determined on a case-by-case basis. The pilot burners work as independent premix burners in the entire load range of the combustion chamber, with the air ratio remaining almost constant. Because the pilot burners can now be operated in the entire load range with an ideal mixture (premix burner), the NO x emissions are very low even at partial load. It also shows that, in the interest of "up-prizing" potential for gas turbines with higher turbine inlet temperatures, the proportion of air that cannot be formed by the burners (lean blowoff limit, CO / UHC) is not, because of the pattern factor, should only be used for cooling purposes. A certain proportion of air is introduced via the air nozzles provided here, preferably after the primary combustion zone of the combustion chamber, and there it is ensured that perfect mixing takes place. This has the advantage that the proportion of air that ensures "up-rating" and is therefore blown directly into the secondary combustion zone prevents the undesirable "thinning" of the primary zone. Since the air nozzles are located at a point with a very low air velocity and only occupy a limited width of the front wall, their influence on the main flow field in the primary area is only very weak. In particular, the air nozzles do not interfere with the cross-ignition between primary burners and main burners. Another advantage of these air nozzles results from their position on the front wall; this zone would become very hot there without the cooling effect of the air jets. The main advantage of these air nozzles, however, can be seen in the fact that the shear layers occurring between main burners and pilot burners are stabilized. For this reason the "Lean Stability Limit" of the combustion chamber, at which only the pilot burners burn independently, significantly improved by the air nozzles.

Eine vorteilhafte Ausgestaltung der Erfindung wird dann er­zielt, wenn die Hauptbrenner und die Pilotbrenner aus unterschiedlich grossen sogenannten Doppelkegelbrennern bestehen, und wenn diese in eine Ringbrennkammer integriert sind. Weil bei einer solchen Konstellation die umlaufenden Stromlinien in der Ringbrennkammer sehr nahe an die Wirbelzentren der Pilotbrenner herankommen, ist eine Zün­dung nur mit diesen Pilotbrennern möglich. Beim Hochfahren wird die Brennstoffmenge, die über die Pilotbrenner zuge­führt wird, soweit gesteigert bis die Pilotbrenner ange­steuert sind, d.h. bis die volle Brennstoffmenge zur Verfü­gung steht. Die Konfiguration wird so gewählt, dass dieser Punkt der Lastabwurfbedingung der Gasturbine entspricht. Die weitere Leistungssteigerung erfolgt dann über die Hauptbrenner. Bei der Spitzenlast der Anlage sind auch die Hauptbrenner voll angesteuert. Weil die Konfiguration "kleine" heisse Wirbelzentren (Pilotbrenner) zwischen grossen kühleren Wirbelzentren (Hauptbrenner) extrem insta­bil ist, wird auch bei mager betriebenen Hauptbrennern im Teillastbereich ein sehr guter Ausbrand mit niedrigen CO/UHC-Emissionen erreicht, d.h. die heissen Wirbel der Pi­lotbrenner dringen sofort in die kalten Wirbel der Haupt­brenner ein.An advantageous embodiment of the invention is achieved if the main burners and the pilot burners consist of so-called double-cone burners of different sizes, and if these are integrated in an annular combustion chamber. Because the circulating streamlines in the annular combustion chamber come very close to the vortex centers of the pilot burners in such a constellation, ignition is only possible with these pilot burners. When starting up, the amount of fuel that is supplied via the pilot burner is increased until the pilot burner is activated, i.e. until the full amount of fuel is available. The configuration is chosen so that this point corresponds to the load shedding condition of the gas turbine. The further increase in output then takes place via the main burner. The main burners are also fully controlled at the peak load of the system. Because the configuration of "small" hot vortex centers (pilot burner) between large, cooler vortex centers (main burner) is extremely unstable, very good burnout with low CO / UHC emissions is achieved even with lean operated main burners in the partial load range, i.e. the hot eddies of the pilot burner immediately penetrate the cold eddies of the main burner.

Vorteilhafte zweckmässige Weiterbildungen der erfindungsgemässen Aufgabenlösung sind in den weiteren ab­hängigen Ansprüchen gekennzeichnet.Advantageous expedient developments of the task solution according to the invention are characterized in the further dependent claims.

Im folgenden werden anhand der Zeichnung Ausführungs­beispiele der Erfindung näher erläutert. Alle für das un­ mittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind fortgelassen. In den verschiedenen Figuren sind gleiche Elemente jeweils mit den gleichen Bezugs­zeichen versehen. Die Strömungsrichtung der Medien ist mit Pfeilen gekennzeichnet.Exemplary embodiments of the invention are explained in more detail below with reference to the drawing. All for the un indirect understanding of the invention not necessary elements are omitted. In the different figures, the same elements are each provided with the same reference symbols. The flow direction of the media is marked with arrows.

Kurze Beschreibung der FigurenBrief description of the figures

Es zeigt:

  • Fig.1 eine schematische Aufsicht auf einen Teil der Frontwand einer Ringbrennkammer, mit ebenfalls schematisch dargestellten Primär-, Hauptbrennern sowie Luftdüsen,
  • Fig.2 einen schematischen Schnitt durch eine Ringbrennkammer in der Ebene eines Hauptbrenners,
  • Fig.3 einen weiteren Schnitt durch eine Ringbrennkammer in der Ebene eines Pilotbrenners,
  • Fig.4 einen schematischen Axial-Schnitt durch einen Brenner,
  • Fig.5 einen schematischen Axial-Schnitt im Bereich der Luftdüsen,
  • Fig.6 einen Brenner in der Ausführung als Doppelkegelbrenner in perspektivischer Darstel­lung, entsprechend aufgeschnitten,
  • Fig.7,8,9 entsprechende Schnitte durch die Ebenen VII-VII (Fig.7), VIII-VIII (Fig. 8) und IX-IX (Fig.9), wobei diese Schnitte nur eine schematische, ver­einfachte Darstellung des Doppelkegelbrenners gemäss Fig. 6 sind.
It shows:
  • 1 shows a schematic view of part of the front wall of an annular combustion chamber, with primary, main burners and air nozzles also shown schematically,
  • 2 shows a schematic section through an annular combustion chamber in the plane of a main burner,
  • 3 shows a further section through an annular combustion chamber in the plane of a pilot burner,
  • 4 shows a schematic axial section through a burner,
  • 5 shows a schematic axial section in the area of the air nozzles,
  • 6 a burner in the design as a double-cone burner in a perspective view, cut open accordingly,
  • Fig. 7,8,9 corresponding sections through the levels VII-VII (Fig. 7), VIII-VIII (Fig. 8) and IX-IX (Fig. 9), these sections being only a schematic, simplified representation of the double-cone burner 6 are.

Beschreibung der AusführungsbeispieleDescription of the embodiments

Fig.1 zeigt einen Ausschnitt eines Sektors der Frontwand 10. Daraus geht die Plazierung der einzelnen Hauptbrenner B und Pilotbrenner C hervor. Diese sind auf den Umfang der Ringbrennkammer A gleichmässig und abwechslungsweise verteilt. Der dargestellte Grössenunterschied zwischen Hauptbrennern B und Pilotbrennern C ist nur von qualita­tiver Natur. Die effektive Grösse der einzelnen Brenner sowie deren Verteilung und Anzahl auf den Umfang der Front­wand 10 der Ringbrennkammer A richtet sich, wie bereits vorne dargelegt, nach der Leistung und Grösse der Brennkam­mer selbst. Die Hauptbrenner B und Pilotbrenner C, die ab­wechslungsweise angeordnet sind, münden alle auf gleicher Höhe in eine einheitliche ringförmige Frontwand 10, welche die Eintrittsfläche der Ringbrennkammer A bildet. Zwischen den einzelnen Brennern B, C sind jeweils eine An­zahl Luftdüsen D, hier in schematischer Darstellung, vorge­sehen, welche in radialer Richtung etwa die halbe Breite der Frontwand 10 einnehmen. Wenn die Hauptbrenner B und Pi­lotbrenner C gleichläufige Wirbel erzeugen, entsteht ober­halb und unterhalb derselben eine umlaufende, die Brenner B und C umschliessende Strömung. Zur Erklärung dieses Zu­standes sei vergleichsweise auf ein endloses Förderband hingewiesen, dass durch gleichsinnige Rollen in Bewegung gehalten wird. Die Rolle der Rollen wird hier durch die gleichläufigen Brenner übernommen. Um den jeweiligen Bren­ner entsteht überdies ein Wirbelzentrum; um die Pilotbren­ner C sind die Wirbelzentren klein und heiss, und an sich instabil. Diese kommen zwischen den grossen kühleren, von den Hauptbrennern B stammenden Wirbelzentren zu stehen. In diesem Bereich zwischen den kleinen heissen und grossen kühleren Wirbelzentren wirken die Luftdüsen F, welche die Stabilisierung der beiden entscheidend verbessern, wie dies vorne bereits gewürdigt wurde. Selbst wenn die Hauptbrenner B mager betrieben werden, wie dies im Teillastbetrieb der Fall ist, ist mit einem sehr guten Ausbrand mit niedrigen CO/UHC-Emmissionen zu rechnen.1 shows a section of a sector of the front wall 10. This shows the placement of the individual main burners B and pilot burners C. These are evenly and alternately distributed over the circumference of the annular combustion chamber A. The size difference shown between main burners B and pilot burners C is only of a qualitative nature. The effective size of the individual burners and their distribution and number on the circumference of the front wall 10 of the annular combustion chamber A, as already explained above, depends on the power and size of the combustion chamber itself. The main burners B and pilot burners C, which are arranged alternately, open out all at the same height in a uniform annular front wall 10, which forms the entry surface of the annular combustion chamber A. Between the individual burners B, C, a number of air nozzles D, here in a schematic representation, are provided, which occupy approximately half the width of the front wall 10 in the radial direction. When the main burners B and pilot burners C produce co-rotating vortices, a circulating flow that surrounds the burners B and C is created above and below them. To explain this condition, we would like to refer to an endless conveyor belt that is kept in motion by rollers moving in the same direction. The role of the roles is here through the co-rotating burner taken over. A vortex center is also created around the respective burner; around the pilot burner C, the vortex centers are small and hot, and inherently unstable. These come to rest between the large, cooler vortex centers originating from the main burners B. In this area between the small hot and large cooler vortex centers, the air nozzles F act, which decisively improve the stabilization of the two, as has already been appreciated in the foregoing. Even if the main burners B are operated lean, as is the case in part-load operation, a very good burnout with low CO / UHC emissions can be expected.

Fig. 2 und 3 zeigen einen schematischen Schnitt durch eine Ringbrennkammer A, jeweils in der Ebene eines Pilotbrenners C resp. eines Hauptbrenners B. Die hier dargestellte Ringbrennkammer A verläuft Richtung Turbineneintritt D konisch aus, wie aus der gezeigten Mittelachse E der Ring­brennkammer A hervorgeht. Jedem Brenner B, C ist eine indi­viduelle Düse 3 zugeteilt. Schon aus dieser schematischen Darstellung ist zu erkennen, dass die Brenner B, C zugleich Vormischbrenner sind, also ohne der sonst üblichen Vormischzone auskommen. Freilich müssen diese Vormischbren­ner B, C, unabhängig ihrer spezifischen Konzeption, so aus­gelegt sein, dass eine Rückzündung in die Vormischzone über die jeweiligen Frontpanel 10 nicht zu befürchten ist. Ein Vormischbrenner, der diese Bedingung vorzüglich erfüllt, wird umfassend in den Fig.6 - 9 dargestellt und dort näher erläutert, wobei der Aufbau für beide Brennerarten (Hauptbrenner B/Pilotbrenner C) gleich sein kann, lediglich deren Grösse wird verschieden sein. Bei einer Ringbrenn­kammer A mittlerer Grösse wird das Grössenverhältnis zwi­schen Hauptbrenner B und Pilotbrenner C so gewählt, dass etwa 23 % der Brennerluft durch die Pilotbrenner C und etwa 77 % durch die Hauptbrenner B strömen.2 and 3 show a schematic section through an annular combustion chamber A, respectively in the plane of a pilot burner C and. of a main burner B. The annular combustion chamber A shown here is tapered in the direction of the turbine inlet D, as can be seen from the central axis E of the annular combustion chamber A shown. An individual nozzle 3 is allocated to each burner B, C. Already from this schematic representation it can be seen that the burners B, C are at the same time premix burners, that is to say they do without the otherwise usual premix zone. Of course, these premix burners B, C, regardless of their specific design, must be designed in such a way that there is no fear of re-ignition into the premix zone via the respective front panel 10. A premix burner which excellently fulfills this condition is shown comprehensively in FIGS. 6-9 and explained in more detail there, the structure being able to be the same for both burner types (main burner B / pilot burner C), only their size will be different. In the case of an annular combustion chamber A of medium size, the size ratio between main burner B and pilot burner C is selected such that about 23% of the burner air flows through the pilot burner C and about 77% through the main burner B.

Fig. 4 und 5 zeigen schematisch einen Hauptbrenner B, gemäss Schnitt IV-IV aus Fig. 1, und die Luftdüsen F, gemäss Schnitt V-V aus Fig. 1, in einem lagemässig koor­dinierten achsialen Schnitt. Zu beachten in diesem Zusam­menhang ist die bezüglich Frontwand 10 weit in den Brenn­raum hineinragende Aufbaute für die Luftdüsen F zu beachten, welche bewirkt, dass die Luftein den Brennraum weiter stromabwärts gegenüber der Flammenfront der Brenner B und C einwirkt.4 and 5 schematically show a main burner B, according to section IV-IV from FIG. 1, and the air nozzles F, according to section V-V from FIG. 1, in a positionally coordinated axial section. In this connection, the structure for the air nozzles F which extends far into the combustion chamber with respect to the front wall 10 and which causes the air to act further downstream of the flame front of the burners B and C must be observed.

Um den Aufbau des Brenners B/C besser zu verstehen, ist es von Vorteil, wenn gleichzeitig zu Fig. 6 die einzelnen Schnitte nach Fig. 7 - 9 herangezogen werden. Des weiteren, um Fig. 6 nicht unnötig unübersichtlich zu gestalten, sind in ihr die nach Fig. 7 - 9 schematisch gezeigten Leitbleche 21a, 21b nur andeutungsweise aufgenommen worden. Im folgen­den werden auch bei der Beschreibung von Fig. 6 wahlweise, nach Bedarf, auf die restlichen Fig. 7 - 9 hingewiesen.In order to better understand the structure of the burner B / C, it is advantageous if the individual sections according to FIGS. 7-9 are used simultaneously with FIG. 6. Furthermore, in order not to make FIG. 6 unnecessarily confusing, the guide plates 21a, 21b shown schematically according to FIGS. 7-9 have only been hinted at in it. In the following, the description of FIG. 6 will optionally refer to the remaining FIGS. 7-9 as required.

Der Brenner B/C gemäss Fig.6, der vom Aufbau her sowohl Pilotbrenner C als auch Hauptbrenner B sein kann, besteht aus zwei halben hohlen Teilkegelkörpern 1, 2, die versetzt zueinander aufeinander liegen. Die Versetzung der jeweili­gen Mittelachse 1b, 2b der Teilkegelkörper 1, 2 zueinander schafft auf beiden Seiten in spiegelbildlicher Anordnung jeweils einen tangentialen Lufteintrittsschlitz 19, 20 frei, (Fig. 7 - 9), durch welche die Verbrennungsluft 15 in den Innenraum des Brenners, d.h. in den Kegelhohlraum 14 strömt. Die beiden Teilkegelkörper 1, 2 haben je einen zylindrischen Anfangsteil 1a, 2a die ebenfalls analog den Teilkegelkörpern 1, 2 versetzt zueinander verlaufen, so dass die tangentialen Lufteintrittsschlitze 19, 20 vom An­fang an vorhanden sind. In diesem zylindrischen Anfangsteil 1a, 2a ist eine Düse 3 untergebracht, deren Brenn­stoffeindüsung 4 mit dem engsten Querschnitt des durch die zwei Teilkegelkörper 1, 2 gebildeten kegeligen Hohlraumes 14 zusammenfällt. Die Grösse dieser Düse 3 richtet sich nach der Art des Brenners, d.h., ob es sich um einen Pilot­brenner C oder Hauptbrenner B handelt. Selbstverständlich kann der Brenner rein kegelig, also ohne zylindrische An­fangsteile 1a, 2a, ausgeführt sein. Beide Teilkegelkörper 1, 2 weisen je eine Brennstoffleitung 8, 9 auf, die mit Öffnungen 17 versehen sind, durch welche der gasförmige Brennstoff 13, der durch die tangentialen Lufteintritts­schlitze 19, 20 strömenden Verbrennungsluft 15 zugemischt wird. Die Lage dieser Brennstoffleitungen 8, 9 sind am Ende der tangentialen Lufteintrittsschlitze 19, 20 angebracht, so dass dort auch die Zumischung 16 dieses Brennstoffes 13 mit der einströmenden Verbrennungsluft 15 stattfindet. Brennraumseitig 22 weist der Brenner B/C eine Platte auf, welche die Frontwand 10 bildet. Der durch die Düse 3 strö­mende flüssigen Brennstoff 12 wird in einem spitzen Winkel in den Kegelhohlraum 14 eingedüst, dergestalt, dass sich in der Brenneraustrittsebene ein möglichst homogener kegeliger Brennstoffspray einstellt. Bei der Brennstoffeindüsung 4 kann es sich um eine Luftunterstützte Düse oder um einen Druckzerstäuber handeln. Selbstverständlich kann es sich, bei gewissen Betriebsarten der Brennkammer, auch um einen Dualbrenner mit gasförmiger und flüssiger Brennstoff­zuführung, wie dies beispielsweise in EP-A1 210 462 beschrieben wird. Das kegelige Flüssigbrennstoffprofil 5 aus Düse 3 wird von einem tangential einströmenden rotierenden Verbrennungsluftstrom 15 umschlossen. In axia­ ler Richtung wird die Konzentration des flüssigen Brennstoffes 12 fortlaufend durch die eingemischte Verbren­nungsluft 15 abgebaut. Wird gasförmiger Brennstoff 13/16 verbrannt, geschieht die Gemischbildung mit der Verbren­nungsluft 15 direkt am Ende der Lufteintrittsschlitze 19, 20. Bei der Eindüsung des flüssigen Brennstoffs 12 wird im Bereich des Wirbelaufplatzens, also im Bereich der Rück­strömzone 6, die optimale, homogene Brennstoffkonzentration über den Querschnitt erreicht. Die Zündung erfolgt an der Spitze der Rückströmzone 6. Erst an dieser Stelle kann eine stabile Flammenfront 7 entstehen. Ein Rückschlag der Flamme ins Innere des Brenners, wie dies bei bekannten Vormischstrecken latent der Fall ist, wogegen dort mit kom­plizierten Flammenhaltern Abhilfe gesucht wird, ist hier nicht zu befürchten. Ist die Verbrennungsluft 15 vorge­heizt, so stellt sich eine natürliche Verdampfung des flüssigen Brennstoffes 12 ein, bevor der Punkt am Ausgang des Brenners erreicht ist, an dem die Zündung des Gemisches stattfinden kann. Der Grad der Verdampfung ist selbstver­ständlich von der Grösse des Brenners, der Tropfengrössen­verteilungn bei flüssigem Brennstoff und der Temperatur der Verbrennungsluft 15 abhängig. Unabhängig aber davon, ob neben einer homogenen Tropfenmischung durch Verbren­nungsluft 15 niedriger Temperatur oder zusätzlich nur eine partielle oder die vollständige Tropfenverdampfung durch vorgeheizte Verbrennungsluft 15 erreicht wird, fallen die Stickoxid- und Kohlenmonoxidemissionen niedrig aus, wenn der Luftüberschuss mindestens 60 % beträgt, womit hier eine zusätzliche Vorkehrung zur Minimierung der NOx-Emissionen zur Verfügung steht. Im Falle der vollständigen Verdampfung vor dem Eintritt in die Verbrennungszone sind die Schad­stoffemissionswerte am niedrigsten. Gleiches gilt auch für den nahstöchiometrischen Betrieb, wenn die Überschussluft durch rezirkulierendes Abgas ersetzt wird. Bei der Gestal­tung der Teilkegelkörper 1, 2 hinsichtlich Kegelneigung und der Breite der tangentialen Lufteintrittsschlitze 19, 20 sind enge Grenzen einzuhalten, damit sich das gewünschte Strömungsfeld der Luft mit ihrer Rückströmzone 6 im Bereich der Brennermündung zur Flammenstabilisierung einstellt. Allgemein ist zu sagen, dass eine Verkleinerung der Lufteintrittsschlitze 19, 20 die Rückströmzone 6 weiter stromaufwärts verschiebt, wodurch dann allerdings das Gemisch früher zur Zündung käme. Immerhin ist hier zu festzustellen, dass die einmal geometrisch fixierte Rück­strömzone 6 an sich positionsstabil ist, denn die Drallzahl nimmt in Strömungsrichtung im Bereich der Kegelform des Brenners zu. Die Konstruktion des Brenners eignet sich vorzüglich, bei vorgegebener Baulänge des Brenners, die Grösse der tangentialen Lufteintrittsschlitze 19, 20 zu verändern, indem die Teilkegelkörper 1, 2 anhand einer lös­baren Verbindung mit der Abschlussplatte 10 fixiert sind. Durch radiale Verschiebung der beiden Teilkegelkörper 1, 2 zu- oder auseinander verkleinert bzw. vergrössert sich der Abstand der beiden Mittelachsen 1b, 2b, und dementsprechend verändert sich die Spaltgrösse der tangentialen Luftein­trittsschlitze 19, 20, wie dies aus Fig. 7 - 9 besonders gut hervorgeht. Selsbtverständlich sind die Teilkegelkörper 1, 2 auch in einer anderen Ebene zueinander verschiebbar, wodurch sogar eine Überlappung derselben angesteuert werden kann. Ja, es ist sogar möglich, die Teilkegelkörper 1, 2 durch eine gegenläufige drehende Bewegung spiralartig einander zu verschieben. Somit hat man es in der Hand, die Form und die Grösse der tangentialen Lufteintritte 19, 20 beliebig zu variieren, womit der Brenner ohne Veränderung seiner Baulänge individuell angepasst werden kann.The burner B / C according to FIG. 6, which can be both a pilot burner C and a main burner B in terms of structure, consists of two half-hollow partial cone bodies 1, 2 which are offset from one another. The offset of the respective central axis 1b, 2b of the partial cone bodies 1, 2 to each other creates a tangential air inlet slot 19, 20 on both sides in a mirror-image arrangement (FIGS. 7-9), through which the combustion air 15 enters the interior of the burner, ie flows into the cone cavity 14. The two partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a which is also analogous to that Partial cone bodies 1, 2 run offset from one another, so that the tangential air inlet slots 19, 20 are present from the beginning. In this cylindrical initial part 1a, 2a, a nozzle 3 is accommodated, the fuel injection 4 of which coincides with the narrowest cross section of the conical cavity 14 formed by the two partial cone bodies 1, 2. The size of this nozzle 3 depends on the type of burner, ie whether it is a pilot burner C or main burner B. Of course, the burner can be made purely conical, that is to say without cylindrical starting parts 1a, 2a. Both partial cone bodies 1, 2 each have a fuel line 8, 9, which are provided with openings 17 through which the gaseous fuel 13, which is mixed with the combustion air 15 flowing through the tangential air inlet slots 19, 20. The position of these fuel lines 8, 9 are provided at the end of the tangential air inlet slots 19, 20, so that the admixture 16 of this fuel 13 with the inflowing combustion air 15 also takes place there. On the combustion chamber side 22, the burner B / C has a plate which forms the front wall 10. The liquid fuel 12 flowing through the nozzle 3 is injected into the cone cavity 14 at an acute angle such that a cone-shaped fuel spray which is as homogeneous as possible occurs in the burner outlet plane. The fuel injector 4 can be an air-assisted nozzle or a pressure atomizer. Of course, in certain operating modes of the combustion chamber, it can also be a dual burner with gaseous and liquid fuel supply, as is described, for example, in EP-A1 210 462. The conical liquid fuel profile 5 from the nozzle 3 is enclosed by a rotating combustion air stream 15 flowing in tangentially. In axia The concentration of the liquid fuel 12 is continuously reduced in the direction by the mixed-in combustion air 15. If gaseous fuel 13/16 is burned, the mixture is formed with the combustion air 15 directly at the end of the air inlet slots 19, 20. When the liquid fuel 12 is injected, the optimal, homogeneous fuel concentration is in the area of the vortex bursting, that is to say in the area of the backflow zone 6 reached the cross section. The ignition takes place at the top of the return flow zone 6. Only at this point can a stable flame front 7 arise. A flashback of the flame into the interior of the burner, as is latently the case with known premixing sections, while there is a remedy with complicated flame holders, there is no fear here. If the combustion air 15 is preheated, natural evaporation of the liquid fuel 12 occurs before the point at the burner outlet at which the ignition of the mixture can take place is reached. The degree of evaporation is of course dependent on the size of the burner, the drop size distribution in the case of liquid fuel and the temperature of the combustion air 15. Regardless of whether, in addition to a homogeneous drop mixture through combustion air 15 at low temperature or additionally only partial or complete drop evaporation through preheated combustion air 15, the nitrogen oxide and carbon monoxide emissions are low if the excess air is at least 60%, which is one of them additional precaution to minimize NO x emissions is available. In the case of complete evaporation before entering the combustion zone, the pollutant emission values are lowest. The same also applies to near-stoichiometric operation when the excess air is replaced by recirculating exhaust gas. When designing the partial cone bodies 1, 2 with regard to the taper inclination and the width of the tangential air inlet slots 19, 20, narrow limits must be observed so that the desired flow field of the air with its return flow zone 6 is established in the area of the burner mouth for flame stabilization. In general, it can be said that a reduction in the size of the air inlet slots 19, 20 shifts the backflow zone 6 further upstream, which would cause the mixture to ignite earlier, however. After all, it must be ascertained here that the backflow zone 6, which is once geometrically fixed, is inherently positionally stable, because the swirl number increases in the direction of flow in the region of the cone shape of the burner. The design of the burner is particularly suitable for changing the size of the tangential air inlet slots 19, 20 for a given overall length of the burner by fixing the partial cone bodies 1, 2 to the end plate 10 by means of a releasable connection. The distance between the two central axes 1b, 2b decreases or increases as a result of radial displacement of the two partial cone bodies 1, 2 to and from one another, and the gap size of the tangential air inlet slots 19, 20 changes accordingly, as is particularly well shown in FIGS. 7-9 emerges. Of course, the partial cone bodies 1, 2 can also be displaced relative to one another in another plane, as a result of which even an overlap thereof can be controlled. Yes, it is even possible to move the partial cone bodies 1, 2 spirally to one another by a counter-rotating movement. It is therefore in your hands to vary the shape and size of the tangential air inlets 19, 20 as desired, with which the burner can be individually adapted without changing its overall length.

Aus Fig. 7 - 9 geht auch die Lage der Leitbleche 21a, 21b hervor. Sie haben Strömungseinleitungsfunktionen, wobei sie, entsprechend ihrer Länge, das jeweilige Ende der Teilkegelkörper 1 und 2 in Anströmungsrichtung der Verbren­nungsluft 15 verlängern. Die Kanalisierung der Verbren­nungsluft in den Kegelhohlraum 14 kann durch Öffnung bzw. Schliessung der Leitbleche 21a, 21b um den Drehpunkt 23 op­timiert werden, insbesondere ist dies dann vonnöten, wenn die ursprüngliche Spaltgrösse der tangentialen Luftein­trittsschlitze 19, 20 verändert wird. Selbstverständlich kann der Brenner auch ohne Leitbleche betrieben werden.7-9 also shows the position of the guide plates 21a, 21b. They have flow introduction functions, whereby, depending on their length, they extend the respective end of the partial cone bodies 1 and 2 in the flow direction of the combustion air 15. The channeling of the combustion air into the cone cavity 14 can be optimized by opening or closing the guide plates 21a, 21b about the pivot point 23, in particular this is necessary if the original gap size of the tangential air inlet slots 19, 20 is changed. Of course, the burner can also be operated without baffles.

Claims (9)

1. Brennkammer einer Gasturbine, dadurch gekennzeichnet, dass die Brennkammer (A) brennerluftanströmungsseitig mit einer Anzahl Vormischbrenner (B, C) bestückt ist, die nebeneinander angeordnet und, bezüglich Durch­lasses der Brennerluft, unterschiedlich gross sind, wobei die grossen Vormischbrenner (B) und die kleinen Vormischbrenner (C) abwechslungsweise aufeinander fol­gen, und wobei zwischen den einzelnen Vormischbrennern (B, C) Luftdüsen (F) plaziert sind.1. Combustion chamber of a gas turbine, characterized in that the combustion chamber (A) is equipped on the burner air inflow side with a number of premix burners (B, C) which are arranged next to one another and, with respect to passage of the burner air, are of different sizes, the large premix burners (B) and the small premix burners (C) follow one another alternately, and air nozzles (F) are placed between the individual premix burners (B, C). 2. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die grossen Vormischbrenner (B) und die kleinen Vormischbrenner (C) drallgleich gerichtet sind.2. Combustion chamber according to claim 1, characterized in that the large premix burners (B) and the small premix burners (C) are directed in a swirling manner. 3. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die grossen Vormischbrenner (B) die Hauptbrenner, die kleinen Vormischbrenner (C) die Pilotbrenner der Brennkammer (A) sind.3. Combustion chamber according to claim 1, characterized in that the large premix burners (B) are the main burners, the small premix burners (C) are the pilot burners of the combustion chamber (A). 4. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Eindüsung der Luft über die Luftdüsen (D) in den Brennraum (22) der Brennkammer (A) gerichtet ist und weiter stromabwärts gegenüber der Frontwand (10) der Vormischbrenner (B, C) erfolgt.4. Combustion chamber according to claim 1, characterized in that the injection of the air via the air nozzles (D) is directed into the combustion chamber (22) of the combustion chamber (A) and further downstream relative to the front wall (10) of the premix burners (B, C) he follows. 5. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass der Vormischbrenner (B, C) aus mindestens zwei aufeinander positionierten hohlen Teilkegelkörpern (1, 2) mit in Strömungsrichtung zunehmender Kegelneigung besteht, deren Mittelachsen (1b, 2b) in Längsrichtung der Teilkegelkörper (1, 2) zueinander versetzt ver­laufen, wobei anströmungsseitig im durch die Teilkegelkörper (1, 2) gebildeten kegelhohlförmigen Innenraum (14) mindestens eine Brennstoffdüse (3) plaziert ist, deren Brennstoffeindüsung zwischen der zueinander versetzten Mittelachsen (1b, 2b) der Teilkegelkörper (1, 2) liegt, wobei die Versetzung der Mittelachsen (1b, 2b) zueiander ein Mass für die grösse der tangentialen Lufteintrittsschlitze (19, 20) zwischen den Teilkegelkörpern (1, 2) ist.5. Combustion chamber according to claim 1, characterized in that the premix burner (B, C) consists of at least two hollow partial cone bodies (1, 2) positioned one above the other with an increasing cone inclination in the direction of flow, the central axes (1b, 2b) of which in the longitudinal direction the partial cone body (1, 2) is offset from one another, at least one fuel nozzle (3) being placed on the inflow side in the conical hollow interior (14) formed by the partial cone body (1, 2), the fuel nozzle of which is injected between the offset central axes (1b, 2b) Partial cone body (1, 2), the offset of the central axes (1b, 2b) to each other is a measure of the size of the tangential air inlet slots (19, 20) between the partial cone bodies (1, 2). 6. Brennkammer nach Anspruch 5, dadurch gekennzeichnet, dass die Brennstoffdüse (3) mit einem flüssigen Brennstoff betreibbar ist.6. Combustion chamber according to claim 5, characterized in that the fuel nozzle (3) can be operated with a liquid fuel. 7. Brennkammer nach Anspruch 5, dadurch gekennzeichnet, dass im Bereich der tangentialen Lufteintrittsschlitze (19, 20) weitere Brennstoffdüsen (17) vorhanden sind.7. Combustion chamber according to claim 5, characterized in that in the region of the tangential air inlet slots (19, 20) there are further fuel nozzles (17). 8. Brennkammer nach Anspruch 7, dadurch gekennzeichnet, dass die Brennstoffdüsen (17) mit einem gasförmigen Brennstoff betreibbar sind.8. Combustion chamber according to claim 7, characterized in that the fuel nozzles (17) can be operated with a gaseous fuel. 9. Brennkammer nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, dass die Brennkammer (A) eine Ring­brennkammer ist, auf deren ringförmige Frontwand (10) die grossen Vormischbrenner (B), die kleinen Vormischbrenner (C) sowie die Luftdüsen (D) münden.9. Combustion chamber according to one of claims 1 to 8, characterized in that the combustion chamber (A) is an annular combustion chamber, on the annular front wall (10) of the large premix burners (B), the small premix burners (C) and the air nozzles (D) flow out.
EP90108684A 1989-06-06 1990-05-09 Gas turbine combustion chamber Expired - Lifetime EP0401529B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2099/89 1989-06-06
CH2099/89A CH680084A5 (en) 1989-06-06 1989-06-06

Publications (2)

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EP0401529A1 true EP0401529A1 (en) 1990-12-12
EP0401529B1 EP0401529B1 (en) 1994-06-29

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EP90108684A Expired - Lifetime EP0401529B1 (en) 1989-06-06 1990-05-09 Gas turbine combustion chamber

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US (1) US5154059A (en)
EP (1) EP0401529B1 (en)
JP (1) JP3075732B2 (en)
AT (1) ATE108011T1 (en)
CH (1) CH680084A5 (en)
DE (1) DE59006282D1 (en)
ES (1) ES2058667T3 (en)
HU (1) HUT56923A (en)
PL (1) PL165109B1 (en)
RU (1) RU2002165C1 (en)

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EP0481111A1 (en) * 1990-10-17 1992-04-22 Asea Brown Boveri Ag Gas-turbine combustion chamber
WO1992019915A1 (en) * 1991-04-30 1992-11-12 Rolls-Royce Plc Combustion chamber assembly in a gas turbine engine
FR2683891A1 (en) * 1991-11-20 1993-05-21 Snecma TURBOMACHINE COMPRISING A DEVICE FOR REDUCING THE EMISSION OF NITROGEN OXIDES.
US5400587A (en) * 1991-11-13 1995-03-28 Asea Brown Boveri Ltd. Gas turbine annular combustion chamber having radially displaced groups of oppositely swirling burners.
DE4412315A1 (en) * 1994-04-11 1995-10-12 Abb Management Ag Method of operating gas turbine combustion chamber
DE4429539A1 (en) * 1994-08-19 1996-02-22 Abb Management Ag Process for speed control of a gas turbine when shedding loads
DE4429757A1 (en) * 1994-08-22 1996-02-29 Abb Management Ag Two=stage combustion chamber
EP0751351A1 (en) * 1995-06-26 1997-01-02 Abb Research Ltd. Combustion chamber
WO2015122797A1 (en) 2014-02-12 2015-08-20 Otkrytoe Aktsionernoe Obshchestvo "Gazprom" Annular combustion chamber in a gas turbine engine and its operation method

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DE4411624A1 (en) * 1994-04-02 1995-10-05 Abb Management Ag Combustion chamber with premix burners
US5479773A (en) * 1994-10-13 1996-01-02 United Technologies Corporation Tangential air entry fuel nozzle
US5896739A (en) * 1996-12-20 1999-04-27 United Technologies Corporation Method of disgorging flames from a two stream tangential entry nozzle
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
DE19948674B4 (en) * 1999-10-08 2012-04-12 Alstom Combustion device, in particular for the drive of gas turbines
DE10000415A1 (en) * 2000-01-07 2001-09-06 Alstom Power Schweiz Ag Baden Method and device for suppressing flow vortices within a fluid power machine
DE10049203A1 (en) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Process for introducing fuel into a premix burner
US6360776B1 (en) 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
DE10205839B4 (en) * 2002-02-13 2011-08-11 Alstom Technology Ltd. Premix burner for reducing combustion-driven vibrations in combustion systems
DE10219354A1 (en) * 2002-04-30 2003-11-13 Rolls Royce Deutschland Gas turbine combustion chamber with targeted fuel introduction to improve the homogeneity of the fuel-air mixture
US6931853B2 (en) * 2002-11-19 2005-08-23 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
US7097448B2 (en) * 2004-05-07 2006-08-29 Peter Chesney Vortex type gas lamp
DE102007043626A1 (en) 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity
US8122725B2 (en) * 2007-11-01 2012-02-28 General Electric Company Methods and systems for operating gas turbine engines
FR2950109B1 (en) * 2009-09-17 2012-07-27 Turbomeca TURBOMOTEUR WITH PARALLEL TREES
WO2011085105A2 (en) 2010-01-06 2011-07-14 The Outdoor Greatroom Company Llp Fire container assembly
EP2685163B1 (en) 2012-07-10 2020-03-25 Ansaldo Energia Switzerland AG Premix burner of the multi-cone type for a gas turbine

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US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
GB2043868A (en) * 1979-03-08 1980-10-08 Rolls Royce Gas turbine
GB2072827A (en) * 1980-03-29 1981-10-07 Rolls Royce A tubo-annular combustion chamber
EP0210462A1 (en) * 1985-07-30 1987-02-04 BBC Brown Boveri AG Dual combustor

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US3267676A (en) * 1965-06-23 1966-08-23 Curtiss Wright Corp Fuel burner structure
DE2223093A1 (en) * 1972-05-12 1973-11-22 Gen Electric BURNER AND FUEL INJECTOR
US4058977A (en) * 1974-12-18 1977-11-22 United Technologies Corporation Low emission combustion chamber
GB2043868A (en) * 1979-03-08 1980-10-08 Rolls Royce Gas turbine
GB2072827A (en) * 1980-03-29 1981-10-07 Rolls Royce A tubo-annular combustion chamber
EP0210462A1 (en) * 1985-07-30 1987-02-04 BBC Brown Boveri AG Dual combustor

Cited By (17)

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Publication number Priority date Publication date Assignee Title
US5274993A (en) * 1990-10-17 1994-01-04 Asea Brown Boveri Ltd. Combustion chamber of a gas turbine including pilot burners having precombustion chambers
EP0481111A1 (en) * 1990-10-17 1992-04-22 Asea Brown Boveri Ag Gas-turbine combustion chamber
US5479774A (en) * 1991-04-30 1996-01-02 Rolls-Royce Plc Combustion chamber assembly in a gas turbine engine
WO1992019915A1 (en) * 1991-04-30 1992-11-12 Rolls-Royce Plc Combustion chamber assembly in a gas turbine engine
GB2257781B (en) * 1991-04-30 1995-04-12 Rolls Royce Plc Combustion chamber assembly in a gas turbine engine
US5400587A (en) * 1991-11-13 1995-03-28 Asea Brown Boveri Ltd. Gas turbine annular combustion chamber having radially displaced groups of oppositely swirling burners.
FR2683891A1 (en) * 1991-11-20 1993-05-21 Snecma TURBOMACHINE COMPRISING A DEVICE FOR REDUCING THE EMISSION OF NITROGEN OXIDES.
EP0543720A1 (en) * 1991-11-20 1993-05-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for the introduction of a controlled amount of air at the intersections of the cones of injected fuel in a gas turbine combustor
US5285630A (en) * 1991-11-20 1994-02-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. System for reducing nitrogen-oxide emissions from a gas turbine engine
DE4412315A1 (en) * 1994-04-11 1995-10-12 Abb Management Ag Method of operating gas turbine combustion chamber
DE4412315B4 (en) * 1994-04-11 2005-12-15 Alstom Method and device for operating the combustion chamber of a gas turbine
DE4429539A1 (en) * 1994-08-19 1996-02-22 Abb Management Ag Process for speed control of a gas turbine when shedding loads
DE4429539C2 (en) * 1994-08-19 2002-10-24 Alstom Process for speed control of a gas turbine when shedding loads
DE4429757A1 (en) * 1994-08-22 1996-02-29 Abb Management Ag Two=stage combustion chamber
EP0751351A1 (en) * 1995-06-26 1997-01-02 Abb Research Ltd. Combustion chamber
WO2015122797A1 (en) 2014-02-12 2015-08-20 Otkrytoe Aktsionernoe Obshchestvo "Gazprom" Annular combustion chamber in a gas turbine engine and its operation method
DE112014005025B4 (en) 2014-02-12 2021-08-26 Publichnoe Aktsionernoe Obschestvo "Gazprom" Annular combustion chamber in a gas turbine engine and method for its operation

Also Published As

Publication number Publication date
US5154059A (en) 1992-10-13
PL285434A1 (en) 1991-10-21
ATE108011T1 (en) 1994-07-15
DE59006282D1 (en) 1994-08-04
JP3075732B2 (en) 2000-08-14
RU2002165C1 (en) 1993-10-30
JPH0320524A (en) 1991-01-29
EP0401529B1 (en) 1994-06-29
CH680084A5 (en) 1992-06-15
ES2058667T3 (en) 1994-11-01
HUT56923A (en) 1991-10-28
HU903493D0 (en) 1990-10-28
PL165109B1 (en) 1994-11-30

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