EP3430316A1 - Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy - Google Patents

Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy

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Publication number
EP3430316A1
EP3430316A1 EP17705924.3A EP17705924A EP3430316A1 EP 3430316 A1 EP3430316 A1 EP 3430316A1 EP 17705924 A EP17705924 A EP 17705924A EP 3430316 A1 EP3430316 A1 EP 3430316A1
Authority
EP
European Patent Office
Prior art keywords
holes
combustion chamber
turbine
row
diffuser
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.)
Granted
Application number
EP17705924.3A
Other languages
German (de)
French (fr)
Other versions
EP3430316B1 (en
Inventor
Hubert BAYA TODA
Jean-Baptiste Michel
Julien Thiriot
Thomas VALIN
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.)
IFP Energies Nouvelles IFPEN
Original Assignee
IFP Energies Nouvelles IFPEN
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Application filed by IFP Energies Nouvelles IFPEN filed Critical IFP Energies Nouvelles IFPEN
Publication of EP3430316A1 publication Critical patent/EP3430316A1/en
Application granted granted Critical
Publication of EP3430316B1 publication Critical patent/EP3430316B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants

Definitions

  • the invention relates to a combustion chamber of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy.
  • a thermodynamic cycle turbine with recuperator for the production of energy, especially electrical energy.
  • It relates more particularly to a microturbine with recuperator for the production of electricity from a liquid or gaseous fuel.
  • microturbine a small power turbine usually less than 200KW.
  • a turbine with recuperator generally comprises at least one compression stage with at least one compressor, a combustion chamber (or burner), at least one expansion stage with at least one turbine a heat exchange device (or recuperator) between the compressor and the burner for heating the compressed gases by the compressor to send them with a high temperature to the burner, this exchange device being traversed by the hot gases from the turbine.
  • the burner comprises an outer casing through which circulates the hot compressed air from the recuperator and a flame tube, located inside this casing, in which takes place combustion.
  • the flame tube comprises a primary zone that receives a portion of the total hot compressed air flow rate and in which combustion occurs and a dilution zone where mixing between the primary zone burned gases and the compressed gases occurs. from the dilution holes on the tube.
  • the primary zone further comprises a perforated diffuser allowing the passage of hot compressed air as well as fuel from a fuel injection system (liquid or gas) placed upstream of the diffuser.
  • a fuel injection system liquid or gas
  • a turbine with recuperator has a low compression ratio (of the order of 3 to 5 bars of pressure) and low inlet temperatures of the turbine in comparison with high-power aeronautical or stationary gas turbines.
  • This combustion chamber comprises a housing housing a flame tube with a perforated diffuser for the passage of hot compressed air, a flame stabilizer, recirculation passages for combustion gases, a mixing tube and an injection means of a fuel.
  • the present invention relates to a combustion chamber of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising a housing housing a flame tube. with a diffusion partition carrying a flame stabilizer comprising a perforated air diffuser and a mixing tube, said chamber further comprising means for injecting at least one fuel, characterized in that the perforated diffuser comprises at least two circumferential rows of holes.
  • the diffuser may include a bore for fuel passage and the circumferential rows of holes may be concentrically disposed in said bore.
  • the diffuser may include a row of holes whose opening is smaller than the opening of the holes of the other row.
  • the diffuser may include one row of holes, the number of which is greater than the number of holes in the other row.
  • the diffuser may include holes with a shape in a closed curve.
  • the diffuser may comprise holes whose angular spacing between two adjacent holes of a row is a multiple or a sub-multiple of the angular difference between two holes of the other row.
  • the perforated diffuser can carry the mixing tube by arms.
  • the invention also relates to a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage with at least one gas compressor, an exchanger of heat, a combustion chamber fed with fuel by at least one tank, at least one expansion stage with at least one expansion turbine connected by a shaft to the compressor, and a means for producing energy, characterized in that it comprises a combustion chamber as defined above.
  • FIG. 1 which is a diagram illustrating a turbine with a combustion chamber according to the invention for the production of energy, in particular electrical energy,
  • FIG. 2 which is an axial sectional view showing the combustion chamber according to the invention
  • FIG. 3 which is a perspective view of an element of the combustion chamber according to the invention.
  • the turbine illustrated is more particularly a microturbine 10, operating from at least one fuel, such as a liquid fuel, for example of the diesel fuel type, or a gaseous fuel, such as natural gas.
  • the turbine comprises at least one compression stage 12 with at least one gas compressor 14, a heat exchanger 1 6 (or recuperator), a combustion chamber 18 (or burner) supplied with fuel by at least one tank 20, at the at least one expansion stage 22 with at least one expansion turbine 24 connected by a shaft 26 to the compressor.
  • This turbine also comprises a power generation means, here electrical, which comprises an electric generator 28 advantageously placed on the shaft 26 between the compressor and the turbine.
  • this generator can be alternately connected to the expansion turbine or to the compressor by a shaft other than that connecting the turbine and the compressor.
  • the compressor 14 comprises a fresh gas inlet containing oxygen, here outside air generally at ambient temperature, and a compressed air outlet 32 leading to a compressed air inlet 34 of the exchanger 16.
  • the hot compressed air outlet 36 of the exchanger 16 arrives at an inlet of hot compressed air 38 from the burner 18.
  • the superheated gas outlet 40 of the burner is connected to the inlet 42 of the turbine, whose outlet 44 is connected to another inlet 46 of the exchanger.
  • the exchanger 16 also includes a cooled gas outlet 48 to be directed to any means of evacuation and treatment, such as a chimney (not shown).
  • the burner 18 comprises an outer casing 50, here of cylindrical shape, closed at one of its ends by an injector septum 52 and at the other end thereof by a partition 54 with an opening 56 of smaller diameter than that of the housing 50.
  • This burner also comprises a flame tube 58, here also of substantially cylindrical shape, housed coaxially in the housing being of smaller diameter than the housing but of identical diameter to that of the opening 56 of the annular partition 54.
  • This tube comprises an end closed by a diffusion partition 60 opposite and at a distance from the injector wall 52 and an open end 62 which passes through the annular partition cooperating sealingly with the inner diameter of this annular partition to form the outlet 40 of this burner.
  • the housing carries, on its periphery and near the annular partition 54, the inlet of hot compressed air 38 for introducing this air into the space formed between the housing and the flame tube as well as in the space formed between the injector partition and the diffusion partition.
  • the injector partition comprises a plate 64, through which is mounted an injection means 66 of at least one fuel, here in the form of an injector coaxial with the flame tube. .
  • This plate is surrounded by an air deflecting wall 68, here semi-toric whose concavity is directed towards the flame tube and which is connected to the periphery of the housing.
  • the flame tube comprises circumferential rows of radial dilution orifices 70 placed at a distance from the diffusion partition 60 and close to the annular partition of the casing, being distributed regularly advantageously opposite the inlet 38.
  • This flame tube also comprises a flame stabilizer 72 which is placed on the diffusion partition 60 and inside the tube being housed in an orifice 74 provided in this diffusion partition.
  • the burner also comprises an ignition device 76 for a fuel mixture.
  • this device may be a spark plug of the type for internal combustion engine with spark ignition, a glow plug, ignition electrodes, etc.
  • FIGS. 3 and 4 illustrate an exemplary embodiment of a flame stabilizer 72.
  • This stabilizer comprises a perforated air diffuser 78 in the form of a flat circular soleplate 80 intended to be housed in the orifice 74 of the diffusion partition 60.
  • This sole includes a central axial bore 82 for the passage of fuel from the injector 64 and comprises a plurality of holes 84 which pass through the thickness of the sole being in the same axial direction as that of the bore.
  • the holes 84 are distributed in a multiplicity of circumferential rows concentric with the bore 82.
  • One of the rows C1 of holes which is located closest to the outer edge of the sole, comprises holes 84a which have an opening which is smaller than the opening of the holes 84b of the other row C2 of holes.
  • the holes are of circular shape and the holes 84a of the outer row have a diameter D1 which is smaller than the diameter D2 of the holes 84b of the other row C2 of holes.
  • the holes 84a of the outer row C1 are advantageously in greater number than those of the inner row C2 In the example illustrated, the holes 84a are twice as numerous as those of the inner row.
  • the shape of the holes 84a, 84b is not limited to that of the circular shape, as illustrated in the figures, but may be a completely different shape with a closed curve, such as a square, ellipsoidal, trapezoidal, triangular shape etc.
  • the circumferential angular gap between two adjacent holes may be constant or variable throughout the row.
  • the angular difference between two adjacent holes of a row may be a multiple or a sub-multiple of the angular difference between two holes of the other row.
  • the angular difference ⁇ between two adjacent holes 84a of the outer row is half the angle ⁇ between two adjacent holes of the inner row.
  • the sole 80 continues in an axial direction and away from the partition by axial arms 86, here three arms arranged at 120 ° from each other, and carrying at their ends a mixing tube 88 of outside diameter less than the inside diameter of the flame tube 58.
  • the mixing tube 88 is connected by radial arms to the flame tube 58 instead of being connected to the soleplate.
  • the fuel here in liquid form
  • the injector 64 is injected by the injector 64 in the direction the perforated plate 80 to pass through the central hole 82.
  • the hot compressed air from the inlet 38 enters the space 90 between the partitions, is then deflected by the deflector wall 68. This air then passes through the holes 84a and 84b of the soleplate and is directed into the mixing tube 88 in which takes place the evaporation of the liquid fuel, then the combustion.
  • the recirculations around the flame catch are favored and the speed of passage of the air is relatively important.
  • the combustion chamber can operate at low average wealth, for example 0.35 in stability limit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Spray-Type Burners (AREA)

Abstract

The invention relates to a combustion chamber (18) of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy, said combustion chamber comprising a housing (50) containing a fire tube (58) with a diffusion wall (60) carrying a flame stabiliser (72) comprising a perforated air diffuser (78) and a mixing tube (88), said chamber also comprising a means (64) for injecting at least one fuel. According to the invention, the perforated diffuser (78) comprises at least two peripheral rows (C1, C2) of holes (84; 84a, 84b).

Description

Chambre de combustion d'une turbine, notamment d'une turbine à cycle thermodynamique avec récupérateur, pour la production d'énergie, en particulier d'énergie électrique La présente invention se rapporte à une chambre de combustion d'une turbine, notamment d'une turbine à cycle thermodynamique avec récupérateur, pour la production d'énergie, notamment d'énergie électrique.  The invention relates to a combustion chamber of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy. a thermodynamic cycle turbine with recuperator, for the production of energy, especially electrical energy.
Elle concerne plus particulièrement une microturbine avec récupérateur pour la production d'électricité à partir d'un combustible liquide ou gazeux. It relates more particularly to a microturbine with recuperator for the production of electricity from a liquid or gaseous fuel.
Généralement, il est entendu par microturbine une turbine de petite puissance usuellement inférieure à 200KW.  Generally, it is understood by microturbine a small power turbine usually less than 200KW.
Comme mieux décrit dans la demande WO 2012/03961 1 , une turbine avec récupérateur comprend généralement au moins un étage de compression avec au moins un compresseur, une chambre de combustion (ou brûleur), au moins un étage de détente avec au moins une turbine de détente, un dispositif d'échange de chaleur (ou récupérateur) entre le compresseur et le brûleur permettant de chauffer les gaz comprimés par le compresseur pour les envoyer avec une température élevée au brûleur, ce dispositif d'échange étant parcouru par les gaz chauds provenant de la turbine. As better described in the application WO 2012/03961 1, a turbine with recuperator generally comprises at least one compression stage with at least one compressor, a combustion chamber (or burner), at least one expansion stage with at least one turbine a heat exchange device (or recuperator) between the compressor and the burner for heating the compressed gases by the compressor to send them with a high temperature to the burner, this exchange device being traversed by the hot gases from the turbine.
Tel que cela est décrit dans la demande précitée, le brûleur comprend un boîtier extérieur au travers duquel circule l'air comprimé chaud provenant du récupérateur et d'un tube à flamme, situé à l'intérieur de ce boîtier, au sein duquel a lieu la combustion. As described in the aforementioned application, the burner comprises an outer casing through which circulates the hot compressed air from the recuperator and a flame tube, located inside this casing, in which takes place combustion.
Le tube à flamme comprend une zone primaire qui reçoit une partie du débit d'air comprimé chaud total et dans laquelle se produit la combustion et une zone de dilution où a lieu le mélange entre les gaz brûlés issus de la zone primaire et des gaz comprimés chauds provenant de trous de dilution prévus sur le tube.  The flame tube comprises a primary zone that receives a portion of the total hot compressed air flow rate and in which combustion occurs and a dilution zone where mixing between the primary zone burned gases and the compressed gases occurs. from the dilution holes on the tube.
La zone primaire comprend en outre un diffuseur perforé permettant le passage de l'air comprimé chaud ainsi que du combustible provenant d'un système d'injection de combustible (liquide ou gazeux) placé en amont du diffuseur. The primary zone further comprises a perforated diffuser allowing the passage of hot compressed air as well as fuel from a fuel injection system (liquid or gas) placed upstream of the diffuser.
Généralement, une turbine avec récupérateur présente un faible taux de compression (de l'ordre de 3 à 5 bars de pression) et des températures faibles en entrée de la turbine en comparaison des turbines à gaz aéronautiques ou stationnaires hautes puissances. Generally, a turbine with recuperator has a low compression ratio (of the order of 3 to 5 bars of pressure) and low inlet temperatures of the turbine in comparison with high-power aeronautical or stationary gas turbines.
L'une des conséquences de ces caractéristiques de fonctionnement est la richesse globale dans la chambre de combustion, inférieure à 0,20 en général, c'est-à-dire en-deçà des limites d'inflammabilité du combustible. One of the consequences of these operating characteristics is the overall richness in the combustion chamber, lower than 0.20 in general, that is to say below the flammability limits of the fuel.
De plus, se pose le problème de la pré-vaporisation du combustible dans le cas d'un combustible liquide. Généralement, le mode de combustion permettant d'atteindre de faibles émissions est la combustion pré-mélangée avec richesse pauvre.  In addition, there is the problem of the pre-vaporization of the fuel in the case of a liquid fuel. Generally, the combustion mode to achieve low emissions is premixed combustion with poor wealth.
Cependant, ce type de combustion pose d'importants problèmes quant à la stabilisation de la flamme. Ces problèmes sont d'autant plus renforcés par l'action du récupérateur qui augmente la température de l'air en entrée du brûleur en accentuant les risques d'instabilité de la flamme.  However, this type of combustion poses significant problems in the stabilization of the flame. These problems are all the more reinforced by the action of the recuperator which increases the air temperature at the burner inlet by increasing the risk of instability of the flame.
De plus, le coût de conception est également un verrou. En effet, ce type de chambre est caractérisé par une forte interaction entre la flamme et la paroi ce qui nécessite le choix de matériaux onéreux sur un important volume et un système de refroidissement des parois du brûleur généralement constitué de multiple trous servant à créer un coussin d'air entre la flamme et la paroi. Ce système de refroidissement entraine un surcoût non négligeable dans le processus de fabrication ainsi qu'une complexité de réalisation. Tous ces inconvénients rendent difficile une combustion complète et le respect des exigences de faibles émissions en terme de d'oxydes d'azote (NOx), d'oxyde de carbone (CO), d'hydrocarbures imbrûlés (HC) et de particules (PM). Pour améliorer les turbines précitées, le demandeur a proposé une nouvelle chambre de combustion d'une turbine, comme cela est mieux décrit dans la demande de brevet FR 15/59314. In addition, the cost of design is also a lock. Indeed, this type of chamber is characterized by a strong interaction between the flame and the wall which requires the choice of expensive materials on a large volume and a cooling system of the walls of the burner generally consists of multiple holes used to create a cushion of air between the flame and the wall. This cooling system leads to a significant additional cost in the manufacturing process and a complexity of implementation. All these disadvantages make it difficult to achieve complete combustion and compliance with low emission requirements in terms of nitrogen oxides (NOx), carbon monoxide (CO), unburned hydrocarbons (HC) and particulate matter (PM). ). To improve the aforementioned turbines, the applicant has proposed a new combustion chamber of a turbine, as is better described in the patent application FR 15/59314.
Cette chambre de combustion comporte un boîtier logeant un tube à flamme avec un diffuseur perforé pour le passage de l'air comprimé chaud, un stabilisateur de flamme, des passages de recirculation de gaz de combustion, un tube de mélange et un moyen d'injection d'un combustible.  This combustion chamber comprises a housing housing a flame tube with a perforated diffuser for the passage of hot compressed air, a flame stabilizer, recirculation passages for combustion gases, a mixing tube and an injection means of a fuel.
Le demandeur a encore plus amélioré la chambre de combustion de la demande de brevet précitée de manière à obtenir une réduction accrue des polluants résultant de la combustion, une absence de particules de suies à l'échappement avec les techniques de mesures usuelles, une réduction de bruit de combustion et une réduction des gradients de température en entrée de la turbine. A cet effet, la présente invention concerne une chambre de combustion d'une turbine, notamment d'une turbine à cycle thermodynamique avec récupérateur, pour la production d'énergie, en particulier d'énergie électrique, comportant un boîtier logeant un tube à flamme avec une cloison de diffusion portant un stabilisateur de flamme comprenant un diffuseur d'air perforé et un tube mélangeur, ladite chambre comportant en outre un moyen d'injection d'au moins un combustible, caractérisée en ce que le diffuseur perforé comprend au moins deux rangées circonférentielles de trous. The applicant has further improved the combustion chamber of the aforementioned patent application so as to obtain an increased reduction of the pollutants resulting from the combustion, an absence of soot particles at the exhaust with the usual measurement techniques, a reduction of combustion noise and a reduction of the temperature gradients at the inlet of the turbine. For this purpose, the present invention relates to a combustion chamber of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising a housing housing a flame tube. with a diffusion partition carrying a flame stabilizer comprising a perforated air diffuser and a mixing tube, said chamber further comprising means for injecting at least one fuel, characterized in that the perforated diffuser comprises at least two circumferential rows of holes.
Le diffuseur peut comprendre un alésage pour le passage du combustible et les rangées circonférentielles de trous peuvent être disposées concentriquement audit alésage. The diffuser may include a bore for fuel passage and the circumferential rows of holes may be concentrically disposed in said bore.
Le diffuseur peut comprendre une rangée de trous dont l'ouverture est plus petite que l'ouverture des trous de l'autre rangée. The diffuser may include a row of holes whose opening is smaller than the opening of the holes of the other row.
Le diffuseur peut comprendre une rangée de trous dont le nombre est plus élevé que le nombre de trous de l'autre rangée. Le diffuseur peut comprendre des trous avec une forme selon une courbe fermée. The diffuser may include one row of holes, the number of which is greater than the number of holes in the other row. The diffuser may include holes with a shape in a closed curve.
Le diffuseur peut comprendre des trous dont l'écart angulaire entre deux trous voisins d'une rangée est un multiple ou un sous multiple de l'écart angulaire entre deux trous de l'autre rangée. The diffuser may comprise holes whose angular spacing between two adjacent holes of a row is a multiple or a sub-multiple of the angular difference between two holes of the other row.
Le diffuseur perforé peut porter le tube mélangeur par des bras. L'invention concerne également une turbine, notamment d'une turbine à cycle thermodynamique avec récupérateur, pour la production d'énergie, en particulier d'énergie électrique, comprenant au moins un étage de compression avec au moins un compresseur de gaz, un échangeur de chaleur, une chambre de combustion alimentée en combustible par au moins un réservoir, au moins un étage de détente avec au moins une turbine de détente reliée par un arbre au compresseur, et un moyen de production d'énergie, caractérisée en ce qu'elle comprend une chambre de combustion comme définie précédemment. The perforated diffuser can carry the mixing tube by arms. The invention also relates to a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage with at least one gas compressor, an exchanger of heat, a combustion chamber fed with fuel by at least one tank, at least one expansion stage with at least one expansion turbine connected by a shaft to the compressor, and a means for producing energy, characterized in that it comprises a combustion chamber as defined above.
Les autres caractéristiques et avantages de l'invention vont apparaître maintenant à la lecture de la description qui va suivre, donnée à titre uniquement illustratif et non limitatif, et à laquelle sont annexées : The other features and advantages of the invention will now appear on reading the following description, given solely by way of illustration and not limitation, and to which are appended:
- la figure 1 qui est un schéma illustrant une turbine avec une chambre de combustion selon l'invention pour la production d'énergie, notamment d'énergie électrique,  FIG. 1 which is a diagram illustrating a turbine with a combustion chamber according to the invention for the production of energy, in particular electrical energy,
- la figure 2 qui est une vue en coupe axiale montrant la chambre de combustion selon l'invention,  FIG. 2 which is an axial sectional view showing the combustion chamber according to the invention,
- la figure 3 qui est une vue en perspective d'un élément de la chambre de combustion selon l'invention et  FIG. 3 which is a perspective view of an element of the combustion chamber according to the invention and
- la figure 4 qui est une vue latérale selon la flèche A de l'élément de la chambre de combustion de la figure 3.  - Figure 4 which is a side view along the arrow A of the element of the combustion chamber of Figure 3.
Sur la figure 1 , la turbine illustrée est plus particulièrement une microturbine 10, fonctionnant à partir d'au moins un combustible, tel qu'un combustible liquide, par exemple de type gazole, ou un combustible gazeux, tel que du gaz naturel. La turbine comprend au moins un étage de compression 12 avec au moins un compresseur de gaz 14, un échangeur de chaleur 1 6 (ou récupérateur), une chambre de combustion 18 (ou brûleur) alimentée en combustible par au moins un réservoir 20, au moins un étage de détente 22 avec au moins une turbine de détente 24 reliée par un arbre 26 au compresseur. Cette turbine comprend également un moyen de production d'énergie, ici électrique, qui comporte une génératrice électrique 28 placée avantageusement sur l'arbre 26 entre le compresseur et la turbine. In FIG. 1, the turbine illustrated is more particularly a microturbine 10, operating from at least one fuel, such as a liquid fuel, for example of the diesel fuel type, or a gaseous fuel, such as natural gas. The turbine comprises at least one compression stage 12 with at least one gas compressor 14, a heat exchanger 1 6 (or recuperator), a combustion chamber 18 (or burner) supplied with fuel by at least one tank 20, at the at least one expansion stage 22 with at least one expansion turbine 24 connected by a shaft 26 to the compressor. This turbine also comprises a power generation means, here electrical, which comprises an electric generator 28 advantageously placed on the shaft 26 between the compressor and the turbine.
Bien entendu, cette génératrice peut être alternativement reliée à la turbine de détente ou au compresseur par un arbre autre que celui reliant la turbine et le compresseur. Le compresseur 14 comprend une entrée 30 de gaz frais contenant de l'oxygène, ici de l'air extérieur généralement à température ambiante, et une sortie d'air comprimé 32 aboutissant à une entrée d'air comprimé 34 de l'échangeur 1 6. La sortie d'air comprimé chaud 36 de l'échangeur 16 arrive à une admission d'air comprimé chaud 38 du brûleur 18. La sortie de gaz surchauffés 40 du brûleur est connectée à l'entrée 42 de la turbine dont la sortie 44 est reliée à une autre entrée 46 de l'échangeur. L'échangeur 1 6 comprend également une sortie de gaz refroidis 48 pour être dirigés vers tous moyens d'évacuation et de traitement, comme une cheminée (non représentée). En se rapportant à la figure 2, le brûleur 18 comprend un boîtier extérieur 50, ici de forme cylindrique, fermé à l'une de ses extrémités par une cloison porte- injecteur 52 et à l'autre de ses extrémités par une cloison 54 avec une ouverture 56 de diamètre inférieur à celui du boîtier 50. Ce brûleur comprend également un tube à flamme 58, ici également de forme sensiblement cylindrique, logé coaxialement dans le boîtier en étant de diamètre inférieur au boîtier mais de diamètre identique à celui de l'ouverture 56 de la cloison annulaire 54. Of course, this generator can be alternately connected to the expansion turbine or to the compressor by a shaft other than that connecting the turbine and the compressor. The compressor 14 comprises a fresh gas inlet containing oxygen, here outside air generally at ambient temperature, and a compressed air outlet 32 leading to a compressed air inlet 34 of the exchanger 16. The hot compressed air outlet 36 of the exchanger 16 arrives at an inlet of hot compressed air 38 from the burner 18. The superheated gas outlet 40 of the burner is connected to the inlet 42 of the turbine, whose outlet 44 is connected to another inlet 46 of the exchanger. The exchanger 16 also includes a cooled gas outlet 48 to be directed to any means of evacuation and treatment, such as a chimney (not shown). Referring to Figure 2, the burner 18 comprises an outer casing 50, here of cylindrical shape, closed at one of its ends by an injector septum 52 and at the other end thereof by a partition 54 with an opening 56 of smaller diameter than that of the housing 50. This burner also comprises a flame tube 58, here also of substantially cylindrical shape, housed coaxially in the housing being of smaller diameter than the housing but of identical diameter to that of the opening 56 of the annular partition 54.
Ce tube comprend une extrémité fermée par une cloison de diffusion 60 en regard et à distance de la cloison porte-injecteur 52 et une extrémité ouverte 62 qui traverse la cloison annulaire en coopérant à étanchéité avec le diamètre intérieur de cette cloison annulaire pour former la sortie 40 de ce brûleur. This tube comprises an end closed by a diffusion partition 60 opposite and at a distance from the injector wall 52 and an open end 62 which passes through the annular partition cooperating sealingly with the inner diameter of this annular partition to form the outlet 40 of this burner.
Le boîtier porte, sur sa périphérie et à proximité de la cloison annulaire 54, l'admission d'air comprimé chaud 38 pour introduire cet air dans l'espace formé entre le boîtier et le tube à flamme ainsi que dans l'espace formé entre la cloison porte-injecteur et la cloison de diffusion. The housing carries, on its periphery and near the annular partition 54, the inlet of hot compressed air 38 for introducing this air into the space formed between the housing and the flame tube as well as in the space formed between the injector partition and the diffusion partition.
Comme mieux illustré sur la figure 2, la cloison porte-injecteur comprend une plaque 64, au travers de laquelle est monté un moyen d'injection 66 d'au moins un combustible, ici sous la forme d'un injecteur coaxial au tube à flamme. Cette plaque est entourée d'une paroi déflectrice d'air 68, ici semi-torique dont la concavité est dirigée vers le tube à flamme et qui est reliée à la périphérie du boîtier. As best illustrated in FIG. 2, the injector partition comprises a plate 64, through which is mounted an injection means 66 of at least one fuel, here in the form of an injector coaxial with the flame tube. . This plate is surrounded by an air deflecting wall 68, here semi-toric whose concavity is directed towards the flame tube and which is connected to the periphery of the housing.
Le tube à flamme comprend des rangées circonférentielles d'orifices de dilution radiaux 70 placés à distance de la cloison de diffusion 60 et à proximité de la cloison annulaire du boîtier en étant reparties régulièrement avantageusement en regard de l'admission 38.  The flame tube comprises circumferential rows of radial dilution orifices 70 placed at a distance from the diffusion partition 60 and close to the annular partition of the casing, being distributed regularly advantageously opposite the inlet 38.
Ce tube à flamme comprend également un stabilisateur de flamme 72 qui est placé sur la cloison de diffusion 60 et à l'intérieur du tube en étant logé dans un orifice 74 prévu dans cette cloison de diffusion.  This flame tube also comprises a flame stabilizer 72 which is placed on the diffusion partition 60 and inside the tube being housed in an orifice 74 provided in this diffusion partition.
Le brûleur comprend également un dispositif d'allumage 76 pour un mélange carburé. A titre d'exemple, ce dispositif peut être une bougie du type pour moteur à combustion interne à allumage commandé, une bougie de préchauffage, des électrodes d'allumage, ... The burner also comprises an ignition device 76 for a fuel mixture. By way of example, this device may be a spark plug of the type for internal combustion engine with spark ignition, a glow plug, ignition electrodes, etc.
On se rapporte maintenant en plus aux figures 3 et 4 qui illustrent un exemple de réalisation de stabilisateur de flamme 72. Referring now to FIGS. 3 and 4 which illustrate an exemplary embodiment of a flame stabilizer 72.
Ce stabilisateur comprend un diffuseur d'air perforé 78 sous la forme d'une semelle circulaire plane 80 prévue pour être logée dans l'orifice 74 de la cloison de diffusion 60. Cette semelle comprend un alésage axial central 82 pour le passage du combustible provenant de l'injecteur 64 et comporte une multiplicité de trous 84 qui traversent l'épaisseur de la semelle en étant de même direction axial que celle de l'alésage. This stabilizer comprises a perforated air diffuser 78 in the form of a flat circular soleplate 80 intended to be housed in the orifice 74 of the diffusion partition 60. This sole includes a central axial bore 82 for the passage of fuel from the injector 64 and comprises a plurality of holes 84 which pass through the thickness of the sole being in the same axial direction as that of the bore.
Comme mieux visible sur ces figures, les trous 84 sont répartis selon une multiplicité de rangées circonférentielles concentriques à l'alésage 82. As better visible in these figures, the holes 84 are distributed in a multiplicity of circumferential rows concentric with the bore 82.
L'exemple illustré sur ces figures montrent que ces trous sont réparties régulièrement circonférentiellement selon deux rangées circonférentielles C1 et C2.  The example illustrated in these figures show that these holes are regularly distributed circumferentially along two circumferential rows C1 and C2.
Une des rangées C1 de trous, baptisée rangée externe, qui est située le plus près du bord externe de la semelle, comprend des trous 84a qui ont une ouverture qui est plus petite que l'ouverture des trous 84b de l'autre rangée C2 de trous.  One of the rows C1 of holes, called outer row, which is located closest to the outer edge of the sole, comprises holes 84a which have an opening which is smaller than the opening of the holes 84b of the other row C2 of holes.
Plus précisément, les trous sont de forme circulaire et les trous 84a de la rangée externe ont un diamètre D1 qui est plus petit que le diamètre D2 des trous 84b de l'autre rangée C2 de trous.  More precisely, the holes are of circular shape and the holes 84a of the outer row have a diameter D1 which is smaller than the diameter D2 of the holes 84b of the other row C2 of holes.
Les trous 84a de la rangée externe C1 sont avantageusement en plus grand nombre que ceux de la rangée interne C2 Dans l'exemple illustré, les trous 84a sont deux fois plus nombreux que ceux de la rangée interne. The holes 84a of the outer row C1 are advantageously in greater number than those of the inner row C2 In the example illustrated, the holes 84a are twice as numerous as those of the inner row.
Bien entendu, la forme des trous 84a, 84b n'est pas limitée à celle de la forme circulaire, comme illustrée sur les figures, mais peut être une toute autre forme avec une courbe fermée, comme une forme carrée, ellipsoïdale, trapézoïdale, triangulaire, etc. Of course, the shape of the holes 84a, 84b is not limited to that of the circular shape, as illustrated in the figures, but may be a completely different shape with a closed curve, such as a square, ellipsoidal, trapezoidal, triangular shape etc.
De même, l'écart angulaire circonférentiel entre deux trous voisins peut être constant ou variable tout au long de la rangée. Enfin, l'écart angulaire entre deux trous voisins d'une rangée peut être un multiple ou un sous multiple de l'écart angulaire entre deux trous de l'autre rangée. Likewise, the circumferential angular gap between two adjacent holes may be constant or variable throughout the row. Finally, the angular difference between two adjacent holes of a row may be a multiple or a sub-multiple of the angular difference between two holes of the other row.
Ainsi pour la rangée externe, l'écart angulaire a entre deux trous voisins 84a de la rangée externe est la moitié de l'angle β entre deux trous voisins de la rangée interne. En revenant à la figure 3, la semelle 80 se poursuit dans une direction axiale et à l'opposé de la cloison par des bras axiaux 86, ici trois bras disposés à 120° les uns des autres, et portant à leurs extrémités un tube mélangeur 88 de diamètre extérieur inférieur au diamètre intérieur du tube à flamme 58. Thus, for the outer row, the angular difference α between two adjacent holes 84a of the outer row is half the angle β between two adjacent holes of the inner row. Returning to FIG. 3, the sole 80 continues in an axial direction and away from the partition by axial arms 86, here three arms arranged at 120 ° from each other, and carrying at their ends a mixing tube 88 of outside diameter less than the inside diameter of the flame tube 58.
Il peut aussi être prévu que le tube mélangeur 88 soit relié par des bras radiaux au tube à flamme 58 au lieu d'être relié à la semelle En fonctionnement, le combustible, ici sous forme liquide, est injecté par l'injecteur 64 en direction de la semelle perforée 80 pour traverser le trou central 82. L'air comprimé chaud provenant de l'admission 38 pénètre dans l'espace 90 entre les cloisons, est ensuite dévié par la paroi déflectrice 68. Cet air traverse ensuite les trous 84a et 84b de la semelle et est dirigé dans le tube mélangeur 88 dans lequel a lieu l'évaporation du combustible liquide, puis la combustion. It can also be expected that the mixing tube 88 is connected by radial arms to the flame tube 58 instead of being connected to the soleplate. In operation, the fuel, here in liquid form, is injected by the injector 64 in the direction the perforated plate 80 to pass through the central hole 82. The hot compressed air from the inlet 38 enters the space 90 between the partitions, is then deflected by the deflector wall 68. This air then passes through the holes 84a and 84b of the soleplate and is directed into the mixing tube 88 in which takes place the evaporation of the liquid fuel, then the combustion.
Grâce à la disposition des rangées de trous, les recirculations autour de l'accroche flamme sont favorisées et la vitesse de passage de l'air est relativement importante. Thanks to the arrangement of the rows of holes, the recirculations around the flame catch are favored and the speed of passage of the air is relatively important.
De plus, la localisation d'une rangée de trous qui viennent raser le tube accroche flamme permet d'augmenter le débit qui circule. In addition, the location of a row of holes that shave the tube hangs flame increases the flow that flows.
Ainsi en favorisant les recirculations et avec une vitesse d'air suffisante, - on évite la stabilisation de la flamme dans l'accroche flamme, ce qui conduit à une structure de type flamme jet diffusive, Thus by promoting recirculation and with a sufficient air velocity, it avoids the stabilization of the flame in the flame catch, which leads to a diffusive jet flame type structure,
- on recircule des gaz brûlés qui favorisent l'évaporation, et plus généralement le mélange, et les gouttes de combustible sont évaporées avant d'arriver dans la flamme,  recirculating burnt gases which promote evaporation, and more generally the mixture, and the drops of fuel are evaporated before reaching the flame,
- on a une combustion relativement prémélangée, c'est-à-dire sans zones riches donc avec des productions de polluants faibles,  - It has a relatively premixed combustion, that is to say without rich areas with low pollutant production,
- la chambre de combustion peut fonctionner à des richesses moyennes faibles, par exemple à 0,35 en limite de stabilité.  - The combustion chamber can operate at low average wealth, for example 0.35 in stability limit.

Claims

REVENDICATIONS
1 ) Chambre de combustion (18) d'une turbine, notamment d'une turbine à cycle thermodynamique avec récupérateur, pour la production d'énergie, en particulier d'énergie électrique, comportant un boîtier (50) logeant un tube à flamme (58) avec une cloison de diffusion (60) portant un stabilisateur de flamme (72) comprenant un diffuseur d'air perforé (78) et un tube mélangeur (88), ladite chambre comportant en outre un moyen d'injection (64) d'au moins un combustible, caractérisée en ce que le diffuseur perforé (78) comprend au moins deux rangées circonférentielles (C1 , C2) de trous (84; 84a, 84b). 1) A combustion chamber (18) of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising a housing (50) housing a flame tube ( 58) with a diffusion septum (60) carrying a flame stabilizer (72) comprising a perforated air diffuser (78) and a mixing tube (88), said chamber further comprising injection means (64) for at least one fuel, characterized in that the perforated diffuser (78) comprises at least two circumferential rows (C1, C2) of holes (84; 84a, 84b).
2) Chambre de combustion selon la revendication 1 , caractérisée en ce que le diffuseur comprend un alésage (82) pour le passage du combustible et en ce que les rangées circonférentielles (C1 , C2) de trous sont disposées concentriquement audit alésage. 2) combustion chamber according to claim 1, characterized in that the diffuser comprises a bore (82) for the passage of the fuel and in that the circumferential rows (C1, C2) of holes are arranged concentrically in said bore.
3) Chambre de combustion selon la revendication 1 ou 2, caractérisée en ce que le diffuseur comprend une rangée (C1 ) de trous (84a) dont l'ouverture (D1 ) est plus petite que l'ouverture (D2) des trous (84b) de l'autre rangée (C2). 3) combustion chamber according to claim 1 or 2, characterized in that the diffuser comprises a row (C1) of holes (84a) whose opening (D1) is smaller than the opening (D2) holes (84b ) of the other row (C2).
4) Chambre de combustion selon l'une des revendications précédentes, caractérisée en ce que le diffuseur comprend une rangée (C1 ) de trous (84a) dont le nombre est plus élevé que le nombre de trous (84b) de l'autre rangée. 5) Chambre de combustion selon l'une des revendications précédentes, caractérisée en ce que le diffuseur comprend des trous (84; 84a, 84b) avec une forme selon une courbe fermée. 4) Combustion chamber according to one of the preceding claims, characterized in that the diffuser comprises a row (C1) of holes (84a) whose number is greater than the number of holes (84b) of the other row. 5) Combustion chamber according to one of the preceding claims, characterized in that the diffuser comprises holes (84; 84a, 84b) with a shape in a closed curve.
6) Chambre de combustion selon l'une des revendications précédentes, caractérisée en ce que le diffuseur comprend des trous (84a, 8b) dont l'écart angulaire (α, β) entre deux trous voisins (84a) d'une rangée est un multiple ou un sous multiple de l'écart angulaire (β, a) entre deux trous (84b) de l'autre rangée. 7) Chambre de combustion selon l'une des revendications précédentes, caractérisée en ce que le diffuseur perforé (78) porte le tube mélangeur (88) par des bras (86). 8) Turbine, notamment d'une turbine à cycle thermodynamique avec récupérateur, pour la production d'énergie, en particulier d'énergie électrique, comprenant au moins un étage de compression (12) avec au moins un compresseur de gaz (14), un échangeur de chaleur (1 6), une chambre de combustion (18) alimentée en combustible par au moins un réservoir (20), au moins un étage de détente (22) avec au moins une turbine de détente (24) reliée par un arbre (26) au compresseur, et un moyen de production d'énergie (28), caractérisée en ce qu'elle comprend une chambre de combustion (18) selon l'une des revendications précédentes. 6) combustion chamber according to one of the preceding claims, characterized in that the diffuser comprises holes (84a, 8b), the angular distance (α, β) between two adjacent holes (84a) of a row is a multiple or a sub-multiple of the angular difference (β, a) between two holes (84b) of the other row. 7) Combustion chamber according to one of the preceding claims, characterized in that the perforated diffuser (78) carries the mixing tube (88) by arms (86). 8) Turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage (12) with at least one gas compressor (14), a heat exchanger (1 6), a combustion chamber (18) supplied with fuel by at least one reservoir (20), at least one expansion stage (22) with at least one expansion turbine (24) connected by a shaft (26) to the compressor, and energy generating means (28), characterized in that it comprises a combustion chamber (18) according to one of the preceding claims.
EP17705924.3A 2016-03-18 2017-02-23 Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy Active EP3430316B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1652294A FR3049044B1 (en) 2016-03-18 2016-03-18 COMBUSTION CHAMBER OF A TURBINE, IN PARTICULAR OF A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, PARTICULARLY ELECTRICAL ENERGY.
PCT/EP2017/054167 WO2017157631A1 (en) 2016-03-18 2017-02-23 Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy

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EP3430316A1 true EP3430316A1 (en) 2019-01-23
EP3430316B1 EP3430316B1 (en) 2020-10-21

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FR3084447B1 (en) 2018-07-30 2020-07-31 Ifp Energies Now COMBUSTION CHAMBER FOR A GAS TURBINE INTENDED FOR ENERGY PRODUCTION, ESPECIALLY ELECTRICAL ENERGY, INCLUDING ASYMMETRICAL DILUTION HOLES IN A FLAME TUBE.
FR3084450B1 (en) 2018-07-30 2020-07-31 Ifp Energies Now COMBUSTION CHAMBER INCLUDING A PASSAGE SECTION OF A MODIFIED FLAME TUBE IN PARTICULAR FOR A TURBINE INTENDED FOR ENERGY PRODUCTION, ESPECIALLY ELECTRICAL ENERGY
FR3088969B1 (en) 2018-11-27 2021-02-19 Ifp Energies Now Fuel injector with cooling means
FR3119868B1 (en) 2021-02-15 2023-01-13 Ifp Energies Now Combustion system with a tubular combustion chamber and an annular heat exchanger

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2517015A (en) * 1945-05-16 1950-08-01 Bendix Aviat Corp Combustion chamber with shielded fuel nozzle
GB624779A (en) * 1946-01-09 1949-06-16 Bendix Aviat Corp An improved burner for gaseous, liquid or powdered solid fuel
US2621477A (en) * 1948-06-03 1952-12-16 Power Jets Res & Dev Ltd Combustion apparatus having valve controlled passages for preheating the fuel-air mixture
DE1627878A1 (en) 1967-03-14 1970-08-06 Schloemann Ag Device to compensate for the spring deflection on machines, in particular on forging presses or the like.
DE2020416A1 (en) * 1970-04-27 1971-11-11 Motoren Turbinen Union Combustion chamber for gas turbine engines
GB1335134A (en) * 1970-12-05 1973-10-24 Nissan Motor Combustion apparatus of a gas turbine engine
DE10064259B4 (en) * 2000-12-22 2012-02-02 Alstom Technology Ltd. Burner with high flame stability
US6968693B2 (en) * 2003-09-22 2005-11-29 General Electric Company Method and apparatus for reducing gas turbine engine emissions
JP4959620B2 (en) * 2007-04-26 2012-06-27 株式会社日立製作所 Combustor and fuel supply method for combustor
NL2005381C2 (en) * 2010-09-21 2012-03-28 Micro Turbine Technology B V Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine.

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FR3049044B1 (en) 2019-12-20
FR3049044A1 (en) 2017-09-22
WO2017157631A1 (en) 2017-09-21
CN108779918A (en) 2018-11-09
CN108779918B (en) 2020-10-30

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