EP0925472B1 - Procede pour la suppression des oscillations de combustion et dispositif pour la combustion d'un combustible avec de l'air - Google Patents

Procede pour la suppression des oscillations de combustion et dispositif pour la combustion d'un combustible avec de l'air Download PDF

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Publication number
EP0925472B1
EP0925472B1 EP97941847A EP97941847A EP0925472B1 EP 0925472 B1 EP0925472 B1 EP 0925472B1 EP 97941847 A EP97941847 A EP 97941847A EP 97941847 A EP97941847 A EP 97941847A EP 0925472 B1 EP0925472 B1 EP 0925472B1
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EP
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Prior art keywords
burner
fuel
air
burners
combustion chamber
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EP97941847A
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German (de)
English (en)
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EP0925472A1 (fr
Inventor
Stefan Hoffmann
Peter Berenbrink
Hans Judith
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Siemens AG
Siemens Corp
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Siemens AG
Siemens Corp
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    • 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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a method for suppressing combustion vibrations during a combustion of Fuel with air in a combustion chamber, which by at least an air intake through the air and through several burners the fuel are supplied, each burner having an associated one Delay time, which corresponds to a period of time, after which an acoustic pulse in the combustion chamber thermal impulse in the combustion of this burner fuel supplied.
  • the invention relates also a corresponding device for combustion of fuel with air.
  • the invention relates in particular to a method and a device of the type mentioned for use in a gas turbine, a gas turbine being a composite of a Compressor for air, comprising a combustion device at least one combustion chamber for burning a fuel in the air with the formation of a flue gas and a turbine in the true sense to relax the flue gas is.
  • the turbine can be made up of several parts, i.e. several series connected Partial turbines include; the same applies to the compressor.
  • the compressor is in particular a turbo compressor.
  • the turbine drives as part of common practice the compressor.
  • the invention relates to the task of damping or avoiding acoustic vibrations in a combustion chamber, which Vibrations induced by the combustion and as "Burning vibrations" are known.
  • thermodynamic operating parameters such as air ratio and thermal power
  • unstable operating conditions are due to correlated fluctuations in heat production with the combustion and the static pressure in the combustion chamber and / or in this upstream and downstream parts of the system. These fluctuations are expressed in that in the Combustion chamber self-excited acoustic vibrations occur. These acoustic vibrations cause an increased one Noise pollution in the vicinity of the affected plant increased mechanical and thermal stresses on the combustion chamber and other parts of the system which are quite short Time can lead to complete or partial failure.
  • a combustion vibration is generally based on one Interaction between the flow of the used Burner escaping reactants and energy turnover when burning, the interaction being related with one in the combustion chamber and connected system parts occurring acoustic resonance a stable acoustic Vibration generates and maintains.
  • the training and maintenance of acoustic The energy required for vibration comes from the combustion process delivered itself.
  • Derivable from the Rayleigh criterion is also a criterion which is the period of an acoustic vibration, for which discusses the possibility of their occurrence in a relationship relies on a burner and its operation essential characterizing "delay time".
  • This delay time is a time period after which an acoustic pulse in the Combustion chamber to which the burner is connected, one thermal impulse during the combustion of the burner fuel supplied. Relating to one in the Combustion chamber stable vibration and one of these thermal vibration caused by the burner, ie a periodic fluctuation in energy turnover at combustion caused by the burner corresponds to the delay time a phase difference between the acoustic and thermal vibration. It is important to point this out to Büchner's thesis, pp.
  • the delay time of a burner in a combustion chamber sets composed of different summands, each based on individual components of the system from burner, combustion chamber and Flame are traceable.
  • the on the burner and the combustion chamber Available summands are mainly determined due to the geometry of the burner and combustion chamber; one on the Flame itself is a summand that is essentially recyclable determines the properties of the combustion itself.
  • the summand itself can be further broken down into a "convective Delay Time ", which is a transportation time for the transportation of the Reaction partner to the flame front, where the combustion begins, characterized a "heating time” which the Time for the reactants to heat up for ignition indicates the required temperature, and a “reaction kinetic delay time", which is due to the expiry the combustion itself is determined.
  • the convective delay time clearly shows the other two summands.
  • the conventional passive measures to suppress Combustion vibrations aim to operate the System by shifting the acoustic properties of Stabilize subsystems so that the entire desired Operating area no more combustion vibrations occur. These measures require funds in individual cases have to be adapted to the respective system and continuously involve the risk that known unstable operating points stabilized, however new instabilities under other operating conditions.
  • DE 43 36 096 A1 describes a device for reducing Vibrations in combustion chambers specified.
  • several burners arranged in front of the combustion chamber, with adjacent burners each in the direction of flow predetermined distance from each other are. This predetermined distance is chosen so that when the burner is in operation in the direction of flow spreading temperature fluctuations of neighboring burners straight are opposite.
  • This predetermined distance is chosen so that when the burner is in operation in the direction of flow spreading temperature fluctuations of neighboring burners straight are opposite.
  • This is said to be a combustion vibration induced by temperature fluctuations and thus prevent pressure fluctuations due to different densities.
  • the object of the invention to create new passive ones Specify measures on a combustion chamber with several burners, which reliably suppresses combustion vibrations are suitable.
  • the measures should both independent for liquid as well as for gaseous fuels of apparatus and functional details of the Combustion chamber applicable. There should be no moving parts or other active components are used.
  • the invention should be both a corresponding procedure as well specify an appropriate facility.
  • the invention is based on the knowledge that it is in a Combustion chamber, as is usually used in a gas turbine is and usually several similar burners has, by interaction of the burner to a reinforced Excitation of combustion vibrations can come.
  • Form thermal vibrations occur with only one burner in interaction with acoustic vibrations in the combustion chamber off, this one burner excites every other burner also starts to vibrate in the combustion chamber.
  • This effect is expressed, for example, in the fact that it is in a combustion chamber with several, similar burners each with sharp transitions between operating states with or without combustion vibrations gives. Since combustion vibrations occur always start from several burners, such combustion vibrations very high amplitudes were also observed.
  • the invention provides burners with different acoustic properties, d. H. especially different Delay times to be provided. This allows the Do not excite burners among themselves and it can also Always a damping effect based on a stable working burner.
  • the method is used in a case where everyone Burner is assigned an associated air inlet through which associated air inlet the air in an associated Current is supplied to the combustion chamber, designed so that the associated currents of the burners differ considerably from one another are. This ensures that the respective Operation of the burner characterizing thermodynamic Relationships are certainly different from each other and the difference in the delay times between the burners is guaranteed.
  • each Burner is assigned an associated air inlet through which the air is supplied to the combustion chamber in an associated stream is characterized in that the burner in are designed essentially the same among each other, and on each apart from an associated air inlet, the associated stream is throttled so that all associated currents are essential are different from each other.
  • the associated flow throttled may be associated with each Air inlet the associated flow throttled; this may be desirable to give the stream certain desirable properties to give, e.g. to homogenize him.
  • each burner is assigned an associated air inlet is through which the air flows into an associated stream Combustion chamber is guided, and the associated streams are geometrically similar to each other, is characterized by that the burners are geometrically similar to one another, however are different sizes.
  • This configuration is also in With regard to an appropriate facility of interest, since this configuration at least allows one for the burners to provide only shape and this for the production of the different Simply scale the burner differently. The difference in the delay times remains guaranteed because the delay time of a burner is not by itself determines its geometry and is therefore not scale-invariant.
  • each burner's fuel is supplied in such a way that a mixing ratio specified for all burners between a rate of fuel supplied and a rate of through the associated air intake supplied air is observed.
  • This configuration is of particular interest because it allows everyone Burner in terms of total combustion desired thermal performance optimal with regard to a always operate undesirable production of nitrogen oxides.
  • the design requires an appropriately upgraded one Fuel supply.
  • each burner Fuel is supplied at a rate specified for all burners becomes. While this means that individual burners are under Maybe not optimal with regard to the production of Nitrogen oxides are operated, but what with regard to simple fuel supply may be acceptable.
  • the method for use in is of particular importance Relation to a combustion chamber that is resonant for one acoustic vibration with a certain period, whereby the associated delay time of each burner between one integer multiples minus a quarter and the integer Multiples plus a quarter of the period. This corresponds to the adherence to that of Herrmann et al as well Büchner criterion derived from the Rayleigh criterion between the delay time and the period in question taken acoustic vibration.
  • the term "Integer multiple" also includes zero. It it goes without saying that the delay time is by definition not negative Can assume values.
  • combustion chamber should be resonant for a certain acoustic vibration should not be construed as a limitation that for this resonance can only determine the combustion chamber alone may; it goes without saying that the combustion chamber as a rule Part of a more or less complex overall acoustic system is, the resonance with all essential parameters is defined by the overall acoustic system.
  • An embodiment of the process is also of particular interest in that the fuel with in each burner the air is mixed before being burned in the combustion chamber becomes.
  • the Premix combustion is of particular interest, because they are at lower temperatures than those with simpler ones Diffusion combustion to be effected expires and therefore significantly less than diffusion combustion for production of nitrogen oxides.
  • the invention also compensates for the thermodynamic-acoustic problems mentioned at the beginning premix combustion.
  • the process of any configuration is particularly excellent for use on a gas turbine, the air is provided from a compressor and flue gas, which in the combustion chamber is created by the fuel in the Air is burned and fed to a turbine.
  • a preferred further development of the facility is emerging characterized in that the burners differ geometrically from one another are.
  • the burners in the device are geometric right next to each other, and the fuel supply is set up to supply the fuel to the burners with respective Guess which rates are significantly different from each other are.
  • Another alternative is characterized in that everyone Burner is assigned an associated air inlet, and on a throttle for everyone except one, or on each burner Throttling a flowing through the associated air inlet Current of the air is provided.
  • a choke can for example, an aperture upstream of the burner.
  • a further development of the device is particularly preferred in that the combustion chamber is resonant for an acoustic Vibration with a certain period, and that the associated delay time between one for each burner integer multiples minus a quarter and the integer Multiples plus a quarter of the period lies.
  • the device is particularly preferred for use on a Gas turbine, the combustion chamber between a compressor and a turbine of the gas turbine is arranged.
  • an asymmetrical arrangement if possible the burner is preferred. Like the asymmetrical arrangement can look in individual cases, and according to which criterion a "Sufficient asymmetry" can be determined, remains for everyone In individual cases, at the discretion of those who are relevant and active Leave person.
  • the main one to be observed Principle boils down to an acoustic vibration is usually characterized by a more or less symmetrical arrangement of standing acoustic waves in the vibrating overall system.
  • a combustion oscillation observed on an annular combustion chamber which was characterized by acoustic Waves that closed around the annular combustion chamber.
  • the wavelength of the acoustic vibrations corresponded to this half an average circumference of the annular combustion chamber. To suppress such a vibration, it would be advantageous in the arrangement of the burners two-fold or four-fold To avoid symmetries.
  • the invention does not require that there be none in the combustion chamber may give two burners with identical properties; the Purpose of the invention can be served with a Combustion chamber to which of several types of burners each several burners are connected.
  • a gas turbine with two silo combustion chambers conventional type, each of which is the same as six Burner for the combustion of heating oil exhibited when operating under 80% of the nominal load relevant for the design acoustic Vibrations with amplitudes of 100 mbar observed.
  • These acoustic vibrations could be eliminated by against each of the six burners in each silo combustion chamber slightly modified burners were replaced.
  • the modified Burners were designed so that they operate at nominal load Received 8% less fuel than the unchanged burners.
  • the modified burners were used so that they each included an unchanged burner between them.
  • the modified configuration of the burners allowed operate the gas turbine up to 100% of its nominal load, without acoustic vibrations occurring at a noticeable height.
  • FIG. 1 shows a gas turbine with a compressor 1 and one Turbine 2, which drives the compressor 1 via a shaft 3.
  • Compressed air passes from the compressor 1 an air line 4 to the combustion chamber 5 and enters it through air inlets 6, each of which is assigned to a burner 7 is, each burner 7 in a rear wall 8 of the combustion chamber 5 is arranged in the combustion chamber 5.
  • the burners 7 are from a tank 9 via a pump 10 and a fuel line 11, which branches in front of the burners 7, fueled. This fuel burns in the Combustion chamber 5 with the one supplied via the air line 4 Air.
  • the combustion chamber 5 is capable of acoustic vibrations Form and can, if necessary as part of a overall system capable of acoustic vibrations, which, for example combustion chamber 5, one of them to turbine 2 leading flue gas line 13 and possibly the air line 4 and the fuel line 11 are considered.
  • Acoustic vibrations in the combustion chamber 5, which alone or vibrates as part of such an overall system, can be caused by fluctuations in the combustion of the fuel be stimulated and maintained; in such a Fall one speaks of combustion vibrations.
  • Such combustion vibrations can become so strong that the combustion chamber 5 and other parts of the gas turbine may be damaged can.
  • Burner 7 designed differently from one another. This leads to to the fact that not all burners 7 have the same relevant properties have, and in particular that the respective Delay times characterizing the combustion process differ are from each other. That way it is with the Configuration according to FIG 1 in any case excluded that the Burner 7 collectively stimulate combustion oscillation.
  • the burners 7 in FIG. 1 are shown as so-called diffusion burners, since they put the fuel directly into the combustion chamber 5 inject.
  • the fuel can only in the combustion chamber 5 mix with the supplied air what experience has shown that diffusion takes place.
  • Diffusion burner are simple and can be operated relatively easily, but they are the most concerned with the production of nitrogen oxides complicated premix burners, which are still based on FIG be explained, inferior.
  • FIG. 2 shows a plan view of the rear wall 8 of a combustion chamber 5, seen in the direction in which the air flows to the combustion chamber 5.
  • five burners 7, all of which are essentially identical to one another are designed.
  • Each burner 7 has a number of Swirl blades 14, which one of the air that passes through it Imprint swirl. Such a twist is beneficial for that Combustion itself and for the intimate mixing of the fuel with the air.
  • the swirl blades 14 Provided in the swirl blades 14 are the nozzles 12 from which the fuel gets into the air, before it flows into the combustion chamber 5 and the Fuel can ignite. Accordingly, those in FIG. 2 illustrated burner 7 so-called "premix burner".
  • a premix burner brings a mixture of fuel and air with defined Composition for combustion, so that a much more sensitive Control of the combustion than with a diffusion burner, where the process of mixing fuel and air is practically not controllable, is possible. It also runs Combustion in a premix burner at significantly less Maximum temperatures than with a diffusion burner, which is advantageous for avoiding the production of nitrogen oxides is.
  • the blades 14 surround a hub 15; this hub 15 can serve to supply fuel to the nozzles 12 to lead.
  • FIG. 3 shows a longitudinal section through a combustion chamber 5 together with their rear wall 8 and two burners 7.
  • the burners 7 are again designed as a premix burner.
  • Each burner 7 shows three nozzles 12 for supplying fuel, all of which the hub 15 are arranged. Arrived from two of these nozzles the fuel between the swirl blades 14 so that it with the air flowing through it is mixed.
  • a nozzle 12 is immediate facing the interior of the combustion chamber 5.
  • This nozzle 12 forms a so-called "pilot flame” in which one Combustion takes place in the manner of a diffusion burner; this pilot flame is used to burn the between generated the swirl blades 14 and usually a clear one Excess of oxygen-containing mixture Stabilize air and fuel. This allows the Production of heat by the burner 7 within wide limits regulate.
  • the two premix burners are geometrically similar to each other, d. H. that they are only in their size, but not in theirs Differentiate proportions. This also results in a difference the relevant operating parameters, which for Exclusion of interaction of these burners 7 in the excitation a combustion vibration in the combustion chamber 5 is used becomes.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

L'invention concerne un procédé et un dispositif pour la combustion d'un combustible avec de l'air dans une chambre de combustion (5), l'alimentation en air se faisant par au moins une entrée d'air (6) et l'alimentation en combustible se faisant par une pluralité de brûleurs (7). Chaque brûleur (7) présente un temps de retard approprié correspondant à une durée après laquelle une impulsion acoustique dans la chambre de combustion (5) provoque une impulsion thermique lors de la combustion du combustible acheminé par l'intermédiaire de ce brûleur. L'alimentation en combustible est commandée par l'intermédiaire des brûleurs (7), de telle façon que les temps de retard de ces brûleurs soient sensiblement différents entre eux. L'invention est applicable pour une chambre de combustion (5) d'une turbine à gaz (1, 2, 3, 4, 5, 13).

Claims (17)

  1. Procédé de suppression d'oscillations de combustion lors de la combustion de combustible et d'air dans une chambre (6) de combustion, à laquelle l'air est apporté par au moins une entrée (6) d'air et le combustible par plusieurs brûleurs (7), chaque brûleur (7) ayant son propre temps de retard qui correspond à une durée après laquelle une impulsion acoustique provoque dans la chambre (5) de combustion une impulsion thermique lors de la combustion du combustible apporté par ce brûleur (7), caractérisé en ce que l'apport du combustible par le brûleur (7) et l'apport de l'air par l'entrée (6) d'air sont réglés de façon que les durées de retard des brûleurs (7) soient essentiellement différentes les unes des autres.
  2. Procédé suivant la revendication 1, dans lequel
    a) au brûleur (7) est associée une entrée (6) d'air par laquelle l'air en un courant associé est apporté à la chambre (5) de combustion ;
    b) les courants associés des brûleurs (7) sont sensiblement différents les uns des autres.
  3. Procédé suivant la revendication 1, dans lequel
    a) les brûleurs sont conformés sensiblement de la même façon les uns que les autres ;
    b) à chaque brûleur (7) est associée une entrée d'air, par laquelle l'air en un courant associé est apporté à la chambre (5) de combustion ; et
    c) à chaque entrée (6) d'air associée à l'exception d'une seule, le courant associé est étranglé de sorte que tous les courants associés sont sensiblement différents les uns des autres.
  4. Procédé suivant la revendication 1, dans lequel
    a) les brûleurs sont conformés sensiblement de manière identique les uns aux autres ;
    b) à chaque brûleur (7) est associée une entrée (6) d'air associée par laquelle l'air en un courant associé est apporté à la chambre (5) de combustion ; et
    c) à chaque entrée (6) d'air associé, le courant associé est étranglé, les courants associés étant différents les uns des autres.
  5. Procédé suivant la revendication 1, dans lequel
    a) les brûleurs sont géométriquement semblables les uns aux autres mais de dimensions différentes ;
    b) à chaque brûleur (7) est associée une entrée (6) d'air associée par laquelle l'air en un courant associé est envoyé dans la chambre (5) de combustion, les courants associés étant géométriquement semblables les uns aux autres.
  6. Procédé suivant l'une des revendications 1 à 5, dans lequel le combustible est apporté à chaque brûleur (7) de façon à maintenir un rapport de mélange prescrit pour tous les brûleurs (7) entre un débit du combustible apporté et un débit stoechiométrique correspondant à l'air apporté par l'entrée (6) d'air associée.
  7. Procédé suivant l'une des revendications 1 à 5, dans lequel le combustible est apporté à chaque brûleur (7) à un débit prescrit pour tous les brûleurs (7).
  8. Procédé suivant l'une des revendications précédentes, dans lequel la chambre (5) de combustion est résonnante pour une oscillation acoustique ayant une période déterminée et dans lequel, pour chaque brûleur (7), la durée de retard associée est comprise entre un multiple entier moins un quart et le multiple entier plus un quart de la période.
  9. Procédé suivant l'une des revendications précédentes, dans lequel, dans chaque brûleur (7) le combustible est mélangé à l'air avant d'être brûlé dans la chambre (5) de combustion.
  10. Procédé suivant l'une des revendications précédentes, dans lequel l'air est préparé dans un compresseur (1) et dans lequel du gaz de fumée, qui se crée dans la chambre (5) de combustion pendant que le combustible est brûlé dans l'air, est envoyé à une turbine (2).
  11. Dispositif de combustion de combustible par de l'air, comprenant
    a) une chambre (5) de combustion, dans laquelle le combustible est brûlé avec de l'air ;
    b) au moins une entrée (6) d'air pour apporter l'air à la chambre (5) de combustion ;
    c) plusieurs brûleurs (7) d'apport du combustible à la chambre (5) de combustion, chaque brûleur (7) ayant une durée de retard qui correspond à une durée après laquelle une impulsion acoustique provoque dans la chambre (5) de combustion une impulsion thermique lors de la combustion du combustible apporté par ce brûleur (7) ;
    d) des moyens (9, 10, 11) d'apport du combustible aux brûleurs (7) ;
       caractérisé en ce que les durées de retard des brûleurs (7) sont sensiblement différentes les unes des autres.
  12. Dispositif suivant la revendication 11, dans lequel les brûleurs sont géométriquement différents les uns des autres.
  13. Dispositif suivant la revendication 11, dans lequel les brûleurs (7) sont géométriquement identiques les uns des autres et dans lequel les moyens (9, 10, 11) d'apport du combustible sont tels qu'ils apportent le combustible aux brûleurs (7) à des débits qui sont sensiblement différents les uns des autres.
  14. Dispositif suivant l'une des revendications 11 à 13, dans lequel à chaque brûleur (7) est associée une entrée (6) d'air correspondante et il est prévu, sur chaque brûleur (7) à l'exception d'un seul, un étranglement (16) pour étrangler un courant d'air passant dans l'entrée (6) d'air associée.
  15. Dispositif suivant l'une des revendications 11 à 13, dans lequel à chaque brûleur (7) est associée une entrée (6) d'air associée et sur chaque brûleur (7) il est prévu un étranglement (16) pour étrangler un courant d'air passant dans l'entrée (6) d'air associée.
  16. Dispositif suivant l'une des revendications 11 à 15, dans lequel la chambre (5) de combustion est résonnante pour une oscillation acoustique ayant une période déterminée et dans lequel, pour chaque brûleur (7), la durée de retard associée est comprise entre un multiple entier moins un quart et le multiple entier plus un quart de la période.
  17. Dispositif suivant l'une des revendications 11 à 16, dans lequel la chambre (5) de combustion est montée dans une turbine (1, 2, 3, 4, 5, 13) à gaz entre un compresseur (1) et une turbine (2).
EP97941847A 1996-09-16 1997-08-28 Procede pour la suppression des oscillations de combustion et dispositif pour la combustion d'un combustible avec de l'air Expired - Lifetime EP0925472B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19637725 1996-09-16
DE19637725 1996-09-16
PCT/DE1997/001881 WO1998012478A1 (fr) 1996-09-16 1997-08-28 Procede et dispositif pour la combustion d'un combustible avec de l'air

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EP0925472A1 EP0925472A1 (fr) 1999-06-30
EP0925472B1 true EP0925472B1 (fr) 2001-04-04

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US (1) US6052986A (fr)
EP (1) EP0925472B1 (fr)
JP (1) JP4249263B2 (fr)
DE (1) DE59703302D1 (fr)
RU (1) RU2186298C2 (fr)
WO (1) WO1998012478A1 (fr)

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DE19939235B4 (de) * 1999-08-18 2012-03-29 Alstom Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
GB0019533D0 (en) 2000-08-10 2000-09-27 Rolls Royce Plc A combustion chamber
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
US6931853B2 (en) * 2002-11-19 2005-08-23 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
EP1493972A1 (fr) * 2003-07-04 2005-01-05 Siemens Aktiengesellschaft Ensemble de brûleur pour une turbine à gaz et turbine à gaz
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EP0925472A1 (fr) 1999-06-30
DE59703302D1 (de) 2001-05-10
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WO1998012478A1 (fr) 1998-03-26
RU2186298C2 (ru) 2002-07-27
JP4249263B2 (ja) 2009-04-02

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