EP1864056B1 - Bruleur de premelange destine a une chambre de combustion de turbine a gaz - Google Patents

Bruleur de premelange destine a une chambre de combustion de turbine a gaz Download PDF

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Publication number
EP1864056B1
EP1864056B1 EP06725400.3A EP06725400A EP1864056B1 EP 1864056 B1 EP1864056 B1 EP 1864056B1 EP 06725400 A EP06725400 A EP 06725400A EP 1864056 B1 EP1864056 B1 EP 1864056B1
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EP
European Patent Office
Prior art keywords
injection
main
liquid fuel
injection orifices
premix burner
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Not-in-force
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EP06725400.3A
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German (de)
English (en)
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EP1864056A1 (fr
Inventor
Adnan Eroglu
Majed Toqan
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General Electric Technology GmbH
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Alstom Technology AG
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Publication of EP1864056A1 publication Critical patent/EP1864056A1/fr
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • 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

Definitions

  • the invention relates to a premix burner for a combustion chamber of a gas turbine, in particular in a power plant, at least comprising a mixing space limiting housing, an oxidant supply for supplying a gaseous oxidizer in the mixing chamber, a gas fuel supply for supplying a gaseous fuel into the mixing chamber and a liquid fuel supply means for feeding a liquid fuel into the mixing chamber, comprising a centrally disposed burner lance extending from a burner head into the mixing space, and an outlet opening for the exit of the fuel / air mixture.
  • a premix burner of the type mentioned is out EP 0 433 790 known.
  • the known burner has a built-up of several nested shells housing which surrounds a mixing chamber.
  • the staggered arrangement of the half-shells slots for tangentially supplying an oxidizer, in particular combustion air, formed in the mixing chamber.
  • a swirling flow is formed in the mixing chamber, which at the burner outlet due to a Cross-sectional jump becomes unstable and merges into an annular swirling flow with a backflow in the core. This backflow allows the stabilization of a flame front downstream of the burner outlet.
  • Within the inlet slots for the combustion air injectors are provided for injecting a gaseous fuel into the combustion air.
  • the burner is equipped with a central lance for supplying a liquid fuel which extends from the burner head into the mixing chamber.
  • the lance has at its free-standing, axial end an injection port through which the liquid fuel in the mixing chamber and in the combustion chamber arranged downstream of the combustion chamber of a combustion chamber can be injected.
  • the injection of the liquid fuel into the mixing chamber is parallel to the burner axis and the injection of the gaseous fuel into the combustion air parallel to the flow direction.
  • the arrangement of the outlet openings determines the quality of mixing of fuel and combustion air as well as the fuel distribution at the burner outlet. But these variables have a significant influence on the NO x emissions and extinguishing limit of the burner and its stability with regard to combustion pulsations.
  • the problem with the operation of premix burners, in particular those in connection with gas turbine plants, is the partial load range, since in this case only comparatively small amounts of fuel are added to the combustion air. In the complete mixing of the fuel with the entire combustion air but creates a mixture, which is just in the lower part load range is no longer flammable or only forms a very unstable flame. This leads to undesirable combustion pulsations or possible extinguishment of the flame.
  • One way to reduce these adverse effects is to deliver the entire required amount of fuel through the central lance.
  • the burner is then operated at very high air ratios as a diffusion burner. This results in high flame stability on the one hand, but also very high NO x emissions on the other hand.
  • This premix burner comprises a housing composed of a plurality of shells, a mixing space into which combustion air is introduced via tangentially arranged slots, which merges into a swirling flow in the mixing space, means for introducing fuel into the combustion air flow, these means being a first group substantially parallel to the first Burner axis aligned fuel outlet openings for a first fuel and at least a second group comprises substantially aligned parallel to the burner axis fuel outlet openings for a second fuel, wherein the first and the second group are acted upon independently, and these means are preferably arranged in the region of the combustion air inlet slots.
  • pilot fuel can also be introduced via a lance.
  • the burner can be operated exclusively with liquid fuel, there is the possibility to maintain or repair the gas fuel supply without the operation of the burner or the combustion chamber must be completely interrupted. This is advantageous for the efficiency of the gas turbine equipped therewith.
  • the injection of liquid fuel into the mixing chamber of the burner or in the combustion chamber of the combustion chamber usually to significantly increased flame temperatures, which is due for example to insufficient atomization, mixing and evaporation of the liquid fuel before its ignition. Increased flame temperatures, however, are accompanied by a disproportionately increased production of NO x emissions and soot.
  • a generic Vormischbrenner is the subject of EP 1 336 800 which is characterized in particular by measures to further reduce thermoacoustic vibrations within the combustion system and thus increased combustion stability.
  • This burner is based on the basic idea of stabilizing by means of fluidic measures the central backflow zone forming downstream of the burner outlet, within which the fuel / air mixture ignites.
  • the relatively far reaching into the mixing chamber central burner lance in its downstream end region with a widening cross section.
  • the lance has outlet openings for preferably liquid fuel and combustion air and the corresponding feed channels for these media.
  • the proximity of the introduction of fuel prevents the risk of the flame from migrating into the mixing space and, on the other hand, this proximity promotes the swirl breakdown of the fuel / air mixture which propagates in the direction of flow, with the result that the backflow zone is stabilized.
  • Different cross-sectional shapes of the end portion of the lance also affect, to varying degrees, the formation of coherent structures.
  • the far reaching into the mixing chamber injection of fuel has the disadvantage of a reduced mixing quality of the fuel / air mixture with the already mentioned elsewhere sequence of increased NO x emissions.
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, the object of the invention to provide for a generic burner, an improved embodiment, which is particularly comparatively inexpensive feasible and thereby allows a reduction of NO x emissions and soot formation.
  • the invention is based on the general idea, in a generic burner according to EP 1336800 providing the lance with at least one pilot injection hole and part of the injection holes of the liquid fuel, the injection holes (14) of the lance (6) being arranged in at least one row parallel to the main discharge direction (9), and a second liquid fuel supply means in the form of one of the oxidizer stream flow around the tube at least predominantly within or upstream of the inlet opening of the housing.
  • This design distributes the liquid fuel injection to several injection holes, reducing the flow rate at the single injection hole. In this way, the atomization effect of the individual injection holes can be improved. At the same time, this results in improved mixing and improved evaporation of the liquid fuel.
  • the arrangement of the injection holes in series and parallel to the main outflow direction inevitably results in a part of the injection holes being relatively far removed from the outlet opening of the mixing chamber.
  • the liquid fuel injected there has therefore an increased residence time in the mixing chamber, which favors the mixing and evaporation of the fuel.
  • Also particularly advantageous for the mixing and evaporation is the radial component of the main injection direction at the respective injection hole. Because this measure intensifies the mixing and evaporation of the liquid fuel.
  • the construction according to the invention thus results in a significant improvement in the atomization, the mixing and the evaporation of the liquid fuel. This delays the ignition of the liquid fuel and reduces the risk of locally excessive flame temperatures. As a result, NO x formation is reduced; In addition, less soot is produced. It is of particular advantage in this case that the described improvement of the emission values can be achieved without the liquid fuel being required for this purpose Water or steam or other diluent would have to be supplied. As a consequence, the burner according to the invention does not require water for operation with liquid fuel. The proportion of water in the liquid fuel (so-called " ⁇ value”) is therefore low and is preferably zero. Since no such diluent is needed for the operation of the burner with liquid fuel, corresponding facilities for the preparation of such a diluent accounted for. The cost of implementing such a burner are therefore comparatively low.
  • the admixing of the liquid fuel takes place within the tangential inlet opening of the mixing space or immediately upstream thereof.
  • This injection in conjunction with the turbulent swirl flow within the mixing space, leads to an intensive mixing of fuel and oxidizer. At the same time thereby extends the residence time of the injected liquid fuel, which also improves the mixing and especially the evaporation of the liquid fuel.
  • the injection of the liquid fuel is enabled by the second liquid fuel supply device via such a tube an optimal distribution of the injection of the liquid fuel along the respective inlet opening. This also supports the atomization, mixing and evaporation of the liquid fuel.
  • the said pipe can additionally be used to supply the same to the oxidator stream via the pipe upstream of the respective inlet opening for the operation of the burner with gas fuel.
  • the tube contains at least one gas fuel channel in addition to the liquid fuel channel.
  • the injected at this point gas fuel thus also has a particularly long residence time in the burner, which intensifies the mixing with the Oxidatorstrom.
  • the integration of the liquid fuel channel and the at least one gas fuel channel into a common tube thereby reduces the manufacturing cost of the burner.
  • a burner 1 according to the invention comprises a mixing space 3 delimited by a housing 2.
  • the burner 1 also has a burner head 4, which is arranged opposite an outlet opening 5 of the mixing space 3.
  • a lance 6 is mounted, which projects centrally into the mixing chamber 3.
  • the housing 2 is designed in the embodiments shown here so that the mixing chamber 3 has two inlet openings 7 for the oxidizer. These inlet openings 7 are arranged and designed so that forms a tangential inflow and thus a concentric vortex system for the mixing chamber 3.
  • This is achieved here by a half-shell construction of the housing 2, wherein the half-shells are arranged offset in their parting plane with respect to a longitudinal center axis of the housing 2 eccentrically to each other.
  • the housing 2 is formed substantially conically with a cross-section widening towards the outlet opening 5.
  • the conical design of the housing 2 is not mandatory. It may also be cylindrical, wherein it is expedient in such an embodiment of the housing 2, a conical to arrange tapered inner body within the mixing chamber 3, as in the cited above EP 1 292 795 is explained in more detail.
  • the burner 1 is used to supply a combustion chamber, not shown, of a gas turbine, in particular in a power plant, with an oxidizer-fuel mixture.
  • the burner 1 is connected to said combustion chamber, in such a way that the outlet opening 5 opens at a combustion chamber 8 of the combustion chamber.
  • the burner 1 is equipped with an oxidant supply device 10, which in the Fig. 1, 2, 3 symbolized by an arrow.
  • the Oxidatorzu slaughter 10 is used for supplying a gaseous oxidizer, usually air, in the mixing chamber 3.
  • the inventive burner 1 is designed for operation with liquid fuel, such as fuel oil.
  • the burner 1 has a first liquid fuel supply device 12, with the aid of which liquid fuel can be introduced into the mixing chamber 3.
  • This first liquid fuel supply device 12 is equipped with at least one main supply line 13, which supplies the liquid fuel to a plurality of injection holes 14. Through these injection holes 14, the liquid fuel can be introduced into the mixing chamber 3.
  • the injection holes 14 are arranged or distributed such that at least a plurality of injection holes 14 are arranged with respect to the main outflow direction 9 in at least one row.
  • the individual injection holes 14 are configured in such a way that a main injection direction 15 of the respective injection hole 14 symbolized here by an arrow has a radial component which extends radially to the main outflow direction 9.
  • Main injection direction is understood to mean that direction which has a spray jet with or without spin on average.
  • the injection holes 14 are formed on the lance 6, whereby the injection of liquid fuel into the swirl flow, which is due to the tangential supply of the oxidizer in the mixing chamber 3, quasi from the inside.
  • the injection holes 14 are arranged in more than one row parallel to the main outflow direction 9, for example in two diametrically opposite rows.
  • Fig. 2 lie the injection holes 14, for example, in the parting plane of the two housing halves 2, within which the two housing halves 2 are arranged eccentrically offset from each other and the slot-shaped inlet openings 7 form.
  • the number of rows of injection holes 14 suitably corresponds to the number of inlet openings 7 of the mixing space 3. In this way, each group of the injection holes 14 can be assigned specifically to an inlet opening 7. However, this is not mandatory. As well, more or less rows of injection holes 17 may be arranged, or the rows may be offset from the inlet opening 7 upstream or downstream.
  • the injection holes 14 mounted in two opposite rows are arranged in pairs in the same longitudinal plane, the injection holes of the opposite rows also be offset to each other.
  • the lined-up injection holes 14 of each row preferably have a uniform spacing from one another.
  • the liquid fuel supply device 12 is equipped with a pilot supply line 16, by means of which at least one pilot injection hole 17 liquid fuel can be supplied.
  • the at least one pilot injection hole 17 is designed such that it has a main injection direction 18, indicated by an arrow, which exclusively has an axial component which extends parallel to the main discharge direction 9.
  • liquid fuel can thus be injected into the mixing chamber 3 or directly into the combustion chamber 8 axially, ie, parallel to the main outflow direction 9 with or without swirl.
  • the injection holes 14 may also be configured such that their respective main injection direction 15 also has an axial component in addition to the radial component, which therefore extends parallel to the main outflow direction 9. In this way, for example, the mixing with the oxidizer flow can be improved.
  • the injection holes 14 may also be configured such that the respective main injection direction 15 also has a peripheral component in addition to the radial component. This peripheral component or tangential component extends transversely to the main outflow direction 9 and transversely to the radial component. In this case, this peripheral component is expediently oriented in the direction of rotation of the swirl flow, which forms due to the tangential inflow of the oxidizer in the mixing chamber 3.
  • the perimeter component can help improve the mixing of the liquid fuel with the oxidizer. It is understood that the injection holes 14 may be configured such that the main injection direction 15 has the axial component and the circumferential component cumulatively or alternatively in addition to the radial component.
  • the injection holes 14 For the arrangement, positioning and dimensioning of the injection holes 14 and for the orientation of the main injection direction 15, an optimum is advantageously sought, which leads to a particularly good atomization, mixing and evaporation of the liquid fuel in the oxidizer gas.
  • the injection holes 14 must have a specific ratio of length to diameter in order to be able to represent the respective desired main injection direction clean. It is quite possible that it will be necessary to choose the wall thickness of the lance 6 larger than is the case, for example, in a conventional lance 6 for injecting liquid fuel.
  • Each inlet opening 7 is associated with a tube 19, see also the FIGS. 2 and 3 ,
  • the tubes 19 are arranged inside or with respect to the oxidizer flow upstream of the respective associated inlet opening 7 and extend quasi parallel along the entire respective inlet opening 7.
  • the tubes 19 are expediently not provided with a circular cross-section, but have in adaptation to the space. and flow conditions within or immediately upstream of the inlet port 7 have a long-round, oval or streamline profile.
  • a gas fuel supply device 11 comprises at least one supply line; In the present case, two supply lines are provided, namely a first supply line 20 and a second supply line 21. With the supply lines 20, 21 can be supplied to several injection holes 22, 23 gas fuel. In this case, first injection holes 22 are supplied by the first supply line 20, while second injection holes 23 are supplied from the second supply line 21. The injection holes 22, 23 are arranged upstream of the respective inlet opening 7 with respect to the oxidizer flow.
  • the respective tube 19 contains at least one gas fuel channel which is connected to the respective supply line 20, 21 and which leads to the respective associated injection holes 22, 23. In the present case, a first gas fuel channel 24 is therefore contained in each tube 19, which communicates the first supply line 20 with the first injection holes 22 in a communicative manner.
  • each tube 19 also includes a second gas fuel passage 25 communicating the second feed line 21 with the second injection holes 23.
  • the first injection holes 22 are arranged in a first longitudinal section of the mixing chamber 3, which is remote from the outlet opening 5 and adjoins the burner head 4, thereby forming a first burner stage.
  • the second injection holes 23 are arranged in a second longitudinal section of the mixing chamber 3 adjoining the outlet opening 5 and thereby form a second burner stage, which is arranged downstream of the first burner stage with respect to the main outflow direction 9.
  • the two burner stages can be controlled independently. In that regard, it is in the embodiment of the Fig. 1 around a two-stage burner 1.
  • both the first group of injection holes 22 and the second group of injection holes 23 are individually arranged in at least one row, which extend substantially along the respective inlet opening 7.
  • the tube 19 additionally includes a liquid fuel channel 26 which extends parallel to the gas fuel channels 24, 25.
  • the liquid fuel channel 26 establishes a communicating connection between the main supply pipe 13 and the injection holes 14.
  • the integration of the injection holes 14 in the tube 19 results in a particularly simple structure for the burner 1, which can be operated both with gaseous fuel and with liquid fuel. At the same time results in this type of injection of the liquid fuel a particularly long residence time for the liquid fuel in the mixing chamber 3, whereby the atomization, mixing and evaporation of the liquid fuel is improved.
  • the at least one tube 19 may contain only the liquid fuel channel 26, wherein then the introduction of the gas fuel may be carried out by means of a separate tube or in any other suitable manner.
  • the tube 19 has a dreittingigen structure in the region of the first gas fuel channel 24, wherein each chamber forms one of the channels 24, 25, 26.
  • the cut for the presentation according to Fig. 4 is selected such that a pair of opposite first injection holes 22 communicating with the first gas fuel channel 24, a pair of opposite second injection holes 23 communicating with the second gas fuel channel 25 and a plurality of injection holes 14 communicating with the liquid fuel channel 26 can be seen ,
  • a plurality of injection holes 14 are again combined into groups, which are each arranged one behind the other in a row parallel to the main outflow direction 9.
  • all of the injection holes 14 are each designed such that their respective main injection direction 15 has a radial component with respect to the main outflow direction 9 of the burner 1.
  • a plurality of injection holes 14 are arranged along a trailing edge of the tube 19 and thereby configured such that their respective main injection direction 15 runs parallel to a main inflow direction of the burner 1.
  • injection holes 14 are provided, each of which is designed so that their respective main injection direction 15 with respect to the main inflow 27 has a transverse component. In this way, the injection takes place directly into the oxidizer flow, which flows around the tube 19 and enters the mixing chamber 3 downstream of the tube 19 through the inlet opening 7.
  • the injection holes 14 and the second injection holes 23 formed on the same side of the tube 19 are offset relative to each other with respect to the main discharge direction 9 so as to avoid mutual overlap.
  • the staggered arrangement can be avoided, for example, that an ignitable mixture passes through the injection holes 14 in the liquid fuel supply 12 during operation of the burner 1 with gas fuel.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Claims (13)

  1. Brûleur à prémélange pour une chambre de combustion d'une turbine à gaz, comprenant
    - une enceinte (2) pour délimiter une chambre de mélange (3) destinée au prémélange d'un oxydant avec un combustible gazeux et/ou liquide,
    - un dispositif de fourniture d'oxydant (12) pour fournir l'oxydant dans la chambre de mélange (3), qui présente au moins une ouverture d'admission (7), qui est configurée et disposée de telle manière que l'oxydant fourni à la chambre de mélange par cette au moins une ouverture d'admission (7) pénètre essentiellement tangentiellement dans la chambre de mélange (3),
    - un dispositif de fourniture de combustible gazeux (11) pour fournir le combustible gazeux dans la chambre de mélange (3),
    - un premier dispositif de fourniture de combustible liquide (12) pour fournir le combustible liquide dans la chambre de mélange (3), comprenant une lance disposée au centre (6), qui s'étend dans la chambre de mélange (3) à partir d'une tête de brûleur (4),
    - une ouverture de sortie (5) de l'enceinte (2) pour la sortie du mélange oxydant-combustible hors de la chambre de mélange (3) dans la chambre de combustion, dans lequel le premier dispositif de fourniture de combustible liquide (12) présente une conduite de fourniture principale (13) comportant plus d'un trou d'injection (14) pour le combustible liquide, et au moins la plus grande partie ou la totalité de ces trous d'injection (14) sont configurés de telle manière qu'une direction d'injection principale (15) du trou d'injection respectif (14) présente une composante radiale, qui s'étend perpendiculairement à une direction de sortie principale (9) du brûleur, dans lequel il faut entendre par direction de sortie principale (9) du brûleur une direction que le mélange oxydant-combustible sortant de la chambre de mélange (3) présente à l'ouverture de sortie (5) de la chambre de mélange (3),
    caractérisé en ce que la lance (6) présente au moins un trou d'injection pilote (17) et une partie des trous d'injection (14), dans lequel les trous d'injection (14) de la lance (6) sont disposés en au moins une rangée parallèlement à la direction de sortie principale (9), et en ce qu'un deuxième dispositif de fourniture de combustible liquide sous la forme d'un tube (19) balayé par le courant d'oxydant est disposé au moins principalement à l'intérieur ou en amont de l'ouverture d'admission (7) de l'enceinte (2).
  2. Brûleur à prémélange selon la revendication 1, caractérisé en ce que
    - un premier nombre de ces trous d'injection (14) sont disposés le long d'une première rangée parallèlement à la direction de sortie principale (9),
    - un deuxième nombre de ces trous d'injection (14) sont disposés le long d'une deuxième rangée parallèlement à la direction de sortie principale (9), et
    - les deux rangées de trous d'injection (14) du premier dispositif de fourniture de combustible liquide (12) sont diamétralement opposées l'une à l'autre.
  3. Brûleur à prémélange selon une des revendications 1 ou 2, caractérisé en ce que
    - les trous d'injection (14) sont configurés au moins principalement de telle manière que la direction d'injection principale (15) du trou d'injection respectif (14) présente en plus une composante axiale en direction de la direction de sortie principale (9), et/ou
    - les trous d'injection (14) sont configurés au moins principalement de telle manière que la direction d'injection principale (15) du trou d'injection respectif (14) présente en plus une composante tangentielle dans une direction de rotation dans la chambre de mélange (3).
  4. Brûleur à prémélange selon la revendication 1, caractérisé en ce que
    - la lance (6) est équipée d'une conduite de fourniture principale (13) et d'une conduite de fourniture pilote (16),
    - la conduite de fourniture pilote (16) alimente le trou d'injection pilote (17), qui est disposé à l'extrémité libre de la lance (6) et dont la direction d'injection principale (18) est dirigée parallèlement à la direction de sortie principale (9),
    - la conduite de fourniture principale (13) alimente au moins une rangée de trous d'injection (14), qui s'étendent sur la surface latérale de la lance (6) parallèlement à la direction de sortie principale (18) et dont la direction d'injection principale (15) présente une composante radiale.
  5. Brûleur à prémélange selon la revendication 4, caractérisé en ce que la lance (6) présente deux rangées de trous d'injection (14) diamétralement opposées.
  6. Brûleur à prémélange selon la revendication 4 ou 5, caractérisé en ce que les trous d'injection (14) présentent une direction d'injection principale (15) avec une composante radiale et avec une composante axiale et/ou une composante tangentielle.
  7. Brûleur à prémélange selon la revendication 1, caractérisé en ce que le tube (19) présente une section transversale de forme ovale.
  8. Brûleur à prémélange selon la revendication 1, caractérisé en ce que
    - un nombre des trous d'injection (14) sont configurés de telle manière qu'une direction d'injection principale (15) du trou d'injection respectif (14) s'étende parallèlement à la direction d'entrée principale (27) du courant d'oxydant pénétrant dans la chambre de mélange (3), et/ou
    - un nombre des trous d'injection (14) sont configurés de telle manière qu'une direction d'injection principale (15) du trou d'injection respectif (14) présente une composante transversale, qui s'étend au moins approximativement perpendiculairement à la direction d'entrée principale (27) du courant d'oxydant dans l'ouverture d'admission (7).
  9. Brûleur à prémélange selon la revendication 1, caractérisé en ce que le tube (19) présente au moins un canal de combustible liquide (26), qui alimente plusieurs trous d'injection (14) du dispositif de fourniture de combustible liquide (12).
  10. Brûleur à prémélange selon la revendication 9, caractérisé en ce qu'au moins un canal de combustible gazeux (24, 25) est formé dans le tube (19) parallèlement au canal de combustible liquide (26), et il alimente des trous d'injection (22, 23) et il est raccordé à au moins une conduite de fourniture (20, 21) pour le combustible gazeux.
  11. Brûleur à prémélange selon la revendication 10, caractérisé en ce que
    - un premier canal de combustible gazeux (24) est formé dans le tube (19) parallèlement au canal de combustible liquide (26), et il est raccordé à une première conduite de fourniture (20) et il alimente un premier groupe de trous d'injection (22) avec du combustible gazeux,
    - un deuxième canal de combustible gazeux (25) est formé dans le tube (19) parallèlement au canal de combustible liquide (26), et il est raccordé à une deuxième conduite de fourniture (21) et il alimente un deuxième groupe de trous d'injection (23) avec du combustible gazeux.
  12. Brûleur à prémélange selon la revendication 11, caractérisé en ce que le deuxième groupe de trous d'injection (23) est disposé en aval du premier groupe de trous d'injection (22) par rapport à la direction de sortie principale (9).
  13. Brûleur à prémélange selon la revendication 12, caractérisé en ce que les deux groupes de trous d'injection (22, 23) sont disposés en au moins une rangée sur la surface latérale du tube (19).
EP06725400.3A 2005-03-31 2006-03-29 Bruleur de premelange destine a une chambre de combustion de turbine a gaz Not-in-force EP1864056B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005015152A DE102005015152A1 (de) 2005-03-31 2005-03-31 Vormischbrenner für eine Gasturbinenbrennkammer
PCT/EP2006/061144 WO2006103257A1 (fr) 2005-03-31 2006-03-29 Bruleur de premelange destine a une chambre de combustion de turbine a gaz

Publications (2)

Publication Number Publication Date
EP1864056A1 EP1864056A1 (fr) 2007-12-12
EP1864056B1 true EP1864056B1 (fr) 2015-07-15

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EP06725400.3A Not-in-force EP1864056B1 (fr) 2005-03-31 2006-03-29 Bruleur de premelange destine a une chambre de combustion de turbine a gaz

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US (1) US7565794B2 (fr)
EP (1) EP1864056B1 (fr)
JP (2) JP2008534903A (fr)
DE (1) DE102005015152A1 (fr)
WO (1) WO2006103257A1 (fr)

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JP3169663U (ja) 2011-08-11
US7565794B2 (en) 2009-07-28
US20080115497A1 (en) 2008-05-22
DE102005015152A1 (de) 2006-10-05
EP1864056A1 (fr) 2007-12-12
JP2008534903A (ja) 2008-08-28

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