EP2488791B1 - Multipoint injection device for a combustion chamber of a turbine engine - Google Patents

Multipoint injection device for a combustion chamber of a turbine engine Download PDF

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Publication number
EP2488791B1
EP2488791B1 EP10778699.8A EP10778699A EP2488791B1 EP 2488791 B1 EP2488791 B1 EP 2488791B1 EP 10778699 A EP10778699 A EP 10778699A EP 2488791 B1 EP2488791 B1 EP 2488791B1
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EP
European Patent Office
Prior art keywords
annular
ring
chamber
front face
injection
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Application number
EP10778699.8A
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German (de)
French (fr)
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EP2488791A1 (en
Inventor
Didier Hippolyte Hernandez
Emilie Lachaud
Thomas Olivier Marie Noel
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the present invention relates to a "multipoint" fuel injection device for an annular turbomachine combustion chamber such as an airplane turbojet or turboprop engine.
  • a turbomachine comprises an annular combustion chamber arranged at the outlet of a high pressure compressor and provided with a plurality of fuel injection devices regularly distributed circumferentially at the inlet of the combustion chamber.
  • a multipoint injection device comprises a first venturi inside which is mounted a pilot injector centered on the axis of the first venturi and continuously supplied by a pilot circuit and a second venturi coaxial with the first venturi and surrounding it.
  • This second venturi comprises an annular chamber at its upstream end in which is mounted an annular ring supplied with fuel by a multipoint circuit.
  • the ring has fuel injection orifices formed in a front face and aligned with orifices of a front face of the annular chamber to eject the fuel downstream and outward of the second venturi.
  • the pilot circuit continuously provides optimized fuel flow for low revs and the multi-point circuit provides optimized intermittent fuel flow for high revs.
  • the intermittent use of the multipoint circuit has the major disadvantage of inducing, under the effect of the high temperatures due to the radiation of the flame in the combustion chamber, scrubbing or coking of the fuel stagnant inside the circuit multipoint when it is cut off. These phenomena can lead to the formation of coke in the ring and at the fuel injection ports of the multipoint circuit impacting the spraying of the fuel. fuel by the multipoint circuit and thus the operation of the combustion chamber.
  • the document EP 1806536 discloses a fuel injection device for an annular turbomachine combustion chamber, comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit intermittently supplying injection orifices formed in the front face of an upstream annular chamber of a second venturi coaxial with and surrounding the first venturi, an annular ring mounted in the annular chamber, the device also comprising thermal insulation means of the lateral portion of the annular ring.
  • Such a configuration does not, however, sufficiently reduce the risk of coking the fuel at the front face of the annular chamber which remains highly exposed to the heat radiation generated by the combustion of the fuel downstream.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a fuel injection device for an annular turbomachine combustion chamber comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit intermittently supplying the injection orifices and a annular chamber formed upstream of a second venturi coaxial with and surrounding the first venturi, characterized in that the injection orifices are formed in a front face of an annular ring mounted in the annular chamber and in that that the device comprises means for thermal insulation of the end face of the annular ring comprising an annular cavity formed around the injection orifices between the end face of the annular ring and a front wall of the annular chamber and intended to be filled in operation of air or coked fuel.
  • thermal insulation means formed by an insulating annular cavity interposed between the front face of the ring and a downstream wall the annular chamber protects the injection ports of the crown to prevent coking, and thus ensures a optimal operation of the multipoint circuit.
  • the annular cavity may be filled with air or coked fuel which forms a good thermal insulator of the multipoint annular ring and its fuel injection ports relative to the thermal radiation of the fuel combustion.
  • the device also comprises a cooling circuit of the annular ring by circulation of the fuel of the pilot circuit in an internal annular channel formed between inner cylindrical walls of the ring and the annular chamber and an outer annular channel formed between cylindrical walls. external of the crown and the annular chamber.
  • one of the internal or external channels communicates with the aforementioned annular cavity, the other of the inner or outer channels being isolated from this cavity, which makes it possible to fill the front annular fuel cavity which will coke under the effect of thermal radiation from fuel combustion.
  • the radially inner or outer periphery of the front face of the annular ring comprises an annular flange whose downstream end defines with the front wall of the chamber an annular communication passage between the aforementioned annular cavity. and one of the internal or external channels of the cooling circuit.
  • This annular passage allows a fuel supply inside the front cavity and its coking under the effect of thermal radiation for the isolation of the injection ports of the crown.
  • the radially outer periphery of the front face of the ring is in radial abutment on the outer cylindrical wall of the chamber for centering the ring in the chamber.
  • each injection orifice of the ring is formed in a protruding lug on the front face of the ring, these pins being inserted in abutment in a cavity of a corresponding boss formed on the front wall of the annular chamber.
  • the positioning in abutment ensures a correct axial mounting of the ring in the annular chamber.
  • Each cavity of a boss opens out of the annular chamber by a bore aligned with the injection port of the corresponding stud, this bore having a diameter greater than that of the injection orifice, which allows moving the coking zone of the drops of fuel out of the nipple injection holes and towards the holes of the annular chamber.
  • the injection orifices are formed in cylindrical pins fixed in holes in the end face of the annular ring, these pegs protruding projecting on this front face and forming positioning means and centering in the annular chamber.
  • This configuration is particularly interesting when the space inside the chamber is reduced and does not allow the realization of nipples and bosses as in the previous embodiment.
  • the injection port of each pin comprises a downstream end of larger diameter to prevent coking of the injection ports during the stopping of the multipoint circuit.
  • the axial positioning of the ring in the annular chamber is formed by an annular flange formed at the radially inner end of the downstream wall of the ring, this flange abutting on the front wall of the annular chamber.
  • the invention also relates to an annular turbomachine combustion chamber, comprising at least one fuel injection device of the type described above.
  • FIG 1 illustrating an injection device 10 according to the prior art and comprising two fuel injection systems, one of which is a pilot system operating continuously and the other a multipoint system operating intermittently.
  • This device is intended to be mounted in an opening of a bottom wall of an annular combustion chamber of a turbomachine which is fed with air by an upstream high-pressure compressor and whose combustion gases feed a turbine mounted downstream.
  • This device comprises a first venturi 12 and a second venturi 14 coaxial, the first venturi 12 being mounted inside the second venturi 14.
  • a pilot injector 16 is mounted inside a first stage of tendrils 18 inserted axially to the interior of the first venturi 12.
  • a second stage of tendrils 20 is formed at the upstream end and radially outside the first venturi 12 and separates the first and second venturi, 12, 14.
  • the second venturi 14 comprises an annular chamber 22 formed by two radially inner cylindrical walls 24 and outer 26 connected to each other by a frustoconical downstream wall 28 converging downstream.
  • An annular ring 30 also comprising two radially inner cylindrical walls 32 and external wall 34 connected to each other by a downstream convergent downstream conical downstream wall 36 is mounted inside the annular chamber 22 so that the downstream walls 28, 36 of the annular chamber 22 and the annular ring 30 are in contact.
  • the annular ring 30 and the annular chamber 22 each comprise an annular opening at their upstream end.
  • the cylindrical walls 24, 26 of the annular chamber 22 extend projecting upstream with respect to the upstream ends of the cylindrical walls 32, 34 of the annular ring 30.
  • the downstream wall 36 of the annular ring 30 comprises injection orifices 40 uniformly distributed circumferentially and opening into corresponding orifices 42 in the downstream wall 28 of the annular chamber 22.
  • the orifices 40, 42 of the annular chamber 22 and the annular ring 30 have identical diameters.
  • An internal annular channel 44 for passing fuel is defined between the inner cylindrical walls 24, 34 of the annular ring 30 and the annular chamber 22.
  • an annular channel external fuel passage 46 is defined between the outer cylindrical walls 26, 34 of the annular ring 30 and the annular chamber 22.
  • the injection device comprises a fuel feed body 48 whose downstream portion is annular and comprises a cylindrical duct 50 axially engaged with sealing between the inner cylindrical walls 24 and outer 26 of the annular chamber 22 and opening sealing between internal cylindrical walls 32 and outer 34 of the annular ring 30.
  • the duct 50 has a radial shoulder 54 abutting on the upstream ends of the inner cylindrical walls 32 and outer 34 of the annular ring 30.
  • This sealing assembly of the body 48 makes it possible to guarantee that the inner and outer annular channels 44 and 44 are sealed with respect to the annular space formed inside the annular ring 30.
  • a fuel supply arm 56 is connected to the body 48 and comprises two coaxial ducts of which one central 58 feeds a channel 60 of the body 48 opening downstream inside the annular ring 30 and the other formed outer 62 around the central duct 58 supplies at the output of separate channels (not shown) opening into the inner annular channels 44 and outer 46, respectively.
  • the body 48 comprises a fuel collection cavity 64 formed diametrically opposite the fuel supply arm 56 and at the upstream ends of the cylindrical walls 32, 34 of the annular ring 30 so that the annular channels internal 44 and outer 46 communicate with the collection cavity 64.
  • a duct 66 is connected at one end to the pilot injector 16 and at the other end opens into the collection cavity 64.
  • the central duct 58 of the arm 56 supplies fuel to the channel 60 of the body 48, the fuel then circulating in the annular ring 30 and being injected into the combustion chamber downstream through the orifices 40, 42 of the ring gear 30 and from bedroom 22.
  • the external duct 62 of the arm 56 feeds the channels of the body 48 opening into the inner and outer annular channels 44 and 46, the fuel then passing into the collection cavity 64 to supply the pilot injector 16 via the duct 66.
  • the pilot circuit operates continuously while the multipoint circuit operates intermittently during specific flight phases such as takeoff requiring additional power.
  • the hot air (at about 600 ° C.) coming from the high-pressure compressor flows inside the first venturi 12, in the first radial swirler 18, and from the air also flows inside the second radial swirler 20, between the first 12 and second 14 venturis.
  • downstream face 28 of the annular ring 22 is subjected directly to the thermal radiation of the combustion, which can lead to a coking of the fuel in the injection orifices 40, 42 of the ring 30 and the annular chamber 22 during flight phases where the multipoint circuit is not used.
  • the invention provides a solution to this problem by integrating in the injection device 68 thermal insulation means of the front wall of the annular ring multipoint.
  • thermal insulation means comprise an insulating annular cavity 70 formed between the end face 72 of the annular ring 74 and the downstream wall 76 of the annular chamber 78.
  • This cavity 70 extends between the injection orifices 80 so as to achieve thermal insulation closer to them. This reduces the risk of coking fuel at the fuel injection ports 80 to ensure optimum operation of the multipoint circuit.
  • the end face 72 of the annular ring 74 comprises a plurality of pins 82 projecting regularly distributed around the ring 74 and each comprising an injection port 80. These pins 82 are inserted into boss cavities 84 of the upstream face. of the downstream wall 76 of the annular chamber 78. The pins 82 are engaged inside the cavities of the bosses so as to abut on the downstream wall 76 of the annular chamber 78 to ensure correct axial positioning of the ring 74 in the annular chamber 78.
  • the downstream wall 76 of the annular chamber 78 comprises ( figure 3 ) bores 86 each opening upstream in the cavity of a boss 84 and downstream to the outside of the second venturi, each bore 86 being aligned with an injection port 80 of the ring 74 and having a diameter greater than that of an injection orifice 80, in order to move the coking zone of the drops of fuel towards the bores 86 of the annular chamber 78.
  • the pins 82 have a substantially cylindrical shape and are brazed inside the cavities of the bosses 84 to seal between the driver circuit and the multipoint circuit. It is possible to check the good performance of the stirring by visual inspection through the holes 86 of the downstream wall 76 of the annular chamber 78 because these holes 86 have a diameter greater than that of the injection orifices 80.
  • the radially outer periphery of the end face 72 of the ring 74 extends radially outside its outer cylindrical wall 90 and bears radially on the outer cylindrical wall 92 of the annular chamber 78 so as to center the ring 74 in the annular chamber 78.
  • the radially inner periphery of the end face 72 comprises an annular flange 94 extending downstream of the end face 72 and in the extension of the internal cylindrical wall 96. The downstream end this annular flange 94 forms an annular fuel passage between the inner annular channel 44 and the front annular cavity 70.
  • the device according to the invention also comprises a cooling circuit formed by an internal annular channel 44 delimited by the internal cylindrical walls 96, 97 of the ring 74 and the annular chamber 78 and an external annular channel 46 delimited by the outer cylindrical walls 90, 92 of the crown 74 and the annular chamber 78.
  • the outer annular channel 46 is isolated from the front cavity by the radially outer periphery of the end face 72 of the ring 74 which can be brazed or not on the outer cylindrical wall 92 of the annular chamber 78 so as to achieve or not a tight connection.
  • the device comprises a plurality of pins 96 for centering the ring gear 100 in the annular chamber 102, these pins 98 being regularly distributed around the ring gear 100 and mounted axially in holes 101 in the front wall 104 of the ring gear 100 and in corresponding holes 103 in the annular chamber 102.
  • the upstream and downstream faces of the pins are substantially parallel to the frustoconical walls 104, 106 of the ring gear 100 and of the annular chamber 102.
  • the axial dimension of each pin is such that its upstream faces and downstream are aligned with the upstream face of the front wall 104 of the ring 100 and with the downstream face of the downstream wall 106 of the annular chamber 102, respectively.
  • Each pin 98 comprises an injection orifice 108 formed of a first bore 110 opening upstream inside the annular ring 100 and downstream in a second hole 112 of larger diameter which opens outwards from the second venturi 14.
  • the holes 110, 112 are aligned along a straight line perpendicular to the walls frustoconical downstream 104, 106 of the crown 100 and the annular chamber 102.
  • the larger diameter of the holes 112 of the annular chamber with respect to the diameters of the injection orifices 110 makes it possible to limit the coking of the injection orifices 110.
  • the radially inner and outer peripheries of the front wall 104 of the ring gear 100 each comprise an inner and outer annular rim 114, extending downstream of the end wall 104 and in the extension of the inner cylindrical 118 and outer 120, respectively .
  • the inner annular flange 114 is in contact with the downstream wall 106 of the chamber 102 to provide an axial positioning stop of the ring gear 100 in the annular chamber 102 while the outer annular flange 116 defines with the front wall 106 of the chamber 102 an annular passage of communication between the outer annular cavity 46 of the pilot circuit and the front cavity 70 of thermal insulation.
  • the assembly of the ring gear 100, the chamber 102 and the pins 98 is made in the following manner: the annular ring 100 is mounted in axial abutment inside the annular chamber 102 by virtue of the internal annular flange 114 of the ring 100 and oriented angularly so that the holes 101 of the ring 100 are aligned with the holes 103 of the annular chamber 102.
  • the centering pins 98 are then mounted in the holes 101, 103 of the ring 100 and the chamber 102 and a soldering operation of pins 98 in these holes, for sealing between the pilot circuit and the multipoint circuit.
  • the upstream and downstream faces of the pins 98 are machined again.
  • the bores 110, 112 are formed in each of the pins 98, this operation being performed after the soldering and machining operations to avoid a partial closure of the holes 110, 112 of the pins 98.
  • This configuration with centering pins is particularly interesting in multipoint nozzle configurations where the space inside the chamber is reduced and does not allow to make nipples and bosses.
  • the front annular cavity is in communication with one of the internal channels ( figure 4 ) or external ( figure 8 ) of the cooling circuit to supply the front annular cavity 70 with fuel during operation of the turbomachine.
  • the fuel present inside the front cavity will coke under the effect of thermal radiation, thus forming a thermal insulation protecting the multipoint annular ring.

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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)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Description

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

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

Le circuit pilote fournit en permanence un débit de carburant optimisé pour les bas régimes et le circuit multipoint fournit un débit de carburant intermittent optimisé pour les hauts régimes.The pilot circuit continuously provides optimized fuel flow for low revs and the multi-point circuit provides optimized intermittent fuel flow for high revs.

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

Le document EP 1806536 décrit un dispositif d'injection de carburant pour une chambre annulaire de combustion de turbomachine, comprenant un circuit pilote alimentant en permanence un injecteur débouchant dans un premier venturi et un circuit multipoint alimentant par intermittence des orifices d'injection formés dans la face frontale d'une chambre annulaire amont d'un second venturi coaxial au premier venturi et entourant celui-ci, une couronne annulaire montée dans la chambre annulaire, le dispositif comprenant aussi des moyens d'isolation thermique de la partie latérale de la couronne annulaire.The document EP 1806536 discloses a fuel injection device for an annular turbomachine combustion chamber, comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit intermittently supplying injection orifices formed in the front face of an upstream annular chamber of a second venturi coaxial with and surrounding the first venturi, an annular ring mounted in the annular chamber, the device also comprising thermal insulation means of the lateral portion of the annular ring.

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

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

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

A cet effet, elle propose un dispositif d'injection de carburant pour une chambre annulaire de combustion de turbomachine, comprenant un circuit pilote alimentant en permanence un injecteur débouchant dans un premier venturi et un circuit multipoint alimentant par intermittence des orifices d'injection et une chambre annulaire formée à l'amont d'un second venturi coaxial au premier venturi et entourant celui-ci, caractérisé en ce que les orifices d'injection sont formés dans une face frontale d'une couronne annulaire montée dans la chambre annulaire et en ce que le dispositif comprend des moyens d'isolation thermique de la face frontale de la couronne annulaire comprenant une cavité annulaire formée autour des orifices d'injection entre la face frontale de la couronne annulaire et une paroi frontale de la chambre annulaire et destinée à être remplie en fonctionnement d'air ou de carburant cokéfié.For this purpose, it proposes a fuel injection device for an annular turbomachine combustion chamber, comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit intermittently supplying the injection orifices and a annular chamber formed upstream of a second venturi coaxial with and surrounding the first venturi, characterized in that the injection orifices are formed in a front face of an annular ring mounted in the annular chamber and in that that the device comprises means for thermal insulation of the end face of the annular ring comprising an annular cavity formed around the injection orifices between the end face of the annular ring and a front wall of the annular chamber and intended to be filled in operation of air or coked fuel.

L'intégration de moyens d'isolation thermique formés par une cavité annulaire isolante intercalée entre la face frontale de la couronne et une paroi aval la chambre annulaire permet de protéger les orifices d'injection de la couronne pour éviter leur cokéfaction, et garantit ainsi un fonctionnement optimal du circuit multipoint.The integration of thermal insulation means formed by an insulating annular cavity interposed between the front face of the ring and a downstream wall the annular chamber protects the injection ports of the crown to prevent coking, and thus ensures a optimal operation of the multipoint circuit.

La cavité annulaire peut être remplie d'air ou de carburant cokéfié qui forme un bon isolant thermique de la couronne annulaire multipoint et de ses orifices d'injection de carburant par rapport au rayonnement thermique de la combustion du carburant.The annular cavity may be filled with air or coked fuel which forms a good thermal insulator of the multipoint annular ring and its fuel injection ports relative to the thermal radiation of the fuel combustion.

Préférentiellement, le dispositif comprend également un circuit de refroidissement de la couronne annulaire par circulation du carburant du circuit pilote dans un canal annulaire interne formé entre des parois cylindriques internes de la couronne et de la chambre annulaire et un canal annulaire externe formé entre des parois cylindriques externes de la couronne et de la chambre annulaire.Preferably, the device also comprises a cooling circuit of the annular ring by circulation of the fuel of the pilot circuit in an internal annular channel formed between inner cylindrical walls of the ring and the annular chamber and an outer annular channel formed between cylindrical walls. external of the crown and the annular chamber.

Avantageusement, l'un des canaux interne ou externe communique avec la cavité annulaire précitée, l'autre des canaux interne ou externe étant isolé de cette cavité, ce qui permet de remplir la cavité annulaire frontale de carburant lequel va cokéfier sous l'effet du rayonnement thermique de la combustion du carburant.Advantageously, one of the internal or external channels communicates with the aforementioned annular cavity, the other of the inner or outer channels being isolated from this cavity, which makes it possible to fill the front annular fuel cavity which will coke under the effect of thermal radiation from fuel combustion.

Selon une autre caractéristique de l'invention, la périphérie radialement interne ou externe de la face frontale de la couronne annulaire comprend un rebord annulaire dont l'extrémité aval définit avec la paroi frontale de la chambre un passage annulaire de communication entre la cavité annulaire précitée et l'un des canaux interne ou externe du circuit de refroidissement.According to another characteristic of the invention, the radially inner or outer periphery of the front face of the annular ring comprises an annular flange whose downstream end defines with the front wall of the chamber an annular communication passage between the aforementioned annular cavity. and one of the internal or external channels of the cooling circuit.

Ce passage annulaire permet une arrivée de carburant à l'intérieur de la cavité frontale et sa cokéfaction sous l'effet du rayonnement thermique pour l'isolation des orifices d'injection de la couronne.This annular passage allows a fuel supply inside the front cavity and its coking under the effect of thermal radiation for the isolation of the injection ports of the crown.

Selon encore une autre caractéristique de l'invention, la périphérie radialement externe de la face frontale de la couronne est en appui radial sur la paroi cylindrique externe de la chambre pour le centrage de la couronne dans la chambre.According to yet another characteristic of the invention, the radially outer periphery of the front face of the ring is in radial abutment on the outer cylindrical wall of the chamber for centering the ring in the chamber.

Selon une première forme de réalisation de l'invention, chaque orifice d'injection de la couronne est formé dans un téton en saillie sur la face frontale de la couronne, ces tétons étant inséré en butée dans une cavité d'un bossage correspondant formé sur la paroi frontale de la chambre annulaire. Le positionnement en butée permet de garantir un montage axial correct de la couronne dans la chambre annulaire.According to a first embodiment of the invention, each injection orifice of the ring is formed in a protruding lug on the front face of the ring, these pins being inserted in abutment in a cavity of a corresponding boss formed on the front wall of the annular chamber. The positioning in abutment ensures a correct axial mounting of the ring in the annular chamber.

Chaque cavité d'un bossage débouche à l'extérieur de la chambre annulaire par un perçage aligné avec l'orifice d'injection du téton correspondant, ce perçage ayant un diamètre supérieur à celui de l'orifice d'injection, ce qui permet de déplacer la zone de cokéfaction des gouttes de carburant hors des orifices d'injection des tétons et vers les perçages de la chambre annulaire.Each cavity of a boss opens out of the annular chamber by a bore aligned with the injection port of the corresponding stud, this bore having a diameter greater than that of the injection orifice, which allows moving the coking zone of the drops of fuel out of the nipple injection holes and towards the holes of the annular chamber.

Selon une variante de réalisation de l'invention, les orifices d'injection sont formés dans des pions cylindriques fixés dans des trous de la face frontale de la couronne annulaire, ces pions dépassant en saillie sur cette face frontale et formant des moyens de positionnement et de centrage dans la chambre annulaire.According to an alternative embodiment of the invention, the injection orifices are formed in cylindrical pins fixed in holes in the end face of the annular ring, these pegs protruding projecting on this front face and forming positioning means and centering in the annular chamber.

Cette configuration est particulièrement intéressante lorsque l'encombrement à l'intérieur de la chambre est réduit et ne permet pas la réalisation de tétons et de bossages comme dans la réalisation précédente.This configuration is particularly interesting when the space inside the chamber is reduced and does not allow the realization of nipples and bosses as in the previous embodiment.

L'orifice d'injection de chaque pion comprend une extrémité aval de plus grand diamètre afin d'éviter une cokéfaction des orifices d'injection lors de l'arrêt du circuit multipoint.The injection port of each pin comprises a downstream end of larger diameter to prevent coking of the injection ports during the stopping of the multipoint circuit.

Le positionnement axial de la couronne dans la chambre annulaire est réalisé par un rebord annulaire formé à l'extrémité radialement interne de la paroi aval de la couronne, ce rebord venant en butée sur la paroi frontale de la chambre annulaire.The axial positioning of the ring in the annular chamber is formed by an annular flange formed at the radially inner end of the downstream wall of the ring, this flange abutting on the front wall of the annular chamber.

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

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

  • la figure 1 est une vue schématique partielle en coupe axiale d'un dispositif d'injection de carburant multipoint selon la technique antérieure ;
  • la figure 2 est une vue schématique partielle en coupe axiale d'un dispositif d'injection de carburant multipoint selon l'invention ;
  • la figure 3 est une vue schématique en coupe axiale à plus grande échelle de la couronne et de la chambre annulaire du dispositif d'injection de la figure 2 selon un plan passant par un orifice d'injection multipoint,
  • la figure 4 est une vue schématique en coupe axiale à plus grande échelle de la couronne et de la chambre annulaire du dispositif d'injection de la figure 2 selon un plan passant entre deux orifices d'injection multipoint,
  • la figure 5 est une vue schématique en perspective de la face frontale de la couronne annulaire du dispositif d'injection de la figure 2 ;
  • la figure 6 est une vue schématique en perspective de la chambre annulaire du dispositif d'injection de la figure 2 ;
  • la figure 7 est une vue schématique en coupe axiale d'une couronne et d'une chambre annulaire d'un dispositif selon une variante de l'invention et selon un plan passant par un orifice d'injection multipoint ;
  • la figure 8 est une vue schématique en coupe axiale similaire à celle de la figure 7 selon un plan passant entre deux orifices d'injection multipoint ;
  • la figure 9 est une vue en perspective éclatée du dispositif d'injection des figures 7 et 8.
The invention will be better understood and other details, advantages and features of the invention will appear on reading the following description given by way of non-limiting example, with reference to the accompanying drawings in which:
  • the figure 1 is a partial diagrammatic view in axial section of a multipoint fuel injection device according to the prior art;
  • the figure 2 is a partial schematic view in axial section of a multipoint fuel injection device according to the invention;
  • the figure 3 is a diagrammatic view in axial section on a larger scale of the ring and the annular chamber of the injection device of the figure 2 according to a plane passing through a multipoint injection port,
  • the figure 4 is a diagrammatic view in axial section on a larger scale of the ring and the annular chamber of the injection device of the figure 2 according to a plane passing between two multipoint injection ports,
  • the figure 5 is a schematic perspective view of the front face of the annular ring of the injection device of the figure 2 ;
  • the figure 6 is a schematic perspective view of the annular chamber of the injection device of the figure 2 ;
  • the figure 7 is a schematic view in axial section of a ring and an annular chamber of a device according to a variant of the invention and in a plane passing through a multipoint injection port;
  • the figure 8 is a schematic view in axial section similar to that of the figure 7 in a plane passing between two multipoint injection ports;
  • the figure 9 is an exploded perspective view of the injection device of Figures 7 and 8 .

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

L'invention apporte une solution à ce problème en intégrant dans le dispositif d'injection 68 des moyens d'isolation thermique de la paroi frontale de la couronne annulaire multipoint.The invention provides a solution to this problem by integrating in the injection device 68 thermal insulation means of the front wall of the annular ring multipoint.

Ces moyens d'isolation thermique comprennent une cavité annulaire isolante 70 formée entre la face frontale 72 de la couronne annulaire 74 et la paroi aval 76 de la chambre annulaire 78. Cette cavité 70 s'étend entre les orifices d'injection 80 de manière à réaliser une isolation thermique au plus près de ceux-ci. Cela permet de diminuer les risques de cokéfaction du carburant au niveau des orifices d'injection 80 de carburant afin de garantir un fonctionnement optimal du circuit multipoint.These thermal insulation means comprise an insulating annular cavity 70 formed between the end face 72 of the annular ring 74 and the downstream wall 76 of the annular chamber 78. This cavity 70 extends between the injection orifices 80 so as to achieve thermal insulation closer to them. This reduces the risk of coking fuel at the fuel injection ports 80 to ensure optimum operation of the multipoint circuit.

Dans une première forme de réalisation de l'invention représentée aux figures 2 à 6, la face frontale 72 de la couronne annulaire 74 comprend une pluralité de tétons 82 en saillie régulièrement répartis autour de la couronne 74 et comprenant chacun un orifice d'injection 80. Ces tétons 82 sont insérés dans des cavités de bossages 84 de la face amont de la paroi aval 76 de la chambre annulaire 78. Les tétons 82 sont engagés à l'intérieur des cavités des bossages de manière à venir en butée sur la paroi aval 76 de la chambre annulaire 78 pour assurer un positionnement axial correct de la couronne 74 dans la chambre annulaire 78.In a first embodiment of the invention shown in Figures 2 to 6 , the end face 72 of the annular ring 74 comprises a plurality of pins 82 projecting regularly distributed around the ring 74 and each comprising an injection port 80. These pins 82 are inserted into boss cavities 84 of the upstream face. of the downstream wall 76 of the annular chamber 78. The pins 82 are engaged inside the cavities of the bosses so as to abut on the downstream wall 76 of the annular chamber 78 to ensure correct axial positioning of the ring 74 in the annular chamber 78.

La paroi aval 76 de la chambre annulaire 78 comprend (figure 3) des perçages 86 débouchant chacun en amont dans la cavité d'un bossage 84 et en aval vers l'extérieur du second venturi, chaque perçage 86 étant aligné avec un orifice d'injection 80 de la couronne 74 et ayant un diamètre supérieur à celui d'un orifice d'injection 80, afin de déplacer la zone de cokéfaction des gouttes de carburant vers les perçages 86 de la chambre annulaire 78.The downstream wall 76 of the annular chamber 78 comprises ( figure 3 ) bores 86 each opening upstream in the cavity of a boss 84 and downstream to the outside of the second venturi, each bore 86 being aligned with an injection port 80 of the ring 74 and having a diameter greater than that of an injection orifice 80, in order to move the coking zone of the drops of fuel towards the bores 86 of the annular chamber 78.

Les tétons 82 ont une forme sensiblement cylindrique et sont brasés à l'intérieur des cavités des bossages 84 afin d'assurer l'étanchéité entre le circuit pilote et le circuit multipoint. Il est possible de vérifier la bonne réalisation du brassage par contrôle visuel à travers les perçages 86 de la paroi aval 76 de la chambre annulaire 78 du fait que ces perçages 86 ont un diamètre supérieur à celui des orifices d'injection 80.The pins 82 have a substantially cylindrical shape and are brazed inside the cavities of the bosses 84 to seal between the driver circuit and the multipoint circuit. It is possible to check the good performance of the stirring by visual inspection through the holes 86 of the downstream wall 76 of the annular chamber 78 because these holes 86 have a diameter greater than that of the injection orifices 80.

La périphérie radialement externe de la face frontale 72 de la couronne 74 s'étend radialement à l'extérieur de sa paroi cylindrique externe 90 et est en appui radial sur la paroi cylindrique externe 92 de la chambre annulaire 78 afin de centrer la couronne 74 dans la chambre annulaire 78. La périphérie radialement interne de la face frontale 72 comprend un rebord annulaire 94 s'étendant en aval de la face frontale 72 et dans le prolongement de la paroi cylindrique interne 96. L'extrémité aval de ce rebord annulaire 94 forme un passage annulaire de carburant entre le canal annulaire interne 44 et la cavité annulaire frontale 70.The radially outer periphery of the end face 72 of the ring 74 extends radially outside its outer cylindrical wall 90 and bears radially on the outer cylindrical wall 92 of the annular chamber 78 so as to center the ring 74 in the annular chamber 78. The radially inner periphery of the end face 72 comprises an annular flange 94 extending downstream of the end face 72 and in the extension of the internal cylindrical wall 96. The downstream end this annular flange 94 forms an annular fuel passage between the inner annular channel 44 and the front annular cavity 70.

Le dispositif selon l'invention comprend également un circuit de refroidissement formé d'un canal annulaire interne 44 délimité par les parois cylindriques internes 96, 97 de la couronne 74 et de la chambre annulaire 78 et d'un canal annulaire externe 46 délimité par les parois cylindriques externes 90, 92 de la couronne 74 et de la chambre annulaire 78.The device according to the invention also comprises a cooling circuit formed by an internal annular channel 44 delimited by the internal cylindrical walls 96, 97 of the ring 74 and the annular chamber 78 and an external annular channel 46 delimited by the outer cylindrical walls 90, 92 of the crown 74 and the annular chamber 78.

Dans cette réalisation, le canal annulaire externe 46 est isolé de la cavité frontale par la périphérie radialement externe de la face frontale 72 de la couronne 74 laquelle peut être brasée ou non sur la paroi cylindrique externe 92 de la chambre annulaire 78 de manière à réaliser ou non une liaison étanche.In this embodiment, the outer annular channel 46 is isolated from the front cavity by the radially outer periphery of the end face 72 of the ring 74 which can be brazed or not on the outer cylindrical wall 92 of the annular chamber 78 so as to achieve or not a tight connection.

Dans une variante de réalisation de l'invention représentée aux figures 7 à 9, le dispositif comprend une pluralité de pions 98 de centrage de la couronne 100 dans la chambre annulaire 102, ces pions 98 étant régulièrement répartis autour de la couronne 100 et montés axialement dans des trous 101 de la paroi frontale 104 de la couronne 100 et dans des trous 103 correspondants de la chambre annulaire 102. Les faces amont et aval des pions sont sensiblement parallèles aux parois tronconiques 104, 106 de la couronne 100 et de la chambre annulaire 102. La dimension axiale de chaque pion est telle que ses faces amont et aval sont alignées avec la face amont de la paroi frontale 104 de la couronne 100 et avec la face aval de la paroi aval 106 de la chambre annulaire 102, respectivement.In an alternative embodiment of the invention shown in Figures 7 to 9 , the device comprises a plurality of pins 96 for centering the ring gear 100 in the annular chamber 102, these pins 98 being regularly distributed around the ring gear 100 and mounted axially in holes 101 in the front wall 104 of the ring gear 100 and in corresponding holes 103 in the annular chamber 102. The upstream and downstream faces of the pins are substantially parallel to the frustoconical walls 104, 106 of the ring gear 100 and of the annular chamber 102. The axial dimension of each pin is such that its upstream faces and downstream are aligned with the upstream face of the front wall 104 of the ring 100 and with the downstream face of the downstream wall 106 of the annular chamber 102, respectively.

Chaque pion 98 comprend un orifice d'injection 108 formé d'un premier perçage 110 débouchant en amont à l'intérieur de la couronne annulaire 100 et en aval dans un second perçage 112 de plus grand diamètre lequel débouche vers l'extérieur du second venturi 14. Les perçages 110, 112 sont alignés selon une droite perpendiculaire aux parois aval tronconiques 104, 106 de la couronne 100 et de la chambre annulaire 102.Each pin 98 comprises an injection orifice 108 formed of a first bore 110 opening upstream inside the annular ring 100 and downstream in a second hole 112 of larger diameter which opens outwards from the second venturi 14. The holes 110, 112 are aligned along a straight line perpendicular to the walls frustoconical downstream 104, 106 of the crown 100 and the annular chamber 102.

Comme dans la réalisation précédemment décrite, le diamètre plus grand des perçages 112 de la chambre annulaire par rapport aux diamètres des orifices d'injection 110 permet de limiter la cokéfaction des orifices d'injection 110.As in the embodiment described above, the larger diameter of the holes 112 of the annular chamber with respect to the diameters of the injection orifices 110 makes it possible to limit the coking of the injection orifices 110.

Les périphéries radialement interne et externe de la paroi frontale 104 de la couronne 100 comprennent chacune un rebord annulaire interne 114 et externe 116, s'étendant en aval de la paroi frontale 104 et dans le prolongement des parois cylindriques interne 118 et externe 120, respectivement. Le rebord annulaire interne 114 est en contact avec la paroi aval 106 de la chambre 102 afin de réaliser une butée de positionnement axial de la couronne 100 dans la chambre annulaire 102 tandis que le rebord annulaire externe 116 définit avec la paroi frontale 106 de la chambre 102 un passage annulaire de communication entre la cavité annulaire externe 46 du circuit pilote et la cavité frontale 70 d'isolation thermique.The radially inner and outer peripheries of the front wall 104 of the ring gear 100 each comprise an inner and outer annular rim 114, extending downstream of the end wall 104 and in the extension of the inner cylindrical 118 and outer 120, respectively . The inner annular flange 114 is in contact with the downstream wall 106 of the chamber 102 to provide an axial positioning stop of the ring gear 100 in the annular chamber 102 while the outer annular flange 116 defines with the front wall 106 of the chamber 102 an annular passage of communication between the outer annular cavity 46 of the pilot circuit and the front cavity 70 of thermal insulation.

L'assemblage de la couronne 100, de la chambre 102 et des pions 98 est réalisé de la manière suivante : la couronne annulaire 100 est montée en butée axiale à l'intérieur de la chambre annulaire 102 grâce au rebord annulaire interne 114 de la couronne 100 et orientée angulairement de manière à ce que les trous 101 de la couronne 100 soient alignés avec les trous 103 de la chambre annulaire 102. Les pions de centrage 98 sont ensuite montés dans les trous 101, 103 de la couronne 100 et de la chambre 102 et on réalise une opération de brasage de pions 98 dans ces trous, pour réaliser une étanchéité entre le circuit pilote et le circuit multipoint. Les faces amont et aval des pions 98 sont reprises en usinage. Enfin, les perçages 110, 112 sont formés dans chacun des pions 98, cette opération étant réalisée après les opérations de brasage et d'usinage pour éviter une obturation partielle des perçages 110, 112 des pions 98.The assembly of the ring gear 100, the chamber 102 and the pins 98 is made in the following manner: the annular ring 100 is mounted in axial abutment inside the annular chamber 102 by virtue of the internal annular flange 114 of the ring 100 and oriented angularly so that the holes 101 of the ring 100 are aligned with the holes 103 of the annular chamber 102. The centering pins 98 are then mounted in the holes 101, 103 of the ring 100 and the chamber 102 and a soldering operation of pins 98 in these holes, for sealing between the pilot circuit and the multipoint circuit. The upstream and downstream faces of the pins 98 are machined again. Finally, the bores 110, 112 are formed in each of the pins 98, this operation being performed after the soldering and machining operations to avoid a partial closure of the holes 110, 112 of the pins 98.

Cette configuration avec des pions de centrage s'avère particulièrement intéressante dans les configurations d'injecteurs multipoint où l'encombrement à l'intérieur de la chambre est réduit et ne permet pas de réaliser des tétons et bossages.This configuration with centering pins is particularly interesting in multipoint nozzle configurations where the space inside the chamber is reduced and does not allow to make nipples and bosses.

Dans les réalisations décrites ci-dessus, le cavité annulaire frontale est en communication avec l'un des canaux interne (figure 4) ou externe (figure 8) du circuit de refroidissement afin d'alimenter la cavité annulaire frontale 70 en carburant lors du fonctionnement de la turbomachine. Dans ces configurations, le carburant présent à l'intérieur de la cavité frontale va cokéfier sous l'effet du rayonnement thermique, formant ainsi un isolant thermique protégeant la couronne annulaire multipoint.In the embodiments described above, the front annular cavity is in communication with one of the internal channels ( figure 4 ) or external ( figure 8 ) of the cooling circuit to supply the front annular cavity 70 with fuel during operation of the turbomachine. In these configurations, the fuel present inside the front cavity will coke under the effect of thermal radiation, thus forming a thermal insulation protecting the multipoint annular ring.

Dans d'autres réalisations non représentées aux dessins, il est possible d'isoler la cavité frontale 70 des canaux annulaire interne 44 et externe 46, celle-ci étant alors remplie d'air formant un isolant thermique de la face frontale 72 de la couronne annulaire 74, 100.In other embodiments not shown in the drawings, it is possible to isolate the front cavity 70 of the inner annular channel 44 and outer channel 46, which is then filled with air forming a thermal insulation of the front face 72 of the crown. ring 74, 100.

Claims (11)

  1. A fuel injector device for an annular combustion chamber of a turbine engine, the device comprising a pilot circuit continuously feeding an injector (16) leading into a first venturi (12) and a multipoint circuit intermittently feeding injection orifices (80, 110) and an annular chamber (78, 102) formed at the upstream end of a second venturi (14) coaxially surrounding the first venturi (12), the device being characterized in that the injection orifices (80, 110) are formed in a front face (72, 104) of an annular ring (74, 100) mounted in the annular chamber (78, 102) and in that the device includes thermal insulation means for insulating the front face (72, 104) of the annular ring (74, 100), said means comprising an annular cavity (70) formed around the injection orifices (80, 100) between the front face (72, 104) of the annular ring and a front wall (76, 106) of the annular chamber (78, 102) and being designed to be filled in operation with air or with coked fuel.
  2. A device according to claim 1, characterized in that it also includes a cooling circuit for cooling the annular ring (74, 100) by causing the fuel of the pilot circuit to flow in an inner annular channel (44) formed between inner cylindrical walls (96, 118, 97) of the ring (74, 100) and of the annular chamber (78, 102), and in an outer annular channel (46) formed between outer cylindrical walls (90, 120, 92) of the ring (74, 100) and of the annular chamber (78, 102).
  3. A device according to claim 2, characterized in that one of the inner and outer channels (44, 46) communicates with the above-mentioned annular cavity (70), the other one of the inner and outer channels (44, 46) being isolated from said cavity (70).
  4. A device according to claim 3, characterized in that the radially inner or outer periphery of the front face (72, 104) of the annular ring (74, 100) includes an annular rim (94) having a downstream edge that cooperates with the front wall (76) of the chamber (78, 102) to define an annular passage for communication between the above-mentioned annular cavity (70) and one of the inner and outer channels (44, 46) of the cooling circuit.
  5. A device according to any one of claims 2 to 4, characterized in that the radially outer periphery of the front face (72) of the ring (74) bears radially against the outer cylindrical wall (92) of the chamber (78) in order to center the ring (74) in the chamber (78).
  6. A device according to any one of claims 1 to 5, characterized in that each injection orifice (80) in the ring (74) is formed in a stud (82) projecting from the front face (72) of the ring (74), these studs (82) being inserted into abutment in respective cavities of corresponding projections (84) formed on the front face (76) of the annular chamber (78).
  7. A device according to claim 6, characterized in that each cavity in a projection (84) leads to the outside of the annular chamber (78) via a hole (86) in alignment with the injection orifice (80) of the corresponding stud (82), the hole (86) having a diameter that is greater than the diameter of the injection orifice (80).
  8. A device according to any one of claims 1 to 5, characterized in that the injection orifices (108) are formed in cylindrical pins (98) fastened in holes in the front face (104) of the annular ring (100), the pins (98) projecting beyond said front face and forming positioning and centering means in the annular chamber (102).
  9. A device according to claim 8, characterized in that the injection orifice (108) in each pin (98) has a downstream end of greater diameter.
  10. A device according to claim 8 or claim 9, characterized in that the radially inner end of the front face (104) of the ring (100) includes an annular rim (114) for axial positioning in the annular chamber (102).
  11. An annular combustion chamber for a turbine engine, the combustion chamber being characterized in that it includes at least one fuel injector device (68) according to any preceding claim.
EP10778699.8A 2009-10-13 2010-10-06 Multipoint injection device for a combustion chamber of a turbine engine Active EP2488791B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0904906A FR2951245B1 (en) 2009-10-13 2009-10-13 MULTI-POINT INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
PCT/FR2010/052101 WO2011045503A1 (en) 2009-10-13 2010-10-06 Multipoint injection device for a combustion chamber of a turbine engine

Publications (2)

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EP2488791A1 EP2488791A1 (en) 2012-08-22
EP2488791B1 true EP2488791B1 (en) 2014-08-06

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EP10778699.8A Active EP2488791B1 (en) 2009-10-13 2010-10-06 Multipoint injection device for a combustion chamber of a turbine engine

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US (1) US9003802B2 (en)
EP (1) EP2488791B1 (en)
JP (1) JP5616456B2 (en)
CN (1) CN102575843B (en)
BR (1) BR112012008509B1 (en)
CA (1) CA2776848C (en)
FR (1) FR2951245B1 (en)
RU (1) RU2539223C2 (en)
WO (1) WO2011045503A1 (en)

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US10859269B2 (en) 2017-03-31 2020-12-08 Delavan Inc. Fuel injectors for multipoint arrays
CN107238106B (en) * 2017-06-10 2020-01-24 北京航空航天大学 Multilayer annular oil rail for multi-point injection combustion chamber
US10989118B2 (en) 2017-12-20 2021-04-27 Wrightspeed, Inc. Controlled evaporation and heating of fuels for turbine engines
FR3084449B1 (en) * 2018-07-25 2020-07-17 Safran Aircraft Engines MULTI-POINT FUEL INJECTION DEVICE
GB201909167D0 (en) 2019-06-26 2019-08-07 Rolls Royce Plc Fuel injector
FR3099546B1 (en) 2019-07-29 2021-08-06 Safran Aircraft Engines COMBUSTION CHAMBER CONTAINING SECONDARY INJECTION SYSTEMS INJECTING AIR AND FUEL DIRECTLY INTO CORNER RECIRCULATION ZONES, TURBOMACHINE INCLUDING IT, AND METHOD OF SUPPLYING FUEL THEREOF
FR3115075B1 (en) * 2020-10-14 2022-10-21 Safran Aircraft Engines FUEL SUPPLY CIRCUIT FOR A TURBOMACHINE COMBUSTION CHAMBER

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RU2539223C2 (en) 2015-01-20
CN102575843B (en) 2014-12-24
BR112012008509A2 (en) 2016-04-05
JP5616456B2 (en) 2014-10-29
CA2776848A1 (en) 2011-04-21
US9003802B2 (en) 2015-04-14
JP2013507600A (en) 2013-03-04
US20120198853A1 (en) 2012-08-09
RU2012119598A (en) 2013-11-20
CN102575843A (en) 2012-07-11
BR112012008509B1 (en) 2020-09-29
EP2488791A1 (en) 2012-08-22
CA2776848C (en) 2017-07-04
FR2951245A1 (en) 2011-04-15
WO2011045503A1 (en) 2011-04-21
FR2951245B1 (en) 2013-05-17

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