EP3227612B1 - Air intake ring for turbo machine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring - Google Patents

Air intake ring for turbo machine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring Download PDF

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Publication number
EP3227612B1
EP3227612B1 EP15817462.3A EP15817462A EP3227612B1 EP 3227612 B1 EP3227612 B1 EP 3227612B1 EP 15817462 A EP15817462 A EP 15817462A EP 3227612 B1 EP3227612 B1 EP 3227612B1
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Prior art keywords
air intake
intake ring
internal profile
injection system
combustion chamber
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EP15817462.3A
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German (de)
French (fr)
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EP3227612A1 (en
Inventor
Yoann Mery
Alain René CAYRE
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Safran Aircraft Engines SAS
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Safran Aircraft Engines 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—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
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers

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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

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention se rapporte au domaine des turbomachines pour aéronef et concerne plus particulièrement une couronne d'admission d'air destinée à faire partie d'un système d'injection de carburant et d'air dans une chambre de combustion au sein d'une turbomachine.The present invention relates to the field of aircraft turbomachines and more particularly relates to an air intake ring intended to be part of a fuel injection system and air in a combustion chamber within a combustion chamber. turbine engine.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

La figure 1 annexée illustre une turbomachine 10 pour aéronef d'un type connu, par exemple un turboréacteur à double flux, comportant de manière générale une soufflante 12 destinée à l'aspiration d'un flux d'air se divisant en aval de la soufflante en un flux primaire alimentant un coeur de la turbomachine et un flux secondaire contournant ce coeur. Le coeur de la turbomachine comporte, de manière générale, un compresseur basse pression 14, un compresseur haute pression 16, une chambre de combustion 18, une turbine haute pression 20 et une turbine basse pression 22. La turbomachine est carénée par une nacelle 24 entourant l'espace d'écoulement 26 du flux secondaire. Les rotors de la turbomachine sont montés rotatifs autour d'un axe longitudinal 28 de la turbomachine.The figure 1 annexed illustrates a turbine engine 10 for an aircraft of a known type, for example a turbofan engine, generally comprising a fan 12 intended for the suction of an air flow dividing downstream of the fan into a flow primary supplying a core of the turbomachine and a secondary flow bypassing this heart. The core of the turbomachine comprises, in general, a low-pressure compressor 14, a high-pressure compressor 16, a combustion chamber 18, a high-pressure turbine 20 and a low-pressure turbine 22. The turbine engine is streamlined by a nacelle 24 surrounding the flow space 26 of the secondary flow. The rotors of the turbomachine are rotatably mounted about a longitudinal axis 28 of the turbomachine.

La figure 2 représente la chambre de combustion 18 de la turbomachine de la figure 1. De manière classique, cette chambre de combustion, qui est de type annulaire, comprend deux parois annulaires coaxiales, respectivement radialement interne 32 et radialement externe 34, qui s'étendent de l'amont vers l'aval, selon le sens 36 d'écoulement du flux primaire de gaz dans la turbomachine, autour de l'axe de la chambre de combustion qui se confond avec l'axe 28 de la turbomachine. Ces parois annulaires interne 32 et externe 34 sont reliées entre elles à leur extrémité amont par une paroi annulaire de fond de chambre 40 qui s'étend sensiblement radialement autour de l'axe 28. Cette paroi annulaire de fond de chambre 40 est équipée de systèmes d'injection 42 répartis autour de l'axe 28 pour permettre l'injection d'un pré-mélange d'air et de carburant centré selon un axe d'injection 44.The figure 2 represents the combustion chamber 18 of the turbomachine of the figure 1 . Typically, this combustion chamber, which is of annular type, comprises two coaxial annular walls, respectively radially inner 32 and radially outer 34, which extend from upstream to downstream, in the direction of flow 36 the primary flow of gas in the turbomachine, around the axis of the combustion chamber which merges with the axis 28 of the turbomachine. These inner and outer annular walls 32 are interconnected at their upstream end by an annular bottom wall of chamber 40 which extends substantially radially about the axis 28. This annular bottom wall of chamber 40 is equipped with injection systems 42 distributed around the axis 28 to allow the injection of a premix of air and fuel centered along an injection axis 44.

En fonctionnement, une partie 46 d'un flux d'air 48 provenant du compresseur 16 alimente les systèmes d'injection 42 tandis qu'une autre partie 50 de ce flux d'air contourne la chambre de combustion en s'écoulant vers l'aval le long des parois coaxiales 32 et 34 de cette chambre et permet notamment l'alimentation d'orifices d'air prévus au sein de ces parois 32 et 34.In operation, a portion 46 of an air flow 48 coming from the compressor 16 feeds the injection systems 42 while another part 50 of this air flow bypasses the combustion chamber while flowing towards the downstream along the coaxial walls 32 and 34 of this chamber and allows in particular the supply of air openings provided within these walls 32 and 34.

La figure 3 est une vue en demi-coupe axiale de l'un des systèmes d'injection 42. Celui-ci comporte, de manière générale, une tête 52 d'un injecteur de carburant, une douille 54, parfois dénommée « traversée coulissante », dans laquelle la tête 52 de l'injecteur est montée, une couronne d'admission d'air 56, et un bol 58, parfois dénommé « bol mélangeur ». Ces éléments sont centrés par rapport à l'axe d'injection 44 défini par la tête 52 de l'injecteur de carburant.The figure 3 is an axial half-sectional view of one of the injection systems 42. This generally comprises a head 52 of a fuel injector, a bush 54, sometimes referred to as a "sliding bushing", in which the head 52 of the injector is mounted, an air intake ring 56, and a bowl 58, sometimes referred to as "mixing bowl". These elements are centered with respect to the injection axis 44 defined by the head 52 of the fuel injector.

La couronne d'admission d'air 56 présente une forme globalement de révolution autour de l'axe d'injection 44, cet axe constituant donc un axe de révolution pour la couronne d'admission d'air 56.The air intake ring 56 has a generally circular shape around the injection axis 44, this axis therefore constituting an axis of revolution for the air intake ring 56.

La couronne d'admission d'air 56 comprend une paroi annulaire de séparation 60 qui partage la couronne d'admission d'air en un espace de circulation d'air amont 62 et un espace de circulation d'air aval 64. Ces deux espaces sont couramment appelés « vrilles ».The air intake crown 56 comprises an annular partition wall 60 which divides the air intake crown into an upstream air circulation space 62 and a downstream air circulation space 64. These two spaces are commonly called "tendrils".

La paroi annulaire de séparation 60 se prolonge radialement vers l'intérieur en une paroi annulaire de déflection 66, couramment dénommée « venturi », ayant un profil interne 68 de forme convergente-divergente présentant en particulier un col 70, ainsi qu'un profil externe 72.The annular separation wall 60 extends radially inwardly into an annular deflection wall 66, commonly called "venturi", having an internal profile 68 of convergent-divergent shape having in particular a collar 70, as well as an external profile. 72.

Chacun des espaces de circulation d'air amont 62 et aval 64 est traversé par des ailettes 74 permettant la giration de l'air autour de l'axe de révolution 44 de la couronne d'admission d'air.Each of the upstream and downstream air circulation spaces 62 and 62 is traversed by fins 74 allowing the air to be swirled around the axis of revolution 44 of the air intake ring.

En fonctionnement, une partie de l'air 46 alimentant le système d'injection pénètre dans les espaces de circulation d'air 62 et 64 de la couronne d'admission d'air 56 et poursuit son trajet sous la forme de flux d'air 76 et 78 le long des profils interne 68 et externe 72 de la paroi annulaire de déflection 66.In operation, a part of the air 46 supplying the injection system enters the air circulation spaces 62 and 64 of the air intake ring 56 and continues its course in the form of air flow. 76 and 78 along the inner 68 and outer 72 profiles of the annular deflection wall 66.

De plus, du carburant est éjecté par la tête 52 de l'injecteur, sous la forme d'un cône 80 d'angle 0 par rapport à l'axe d'injection 44.In addition, fuel is ejected by the head 52 of the injector, in the form of a cone 80 of angle 0 with respect to the injection axis 44.

Une partie importante de ce carburant se dépose et forme un film 82 sur le profil interne 68 de la paroi annulaire de déflection 66.A large part of this fuel is deposited and forms a film 82 on the internal profile 68 of the annular deflection wall 66.

Entraîné par le flux d'air circulant vers l'aval le long de ce profil interne 68, le carburant ruisselle vers l'aval sur le profil interne 68.Driven by the flow of air flowing downstream along this internal profile 68, the fuel flows downstream on the internal profile 68.

Arrivé à l'extrémité aval du profil interne 68, le carburant rencontre le flux d'air 78 circulant le long du profil externe 72 de la paroi annulaire de déflection 66. Ce flux d'air 78 induit un effet de cisaillement qui conduit le carburant à se détacher de la paroi annulaire de déflection en formant des gouttelettes en suspension dans l'air.Arrived at the downstream end of the internal profile 68, the fuel meets the flow of air 78 flowing along the outer profile 72 of the annular deflection wall 66. This air flow 78 induces a shearing effect which drives the fuel to detach from the annular deflection wall by forming droplets suspended in the air.

Il est à noter que la partie du profil interne 68 recouverte par le film de carburant 82 forme donc une région annulaire 83, qui s'étend jusqu'à l'extrémité aval du profil interne 68.It should be noted that the portion of the internal profile 68 covered by the fuel film 82 thus forms an annular region 83, which extends to the downstream end of the internal profile 68.

Les gouttelettes de carburant détachées de la paroi annulaire de déflection ont vocation à s'évaporer dans l'air, de préférence avant d'atteindre l'entrée du foyer de la chambre de combustion.The fuel droplets detached from the annular deflection wall are designed to evaporate into the air, preferably before reaching the combustion chamber firebox inlet.

L'évaporation des gouttelettes est favorisée, autant que possible, par la turbulence induite par la rencontre des flux d'air 76 et 78 circulant respectivement de part et d'autre de la paroi annulaire de déflection.The evaporation of the droplets is favored, as far as possible, by the turbulence induced by the meeting of the air flows 76 and 78 flowing respectively on either side of the annular deflection wall.

Ce type de système d'injection n'est toutefois pas optimal du fait que les gouttelettes de carburant formées à l'extrémité aval de la paroi annulaire de déflection sont de taille relativement grande, et bénéficient d'un volume relativement limité pour s'évaporer.This type of injection system is however not optimal because the fuel droplets formed at the downstream end of the annular deflection wall are of relatively large size, and have a relatively limited volume to evaporate. .

De ce fait, le rendement de combustion demeure lui-même limité.As a result, the combustion efficiency itself remains limited.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

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

Elle propose à cet effet une couronne d'admission d'air pour système d'injection de chambre de combustion de turbomachine, présentant un axe de révolution, et comprenant une paroi annulaire de séparation qui partage la couronne d'admission d'air en un espace de circulation d'air amont et un espace de circulation d'air aval et qui se prolonge radialement vers l'intérieur en une paroi annulaire de déflection présentant un profil interne ayant une forme convergente-divergente.It proposes for this purpose an air intake ring for a turbomachine combustion chamber injection system, having an axis of revolution, and comprising an annular partition wall which divides the air intake crown into one. an upstream air circulation space and a downstream air circulation space which extends radially inwardly into an annular deflection wall having an internal profile having a convergent-divergent shape.

Selon l'invention, le profil interne de la paroi annulaire de déflection présente un décrochement induisant un accroissement du rayon du profil interne en aval dudit décrochement.According to the invention, the internal profile of the annular deflection wall has a recess inducing an increase in the radius of the internal profile downstream of said recess.

Le décrochement induit la présence d'une arête au niveau de l'extrémité aval d'une portion amont du profil interne.The recess induces the presence of an edge at the downstream end of an upstream portion of the internal profile.

Le carburant ruisselant sur le profil interne tend donc à se détacher au niveau de cette arête, entraîné en cela par le flux d'air circulant le long du profil interne, issu de l'espace de circulation d'air amont.The fuel dripping on the internal profile thus tends to detach at this edge, thereby caused by the flow of air flowing along the internal profile, from the upstream air circulation space.

La séparation du carburant en gouttelettes a donc lieu plus en amont qu'avec les couronnes d'admission d'air de type connu.The separation of the fuel into droplets therefore takes place further upstream than with the air intake crowns of known type.

Les gouttelettes disposent ainsi d'un volume plus important pour s'évaporer avant de pénétrer dans la chambre de combustion.The droplets thus have a larger volume to evaporate before entering the combustion chamber.

De plus, le décrochement crée une zone de recirculation en aval de celui-ci et induit de la turbulence, propice au mélange du carburant et de l'air, et rendant de surcroît possible un épaississement du front de flamme.In addition, the recess creates a recirculation zone downstream thereof and induces turbulence, conducive to the mixing of fuel and air, and further making possible a thickening of the flame front.

D'une manière générale, l'invention permet ainsi d'améliorer le rendement de combustion.In general, the invention thus makes it possible to improve the combustion efficiency.

De préférence, le décrochement est formé au niveau d'un col du profil interne de la paroi annulaire de déflection.Preferably, the recess is formed at a neck of the inner profile of the annular deflection wall.

De plus, ledit décrochement définit de préférence un épaulement s'étendant orthogonalement audit axe de révolution de la couronne d'admission d'air.In addition, said recess preferably defines a shoulder extending orthogonally to said axis of revolution of the air intake crown.

Dans un mode de réalisation préféré de l'invention, chacun des espaces de circulation d'air amont et aval est traversé par des ailettes permettant la giration de l'air autour dudit axe de révolution de la couronne d'admission d'air.In a preferred embodiment of the invention, each of the upstream and downstream air circulation spaces is traversed by fins allowing the air to gyrate around said axis of revolution of the air intake crown.

L'invention concerne également un système d'injection pour chambre de combustion de turbomachine, comprenant une tête d'injecteur de carburant, ainsi qu'une couronne d'admission d'air du type décrit ci-dessus, dans lequel la tête d'injecteur de carburant est configurée pour pulvériser du carburant sur une région annulaire du profil interne de la paroi annulaire de déflection, et dans lequel le décrochement est formé en aval d'une extrémité amont de ladite région annulaire du profil interne.The invention also relates to an injection system for a turbomachine combustion chamber, comprising a fuel injector head, and an air intake ring of the type described above, in which the head of fuel injector is configured to spray fuel on an annular region of the inner profile of the annular deflection wall, and wherein the recess is formed downstream of an upstream end of said annular region of the inner profile.

L'invention concerne aussi une chambre de combustion pour turbomachine, comprenant au moins un système d'injection du type décrit ci-dessus.The invention also relates to a combustion chamber for a turbomachine, comprising at least one injection system of the type described above.

L'invention concerne également une turbomachine, notamment pour aéronef, comprenant au moins une chambre de combustion du type décrit ci-dessus.The invention also relates to a turbomachine, particularly for an aircraft, comprising at least one combustion chamber of the type described above.

L'invention concerne enfin un procédé d'atomisation de carburant dans un système d'injection du type décrit ci-dessus, équipant une chambre de combustion de turbomachine, dans lequel du carburant issu de la tête d'injecteur ruisselle sur le profil interne de la paroi annulaire de déflection, et se détache de ce profil interne au niveau du décrochement de ce dernier de manière à former des gouttelettes au sein d'un flux d'air issu de l'espace de circulation d'air amont de la couronne d'admission d'air et circulant le long du profil interne de la paroi annulaire de déflection.Finally, the invention relates to a fuel atomization method in an injection system of the type described above, fitted to a turbomachine combustion chamber, in which fuel from the injector head flows on the internal profile of the engine. the annular deflection wall, and detaches from this internal profile at the recess of the latter so as to form droplets within a stream of air from the upstream air circulation space of the crown of air intake and circulating along the inner profile of the annular deflection wall.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

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

  • la figure 1, déjà décrite, est une vue schématique partielle en coupe axiale d'une turbomachine d'un type connu ;
  • la figure 2, déjà décrite, est une vue schématique partielle en coupe axiale d'une chambre de combustion de la turbomachine de la figure 1 ;
  • la figure 3, déjà décrite, est une demi-vue schématique partielle en coupe axiale d'un système d'injection équipant la chambre de combustion de la figure 2 ;
  • la figure 4 est une vue semblable à la figure 3, illustrant un système d'injection comprenant une couronne d'admission d'air selon un mode de réalisation préféré de l'invention ;
  • la figure 5 est une vue à plus grande échelle d'une partie de la figure 4.
The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of nonlimiting example and with reference to the accompanying drawings in which:
  • the figure 1 , already described, is a partial schematic view in axial section of a turbomachine of a known type;
  • the figure 2 , already described, is a partial schematic view in axial section of a combustion chamber of the turbomachine of the figure 1 ;
  • the figure 3 , already described, is a partial schematic half-view in axial section of an injection system equipping the combustion chamber of the figure 2 ;
  • the figure 4 is a view similar to the figure 3 , illustrating an injection system comprising an air intake crown according to a preferred embodiment of the invention;
  • the figure 5 is a larger-scale view of some of the figure 4 .

Dans l'ensemble de ces figures, des références identiques peuvent désigner des éléments identiques ou analogues.In all of these figures, identical references may designate identical or similar elements.

EXPOSÉ DÉTAILLÉ D'UN MODE DE RÉALISATION PRÉFÉRÉDETAILED DESCRIPTION OF A PREFERRED EMBODIMENT

Les figures 4 et 5 illustrent un système d'injection 42 qui est globalement semblable au système d'injection des figures 1 à 3 mais qui s'en distingue du fait qu'il comprend une couronne d'admission d'air 56 selon un mode de réalisation préféré de l'invention.The figures 4 and 5 illustrate an injection system 42 which is broadly similar to the injection system of the Figures 1 to 3 but differs from the fact that it comprises an air intake crown 56 according to a preferred embodiment of the invention.

Cette couronne d'admission d'air 56 présente la particularité que le profil interne 68 de la paroi annulaire de déflection 66 présente un décrochement 90 induisant un accroissement du rayon φ du profil interne en aval de ce décrochement 90.This air intake ring 56 has the particularity that the internal profile 68 of the annular deflection wall 66 has a recess 90 inducing an increase in radius φ of the internal profile downstream of this recess 90.

Ainsi, une partie aval du profil interne 68 se trouve en retrait, c'est-à-dire décalée radialement vers l'extérieur, par rapport à une partie amont de ce profil interne 68.Thus, a downstream part of the internal profile 68 is set back, that is to say offset radially outwards, with respect to an upstream portion of this internal profile 68.

Le décrochement 90 induit la présence d'une arête 92 au niveau de l'extrémité aval de la portion amont du profil interne.The recess 90 induces the presence of an edge 92 at the downstream end of the upstream portion of the internal profile.

De plus, le décrochement 90 est formé en aval d'une extrémité amont 93 de la région annulaire 83 du profil interne 68, sur laquelle ruisselle le film de carburant 82.In addition, the recess 90 is formed downstream of an upstream end 93 of the annular region 83 of the internal profile 68, on which the film of fuel 82 flows.

En fonctionnement, le carburant formant le film de carburant 82 ruisselant sur le profil interne 68 tend à se détacher au niveau de cette arête 92, entraîné en cela par le flux d'air 76 circulant le long du profil interne 68.In operation, the fuel forming the fuel film 82 dripping on the internal profile 68 tends to detach at this edge 92, driven by the air flow 76 flowing along the internal profile 68.

La séparation du carburant en gouttelettes, ou atomisation, a donc lieu plus en amont qu'avec les couronnes d'admission d'air de type connu. Les gouttelettes disposent ainsi d'un volume plus important pour s'évaporer avant de pénétrer dans la chambre de combustion.The separation of the fuel into droplets, or atomization, therefore takes place further upstream than with the air intake crowns of known type. The droplets thus have a larger volume to evaporate before entering the combustion chamber.

De plus, le décrochement 90 crée une zone de recirculation en aval de celui-ci et induit de la turbulence, propice au mélange du carburant et de l'air, et rendant possible un épaississement du front de flamme.In addition, the recess 90 creates a recirculation zone downstream thereof and induces turbulence, conducive to the mixing of fuel and air, and making possible a thickening of the flame front.

D'une manière générale, l'invention permet ainsi d'améliorer le mélange d'air et de carburant, et donc d'améliorer le rendement de combustion.In general, the invention thus improves the mixture of air and fuel, and thus improve the combustion efficiency.

A titre d'exemple préférentiel, comme cela apparaît sur la figure 4, le décrochement 90 est formé au niveau du col 70 du profil interne 68.As a preferred example, as it appears on the figure 4 , the recess 90 is formed at the neck 70 of the internal profile 68.

Ainsi, la séparation du carburant en gouttelettes a lieu à l'endroit où la vitesse du flux d'air 76 circulant le long du profil interne 68 est la plus importante. Cela permet de minimiser la taille des gouttelettes de carburant générées.Thus, the separation of the fuel into droplets takes place where the speed of the airflow 76 flowing along the internal profile 68 is the largest. This minimizes the size of the generated fuel droplets.

De préférence, le décrochement définit un épaulement 94 s'étendant orthogonalement à l'axe de révolution 44 de la couronne d'admission d'air 56 (figure 5).Preferably, the recess defines a shoulder 94 extending orthogonally to the axis of revolution 44 of the air intake ring 56 ( figure 5 ).

A titre illustratif, le système d'injection 42 équipe une chambre de combustion semblable à la chambre de combustion de la figure 2 au sein d'une turbomachine semblable à la turbomachine de la figure 1.As an illustration, the injection system 42 equips a combustion chamber similar to the combustion chamber of the figure 2 in a turbomachine similar to the turbomachine of the figure 1 .

Le système d'injection permet donc la mise en oeuvre d'un procédé d'atomisation de carburant, dans lequel du carburant issu de la tête d'injecteur 52 ruisselle sur le profil interne 68 de la paroi annulaire de déflection 66, et se détache de ce profil interne 68 au niveau du décrochement 90 de ce dernier de manière à former des gouttelettes au sein du flux d'air 76 issu de l'espace de circulation d'air amont 62 de la couronne d'admission d'air 56 et circulant le long du profil interne 68.The injection system therefore allows the implementation of a fuel atomization process, in which fuel from the injector head 52 flows on the inner profile 68 of the annular deflection wall 66, and detaches of this internal profile 68 at the recess 90 of the latter so as to form droplets within the air flow 76 from the upstream air circulation space 62 of the air intake ring 56 and flowing along the internal profile 68.

D'une manière générale, l'invention permet de diminuer la richesse d'extinction pauvre et de réduire les émissions CO/CH.In general, the invention makes it possible to reduce the poor quenching richness and to reduce CO / CH emissions.

Claims (8)

  1. Air intake ring (56) for an injection system (42) of a combustion chamber (18) of a turbomachine (10), having an axis of revolution (44), and comprising an annular separation wall (60) that divides the air intake ring into an upstream air circulation space (62) and a downstream air circulation space (64), and that extends radially inwards into an annular deflection wall (66) having an internal profile (68) with a convergent-divergent shape, the internal profile (68) of the annular deflection wall having a discontinuity (90), characterised in that said discontinuity (90) induces an increase in the radius (φ) of the internal profile downstream of said discontinuity.
  2. Air intake ring according to claim 1, wherein said discontinuity (90) is formed at the level of a neck (70) of the internal profile (68) of the annular deflection wall.
  3. Air intake ring according to claim 1 or 2, wherein said discontinuity (90) defines a shoulder (94) extending orthogonally to said axis of revolution (44) of the air intake ring.
  4. Air intake ring according to any one of claims 1 to 3, wherein each of the upstream (62) and downstream (64) air circulation spaces are passed through by fins (74) allowing for the gyration of the air about said axis of revolution (44) of the air intake ring.
  5. Injection system (42) for a combustion chamber (18) of a turbomachine (10), comprising a fuel injector head (52) in addition to an air intake ring (56) according to any one of claims 1 to 4,
    wherein the fuel injector head (52) is configured to spray fuel (82) over an annular region (83) of the internal profile (68) of the annular deflection wall (66), and
    wherein said discontinuity (90) is formed downstream of an upstream end (93) of said annular region (83) of the internal profile.
  6. Combustion chamber (18) for a turbomachine, comprising at least one injection system (42) according to claim 5.
  7. Turbomachine (10), in particular for an aircraft, comprising at least one combustion chamber (18) according to claim 6.
  8. Method of atomising fuel in an injection system (42) according to claim 5, with which a turbomachine combustion chamber (18) is equipped, wherein fuel (82) originating from the injector head (52) trickles over the internal profile (68) of the annular deflection wall (66), and separates from said internal profile at the level of the discontinuity (90) of the latter, so as to form droplets within a flow of air (76) coming from the upstream air circulation space (62) of the air intake ring (56) and circulating along the internal profile (68) of the annular deflection wall.
EP15817462.3A 2014-12-03 2015-12-02 Air intake ring for turbo machine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring Active EP3227612B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1461862A FR3029608B1 (en) 2014-12-03 2014-12-03 AIR INTAKE CROWN FOR TURBOMACHINE COMBUSTION CHAMBER INJECTION SYSTEM AND FUEL ATOMIZATION METHOD IN INJECTION SYSTEM COMPRISING SAID AIR INTAKE CROWN
PCT/FR2015/053296 WO2016087780A1 (en) 2014-12-03 2015-12-02 Air intake ring for turbo machine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring

Publications (2)

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EP3227612A1 EP3227612A1 (en) 2017-10-11
EP3227612B1 true EP3227612B1 (en) 2018-09-05

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EP15817462.3A Active EP3227612B1 (en) 2014-12-03 2015-12-02 Air intake ring for turbo machine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring

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US (1) US10677463B2 (en)
EP (1) EP3227612B1 (en)
CN (1) CN107003003B (en)
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
FR3070198B1 (en) * 2017-08-21 2019-09-13 Safran Aircraft Engines AIRCRAFT TURBOMACHINE COMBUSTION CHAMBER MODULE COMPRISING BRANDS FACILITATING REPERAGE DURING ENDOSCOPIC INSPECTION OF THE COMBUSTION CHAMBER
US11885497B2 (en) * 2019-07-19 2024-01-30 Pratt & Whitney Canada Corp. Fuel nozzle with slot for cooling

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Publication number Priority date Publication date Assignee Title
GB2272756B (en) * 1992-11-24 1995-05-31 Rolls Royce Plc Fuel injection apparatus
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
US6314739B1 (en) * 2000-01-13 2001-11-13 General Electric Company Brazeless combustor dome assembly
FR2827367B1 (en) * 2001-07-16 2003-10-17 Snecma Moteurs AEROMECHANICAL INJECTION SYSTEM WITH ANTI-RETURN PRIMARY LOCK
GB0219461D0 (en) * 2002-08-21 2002-09-25 Rolls Royce Plc Fuel injection arrangement
US20050229600A1 (en) * 2004-04-16 2005-10-20 Kastrup David A Methods and apparatus for fabricating gas turbine engine combustors
JP4364911B2 (en) * 2007-02-15 2009-11-18 川崎重工業株式会社 Gas turbine engine combustor
FR2941288B1 (en) * 2009-01-16 2011-02-18 Snecma DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL IN A TURBOMACHINE COMBUSTION CHAMBER

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WO2016087780A1 (en) 2016-06-09
FR3029608B1 (en) 2017-01-13
EP3227612A1 (en) 2017-10-11
CN107003003A (en) 2017-08-01
US10677463B2 (en) 2020-06-09
US20170363290A1 (en) 2017-12-21
FR3029608A1 (en) 2016-06-10
CN107003003B (en) 2019-07-12

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