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EP2179222B2 - Brûleur pour une chambre de combustion d'un turbogroupe - Google Patents
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EP2179222B2 - Brûleur pour une chambre de combustion d'un turbogroupe - Google Patents

Brûleur pour une chambre de combustion d'un turbogroupe Download PDF

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Publication number
EP2179222B2
EP2179222B2 EP08775142.6A EP08775142A EP2179222B2 EP 2179222 B2 EP2179222 B2 EP 2179222B2 EP 08775142 A EP08775142 A EP 08775142A EP 2179222 B2 EP2179222 B2 EP 2179222B2
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EP
European Patent Office
Prior art keywords
burner
lance
interior
channel
outlet opening
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.)
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Application number
EP08775142.6A
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German (de)
English (en)
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EP2179222A2 (fr
EP2179222B1 (fr
Inventor
Jaan Hellat
Adnan Eroglu
Jan Cerny
Douglas Anthony Pennell
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
Priority date (The priority date 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 date listed.)
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Publication date
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Application filed by Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Publication of EP2179222A2 publication Critical patent/EP2179222A2/fr
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Publication of EP2179222B1 publication Critical patent/EP2179222B1/fr
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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
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • 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
    • F23C2900/07021—Details of lances
    • 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
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention relates to a burner for a combustion chamber of a turbo group, in particular in a power plant, according to the preamble of claim 1.
  • the DE 103 45 137 A1 shows an injection device intended for gas turbines, which is designed in the manner of a lance and protrudes in a self-supporting manner into a burner.
  • Axial discharge openings for fuel and air are provided at the free end of the lance in such a way that a fuel jet encased by a flow of shielding air is generated.
  • the temperature changes occurring at the injection device are used. In this way, an automatic adaptation to different operating states is to be achieved in such a way that optimal operation is continuously maintained.
  • this publication indicates that it is known to provide aerodynamic methods for flame stabilization, reference being made to swirl currents. It is emphasized that the entire flow in swirl-stabilized burners reacts extremely sensitively to changes in the flow field.
  • a fuel injector for gas turbines is known.
  • the injector has a rod-like end piece which is arranged on the head of a vortex chamber essentially coaxially to the longitudinal axis of this chamber. On the outlet side, this vortex chamber opens into a combustion chamber.
  • the aforementioned end piece of the injector has, on the one hand, axial outlet openings through which fuel can be ejected as a liquid jet, and, on the other hand, discharge openings are provided through which the fuel can be ejected as an evaporating liquid jet.
  • the EP 0 704 657 A2 relates to a burner for gas turbines or the like.
  • this burner consists of a swirl generator and an axially adjoining mixing section, with a special transition geometry being provided at the beginning of a mixing tube such that a swirling flow passes through the mixing tube.
  • film-laying bores are arranged in the wall of the mixing section, which bring about an increase in the flow velocity along the pipe wall.
  • the mixing section opens into a combustion chamber, in which a return flow zone is formed in the area of a jump in cross section between the mixing section and the combustion chamber, which is intended to act as a flame holder.
  • a central fuel nozzle for injecting an in particular liquid fuel into the swirl generator is arranged in a cylindrical initial part upstream of the swirl generator.
  • the DE 10 2005 015 152 A1 relates to a premix burner for a gas turbine combustor.
  • This burner comprises an oxidizer supply device for supplying a gaseous oxidizer into a mixing space, to which gaseous fuel is supplied by means of a gas fuel supply device and liquid fuel is supplied by means of a liquid fuel supply device.
  • the liquid fuel supply device has a plurality of injection holes communicating with a main supply line, which are designed so that the spray jet generated has a component radial to a main outflow direction of the burner.
  • a method for operating a premix burner is described. This has different groups of injection openings for premix fuel as well as a central fuel injection with several injection openings. In this case, different groups of the injection openings are acted upon with gaseous fuel independently of one another in order to form a premix stage on the one hand and a diffusion stage of the premix burner on the other hand. The result is an extended operating range of the premix burner with low pollutant emissions.
  • burners of the type specified at the beginning have the problem of flashback from the combustion chamber into the interior of the burner.
  • the invention deals with the problem, for a burner of the in EP 704657 mentioned type to provide an improved embodiment, which is characterized in particular by an increased stability of the combustion process in the combustion chamber.
  • the invention is based on the general idea of making the lance significantly longer so that it can protrude deeper into the interior of the burner in the direction of the outlet opening.
  • the knowledge is used that a velocity profile develops in the mixer for the mixture flow, that in the center has significantly higher speeds than in the edge area.
  • a flame front which occurs during operation of the combustion chamber as a result of the combustion reaction, at least partially extends into the interior of the burner. This is due to the reduced flow velocity in the center of the velocity profile in the mixer.
  • the stationary flame front can run partially inside the burner. This is beneficial in several ways. On the one hand, the targeted introduction of fuel into the flame front can be improved with the aid of the lance, since the distance between the free-standing lance end and the flame front is reduced.
  • the lance has a plurality of concentrically arranged tubes on a central inner tube which contains a central channel for liquid fuel and has at least one axial outlet opening at the end of the lance.
  • a hollow-walled outer tube is provided which encloses the inner tube with the formation of an inner annular channel and contains at least one outer channel for gaseous fuel in its hollow wall.
  • the inner ring channel ends axially open at the end of the lance and is used to guide air. Due to the proposed construction with concentric tubes, on the one hand liquid fuel and on the other hand gaseous fuel can be fed alternately or simultaneously via the lance. At the same time, the air flow through the ring channel enables the lance to be cooled.
  • the air flow through the inner ring channel makes flushing of the central channel or the at least one outer channel unnecessary if only gaseous or only liquid fuel is supplied via the lance.
  • a media separation between liquid fuel and gaseous fuel can be achieved at least up to the flame front. This can be advantageous for realizing a stable combustion reaction.
  • a burner 1 comprises a swirl generator 2, a mixer 3 and a lance 4.
  • the burner 1 forms part of a combustion chamber, otherwise not shown here, of a turbo group, which is in particular arranged in a power plant.
  • the swirl generator 2 encloses an inlet-side section of a burner interior 5 and has at least one air inlet 6 which extends tangentially with respect to a longitudinal center axis 7 of the burner 1.
  • the swirl generator 2 is designed to be conical.
  • the respective air inlet 6 forms a longitudinal slot along the cone jacket.
  • a plurality of such air inlets 6 are preferably arranged distributed in the circumferential direction. As a result, the air can penetrate tangentially into the burner interior 5, as a result of which it is subjected to a swirl.
  • the swirl generator 2 also has a fuel inlet 8, via which gaseous fuel can be introduced into the burner interior 5.
  • this fuel inlet 8 consists of several rows of individual inlet openings running along the surface line of the conical swirl generator 2, through which the fuel gas can enter the burner interior 5.
  • the Fuel inlet 8 be aligned tangentially in order to increase the swirl effect.
  • the fuel inlet 8 can also generate a certain radial component in order to improve the mixing with the air.
  • the mixer 3 encloses an outlet-side section of the burner interior 5 and has an outlet opening 9 which is open to a combustion chamber 10 of the combustion chamber.
  • the mixer 3 comprises, for example, a tubular body 11 which is connected to the swirl generator 2 via a tubular transition piece 12 and which has an outlet flange 13 with the outlet opening 9.
  • the burner 1 can be connected to the combustion chamber via the outlet flange 13.
  • the mixer 3 is expediently cylindrical in shape.
  • the lance 4 is used to introduce pilot fuel into the combustion chamber 10.
  • the lance 4 is arranged coaxially to the longitudinal center axis 7.
  • the lance 4 extends, at least in a pilot mode of the burner 1, from a burner head 14, which essentially forms the tip of the conical swirl generator 2, into the burner interior 5.
  • the lance 4 thus starts from the burner head 14 and ends with a lance end 15 free-standing in a section of the burner interior 5 enclosed by the mixer 3 at a distance 17 from the outlet opening 9 which is greater than 25% and less than 50% of the distance 18, which has an outlet-side end 19 of the swirl generator 2 from the outlet opening 9.
  • the embodiment shown also shows part of a flame front 16 which is formed during operation of the combustion chamber as a result of the combustion reaction taking place in the combustion chamber 10. It can be seen that part of this flame front 16 protrudes into the interior of the burner 5, specifically into an end section of the interior of the burner 5, which is enclosed by an end region of the mixer 3 on the outlet side. In the example shown, the flame front 16 remains within the section of the burner interior 5 that is enclosed by the outlet flange 13. or arrangement of the lance 4 is achieved. In the pilot operation of the burner 1, the lance 4 extends with its free-standing end 15 comparatively far into the burner interior 5, namely to the extent that part of the flame front 16 extends into the burner interior 5.
  • the lance 4 can protrude so deep into the burner interior 5 in the direction of the outlet opening 9, the lance 4 must be designed accordingly so that it has the axial length required for this.
  • the lance 4 is positioned in the burner 1 in such a way that its free-standing end 15 is located in a section of the burner interior 5 enclosed by the mixer 3. In other words, the lance 4 extends into the mixer 3.
  • the lance 4 extends with its free-standing end 15 in the axial direction up to about half of the mixer 3 or even beyond it into the mixer 3.
  • the registered distance 17 that the free-standing lance end 15 has from the outlet opening 9 is greater than 25% and smaller than 50% of the distance 18 that the outlet-side end 19 of the swirl generator 2 has from the outlet opening 9.
  • an inlet pipe 20, which extends coaxially to the lance 4, can be arranged on the burner head 14.
  • This inlet pipe 20 protrudes in the axial direction into a section of the burner interior 5 enclosed by the swirl generator 2.
  • This inlet pipe 20 can form an annular inlet channel 21 for liquid fuel.
  • the inlet channel 21 has at least one axially oriented outlet opening 22. Through this at least one axial outlet opening 22, the liquid fuel can enter the burner interior 5 in accordance with arrows 48, essentially in the axial direction.
  • the burner 1 can thus be operated with fuel gas and / or with liquid fuel.
  • a plurality of such axial outlet openings 22 are preferably arranged at the end of the inlet pipe 20 which ends in the burner interior 5.
  • the lance 4 can be arranged on the burner head 14 so as to be adjustable in the axial direction.
  • the axial position of the free-standing lance end 15 within the burner interior 5 can thus be adjusted.
  • the position of the part of the flame front 16 protruding into the burner interior 5 can thereby be adjusted.
  • the burner 1 can be adapted to the operating parameters of the combustion chamber, which enables the combustion process to be stabilized.
  • the lance 4 can thus be moved more or less deeply into the burner interior 5 or extended more or less far out of the burner interior 5, depending on requirements.
  • Fig. 3 shows a situation in which the lance 4 is largely extended out of the burner interior 5.
  • the lance end 15 then expediently ends on the inside of the burner head 14 facing the burner interior 5 Fig. 3 the lance 4 is fully extended to simplify the illustration. It can be moved back into the burner interior 5 according to an arrow 23.
  • the flame front 16 is arranged completely outside the burner interior 5 and is located downstream of the outlet opening 9 with respect to the flow direction of the burner 1.
  • a speed profile 24 is shown in simplified form, which represents the distribution of the flow speed along the cross section of the burner 1 within the mixer 3. It can be seen that if there is no lance 4 in the center, the flow has a significant maximum. By moving the lance 4 into the described area within the mixer 3, the flow velocity in the center of the cross section of the mixer 3 is inevitably reduced. At the same time, the speed is thereby outside the lance 4, that is to say in the edge region of the cross section increased accordingly to ensure a constant volume flow. The reduction in the central flow velocity enables the flame front 16 to migrate upstream. With the appropriate positioning and configuration of the lance 4, the flame front 16 partially protrudes into the burner interior 5, as shown in FIG Fig. 1 is shown.
  • the lance 4 is also shown in section. The following detailed description of the lance 4 also applies in particular to the embodiments of FIG Figs. 1 to 3 .
  • the lance 4 has several tubes arranged concentrically to one another, namely a central inner tube 25 and an outer tube 26.
  • the inner tube 25 contains a central channel 27 and has axially oriented outlet opening 28 arranged at least on the free-standing lance end 15.
  • the central channel 27 serves to supply liquid fuel to the at least one outlet opening 28.
  • the inner tube 25 is equipped with a nozzle-shaped cross-sectional constriction 29 in the area of the outlet opening 28, which enables the formation of an intense liquid jet.
  • This jet of liquid fuel is in the Fig. 4 and 5 indicated by an arrow 32.
  • the outer tube 26 is dimensioned such that it encloses the inner tube 25 while forming an inner annular channel 30.
  • This inner ring channel 30 is axially open at the lance end 15 and thus opens into the burner interior 5.
  • the inner ring channel 30 is used to guide air, which can exit from the inner ring channel 30 in the axial direction according to an arrow 31.
  • the outer tube 26 is designed with a hollow wall, that is, the outer tube 26 has a hollow wall 33 with an inner wall 34 and an outer wall 35 radially spaced therefrom.
  • the outer tube 26 contains at least one outer channel 36 ( Fig. 4 ) or 37 ( Fig. 5 ).
  • This at least one outer channel 36, 37 serves to supply gaseous fuel.
  • the outer channel 36, 37 can be designed as an annular channel which is simply formed between the two walls 34, 35 of the wall 33.
  • This outer ring channel 36 or 37 can according to Fig. 4 have at least one axially oriented outlet opening 38 at the lance end 15, whereby a substantially axially oriented injection of fuel gas according to an arrow 39 can be achieved.
  • an in Fig. 5 Lance end section 40 which is marked with a curly bracket and which has the free-standing lance end 15, an arrangement of several radial outlet openings 41 can be provided. These radial outlet openings 41 are preferably formed in the outer wall 35 of the hollow wall 33 of the outer tube 26.
  • a corresponding control can be provided which works, for example, with a sleeve-shaped control element that is located in a first position in front of the radial outlet openings 41, while in a second position it blocks the at least one axial outlet opening 38.
  • a plurality of axial outlet openings 38 distributed in the circumferential direction are preferably arranged at the axial end of the outer tube 26.
  • At least one first outer channel 36 can be formed in the hollow wall 33, which leads at the lance end 15 to the at least one axial outlet opening 38.
  • at least one second outer channel 37 can be formed in the hollow wall 33, which leads to at least one of the radial outlet openings 41 formed in the lance end section 40.
  • Fig. 4 shows, for example, a section through the first outer channels 36
  • Fig. 5 shows a section through the second outer channels 37.
  • the first and second outer channels 36, 37 can be connected on the input side to different, independently operable supply devices or control devices. This makes it possible to introduce the gaseous fuel either through the at least one axial outlet opening 38 or only through the at least one radial outlet opening 41 or both through the at least one axial outlet opening 38 and through the at least one radial outlet opening 41.
  • the inner tube 25 protrudes axially beyond the outer tube 26. In this way, a certain media separation can be achieved during operation of the lance 4 for injecting the liquid fuel and for injecting the fuel gas. This media separation can also be supported by the air 31 that is blown in.
  • the inlet pipe 20 arranged on the burner head 14 is also designed with a hollow wall, so that it has a hollow wall 43 with an inner wall 44 and an outer wall 45.
  • the hollow-walled inlet pipe 20 is also dimensioned here in such a way that it encloses the lance 4 or the outer pipe 26 while forming an axially open annular channel 46. Air can be blown into the interior of the burner through this annular channel 46 in accordance with an arrow 47. In this way, effective cooling of the lance in the area of the burner head 14 can be achieved.
  • the inlet channel 21, which is used to introduce the liquid fuel according to arrows 48, is formed in the hollow wall 43 and can in particular also be configured in an annular manner.
  • a wall 49 of the mixer 3 is equipped with a film cooling 50.
  • a film cooling 50 is implemented, for example, by means of several cooling bores 51, which penetrate the corresponding wall 49 and can be flowed through by coolant, which is applied to the side of the wall 49 facing the burner interior 5 and thereby generates a cooling film protecting the wall 49. Air is usually used as the coolant.
  • the cooling bores 51 can be made in the main flow direction of the burner 1 in order to improve the formation of a cooling film.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)

Claims (8)

  1. Brûleur pour une chambre de combustion d'un turbogroupe, comprenant au moins un générateur de tourbillonnement (2), un mélangeur (3) et un dispositif d'injection de combustible sous forme d'une lance (4), qui introduit de l'air et des combustibles dans un intérieur de brûleur (5) pour une réaction de combustion se déroulant dans une chambre de combustion (10), dans lequel le générateur de tourbillonnement (2), qui entoure l'intérieur de brûleur (5) côté entrée, présente au moins une entrée d'air (6) tangentielle par rapport à un axe longitudinal médian (7), et le mélangeur (3), qui entoure l'intérieur de brûleur (5) côté sortie, présente une ouverture de sortie ouverte en direction de la chambre de combustion (10), et la lance (4) disposée de manière coaxiale par rapport à l'axe longitudinal médian (7) pour l'introduction de combustible pilote dans un mode pilote du brûleur (1) s'étend à partir d'une tête de brûleur (14) dans l'intérieur de brûleur (5), caractérisé en ce que la lance (4) s'étend au moins dans le mode pilote du brûleur (1) si loin dans l'intérieur de brûleur (5) qu'un front de flamme (16) de la réaction de combustion se déroulant dans la chambre de combustion (10) s'étend au moins en partie jusque dans une partie d'extrémité de l'intérieur de brûleur (5) entourée par une zone d'extrémité côté sortie du mélangeur (3), du fait que la lance (4) est disposée au moins dans le mode pilote du brûleur (1) avec son extrémité côté sortie (15) dans une partie de l'intérieur de brûleur (5) entourée par le mélangeur (3) et une distance (17) de l'extrémité de lance (15) par rapport à l'ouverture de sortie (9) est supérieure à 25 % et inférieure à 50 % de la distance (18) qu'une extrémité côté sortie (19) du générateur de tourbillonnement (2) présente par rapport à l'ouverture de sortie (9) -, et que la lance (4) présente plusieurs tubes (25, 26) disposés de manière concentrique, qu'un tube intérieur central (25) contient un canal central (27) pour un combustible liquide et présente au moins une ouverture de sortie (28) axiale à l'extrémité de lance (15), qu'un tube extérieur (26) à paroi creuse entoure le tube intérieur (25) avec formation d'un canal annulaire intérieur (30) et contient dans sa paroi creuse (33) au moins un canal extérieur (36, 37) pour un combustible gazeux, et que le canal annulaire intérieur (30) termine de manière ouverte axialement à l'extrémité de lance (15) et sert au guidage d'air.
  2. Brûleur selon la revendication 1, caractérisé en ce que la lance (4) est disposée sur la tête de brûleur (14) de manière réglable en longueur, de sorte qu'en fonction des besoins elle peut rentrer plus ou moins profondément dans l'intérieur de brûleur (5) et peut en sortir plus ou moins loin.
  3. Brûleur selon la revendication 1 ou 2, caractérisé en ce qu'un tube d'entrée (20), qui fait saillie de manière coaxiale par rapport à la lance (4) dans la partie de l'intérieur de brûleur (5) entourée par le générateur de tourbillonnement (2) et qui réalise un canal d'entrée annulaire (21) pour un combustible liquide, qui présente au moins une ouverture de sortie axiale (22), est disposé sur la tête de brûleur (14).
  4. Brûleur selon la revendication 3, caractérisé en ce que le tube d'entrée (20) est conçu avec une paroi creuse, que le tube d'entrée (20) entoure la lance (4) avec formation d'un canal annulaire (46) ouvert axialement pour l'air, et que le canal d'entrée (21) est réalisé dans la paroi creuse (43) du tube d'entrée (20).
  5. Brûleur selon la revendication 1, caractérisé en ce que le canal extérieur (36, 37) est conçu dans la paroi creuse (33) du tube extérieur (26) en tant que canal annulaire, qui présente à l'extrémité de lance (15) au moins une ouverture de sortie axiale (28), et/ou qui présente dans une partie d'extrémité de lance (40) présentant l'extrémité de lance (15) plusieurs ouvertures de sortie radiales (41).
  6. Brûleur selon la revendication 1, caractérisé en ce qu'au moins un (premier) canal extérieur (36), qui présente à l'extrémité de lance (15) au moins une ouverture de sortie axiale (28), est réalisé dans la paroi creuse (33) du tube extérieur (26), et/ou qu'au moins un (deuxième) canal extérieur (37), qui présente dans une partie d'extrémité de lance (40) présentant l'extrémité de lance (15) plusieurs ouvertures de sortie radiales (41), est réalisé dans la paroi creuse (33) du tube extérieur (26).
  7. Brûleur selon l'une quelconque des revendications 1 ou 5 à 6, caractérisé en ce que le tube intérieur (25) fait saillie axialement du tube extérieur (26).
  8. Brûleur selon l'une quelconque des revendications 1 à 7, caractérisé en ce qu'une paroi (49) du brûleur (3) est équipée d'un refroidissement pelliculaire (50).
EP08775142.6A 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe Active EP2179222B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007037289 2007-08-07
PCT/EP2008/059321 WO2009019113A2 (fr) 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe

Publications (3)

Publication Number Publication Date
EP2179222A2 EP2179222A2 (fr) 2010-04-28
EP2179222B1 EP2179222B1 (fr) 2014-10-22
EP2179222B2 true EP2179222B2 (fr) 2021-12-01

Family

ID=39865130

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08775142.6A Active EP2179222B2 (fr) 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe

Country Status (3)

Country Link
US (1) US8069671B2 (fr)
EP (1) EP2179222B2 (fr)
WO (1) WO2009019113A2 (fr)

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EP2225488B1 (fr) * 2007-11-27 2013-07-17 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
US8413446B2 (en) * 2008-12-10 2013-04-09 Caterpillar Inc. Fuel injector arrangement having porous premixing chamber
ES2400247T3 (es) 2008-12-19 2013-04-08 Alstom Technology Ltd Quemador de una turbina de gas que tiene una configuración de lanza especial
US20100175380A1 (en) * 2009-01-13 2010-07-15 General Electric Company Traversing fuel nozzles in cap-less combustor assembly
WO2011054739A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage
WO2011054760A1 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système de refroidissement permettant d'accroître le rendement d'une turbine à gaz
WO2011054771A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Brûleur à prémélange pour chambre de combustion de turbine à gaz
WO2011054757A2 (fr) * 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage avec lances à combustible
WO2013085411A1 (fr) * 2011-12-05 2013-06-13 General Electric Company Chambre de combustion multizones
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor
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WO2009019113A3 (fr) 2009-06-11
US8069671B2 (en) 2011-12-06
US20100146983A1 (en) 2010-06-17
WO2009019113A2 (fr) 2009-02-12
EP2179222A2 (fr) 2010-04-28
EP2179222B1 (fr) 2014-10-22

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