EP0095788B1 - Chambre de combustion d'une turbine à gaz et sa méthode - Google Patents

Chambre de combustion d'une turbine à gaz et sa méthode Download PDF

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Publication number
EP0095788B1
EP0095788B1 EP83200492A EP83200492A EP0095788B1 EP 0095788 B1 EP0095788 B1 EP 0095788B1 EP 83200492 A EP83200492 A EP 83200492A EP 83200492 A EP83200492 A EP 83200492A EP 0095788 B1 EP0095788 B1 EP 0095788B1
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EP
European Patent Office
Prior art keywords
fuel
combustion
elements
diffusion
approximately
Prior art date
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Expired
Application number
EP83200492A
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German (de)
English (en)
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EP0095788A1 (fr
Inventor
Eduard Brühwiler
Hans Koch
Gerald A. Roffe
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BBC Brown Boveri AG Switzerland
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BBC Brown Boveri AG Switzerland
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Publication of EP0095788A1 publication Critical patent/EP0095788A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to the combustion chamber of a gas turbine according to the preamble of claim 1. It also relates to a method for starting and loading such a combustion chamber.
  • a combustion chamber of the type mentioned at the outset without water or steam injection is known from DE-A No. 2950535.
  • this optimization process can be driven in the direction of even lower NO x values in such a way that the space for combustion and after-reactions is kept much longer than would be necessary for the actual combustion.
  • This allows a larger excess air number to be selected, which initially produces larger amounts of CO, but can react further to CO 2 , so that ultimately the CO emissions remain small.
  • due to the large excess of air little additional NO is formed. Since several tubular elements take over the pre-mixing / pre-evaporation, only so many elements are operated with fuel in the load control that the optimum excess air number results for the respective operating phase (start, partial load, etc.).
  • the invention seeks to remedy this.
  • the object of the invention is to raise the stability limit in the entire operating range in a combustion chamber of the type mentioned at the outset in such a way that extinguishing of the flame is avoided with certainty.
  • the inventive solution to this problem is characterized in claim 1.
  • the advantage of the invention can essentially be seen in the fact that a means is provided in a relatively simple manner to keep the combustion at all times within the ignition limits by appropriately distributing the fuel to the premixing or diffusion nozzles.
  • the fact that the use of previous pilot burners can be dispensed with also has a particularly favorable effect.
  • combustion chamber is driven according to a fuel control curve, as defined in claims 4 or 6, and if the burners are gradually ignited from the inside to the outside, there is a combustion in addition to the required flame stability, in which the CO emissions are far greater have better values than can be achieved, for example, with the combustion chamber mentioned at the beginning.
  • FIG. 1 shows, in a highly simplified manner, the design of a combustion chamber with the fuel supply according to the invention.
  • 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 which 36 tubular elements 2 are arranged around a central pilot burner 5. The number is not mandatory, however, because it depends on the size of the combustion chamber, which in turn is dependent on the desired combustion output.
  • a support bridge 27, with which the tubular elements 2 are connected by means of suitable means, is anchored to a support rib 23.
  • the tubular elements 2 are guided laterally in the middle of their longitudinal extent by means of a guide plate 6.
  • the tubular elements 2 can also be anchored differently than with the support bridge 27 shown; In such cases, however, it will always be necessary to ensure that the selected anchorage is placed as far as possible from the combustion chamber 7 so that the thermal expansions cannot develop a disruptive effect.
  • the greater part of the compressed air quantity flows through the openings 9 into a distribution chamber 19 provided in the combustion chamber shell, which is delimited downwards by the support bridge 27 and upwards by the cover 35 flanged by the flange rib 38 becomes. From this distribution chamber 19, the compressed air then flows through the air funnels 14 into the individual tubular elements 2.
  • the fuel supply is provided for each tubular element 2 by a fuel line 4, a fuel nozzle 15 ′ projecting into the tubular element 2 providing the atomization of the oil and a fuel nozzle 15 ′′ blowing gas.
  • the fuel mixes with the inflowing compressed air in such a way that A pre-mixing / pre-evaporation process takes place in the tubular element 2.
  • the fuel evaporates and mixes with the air.
  • the degree of evaporation is stronger, the greater the temperature and the residence time and the smaller the drop size of the atomized fuel.
  • the critical time until the mixture self-ignites decreases, so that the length of the tubular elements 2 is coordinated in such a way that the best possible evaporation results for the shortest possible time.
  • gas there is no evaporation; the gas only needs to be distributed evenly with the air.
  • the flame holder 3 which forms the end of the downstream part of the tubular elements 2, has the task of preventing the flame from reigniting from the combustion chamber 7 into the interior of the tubular element 2. It is preferably provided with a swirl body 28, the mixture of which is directed to the combustion chamber 7 in a swirling manner through its openings.
  • the swirl body 28 favors a stable flame and good heat distribution due to the backflow occurring downstream in its center, which results in a homogeneous temperature and speed distribution after the combustion chamber 7 with the effect that the turbine, not shown, is acted upon uniformly. So far combustion chambers are known.
  • a diffusion nozzle 8 is now arranged within the flame holder 3 of each element 2 and injects the fuel directly into the combustion chamber 7.
  • This nozzle 8 is intended for both oil and gas operation. It is designed in such a way that the start-up in oil operation can only be carried out with diffusion combustion, i.e. it can process the entire amount of oil supplied to element 2. Because of the different volume ratios in gas operation, it is only possible to process about 50% of the total amount of gas supplied to an element 2 with the flow cross-section of the nozzle 8 unchanged.
  • FIG. 3 A simplified schematic diagram of the fuel supply is shown in FIG. 3.
  • the fuel depending on the operating mode oil or gas, is fed into a swirl chamber 11 via a central line 10.
  • the atomizing air is guided in an annular space 12 enveloping the central line 10 and reaches the chamber 11 via openings 13.
  • the mixture is injected into the combustion chamber 7 via a commercially available diffusion nozzle 8.
  • the diffusion nozzle is cooled by an air flow which is removed from the annular space 12 upstream of the swirl chamber 11 via a bore 16 and is guided in an annular chamber 17 which is delimited on the outside by a sleeve 18.
  • the swirl bodies 28 of the flame holder 3 are fastened to this sleeve 18.
  • separate fuel nozzles 15 ′ are each provided for gas and oil operation. respectively 15 ".
  • the decisive factor here is that the oil is expediently introduced into the mixing chamber against the direction of air inflow, while the gas is introduced into or across the direction of the air.
  • a ring line 20 for the fuel oil is arranged around the central line 10 and communicates with an outlet chamber 24 via a bore 21, approximately at half the chamber height.
  • the atomizing air is guided in this area in longitudinal bores 26 which are evenly distributed over the circumference and which open into the annular space 12 already mentioned at their lower end.
  • this annular space 12 communicates with the lower, closed end of the outlet chamber 24 via a bore 29.
  • the outlet chamber 24 is provided at its upper end with an annular nozzle 15 ', via which the mixture against the combustion air in the actual mixing and Evaporation space is injected.
  • the gas premix system is arranged above the oil premix system.
  • the atomizing air that is not required in this area is in turn guided in an annular chamber 30 concentrically surrounding the channels 12 and 20.
  • This annular chamber 30 is surrounded on the outside by a gas chamber 31, from which the fuel gas is blown under pressure into the mixing chamber via the nozzles 15 ′′, perpendicular to the direction of flow of the combustion air.
  • the nozzles 15 'and 15 are dimensioned in such a way that they can process the entire amount of fuel supplied to an element 2.
  • the element arrangement shown in FIG. 2 is taken as a basis and the assumption is made that the elements 2 are only switched on or off in groups.
  • the machine speed n is plotted on the abscissa in [%] and the excess air number ⁇ is plotted on the ordinate.
  • the parameters K z4 , K, a , K 15 , K 12 , K s and K s each represent a number of 24.18 ... 6 elements. It is the optimal switching curve when starting the combustion chamber in oil operation. It goes without saying that premix combustion cannot be carried out here, since when starting the air coming from the compressor is still too cold to cause oil evaporation within the elements 2. The starting process and the low load range are therefore carried out with pure diffusion combustion. Since an excess air ratio of at least 1 is required for combustion, the diagram shows that at least 18 elements are required for starting.
  • the actual switching curve is drawn with a thick line.
  • the combustion chamber is started up with 18 elements.
  • the groups u, v and w are in operation.
  • group w is switched off at 60% speed. This means that the same amount of fuel is now burned in just 15 elements, which lowers the excess air figure.
  • group v is switched off at approx. 92% speed, which causes the excess air figure to drop to 1.2.
  • the fact that the curves in this area do not run continuously is due to the fact that the usual blowing off of compressor air is interrupted here.
  • the NO x limit value can easily be fallen below, but then the stability limit S M is low because of the low flame temperature.
  • the range between ignitability and extinguishing is too narrow to be able to safely run the gas turbine in the full load range.
  • the invention is therefore based on a mixed driving style with diffusion and premix combustion in the load range. That is in each case Proportional oil quantity ratio selected so that a driving style with a sufficient distance from the resulting stability limit S DM is possible. Tests have shown that this is best achieved when 90 to 95% of the fuel is burned according to the premix principle and 5 to 10% of the fuel is burned according to the diffusion principle.
  • the diagram shows a mixed driving style with a 10% diffusion percentage. From idle to 15% load, 1/4 of the available elements are used, ie only with group u in pure diffusion mode. Due to the increase in the fuel oil supply, ⁇ has become so low at 15% load that the element group v has to be switched on again. At 20% load, the premixing system is then put into operation for all elements of groups u and v, which leads to a division of the fuel oil in the above-mentioned ratio. The reduction in fuel at the diffusion nozzles while the amount of air remains the same, causing the excess air figure to rise steeply, as shown in dashed lines.
  • the commissioning of the premix can be represented by reducing the excess air from the value oo (infinite) to the value shown at 20% load, as is shown in dash-dot lines. With this measure, the stability limit falls to the displayed value S DM at 20% load.
  • the further control curve for the load increase is now determined in such a way that the excess air figure is constantly between 1.5 and 2.
  • the diagram in Fig. 6 deals with the optimal fuel control curve in the load range for gas combustion. All sizes shown from 20% load. correspond to those in Fig. 5. Gas operation differs from oil operation only in the starting phase and in the lower load range.
  • the starting process from 20% engine speed to idling (not shown) is already carried out with mixed diffusion / premix combustion and it has proven to be advantageous if the process is carried out with 50% premix and 50% diffusion combustion. This is possible because evaporation and the air temperature required for this are not necessary.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Spray-Type Burners (AREA)

Claims (8)

1. Chambre de combustion d'une turbine à gaz, dans laquelle à l'intérieur de l'enveloppe (1 ) de la chambre de combustion une chambre de distribution d'air (19) et un espace de combustion (7) sont localement séparés l'un de l'autre, une pluralité d'éléments tubulaires (2) étant disposés entre la chambre de distribution et l'espace de combustion, éléments dans lesquels se produit, avec l'air comprimé, un prémélange et une prévaporisation du combustible liquide fourni par des gicleurs de prémélange (15') et/ou un prémélange de gaz combustible fourni par des gicleurs de prémélange (15"), et où chaque élément tubulaire (2) est pourvu d'un accrocheur de flamme (3) dans sa partie tournée vers l'espace de combustion (7), caractérisé en ce qu'à l'intérieur de l'accrocheur de flamme (3) est disposé un gicleur de diffusion (8) orienté vers l'espace de combustion (7), gicleur à travers lequel on peut injecter du combustible directement dans l'espace de combustion (7).
2. Chambre de combustion suivant la revendication 1, caractérisée en ce que la pluralité d'éléments tubulaires (2) est subdivisée en un certain nombre de groupes (u, v, w, x, y, z) pouvant être allumés séparément.
3. Chambre de combustion suivant la revendication 1, caractérisé en ce que les gicleurs de diffusion (8) sont dimensionnés de telle façon que la quantité de combustion à fournir à chaque élément (2) puisse, à raison de 100% pour le combustible liquide et à raison de 50% pour le gaz combustible, être introduite directement dans l'espace de combustion (7).
4. Procédé pour faire démarrer et mettre en charge la chambre de combustion suivant la revendication 1,en utilisant du mazout comme combustible liquide, caractérisé en ce que:
a) après l'allumage initial à partir d'environ 20% de la vitesse de rotation de la machine, d'abord environ la moitié des éléments fonctionnent uniquement en combustion par diffusion;
b) à partir d'environ 60% de la vitesse de rotation de la machine, seulement environ % des éléments sont utilisés en combustion par diffusion, avec le combustible correspondant;
c) à partir de 90% de la vitesse de rotation de la machine, seulement environ M. des éléments fonctionnent en combustion par diffusion et en fait aussi longtemps que l'on n'a pas atteint la vitesse nominale et environ 15% de charge;
d) à partir de 15% de charge, on remet en service en combustion par diffusion des élémentsjus- qu'à un nombre total d'environ 2/5 des éléments, avec le combustible correspondant;
e) pour environ 20% de charge, et dans tous les éléments alimentés en combustible, on met également en service les gicleurs de prémélange, la quantité de combustible fournie à chaque élément étant, pour la plus grande partie, injectée par les gicleurs de prémélange;
f) lorsque la charge augmente jusqu'à la pleine charge on met en service par paliers d'autres éléments, avec le combustible correspondant, chaque élément individuel fonctionnant alors aussi bien en combustion par diffusion qu'en combustion par prémélange.
5. Procédé suivant la revendication 4, caractérisé en ce qu'en cas de combustion simultanée par diffusion et par prémélange, les éléments en service avec le combustible correspondant sont alimentés à raison de 90 à 95% du combustible liquide par les gicleurs de prémélange et à raison de 5 à 10% du combustible liquide par les gicleurs de diffusion.
6. Procédé pour faire démarrer et mettre en charge la chambre de combustion suivant la revendication 1, en utilisant du gaz comme combustible, caractérisé en ce que:
a) après l'allumage initial à partir d'environ 20% de la vitesse de rotation de la machine, d'abord environ la moitié des éléments fonctionnent aussi bien en combustion par diffusion qu'en combustion par prémélange;
b) à partir d'environ 60% de la vitesse de rotation de la machine, seulement environ 2/5 des éléments sont en fonctionnement, avec le combustible correspondant;
c) à partir de 90% de la vitesse de rotation de la machine, seulement environ'/3 des éléments fonctionnent avec le combustible correspondant, et en fait aussi longtemps que l'on n'a pas atteint la vitesse nominale et environ 15% de charge;
d) à partir de 15% de charge, on fait à nouveau fonctionner des éléments, avec le combustible correspondant, jusqu'à un nombre total de 2/5;
e) lorsque la charge augmente jusqu'à la pleine charge, on met en service par paliers d'autres éléments, avec le combustible correspondant, chaque élément individuel fonctionnant aussi bien en combustion par diffusion qu'en combustion par prémélange.
7. Procédé suivant la revendication 6, caractérisé en ce qu'au démarrage, environ 30 à 50% du gaz fourni à chaque élément est brûlé suivant le principe de la diffusion et le reste est brûlé suivant le principe du prémélange, et en ce qu'entre la marche à vide et la pleine charge, environ 5 à 10% du gaz fourni est brûlé suivant le principe de la diffusion et la majeure partie, soit 90 à 95%, est brûlée suivant le principe du prémélange.
8. Procédé suivant l'une des revendications 4 ou 6 pour la conduite d'une chambre de combustion suivant la revendication 2, caractérisé en ce qu'après l'allumage initial, d'abord les groupes (u, v) des éléments intérieurs centraux sont en fonctionnement avec le combustible correspondant, et en ce que, lors de l'augmentation de la charge à partir d'environ 15% de charge, les autres groupes d'éléments plus extérieurs (w, x, y, z) sont allumés successivement dans l'ordre de leur éloignement croissant du centre.
EP83200492A 1982-05-28 1983-04-07 Chambre de combustion d'une turbine à gaz et sa méthode Expired EP0095788B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH3295/82 1982-05-28
CH329582 1982-05-28

Publications (2)

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EP0095788A1 EP0095788A1 (fr) 1983-12-07
EP0095788B1 true EP0095788B1 (fr) 1985-12-18

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EP (1) EP0095788B1 (fr)
JP (1) JPS58219329A (fr)
DE (1) DE3361535D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4412315A1 (de) * 1994-04-11 1995-10-12 Abb Management Ag Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine

Families Citing this family (77)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60207820A (ja) * 1984-03-26 1985-10-19 ザ　ギヤレツト　コーポレーシヨン 燃料を噴出し霧化する方法およびその装置
EP0193029B1 (fr) * 1985-02-26 1988-11-17 BBC Brown Boveri AG Chambre de combustion pour turbines à gaz
DE3663847D1 (en) * 1985-06-07 1989-07-13 Ruston Gas Turbines Ltd Combustor for gas turbine engine
CH670296A5 (en) * 1986-02-24 1989-05-31 Bbc Brown Boveri & Cie Gas turbine fuel nozzle - has externally-supported premixing chamber for liq. fuel and air
EP0269824B1 (fr) * 1986-11-25 1990-12-19 General Electric Company Brûleur combiné à diffusion et à prémélange pour veilleuse
US4982570A (en) * 1986-11-25 1991-01-08 General Electric Company Premixed pilot nozzle for dry low Nox combustor
CH672541A5 (fr) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
JP2528894B2 (ja) * 1987-09-04 1996-08-28 株式会社日立製作所 ガスタ―ビン燃焼器
CH680946A5 (fr) * 1989-12-19 1992-12-15 Asea Brown Boveri
US5199265A (en) * 1991-04-03 1993-04-06 General Electric Company Two stage (premixed/diffusion) gas only secondary fuel nozzle
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
US5261226A (en) * 1991-08-23 1993-11-16 Westinghouse Electric Corp. Topping combustor for an indirect fired gas turbine
US5263325A (en) * 1991-12-16 1993-11-23 United Technologies Corporation Low NOx combustion
US5274991A (en) * 1992-03-30 1994-01-04 General Electric Company Dry low NOx multi-nozzle combustion liner cap assembly
DE4223828A1 (de) * 1992-05-27 1993-12-02 Asea Brown Boveri Verfahren zum Betrieb einer Brennkammer einer Gasturbine
US5410884A (en) * 1992-10-19 1995-05-02 Mitsubishi Jukogyo Kabushiki Kaisha Combustor for gas turbines with diverging pilot nozzle cone
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
US5408825A (en) * 1993-12-03 1995-04-25 Westinghouse Electric Corporation Dual fuel gas turbine combustor
JP2580527B2 (ja) * 1993-12-27 1997-02-12 工業技術院長 液化ｌｐガスを用いるガスタービン燃焼器
IT1273369B (it) * 1994-03-04 1997-07-08 Nuovo Pignone Spa Sistema perfezionato combustione a basse emissioni inquinanti per turbine a gas
US5491970A (en) 1994-06-10 1996-02-20 General Electric Co. Method for staging fuel in a turbine between diffusion and premixed operations
EP0747635B1 (fr) * 1995-06-05 2003-01-15 Rolls-Royce Corporation Brûleur à prémélange pauvre avec faible production de NOx pour turbines à gaz industrielles
US5822992A (en) * 1995-10-19 1998-10-20 General Electric Company Low emissions combustor premixer
GB2307980B (en) * 1995-12-06 2000-07-05 Europ Gas Turbines Ltd A fuel injector arrangement; a method of operating a fuel injector arrangement
US5881756A (en) * 1995-12-22 1999-03-16 Institute Of Gas Technology Process and apparatus for homogeneous mixing of gaseous fluids
US5797268A (en) * 1996-07-05 1998-08-25 Westinghouse Electric Corporation Partially swirled multi-swirl combustor plate and chimneys
SE514341C2 (sv) * 1998-06-18 2001-02-12 Abb Ab Förfarande för start av en brännaranordning till en gasturbin
WO2000012940A1 (fr) * 1998-08-31 2000-03-09 Siemens Aktiengesellschaft Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante
IT1313547B1 (it) * 1999-09-23 2002-07-24 Nuovo Pignone Spa Camera di premiscelamento per turbine a gas
EP1199523A1 (fr) * 2000-10-20 2002-04-24 Siemens Aktiengesellschaft Procédé pour alimenter des brûleurs dans une chambre de combustion et chambre de combustion avec plusieurs brûleurs
US6928823B2 (en) * 2001-08-29 2005-08-16 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6813889B2 (en) * 2001-08-29 2004-11-09 Hitachi, Ltd. Gas turbine combustor and operating method thereof
US6962055B2 (en) * 2002-09-27 2005-11-08 United Technologies Corporation Multi-point staging strategy for low emission and stable combustion
US6931853B2 (en) * 2002-11-19 2005-08-23 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
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US9353950B2 (en) * 2012-12-10 2016-05-31 General Electric Company System for reducing combustion dynamics and NOx in a combustor
CN106907740B (zh) * 2013-10-18 2019-07-05 三菱重工业株式会社 燃料喷射器
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WO2019117467A1 (fr) * 2017-12-11 2019-06-20 (주)넥스트가스이노베이션 Dispositif de combustion à injection directe de gpl
US10890329B2 (en) 2018-03-01 2021-01-12 General Electric Company Fuel injector assembly for gas turbine engine
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EP3861255A2 (fr) * 2018-10-05 2021-08-11 Fives Pillard Bruleur et procede de combustion pour bruleur
US10935245B2 (en) 2018-11-20 2021-03-02 General Electric Company Annular concentric fuel nozzle assembly with annular depression and radial inlet ports
US11073114B2 (en) 2018-12-12 2021-07-27 General Electric Company Fuel injector assembly for a heat engine
US11286884B2 (en) 2018-12-12 2022-03-29 General Electric Company Combustion section and fuel injector assembly for a heat engine
US11156360B2 (en) 2019-02-18 2021-10-26 General Electric Company Fuel nozzle assembly
DE102020119619A1 (de) * 2020-07-24 2022-01-27 Friedrich-Alexander-Universität Erlangen-Nürnberg Düsencluster
KR102583225B1 (ko) * 2022-02-07 2023-09-25 두산에너빌리티 주식회사 마이크로 믹서 및 이를 포함하는 가스 터빈

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH305532A (de) * 1951-06-25 1955-02-28 Parsons & Co Ltd C A Gasturbinenanlage.
CH303030A (de) * 1952-08-15 1954-11-15 Bbc Brown Boveri & Cie Gasbrenner, vorzugsweise für Brennkammern von Gasturbinenanlagen.
DE1074920B (de) * 1955-07-07 1960-02-04 Ing habil Fritz A F Schmidt Murnau Dr (Obb) Verfahren und \ orrichtung zur Regelung von Gas turbmenbrennkammern mit unterteilter Verbrennung und mehreren Druckstufen
CH388022A (de) * 1960-10-07 1965-02-15 Maschf Augsburg Nuernberg Ag Brennkammer für die gleichzeitige Verbrennung gasförmiger und nichtgasförmiger Brennstoffe, insbesondere für Gasturbinenanlagen
GB1284439A (en) * 1969-12-09 1972-08-09 Rolls Royce Fuel injector for a gas turbine engine
US3630024A (en) * 1970-02-02 1971-12-28 Gen Electric Air swirler for gas turbine combustor
US3777983A (en) * 1971-12-16 1973-12-11 Gen Electric Gas cooled dual fuel air atomized fuel nozzle
US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US3886728A (en) * 1974-05-01 1975-06-03 Gen Motors Corp Combustor prechamber
GB1559779A (en) * 1975-11-07 1980-01-23 Lucas Industries Ltd Combustion assembly
US4134719A (en) * 1976-09-27 1979-01-16 Velie Wallace W Multi-flame fuel burner for liquid and gaseous fuels
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
US4327547A (en) * 1978-11-23 1982-05-04 Rolls-Royce Limited Fuel injectors
US4288980A (en) * 1979-06-20 1981-09-15 Brown Boveri Turbomachinery, Inc. Combustor for use with gas turbines
DE2950535A1 (de) * 1979-11-23 1981-06-11 BBC AG Brown, Boveri & Cie., Baden, Aargau Brennkammer einer gasturbine mit vormisch/vorverdampf-elementen
HU181665B (en) * 1979-11-28 1983-10-28 Chinoin Gyogyszer Es Vegyeszet Plant protective composition containing carbofurane with increased growth promoting and insecticide effect
DE2949388A1 (de) * 1979-12-07 1981-06-11 Kraftwerk Union AG, 4330 Mülheim Brennkammer fuer gasturbinen und verfahren zum betrieb der brennkammer
US4356698A (en) * 1980-10-02 1982-11-02 United Technologies Corporation Staged combustor having aerodynamically separated combustion zones

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4412315A1 (de) * 1994-04-11 1995-10-12 Abb Management Ag Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine
DE4412315B4 (de) * 1994-04-11 2005-12-15 Alstom Verfahren und Vorrichtung zum Betreiben der Brennkammer einer Gasturbine

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JPS58219329A (ja) 1983-12-20
DE3361535D1 (en) 1986-01-30
US4967561A (en) 1990-11-06
JPH0356369B2 (fr) 1991-08-28
EP0095788A1 (fr) 1983-12-07

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