EP1278012A2 - Aeromechanical injection system with non-return primary swirler - Google Patents

Aeromechanical injection system with non-return primary swirler Download PDF

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Publication number
EP1278012A2
EP1278012A2 EP02291767A EP02291767A EP1278012A2 EP 1278012 A2 EP1278012 A2 EP 1278012A2 EP 02291767 A EP02291767 A EP 02291767A EP 02291767 A EP02291767 A EP 02291767A EP 1278012 A2 EP1278012 A2 EP 1278012A2
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EP
European Patent Office
Prior art keywords
fuel
injection nozzle
injection
combustion chamber
injection system
Prior art date
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Granted
Application number
EP02291767A
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German (de)
French (fr)
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EP1278012B1 (en
EP1278012A3 (en
Inventor
Christophe Baudoin
Patrice-André Commaret
Christophe Viguier
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • the present invention relates to the specific field of turbomachines and is particularly interested in the problem posed by injecting fuel into the combustion chamber of a turbomachine.
  • fuel injection into the chamber of combustion 50 is carried out from several injection systems 52 each comprising, on the one hand, a fuel injection nozzle 54 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 56 which produces the combustion / fuel mixture and diffuses it into this combustion chamber.
  • This mixer / baffle assembly includes a first swirl device or primary swirler (swirler 58) mounted sliding on the fuel injection nozzle 54 (via a sleeve 60), a venturi device 62, a second vortex or secondary spin device 64 and a deflector 66 fixed on the bottom of the combustion chamber 68.
  • This conventional injection system architecture however has the major disadvantage of presenting, under certain particular conditions of use, a risk of self-ignition likely to cause destruction of the combustion chamber. Indeed, the impact of fuel on the internal surface venturi, necessary to obtain a film of fuel whose fragmentation into fine droplets will be ensured by the shears generated by the primary tendrils and secondary, sometimes results in fuel lift in the bladders of the primary spin. Moreover, because the impact zone of the fuel on this internal surface is not precisely localized, a fuel injection to countercurrent in this primary swirl may also possibly occur. However, such a return of fuel in the primary swirler can help to bring this fuel on the outside of the flame tube and thus risk destroying the fire of the combustion chamber of the turbomachine.
  • the present invention overcomes these disadvantages by proposing a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand a mixer / deflector assembly disposed coaxially with said nozzle of injection and which carries out the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly having a first vortex device (or primary swirler) and at least one second device with a vortex (or secondary swirl) arranged axially at a determined distance from each other and separated by a venturi device arranged coaxially with said injection nozzle, characterized in that said first vortex device is attached integrally with said injection nozzle and separated therefrom by a radial distance constant, determined so that the fuel vaporized by said nozzle injection device can not in any way impact on said first device whirlwind.
  • a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand
  • the second vortex device is slidably mounted by relative to said injection nozzle via a fixed crown of said second vortex device and which can move, perpendicular to a axis of revolution of said injection nozzle, in an annular housing of said Venturi device.
  • this venturi device comprises an inner surface having on an upstream portion a slope discontinuity.
  • This upstream part of the internal surface of the venturi device may comprise a concave step or a convex step.
  • the annular combustion chamber is formed of an outer axial wall 24 and an inner axial wall 26, both coaxial axis 10, and a wall transverse 28 forming chamber bottom and provided with a plurality of openings 30 for fixing the injection systems.
  • the different links between upstream ends of the axial walls of the chamber 24, 26, optionally caps 32, 34 extending upstream these ends of walls, and ends folded from the bottom chamber 28 is performed by any means of attachment conventional (not shown), for example screw bolts with conical head, preferably of prison nut type.
  • Each injection system of the injection assembly comprises on the one hand a fuel injection nozzle 36 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 38 coaxial with this injection nozzle and which produces the fuel / fuel mixture and the diffuses into this combustion chamber.
  • This mixer / baffle assembly has at least one first vortex or swirl device (swirler 40) and a second secondary vortex or swirl device 42 spaced axially from each other by a determined distance and separated by a venturi device 44.
  • the secondary swirler is extended by a deflector 46 fixed to the chamber bottom 28 and which extends through the opening 30 in the combustion chamber 22.
  • the primary swirler 40 is fixed integrally to the nozzle injection device 36, for example by means of a sleeve 48, and of which it is therefore separated by a constant radial distance. This distance is determined from such that, irrespective of the operating conditions of the turbomachine (autorotation, idle, full throttle), the fuel vaporized by the injection nozzle can in no way impact the primary swirler.
  • the turbomachine autorotation, idle, full throttle
  • the fuel vaporized by the injection nozzle can in no way impact the primary swirler.
  • venturi device further comprises on its inner surface 44A an upstream portion P with a slope discontinuity so as to prevent, or at the very least, significantly reduce any risk of fuel rising by capillarity in the primary swirl 40 of the injection system 20.
  • This discontinuity of slope carried out upstream of the outer surface E of the fuel injection cone may example be constituted by a concave step.
  • this discontinuity of slope is instead constituted by a step convex.
  • the secondary spin 42 is slidably mounted relative to this injection nozzle, perpendicular to a axis of revolution S of the nozzle, for example by means of a ring 47 fixed on this secondary swirler and able to move in an annular housing 49 of the venturi device 44.
  • sufficient clearance is left between the inner periphery of this annular housing and the outer periphery of the crowned.
  • the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any fuel injection against the current, and the discontinuity of slope of this venturi also makes it possible to avoid any fuel capillarity.
  • the particular structure of the invention ensures a good spraying fuel in all flight conditions and in particular in the most severe conditions for re-ignition in low autorotation Mach, conditions under which the air supply pressure drops are too small to guarantee sufficient fragmentation of the fuel and thus access a vast re-ignition domain.

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

Abstract

Système d'injection d'une chambre de combustion de turbomachine comportant une buse d'injection de carburant assurant la vaporisation du carburant dans la chambre de combustion et un ensemble mélangeur/déflecteur coaxial à cette buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans la chambre de combustion, cet ensemble mélangeur/déflecteur comportant une vrille primaire (40) et une vrille secondaire (42) disposés axialement à une distance déterminée l'un de l'autre et séparés par un dispositif à venturi (44) disposé coaxialement à la buse d'injection, la vrille primaire étant fixée solidairement à la buse d'injection et séparée de celle-ci d'une distance radiale constante, déterminée de telle sorte que le carburant vaporisé par la buse d'injection ne peut en aucune façon impacter sur la vrille primaire. De préférence, le dispositif à venturi comporte une surface interne (44A) présentant sur une partie amont une discontinuité de pente P. <IMAGE>Injection system of a turbomachine combustion chamber comprising a fuel injection nozzle for vaporizing the fuel in the combustion chamber and a mixer / deflector assembly coaxial with this injection nozzle and which carries out the combustion / fuel and diffuses it into the combustion chamber, this mixing / deflecting assembly comprising a primary swirler (40) and a secondary swirler (42) arranged axially at a determined distance from one another and separated by a venturi device ( 44) disposed coaxially with the injection nozzle, the primary swirler being integrally fixed to the injection nozzle and separated therefrom by a constant radial distance, determined so that the fuel vaporized by the injection nozzle can not in any way impact on the primary spin. Preferably, the venturi device comprises an inner surface (44A) presenting on an upstream part a slope discontinuity P. <IMAGE>

Description

Domaine de l'inventionField of the invention

La présente invention se rapporte au domaine spécifique des turbomachines et elle s'intéresse plus particulièrement au problème posé par l'injection de carburant dans la chambre de combustion d'une turbomachine.The present invention relates to the specific field of turbomachines and is particularly interested in the problem posed by injecting fuel into the combustion chamber of a turbomachine.

Art antérieurPrior art

Classiquement, dans un turboréacteur ou un turbopropulseur, comme l'illustre la figure 4, l'injection de carburant dans la chambre de combustion 50 est effectuée à partir de plusieurs systèmes d'injection 52 comportant chacun, d'une part une buse d'injection de carburant 54 assurant la vaporisation du carburant dans la chambre de combustion et d'autre part un ensemble mélangeur/déflecteur 56 qui réalise le mélange comburant/carburant et le diffuse dans cette chambre de combustion. Cet ensemble mélangeur/déflecteur comporte un premier dispositif à tourbillon ou vrille primaire (swirler 58) monté coulissant sur la buse d'injection de carburant 54 (via un manchon 60), un dispositif à venturi 62, un second dispositif à tourbillon ou vrille secondaire 64 et un déflecteur 66 fixé sur le fond de la chambre de combustion 68. La demande de brevet française N° 2 728 330 et le brevet américain N° 5 490 378 sont deux exemples parfaits de cet art antérieur. On notera que dans les tous systèmes d'injection divulgués à ce jour, comme l'illustre la figure 5, la surface interne du venturi 62A sur laquelle va impacter le carburant vaporisé par la buse d'injection 54 présente toujours une surface continue (sans discontinuité de pente) jusqu'à la sortie d'air de la vrille primaire.Conventionally, in a turbojet engine or a turboprop engine, as illustrated in Figure 4, fuel injection into the chamber of combustion 50 is carried out from several injection systems 52 each comprising, on the one hand, a fuel injection nozzle 54 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 56 which produces the combustion / fuel mixture and diffuses it into this combustion chamber. This mixer / baffle assembly includes a first swirl device or primary swirler (swirler 58) mounted sliding on the fuel injection nozzle 54 (via a sleeve 60), a venturi device 62, a second vortex or secondary spin device 64 and a deflector 66 fixed on the bottom of the combustion chamber 68. The request for French Patent No. 2,728,330 and US Patent No. 5,490,378 are two perfect examples of this prior art. Note that in all systems currently disclosed, as shown in Figure 5, the internal surface of the venturi 62A on which will impact the fuel vaporized by the injection nozzle 54 always has a continuous surface (without discontinuity of slope) until the air outlet of the primary swirler.

Cette architecture conventionnelle de système d'injection a toutefois l'inconvénient majeur de présenter, dans certaines conditions particulières d'utilisation, un risque d'auto-inflammation de nature à provoquer une destruction de la chambre de combustion. En effet, l'impact du carburant sur la surface interne du venturi, nécessaire pour obtenir un film de carburant dont la fragmentation en fines gouttelettes sera assurée par les cisaillements générés par les vrilles primaire et secondaire, se traduit parfois par des remontées de carburant dans les aubages de la vrille primaire. De plus, du fait que la zone d'impact du carburant sur cette surface interne n'est pas précisément localisée, une injection de carburant à contre-courant dans cette vrille primaire peut aussi éventuellement se produire. Or, un tel retour de carburant dans la vrille primaire peut contribuer à amener ce carburant à l'extérieur du tube à flamme et donc risquer une destruction du foyer de la chambre de combustion de la turbomachine.This conventional injection system architecture however has the major disadvantage of presenting, under certain particular conditions of use, a risk of self-ignition likely to cause destruction of the combustion chamber. Indeed, the impact of fuel on the internal surface venturi, necessary to obtain a film of fuel whose fragmentation into fine droplets will be ensured by the shears generated by the primary tendrils and secondary, sometimes results in fuel lift in the bladders of the primary spin. Moreover, because the impact zone of the fuel on this internal surface is not precisely localized, a fuel injection to countercurrent in this primary swirl may also possibly occur. However, such a return of fuel in the primary swirler can help to bring this fuel on the outside of the flame tube and thus risk destroying the fire of the combustion chamber of the turbomachine.

Objet et définition de l'inventionObject and definition of the invention

La présente invention pallie ces inconvénients en proposant un système d'injection de turbomachine comportant d'une part une buse d'injection de carburant assurant la vaporisation du carburant dans la chambre de combustion et d'autre part un ensemble mélangeur/déflecteur disposé coaxialement à ladite buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans ladite chambre de combustion, ledit ensemble mélangeur/déflecteur comportant un premier dispositif à tourbillon (ou vrille primaire) et au moins un second dispositif à tourbillon (ou vrille secondaire) disposés axialement à une distance déterminée l'un de l'autre et séparés par un dispositif à venturi disposé coaxialement à ladite buse d'injection, caractérisé en ce que ledit premier dispositif à tourbillon est fixé solidairement à ladite buse d'injection et séparé de celle-ci d'une distance radiale constante, déterminée de telle sorte que le carburant vaporisé par ladite buse d'injection ne peut en aucune façon impacter sur ledit premier dispositif à tourbillon.The present invention overcomes these disadvantages by proposing a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand a mixer / deflector assembly disposed coaxially with said nozzle of injection and which carries out the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly having a first vortex device (or primary swirler) and at least one second device with a vortex (or secondary swirl) arranged axially at a determined distance from each other and separated by a venturi device arranged coaxially with said injection nozzle, characterized in that said first vortex device is attached integrally with said injection nozzle and separated therefrom by a radial distance constant, determined so that the fuel vaporized by said nozzle injection device can not in any way impact on said first device whirlwind.

De préférence, le second dispositif à tourbillon est monté coulissant par rapport à ladite buse d'injection par l'intermédiaire d'une couronne solidaire dudit second dispositif à tourbillon et qui peut se déplacer, perpendiculairement à un axe de révolution de ladite buse d'injection, dans un logement annulaire dudit dispositif à venturi.Preferably, the second vortex device is slidably mounted by relative to said injection nozzle via a fixed crown of said second vortex device and which can move, perpendicular to a axis of revolution of said injection nozzle, in an annular housing of said Venturi device.

Avec ce système de liaison coulissante au niveau de la seule vrille secondaire, l'injection de carburant à contre-courant dans la vrille primaire est éliminée.With this sliding link system at the level of the single twist secondary, fuel injection against the current in the primary spin is eliminated.

Selon un mode de réalisation avantageux, ce dispositif à venturi comporte une surface interne présentant sur une partie amont une discontinuité de pente. Cette partie amont de la surface interne du dispositif à venturi peut comporter une marche concave ou une marche convexe. According to an advantageous embodiment, this venturi device comprises an inner surface having on an upstream portion a slope discontinuity. This upstream part of the internal surface of the venturi device may comprise a concave step or a convex step.

Avec cette architecture spécifique de venturi, l'injection de carburant par capillarité dans la vrille primaire peut être limitée.With this specific Venturi architecture, fuel injection by capillarity in the primary swirler can be limited.

Brève description des dessinsBrief description of the drawings

Les caractéristiques et avantages de la présente invention ressortiront mieux de la description suivante, faite à titre indicatif et non limitatif, en regard des dessins annexés sur lesquels :

  • la figure 1 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine conforme à l'invention,
  • la figure 2 est une vue agrandie d'une partie de la figure 1 dans un premier exemple de réalisation de l'invention,
  • la figure 3 est une vue agrandie d'une partie de la figure 1 dans un second exemple de réalisation de l'invention,
  • la figure 4 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un système d'injection de l'art antérieur, et
  • la figure 5 est une vue agrandie d'une partie de la figure 4.
The features and advantages of the present invention will emerge more clearly from the following description, given by way of non-limiting indication, with reference to the appended drawings in which:
  • FIG. 1 is a diagrammatic axial half-section view of an injection part of a turbomachine according to the invention,
  • FIG. 2 is an enlarged view of a portion of FIG. 1 in a first embodiment of the invention;
  • FIG. 3 is an enlarged view of part of FIG. 1 in a second embodiment of the invention;
  • FIG. 4 is a diagrammatic axial half-section view of an injection part of a turbomachine incorporating an injection system of the prior art, and
  • Figure 5 is an enlarged view of a portion of Figure 4.

Description détaillée d'un mode de réalisation préférentielDetailed description of a preferred embodiment

La figure 1 montre en demi-coupe axiale une partie d'injection d'une turbomachine comprenant :

  • une enveloppe annulaire externe (ou carter externe) 12, d'axe longitudinal 10,
  • une enveloppe annulaire interne (ou carter interne) coaxiale 14,
  • un espace annulaire 16 compris entre les deux enveloppes 12 et 14 recevant le comburant comprimé, généralement de l'air, provenant en amont d'un compresseur (non représenté) de la turbomachine, au travers d'un conduit annulaire de diffusion 18 (on notera la présence de la grille de diffusion 18a) définissant un flux général F d'écoulement des gaz, cet espace 16 comportant, dans le sens d'écoulement de ces gaz, tout d'abord un ensemble d'injection comportant une pluralité de systèmes d'injection 20 fixés sur l'enveloppe annulaire externe 12 et régulièrement répartis autour du conduit 18, ensuite une chambre de combustion annulaire 22, et enfin un distributeur annulaire (non représenté) formant un étage d'entrée d'une turbine haute pression.
FIG. 1 shows in axial half-section an injection part of a turbomachine comprising:
  • an outer annular casing (or outer casing) 12, of longitudinal axis 10,
  • an inner annular envelope (or inner casing) coaxial 14,
  • an annular space 16 between the two envelopes 12 and 14 receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular diffusion duct 18 (on note the presence of the diffusion gate 18a) defining a general flow F of gas flow, this space 16 having, in the direction of flow of these gases, first of all an injection assembly comprising a plurality of systems injection 20 fixed on the outer annular envelope 12 and regularly distributed around the conduit 18, then an annular combustion chamber 22, and finally an annular distributor (not shown) forming an inlet stage of a high pressure turbine.

La chambre de combustion annulaire est formée d'une paroi axiale externe 24 et d'une paroi axiale interne 26, toutes deux coaxiales d'axe 10, et d'une paroi transversale 28 formant fond de chambre et pourvue d'une pluralité d'ouvertures 30 pour la fixation des systèmes d'injection. Les différentes liaisons entre les extrémités amont des parois axiales de la chambre 24, 26, éventuellement des casquettes 32, 34 prolongeant en amont ces extrémités de parois, et des extrémités rabattues du fond de chambre 28 est effectuée par tout moyen de fixation conventionnel (non représenté), par exemple des boulons à vis à tête conique, de préférence de type à écrou prisonnier.The annular combustion chamber is formed of an outer axial wall 24 and an inner axial wall 26, both coaxial axis 10, and a wall transverse 28 forming chamber bottom and provided with a plurality of openings 30 for fixing the injection systems. The different links between upstream ends of the axial walls of the chamber 24, 26, optionally caps 32, 34 extending upstream these ends of walls, and ends folded from the bottom chamber 28 is performed by any means of attachment conventional (not shown), for example screw bolts with conical head, preferably of prison nut type.

Chaque système d'injection de l'ensemble d'injection comporte d'une part une buse d'injection de carburant 36 assurant la vaporisation du carburant dans la chambre de combustion et d'autre part un ensemble mélangeur/déflecteur 38 coaxial à cette buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans cette chambre de combustion. Cet ensemble mélangeur/déflecteur comporte au moins un premier dispositif à tourbillon ou vrille primaire (swirler 40) et un second dispositif à tourbillon ou vrille secondaire 42 espacés axialement l'un de l'autre d'une distance déterminée et séparés par un dispositif à venturi 44. La vrille secondaire est prolongée par un déflecteur 46 fixé au fond de chambre 28 et qui s'étend au travers de l'ouverture 30 dans la chambre de combustion 22.Each injection system of the injection assembly comprises on the one hand a fuel injection nozzle 36 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 38 coaxial with this injection nozzle and which produces the fuel / fuel mixture and the diffuses into this combustion chamber. This mixer / baffle assembly has at least one first vortex or swirl device (swirler 40) and a second secondary vortex or swirl device 42 spaced axially from each other by a determined distance and separated by a venturi device 44. The secondary swirler is extended by a deflector 46 fixed to the chamber bottom 28 and which extends through the opening 30 in the combustion chamber 22.

Selon l'invention, la vrille primaire 40 est fixée solidairement à la buse d'injection 36, par exemple par l'intermédiaire d'un manchon 48, et dont elle est donc séparée par une distance radiale constante. Cette distance est déterminée de telle sorte que, quels que soient les régimes de fonctionnement de la turbomachine (autorotation, ralenti, plein gaz), le carburant vaporisé par la buse d'injection ne peut en aucune façon impacter sur la vrille primaire. Ainsi, on peut éviter toute éventuelle injection à contre-courant de carburant dans cette vrille primaire résultant des dispersions de carburant existant naturellement d'un injecteur à l'autre (du fait des angles d'injection, de l'homogénéité circonférentielle, etc.) comme des rebonds de carburant sur le dispositif à venturi.According to the invention, the primary swirler 40 is fixed integrally to the nozzle injection device 36, for example by means of a sleeve 48, and of which it is therefore separated by a constant radial distance. This distance is determined from such that, irrespective of the operating conditions of the turbomachine (autorotation, idle, full throttle), the fuel vaporized by the injection nozzle can in no way impact the primary swirler. Thus, we can avoid any possible countercurrent injection of fuel into this primary swirler resulting from naturally occurring fuel dispersions from an injector to the other (due to injection angles, circumferential homogeneity, etc.) like fuel rebounds on the venturi device.

Selon un premier mode de réalisation de l'invention illustré à la figure 2, le dispositif à venturi comporte en outre sur sa surface interne 44A une partie amont présentant en P une discontinuité de pente de façon à empêcher, ou à tout le moins réduire notablement, tout risque de remontée du carburant par capillarité dans la vrille primaire 40 du système d'injection 20. Cette discontinuité de pente effectuée en amont de la surface externe E du cône d'injection de carburant peut par exemple être constituée par une marche concave. Sur l'exemple de réalisation de la figure 3, cette discontinuité de pente est au contraire constituée par une marche convexe.According to a first embodiment of the invention illustrated in FIG. venturi device further comprises on its inner surface 44A an upstream portion P with a slope discontinuity so as to prevent, or at the very least, significantly reduce any risk of fuel rising by capillarity in the primary swirl 40 of the injection system 20. This discontinuity of slope carried out upstream of the outer surface E of the fuel injection cone may example be constituted by a concave step. On the exemplary embodiment of FIG. 3, this discontinuity of slope is instead constituted by a step convex.

En outre, afin de laisser un débattement suffisant entre la buse d'injection 36 solidaire de l'enveloppe externe 12 et l'ensemble mélangeur/déflecteur 38 (notamment pour la gestion des dilatations thermiques), la vrille secondaire 42 est montée coulissante par rapport à cette buse d'injection, perpendiculairement à un axe de révolution S de la buse, par exemple par l'intermédiaire d'une couronne 47 fixée sur cette vrille secondaire et pouvant se déplacer dans un logement annulaire 49 du dispositif à venturi 44. A cet effet, un jeu suffisant est laissé entre la périphérie interne de ce logement annulaire et la périphérie externe de la couronne.In addition, to allow sufficient clearance between the injection nozzle 36 secured to the outer casing 12 and the mixer / deflector assembly 38 (especially for the management of thermal expansions), the secondary spin 42 is slidably mounted relative to this injection nozzle, perpendicular to a axis of revolution S of the nozzle, for example by means of a ring 47 fixed on this secondary swirler and able to move in an annular housing 49 of the venturi device 44. For this purpose, sufficient clearance is left between the inner periphery of this annular housing and the outer periphery of the crowned.

Avec la configuration de liaison coulissante proposée, la buse d'injection est constamment centrée par rapport à la vrille primaire et le dispositif à venturi évitant ainsi toute injection de carburant à contre-courant, et la discontinuité de pente de ce venturi permet en outre d'éviter toute remontée de carburant par capillarité. Ainsi, avec la structure particulière de l'invention, on assure une bonne pulvérisation du carburant dans toutes les conditions de vol et notamment dans les conditions particulières les plus sévères de rallumage en autorotation à faible Mach, conditions dans lesquelles les pertes de charge d'alimentation en air sont trop faibles pour garantir une fragmentation suffisante du carburant et ainsi accéder à un vaste domaine de rallumage.With the proposed sliding link configuration, the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any fuel injection against the current, and the discontinuity of slope of this venturi also makes it possible to avoid any fuel capillarity. Thus, with the particular structure of the invention, it ensures a good spraying fuel in all flight conditions and in particular in the most severe conditions for re-ignition in low autorotation Mach, conditions under which the air supply pressure drops are too small to guarantee sufficient fragmentation of the fuel and thus access a vast re-ignition domain.

Claims (5)

Système d'injection d'une chambre de combustion de turbomachine comportant d'une part une buse d'injection de carburant (36) assurant la vaporisation du carburant dans la chambre de combustion (22) et d'autre part un ensemble mélangeur/déflecteur (38) disposé coaxialement à ladite buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans ladite chambre de combustion, ledit ensemble mélangeur/déflecteur comportant un premier dispositif à tourbillon (ou vrille primaire 40) et au moins un second dispositif à tourbillon (ou vrille secondaire 42) disposés axialement à une distance déterminée l'un de l'autre et séparés par un dispositif à venturi (44) disposé coaxialement à ladite buse d'injection, caractérisé en ce que ledit premier dispositif à tourbillon est fixé solidairement à ladite buse d'injection et séparé de celle-ci d'une distance radiale constante, déterminée de telle sorte que le carburant vaporisé par ladite buse d'injection ne peut en aucune façon impacter sur ledit premier dispositif à tourbillon.Injection system of a turbomachine combustion chamber comprising on the one hand a fuel injection nozzle (36) for vaporizing the fuel in the combustion chamber (22) and on the other hand a mixer / deflector assembly (38) disposed coaxially with said injection nozzle and which carries the fuel / fuel mixture and diffuses it into said combustion chamber, said mixer / baffle assembly including a first vortex device (or primary swirler 40) and at least a second vortex device (or secondary swirler 42) arranged axially at a determined distance from each other and separated by a venturi device (44) disposed coaxially with said injection nozzle, characterized in that said first vortex device is fixedly secured to said injection nozzle and separated therefrom by a constant radial distance, determined so that the fuel vaporized by said injection nozzle can not in any way impact on said first vortex device. Système d'injection selon la revendication 1, caractérisé en ce que ledit second dispositif à tourbillon est monté coulissant par rapport à ladite buse d'injection par l'intermédiaire d'une couronne (47) solidaire dudit second dispositif à tourbillon et qui peut se déplacer, perpendiculairement à un axe de révolution S de ladite buse d'injection, dans un logement annulaire (49) dudit dispositif à venturi.Injection system according to claim 1, characterized in that said second vortex device is slidably mounted relative to said injection nozzle via a ring (47) integral with said second vortex device and which can be moving, perpendicularly to an axis of revolution S of said injection nozzle, in an annular housing (49) of said venturi device. Système d'injection selon la revendication 1, caractérisé en ce que ledit dispositif à venturi comporte une surface interne (44A) présentant sur une partie amont une discontinuité de pente P.Injection system according to claim 1, characterized in that said venturi device comprises an inner surface (44A) presenting on an upstream part a discontinuity of slope P. Système d'injection selon la revendication 3, caractérisé en ce que ladite partie amont de la surface interne du dispositif à venturi comporte une marche concave.Injection system according to claim 3, characterized in that said upstream portion of the inner surface of the venturi device comprises a concave step. Système d'injection selon la revendication 3, caractérisé en ce que ladite partie amont de la surface interne du dispositif à venturi comporte une marche convexe.Injection system according to claim 3, characterized in that said upstream portion of the inner surface of the venturi device comprises a convex step.
EP02291767A 2001-07-16 2002-07-12 Aeromechanical injection system with non-return primary swirler Expired - Lifetime EP1278012B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0109456A FR2827367B1 (en) 2001-07-16 2001-07-16 AEROMECHANICAL INJECTION SYSTEM WITH ANTI-RETURN PRIMARY LOCK
FR0109456 2001-07-16

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EP1278012A2 true EP1278012A2 (en) 2003-01-22
EP1278012A3 EP1278012A3 (en) 2003-11-19
EP1278012B1 EP1278012B1 (en) 2006-10-25

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EP (1) EP1278012B1 (en)
JP (1) JP4066241B2 (en)
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CA (1) CA2393082C (en)
DE (1) DE60215589T2 (en)
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Also Published As

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RU2295645C2 (en) 2007-03-20
CN1407280A (en) 2003-04-02
CA2393082A1 (en) 2003-01-16
RU2002118252A (en) 2004-02-10
US6959551B2 (en) 2005-11-01
CN1230650C (en) 2005-12-07
UA76709C2 (en) 2006-09-15
FR2827367A1 (en) 2003-01-17
JP2003042452A (en) 2003-02-13
EP1278012B1 (en) 2006-10-25
US20030010034A1 (en) 2003-01-16
JP4066241B2 (en) 2008-03-26
DE60215589T2 (en) 2007-08-30
DE60215589D1 (en) 2006-12-07
ES2272650T3 (en) 2007-05-01
FR2827367B1 (en) 2003-10-17
EP1278012A3 (en) 2003-11-19
CA2393082C (en) 2010-10-19

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