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EP2026002A1 - Multi-point injector for turbomachine - Google Patents

Multi-point injector for turbomachine Download PDF

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Publication number
EP2026002A1
EP2026002A1 EP08161242A EP08161242A EP2026002A1 EP 2026002 A1 EP2026002 A1 EP 2026002A1 EP 08161242 A EP08161242 A EP 08161242A EP 08161242 A EP08161242 A EP 08161242A EP 2026002 A1 EP2026002 A1 EP 2026002A1
Authority
EP
European Patent Office
Prior art keywords
injector
fuel
multipoint
ferrule
channels
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
EP08161242A
Other languages
German (de)
French (fr)
Other versions
EP2026002B1 (en
Inventor
Didier Hippolyte Hernandez
Thomas Olivier Marie Noel
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2026002A1 publication Critical patent/EP2026002A1/en
Application granted granted Critical
Publication of EP2026002B1 publication Critical patent/EP2026002B1/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
    • F23R3/28—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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49405—Valve or choke making
    • Y10T29/49412—Valve or choke making with assembly, disassembly or composite article making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49405—Valve or choke making
    • Y10T29/49412—Valve or choke making with assembly, disassembly or composite article making
    • Y10T29/49416—Valve or choke making with assembly, disassembly or composite article making with material shaping or cutting
    • Y10T29/49419—Valve or choke making with assembly, disassembly or composite article making with material shaping or cutting including machining or drilling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49428—Gas and water specific plumbing component making
    • Y10T29/49446—Ferrule making or reforming

Definitions

  • the invention relates to a multipoint injector intended to be mounted in an injection system fixed to a combustion chamber casing of a turbomachine, such as an aircraft engine.
  • It relates more particularly to the structure of such an injector, and in particular the part of the structure dedicated to supplying the pilot and multipoint circuits and cooling the latter.
  • Fuel injectors called “multipoint” are new generation injectors that allow adaptation to different speeds of the turbomachine. Each injector is equipped with two fuel circuits: the so-called “pilot” which has a steady flow optimized for low speeds and the one called “multipoint” which has an intermittent flow optimized for high speeds.
  • the multipoint circuit is used when there is a need for additional engine thrust, especially in the cruising and take-off phases of aircraft.
  • the intermittent operation of the multipoint circuit has the major disadvantage of inducing, under the effect of high temperatures, a decomposition otherwise known as coking of the stagnant fuel inside the multipoint circuit when the flow of the latter is greatly reduced. even cut.
  • a decomposition otherwise known as coking of the stagnant fuel inside the multipoint circuit when the flow of the latter is greatly reduced. even cut.
  • the object of the invention is then to propose a new multipoint injector structure making it possible to obtain homogeneous cooling of the stagnant fuel inside the multipoint circuit.
  • the intake chamber is arranged on a sector angular diametrically opposed to the angular sector into which the flow channels in the baffles.
  • the intake chamber is arranged at least partly according to the diameter of the ferrule passing through the multi-point traffic channel.
  • the multipoint fuel flow is homogeneous.
  • the first and second ferrules each comprise a one-piece piece machined with at least one in the form of a first hollow cylindrical crown, the baffles being constituted by said first hollow cylindrical crown and a second cylindrical crown housed at the inside and soldered to the first and whose base is pierced with channels opposite the multipoint channels, in order to control the cooling / supply flow rate in the pilot injection channels.
  • the baffles were made by machining essentially electroerosion directly and partially in one two monobloc ferrules. However, this direct machining in a one-piece part does not allow for grooves of low height, that is to say, baffles of low height.
  • the sections of the baffles and therefore directly machined circuits monobloc can not be adapted to the desired flow rates and speeds.
  • Machine two cylindrical hollow crowns of different section and then lodge one in the other and finally braze together to obtain sections of very precise dimensions.
  • they can be easily adapted to the desired flow rates and / or fuel speeds. It is also possible to use conventional machining techniques without using EDM machining.
  • the inlet chamber is formed in the first ferrule and communicates with the nozzle through a pipe not passing through the tendrils or any space separating them.
  • the pilot circuit is connected to the nozzle by the outside of the injection head. This eliminates the drilling of additional channels in the tendrils as currently performed. This also makes it possible to obtain new configurations of multi-point injector with fine tendrils and / or of multi-twist type, that is to say with several stages of tendrils. Indeed, in these injector configurations, the drilling of the tendrils or the crossing of several floors is impossible to achieve.
  • the pipe is connected on the one hand to the portion of the inlet chamber facing the opening portion of the peripheral baffles and on the other hand to the part of the hub of the stage of tendrils facing and communication with the jet housing.
  • the pipe is a U-shaped bent tube, one of whose branches connected to the hub of the stage of tendrils extends along the axis of the nozzle and the other of the branches connected parallel to the chamber intake extending parallel to the axis of the nozzle.
  • This provides a space-saving connection that does not interfere with the entry of air on the tendrils.
  • the implementation of a bent and brazed tube is also easy to perform and inexpensive.
  • the body of the distributor is pierced with four distinct channels, two of which each communicate with a pilot circulation channel of the first ferrule itself opening on the outer peripheral baffle and the other two each communicate with a pilot circulation channel of the first ferrule itself leading to the internal peripheral baffle.
  • the tendrils of each stage are tendrils arranged helically with respect to the axis of the injector and of constant thickness over the width of the stage.
  • two stages of tendrils nested one inside the other with the device itself encased in the inner opening of the second ferrule.
  • the invention also relates to a combustion chamber for a turbomachine comprising at least one multipoint injector as described above.
  • the invention also relates to a turbomachine comprising a combustion chamber to which is fixed an injector as described above, mounted in an injection system itself attached to the combustion chamber.
  • FIG. figure 1 A combustion chamber portion 1 of a turbomachine is shown in FIG. figure 1 .
  • the combustion chamber 1 usually comprises an outer wall 10, an inner wall 11, hooking flanges 10 and outer inner walls 11 (not shown) with the chamber casing C in a junction zone 12, a chamber fund 13 bolted or welded to the walls 10, 11, a deflector 14 to protect the chamber 13 of the radiation of the flames from combustion, various fairings monoblock or separate and finally a plurality of injection systems 2 in each of which is mounted an injector 3.
  • a revolution combustion chamber usually comprises a large number of injectors 3, generally 10 to 50, depending on the number of engine power to be supplied.
  • Each system injection 2 comprises a bowl 20 diverging towards the interior of the chamber for bursting the outgoing air and fuel mixture jet, a floating ring 21 for sliding the bowl 20 into the anchor sleeve 22, a or several tendrils 23 for introducing air with a gyration movement, an air-cooled collar 24 for thermally protecting the fastening system.
  • Each multipoint injector 3 essentially comprises a fuel supply arm 30, one or more stages of vortex 31 allowing, like the tendrils 23 of the injection system, to introduce air with a gyration movement, a nozzle of fuel 32 placed on the axis II 'of the injector 3 and a network 33 of n fuel injection orifices 330 pierced at the periphery of the injector 3 ( figure 1 ).
  • Each injector 3 is fixed to the chamber housing 10 and is mounted in an injection system 2 described above. More exactly, the supply arm 30 is fixed to the housing 10 in such a way that the network 33 of injection orifices 330 is mounted in the upstream part of the body of tendrils 23 ( figure 1 ).
  • a multipoint injector 3 comprises one or more bleed holes t for introducing air axially into the injection system 2.
  • a multipoint injector 3 is designed to have on the one hand a fuel nozzle 32 disposed along its axis which injects fuel at a steady flow, generally optimized for low speeds of the engine, and on the other hand multipoint ports 330 pierced at the periphery of the injector and injecting fuel at an intermittent flow for the high engine speeds, for example those required during takeoff of an aircraft equipped with the engine.
  • the fuel circuit provided to supply the nozzle 32 and called “pilot circuit” is also used to cool the fuel circuit provided to feed the multipoint ports 330 and called “multipoint circuit”. Indeed, since this multipoint circuit is intended to supply fuel intermittently, fuel stagnates inside it and a risk of coking or scrubbing of this stagnant fuel remains. Constantly cooling the multipoint circuit by the pilot circuit therefore aims to avoid any risk of coking fuel.
  • a multipoint injector 3 firstly comprises a fuel supply arm 30. It also comprises a first ferrule 34 comprising a connection portion 340 for housing an end of the arm 30 and a body portion 341 internally open O1, having an outer diameter D1, and pierced internally with fuel circulation channels 342 communicating with the supply arm 30. At least one stage of tendrils 31 is engaged in the opening of the body of the first ferrule. A jet fuel 32 is housed in a hub portion 310 of the vane stage 31, for injecting fuel from the interior of the circulation channels 342 of the first ferrule towards the axis I of the injection system.
  • the injector 3 finally comprises a second shell 35 which comprises a body portion 350 open internally 02, having an outer diameter D2 and whose periphery is pierced with multipoint channels 351 for injecting fuel to the periphery of the injection system.
  • the output ports 330 of the multipoint channels 351 constitute the multipoint network 33 of the injector.
  • the bodies 341, 350 of the first 34 and second ferrules are nested one inside the other so that their inner openings O1, 02 and outer diameters D1, D2 overlap each other at least partially. Their overlap delimits a hollow volume comprising at least three concentric baffles 36, of which the central 360 opens on the multipoint channels 351 and the other peripherals 361, 362 are adapted to circulate fuel around the central baffle 360 to cool the fuel supplying fuel. the multipoint channels 351 and then to supply the nozzle 32 ( Figure 2C ).
  • the baffles 361, 362 of the fuel pilot circuit are arranged concentrically with the central one 360 of the multipoint circuit in order to cool it as well as possible, and thus to avoid any risk of coking.
  • the central baffle 360 is discontinuous, the peripheral baffles 361, 362 communicate with each other by the discontinuity 3600 made in the central baffle 360, and the internal peripheral baffle 362 does not communicate with the circulation channels 342 pierced in the body of the first ferrule 34.
  • the outer peripheral baffle 361 communicates with a circulation channel 342 ( Figure 2A ) or two circulation channels 342 ( Figure 2B ).
  • the pilot fuel circulates within the inner peripheral baffle 362 from the circulation channel (s) 342 firstly into the outer peripheral baffle 361 and then through the discontinuity 3600.
  • the arrows, represented in Figures 2A and 2B , inside two peripheral cavities 361, 362 thus indicate the route of the pilot fuel before its circulation in the intake channel 310 drilled inside the stage of tendrils 31.
  • the pilot fuel circulating in the duct admission 310 arrives in the nozzle 32 ( Figure 2C ).
  • the three concentric baffles 360, 361, 362 are continuous over their entire circumference ( figures 3 and 3A ) and they each communicate with at least one separate circulation channel 342 ( figure 3C , 3D figures and 3E ).
  • the peripheral baffles 361, 362 open into a fuel intake chamber 37 diametrically opposed to the circulation channels 342 and which communicates with the nozzle 32 (FIG. figure 3B ).
  • the baffles 360, 361, 362 of both the pilot fuel circuit and the multipoint fuel system are concentric complete rings from which homogeneous cooling.
  • the baffles 360, 361, 362 do not communicate with each other, which simplifies their geometry. They can thus be produced by conventional machining.
  • the first 34 and second 35 rings are each constituted by a one-piece piece machined with the second 35 in the form of a first cylindrical ring hollow 350: the baffles 360, 361, 362 are thus constituted by the hollow cylindrical crown 350 and another hollow cylindrical crown 380 housed inside the ring 350 by being brazed therein.
  • the base 380a of this other hollow cylindrical crown 380 is pierced with channels 3800 facing the multipoint channels 351.
  • the ferrule 35 is a one-piece piece machined to form the hollow cylindrical ring 350
  • the other ring 380 is also a single piece 38 of suitable dimensions to be housed inside the large cylindrical ring hollow and machined.
  • the two bases 380a, 350 are soldered tightly together and then drilled simultaneously to obtain the multipoint injection channels 351, 3800.
  • a one-piece piece is produced comprising a large full cylindrical crown 343 and a small full cylindrical ring 344 projecting axially with respect to the large ring 343, the pilot circulation channels 342p and multipoint 342m are drilled in the solid cylindrical rings 343, 344 and then machined the diameters of the solid cylindrical rings 343, 344 drilled.
  • the first ferrule 34 is then engaged in the second ferrule 35 so as to overlap both between the large full and hollow crowns 343, 350 and between the small solid and hollow crowns 344, 380 and then brazing is carried out. sealing rings 343, 350, 344, 380 between them.
  • the inlet chamber 37 is formed in the first ferrule 34 and communicates with the nozzle 32 via a pipe 39 which does not pass through the stages of tendrils 31 or any space between the tendrils.
  • the peripheral pilot fuel circuit is connected to the axis II 'of the injector 3 by the outside of the injection head. Such a connection is advantageous because it can be obtained whatever the configuration of the tendrils 311, 311a (inclination, length, thickness, number of stages of tendrils ).
  • the pipe 39 is preferably connected on the one hand to the portion of the inlet chamber 37 facing the opening portion of the peripheral baffles 361, 362 ( figure 3B ) and on the other hand to the part of the hub of the stage 31 of tendrils opposite and in communication with the housing of the nozzle 32 ( figure 3A ).
  • the pipe 39 is a U-shaped bent tube, one of the branches 390 connected to the hub 310 of the stage 31 of tendrils extends along the axis II 'of the nozzle 32 and the other of the branches 391 connected parallel to the inlet chamber 37 extending parallel to the axis II 'of the nozzle 32.
  • the swirlers of each stage 31, 31a can thus be spirals 31 arranged helically with respect to the axis II 'of the injector and of constant thickness over the width of the stage and advantageously reduced to a minimum.
  • the injector 3 may comprise two stages 31, 31a of tendrils nested one inside the other with the peripheral device itself encased in the inner opening of the ferrule 35 ( figure 3 ).
  • a one-piece piece 4 forming a fuel distributor whose body 40 is brazed inside the connection 340 of the shell 34 and pierced with at least two separate channels 400, 401, 402, 403 each communicating with each other. a part with the inside of the arm 30 connected to the pilot supply circuit and secondly with at least one pilot circulation channel 342p pierced in the shell 34.
  • the distributor 4 also comprises a duct 41 which extends to the the interior of the arm 30 and which is connected on the one hand to the multipoint supply circuit and on the other hand with a multipoint circulation channel 342m pierced in the first ferrule 34.
  • the body 40 of the distributor 4 is pierced four separate channels 400, 401, 402, 403, two of which 400, 401 each communicate with a pilot circulation channel 342p of the first ferrule itself opening on the outer peripheral baffle 361 and both of which other 402, 403 each communicate with a pilot circulation channel 342p of the shell 34 itself opening on the internal peripheral baffle 362.
  • completely separate pilot supply channels 400, 401, 402, 403 are obtained for feeding the baffle external device 361 and partially joined to supply the inner peripheral baffle 362 by means of drilling a hole shaped "bean". This provides a set of duct 41 and supply channels 400, 401, 402, 403 made with minimal space.
  • a second shell 35 in the form of a single piece ( figure 3A ) in which are integrally formed venturis 500 and 501. This avoids so-called “aero” steps which are obstacles at the junction between two parts located in the air flow.
  • a ferrule without venturi is, of course, within the scope of the invention.

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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)

Abstract

The injector has two shells (34, 35) with bodies encased relative to each other such that internal openings and external diameters of the bodies mutually and partially overlap by defining a hollow volume. The volume comprises three concentric baffles (360-362) that are continuous and communicated with distinct controlled circulation channels. The baffles (361, 362) are opened into a fuel intake chamber (37) placed in a zone for supply of fuel and homogenous cooling of the injector, where the zone is diametrically opposite to the channels and communicated with a metering jet. An independent claim is also included for a method for manufacturing a multipoint type fuel injector.

Description

L'invention concerne un injecteur multipoint destiné à être monté dans un système d'injection fixé à un carter de chambre de combustion d'une turbomachine, telle qu'un moteur d'aéronef.The invention relates to a multipoint injector intended to be mounted in an injection system fixed to a combustion chamber casing of a turbomachine, such as an aircraft engine.

Elle concerne plus particulièrement la structure d'un tel injecteur, et notamment la partie de structure dédiée à l'alimentation des circuits pilote et multipoint et au refroidissement de ce dernier.It relates more particularly to the structure of such an injector, and in particular the part of the structure dedicated to supplying the pilot and multipoint circuits and cooling the latter.

Les injecteurs de carburant appelés « multipoint » sont des injecteurs de nouvelle génération qui permettent l'adaptation aux différents régimes de la turbomachine. Chaque injecteur est pourvu de deux circuits de carburant : celui appelé « pilote » qui présente un débit permanent optimisé pour les bas régimes et celui appelé « multipoint » qui présente un débit intermittent optimisé pour les forts régimes. Le circuit multipoint est utilisé lorsqu'il y a nécessité d'avoir une poussée du moteur supplémentaire, en particulier dans les phases de croisière et décollage d'aéronef.Fuel injectors called "multipoint" are new generation injectors that allow adaptation to different speeds of the turbomachine. Each injector is equipped with two fuel circuits: the so-called "pilot" which has a steady flow optimized for low speeds and the one called "multipoint" which has an intermittent flow optimized for high speeds. The multipoint circuit is used when there is a need for additional engine thrust, especially in the cruising and take-off phases of aircraft.

Le fonctionnement par intermittence du circuit multipoint a pour inconvénient majeur d'induire, sous l'effet des températures élevées, une décomposition autrement appelée cokéfaction du carburant stagnant à l'intérieur du circuit multipoint lorsque le débit de ce dernier est fortement réduit voire coupé. Pour supprimer ce risque de cokéfaction, il est connu d'utiliser le carburant circulant dans le circuit pilote comme fluide de refroidissement du carburant stagnant dans le circuit multipoint.The intermittent operation of the multipoint circuit has the major disadvantage of inducing, under the effect of high temperatures, a decomposition otherwise known as coking of the stagnant fuel inside the multipoint circuit when the flow of the latter is greatly reduced. even cut. To eliminate the risk of coking, it is known to use the fuel flowing in the pilot circuit as a stagnant fuel cooling fluid in the multipoint circuit.

Malheureusement, à ce jour, la structure des injecteurs multipoints existants est telle que les deux circuits pilote et multipoint s'imbriquent l'un dans l'autre. Or, une telle imbrication ne permet pas d'obtenir une homogénéité satisfaisante du refroidissement.Unfortunately, to date, the structure of the existing multipoint injectors is such that the two pilot circuits and multipoint interlock one into the other. However, such imbrication does not make it possible to obtain a satisfactory homogeneity of the cooling.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

Le but de l'invention est alors de proposer une nouvelle structure d'injecteur multipoint permettant d'obtenir un refroidissement homogène du carburant stagnant à l'intérieur du circuit multipoint.The object of the invention is then to propose a new multipoint injector structure making it possible to obtain homogeneous cooling of the stagnant fuel inside the multipoint circuit.

A cet effet, l'invention concerne un injecteur de carburant de type multipoint, destiné à être monté dans un système d'injection de chambre de combustion, comprenant :

  • un bras d'alimentation en carburant,
  • une première virole comprenant une partie formant connexion dans laquelle est logée une extrémité du bras et une partie formant corps ouvert intérieurement, présentant un diamètre externe, et percé intérieurement de canaux de circulation de carburant communiquant avec le bras d'alimentation,
  • au moins un étage de vrilles emboité dans l'ouverture du corps de la première virole,
  • un gicleur de carburant, logé dans une partie formant moyeu de l'étage de vrilles, pour injecter du carburant provenant de l'intérieur des canaux de circulation pilote de la première virole vers l'axe du système d'injection,
  • une deuxième virole comprenant une partie formant corps ouvert intérieurement, présentant un diamètre externe et dont la périphérie est percée de canaux d'injection multipoint pour injecter du carburant vers la périphérie du système d'injection, injecteur dans lequel les corps des première et deuxième viroles sont emboités l'un dans l'autre de sorte que leurs ouvertures intérieures et diamètres externes se chevauchent mutuellement au moins partiellement en délimitant un volume creux comprenant au moins trois chicanes concentriques communiquant avec les canaux de circulation, dont celle centrale débouche sur les canaux d'injection multipoint et les autres périphériques sont adaptées pour faire circuler du carburant autour de la chicane centrale afin de refroidir le carburant alimentant les canaux d'injection multipoint puis d'alimenter le gicleur. Selon l'invention, les chicanes sont continues et communiquent chacune avec au moins un canal de circulation distinct, les chicanes périphériques débouchant dans une chambre d'admission du carburant disposée dans une zone diamétralement opposée aux canaux de circulation et qui communique avec le gicleur, afin d'obtenir une alimentation et un refroidissement homogènes de l'injecteur.
For this purpose, the invention relates to a multipoint type fuel injector, intended to be mounted in a combustion chamber injection system, comprising:
  • a fuel supply arm,
  • a first ferrule comprising a connection portion in which is housed an end of the arm and an internally open body portion having an outer diameter, and internally pierced with fuel flow channels communicating with the supply arm,
  • at least one stage of tendrils fitted into the opening of the body of the first ferrule,
  • a fuel nozzle, housed in a hub portion of the tendrel stage, for injecting fuel from inside the pilot circulation channels of the first ferrule towards the axis of the injection system,
  • a second ferrule comprising an internally open body portion having an outer diameter and the periphery of which is pierced with multipoint injection channels for injecting fuel towards the periphery of the injection system, an injector in which the bodies of the first and second ferrules are nested one inside the other so that their inner openings and external diameters mutually overlap each other at least partially by delimiting a hollow volume comprising at least three concentric baffles communicating with the circulation channels, the central one of which opens onto the d channels; The multipoint injection and other peripherals are adapted to circulate fuel around the central baffle to cool the fuel supplying the multipoint injection channels and then feed the nozzle. According to the invention, the baffles are continuous and each communicate with at least one separate circulation channel, the peripheral baffles opening into a fuel inlet chamber disposed in a zone diametrically opposite to the circulation channels and which communicates with the nozzle, to obtain a homogeneous supply and cooling of the injector.

Par « disposée dans une zone diamétralement opposée aux canaux de circulation », il faut comprendre que la chambre d'admission est disposée sur un secteur angulaire diamétralement opposé au secteur angulaire dans lequel débouchent les canaux de circulation dans les chicanes. Par exemple, lorsque l'injecteur comprend un seul canal de circulation multipoint qui s'étend en regard du bras d'alimentation, la chambre d'admission est disposée au moins en partie selon le diamètre de la virole passant par le canal de circulation multipoint.By "arranged in a zone diametrically opposed to the traffic channels", it is to be understood that the intake chamber is arranged on a sector angular diametrically opposed to the angular sector into which the flow channels in the baffles. For example, when the injector comprises a single multi-point traffic channel which extends opposite the supply arm, the intake chamber is arranged at least partly according to the diameter of the ferrule passing through the multi-point traffic channel. .

Ainsi, grâce à un agencement concentrique et continu des chicanes périphériques de refroidissement qui débouchent à l'opposé de l'arrivée du carburant pilote servant de liquide de refroidissement du carburant multipoint, on assure un refroidissement homogène tant par les longueurs de circulation du carburant pilote que par les surfaces d'échange entre les deux circuits pilote et multipoint.Thus, thanks to a concentric and continuous arrangement of the peripheral cooling baffles which open opposite the arrival of the pilot fuel serving as the coolant of the multipoint fuel, homogeneous cooling is ensured both by the lengths of circulation of the pilot fuel. than by the exchange surfaces between the two pilot and multipoint circuits.

En outre, avec une chicane centrale continue, la circulation du carburant multipoint est homogène.In addition, with a continuous central baffle, the multipoint fuel flow is homogeneous.

Selon un mode de réalisation avantageux, les première et deuxième viroles comprennent chacune une pièce monobloc usinée avec au moins une sous la forme d'une première couronne cylindrique creuse, les chicanes étant constituées par ladite première couronne cylindrique creuse et une seconde couronne cylindrique logée à l'intérieur et brasée à la première et dont la base est percée de canaux en regard des canaux multipoint, afin de maitriser le débit de refroidissement/alimentation dans les canaux d'injection pilote. Jusqu'à présent les chicanes étaient réalisées par usinage essentiellement par électroérosion directement et partiellement dans l'une des deux viroles monoblocs. Or, cet usinage direct dans une pièce monobloc ne permet pas de réaliser des gorges de faible hauteur, c'est-à-dire des chicanes de faible hauteur. Les sections des chicanes et donc des circuits usinées directement en monobloc ne peuvent donc être adaptées suivants les débits et vitesses souhaitées. Usiner deux couronnes cylindriques creuses de section différente puis en loger l'une dans l'autre et enfin les braser ensemble permet d'obtenir des sections de dimensions très précises. Ainsi, on peut adapter facilement celles-ci aux débits et/ou aux vitesses de carburant souhaitées. On peut en outre utiliser les techniques d'usinage classique sans avoir recours à l'usinage par électroérosion.According to an advantageous embodiment, the first and second ferrules each comprise a one-piece piece machined with at least one in the form of a first hollow cylindrical crown, the baffles being constituted by said first hollow cylindrical crown and a second cylindrical crown housed at the inside and soldered to the first and whose base is pierced with channels opposite the multipoint channels, in order to control the cooling / supply flow rate in the pilot injection channels. Until now the baffles were made by machining essentially electroerosion directly and partially in one two monobloc ferrules. However, this direct machining in a one-piece part does not allow for grooves of low height, that is to say, baffles of low height. The sections of the baffles and therefore directly machined circuits monobloc can not be adapted to the desired flow rates and speeds. Machine two cylindrical hollow crowns of different section and then lodge one in the other and finally braze together to obtain sections of very precise dimensions. Thus, they can be easily adapted to the desired flow rates and / or fuel speeds. It is also possible to use conventional machining techniques without using EDM machining.

En d'autres termes, séparer la couronne externe en deux parties distinctes permet de maîtriser la géométrie des chicanes et donc le débit de refroidissement/alimentation de l'injection pilote.In other words, separating the outer ring into two distinct parts makes it possible to control the geometry of the baffles and therefore the rate of cooling / feeding of the pilot injection.

Selon un mode de réalisation avantageux, la chambre d'admission est ménagée dans la première virole et communique avec le gicleur par l'intermédiaire d'un tuyau ne traversant pas les vrilles ou tout espace les séparant. Ainsi selon ce mode, on relie le circuit pilote au gicleur par l'extérieur de la tête d'injection. Cela permet de s'affranchir du perçage de canaux supplémentaires dans les vrilles tel qu'actuellement réalisé. Cela permet en outre d'obtenir de nouvelles configurations d'injecteur multipoint avec vrilles fines et/ou de type multi vrille, c'est-à-dire avec plusieurs étages de vrilles. En effet, dans ces configurations d'injecteur, le perçage des vrilles ou la traversée de plusieurs étages est impossible à réaliser.According to an advantageous embodiment, the inlet chamber is formed in the first ferrule and communicates with the nozzle through a pipe not passing through the tendrils or any space separating them. Thus according to this mode, the pilot circuit is connected to the nozzle by the outside of the injection head. This eliminates the drilling of additional channels in the tendrils as currently performed. This also makes it possible to obtain new configurations of multi-point injector with fine tendrils and / or of multi-twist type, that is to say with several stages of tendrils. Indeed, in these injector configurations, the drilling of the tendrils or the crossing of several floors is impossible to achieve.

De préférence, le tuyau est connecté d'une part à la partie de la chambre d'admission en regard de la partie débouchant des chicanes périphérique et d'autre part à la partie du moyeu de l'étage de vrilles en regard de et en communication avec le logement du gicleur.Preferably, the pipe is connected on the one hand to the portion of the inlet chamber facing the opening portion of the peripheral baffles and on the other hand to the part of the hub of the stage of tendrils facing and communication with the jet housing.

De préférence encore, le tuyau est un tube coudé en forme de U, dont l'une des branches connectée au moyeu de l'étage de vrilles s'étend selon l'axe du gicleur et l'autre des branches connectée parallèlement à la chambre d'admission s'étendant parallèlement à l'axe du gicleur. On obtient ainsi une connexion peu encombrante et qui ne gêne pas ou prou l'entrée d'air sur les vrilles. La mise en oeuvre d'un tube coudé et brasé est en outre facile à réaliser et peu coûteuse.More preferably, the pipe is a U-shaped bent tube, one of whose branches connected to the hub of the stage of tendrils extends along the axis of the nozzle and the other of the branches connected parallel to the chamber intake extending parallel to the axis of the nozzle. This provides a space-saving connection that does not interfere with the entry of air on the tendrils. The implementation of a bent and brazed tube is also easy to perform and inexpensive.

Afin d'alimenter individuellement les chicanes, l'injecteur peut comprendre en outre une pièce monobloc formant répartiteur de carburant, le répartiteur comprenant :

  • un corps brasé à l'intérieur de la connexion de la première virole et percé d'au moins deux canaux distincts communiquant chacun d'une part avec l'intérieur du bras connecté au circuit d'alimentation pilote et d'autre part avec au moins un canal de circulation pilote percé dans la première virole ;
  • un conduit qui s'étend à l'intérieur du bras et qui est connecté d'une part au circuit d'alimentation multipoint et d'autre part avec un canal de circulation multipoint percé dans la première virole.
In order to supply the baffles individually, the injector may further comprise a single piece forming a fuel distributor, the distributor comprising:
  • a body brazed inside the connection of the first ferrule and pierced with at least two separate channels each communicating on the one hand with the inside of the arm connected to the pilot supply circuit and on the other hand with at least a pilot circulation channel pierced in the first ferrule;
  • a conduit which extends inside the arm and which is connected on the one hand to the multipoint supply circuit and on the other hand with a channel multipoint circulation pierced in the first ferrule.

De préférence, le corps du répartiteur est percé de quatre canaux distincts dont deux communiquent chacun avec un canal de circulation pilote de la première virole lui-même débouchant sur la chicane périphérique externe et dont les deux autres communiquent chacun avec un canal de circulation pilote de la première virole lui-même débouchant sur la chicane périphérique interne.Preferably, the body of the distributor is pierced with four distinct channels, two of which each communicate with a pilot circulation channel of the first ferrule itself opening on the outer peripheral baffle and the other two each communicate with a pilot circulation channel of the first ferrule itself leading to the internal peripheral baffle.

Selon une variante de réalisation, les vrilles de chaque étage sont des vrilles agencées hélicoïdalement par rapport à l'axe de l'injecteur et d'épaisseur constante sur la largeur de l'étage.According to an alternative embodiment, the tendrils of each stage are tendrils arranged helically with respect to the axis of the injector and of constant thickness over the width of the stage.

Avec l'invention, il est en outre possible de réaliser n'importe quelle épaisseur de vrilles.With the invention, it is further possible to achieve any thickness of tendrils.

Selon une autre variante de réalisation, deux étages de vrilles emboités l'un dans l'autre avec celui périphérique lui-même emboîté dans l'ouverture intérieure de la seconde virole.According to another embodiment, two stages of tendrils nested one inside the other with the device itself encased in the inner opening of the second ferrule.

L'invention concerne également une chambre de combustion pour turbomachine comportant au moins un injecteur multipoint tel que décrit ci-dessus.The invention also relates to a combustion chamber for a turbomachine comprising at least one multipoint injector as described above.

L'invention concerne également une turbomachine comprenant une chambre de combustion à laquelle est fixé un injecteur tel que décrit ci-dessus, monté dans un système d'injection lui-même fixé à la chambre de combustion.The invention also relates to a turbomachine comprising a combustion chamber to which is fixed an injector as described above, mounted in an injection system itself attached to the combustion chamber.

L'invention concerne également un procédé de fabrication d'une virole destinée à être assemblée dans un injecteur de carburant multipoint, selon lequel on perce des canaux d'injection multipoint à la périphérie de la virole, caractérisé en ce qu'on réalise les étapes suivantes :

  • usinage d'une première pièce monobloc afin d'obtenir une grande couronne cylindrique creuse ;
  • usinage d'une deuxième pièce monobloc afin d'obtenir une petite couronne cylindrique de dimensions adaptées pour venir se loger à l'intérieur de la grande couronne cylindrique creuse ;
  • brasage étanche entre les deux bases des couronnes ;
  • perçage simultané des deux couronnes brasées entre elles afin d'obtenir des canaux d'injection multipoint.
The invention also relates to a method of manufacturing a shell intended to be assembled in a multipoint fuel injector, according to which multipoint injection channels are pierced at the periphery of the shell, characterized in that the following steps are carried out:
  • machining a first piece to obtain a large hollow cylindrical crown;
  • machining a second one-piece piece to obtain a small cylindrical ring of suitable dimensions to be housed inside the large cylindrical hollow crown;
  • sealed soldering between the two bases of the crowns;
  • simultaneous drilling of the two brazed crowns together to obtain multipoint injection channels.

Un tel procédé qui utilise le brasage de deux pièces monobloc entre elles et leur usinage préalable permet ainsi de réaliser des sections de circuit de refroidissement du carburant multipoint qui soient de dimensions facilement maitrisées.Such a method which uses the brazing of two pieces monobloc them and their prior machining thus allows for multipoint fuel cooling circuit sections that are easily controlled dimensions.

L'invention concerne enfin un procédé de fabrication d'un injecteur de carburant multipoint comprenant une première virole et une deuxième virole fabriquée telle que ci-dessus, caractérisé en qu'on réalise les étapes suivantes :

  • réalisation d'une pièce monobloc comprenant une grande couronne cylindrique pleine et une petite couronne cylindrique pleine en saillie axiale par rapport à la grande couronne ;
  • perçage de canaux de circulation pilote et multipoint dans les couronnes cylindriques pleines ;
  • usinage des diamètres des couronnes cylindriques pleines percées afin d'obtenir la première virole ;
  • emboitement de la première virole dans la deuxième virole de sorte à avoir chevauchement à la fois entre les grandes couronnes pleine et creuse et entre les petites couronnes pleine et creuse ;
  • brasage étanche des couronnes entre elles.
The invention finally relates to a method of manufacturing a multipoint fuel injector comprising a first ferrule and a second ferrule manufactured as above, characterized in that the following steps are carried out:
  • producing a one-piece piece comprising a large full cylindrical crown and a small full cylindrical crown projecting axially with respect to the large crown;
  • drilling of pilot and multipoint circulation channels in solid cylindrical crowns;
  • machining the diameters of the full cylindrical rings drilled to obtain the first ferrule;
  • interlocking the first ferrule in the second ferrule so as to overlap both between the large full and hollow crowns and between the small full and hollow crowns;
  • waterproof soldering of the crowns between them.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

D'autres avantages et caractéristiques ressortiront mieux à la lecture de la description détaillée donnée ci-dessous à titre indicatif et faite en référence aux figures suivantes :

  • la figure 1 est une vue générale en coupe longitudinale d'une partie de chambre de combustion d'une turbomachine, qui montre l'implantation d'un injecteur multipoint,
  • les figures 2A et 2B sont des vues arrières en coupe transversale montrant chacune une variante distincte de circulation de carburant à l'intérieur d'un injecteur multipoint selon l'état de l'art,
  • la figure 2C est une vue en perspective en coupe longitudinale d'une partie de l'injecteur selon l'état de l'art,
  • la figure 3 est une vue extérieure en perspective éclatée d'un mode de réalisation d'un injecteur multipoint selon l'invention,
  • la figure 3A est une vue en coupe longitudinale de l'injecteur selon la figure 3,
  • la figure 3B est une vue agrandie d'une partie de l'injecteur selon la figure 3A,
  • la figure 3C est une vue en perspective d'une partie de l'injecteur selon la figure 3A montrant par transparence l'alimentation du carburant en deux circuits pilote et multipoint distincts,
  • les figures 3D et 3E sont des vues en perspective d'une partie de l'injecteur selon la figure 3A montrant également les circuits pilote et multipoint distincts.
Other advantages and characteristics will emerge more clearly on reading the detailed description given below for information purposes and with reference to the following figures:
  • the figure 1 is a general view in longitudinal section of a combustion chamber part of a turbomachine, which shows the implantation of a multipoint injector,
  • the Figures 2A and 2B are rear cross-sectional views each showing a distinct variant of fuel circulation inside a multipoint injector according to the state of the art,
  • the Figure 2C is a perspective view in longitudinal section of a portion of the injector according to the state of the art,
  • the figure 3 is an external perspective exploded view of an embodiment of a multipoint injector according to the invention,
  • the figure 3A is a longitudinal sectional view of the injector according to the figure 3 ,
  • the figure 3B is an enlarged view of a portion of the injector according to the figure 3A ,
  • the figure 3C is a perspective view of a part of the injector according to the figure 3A showing by transparency the fuel supply in two separate pilot and multipoint circuits,
  • the 3D figures and 3E are perspective views of a portion of the injector according to the figure 3A also showing the separate pilot and multipoint circuits.

EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

Une partie de chambre de combustion 1 d'une turbomachine est représentée à la figure 1. La chambre de combustion 1 comprend usuellement une paroi externe 10, une paroi interne 11, des brides d'accrochage des parois interne 10 et externe 11 (non montrées) avec le carter de chambre C dans une zone de jonction 12, un fonds de chambre 13 boulonné ou soudé aux parois 10, 11, un déflecteur 14 pour protéger le fonds de chambre 13 du rayonnement des flammes issues de la combustion, divers carénages 15 monoblocs ou séparés et enfin d'une pluralité de systèmes d'injection 2 dans chacun desquels est monté un injecteur 3. Sur la figure 1 seul un système d'injection 2 avec un injecteur 3 est représenté : une chambre de combustion de révolution comprend usuellement un nombre important d'injecteurs 3, généralement de 10 à 50, nombre dépendant de la puissance de moteur à fournir. Chaque système d'injection 2 comprend un bol 20 divergent vers l'intérieur de la chambre pour faire éclater le jet de mélange d'air et de carburant sortant, une bague flottante 21 pour le glissement du bol 20 dans le fourreau d'ancrage 22, une ou plusieurs vrilles 23 permettant d'introduire de l'air avec un mouvement de giration, une collerette 24 refroidie à l'air pour protéger thermiquement le système d'accrochage.A combustion chamber portion 1 of a turbomachine is shown in FIG. figure 1 . The combustion chamber 1 usually comprises an outer wall 10, an inner wall 11, hooking flanges 10 and outer inner walls 11 (not shown) with the chamber casing C in a junction zone 12, a chamber fund 13 bolted or welded to the walls 10, 11, a deflector 14 to protect the chamber 13 of the radiation of the flames from combustion, various fairings monoblock or separate and finally a plurality of injection systems 2 in each of which is mounted an injector 3. On the figure 1 only an injection system 2 with an injector 3 is shown: a revolution combustion chamber usually comprises a large number of injectors 3, generally 10 to 50, depending on the number of engine power to be supplied. Each system injection 2 comprises a bowl 20 diverging towards the interior of the chamber for bursting the outgoing air and fuel mixture jet, a floating ring 21 for sliding the bowl 20 into the anchor sleeve 22, a or several tendrils 23 for introducing air with a gyration movement, an air-cooled collar 24 for thermally protecting the fastening system.

Chaque injecteur multipoint 3 comprend essentiellement un bras d'alimentation en carburant 30, un ou plusieurs étages de vrilles 31 permettant, tout comme les vrilles 23 du système d'injection, d'introduire de l'air avec un mouvement de giration, un gicleur de carburant 32 placé sur l'axe I-I' de l'injecteur 3 et un réseau 33 de n orifices d'injection 330 de carburant percés à la périphérie de l'injecteur 3 (figure 1). Chaque injecteur 3 est fixé au carter de chambre 10 et est monté dans un système d'injection 2 décrit ci-dessus. Plus exactement, le bras d'alimentation 30 est fixé au carter 10 de telle manière à ce que le réseau 33 d'orifices d'injection 330 soit monté dans la partie amont du corps de vrilles 23 (figure 1). Le montage est ainsi réalisé de sorte qu'il y ait un centrage (et donc une concentricité) précis entre l'injecteur 3 et son système d'injection associé 2. Le cas échéant, un injecteur multipoint 3 comprend un ou plusieurs trous de purge t permettant d'introduire de l'air axialement dans le système d'injection 2.Each multipoint injector 3 essentially comprises a fuel supply arm 30, one or more stages of vortex 31 allowing, like the tendrils 23 of the injection system, to introduce air with a gyration movement, a nozzle of fuel 32 placed on the axis II 'of the injector 3 and a network 33 of n fuel injection orifices 330 pierced at the periphery of the injector 3 ( figure 1 ). Each injector 3 is fixed to the chamber housing 10 and is mounted in an injection system 2 described above. More exactly, the supply arm 30 is fixed to the housing 10 in such a way that the network 33 of injection orifices 330 is mounted in the upstream part of the body of tendrils 23 ( figure 1 ). The assembly is thus performed so that there is a centering (and therefore a concentricity) accurate between the injector 3 and its associated injection system 2. Where appropriate, a multipoint injector 3 comprises one or more bleed holes t for introducing air axially into the injection system 2.

Un injecteur multipoint 3 est donc conçu pour avoir d'une part un gicleur de carburant 32 disposé selon son axe qui injecte du carburant à un débit permanent, généralement optimisé pour les bas régimes du moteur, et d'autre part des orifices multipoint 330 percés à la périphérie de l'injecteur et qui injectent du carburant à un débit intermittent pour les forts régimes du moteur, par exemple ceux exigés lors d'un décollage d'un aéronef équipé du moteur. Dans les conceptions actuelles, comme expliqué ci-après, le circuit de carburant prévu pour alimenter le gicleur 32 et dénommé « circuit pilote » sert également à refroidir le circuit de carburant prévu pour alimenter les orifices multipoint 330 et dénommé « circuit multipoint ». En effet, puisque que ce circuit multipoint est destiné à fournir du carburant par intermittence, du carburant stagne à l'intérieur de celui-ci et un risque de cokéfaction ou gommage de ce carburant stagnant subsiste. Refroidir en permanence le circuit multipoint par le circuit pilote a donc pour objectif d'éviter tout risque de cokéfaction de carburant.A multipoint injector 3 is designed to have on the one hand a fuel nozzle 32 disposed along its axis which injects fuel at a steady flow, generally optimized for low speeds of the engine, and on the other hand multipoint ports 330 pierced at the periphery of the injector and injecting fuel at an intermittent flow for the high engine speeds, for example those required during takeoff of an aircraft equipped with the engine. In the current designs, as explained below, the fuel circuit provided to supply the nozzle 32 and called "pilot circuit" is also used to cool the fuel circuit provided to feed the multipoint ports 330 and called "multipoint circuit". Indeed, since this multipoint circuit is intended to supply fuel intermittently, fuel stagnates inside it and a risk of coking or scrubbing of this stagnant fuel remains. Constantly cooling the multipoint circuit by the pilot circuit therefore aims to avoid any risk of coking fuel.

Tel qu'actuellement réalisé (figures 2A à 2C), un injecteur multipoint 3 comprend tout d'abord un bras d'alimentation en carburant 30. Il comprend également une première virole 34 comprenant une partie formant connexion 340 pour loger une extrémité du bras 30 et une partie formant corps 341 ouvert intérieurement O1, présentant un diamètre externe D1, et percé intérieurement de canaux de circulation 342 de carburant communiquant avec le bras d'alimentation 30. Au moins un étage de vrilles 31 est emboité dans l'ouverture du corps de la première virole. Un gicleur de carburant 32 est logé dans une partie formant moyeu 310 de l'étage de vrilles 31, pour injecter du carburant provenant de l'intérieur des canaux de circulation 342 de la première virole vers l'axe I du système d'injection. L'injecteur 3 comprend enfin une deuxième virole 35 qui comprend une partie formant corps 350 ouvert intérieurement 02, présentant un diamètre externe D2 et dont la périphérie est percée de canaux multipoint 351 pour injecter du carburant vers la périphérie du système d'injection. Les orifices de sorties 330 des canaux multipoint 351 constituent le réseau 33 multipoint de l'injecteur.As currently realized ( FIGS. 2A to 2C ), a multipoint injector 3 firstly comprises a fuel supply arm 30. It also comprises a first ferrule 34 comprising a connection portion 340 for housing an end of the arm 30 and a body portion 341 internally open O1, having an outer diameter D1, and pierced internally with fuel circulation channels 342 communicating with the supply arm 30. At least one stage of tendrils 31 is engaged in the opening of the body of the first ferrule. A jet fuel 32 is housed in a hub portion 310 of the vane stage 31, for injecting fuel from the interior of the circulation channels 342 of the first ferrule towards the axis I of the injection system. The injector 3 finally comprises a second shell 35 which comprises a body portion 350 open internally 02, having an outer diameter D2 and whose periphery is pierced with multipoint channels 351 for injecting fuel to the periphery of the injection system. The output ports 330 of the multipoint channels 351 constitute the multipoint network 33 of the injector.

Tel qu'actuellement réalisé, les corps 341, 350 des première 34 et deuxième 35 viroles sont emboités l'un dans l'autre de sorte que leurs ouvertures intérieures O1, 02 et diamètres externes D1, D2 se chevauchent mutuellement au moins partiellement. Leur chevauchement délimite un volume creux comprenant au moins trois chicanes 36 concentriques, dont celle centrale 360 débouche sur les canaux multipoint 351 et les autres périphériques 361, 362 sont adaptées pour faire circuler du carburant autour de la chicane centrale 360 afin de refroidir le carburant alimentant les canaux multipoints 351 puis afin d'alimenter le gicleur 32 (figure 2C). En d'autres termes, dans cette conception actuelle, les chicanes 361, 362 du circuit pilote de carburant sont disposés de manière concentrique à celle centrale 360 du circuit multipoint afin de refroidir au mieux celui-ci, et donc d'éviter tout risque de cokéfaction.As currently performed, the bodies 341, 350 of the first 34 and second ferrules are nested one inside the other so that their inner openings O1, 02 and outer diameters D1, D2 overlap each other at least partially. Their overlap delimits a hollow volume comprising at least three concentric baffles 36, of which the central 360 opens on the multipoint channels 351 and the other peripherals 361, 362 are adapted to circulate fuel around the central baffle 360 to cool the fuel supplying fuel. the multipoint channels 351 and then to supply the nozzle 32 ( Figure 2C ). In other words, in this current design, the baffles 361, 362 of the fuel pilot circuit are arranged concentrically with the central one 360 of the multipoint circuit in order to cool it as well as possible, and thus to avoid any risk of coking.

Cependant, dans la conception actuelle (figures 2A et 2B), la chicane centrale 360 est discontinue, les chicanes périphériques 361, 362 communiquent entre elles par la discontinuité 3600 réalisée dans la chicane centrale 360, et la chicane périphérique interne 362 ne communique pas avec des canaux de circulation 342 percé dans le corps de la première virole 34. En effet, seule la chicane périphérique externe 361 communique avec un canal de circulation 342 (figure 2A) ou deux canaux de circulation 342 (figure 2B). Ainsi, le carburant pilote circule à l'intérieur de la chicane périphérique interne 362 en arrivant depuis le(s) canal(ux) de circulation 342 tout d'abord à l'intérieur de la chicane périphérique externe 361 puis en traversant la discontinuité 3600. Les flèches, représentées en figures 2A et 2B, à l'intérieur de deux cavités périphériques 361, 362 indiquent ainsi le parcours du carburant pilote avant sa circulation dans le canal d'admission 310 percé à l'intérieur de l'étage de vrilles 31. Le carburant pilote circulant dans le canal d'admission 310 arrive dans le gicleur 32 (figure 2C).However, in the current design ( Figures 2A and 2B ), the central baffle 360 is discontinuous, the peripheral baffles 361, 362 communicate with each other by the discontinuity 3600 made in the central baffle 360, and the internal peripheral baffle 362 does not communicate with the circulation channels 342 pierced in the body of the first ferrule 34. Indeed, only the outer peripheral baffle 361 communicates with a circulation channel 342 ( Figure 2A ) or two circulation channels 342 ( Figure 2B ). Thus, the pilot fuel circulates within the inner peripheral baffle 362 from the circulation channel (s) 342 firstly into the outer peripheral baffle 361 and then through the discontinuity 3600. The arrows, represented in Figures 2A and 2B , inside two peripheral cavities 361, 362 thus indicate the route of the pilot fuel before its circulation in the intake channel 310 drilled inside the stage of tendrils 31. The pilot fuel circulating in the duct admission 310 arrives in the nozzle 32 ( Figure 2C ).

Ainsi, la structure actuelle d'un injecteur multipoint 3 ne permet pas d'obtenir une homogénéité parfaite dans le refroidissement du carburant multipoint circulant dans la chicane centrale 360. En effet, le carburant pilote circule soit en suivant un parcours en spirale (figure 2A), soit en suivant deux parcours semi-circulaires concentrique (figure 2B). Cette circulation crée donc des zones de refroidissement inhomogènes tant par les surfaces d'échange entre le carburant pilote et celui multipoint que par leur circulation. Ces zones de refroidissement inhomogènes, symboliquement représentées par des ellipses en pointillés sur les figures 2A et 2B, ne suppriment pas totalement le risque d'avoir une cokéfaction du carburant stagnant dans la chicane centrale 360 du circuit multipoint.Thus, the current structure of a multipoint injector 3 does not provide perfect homogeneity in the cooling of the multipoint fuel flowing in the central baffle 360. Indeed, the pilot fuel flows either following a spiral path ( Figure 2A ), or following two concentric semicircular paths ( Figure 2B ). This circulation therefore creates inhomogeneous cooling zones both by the surfaces exchange between the pilot and the multipoint fuel only by their circulation. These inhomogeneous cooling zones, symbolically represented by dotted ellipses on the Figures 2A and 2B , do not completely eliminate the risk of coking the stagnant fuel in the central baffle 360 of the multipoint circuit.

Selon l'invention, un refroidissement complètement homogène du circuit de carburant multipoint par le circuit de carburant est obtenu. Pour ce faire, d'une part les trois chicanes concentriques 360, 361, 362 sont continues sur toute leur circonférence (figures 3 et 3A) et elles communiquent chacune avec au moins un canal de circulation distinct 342 (figure 3C, figures 3D et 3E). D'autre part, les chicanes périphériques 361, 362 débouchent dans une chambre d'admission du carburant 37 diamétralement opposée aux canaux de circulation 342 et qui communique avec le gicleur 32 (figure 3B).According to the invention, a completely homogeneous cooling of the multipoint fuel circuit by the fuel circuit is obtained. To do this, on the one hand the three concentric baffles 360, 361, 362 are continuous over their entire circumference ( figures 3 and 3A ) and they each communicate with at least one separate circulation channel 342 ( figure 3C , 3D figures and 3E ). On the other hand, the peripheral baffles 361, 362 open into a fuel intake chamber 37 diametrically opposed to the circulation channels 342 and which communicates with the nozzle 32 (FIG. figure 3B ).

Ainsi, les chicanes 360, 361, 362 à la fois du circuit de carburant pilote et du circuit de carburant multipoint sont des anneaux complets concentriques d'où le refroidissement homogène. En d'autres termes, les chicanes 360, 361, 362 ne communiquent pas entre elles, ce qui simplifie leur géométrie. On peut ainsi les réaliser par usinage classique.Thus, the baffles 360, 361, 362 of both the pilot fuel circuit and the multipoint fuel system are concentric complete rings from which homogeneous cooling. In other words, the baffles 360, 361, 362 do not communicate with each other, which simplifies their geometry. They can thus be produced by conventional machining.

Tel qu'illustré aux figures 3 et 3A, les première 34 et deuxième 35 viroles sont constituées chacune par une pièce monobloc usinée avec la deuxième 35 sous la forme d'une première couronne cylindrique creuse 350 : les chicanes 360, 361, 362, sont ainsi constituées par la couronne cylindrique creuse 350 et une autre couronne cylindrique creuse 380 logée à l'intérieur de la couronne 350 en y étant brasée. La base 380a de cette autre couronne cylindrique creuse 380 est percée de canaux 3800 en regard des canaux multipoint 351.As illustrated in figures 3 and 3A the first 34 and second 35 rings are each constituted by a one-piece piece machined with the second 35 in the form of a first cylindrical ring hollow 350: the baffles 360, 361, 362 are thus constituted by the hollow cylindrical crown 350 and another hollow cylindrical crown 380 housed inside the ring 350 by being brazed therein. The base 380a of this other hollow cylindrical crown 380 is pierced with channels 3800 facing the multipoint channels 351.

Selon un procédé de fabrication préféré, la virole 35 est une pièce monobloc usinée pour former la couronne cylindrique creuse 350, l'autre couronne 380 étant également une pièce monobloc 38 de dimensions adaptées pour venir se loger à l'intérieur de la grande couronne cylindrique creuse et usinée. Les deux bases 380a, 350 sont brasées de manière étanche entre elles puis percées simultanément afin d'obtenir les canaux d'injection multipoint 351, 3800. Pour obtenir la première virole 34, on réalise une pièce monobloc comprenant une grande couronne cylindrique pleine 343 et une petite couronne cylindrique pleine 344 en saillie axiale par rapport à la grande couronne 343, on perce les canaux de circulation pilote 342p et multipoint 342m dans les couronnes cylindriques pleines 343, 344 puis on usine les diamètres des couronnes cylindriques pleines 343, 344 percées. On réalise alors l'emboitement de la première virole 34 dans la deuxième virole 35 de sorte à avoir chevauchement à la fois entre les grandes couronnes pleine et creuse 343, 350 et entre les petites couronnes pleine et creuse 344, 380 puis on effectue un brasage étanche des couronnes 343, 350, 344, 380 entre elles.According to a preferred manufacturing method, the ferrule 35 is a one-piece piece machined to form the hollow cylindrical ring 350, the other ring 380 is also a single piece 38 of suitable dimensions to be housed inside the large cylindrical ring hollow and machined. The two bases 380a, 350 are soldered tightly together and then drilled simultaneously to obtain the multipoint injection channels 351, 3800. To obtain the first ferrule 34, a one-piece piece is produced comprising a large full cylindrical crown 343 and a small full cylindrical ring 344 projecting axially with respect to the large ring 343, the pilot circulation channels 342p and multipoint 342m are drilled in the solid cylindrical rings 343, 344 and then machined the diameters of the solid cylindrical rings 343, 344 drilled. The first ferrule 34 is then engaged in the second ferrule 35 so as to overlap both between the large full and hollow crowns 343, 350 and between the small solid and hollow crowns 344, 380 and then brazing is carried out. sealing rings 343, 350, 344, 380 between them.

Selon la variante de réalisation des figures 3A et 3B, la chambre d'admission 37 est ménagée dans la première virole 34 et communique avec le gicleur 32 par l'intermédiaire d'un tuyau 39 qui ne traverse pas les étage de vrilles 31 ou tout espace séparant les vrilles entre elles. On lie ainsi le circuit de carburant pilote périphérique à l'axe I-I' de l'injecteur 3 par l'extérieur de la tête d'injection. Une telle liaison est avantageuse car elle peut être obtenue quelle que soit la configuration des vrilles 311, 311a (inclinaison, longueur, épaisseur, nombre d'étages de vrilles...). Le tuyau 39 est de préférence connecté d'une part à la partie de la chambre d'admission 37 en regard de la partie débouchant des chicanes périphériques 361, 362 (figure 3B) et d'autre part à la partie du moyeu de l'étage 31 de vrilles en regard de et en communication avec le logement du gicleur 32 (figure 3A). Tel qu'illustré aux figures 3 et 3A, le tuyau 39 est un tube coudé en forme de U, dont l'une des branches 390 connectée au moyeu 310 de l'étage 31 de vrilles s'étend selon l'axe I-I' du gicleur 32 et l'autre des branches 391 connectée parallèlement à la chambre d'admission 37 s'étendant parallèlement à l'axe I-I' du gicleur 32.According to the variant embodiment of Figures 3A and 3B , the inlet chamber 37 is formed in the first ferrule 34 and communicates with the nozzle 32 via a pipe 39 which does not pass through the stages of tendrils 31 or any space between the tendrils. Thus the peripheral pilot fuel circuit is connected to the axis II 'of the injector 3 by the outside of the injection head. Such a connection is advantageous because it can be obtained whatever the configuration of the tendrils 311, 311a (inclination, length, thickness, number of stages of tendrils ...). The pipe 39 is preferably connected on the one hand to the portion of the inlet chamber 37 facing the opening portion of the peripheral baffles 361, 362 ( figure 3B ) and on the other hand to the part of the hub of the stage 31 of tendrils opposite and in communication with the housing of the nozzle 32 ( figure 3A ). As illustrated in figures 3 and 3A , the pipe 39 is a U-shaped bent tube, one of the branches 390 connected to the hub 310 of the stage 31 of tendrils extends along the axis II 'of the nozzle 32 and the other of the branches 391 connected parallel to the inlet chamber 37 extending parallel to the axis II 'of the nozzle 32.

Les vrilles de chaque étage 31, 31a peuvent être ainsi des vrilles 31 agencées hélicoïdalement par rapport à l'axe I-I' de l'injecteur et d'épaisseur constante sur la largeur de l'étage et avantageusement réduite au minimum. L'injecteur 3 peut comprendre deux étages 31, 31a de vrilles emboîtés l'un dans l'autre avec celui périphérique lui-même emboîté dans l'ouverture intérieure de la virole 35 (figure 3).The swirlers of each stage 31, 31a can thus be spirals 31 arranged helically with respect to the axis II 'of the injector and of constant thickness over the width of the stage and advantageously reduced to a minimum. The injector 3 may comprise two stages 31, 31a of tendrils nested one inside the other with the peripheral device itself encased in the inner opening of the ferrule 35 ( figure 3 ).

Afin d'obtenir des canaux de circulation 342 distincts, une alimentation individualisée en amont dans l'alimentation du carburant doit être réalisée. Il est ainsi prévu une pièce monobloc 4 formant répartiteur de carburant dont le corps 40 est brasé à l'intérieur de la connexion 340 de la virole 34 et percé d'au moins deux canaux distincts 400, 401, 402, 403 communiquant chacun d'une part avec l'intérieur du bras 30 connecté au circuit d'alimentation pilote et d'autre part avec au moins un canal de circulation pilote 342p percé dans la virole 34. Le répartiteur 4 comprend également un conduit 41 qui s'étend à l'intérieur du bras 30 et qui est connecté d'une part au circuit d'alimentation multipoint et d'autre part avec un canal de circulation multipoint 342m percé dans première virole 34.In order to obtain separate circulation channels 342, an individual supply upstream in the fuel supply must be realized. There is thus provided a one-piece piece 4 forming a fuel distributor whose body 40 is brazed inside the connection 340 of the shell 34 and pierced with at least two separate channels 400, 401, 402, 403 each communicating with each other. a part with the inside of the arm 30 connected to the pilot supply circuit and secondly with at least one pilot circulation channel 342p pierced in the shell 34. The distributor 4 also comprises a duct 41 which extends to the the interior of the arm 30 and which is connected on the one hand to the multipoint supply circuit and on the other hand with a multipoint circulation channel 342m pierced in the first ferrule 34.

Selon la variante avantageuse de construction des figures 3C, 3D et 3E le corps 40 du répartiteur 4 est percé quatre canaux distincts 400, 401, 402, 403 dont deux 400, 401 communiquent chacun avec un canal de circulation pilote 342p de la première virole lui-même débouchant sur la chicane périphérique externe 361 et dont les deux autres 402, 403 communiquent chacun avec un canal de circulation pilote 342p de la virole 34 lui-même débouchant sur la chicane périphérique interne 362. Dans la construction des figures 3C, 3D et 3E on obtient des canaux d'alimentation pilote 400, 401, 402, 403 complètement distincts pour l'alimentation de la chicane périphérique externe 361 et en partie réunis pour l'alimentation de la chicane périphérique interne 362 au moyen du perçage d'un trou en forme de « haricot ». On obtient ainsi un ensemble du conduit 41 et canaux d'alimentation 400, 401, 402, 403 réalisés avec un encombrement minimal.According to the advantageous variant of construction of Figures 3C , 3D and 3E the body 40 of the distributor 4 is pierced four separate channels 400, 401, 402, 403, two of which 400, 401 each communicate with a pilot circulation channel 342p of the first ferrule itself opening on the outer peripheral baffle 361 and both of which other 402, 403 each communicate with a pilot circulation channel 342p of the shell 34 itself opening on the internal peripheral baffle 362. In the construction of Figures 3C , 3D and 3E completely separate pilot supply channels 400, 401, 402, 403 are obtained for feeding the baffle external device 361 and partially joined to supply the inner peripheral baffle 362 by means of drilling a hole shaped "bean". This provides a set of duct 41 and supply channels 400, 401, 402, 403 made with minimal space.

Il va de soi que d'autres modifications pourront être réalisées sans pour autant sortir du cadre de l'invention, à savoir proposer des chicanes de refroidissement continues qui ne communiquent pas entre elles et qui sont disposées concentriquement à la chicane centrale multipoint également continue.It goes without saying that other modifications can be made without departing from the scope of the invention, namely to provide continuous cooling baffles which do not communicate with each other and which are arranged concentrically at the central bending multipoint also continuous.

Ainsi, on a représenté une deuxième virole 35 sous la forme d'une pièce monobloc (figure 3A) dans laquelle sont formés intégralement des venturis 500 et 501. Cela permet d'éviter les marches dites « aéro » qui sont des obstacles au niveau de la jonction entre deux pièces se situant dans le flux d'air.Thus, there is shown a second shell 35 in the form of a single piece ( figure 3A ) in which are integrally formed venturis 500 and 501. This avoids so-called "aero" steps which are obstacles at the junction between two parts located in the air flow.

Une virole sans venturi rentre bien entendu dans le cadre de l'invention.A ferrule without venturi is, of course, within the scope of the invention.

Claims (13)

Injecteur (3) de carburant de type multipoint, destiné à être monté dans un système d'injection (2) de chambre de combustion (1), comprenant : - un bras (30) d'alimentation en carburant, - une première virole (34) comprenant une partie formant connexion (340) dans laquelle est logée une extrémité du bras (30) et une partie formant corps (341) ouvert intérieurement (O1), présentant un diamètre externe (D1), et percé intérieurement de canaux de circulation de carburant (342p, 342m) communiquant avec le bras d'alimentation (30), - au moins un étage de vrilles (31, 31a) emboité dans l'ouverture du corps de la première virole, - un gicleur de carburant (32) logé dans une partie formant moyeu (310) de l'étage de vrilles (31), pour injecter du carburant provenant de l'intérieur des canaux de circulation pilote (342p) de la première virole (34) vers l'axe I-I' du système d'injection (2), - une deuxième virole (35) comprenant une partie formant corps (350) ouvert intérieurement (02), présentant un diamètre externe (D2) et dont la périphérie est percée de canaux d'injection multipoint (351) pour injecter du carburant vers la périphérie du système d'injection, injecteur (3) dans lequel les corps (341, 350) des première (34) et deuxième (35) viroles sont emboîtés l'un dans l'autre de sorte que leurs ouvertures intérieures (O1, 02) et diamètres externes (D1, D2) se chevauchent mutuellement au moins partiellement en délimitant un volume creux comprenant au moins trois chicanes concentriques (360, 361, 362) communiquant avec les canaux de circulation (342p, 342m), dont celle centrale (360) débouche sur les canaux d'injection multipoint (351) et les autres périphériques (361, 362) sont adaptées pour faire circuler du carburant autour de la chicane centrale (360) afin de refroidir le carburant alimentant les canaux d'injection multipoint (351) puis d'alimenter le gicleur (32), caractérisé en ce que les chicanes (360, 361, 362) sont continues et communiquent chacune avec au moins un canal de circulation distinct (342p, 342m), les chicanes périphériques (361, 362) débouchant dans une chambre d'admission (37) du carburant disposée dans une zone diamétralement opposée aux canaux de circulation (342p, 342m) et qui communique avec le gicleur (32), afin d'obtenir une alimentation et un refroidissement homogènes de l'injecteur.Multi-point fuel injector (3) for mounting in a combustion chamber injection system (2), comprising: an arm (30) for supplying fuel, a first ferrule (34) comprising a connection part (340) in which is housed an end of the arm (30) and a body portion (341) open internally (O1), having an external diameter (D1), and pierced; internally of fuel circulation channels (342p, 342m) communicating with the supply arm (30), at least one stage of tendrils (31, 31a) fitted into the opening of the body of the first ferrule, a fuel nozzle (32) housed in a hub portion (310) of the auger stage (31) for injecting fuel from within the pilot circulation channels (342p) of the first ferrule (34); ) to the axis II 'of the injection system (2), a second ferrule (35) comprising a body portion (350) open internally (02), having an external diameter (D2) and whose periphery is pierced with multipoint injection channels (351) for injecting fuel towards the periphery; of the injection system, injector (3) in which the bodies (341, 350) of the first (34) and second (35) ferrules are nested one inside the other so that their inner openings (O1, 02) and outer diameters (D1, D2) overlap each other at least partially by delimiting a hollow volume comprising at least three concentric baffles (360, 361, 362) communicating with the circulation channels (342p, 342m ), of which the central one (360) opens on the multipoint injection channels (351) and the other peripherals (361, 362) are adapted to circulate fuel around the central baffle (360) to cool the fuel supplying the fuel. multipoint injection channels (351) and then supplying the nozzle (32), characterized in that the baffles (360, 361, 362) are continuous and each communicate with at least one separate circulation channel (342p, 342m), the peripheral baffles (361, 362) opening into an inlet chamber (37) fuel disposed in a region diametrically opposed to the circulation channels (342p, 342m) and which communicates with the nozzle (32), to obtain a homogeneous supply and cooling of the injector. Injecteur (3) selon la revendication 1, dans lequel les première (34) et deuxième (35) viroles comprennent chacune une pièce monobloc usinée, dont l'une (35) est sous la forme d'une première couronne cylindrique creuse (350), les chicanes (360, 361, 362) étant constituées par ladite première couronne cylindrique creuse (350) et une seconde couronne cylindrique (38, 380) logée à l'intérieur et brasée à la première (350) et dont la base (380a) est percée de canaux (3800) en regard des canaux d'injection multipoint (351), afin de maitriser le débit de refroidissement/alimentation dans les canaux d'injection pilote.Injector (3) according to claim 1, wherein the first (34) and second (35) ferrules each comprise a machined monobloc piece, one (35) of which is in the form of a first hollow cylindrical crown (350) , the baffles (360, 361, 362) being constituted by said first hollow cylindrical ring (350) and a second cylindrical ring (38, 380) housed inside and brazed to the first (350) and whose base (380a ) is pierced channels (3800) next to the multipoint injection channels (351), in order to control the cooling / supply flow rate in the pilot injection channels. Injecteur (3) selon la revendication 1 ou 2, dans lequel la chambre d'admission (37) est ménagée dans la première virole (34) et communique avec le gicleur (32) par l'intermédiaire d'un tuyau (39) ne traversant pas les vrilles (311) ou tout espace les séparant.Injector (3) according to claim 1 or 2, wherein the inlet chamber (37) is formed in the first ferrule (34) and communicates with the nozzle (32) via a pipe (39) not crossing the tendrils (311) or any space separating them. Injecteur (3) selon la revendication 3, dans lequel le tuyau (39) est connecté d'une part à la partie (370) de la chambre d'admission (37) en regard de la partie débouchant des chicanes périphériques (361, 362) et d'autre part à la partie du moyeu (310) de l'étage (31) de vrilles (311) en regard de et en communication avec le gicleur (32).Injector (3) according to claim 3, wherein the pipe (39) is connected on the one hand to the portion (370) of the inlet chamber (37) facing the opening portion of the peripheral baffles (361, 362 ) and on the other hand to the portion of the hub (310) of the stage (31) of tendrils (311) opposite and in communication with the nozzle (32). Injecteur (3) selon la revendication 4, dans lequel le tuyau (39) est un tube coudé en forme de U, dont l'une des branches (390) connectée au moyeu (310) de l'étage (31) de vrilles (311) s'étend selon l'axe I-I' du gicleur et dont l'autre des branches (391) connectée parallèlement à la chambre d'admission s'étend parallèlement à l'axe I-I' du gicleur (32).Injector (3) according to claim 4, in which the pipe (39) is a U-shaped bent tube, one of whose branches (390) is connected to the hub (310) of the stage (31) of tendrils ( 311) extends along the axis II 'of the nozzle and the other of the branches (391) connected parallel to the inlet chamber extends parallel to the axis II' of the nozzle (32). Injecteur (3) selon l'une quelconque des revendications précédentes, comprenant en outre une pièce monobloc formant répartiteur de carburant (4), le répartiteur (4) comprenant : - un corps (40) brasé à l'intérieur de la connexion (340) de la première virole (34) et percé d'au moins deux canaux distincts (400, 401, 402, 403) communiquant chacun d'une part avec l'intérieur du bras (30) connecté au circuit d'alimentation pilote et d'autre part avec au moins un canal de circulation pilote (342p) percé dans la première virole (34), - un conduit (41) qui s'étend à l'intérieur du bras (30) et qui est connecté d'une part au circuit d'alimentation multipoint et d'autre part avec un canal de circulation multipoint (342m) percé dans la première virole (34). Injector (3) according to any one of the preceding claims, further comprising a monobloc component forming a fuel distributor (4), the distributor (4) comprising: a body (40) brazed inside the connection (340) of the first ferrule (34) and pierced with at least two distinct channels (400, 401, 402, 403) each communicating on the one hand with the inside the arm (30) connected to the pilot supply circuit and secondly with at least one pilot circulation channel (342p) pierced in the first ferrule (34), a duct (41) which extends inside the arm (30) and which is connected on the one hand to the multipoint supply circuit and on the other hand with a multipoint circulation channel (342m) pierced in the first ferrule (34). Injecteur (3) selon la revendication 6, dans lequel le corps (40) du répartiteur (4) est percé de quatre canaux distincts (400, 401, 402, 403) dont deux (400, 401) communiquent chacun avec un canal de circulation pilote (342p) de la première virole (34) lui-même débouchant sur la chicane périphérique externe (361) et dont les deux autres (402, 403) communiquent chacun avec un canal de circulation pilote (342p) de la première virole lui-même débouchant sur la chicane périphérique interne (362).Injector (3) according to claim 6, wherein the body (40) of the distributor (4) is pierced with four separate channels (400, 401, 402, 403), two (400, 401) each communicate with a circulation channel pilot (342p) of the first shell (34) itself leading to the external peripheral baffle (361) and whose two others (402, 403) each communicate with a pilot circulation channel (342p) of the first shell itself even leading to the inner peripheral baffle (362). Injecteur (3) selon l'une quelconque des revendications précédentes, dans lequel les vrilles (311, 311a) de chaque étage (31, 31a) sont des vrilles agencées hélicoïdalement par rapport à l'axe I-I' de l'injecteur et d'épaisseur constante sur la largeur de l'étage.Injector (3) according to any one of the preceding claims, wherein the tendrils (311, 311a) of each stage (31, 31a) are tendrils arranged helically with respect to the axis II 'of the injector and constant thickness over the width of the floor. Injecteur (3) selon l'une des revendications précédentes, comprenant deux étages (31 et 31a) de vrilles (311 et 311a) emboités l'un dans l'autre avec celui périphérique (31a) lui-même emboîté dans l'ouverture intérieure (02) de la seconde virole (35) .Injector (3) according to one of the preceding claims, comprising two stages (31 and 31a) of tendrils (311 and 311a) nested one inside the other with the peripheral one (31a) itself fitted into the inner opening (02) of the second ferrule (35). Chambre de combustion pour turbomachine comportant au moins un injecteur multipoint selon l'une quelconque des revendications précédentes.Combustion chamber for a turbomachine comprising at least one multipoint injector according to any one of the preceding claims. Turbomachine comprenant une chambre de combustion (1) à laquelle est fixée un injecteur (3) selon l'une quelconque des précédentes monté dans un système d'injection (2) lui-même fixé à la chambre de combustion.Turbomachine comprising a combustion chamber (1) to which is fixed an injector (3) according to any one of the preceding mounted in an injection system (2) itself attached to the combustion chamber. Procédé de fabrication d'une virole (35) destinée à être assemblée dans un injecteur (3) de carburant multipoint, selon lequel on perce des canaux d'injection multipoint (351) à la périphérie de la virole, caractérisé en ce qu'on réalise les étapes suivantes : - usinage d'une première pièce monobloc (35) afin d'obtenir une grande couronne cylindrique creuse (350), - usinage d'une deuxième pièce monobloc (38) afin d'obtenir une petite couronne cylindrique (380) de dimensions adaptées pour venir se loger à l'intérieur de la grande couronne cylindrique creuse (350), - brasage étanche entre les deux bases (350a, 380a) des couronnes, - perçage simultané des deux couronnes (35, 38) brasées entre elles afin d'obtenir des canaux d'injection multipoint (351, 3800). A method of manufacturing a ferrule (35) to be assembled in a multipoint fuel injector (3), wherein multipoint injection channels (351) are pierced at the periphery of the ferrule, characterized in that perform the following steps: machining a first one-piece piece (35) in order to obtain a large hollow cylindrical crown (350), machining a second one-piece piece (38) in order to obtain a small cylindrical crown (380) of suitable dimensions to be housed in the inside of the large cylindrical hollow crown (350), soldering between the two bases (350a, 380a) of the crowns, - Simultaneous drilling of the two rings (35, 38) brazed together to obtain multipoint injection channels (351, 3800). Procédé de fabrication d'un injecteur (3) de carburant multipoint comprenant une première virole (34) et une deuxième virole (35) fabriquée selon la revendication 12, caractérisé en qu'on réalise les étapes suivantes : - réalisation d'une pièce monobloc (34) comprenant une grande couronne cylindrique pleine (343) et une petite couronne cylindrique (344) pleine en saillie axiale par rapport à la grande couronne (343), - perçage de canaux de circulation pilote (342p) et multipoint (342m) dans les couronnes cylindriques pleines (343, 344), - usinage des diamètres des couronnes cylindriques pleines (343, 344) percées afin d'obtenir la première virole (34), - emboitement de la première virole (34) dans la deuxième virole (35) de sorte à avoir chevauchement à la fois entre les grandes couronnes pleine et creuse (343, 350) et entre les petites couronnes pleine et creuse (344, 380), - brasage étanche des couronnes (343, 350, 344, 380) entre elles. A method of manufacturing a multipoint fuel injector (3) comprising a first ferrule (34) and a second ferrule (35) made according to claim 12, characterized in that the following steps are carried out: - producing a one-piece piece (34) comprising a large cylindrical solid crown (343) and a small cylindrical ring (344) solid projecting axially with respect to the large ring (343), - Drilling pilot (342p) and multipoint (342m) circulation channels in full cylindrical rings (343, 344), machining the diameters of the solid cylindrical rings (343, 344) drilled to obtain the first ferrule (34), - interlocking the first ferrule (34) in the second ferrule (35) so as to overlap both between the large full and hollow crowns (343, 350) and between the small full and hollow crowns (344, 380), - sealing solder rings (343, 350, 344, 380) between them.
EP08161242.6A 2007-08-10 2008-07-28 Multi-point injector for turbomachine Active EP2026002B1 (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2230458A1 (en) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Burner assembly for fluid fuels and method for producing a burner assembly
FR2951246A1 (en) * 2009-10-13 2011-04-15 Snecma MULTI-POINT INJECTOR FOR A TURBOMACHINE COMBUSTION CHAMBER
FR2951245A1 (en) * 2009-10-13 2011-04-15 Snecma MULTI-POINT INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
FR2952699A1 (en) * 2009-11-18 2011-05-20 Snecma Fuel and air injection system for annular combustion chamber of turbomachine of aircraft, has space allowing air flow to be mixed with fuel in system, and fuel injection unit with injection channels to inject one type of fuel in space
FR2958015A1 (en) * 2010-03-24 2011-09-30 Snecma Air and fuel injecting system for annular combustion chamber of turbomachine of aircraft, has air intake annular space arranged radially and inwardly relative to ejecting units for admission of air flow to mix with fuel in annular channel
FR2971038A1 (en) * 2011-01-31 2012-08-03 Snecma INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
EP2489939A1 (en) * 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Combustion chamber with a wall section and a brim element
WO2015025109A1 (en) 2013-08-20 2015-02-26 Snecma Method and system for injecting fuel into an engine combustion chamber
FR3010139A1 (en) * 2013-09-04 2015-03-06 Snecma DEVICE AND METHOD FOR ESTIMATING CLAMPS IN A FUEL INJECTION SYSTEM IN A COMBUSTION CHAMBER OF AN ENGINE
FR3017416A1 (en) * 2014-02-12 2015-08-14 Snecma COOLING A MAIN CHANNEL IN A FUEL SYSTEM WITH MULTIPOINT INJECTION
WO2018060590A1 (en) 2016-09-29 2018-04-05 Safran Helicopter Engines Device for supplying fuel to a turbine engine combustion chamber, improving the homogeneity of the supply of the fuel injection devices
FR3118791A1 (en) * 2021-01-14 2022-07-15 Safran Aircraft Engines System and method for supplying fuel to a combustion chamber in an aircraft turbine engine

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7870737B2 (en) * 2007-04-05 2011-01-18 United Technologies Corporation Hooded air/fuel swirler for a gas turbine engine
US9151227B2 (en) * 2010-11-10 2015-10-06 Solar Turbines Incorporated End-fed liquid fuel gallery for a gas turbine fuel injector
US9188063B2 (en) 2011-11-03 2015-11-17 Delavan Inc. Injectors for multipoint injection
US9316154B2 (en) * 2013-03-07 2016-04-19 Solar Turbines Incorporated Gas turbine fuel injector with metering cavity
EP3401529A1 (en) 2013-03-14 2018-11-14 United Technologies Corporation Hollow-wall heat shield for fuel injector component
FR3003632B1 (en) 2013-03-19 2016-10-14 Snecma INJECTION SYSTEM FOR TURBOMACHINE COMBUSTION CHAMBER HAVING AN ANNULAR WALL WITH CONVERGENT INTERNAL PROFILE
US9366190B2 (en) * 2013-05-13 2016-06-14 Solar Turbines Incorporated Tapered gas turbine engine liquid gallery
US9556795B2 (en) * 2013-09-06 2017-01-31 Delavan Inc Integrated heat shield
US9447976B2 (en) * 2014-01-10 2016-09-20 Solar Turbines Incorporated Fuel injector with a diffusing main gas passage
JP6535442B2 (en) 2014-08-18 2019-06-26 川崎重工業株式会社 Fuel injection device
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles
US9897321B2 (en) 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US10876477B2 (en) * 2016-09-16 2020-12-29 Delavan Inc Nozzles with internal manifolding
US11466620B2 (en) * 2017-10-20 2022-10-11 Siemens Energy, Inc. Hybrid manufacturing of a support housing
FR3091574B1 (en) * 2019-01-08 2020-12-11 Safran Aircraft Engines TURBOMACHINE INJECTION SYSTEM, INCLUDING A MIXER BOWL AND SWIRL HOLES
CN112082174B (en) * 2019-06-12 2022-02-25 中国航发商用航空发动机有限责任公司 Fuel nozzle, combustion chamber, gas turbine and method for preventing coking of fuel in fuel nozzle
GB201910284D0 (en) * 2019-07-18 2019-09-04 Rolls Royce Plc Fuel injector
FR3115075B1 (en) * 2020-10-14 2022-10-21 Safran Aircraft Engines FUEL SUPPLY CIRCUIT FOR A TURBOMACHINE COMBUSTION CHAMBER
CN112590222B (en) * 2020-11-27 2022-12-02 江苏神力医用制品有限公司 Automatic manufacturing equipment of syringe
CN114754378B (en) * 2022-06-13 2022-08-19 成都中科翼能科技有限公司 Gas turbine combustor structure

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6523350B1 (en) * 2001-10-09 2003-02-25 General Electric Company Fuel injector fuel conduits with multiple laminated fuel strips
EP1806536A1 (en) * 2006-01-09 2007-07-11 Snecma Cooling of a multimode injection device for a combustion chamber, particularly for a gas turbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3684186A (en) * 1970-06-26 1972-08-15 Ex Cell O Corp Aerating fuel nozzle
US4111369A (en) * 1977-07-05 1978-09-05 General Motors Corporation Fuel nozzle
SU981652A2 (en) * 1981-02-06 1982-12-15 Казанский Ордена Трудового Красного Знамени Авиационный Институт Им.А.Н.Туполева Flow mixing apparatus
US4708330A (en) * 1985-05-31 1987-11-24 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Alignment and assembly tool for very large diameter cylinders
US6718770B2 (en) * 2002-06-04 2004-04-13 General Electric Company Fuel injector laminated fuel strip
FR2896031B1 (en) * 2006-01-09 2008-04-18 Snecma Sa MULTIMODE INJECTION DEVICE FOR COMBUSTION CHAMBER, IN PARTICULAR A TURBOREACTOR
US8141368B2 (en) * 2008-11-11 2012-03-27 Delavan Inc Thermal management for fuel injectors

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6523350B1 (en) * 2001-10-09 2003-02-25 General Electric Company Fuel injector fuel conduits with multiple laminated fuel strips
EP1806536A1 (en) * 2006-01-09 2007-07-11 Snecma Cooling of a multimode injection device for a combustion chamber, particularly for a gas turbine

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102159890A (en) * 2009-03-17 2011-08-17 西门子公司 Burner arrangement for liquid fuels and method for producing burner arrangement
WO2010105956A1 (en) * 2009-03-17 2010-09-23 Siemens Aktiengesellschaft Burner arrangement for liquid fuels and method for producing a burner arrangement
EP2230458A1 (en) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Burner assembly for fluid fuels and method for producing a burner assembly
RU2523517C2 (en) * 2009-03-17 2014-07-20 Сименс Акциенгезелльшафт Burner facility for fluid fuel and method of manufacturing burner facility
CN102159890B (en) * 2009-03-17 2013-02-13 西门子公司 Burner arrangement for liquid fuels and method for producing burner arrangement
US9046271B2 (en) 2009-10-13 2015-06-02 Snecma Multipoint injector for a turbine engine combustion chamber
CN102575844B (en) * 2009-10-13 2014-12-31 斯奈克玛 Multi-point injector for a turbine engine combustion chamber
WO2011045486A1 (en) 2009-10-13 2011-04-21 Snecma Multi-point injector for a turbine engine combustion chamber
FR2951246A1 (en) * 2009-10-13 2011-04-15 Snecma MULTI-POINT INJECTOR FOR A TURBOMACHINE COMBUSTION CHAMBER
CN102575843A (en) * 2009-10-13 2012-07-11 斯奈克玛 Multipoint injection device for a combustion chamber of a turbine engine
CN102575844A (en) * 2009-10-13 2012-07-11 斯奈克玛 Multi-point injector for a turbine engine combustion chamber
RU2543097C2 (en) * 2009-10-13 2015-02-27 Снекма Multipoint injector for turbo-machine combustion chamber
RU2539223C2 (en) * 2009-10-13 2015-01-20 Снекма Multipoint injection device for combustion chamber of turbo-machine
US9003802B2 (en) 2009-10-13 2015-04-14 Snecma Multipoint injection device for a combustion chamber of a turbine engine
FR2951245A1 (en) * 2009-10-13 2011-04-15 Snecma MULTI-POINT INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
WO2011045503A1 (en) 2009-10-13 2011-04-21 Snecma Multipoint injection device for a combustion chamber of a turbine engine
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FR2958015A1 (en) * 2010-03-24 2011-09-30 Snecma Air and fuel injecting system for annular combustion chamber of turbomachine of aircraft, has air intake annular space arranged radially and inwardly relative to ejecting units for admission of air flow to mix with fuel in annular channel
WO2012104523A3 (en) * 2011-01-31 2013-01-03 Snecma Injection device for a turbo machine combustion chamber
RU2583486C2 (en) * 2011-01-31 2016-05-10 Снекма Injector for turbomachine combustion chamber
US9605594B2 (en) 2011-01-31 2017-03-28 Snecma Injection device for a turbine engine combustion chamber
WO2012104523A2 (en) 2011-01-31 2012-08-09 Snecma Injection device for a turbo machine combustion chamber
FR2971038A1 (en) * 2011-01-31 2012-08-03 Snecma INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
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CA2638814C (en) 2015-11-03
FR2919898B1 (en) 2014-08-22
US8959772B2 (en) 2015-02-24
JP5165495B2 (en) 2013-03-21
CA2638814A1 (en) 2009-02-10
US20120186083A1 (en) 2012-07-26
EP2026002B1 (en) 2016-07-20
JP2009041903A (en) 2009-02-26
FR2919898A1 (en) 2009-02-13
US20090038312A1 (en) 2009-02-12
RU2477808C2 (en) 2013-03-20
RU2008132887A (en) 2010-02-20
US8186163B2 (en) 2012-05-29

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