EP2488792B1 - Multi-point injector for a turbine engine combustion chamber - Google Patents

Multi-point injector for a turbine engine combustion chamber Download PDF

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Publication number
EP2488792B1
EP2488792B1 EP10779566.8A EP10779566A EP2488792B1 EP 2488792 B1 EP2488792 B1 EP 2488792B1 EP 10779566 A EP10779566 A EP 10779566A EP 2488792 B1 EP2488792 B1 EP 2488792B1
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EP
European Patent Office
Prior art keywords
annular
fuel
chamber
ring
orifices
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Application number
EP10779566.8A
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German (de)
French (fr)
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EP2488792A1 (en
Inventor
Didier Hippolyte Hernandez
Thomas Olivier Marie Noel
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention relates to a "multipoint" fuel injection device for an annular turbomachine combustion chamber such as an airplane turbojet or turboprop engine.
  • a turbomachine comprises an annular combustion chamber arranged at the outlet of a high pressure compressor and provided with a plurality of fuel injection devices regularly distributed circumferentially at the inlet of the combustion chamber.
  • Each multipoint injection device comprises a first venturi inside which is mounted a pilot injector centered on the axis of the first venturi and continuously supplied by a pilot circuit and a second venturi coaxial with the first venturi and surrounding it.
  • This second venturi comprises an annular chamber at its upstream end in which is mounted an annular ring supplied with fuel by a multipoint circuit.
  • the ring has fuel injection orifices formed in a front face facing downstream and outward of the second venturi.
  • the pilot circuit continuously provides optimized fuel flow for low revs and the multi-point circuit provides optimized intermittent fuel flow for high revs.
  • Such a fuel injection device is known from the document EP 1 806 536 of the Applicant.
  • the intermittent use of the multipoint circuit has the major drawback of inducing, under the effect of the high temperatures due to the radiation of the flame in the combustion chamber, a scrub or a coking of the stagnant fuel inside the circuit. multipoint when it is cut off. These phenomena can lead to formation of coke in the ring and at the fuel injection ports of the multipoint circuit impacting the fuel spraying by the multipoint circuit and therefore the operation of the combustion chamber.
  • Such a configuration does not, however, sufficiently reduce the risk of coking fuel circulating at the front face of the annular chamber which remains highly exposed to the heat radiation generated by the combustion of the fuel downstream.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a fuel injection device for an annular turbomachine combustion chamber comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit supplying intermittently injection orifices formed in a front face of an upstream annular chamber of a second venturi coaxial with and surrounding the first venturi, an annular ring being mounted in the annular chamber to delimit a fuel supply circuit of the injection ports and a cooling circuit by passage of fuel supplying the injector of the pilot circuit, characterized in that the cooling circuit extends on the front face of the chamber in the immediate vicinity of the injection orifices.
  • a part of the cooling circuit is formed by a groove of a downstream face of the annular ring, this downstream face being applied to the front face of the annular chamber.
  • the cooling circuit also comprises an annular channel formed between the inner cylindrical walls of the ring and the annular chamber, in order to cool the internal cylindrical face of the annular chamber of the second venturi inside which circulates a flow of hot air from the high pressure compressor.
  • the cooling circuit further comprises an annular channel formed between the outer cylindrical walls of the annular ring and the annular chamber, this channel being able to be used for cooling the outer wall of the annular chamber by circulating the fuel of the pilot circuit or for being intended to be isolated from the pilot circuit and to be filled in operation with air or coked fuel as thermal insulation.
  • the outer periphery of the annular chamber of the second venturi is subjected to temperatures lower than those of the inner periphery of the annular chamber and it is therefore not necessary to continuously cool the outer contour of the annular chamber and the use of thermal insulation proves sufficient.
  • the cooling circuit of the front face of the chamber is corrugated and extends alternately radially inside and outside of the injection orifices, which makes it possible to position the cooling system as close as possible to the injection ports.
  • the cooling circuit of the front face of the chamber comprises two semicircular symmetrical branches each extending between input means and fuel outlet means, the latter being connected to the injector of the pilot circuit.
  • the injection of fuel through the orifices of the annular chamber is performed through orifices of the crown which open into the orifices of the annular chamber.
  • the orifices of the downstream wall of the ring have a smaller diameter than that of the orifices of the end face of the annular chamber, which prevents fuel drops coming out of the orifices of the ring from coking the holes of the ring. the wall of the chamber, when stopping the multipoint circuit.
  • the invention also relates to an annular turbomachine combustion chamber comprising at least one fuel injection device of the type described above.
  • the invention also relates to a turbomachine, such as a turbojet engine or a turboprop engine, comprising at least one fuel injection device of the type described above.
  • FIG. 1 representing an injection device 10 comprising two fuel injection systems, one of which is a permanently operating pilot system and the other a multipoint system operating intermittently.
  • This device is intended to be mounted in an opening of a bottom wall of an annular combustion chamber of a turbomachine which is supplied with air by an upstream high-pressure compressor and whose combustion gases feed a turbine mounted downstream.
  • This device comprises a first venturi 12 and a second venturi 14 coaxial, the first venturi 12 being mounted inside the second venturi 14.
  • a pilot injector 16 is mounted inside a first stage of tendrils 18 inserted axially to Inside the first venturi 12.
  • a second stage of tendrils 20 is formed at the upstream end and radially outside the first venturi 12 and separates the first 12 and second 14 venturis.
  • the second venturi 14 comprises an annular chamber 22 formed by two radially inner cylindrical walls 24 and outer 26 connected to each other by a frustoconical downstream wall 28 converging downstream.
  • An annular ring 30 also comprising two radially inner cylindrical walls 32 and external wall 34 connected to each other by a downstream convergent downstream conical downstream wall 36 is mounted inside the annular chamber 22 so that the downstream walls 28, 36 of the annular chamber 22 and the annular ring 30 are in contact.
  • the annular ring 30 is centered inside the annular chamber 22 by means of an annular shoulder 38 formed inside the annular chamber 30 at the junction of the frustoconical downstream wall 28 and the internal cylindrical wall 24 of the chamber ring 22.
  • the annular ring 30 and the annular chamber 22 each comprise an annular opening at their upstream end.
  • the cylindrical walls 24, 26 of the annular chamber 22 extend projecting upstream with respect to the upstream ends of the cylindrical walls 32, 34 of the annular ring 30.
  • the downstream wall 36 of the annular ring 30 comprises injection orifices 40 uniformly distributed circumferentially and opening into corresponding orifices 42 in the downstream wall 28 of the chamber 22.
  • the orifices 40, 42 of the annular chamber 22 and the annular ring 30 have identical diameters.
  • An inner annular channel 44 is defined between the inner cylindrical walls 24, 32 of the annular ring 30 and the annular chamber 22.
  • an outer annular channel 46 is defined between the outer cylindrical walls 26, 34 of the annular ring. 30 and the annular chamber 22.
  • the injection device comprises a body 48 whose downstream portion is annular and comprises a cylindrical duct 50 axially engaged sealing between the inner cylindrical walls 24 and outer 26 of the annular chamber 22 and opening sealing between the inner cylindrical walls 32 and outer ring 34 of the annular ring 30.
  • the duct 50 has a radial shoulder 54 abutting on the upstream ends of the inner cylindrical walls 32 and outer 34 of the annular ring 30.
  • This sealing assembly of the body 48 makes it possible to guarantee that the inner and outer annular channels 44 and 44 are sealed with respect to the annular space formed inside the annular ring 30.
  • a fuel supply arm 56 is connected to the body 48 and comprises two coaxial ducts of which one central 58 feeds a channel 60 of the body 48 opening downstream inside the annular ring 30 and the other formed outer 62 around the central duct 58 supplies at the output of separate channels (not shown) opening into the inner annular channels 44 and outer 46, respectively.
  • the body 48 comprises a fuel collection cavity 64 formed diametrically opposite the fuel supply arm 56 and at the upstream ends of the cylindrical walls 32, 34 of the annular ring 30 so that the annular channels internal 44 and outer 46 communicate with the collection cavity 64.
  • a duct 66 is connected at one end to the pilot injector 16 and at the other end to the body 48 and opens into the collection cavity 64.
  • the central duct 58 of the arm 56 supplies fuel to the channel 60 of the body 48, the fuel then circulating in the annular ring 30 and being injected into the combustion chamber downstream through the orifices 40, 42 of the ring gear 30 and from bedroom 22.
  • the outer conduit 62 of the arm 56 feeds the channels of the body 48 opening into the inner annular channels 44 and outer 46, the fuel then flowing into the collection cavity 64 to supply the pilot injector 16 via the conduit 66 .
  • This circuit forms the pilot circuit and operates continuously while the multipoint circuit operates intermittently during specific flight phases such as takeoff requiring additional power.
  • the hot air (at about 600 ° C.) coming from the high-pressure compressor flows inside the first venturi 12, in the first radial swirler 18, and from the air also flows inside the second radial swirler 20, between the first 12 and second 14 venturis.
  • the front downstream face 28 of the annular chamber 22 is also subjected to thermal radiation combustion, which can lead to coking of the fuel in the injection orifices 40, 42 of the ring 30 and the chamber annular 22 during flight phases where the multipoint circuit is not used.
  • the invention provides a solution to this problem by integrating in the injection device 67 a cooling circuit of the frustoconical front wall 68 of the annular chamber 70, in the immediate vicinity of the injection orifices as shown in the drawings. Figures 2 to 4 .
  • This cooling circuit comprises a groove 72 formed on the downstream face of the frustoconical wall 74 of the annular ring 76, which is applied to the upstream face of the frustoconical wall 68 of the annular chamber 70.
  • the groove 72 is corrugated and extends alternately radially inside and inside the injection ports 78 of the annular ring 76, which makes it possible to cool as much as possible the orifices 78 of the ring 76 and the orifices 80 of the annular chamber 70.
  • the groove 72 comprises two semicircular branches fueled by two channels 82, 84 of the body 48 and connected to the output cavity 64 diametrically opposite. The two branches are symmetrical with respect to a plane passing through the axis of the pilot injector 16 and halfway between the two channels 82, 84 for feeding the groove 72.
  • the cooling circuit according to the invention also comprises an internal annular groove 86 formed in the thickness of the inner cylindrical wall 88 of the ring 76, this groove 86 delimiting an internal annular channel with the internal cylindrical wall 90 of the annular chamber 70
  • the inner annular channel is supplied with fuel by two channels 92, 94 of the body 48 and is connected at the outlet to the collection cavity 64, for cooling the internal cylindrical walls 88, 90 of the annular ring 76 and the annular chamber 70.
  • Two semicircular grooves 96, 98 are formed in the thickness of the outer cylindrical wall 100 of the annular ring 76 and delimit with the outer cylindrical wall 102 of the annular chamber 70 two semicircular channels whose circumferential ends are closed by axial ribs 104 of the annular ring 76. In this way, the two outer semi-circular channels are isolated from the collection chamber supplying the pilot injector.
  • the two channels 96, 98 semicircular are filled with air.
  • these channels can be filled with air if the seal is realized with respect to the pilot circuit and in particular with respect to the front circuit or they can be filled with fuel in the opposite case, which fuel cokes under the effect of the high temperatures.
  • the air or the coked fuel forms a thermal insulator, which is sufficient to prevent coking of the fuel inside the ring as the outer peripheries of the annular ring 76 and the annular chamber 70 are subjected to temperatures lower than those to which the internal peripheries of these same parts are subjected.
  • the orifices 78 of the downstream frustoconical wall 74 of the annular ring 76 have a diameter smaller than that of the orifices of the frustoconical front face 68 of the annular chamber 70. This prevents, when the multipoint circuit is stopped, that drops of fuel remain at the orifices 78 of the annular ring 76 do not coke the orifices 80 of the annular chamber 70.
  • the diameter of the orifices 78 of the annular ring 76 is of the order of 0.5 mm and that of the orifices 80 of the annular chamber 70 is of the order of 1 mm.
  • the downstream face of the frustoconical wall 74 of the ring 72 is fixed to seal on the frustoconical wall 68 of the annular chamber 70, for example by brazing.
  • the junction between an orifice 78 of the ring 76 and an orifice 80 of the annular chamber 70 is sealed.
  • brazing it is possible to produce in one piece, for example by laser sintering, the annular ring 76 and the second venturi 14 comprising the annular chamber 70.
  • the invention is not limited to the corrugated cooling circuit as described above. It is thus possible to form two grooves in the downstream face of the downstream wall 74 of the ring 76, one of the grooves being located radially inside the orifices 78 of the ring 76 and the other being located radially at the outside of these same orifices 78.
  • this circuit would not better cool the orifices 78, 80 of the annular ring 76 and the annular chamber 70 and in particular the circumferential inter-orifices spaces.
  • the external channels 96, 98 are connected to the collection cavity 64 supplying the pilot injector 16 and participate in the cooling of the annular chamber 70 by circulating the fuel of the pilot injector 16.

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

Description

La présente invention concerne un dispositif d'injection de carburant « multipoint » pour une chambre annulaire de combustion de turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to a "multipoint" fuel injection device for an annular turbomachine combustion chamber such as an airplane turbojet or turboprop engine.

De manière connue, une turbomachine comprend une chambre annulaire de combustion agencée en sortie d'un compresseur haute pression et pourvue d'une pluralité de dispositifs d'injection de carburant régulièrement répartis circonférentiellement à l'entrée de la chambre de combustion. Chaque dispositif d'injection multipoint comprend un premier venturi à l'intérieur duquel est monté un injecteur pilote centré sur l'axe du premier venturi et alimenté en permanence par un circuit pilote et un second venturi coaxial au premier venturi et entourant celui-ci. Ce second venturi comprend une chambre annulaire à son extrémité amont dans laquelle est montée une couronne annulaire alimentée en carburant par un circuit multipoint. La couronne comporte des orifices d'injection de carburant formés dans une face frontale orientée vers l'aval et vers l'extérieur du second venturi.In known manner, a turbomachine comprises an annular combustion chamber arranged at the outlet of a high pressure compressor and provided with a plurality of fuel injection devices regularly distributed circumferentially at the inlet of the combustion chamber. Each multipoint injection device comprises a first venturi inside which is mounted a pilot injector centered on the axis of the first venturi and continuously supplied by a pilot circuit and a second venturi coaxial with the first venturi and surrounding it. This second venturi comprises an annular chamber at its upstream end in which is mounted an annular ring supplied with fuel by a multipoint circuit. The ring has fuel injection orifices formed in a front face facing downstream and outward of the second venturi.

Le circuit pilote fournit en permanence un débit de carburant optimisé pour les bas régimes et le circuit multipoint fournit un débit de carburant intermittent optimisé pour les hauts régimes. Un tel dispositif d'injection de carburant est connu du document EP 1 806 536 de la Demanderesse.The pilot circuit continuously provides optimized fuel flow for low revs and the multi-point circuit provides optimized intermittent fuel flow for high revs. Such a fuel injection device is known from the document EP 1 806 536 of the Applicant.

Toutefois, l'utilisation intermittente du circuit multipoint a pour inconvénient majeur d'induire, sous l'effet des températures élevées dues au rayonnement de la flamme dans la chambre de combustion, un gommage ou une cokéfaction du carburant stagnant à l'intérieur du circuit multipoint lorsque celui-ci est coupé. Ces phénomènes peuvent entraîner un formation de coke dans la couronne et au niveau des orifices d'injection de carburant du circuit multipoint impactant la pulvérisation du carburant par le circuit multipoint et donc le fonctionnement de la chambre de combustion.However, the intermittent use of the multipoint circuit has the major drawback of inducing, under the effect of the high temperatures due to the radiation of the flame in the combustion chamber, a scrub or a coking of the stagnant fuel inside the circuit. multipoint when it is cut off. These phenomena can lead to formation of coke in the ring and at the fuel injection ports of the multipoint circuit impacting the fuel spraying by the multipoint circuit and therefore the operation of the combustion chamber.

Pour réduire ce risque de cokéfaction, il est connu du document EP 2026002 de la Demanderesse d'utiliser le circuit pilote de carburant pour refroidir le circuit multipoint et y réduire la formation de coke, grâce à deux canaux annulaires formés dans la chambre annulaire radialement à l'intérieur et à l'extérieur de la couronne annulaire, ces deux canaux étant reliés en sortie à l'injecteur pilote.To reduce this risk of coking, it is known from the document EP 2026002 of the Applicant to use the fuel pilot circuit to cool the multipoint circuit and reduce coke formation therein, thanks to two annular channels formed in the annular chamber radially inside and outside the annular ring, these two channels being connected at the output to the pilot injector.

Une telle configuration ne permet pas toutefois de réduire de manière suffisante les risques de cokéfaction du carburant circulant au niveau de la face frontale de la chambre annulaire qui reste fortement exposée au rayonnement thermique généré par la combustion du carburant en aval.Such a configuration does not, however, sufficiently reduce the risk of coking fuel circulating at the front face of the annular chamber which remains highly exposed to the heat radiation generated by the combustion of the fuel downstream.

L'invention a notamment pour but d'apporter une solution simple, efficace et économique à ce problème.The invention aims in particular to provide a simple, effective and economical solution to this problem.

A cet effet, elle propose un dispositif d'injection de carburant pour une chambre annulaire de combustion de turbomachine, comprenant un circuit pilote alimentant en permanence un injecteur débouchant dans un premier venturi et un circuit multipoint alimentant par intermittence des orifices d'injection formés dans une face frontale d'une chambre annulaire amont d'un second venturi coaxial au premier venturi et entourant celui-ci, une couronne annulaire étant montée dans la chambre annulaire pour y délimiter un circuit d'alimentation en carburant des orifices d'injection et un circuit de refroidissement par passage du carburant alimentant l'injecteur du circuit pilote, caractérisé en ce que le circuit de refroidissement s'étend sur la face frontale de la chambre au voisinage immédiat des orifices d'injection.For this purpose, it proposes a fuel injection device for an annular turbomachine combustion chamber, comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit supplying intermittently injection orifices formed in a front face of an upstream annular chamber of a second venturi coaxial with and surrounding the first venturi, an annular ring being mounted in the annular chamber to delimit a fuel supply circuit of the injection ports and a cooling circuit by passage of fuel supplying the injector of the pilot circuit, characterized in that the cooling circuit extends on the front face of the chamber in the immediate vicinity of the injection orifices.

L'intégration d'une partie du circuit de refroidissement au niveau de la face frontale de la chambre annulaire qui est la plus exposée au rayonnement thermique, permet de refroidir en permanence la partie de cette face frontale qui est au voisinage immédiat des orifices d'injection pour éviter leur cokéfaction.The integration of a portion of the cooling circuit at the end face of the annular chamber which is the most exposed to thermal radiation, allows to permanently cool the portion of this end face which is in the immediate vicinity of the orifices of injection to avoid coking.

Avantageusement, une partie du circuit de refroidissement est formée par une rainure d'une face aval de la couronne annulaire, cette face aval étant appliquée sur la face frontale de la chambre annulaire.Advantageously, a part of the cooling circuit is formed by a groove of a downstream face of the annular ring, this downstream face being applied to the front face of the annular chamber.

On peut ainsi réaliser simplement et à moindre coût le circuit de refroidissement de la face frontale de la chambre annulaire.It is thus possible simply and inexpensively to produce the cooling circuit of the end face of the annular chamber.

Le circuit de refroidissement comporte également un canal annulaire formé entre les parois cylindriques internes de la couronne et de la chambre annulaire, afin de refroidir la face cylindrique interne de la chambre annulaire du second venturi à l'intérieur duquel circule un flux d'air chaud en provenance du compresseur haute pression.The cooling circuit also comprises an annular channel formed between the inner cylindrical walls of the ring and the annular chamber, in order to cool the internal cylindrical face of the annular chamber of the second venturi inside which circulates a flow of hot air from the high pressure compressor.

Le circuit de refroidissement comporte encore un canal annulaire formé entre les parois cylindriques externes de la couronne annulaire et de la chambre annulaire, ce canal pouvant servir au refroidissement de la paroi externe de la chambre annulaire par circulation du carburant du circuit pilote ou bien étant destiné à être isolé du circuit pilote et à être rempli en fonctionnement d'air ou de carburant cokéfié servant d'isolant thermique.The cooling circuit further comprises an annular channel formed between the outer cylindrical walls of the annular ring and the annular chamber, this channel being able to be used for cooling the outer wall of the annular chamber by circulating the fuel of the pilot circuit or for being intended to be isolated from the pilot circuit and to be filled in operation with air or coked fuel as thermal insulation.

En fonctionnement, la périphérie externe de la chambre annulaire du second venturi est soumise à des températures plus basses que celles de la périphérie interne de la chambre annulaire et il n'est donc pas nécessaire de refroidir en permanence le contour externe de la chambre annulaire et l'utilisation d'un isolant thermique s'avère suffisante.In operation, the outer periphery of the annular chamber of the second venturi is subjected to temperatures lower than those of the inner periphery of the annular chamber and it is therefore not necessary to continuously cool the outer contour of the annular chamber and the use of thermal insulation proves sufficient.

Selon un mode de réalisation préféré de l'invention, le circuit de refroidissement de la face frontale de la chambre est ondulé et s'étend en alternance radialement à l'intérieur et à l'extérieur des orifices d'injection, ce qui permet de positionner le circuit de refroidissement au plus près des orifices d'injection.According to a preferred embodiment of the invention, the cooling circuit of the front face of the chamber is corrugated and extends alternately radially inside and outside of the injection orifices, which makes it possible to position the cooling system as close as possible to the injection ports.

Avantageusement, le circuit de refroidissement de la face frontale de la chambre comprend deux branches symétriques semi-circulaires s'étendant chacune entre des moyens d'entrée et des moyens de sortie du carburant, ces derniers étant reliés à l'injecteur du circuit pilote.Advantageously, the cooling circuit of the front face of the chamber comprises two semicircular symmetrical branches each extending between input means and fuel outlet means, the latter being connected to the injector of the pilot circuit.

L'injection de carburant par les orifices de la chambre annulaire est réalisée par l'intermédiaire d'orifices de la couronne qui débouchent dans les orifices de la chambre annulaire.The injection of fuel through the orifices of the annular chamber is performed through orifices of the crown which open into the orifices of the annular chamber.

Avantageusement, les orifices de la paroi aval de la couronne ont un diamètre inférieur à celui des orifices de la face frontale de la chambre annulaire, ce qui évite que des gouttes de carburant sortant des orifices de la couronne n'obturent par cokéfaction les orifices de la paroi de la chambre, lors de l'arrêt du circuit multipoint.Advantageously, the orifices of the downstream wall of the ring have a smaller diameter than that of the orifices of the end face of the annular chamber, which prevents fuel drops coming out of the orifices of the ring from coking the holes of the ring. the wall of the chamber, when stopping the multipoint circuit.

L'invention concerne également une chambre annulaire de combustion de turbomachine comprenant au moins un dispositif d'injection de carburant du type décrit ci-dessus.The invention also relates to an annular turbomachine combustion chamber comprising at least one fuel injection device of the type described above.

L'invention concerne encore une turbomachine, telle qu'un turboréacteur ou un turbopropulseur, comprenant au moins un dispositif d'injection de carburant du type décrit ci-dessus.The invention also relates to a turbomachine, such as a turbojet engine or a turboprop engine, comprising at least one fuel injection device of the type described above.

L'invention sera mieux comprise et d'autres détails, avantages et caractéristiques de l'invention apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif, en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique partielle en coupe axiale d'un dispositif d'injection de carburant multipoint selon la technique antérieure ;
  • la figure 2 est une vue schématique partielle en coupe axiale d'un dispositif d'injection de carburant multipoint selon l'invention ;
  • la figure 3 est une vue schématique en perspective du dispositif d'injection de la figure 2 depuis l'aval,
  • la figure 4 est une vue schématique en perspective du dispositif d'injection de la figure 2 depuis l'aval et selon un autre angle de vue.
The invention will be better understood and other details, advantages and features of the invention will appear on reading the following description given by way of non-limiting example, with reference to the accompanying drawings in which:
  • the figure 1 is a partial diagrammatic view in axial section of a multipoint fuel injection device according to the prior art;
  • the figure 2 is a partial schematic view in axial section of a multipoint fuel injection device according to the invention;
  • the figure 3 is a schematic perspective view of the injection device of the figure 2 since the downstream,
  • the figure 4 is a schematic perspective view of the injection device of the figure 2 from downstream and from another angle of view.

On se réfère tout d'abord à la figure 1 représentant un dispositif d'injection 10 comportant deux systèmes d'injection de carburant dont l'un est un système pilote fonctionnant en permanence et l'autre un système multipoint fonctionnant par intermittence. Ce dispositif est destiné à être monté dans une ouverture d'une paroi de fond d'une chambre de combustion annulaire d'une turbomachine qui est alimentée en air par un compresseur haute-pression amont et dont les gaz de combustion alimentent une turbine montée en aval.We first refer to the figure 1 representing an injection device 10 comprising two fuel injection systems, one of which is a permanently operating pilot system and the other a multipoint system operating intermittently. This device is intended to be mounted in an opening of a bottom wall of an annular combustion chamber of a turbomachine which is supplied with air by an upstream high-pressure compressor and whose combustion gases feed a turbine mounted downstream.

Ce dispositif comprend un premier venturi 12 et un second venturi 14 coaxiaux, le premier venturi 12 étant monté à l'intérieur du second venturi 14. Un injecteur pilote 16 est monté à l'intérieur d'un premier étage de vrilles 18 inséré axialement à l'intérieur du premier venturi 12. Un second étage de vrilles 20 est formé à l'extrémité amont et radialement à l'extérieur du premier venturi 12 et sépare les premier 12 et second 14 venturis.This device comprises a first venturi 12 and a second venturi 14 coaxial, the first venturi 12 being mounted inside the second venturi 14. A pilot injector 16 is mounted inside a first stage of tendrils 18 inserted axially to Inside the first venturi 12. A second stage of tendrils 20 is formed at the upstream end and radially outside the first venturi 12 and separates the first 12 and second 14 venturis.

Le second venturi 14 comprend une chambre annulaire 22 formée par deux parois cylindriques radialement interne 24 et externe 26 reliées l'une à l'autre par une paroi aval tronconique 28 convergeant vers l'aval. Une couronne annulaire 30 comprenant également deux parois cylindriques radialement interne 32 et externe 34 reliée l'une à l'autre par une paroi aval tronconique 36 convergeant vers l'aval est montée à l'intérieur de la chambre annulaire 22 de manière à ce que les parois aval 28, 36 de la chambre annulaire 22 et de la couronne annulaire 30 soient en contact. La couronne annulaire 30 est centrée à l'intérieure de la chambre annulaire 22 grâce à un épaulement annulaire 38 formé à l'intérieur de la chambre annulaire 30 à la jonction de la paroi aval tronconique 28 et de la paroi cylindrique interne 24 de la chambre annulaire 22.The second venturi 14 comprises an annular chamber 22 formed by two radially inner cylindrical walls 24 and outer 26 connected to each other by a frustoconical downstream wall 28 converging downstream. An annular ring 30 also comprising two radially inner cylindrical walls 32 and external wall 34 connected to each other by a downstream convergent downstream conical downstream wall 36 is mounted inside the annular chamber 22 so that the downstream walls 28, 36 of the annular chamber 22 and the annular ring 30 are in contact. The annular ring 30 is centered inside the annular chamber 22 by means of an annular shoulder 38 formed inside the annular chamber 30 at the junction of the frustoconical downstream wall 28 and the internal cylindrical wall 24 of the chamber ring 22.

La couronne annulaire 30 et la chambre annulaire 22 comprennent chacune une ouverture annulaire à leur extrémité amont. Les parois cylindriques 24, 26 de la chambre annulaire 22 s'étendent en saillie vers l'amont par rapport aux extrémités amont des parois cylindriques 32, 34 de la couronne annulaire 30.The annular ring 30 and the annular chamber 22 each comprise an annular opening at their upstream end. The cylindrical walls 24, 26 of the annular chamber 22 extend projecting upstream with respect to the upstream ends of the cylindrical walls 32, 34 of the annular ring 30.

La paroi aval 36 de la couronne annulaire 30 comprend des orifices d'injection 40 régulièrement répartis circonférentiellement et débouchant dans des orifices 42 correspondants de la paroi aval 28 de la chambre annulaire 22. Les orifices 40, 42 de la chambre annulaire 22 et de la couronne annulaire 30 ont des diamètres identiques.The downstream wall 36 of the annular ring 30 comprises injection orifices 40 uniformly distributed circumferentially and opening into corresponding orifices 42 in the downstream wall 28 of the chamber 22. The orifices 40, 42 of the annular chamber 22 and the annular ring 30 have identical diameters.

Un canal annulaire interne 44 est défini entre les parois cylindriques internes 24, 32 de la couronne annulaire 30 et de la chambre annulaire 22. De manière similaire, un canal annulaire externe 46 est défini entre les parois cylindriques externes 26, 34 de la couronne annulaire 30 et de la chambre annulaire 22.An inner annular channel 44 is defined between the inner cylindrical walls 24, 32 of the annular ring 30 and the annular chamber 22. Similarly, an outer annular channel 46 is defined between the outer cylindrical walls 26, 34 of the annular ring. 30 and the annular chamber 22.

Le dispositif d'injection comprend un corps 48 dont la partie aval est annulaire et comprend un conduit cylindrique 50 engagé axialement à étanchéité entre les parois cylindriques interne 24 et externe 26 de la chambre annulaire 22 et débouchant à étanchéité entre les parois cylindriques interne 32 et externe 34 de la couronne annulaire 30. Le conduit 50 comporte un épaulement radial 54 venant en butée sur les extrémités amont des parois cylindriques interne 32 et externe 34 de la couronne annulaire 30.The injection device comprises a body 48 whose downstream portion is annular and comprises a cylindrical duct 50 axially engaged sealing between the inner cylindrical walls 24 and outer 26 of the annular chamber 22 and opening sealing between the inner cylindrical walls 32 and outer ring 34 of the annular ring 30. The duct 50 has a radial shoulder 54 abutting on the upstream ends of the inner cylindrical walls 32 and outer 34 of the annular ring 30.

Ce montage à étanchéité du corps 48 permet de garantir que les canaux annulaires interne 44 et externe 46 sont étanches par rapport à l'espace annulaire formé à l'intérieur de la couronne annulaire 30.This sealing assembly of the body 48 makes it possible to guarantee that the inner and outer annular channels 44 and 44 are sealed with respect to the annular space formed inside the annular ring 30.

Un bras 56 d'alimentation en carburant est relié au corps 48 et comprend deux conduits coaxiaux dont l'un 58 central alimente un canal 60 du corps 48 débouchant en aval à l'intérieur de la couronne annulaire 30 et l'autre 62 externe formé autour du conduit central 58 alimente en sortie des canaux distincts (non représentés) débouchant dans les canaux annulaires interne 44 et externe 46, respectivement.A fuel supply arm 56 is connected to the body 48 and comprises two coaxial ducts of which one central 58 feeds a channel 60 of the body 48 opening downstream inside the annular ring 30 and the other formed outer 62 around the central duct 58 supplies at the output of separate channels (not shown) opening into the inner annular channels 44 and outer 46, respectively.

Le corps 48 comprend une cavité 64 de collecte du carburant formée diamétralement à l'opposé du bras 56 d'alimentation en carburant et au niveau des extrémités amont des parois cylindriques 32, 34 de la couronne annulaire 30 de manière à ce que les canaux annulaires interne 44 et externe 46 communiquent avec la cavité de collecte 64. Un conduit 66 est relié à une extrémité à l'injecteur pilote 16 et à l'autre extrémité au corps 48 et débouche dans la cavité de collecte 64.The body 48 comprises a fuel collection cavity 64 formed diametrically opposite the fuel supply arm 56 and at the upstream ends of the cylindrical walls 32, 34 of the annular ring 30 so that the annular channels internal 44 and outer 46 communicate with the collection cavity 64. A duct 66 is connected at one end to the pilot injector 16 and at the other end to the body 48 and opens into the collection cavity 64.

En fonctionnement, le conduit central 58 du bras 56 alimente en carburant le canal 60 du corps 48, le carburant circulant ensuite dans la couronne annulaire 30 et étant injecté dans la chambre de combustion en aval par les orifices 40, 42 de la couronne 30 et de la chambre 22.In operation, the central duct 58 of the arm 56 supplies fuel to the channel 60 of the body 48, the fuel then circulating in the annular ring 30 and being injected into the combustion chamber downstream through the orifices 40, 42 of the ring gear 30 and from bedroom 22.

Le conduit externe 62 du bras 56 alimente les canaux du corps 48 débouchant dans les canaux annulaires interne 44 et externe 46, le carburant s'écoulant ensuite dans la cavité de collecte 64 pour alimenter l'injecteur pilote 16 par l'intermédiaire du conduit 66.The outer conduit 62 of the arm 56 feeds the channels of the body 48 opening into the inner annular channels 44 and outer 46, the fuel then flowing into the collection cavity 64 to supply the pilot injector 16 via the conduit 66 .

Ce circuit forme le circuit pilote et fonctionne en permanence tandis que le circuit multipoint fonctionne par intermittence lors des phases de vol spécifiques telles que le décollage nécessitant un surcroît de puissance.This circuit forms the pilot circuit and operates continuously while the multipoint circuit operates intermittently during specific flight phases such as takeoff requiring additional power.

Lors du fonctionnement de la turbomachine, l'air chaud (à environ 600°C) en provenance du compresseur haute pression s'écoule à l'intérieur du premier venturi 12, dans la première vrille radiale 18, et de l'air s'écoule également à l'intérieur de la seconde vrille radiale 20, entre les premier 12 et second 14 venturis.During the operation of the turbomachine, the hot air (at about 600 ° C.) coming from the high-pressure compressor flows inside the first venturi 12, in the first radial swirler 18, and from the air also flows inside the second radial swirler 20, between the first 12 and second 14 venturis.

Les canaux annulaires interne 44 et externe 46 dans lesquels circule en permanence du carburant d'alimentation de l'injecteur pilote, forment un circuit de refroidissement radialement à l'extérieur et à l'intérieur de la couronne annulaire 30, ce qui évite une cokéfaction du carburant dans la couronne 30 due au rayonnement thermique de la combustion, et ceci lors des phases de vol où le circuit multi-point n'est pas en fonctionnement.The inner annular channels 44 and outer 46 in which continuously circulates fuel supply of the pilot injector, form a cooling circuit radially outside and inside the annular ring 30, which prevents coking fuel in the ring 30 due to the thermal radiation of the combustion, and this during phases of flight where the multi-point circuit is not in operation.

Comme indiqué précédemment, la face aval frontale 28 de la chambre annulaire 22 est soumise également au rayonnement thermique de la combustion, ce qui peut conduire à une cokéfaction du carburant dans les orifices d'injection 40, 42 de la couronne 30 et de la chambre annulaire 22 lors des phases de vol où le circuit multipoint n'est pas utilisé.As indicated above, the front downstream face 28 of the annular chamber 22 is also subjected to thermal radiation combustion, which can lead to coking of the fuel in the injection orifices 40, 42 of the ring 30 and the chamber annular 22 during flight phases where the multipoint circuit is not used.

L'invention apporte une solution à ce problème en intégrant dans le dispositif d'injection 67 un circuit de refroidissement de la paroi frontale tronconique 68 de la chambre annulaire 70, au voisinage immédiat des orifices d'injection comme cela est représenté sur les figures 2 à 4.The invention provides a solution to this problem by integrating in the injection device 67 a cooling circuit of the frustoconical front wall 68 of the annular chamber 70, in the immediate vicinity of the injection orifices as shown in the drawings. Figures 2 to 4 .

Ce circuit de refroidissement comporte une rainure 72 formée sur la face aval de la paroi tronconique 74 de la couronne annulaire 76, qui est appliquée sur la face amont de la paroi tronconique 68 de la chambre annulaire 70.This cooling circuit comprises a groove 72 formed on the downstream face of the frustoconical wall 74 of the annular ring 76, which is applied to the upstream face of the frustoconical wall 68 of the annular chamber 70.

La rainure 72 est ondulée et s'étend en alternance radialement à l'intérieur et à l'intérieur des orifices d'injection 78 de la couronne annulaire 76, ce qui permet de refroidir au mieux les orifices 78 de la couronne 76 et les orifices 80 de la chambre annulaire 70. Dans cette réalisation, la rainure 72 comporte deux branches semi-circulaires alimentées en carburant par deux canaux 82, 84 du corps 48 et reliées en sortie à la cavité de collecte 64 diamétralement opposée. Les deux branches sont symétriques par rapport à un plan passant par l'axe de l'injecteur pilote 16 et à mi-distance entre les deux canaux 82, 84 d'alimentation de la rainure 72.The groove 72 is corrugated and extends alternately radially inside and inside the injection ports 78 of the annular ring 76, which makes it possible to cool as much as possible the orifices 78 of the ring 76 and the orifices 80 of the annular chamber 70. In this embodiment, the groove 72 comprises two semicircular branches fueled by two channels 82, 84 of the body 48 and connected to the output cavity 64 diametrically opposite. The two branches are symmetrical with respect to a plane passing through the axis of the pilot injector 16 and halfway between the two channels 82, 84 for feeding the groove 72.

Le circuit de refroidissement selon l'invention comprend également une rainure annulaire interne 86 formée dans l'épaisseur de la paroi cylindrique interne 88 de la couronne 76, cette rainure 86 délimitant un canal annulaire interne avec la paroi cylindrique interne 90 de la chambre annulaire 70. Le canal annulaire interne est alimenté en carburant par deux canaux 92, 94 du corps 48 et est relié en sortie à la cavité de collecte 64, pour refroidir les parois cylindriques internes 88, 90 de la couronne annulaire 76 et de la chambre annulaire 70.The cooling circuit according to the invention also comprises an internal annular groove 86 formed in the thickness of the inner cylindrical wall 88 of the ring 76, this groove 86 delimiting an internal annular channel with the internal cylindrical wall 90 of the annular chamber 70 The inner annular channel is supplied with fuel by two channels 92, 94 of the body 48 and is connected at the outlet to the collection cavity 64, for cooling the internal cylindrical walls 88, 90 of the annular ring 76 and the annular chamber 70. .

Deux rainures 96, 98 semi-circulaires sont formées dans l'épaisseur de la paroi cylindrique externe 100 de la couronne annulaire 76 et délimitent avec la paroi cylindrique externe 102 de la chambre annulaire 70 deux canaux semi-circulaires dont les extrémités circonférentielles sont obturées par des nervures axiales 104 de la couronne annulaire 76. De cette manière, les deux canaux semi-circulaires externes sont isolés de la chambre de collecte alimentant l'injecteur pilote.Two semicircular grooves 96, 98 are formed in the thickness of the outer cylindrical wall 100 of the annular ring 76 and delimit with the outer cylindrical wall 102 of the annular chamber 70 two semicircular channels whose circumferential ends are closed by axial ribs 104 of the annular ring 76. In this way, the two outer semi-circular channels are isolated from the collection chamber supplying the pilot injector.

Lors du montage de la couronne 76 à l'intérieur de la chambre annulaire 70, les deux canaux 96, 98 semi-circulaires sont remplis d'air. En fonctionnement, ces canaux peuvent être remplis d'air si l'étanchéité est réalisée par rapport au circuit pilote et en particulier par rapport au circuit frontal ou bien ils peuvent se remplir de carburant dans le cas contraire, lequel carburant se cokéfie sous l'effet des hautes températures. Dans les deux cas, l'air ou le carburant cokéfié forme un isolant thermique, ce qui s'avère suffisant pour éviter une cokéfaction du carburant à l'intérieur de la couronne puisque les périphéries externes de la couronne annulaire 76 et de la chambre annulaire 70 sont soumises à des températures moindres que celles auxquelles sont soumises les périphéries internes de ces mêmes pièces.When mounting the ring 76 inside the annular chamber 70, the two channels 96, 98 semicircular are filled with air. In operation, these channels can be filled with air if the seal is realized with respect to the pilot circuit and in particular with respect to the front circuit or they can be filled with fuel in the opposite case, which fuel cokes under the effect of the high temperatures. In both cases, the air or the coked fuel forms a thermal insulator, which is sufficient to prevent coking of the fuel inside the ring as the outer peripheries of the annular ring 76 and the annular chamber 70 are subjected to temperatures lower than those to which the internal peripheries of these same parts are subjected.

Les orifices 78 de la paroi tronconique aval 74 de la couronne annulaire 76 ont un diamètre inférieur à celui des orifices de la face frontale tronconique 68 de la chambre annulaire 70. Ceci évite, lorsque le circuit multipoint est arrêté, que des gouttes de carburant restées au niveau des orifices 78 de la couronne annulaire 76 n'obturent par cokéfaction les orifices 80 de la chambre annulaire 70. Dans une réalisation particulière, le diamètre des orifices 78 de la couronne annulaire 76 est de l'ordre de 0,5 mm et celui des orifices 80 de la chambre annulaire 70 est de l'ordre de 1 mm.The orifices 78 of the downstream frustoconical wall 74 of the annular ring 76 have a diameter smaller than that of the orifices of the frustoconical front face 68 of the annular chamber 70. This prevents, when the multipoint circuit is stopped, that drops of fuel remain at the orifices 78 of the annular ring 76 do not coke the orifices 80 of the annular chamber 70. In a particular embodiment, the diameter of the orifices 78 of the annular ring 76 is of the order of 0.5 mm and that of the orifices 80 of the annular chamber 70 is of the order of 1 mm.

Afin d'isoler le circuit frontal de refroidissement du circuit multipoint, la face aval de la paroi tronconique 74 de la couronne 72 est fixée à étanchéité sur la paroi tronconique 68 de la chambre annulaire 70, par exemple par brasage. Ainsi, la jonction entre un orifice 78 de la couronne 76 et un orifice 80 de la chambre annulaire 70 est étanche. Au lieu de réaliser un brasage, il est possible de réaliser d'une seule pièce, par exemple par frittage laser, la couronne annulaire 76 et le second venturi 14 comportant la chambre annulaire 70.In order to isolate the front cooling circuit of the multipoint circuit, the downstream face of the frustoconical wall 74 of the ring 72 is fixed to seal on the frustoconical wall 68 of the annular chamber 70, for example by brazing. Thus, the junction between an orifice 78 of the ring 76 and an orifice 80 of the annular chamber 70 is sealed. Instead of brazing, it is possible to produce in one piece, for example by laser sintering, the annular ring 76 and the second venturi 14 comprising the annular chamber 70.

L'invention n'est pas limitée au circuit de refroidissement ondulé tel que décrit précédemment. Il est ainsi possible de former deux rainures dans la face aval de la paroi aval 74 de la couronne 76, l'une des rainures étant est située radialement à l'intérieur des orifices 78 de la couronne 76 et l'autre étant située radialement à l'extérieur de ces mêmes orifices 78. Toutefois, ce circuit ne permettrait pas de refroidir au mieux les orifices 78, 80 de la couronne annulaire 76 et de la chambre annulaire 70 et en particulier les espaces circonférentiels inter-orifices. On pourrait également envisager de relier ces deux rainures interne et externe de la face frontale par des canaux radiaux inter-orifices. Cependant, cette solution induirait la formation d'un écoulement préférentiel dans certains de ces canaux conduisant à un refroidissement non uniforme de la couronne annulaire 76 et de la chambre annulaire 70.The invention is not limited to the corrugated cooling circuit as described above. It is thus possible to form two grooves in the downstream face of the downstream wall 74 of the ring 76, one of the grooves being located radially inside the orifices 78 of the ring 76 and the other being located radially at the outside of these same orifices 78. However, this circuit would not better cool the orifices 78, 80 of the annular ring 76 and the annular chamber 70 and in particular the circumferential inter-orifices spaces. One could also consider connecting these two internal and external grooves of the front face by radial channels inter-orifices. However, this solution would induce the formation of a preferential flow in some of these channels leading to a non-uniform cooling of the annular ring 76 and the annular chamber 70.

Dans une autre variante, les canaux externes 96, 98 sont reliés à la cavité 64 de collecte alimentant l'injecteur pilote 16 et participent au refroidissement de la chambre annulaire 70 par circulation du carburant de l'injecteur pilote 16.In another variant, the external channels 96, 98 are connected to the collection cavity 64 supplying the pilot injector 16 and participate in the cooling of the annular chamber 70 by circulating the fuel of the pilot injector 16.

Claims (12)

  1. A fuel injector device for an annular combustion chamber of a turbine engine, the device comprising a pilot circuit continuously feeding an injector (16) leading into a first venturi (12) and a multipoint circuit intermittently feeding injection orifices (80) formed in a front face (68) of an upstream annular chamber (70) of a second venturi (14) coaxial about the first venturi (12), an annular ring (76) being mounted in the annular chamber (70) to define therein a fuel feed circuit for feeding the injection orifices (80) and a cooling circuit operating by passing the fuel that feeds the injector of the pilot circuit, the injector device being characterized in that the cooling circuit extends over the front face (68) of the chamber (70) in the immediate vicinity of the injection orifices (80).
  2. A device according to claim 1, characterized in that the cooling circuit comprises a groove (72) formed in a downstream face of the annular ring (76), the downstream face being pressed against the front face (68) of the annular chamber (70).
  3. A device according to claim 1 or claim 2, characterized in that the cooling circuit also comprises an annular channel formed between inner cylindrical walls (88, 90) of the ring (76) and of the annular chamber (70).
  4. A device according to any one of claims 1 to 3, characterized in that the cooling circuit also comprises an annular channel formed between the outer cylindrical walls (100, 102) of the ring (76) and of the annular chamber (70).
  5. A device according to claim 4, characterized in that the annular channel formed between the outer cylindrical walls (100, 102) of the ring (76) and of the annular chamber (70) is designed to be isolated from the pilot circuit and to be filled in operation with air or with coked fuel.
  6. A device according to any one of claims 1 to 5, characterized in that the cooling circuit for cooling the front face (68) of the chamber (70) is of undulating shape and extends in alternation radially inside and outside the injection orifices (80).
  7. A device according to any one of claims 1 to 6, characterized in that the cooling circuit for cooling the front face (68) of the chamber (70) comprises two symmetrical semicircular branches, each extending between fuel inlet means and fuel outlet means.
  8. A device according to claim 7, characterized in that the fuel outlet means are connected to the injector (16) of the pilot circuit.
  9. A device according to any one of claims 1 to 8, characterized in that the downstream wall (74) of the ring (76) includes fuel-passing orifices (78) leading into the above-mentioned orifices (80) in the front face (68) of the annular chamber (70).
  10. A device according to claim 9, characterized in that the orifices (78) in the downstream wall (74) of the ring (76) present a diameter that is less than the diameter of the orifices (80) in the front face (68) of the annular chamber (70).
  11. An annular combustion chamber for a turbine engine, the combustion chamber being characterized in that it includes at least one fuel injector device (67) according to any preceding claim.
  12. A turbine engine, such as a turboprop or a turbojet, the engine being characterized in that it includes at least one fuel injector device (67) according to any one of claims 1 to 10.
EP10779566.8A 2009-10-13 2010-10-12 Multi-point injector for a turbine engine combustion chamber Active EP2488792B1 (en)

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FR0904907A FR2951246B1 (en) 2009-10-13 2009-10-13 MULTI-POINT INJECTOR FOR A TURBOMACHINE COMBUSTION CHAMBER
PCT/FR2010/000682 WO2011045486A1 (en) 2009-10-13 2010-10-12 Multi-point injector for a turbine engine combustion chamber

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US20120198852A1 (en) 2012-08-09
US9046271B2 (en) 2015-06-02
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CN102575844A (en) 2012-07-11
JP5762424B2 (en) 2015-08-12
EP2488792A1 (en) 2012-08-22
BR112012008441B1 (en) 2020-09-29
BR112012008441A2 (en) 2016-03-29
FR2951246A1 (en) 2011-04-15
JP2013507599A (en) 2013-03-04
CA2776843A1 (en) 2011-04-21
FR2951246B1 (en) 2011-11-11
CA2776843C (en) 2017-07-04
RU2543097C2 (en) 2015-02-27
RU2012119573A (en) 2013-11-20

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