EP4065892B1 - Air and fuel injection system for a turbomachine, combustion chamber comprising such a system, and associated turbomachine - Google Patents

Air and fuel injection system for a turbomachine, combustion chamber comprising such a system, and associated turbomachine Download PDF

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Publication number
EP4065892B1
EP4065892B1 EP20820511.2A EP20820511A EP4065892B1 EP 4065892 B1 EP4065892 B1 EP 4065892B1 EP 20820511 A EP20820511 A EP 20820511A EP 4065892 B1 EP4065892 B1 EP 4065892B1
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EP
European Patent Office
Prior art keywords
injection
mixing device
injector
injection system
air
Prior art date
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Application number
EP20820511.2A
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German (de)
French (fr)
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EP4065892A1 (en
Inventor
Romain Nicolas Lunel
Haris MUSAEFENDIC
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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
    • F23R3/28—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
    • F23R3/28—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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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

Definitions

  • the invention relates to air and fuel injection systems equipping the annular combustion chambers of turbomachines, particularly those of aircraft.
  • FIG 1 illustrates an air and fuel injection system 1 of known type comprising a fuel injector 2 and a mixing device 3 equipping a bottom wall of a combustion chamber (not shown on the figure 1 ).
  • the mixing device 3 comprises, from upstream to downstream in a general direction 4 of fuel flow, a centering member 5 of a head 12 of the injector 2, an intake crown air 7 and a conical wall 8 which is flared downstream called bowl in the following.
  • the bowl 8 is intended to guide at the outlet of the injection system 1 a mixture of air and fuel intended to ignite in the primary zone of the combustion chamber.
  • the centering member 5 (or sliding bushing) is made up of an annular part flared towards the upstream in order to facilitate the introduction of the injection head during its assembly.
  • the air intake crown 7 comprises fins (not shown) to impart to the air passing through this crown a gyrating movement around a longitudinal axis AA' of the mixing device 3.
  • This crown comprises a primary spinner 71 and a secondary spinner 72.
  • the mixing device 3 is equipped with a venturi 9 in order to accelerate the flow of fluids at its level.
  • the head of the injector 12 comprises an injection nose 13 through which the fuel is intended to be supplied.
  • the head 12 is inserted into the mixing device 3 via the centering member 5.
  • the head 12 of the injector is in contact with the internal annular wall 10 of the mixing device 3 according to a spherical part 11 which allows have a swivel connection between the internal annular wall 10 and the head 12.
  • the invention proposes to overcome at least one of these drawbacks.
  • the invention proposes a combustion chamber of a turbomachine comprising an injection system according to the first aspect of the invention.
  • the invention proposes a turbomachine comprising a combustion chamber according to the second aspect of the invention.
  • FIG. 2 illustrates an air and fuel injection system 21 of a turbomachine according to one embodiment of the invention.
  • Such an injection system comprises an injector 22 and a mixing device 25 arranged downstream of the injector 22 in a direction of flow of the fuel in the injection system.
  • upstream and downstream are defined in relation to the direction of fuel flow (from left to right on the figure 2 ).
  • the injector 22 comprises a fuel supply pipe 23 ending in an injection nose 24.
  • This pipe 23 is an extension of an upstream conduit and makes an elbow with the latter.
  • Pipeline 23 extends from upstream to downstream along a longitudinal axis AA' of the air and fuel injection system.
  • the injector 22 further comprises an air injection crown 26, downstream of the pipe 23.
  • the air injection crown 26 comprises a first twist 261 and a second twist 262.
  • the crown 26 surrounds the nose injection 24.
  • the first and second tendrils of the air injection crown 25 include air passages arranged all around.
  • a ring 28 for connecting the injector 22 to the mixing device 25.
  • This ring 28 comprises an annular part 281 which is extended by a divergent part 282 flared downstream.
  • the mixing device 25 is arranged downstream of the injection nose 24.
  • the mixing device 25 is in particular made up of a bowl 27 comprising an annular inlet 30 which is extended by a conical part 33 flared downstream.
  • the annular inlet 30 constitutes the inlet of the mixing device
  • the mixing device 25 defines an annular cavity 29 in which, in operation, the mixture of air and fuel takes place.
  • the injector is partly arranged in this annular cavity 29.
  • the injector must be in fluid communication with the mixing device.
  • connection ring 28 of the injector It is via the ring 28 of the injector that the injector 22 is in communication with the mixing device 25.
  • the connection ring 28 is advantageously arranged around the inlet 30 of the mixing device 25.
  • the connection ring 28 has an internal diameter greater than that of the inlet 30 of the mixing device 25 so that this connection ring 28 encompasses the inlet of the mixing device.
  • this ring 28 is flared downstream in order to facilitate the insertion of the mixing device inlet 25, at the level of the bowl 27, in the connection ring 28 during the assembly of the injector to the mixing device.
  • the inlet 30 of the mixing device 25 comprises an external surface 31 which takes the form of a truncated sphere and the ring 28 is in contact with the inlet of the bowl via this truncated sphere.
  • the injector and the mixing device present at this contact zone a connection which allows movement relative of the injector relative to the mixing device.
  • the injector and the mixing device have a swivel connection at this contact zone.
  • this arrangement makes it possible, during the operation of the injection system, to authorize relative movements of the injector relative to the mixing device without affecting the operation of the injection system. Indeed, as presented in the introduction during the operation of the turbomachine the injection system is subjected to very strong movements which are applied to the different elements constituting the injection system.
  • the injector 22 comprises a venturi 32 located axially in the vicinity of the injection nose 24.
  • the venturi 32 is part of the injector and not of the mixing device.
  • the venturi 32 is arranged between the first and second tendrils of the air injection crown 26 of the injector 22.
  • the injection head is now axially arranged at the level of the venturi 32 and is closer to the inlet 30 of the mixing device. The mixture is therefore better.
  • the conduit 23, the ring 28 and the venturi 32 are formed in one piece, that is to say that all the parts constituting them are machined in the same part.
  • These parts can be obtained by an additive manufacturing process and are preferably in one piece.
  • the air injection crown and the injector connection ring are formed in a single piece, preferably obtained by an additive manufacturing process.
  • the inlet 30 of the mixing device is located in the air passage of the second swirl 262. Indeed, as can be seen in the figure 2 , the air arriving via the second spindle 262 and guided by the venturi will directly arrive in the inlet 30 of the mixing device.
  • the injection nose 24 is arranged relative to the venturi 32 so as to open the fuel spray angle to the maximum without impacting the venturi 32 or the bowl 27 while maintaining a passage section between the nose 24 and the venturi 32. Indeed, when the assembly is in one piece it is easier to position the different elements in relation to each other since in this case we are freed from relative movements between the parts.
  • FIG 3a illustrates the fuel spray S coming from the injection nose 24.
  • the injection system 22 described above is advantageously implemented in a combustion chamber 40 of a turbomachine as illustrated in the Figure 4 .

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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)

Description

DOMAINE TECHNIQUE GENERALGENERAL TECHNICAL AREA

L'invention concerne les systèmes d'injection d'air et de carburant équipant les chambres annulaires de combustion des turbomachines notamment celles d'aéronef.The invention relates to air and fuel injection systems equipping the annular combustion chambers of turbomachines, particularly those of aircraft.

ETAT DE LA TECHNIQUESTATE OF THE ART

La figure 1 illustre un système d'injection 1 d'air et de carburant de type connu comprenant un injecteur de carburant 2 et un dispositif mélangeur 3 équipant une paroi de fond d'une chambre de combustion (non représentée sur la figure 1).There figure 1 illustrates an air and fuel injection system 1 of known type comprising a fuel injector 2 and a mixing device 3 equipping a bottom wall of a combustion chamber (not shown on the figure 1 ).

De manière plus précise, le dispositif mélangeur 3 comprend de l'amont vers l'aval selon une direction générale 4 d'écoulement du carburant, un organe de centrage 5 d'une tête 12 de l'injecteur 2, une couronne d'admission d'air 7 et une paroi conique 8 qui est évasée vers l'aval appelée bol dans ce qui suit. Le bol 8 est destiné à guider en sortie du système d'injection 1 un mélange d'air et de carburant destiné à s'enflammer dans la zone primaire de la chambre de combustion. L'organe de centrage 5 (ou traversée coulissante) est constitué d'une pièce annulaire évasée vers l'amont afin de faciliter l'introduction de la tête d'injection au cours de son montage. La couronne d'admission d'air 7 comporte des ailettes (non représentées) pour imprimer à l'air passant dans cette couronne un mouvement de giration autour d'un axe longitudinal AA' du dispositif mélangeur 3. Cette couronne comprend une vrille primaire 71 et une vrille secondaire 72. En outre, le dispositif mélangeur 3 est équipé d'un venturi 9 afin d'accélérer l'écoulement des fluides à son niveau.More precisely, the mixing device 3 comprises, from upstream to downstream in a general direction 4 of fuel flow, a centering member 5 of a head 12 of the injector 2, an intake crown air 7 and a conical wall 8 which is flared downstream called bowl in the following. The bowl 8 is intended to guide at the outlet of the injection system 1 a mixture of air and fuel intended to ignite in the primary zone of the combustion chamber. The centering member 5 (or sliding bushing) is made up of an annular part flared towards the upstream in order to facilitate the introduction of the injection head during its assembly. The air intake crown 7 comprises fins (not shown) to impart to the air passing through this crown a gyrating movement around a longitudinal axis AA' of the mixing device 3. This crown comprises a primary spinner 71 and a secondary spinner 72. In addition, the mixing device 3 is equipped with a venturi 9 in order to accelerate the flow of fluids at its level.

Comme cela est visible sur la figure 1, la tête de l'injecteur 12 comprend un nez d'injection 13 par lequel le carburant est destiné à être amené. La tête 12 est insérée dans le dispositif mélangeur 3 via l'organe de centrage 5. De préférence, la tête 12 de l'injecteur est en contact avec la paroi annulaire interne 10 du dispositif mélangeur 3 selon une partie sphérique 11 qui permet d'avoir une liaison rotulante entre la paroi annulaire interne 10 et la tête 12.As can be seen on the figure 1 , the head of the injector 12 comprises an injection nose 13 through which the fuel is intended to be supplied. The head 12 is inserted into the mixing device 3 via the centering member 5. Preferably, the head 12 of the injector is in contact with the internal annular wall 10 of the mixing device 3 according to a spherical part 11 which allows have a swivel connection between the internal annular wall 10 and the head 12.

Une telle liaison permet d'autoriser des mouvements de la tête 12 de l'injecteur au cours du fonctionnement de la turbomachine pour éviter d'endommager cette zone qui pourrait conduire à des pannes avec des conséquences négatives.Such a connection makes it possible to authorize movements of the head 12 of the injector during operation of the turbomachine to avoid damaging this zone which could lead to breakdowns with negative consequences.

Ainsi, en fonctionnement on peut constater des déplacements relatifs entre l'injecteur et le dispositif mélangeur 3 ainsi que des défauts de fabrication. C'est-à-dire que la partie sphérique 11 de la tête de l'injecteur 12 peut se déplacer de l'amont ou l'aval (selon la direction générale 4).Thus, in operation we can observe relative movements between the injector and the mixing device 3 as well as manufacturing defects. That is to say that the spherical part 11 of the head of the injector 12 can move upstream or downstream (in the general direction 4).

De tels déplacements peuvent toutefois être problématiques :

  • Si la tête 12 de l'injecteur est décalée vers l'aval alors selon les cas il est possible que la tête 12 vienne obstruer les vrilles primaire 71 et secondaire 72 et nuisant alors au volume d'air amené dans le dispositif mélangeur 3 ;
  • Si la tête 12 de l'injecteur est décalée vers l'amont alors le spray de carburant issu de la tête 12 peut impacter le venturi 9 et le bol 8. En effet, le rôle de la tête 12 de l'injecteur est de générer un brouillard de fines gouttes, si ces gouttes viennent impacter le venturi 9 celles-ci vont ruisseler et se transformer en gouttes relativement plus grosses. De plus, l'angle de spray carburant ne doit pas être réduit par le venturi 9.
However, such trips can be problematic:
  • If the head 12 of the injector is offset downstream then depending on the case it is possible for the head 12 to obstruct the primary 71 and secondary 72 swirls and thus harm the volume of air brought into the mixing device 3;
  • If the head 12 of the injector is offset upstream then the fuel spray coming from the head 12 can impact the venturi 9 and the bowl 8. Indeed, the role of the head 12 of the injector is to generate a mist of fine drops, if these drops impact the venturi 9 they will flow and transform into relatively larger drops. In addition, the fuel spray angle must not be reduced by the venturi 9.

Un autre système selon l'art antérieur, conforme au préambule de la revendication 1, est connu du document US 6,314,739 B1 .Another system according to the prior art, in accordance with the preamble of claim 1, is known from the document US 6,314,739 B1 .

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

L'invention propose de pallier au moins un de ces inconvénients.The invention proposes to overcome at least one of these drawbacks.

A cet effet, l'invention propose, selon un premier aspect, un système d'injection d'air et de carburant d'une turbomachine comprenant :

  • un injecteur comprenant une canalisation et un nez d'injection disposé à l'intérieur de ladite canalisation qui s'étend d'amont en aval selon un axe longitudinal ;
  • un dispositif mélangeur comprenant un bol comprenant une entrée annulaire, formant entrée du dispositif mélangeur, à partir de laquelle s'étend une partie conique évasée vers l'aval, ledit dispositif mélangeur étant disposé en aval du nez d'injection ; le système d'injection étant caractérisé en ce que l'injecteur comprend une couronne d'injection d'air s'étendant depuis la canalisation et à partir de laquelle s'étend une bague de connexion comprenant une partie divergente, ladite bague étant disposée extérieurement autour de l'entrée annulaire du dispositif mélangeur.
To this end, the invention proposes, according to a first aspect, an air and fuel injection system for a turbomachine comprising:
  • an injector comprising a pipe and an injection nose disposed inside said pipe which extends from upstream to downstream along a longitudinal axis;
  • a mixing device comprising a bowl comprising an annular inlet, forming an inlet of the mixing device, from which extends a conical portion flared downstream, said mixing device being arranged downstream of the injection nose; the injection system being characterized in that the injector comprises an air injection ring extending from the pipe and from which extends a connection ring comprising a divergent part, said ring being arranged externally around the annular inlet of the mixing device.

L'invention, selon le premier aspect, est avantageusement complétée par les caractéristiques suivantes, prises seules ou en une quelconque de leur combinaison techniquement possible :

  • la couronne d'injection d'air est disposée en aval de la canalisation;
  • l'entrée du dispositif mélangeur est disposée en aval du nez d'injection ;
  • l'entrée du dispositif mélangeur comprend une surface externe prenant la forme d'une sphère tronquée, la bague de connexion de l'injecteur étant en contact avec l'entrée du dispositif mélangeur par l'intermédiaire de ladite sphère tronquée ;
  • l'injecteur comprend un venturi situé axialement au niveau de la tête d'injection ;
  • il comprend une première vrille disposée en amont du venturi et une deuxième vrille disposée en aval du venturi, lesdites première et deuxième vrilles comprenant des passages d'air ;
  • le nez d'injection, le venturi, la couronne d'injection d'air sont formés d'une seule pièce, de préférence obtenue par un procédé de fabrication additive.
The invention, according to the first aspect, is advantageously supplemented by the following characteristics, taken alone or in any of their technically possible combinations:
  • the air injection crown is arranged downstream of the pipe;
  • the inlet of the mixing device is located downstream of the injection nose;
  • the inlet of the mixing device comprises an external surface taking the form of a truncated sphere, the connection ring of the injector being in contact with the inlet of the mixing device via said truncated sphere;
  • the injector comprises a venturi located axially at the level of the injection head;
  • it comprises a first auger arranged upstream of the venturi and a second auger disposed downstream of the venturi, said first and second augers comprising air passages;
  • the injection nose, the venturi, the air injection crown are formed in a single piece, preferably obtained by an additive manufacturing process.

Selon un second aspect, l'invention propose une chambre de combustion d'une turbomachine comprenant un système d'injection selon le premier aspect de l'invention.According to a second aspect, the invention proposes a combustion chamber of a turbomachine comprising an injection system according to the first aspect of the invention.

Selon un troisième aspect, l'invention propose une turbomachine comprenant une chambre de combustion selon le deuxième aspect de l'invention.According to a third aspect, the invention proposes a turbomachine comprising a combustion chamber according to the second aspect of the invention.

PRESENTATION DES FIGURESPRESENTATION OF FIGURES

D'autres caractéristiques, buts et avantages de l'invention ressortiront de la description qui suit, qui est purement illustrative et non limitative, et qui doit être lue en regard des dessins annexés sur lesquels, outre la figure 1 illustre un système d'injection de type connu ;

  • la figure 2 illustre un système d'injection selon un mode de réalisation de l'invention ; les figures 3a, 3b et 3c illustre un système d'injection selon l'invention en fonctionnement ;
  • la figure 4 illustre une chambre de combustion selon l'invention.
Other characteristics, aims and advantages of the invention will emerge from the description which follows, which is purely illustrative and not limiting, and which must be read with reference to the appended drawings in which, in addition to the figure 1 illustrates an injection system of known type;
  • there figure 2 illustrates an injection system according to one embodiment of the invention; THE figures 3a, 3b and 3c illustrates an injection system according to the invention in operation;
  • there figure 4 illustrates a combustion chamber according to the invention.

Sur l'ensemble des figures les éléments similaires portent des références identiques.In all the figures, similar elements bear identical references.

DESCRIPTION DETAILLEE DE L'INVENTIONDETAILED DESCRIPTION OF THE INVENTION

La figure 2 illustre un système 21 d'injection d'air et de carburant d'une turbomachine selon un mode de réalisation de l'invention.There figure 2 illustrates an air and fuel injection system 21 of a turbomachine according to one embodiment of the invention.

Un tel système d'injection comprend un injecteur 22 et un dispositif mélangeur 25 disposé en aval de l'injecteur 22 selon une direction d'écoulement du carburant dans le système d'injection.Such an injection system comprises an injector 22 and a mixing device 25 arranged downstream of the injector 22 in a direction of flow of the fuel in the injection system.

On précise ici que l'amont et l'aval sont définis par rapport au sens de d'écoulement du carburant (de la gauche vers la droite sur la figure 2).We specify here that the upstream and downstream are defined in relation to the direction of fuel flow (from left to right on the figure 2 ).

L'injecteur 22 comprend une canalisation 23 d'amenée du carburant se terminant par un nez d'injection 24. Cette canalisation 23 est dans le prolongement d'un conduit amont et fait un coude avec ce dernier.The injector 22 comprises a fuel supply pipe 23 ending in an injection nose 24. This pipe 23 is an extension of an upstream conduit and makes an elbow with the latter.

La canalisation 23 s'étend de l'amont vers l'aval selon un axe longitudinal AA' du système d'injection d'air et de carburant. L'injecteur 22 comprend en outre une couronne 26 d'injection d'air, en aval de la canalisation 23. La couronne 26 d'injection d'air comprend une première vrille 261 et une deuxième vrille 262. La couronne 26 entoure le nez d'injection 24. Les première et deuxième vrilles de la couronne 25 d'injection d'air comprennent des passages d'air disposés tout autour.Pipeline 23 extends from upstream to downstream along a longitudinal axis AA' of the air and fuel injection system. The injector 22 further comprises an air injection crown 26, downstream of the pipe 23. The air injection crown 26 comprises a first twist 261 and a second twist 262. The crown 26 surrounds the nose injection 24. The first and second tendrils of the air injection crown 25 include air passages arranged all around.

Depuis la couronne 26 d'injection d'air s'étend une bague 28 de connexion de l'injecteur 22 au dispositif mélangeur 25. Cette bague 28 comprend une partie annulaire 281 qui est prolongée par une partie divergente 282 évasée vers l'aval. Le dispositif mélangeur 25 est disposé en aval de du nez d'injection 24. Le dispositif mélangeur 25 est notamment constitué d'un bol 27 comprenant une entrée annulaire 30 qui est prolongée par une partie conique 33 évasée vers l'aval. L'entrée annulaire 30 constitue l'entrée du dispositif mélangeurFrom the air injection crown 26 extends a ring 28 for connecting the injector 22 to the mixing device 25. This ring 28 comprises an annular part 281 which is extended by a divergent part 282 flared downstream. The mixing device 25 is arranged downstream of the injection nose 24. The mixing device 25 is in particular made up of a bowl 27 comprising an annular inlet 30 which is extended by a conical part 33 flared downstream. The annular inlet 30 constitutes the inlet of the mixing device

Ainsi, le dispositif mélangeur 25 définit une cavité annulaire 29 dans laquelle, en fonctionnement le mélange d'air et de carburant se fait.Thus, the mixing device 25 defines an annular cavity 29 in which, in operation, the mixture of air and fuel takes place.

En outre, l'injecteur est en partie disposé dans cette cavité annulaire 29.Furthermore, the injector is partly arranged in this annular cavity 29.

L'injecteur doit être en communication fluidique avec le dispositif mélangeur.The injector must be in fluid communication with the mixing device.

C'est par l'intermédiaire de la bague 28 de l'injecteur que l'injecteur 22 est en communication avec le dispositif mélangeur 25. La bague 28 de connexion est avantageusement disposée autour de l'entrée 30 du dispositif mélangeur 25. En outre, la bague 28 de connexion présente un diamètre interne supérieur à celui de l'entrée 30 du dispositif mélangeur 25 de façon à ce que cette bague 28 de connexion englobe l'entrée du dispositif mélangeur.It is via the ring 28 of the injector that the injector 22 is in communication with the mixing device 25. The connection ring 28 is advantageously arranged around the inlet 30 of the mixing device 25. In addition , the connection ring 28 has an internal diameter greater than that of the inlet 30 of the mixing device 25 so that this connection ring 28 encompasses the inlet of the mixing device.

De plus, comme cela est visible sur la figure 2, cette bague 28 est évasée vers l'aval afin de faciliter l'insertion de l'entrée dispositif mélangeur 25, au niveau du bol 27, dans la bague 28 de connexion au cours de l'assemblage de l'injecteur au dispositif mélangeur.Furthermore, as can be seen in the figure 2 , this ring 28 is flared downstream in order to facilitate the insertion of the mixing device inlet 25, at the level of the bowl 27, in the connection ring 28 during the assembly of the injector to the mixing device.

L'entrée 30 du dispositif mélangeur 25 comprend une surface externe 31 qui prend la forme d'une sphère tronquée et la bague 28 est en contact avec l'entrée du bol par l'intermédiaire de cette sphère tronquée. L'injecteur et le dispositif mélangeur présente au niveau de cette zone de contact une liaison qui autorise un déplacement relatif de l'injecteur par rapport au dispositif mélangeur. En particulier, L'injecteur et le dispositif mélangeur présente au niveau de cette zone de contact une liaison rotulante. Comme on l'aura compris, en comparaison avec l'agencement de l'art antérieur tel qu'illustré sur la figure 1, désormais la sphère se situe sur la surface externe de l'entrée 30 du dispositif mélangeur 25 et l'entrée 30 du dispositif mélangeur est située en aval du nez d'injection 24.The inlet 30 of the mixing device 25 comprises an external surface 31 which takes the form of a truncated sphere and the ring 28 is in contact with the inlet of the bowl via this truncated sphere. The injector and the mixing device present at this contact zone a connection which allows movement relative of the injector relative to the mixing device. In particular, the injector and the mixing device have a swivel connection at this contact zone. As will be understood, in comparison with the arrangement of the prior art as illustrated on the figure 1 , now the sphere is located on the external surface of the inlet 30 of the mixing device 25 and the inlet 30 of the mixing device is located downstream of the injection nose 24.

Comme on va le voir par la suite, cet agencement permet, au cours du fonctionnement du système d'injection, d'autoriser des déplacements relatifs de l'injecteur par rapport au dispositif mélangeur sans incidence sur le fonctionnement du système d'injection. En effet, comme présenté en introduction au cours du fonctionnement de la turbomachine le système d'injection est soumis à de très forts mouvements qui sont appliqués sur les différents éléments constituant le système d'injection.As will be seen later, this arrangement makes it possible, during the operation of the injection system, to authorize relative movements of the injector relative to the mixing device without affecting the operation of the injection system. Indeed, as presented in the introduction during the operation of the turbomachine the injection system is subjected to very strong movements which are applied to the different elements constituting the injection system.

De manière avantageuse, l'injecteur 22 comprend un venturi 32 situé axialement au voisinage du nez d'injection 24. Par rapport à l'agencement de l'art antérieur, on remarque ici que le venturi 32 fait partie de l'injecteur et non du dispositif mélangeur. Le venturi 32 est disposé entre les première et deuxième vrilles de la couronne 26 d'injection d'air de l'injecteur 22. Ainsi, à la différence avec l'agencement de l'art antérieur tel qu'illustré sur la figure 1, la tête d'injection est désormais axialement disposée au niveau du venturi 32 et est plus proche de l'entrée 30 du dispositif mélangeur. Le mélange est donc meilleur.Advantageously, the injector 22 comprises a venturi 32 located axially in the vicinity of the injection nose 24. Compared to the arrangement of the prior art, we note here that the venturi 32 is part of the injector and not of the mixing device. The venturi 32 is arranged between the first and second tendrils of the air injection crown 26 of the injector 22. Thus, unlike the arrangement of the prior art as illustrated in the figure 1 , the injection head is now axially arranged at the level of the venturi 32 and is closer to the inlet 30 of the mixing device. The mixture is therefore better.

De manière avantageuse, le conduit 23, la bague 28 et le venturi 32 sont formés d'une seule pièce, c'est-à-dire que toutes les pièces les constituant sont usinés dans la même pièce. Ces pièces peuvent être obtenues par un procédé de fabrication additives et sont de préférence monobloc. Également, la couronne d'injection d'air et la bague de connexion de l'injecteur sont formées d'une seule pièce de préférence obtenue par un procédé de fabrication additive.Advantageously, the conduit 23, the ring 28 and the venturi 32 are formed in one piece, that is to say that all the parts constituting them are machined in the same part. These parts can be obtained by an additive manufacturing process and are preferably in one piece. Also, the air injection crown and the injector connection ring are formed in a single piece, preferably obtained by an additive manufacturing process.

De préférence, l'entrée 30 du dispositif mélangeur est située dans le passage d'air de la deuxième vrille 262. En effet, comme on peut le voir sur la figure 2, l'air arrivant par la deuxième vrille 262 et guidée par le venturi va directement arrivée dans l'entrée 30 du dispositif mélangeur.Preferably, the inlet 30 of the mixing device is located in the air passage of the second swirl 262. Indeed, as can be seen in the figure 2 , the air arriving via the second spindle 262 and guided by the venturi will directly arrive in the inlet 30 of the mixing device.

Grâce au nouvel agencement des éléments du système d'injection, on constate que le fait d'avoir la liaison autorisant un déplacement entre l'injecteur et le dispositif mélangeur limite la zone de recirculation au niveau du venturi 32 et de fuite due aux usures (en particulier grâce à la liaison rotulante sur la surface externe de l'entrée du dispositif mélangeur et en aval du venturi). Désormais, les fuites vont débiter dans la vrilleThanks to the new arrangement of the elements of the injection system, we see that having the connection allowing movement between the injector and the mixing device limits the recirculation zone at the level of the venturi 32 and leakage due to wear ( in particular thanks to the ball joint on the external surface of the inlet of the mixing device and downstream of the venturi). From now on, the leaks will flow into the spin

Par ailleurs et de manière avantageuse, le nez d'injection 24 est agencé par rapport au venturi 32 de manière à ouvrir l'angle de spray de carburant au maximum sans impacter le venturi 32 ou le bol 27 tout en conservant une section de passage entre le nez 24 et le venturi 32. En effet, lorsque l'ensemble est monobloc il est plus facile de positionner les différents éléments les uns par rapport aux autres puisqu'on s'affranchit dans ce cas des déplacements relatifs entre les pièces. La figure 3a illustre le spray S de carburant issu du nez d'injection 24.Furthermore and advantageously, the injection nose 24 is arranged relative to the venturi 32 so as to open the fuel spray angle to the maximum without impacting the venturi 32 or the bowl 27 while maintaining a passage section between the nose 24 and the venturi 32. Indeed, when the assembly is in one piece it is easier to position the different elements in relation to each other since in this case we are freed from relative movements between the parts. There figure 3a illustrates the fuel spray S coming from the injection nose 24.

En outre, lorsque l'injecteur se déplace par rapport au dispositif mélangeur 25, le fait que le venturi et la couronne d'injection d'air soient formés avec l'injecteur alors, il n'y a pas obstructions au niveau de la couronne d'injection d'air, le fonctionnement du système d'injection n'est alors pas impacté par ces déplacements.Furthermore, when the injector moves relative to the mixing device 25, the fact that the venturi and the air injection crown are formed with the injector then, there are no obstructions at the level of the crown air injection, the operation of the injection system is then not impacted by these movements.

Les figures 3b et 3c illustrent deux cas de déplacement de l'injecteur par rapport au dispositif mélangeur. On voit de ces figures, que le venturi 32 et la couronne se déplace mais qu'elle n'est pas obstruée.THE figures 3b and 3c illustrate two cases of movement of the injector relative to the mixing device. We see from these figures that the venturi 32 and the crown move but that it is not obstructed.

Les dimensions des différents éléments sont fixées en fonction des marges de déplacement que l'on souhaite autoriserThe dimensions of the different elements are fixed according to the movement margins that we wish to authorize

Le système d'injection 22 ci-dessus décrit est avantageusement implémenté dans une chambre de combustion 40 d'une turbomachine telle qu'illustrée sur la figure 4.The injection system 22 described above is advantageously implemented in a combustion chamber 40 of a turbomachine as illustrated in the Figure 4 .

Claims (11)

  1. A turbomachine air and fuel injection system comprising:
    - an injector (22) comprising a pipe (23) and an injection nose (24) housed inside said pipe 23) extending from upstream to downstream along a longitudinal axis (AA');
    - a mixing device (25) comprising a bowl (27) comprising an annular inlet (30), forming the inlet of the mixing device, from which extends a downstream flared conical portion (33), said mixing device being housed downstream of the injection nose (24);
    the injector (22) comprising an air injection ring (26) extending from the pipe (23) and from which extends a connecting ring (28) comprising a diverging portion (282), said ring being disposed externally around the annular mixing device inlet (30), wherein the mixing device inlet (30) comprises an external surface (31), the injection system being characterised in that the connection ring (28) of the injector is in contact with the inlet (30) of the mixing device via the external surface (31) so as to allow relative movements of the injector (22) with respect to the mixing device (25).
  2. The injection system according to claim 1, in which the air injection ring is arranged downstream of the pipe (23).
  3. The injection system according to one of claims 1 to 2, in which the inlet (30) of the mixing device is arranged downstream of the injection nose (24).
  4. The injection system according to one of claims 1 to 3, in which the outer surface (31) takes the form of a truncated sphere, the connection ring (28) of the injector being in contact with the inlet (30) of the mixing device via the said truncated sphere.
  5. The injection system according to one of claims 1 to 4, wherein the injector (22) comprises a venturi (32) located axially at the level of the injection head.
  6. The injection system according to claim 5, comprising a first gimlet (261) arranged upstream of the venturi and a second gimlet (262) arranged downstream of the venturi (31), said first and second gimlets comprising air passages.
  7. The injection system according to claim 6, wherein the inlet (30) of the mixing device is located in the air passage of the second spinner (262).
  8. The injection system according to one of claims 6 to 7, wherein the injection nose, the venturi (32) and the air injection ring are formed in one piece, preferably obtained by an additive manufacturing process.
  9. The injection system according to one of the preceding claims, in which the air injection ring (26) and the injector connection ring (28) are formed from in one piece preferably obtained by an additive manufacturing process.
  10. Combustion chamber of a turbomachine comprising an injection system according to one of the preceding claims.
  11. A turbomachine comprising a combustion chamber according to claim 10.
EP20820511.2A 2019-11-26 2020-11-24 Air and fuel injection system for a turbomachine, combustion chamber comprising such a system, and associated turbomachine Active EP4065892B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1913223A FR3103540B1 (en) 2019-11-26 2019-11-26 Fuel injection system of a turbomachine, combustion chamber comprising such a system and associated turbomachine
PCT/FR2020/052164 WO2021105607A1 (en) 2019-11-26 2020-11-24 Fuel injection system for a turbomachine, combustion chamber comprising such a system, and associated turbomachine

Publications (2)

Publication Number Publication Date
EP4065892A1 EP4065892A1 (en) 2022-10-05
EP4065892B1 true EP4065892B1 (en) 2023-11-08

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Application Number Title Priority Date Filing Date
EP20820511.2A Active EP4065892B1 (en) 2019-11-26 2020-11-24 Air and fuel injection system for a turbomachine, combustion chamber comprising such a system, and associated turbomachine

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US (1) US11933497B2 (en)
EP (1) EP4065892B1 (en)
CN (1) CN114746699B (en)
FR (1) FR3103540B1 (en)
WO (1) WO2021105607A1 (en)

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FR2753779B1 (en) * 1996-09-26 1998-10-16 AERODYNAMIC INJECTION SYSTEM FOR A FUEL AIR MIXTURE
US6314739B1 (en) * 2000-01-13 2001-11-13 General Electric Company Brazeless combustor dome assembly
FR2859272B1 (en) * 2003-09-02 2005-10-14 Snecma Moteurs AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER HAVING MEANS FOR GENERATING COLD PLASMA
FR2875584B1 (en) * 2004-09-23 2009-10-30 Snecma Moteurs Sa EFFERVESCENCE INJECTOR FOR AEROMECHANICAL AIR / FUEL INJECTION SYSTEM IN A TURBOMACHINE COMBUSTION CHAMBER
FR2886714B1 (en) * 2005-06-07 2007-09-07 Snecma Moteurs Sa ANTI-ROTARY INJECTION SYSTEM FOR TURBO-REACTOR
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base
FR2899314B1 (en) * 2006-03-30 2008-05-09 Snecma Sa DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE
FR2903172B1 (en) * 2006-06-29 2008-10-17 Snecma Sa ARRANGEMENT FOR A TURBOMACHINE COMBUSTION CHAMBER HAVING A FLANGE FAULT
FR2903170B1 (en) * 2006-06-29 2011-12-23 Snecma DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE
FR2941288B1 (en) * 2009-01-16 2011-02-18 Snecma DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL IN A TURBOMACHINE COMBUSTION CHAMBER
BR112013028196B1 (en) * 2011-05-17 2021-06-22 Snecma ANNULAR COMBUSTION CHAMBER FOR A TURB MACHINE AND TURB MACHINE
FR2988813B1 (en) * 2012-03-29 2017-09-01 Snecma DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL IN A TURBOMACHINE COMBUSTION CHAMBER
FR3001283A1 (en) * 2013-01-18 2014-07-25 Snecma Part for injection system utilized for injecting air fuel mixture in combustion chamber of turboshaft engine of aircraft, has housing space arranged so as to allow slope of sliding bushing with regard to mixing bowl to be of specific angle
FR3029271B1 (en) * 2014-11-28 2019-06-21 Safran Aircraft Engines ANNULAR DEFLECTION WALL FOR TURBOMACHINE COMBUSTION CHAMBER INJECTION SYSTEM PROVIDING EXTENSIVE FUEL ATOMIZATION AREA
FR3033030B1 (en) * 2015-02-20 2018-04-13 Safran Aircraft Engines AIR-FUEL MIX INJECTION SYSTEM IN AN AIRCRAFT TURBOMACHINE COMBUSTION CHAMBER, COMPRISING A PERFORATED AIR INJECTION HOLES VENTURI
FR3040765B1 (en) * 2015-09-09 2017-09-29 Snecma SUPPORTING ELEMENT FOR DAMPING AXIAL MOVEMENTS OF SLIDING INJECTION SYSTEM FOR TURBOMACHINE
FR3081539B1 (en) * 2018-05-23 2021-06-04 Safran Aircraft Engines TURBOMACHINE COMBUSTION CHAMBER BOTTOM
FR3082284B1 (en) * 2018-06-07 2020-12-11 Safran Aircraft Engines COMBUSTION CHAMBER FOR A TURBOMACHINE

Also Published As

Publication number Publication date
FR3103540B1 (en) 2022-01-28
FR3103540A1 (en) 2021-05-28
WO2021105607A1 (en) 2021-06-03
EP4065892A1 (en) 2022-10-05
US20230003386A1 (en) 2023-01-05
CN114746699B (en) 2023-08-25
CN114746699A (en) 2022-07-12
US11933497B2 (en) 2024-03-19

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