EP1730448B1 - Ensemble a plusieurs bruleurs servant a faire fonctionner une chambre de combustion et procede pour faire fonctionner un tel ensemble - Google Patents

Ensemble a plusieurs bruleurs servant a faire fonctionner une chambre de combustion et procede pour faire fonctionner un tel ensemble Download PDF

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Publication number
EP1730448B1
EP1730448B1 EP05729789.7A EP05729789A EP1730448B1 EP 1730448 B1 EP1730448 B1 EP 1730448B1 EP 05729789 A EP05729789 A EP 05729789A EP 1730448 B1 EP1730448 B1 EP 1730448B1
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EP
European Patent Office
Prior art keywords
fuel
burner
premix
burners
swirl
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EP05729789.7A
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German (de)
English (en)
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EP1730448A1 (fr
Inventor
Peter Flohr
Christian Jörg Motz
Majed Toqan
Martin Zajadatz
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Ansaldo Energia IP UK Ltd
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General Electric Technology GmbH
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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
    • F23R3/286—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
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/06—Liquid fuel from a central source to a plurality of burners
    • 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
    • F23R3/346—Feeding into different combustion zones for staged combustion

Definitions

  • the invention relates to a multiple burner arrangement with a plurality of trained as Vormischbrennem individual burners, which serve for firing a combustion chamber for a heat engine, preferably for a gas turbine plant, and each having a swirl space, are fed into the Verbrennungszu slaughter and fuel to form a swirl flow, wherein the swirl flow downstream of the premix burner within the combustion chamber forms a largely stably forming return flow zone, in which a burner flame is formed after ignition of the fuel-air mixture.
  • a method for operating such a multiple burner arrangement will be described.
  • annular combustion chambers which are used for the purpose of driving gas turbine plants and which provide a multiplicity of individual premix burners in a circular arrangement around the rotating components of a gas turbine, whose hot gases are fed directly via a ring-shaped flow channel of the downstream turbine stage.
  • annular combustion chamber arrangement is for example from the EP 597 138 B1 can be seen, which provides a plurality annularly arranged Vormischbrenner, as for example the EP 387 532 A1 can be removed and are each designed as a double-cone burners, which provide a radially enclosed from two hollow conical bodies torso swirl space whose respective center axes are offset from each other, so that adjacent walls of two cone bodies include tangential slots for the combustion air in their longitudinal extent.
  • Liquid fuel can be fed into the swirl chamber, which widens conically in the axial direction, via a fuel nozzle arranged largely centrally within the swirl space.
  • the premix burner can be supplied with gaseous fuel via gas inlet openings distributed along the tangential slots within the wall of both partial cone bodies.
  • gas inlet openings distributed along the tangential slots within the wall of both partial cone bodies.
  • the fuel supply for each premix burner is usually carried out at startup of the gas turbine and at low load ranges via a so-called pilot stage, depending on the design of the premix burner as a central burner lance, as for example in the DE 196 52 899 A1 is described, or as a directly at the burner outlet in the flow direction in front of the combustion chamber provided pilot gas supply is formed.
  • thermoacoustic oscillations moreover preferably also occur in premix mode, i. in the middle and upper load range, through which the forming within the combustion chamber flame stability is greatly impaired.
  • the DE 101 08 560 A1 proposed the previously applied symmetry in the fuel supply of all Purposefully break up premix burners provided in the multiple burner assembly to effectively reduce the incidence of combustor pulsations.
  • at least one premix burner is operated such that the at least one premix burner has a different spatial mixing profile within the fuel-air mixture from all other premix burners provided in the multiple burner arrangement.
  • the at least one premix burner provides a fuel feed for the gaseous fuel, which differs constructively from all other premix burners, along the partial cone shells which radially delimit the conical swirl space.
  • this measure contributes to the damping of the usual form in resonant form circularly circulating in an annular combustion chamber pulsations in the upper load range of the gas turbine plant, but are the further influence on the burner behavior with respect to the operation of the gas turbine plant at different load conditions and taking into account other, the combustion processes within the respective premix burner influencing parameters, such as greatly varying moisture content in the combustion air supply with performance increase of the gas turbine, ambient temperature, change in the fuel composition as well as aging phenomena of the entire gas turbine plant limits.
  • the above-described proposal does not allow subsequent retrofitability to existing gas turbine plants, so that the known measure can be realized only in new-to-be-acquired gas turbine plants.
  • a multiple burner arrangement with a multiplicity of individual burners designed as premix burners according to the preamble of claim 1 is known US2003 / 0041588 A1 ,
  • the invention has the object of providing a multiple burner arrangement with a plurality of trained as Vormischbrennern individual burners, in particular for operating a gas turbine plant according to the preamble of claim 1 such that the operation of a variety of individual premix burners as flexible or variable depending on the particular load condition and the parameter influencing the combustion process, as mentioned above, can be optimized.
  • it is necessary to create a regulatory option which optimizes the operation of a multiple burner arrangement in terms of pollutant emissions and significantly reduces the pulsations caused by the combustion in the entire load range.
  • claim 8 is a method for operating a multiple burner arrangement, as it is suitable for example for the operation of an annular combustion chamber.
  • the multi-burner arrangement according to the invention is based on the targeted use of stepped premix burner systems which have means for internally staged fuel injection into the swirl chamber for premix operation.
  • each individual premix burner provided in the multiple burner arrangement is supplied with fuel, preferably gaseous fuel, via at least two separate fuel lines, a so-called first and a second fuel line, through which the fuel is fed into the swirl space for further formation of the swirl flow.
  • the respective first fuel line of each premix burner is connected to a first ring line via which the respective first fuel lines of all premix burners within the multiple burner arrangement are supplied with fuel.
  • a second ring line is provided, which is connected to each of the second fuel line of each individual, provided in the multi-burner arrangement Vormischbrenners.
  • a fuel supply influencing control unit such as a throttle valve
  • a fuel supply influencing control unit such as a throttle valve
  • the burner concept according to the invention with controllable fuel throttling, at least for selectively selected premix burners within a multiple burner arrangement, can be realized both with premix burners with burner lances or with external pilot feeds.
  • Vorischbrennem with a swirl space at least partially centrally passing burner lance a large part of the preferably gaseous fuel is fed via the burner lance into the swirl chamber during startup or lower load range of the gas turbine.
  • each of the burner lances are connected to the respective first fuel line, which are fed by a respective common ring line with fuel.
  • the multiple burner arrangement is operated such that significantly more than half of the gaseous fuel is supplied via the respective second fuel line to the premix burner via the fuel outlet openings, which extend along the air inlet slots.
  • the inventive burner concept by providing additional control units along the branched off from a ring line fuel lines only for a selected group of provided in the multi-burner arrangement Premixing a targeted disruption of the symmetry in the temperature distribution along the flame forming within the combustion chamber, whereby a decisive influence on the reduction of forming within the combustion chamber thermoacoustic vibrations can be taken.
  • control units provided in the fuel lines which are preferably designed as throttle valves, allow active regulation or control as a function of parameters influencing the combustion process, such as the varying proportion of moisture in the combustion air supply depending on the load range of the gas turbine arrangement, the ambient temperature, change in temperature Fuel composition as well as aging of gas turbine components.
  • Fig. 1 shows a longitudinal section and an oriented against the flow direction S front view of a premix burner 1 with stepped fuel supply.
  • the cone-shaped Vormischbrenner 1 closes with his in Fig. 1 shown highly schematic part cone shells 2 a cone-shaped swirl space 3 a. Due to their mutually overlapping arrangement, the subcone shells 2 each include air inlet slots 4, along which the fuel feed openings 5 are distributed, through which gaseous fuel is fed into the swirl chamber 3 to form a swirl flow.
  • a burner lance 6 is provided, which also has fuel outlet openings through which fuel in the swirl chamber 3 can be fed.
  • the fuel feed via the lance stage 6 is preferably carried out when starting the gas turbine plant and in the lower load range. On the other hand, if the gas turbine is located in the middle or upper load range, the fuel feed takes place primarily via the fuel supply openings 5 extending along the partial cone shells.
  • FIG. 2a schematically shows the fuel supply to a single premix burner in the manner of a FIG. 1 illustrated embodiment.
  • a first fuel line 7 is connected to the lance stage 6, whereas a second fuel line 8 is connected to the fuel inlet openings 5, which extend along the air inlet slots 4 within the Teifkegelschalen 2.
  • FIG. 2c Another variant of the fuel feed is in Figure 2c illustrated, in which a first fuel stage via an external pilot stage 11, which is provided after the burner outlet and upstream to the combustion chamber BK.
  • the second burner stage corresponds to that in the image representation according to FIG. 2b
  • the air inlet slots 4 distributed fuel feed openings 5 along the part cone shells.
  • FIG. 3 schematically a piping plan to remove fuel for the individual fuel lines 7, 8, by the premix burner, not shown in the in FIG. 2 supplied with fuel in the manner indicated.
  • the fuel lines 7 of all premix burners with a first ring line 12 and the fuel lines 8 are connected correspondingly with a second ring line 13.
  • additional control units 15, preferably controllable throttle valves, provided by a targeted throttling of the fuel supply via the example in the first fuel line 7, which is preferably connected to the burner lance is possible.
  • FIG. 4 a schematic representation of a multiple burner arrangement for firing an annular combustion chamber is shown. Equally distributed on an annular surface 18 premix burners are arranged, of which those premix burners are operated unthrottled with a black point, the rest, each marked with a circle throttled, for example, operated with a throttled lance stage. Since, as indicated above, the degree of fuel throttling can be variably adjusted and this ultimately for each individual throttled premix burner, different irregular temperature profiles running along the combustion chamber circumference can be set, which are able to decisively influence the combustion process. By controlled influence on targeted premix burners operable in the multiple burner arrangement, the combustion process can be optimized directly during operation of the gas turbine.
  • the burner concept according to the invention can be used successfully not only for annular combustion chambers, but also for burner arrangements which provide uniformly distributed or unevenly distributed individual burners, for example for firing a pot combustion chamber.
  • Variants are also conceivable in which burner arrangements are arranged axially one behind the other, such as, for example, in axially stepped combustion chambers.

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

Claims (13)

  1. Dispositif à brûleurs multiples avec pluralité de brûleurs individuels conçus comme des brûleurs de pré-mélange (1), qui servent à l'allumage d'une chambre de combustion d'un moteur thermique et qui comprennent chacun une chambre de turbulences (3), dans lequel de l'air de combustion ainsi qu'un carburant peuvent être introduits pour la formation d'un écoulement turbulent, l'écoulement turbulent formant, en aval du brûleur de pré-mélange (1) à l'intérieur de la chambre de combustion, une zone d'écoulement de retour dans laquelle se forme une flamme de brûleur,
    les brûleurs de pré-mélange (1) pouvant être alimentés en carburant par l'intermédiaire d'au moins une première et d'une deuxième conduites de carburant (7, 8), grâce auxquelles du carburant peut être introduit dans la chambre de turbulences (3) en formant un écoulement turbulent, la première conduite de carburant (7) de chaque brûleur de pré-mélange étant reliée à une première conduite annulaire (12) et la deuxième conduite de carburant (8) de chaque brûleur de pré-mélange étant reliée à une deuxième conduite annulaire (13),
    caractérisé en ce que
    au moins dans un premier groupe de brûleurs de pré-mélange, dans au moins une des conduites de carburant (7, 8), se trouve une unité de régulation (15) influençant l'alimentation en carburant et
    le nombre de brûleurs de pré-mélange du premier groupe est inférieur à la moitié du nombre total de la pluralité de brûleurs de pré-mélange.
  2. Dispositif à brûleurs multiples selon la revendication 1,
    caractérisé en ce que l'unité de régulation (15) est une soupape d'étranglement ou un disque d'obturation.
  3. Dispositif à brûleurs multiples selon la revendication 1 ou 2,
    caractérisé en ce que
    les brûleur de pré-mélange (1) comprennent chacun une chambre de turbulences (3) présentant la forme d'un cône partiel, qui est limitée radialement par au moins deux coques partiellement coniques (2) formant entre elles des fentes d'entrée d'air (4) tangentielles se superposant entre elles,
    l'introduction de carburant dirigée vers la chambre de turbulences (3) a lieu par l'intermédiaire d'au moins deux zones d'introduction de carburant distinctes, qui sont séparées axialement de la chambre de turbulences (3) présentant une forme partiellement conique ou sont disposées axialement façon à être superposéee partiellement et sont reliées chacune avec une conduite de carburant (7, 8).
  4. Dispositif à brûleurs multiples selon la revendication 3,
    caractérisé en ce que
    dans la direction axiale, dans la chambre de turbulences (3), est prévue au moins une lance de combustion (6) dépassant au moins partiellement au centre,
    une première zone d'introduction de carburant est prévue le long de la lance de combustion (6) et une deuxième zone d'introduction de carburant est prévue le long des coques partiellement coniques (2) de préférence au niveau des fentes d'entrée d'air (4).
  5. Dispositif à brûleurs multiples selon la revendication 3,
    caractérisé en ce qu'une première zone d'introduction de carburant (9) est prévue le long des coques partiellement coniques (2), de préférence au niveau des fentes d'entrée d'air (4), et une deuxième zone d'introduction de carburant (10) est prévue dans la direction axiale, de manière adjacente à la première zone d'introduction de carburant (9) le long des coques partiellement coniques (2).
  6. Dispositif à brûleurs multiples selon l'une des revendications 1 à 5,
    caractérisé en ce que la pluralité de brûleurs de pré-mélange (1) est disposée sous la forme d'une disposition annulaire pour l'allumage d'une chambre de combustion annulaire ou sous la forme d'une disposition de surface circulaire pour l'allumage d'une chambre de combustion en forme de cloche.
  7. Dispositif à brûleurs multiples selon l'une des revendications 1 à 6,
    caractérisé en ce que, à l'intérieur de la première et/ou de la deuxième conduite annulaire (12, 13), est prévu un dispositif de régulation (14).
  8. Procédé d'exploitation d'un dispositif à brûleurs multiples avec une pluralité de brûleurs individuels, qui permettent l'allumage d'une chambre de combustion d'un moteur thermique et sont conçus sous la forme de brûleurs de pré-mélange (1) qui comprennent chacun une chambre de turbulences (3) dans laquelle de l'air de combustion ainsi que du carburant sont introduits en formant un écoulement turbulent, l'écoulement turbulent formant, en aval du brûleur de pré-mélange (1), à l'intérieur de la chambre de combustion, une zone d'écoulement de retour, dans laquelle se forme une flamme de brûleur, les brûleurs de pré-mélange (1) étant divisés en au moins deux groupes, qui sont alimentés chacun avec des quantités de carburant différentes,
    les brûleurs de pré-mélange étant alimentés en carburant par l'intermédiaire d'au moins une première et une deuxième conduites de carburant (7, 8), grâce auxquelles du carburant est introduit dans la chambre de turbulences (3) pour la formation de l'écoulement turbulent,
    la première conduite de carburant (7) de chaque brûleur de pré-mélange étant alimentée en carburant par l'intermédiaire d'une première conduite annulaire (12) et la deuxième conduite de carburant (8) de chaque brûleur de pré-mélange étant alimentée en carburant par l'intermédiaire d'une deuxième conduite annulaire (13)
    caractérisé en ce que
    au moins dans un premier groupe de brûleurs de pré-mélange, son nombre est inférieur à la moitié de la pluralité de brûleurs individuels prévus dans le dispositif à brûleurs multiples le long d'au moins une des conduites de carburant, l'alimentation en carburant a lieu à l'aide d'un étranglement.
  9. Procédé selon la revendication 8,
    caractérisé en ce que l'étranglement de l'alimentation en carburant est effectué de manière régulée ou contrôlée.
  10. Procédé selon la revendication 9,
    caractérisé en ce que la régulation ou le contrôle de l'étranglement du carburant a lieu en fonction de l'état de charge du moteur thermique, sur la base de la réduction des pulsations se formant à l'intérieur de la chambre de combustion, d'une réduction des valeurs d'émissions de substances polluantes et/ou en fonction de la composition du carburant, de la température ambiante et/ou de l'humidité ambiante.
  11. Procédé selon l'une des revendications 8 à 10,
    caractérisé en ce que l'introduction de carburant a lieu par l'intermédiaire d'au moins deux zones d'introduction de carburant séparées axialement le long de la chambre de turbulences (3) de chaque brûleur de pré-mélange.
  12. Procédé selon la revendication 11,
    caractérisé en ce qu'une première introduction de carburant a lieu par l'intermédiaire d'une lance de combustion (6) prévue au centre à l'intérieur de la chambre de turbulences (3) et une deuxième introduction de carburant a lieu le long des coques partiellement coniques (2) délimitant radialement la chambre de turbulences (3).
  13. Procédé selon la revendication 11,
    caractérisé en ce qu'une première et une deuxième introductions de carburant ont lieu le long des coques partiellement coniques (2) délimitant radialement la chambre de turbulences (3).
EP05729789.7A 2004-03-31 2005-03-29 Ensemble a plusieurs bruleurs servant a faire fonctionner une chambre de combustion et procede pour faire fonctionner un tel ensemble Active EP1730448B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH5592004 2004-03-31
PCT/EP2005/051410 WO2005095864A1 (fr) 2004-03-31 2005-03-29 Ensemble a plusieurs bruleurs servant a faire fonctionner une chambre de combustion et procede pour faire fonctionner un tel ensemble

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Publication Number Publication Date
EP1730448A1 EP1730448A1 (fr) 2006-12-13
EP1730448B1 true EP1730448B1 (fr) 2016-12-14

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US (1) US7878799B2 (fr)
EP (1) EP1730448B1 (fr)
CN (1) CN1938549B (fr)
ES (1) ES2616873T3 (fr)
WO (1) WO2005095864A1 (fr)

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Also Published As

Publication number Publication date
CN1938549A (zh) 2007-03-28
US7878799B2 (en) 2011-02-01
CN1938549B (zh) 2010-09-29
EP1730448A1 (fr) 2006-12-13
WO2005095864A1 (fr) 2005-10-13
US20070105061A1 (en) 2007-05-10
ES2616873T3 (es) 2017-06-14

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