EP3183498B1 - Connection device comprising several curved concentric tubes - Google Patents

Connection device comprising several curved concentric tubes Download PDF

Info

Publication number
EP3183498B1
EP3183498B1 EP15760219.4A EP15760219A EP3183498B1 EP 3183498 B1 EP3183498 B1 EP 3183498B1 EP 15760219 A EP15760219 A EP 15760219A EP 3183498 B1 EP3183498 B1 EP 3183498B1
Authority
EP
European Patent Office
Prior art keywords
connection device
tubes
ribs
tube
connection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP15760219.4A
Other languages
German (de)
French (fr)
Other versions
EP3183498A2 (en
Inventor
Christophe CHABAILLE
Sébastien LOVAL
Bénédicte LELEU
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3183498A2 publication Critical patent/EP3183498A2/en
Application granted granted Critical
Publication of EP3183498B1 publication Critical patent/EP3183498B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • the invention relates to a device making the connection of a turbomachine member, such as an injector of an aircraft turbomachine, with a fuel supply system.
  • the invention relates more particularly to a connection device comprising several concentric tubes bent identically.
  • An aircraft turbomachine comprises in particular a fuel supply system comprising an injector the purpose of which is to inject a certain quantity of fuel into the combustion chamber of the turbomachine.
  • the quantity of fuel injected depends on the operating conditions of the turbomachine.
  • An injector in particular of the aeromechanical type, comprises a first outlet, called primary, which is used during a starting phase of the turbomachine and a second outlet, called secondary, which is used after starting the turbomachine, and by which a large fuel flow is supplied.
  • the fuel system supplies several different fuel streams to the injector. Each of these different streams is associated with and supplies an output of the injector, that is to say a primary stream supplying the primary output, and a secondary stream supplying the secondary output.
  • a connection device is arranged between the injector and the supply system, to lead the various fuel flows through small spaces.
  • connection device comprises several concentric tubes which delimit several conduits through which the fuel flows circulate.
  • a connection device comprises three tubes which define three concentric conduits.
  • a first central duct is associated with the primary flow
  • a second radially intermediate duct is associated with the secondary flow
  • a third radially outer duct is associated with a fuel flow providing thermal protection of the primary and secondary fuel flows.
  • the tubes of the connection device are curved, or bent, to allow access to the location of the associated injector, taking into account the constraints of integration on the turbomachine.
  • the tubes are bent simultaneously.
  • helical springs are installed between the tubes, to keep the tubes at a distance from each other during bending operations.
  • the object of the invention is to provide a connection device making it possible to solve these problems.
  • US 2003/0182945 A1 shows a fuel injector for a turbomachine comprising two concentric tubes supplying the injector with fuel, the radially inner tube comprising longitudinal fins extending radially to the radially outer tube. These two concentric tubes extend inside a third concentric tube serving as a support for the injector and thermal protection for the concentric tubes.
  • US 2011/0247590 A1 and US 2009/0255602 A1 show fuel injectors for a turbomachine whose feed devices are made in one piece using a direct metal laser melting process.
  • the invention proposes a device for connecting an organ to a system for supplying the organ with fluid, the connecting device comprising three concentric tubes delimiting supply ducts for the organ, which are bent along at least a direction, in which the connection device is made in one piece comprising at least the tubes, the connection device further comprising two sets of radial ribs, the radial ribs of a first set of ribs connecting the outer surface of the radially inner tube to the inner surface of the radially intermediate tube and the radial ribs of the second set of ribs connecting the outer surface of the radially intermediate tube to the inner surface of the radially intermediate tube external, the radial ribs between two adjacent tubes extending along the central curve of the tubes over the entire length of said adjacent tubes and being made in one piece with said adjacent tubes.
  • fillets are formed at each radial end of each rib, at the level of the connection of said radial end of the rib with the facing wall of an associated tube.
  • connection device comprises a body for connecting the tubes with a fluid injection system, and said body is made in one piece with the tubes and the ribs.
  • the body has a mounting plate and fillets are formed at the connection between the outer surface of the radially outer tube and each surface of the plate.
  • connection device is produced by implementing a direct laser metal melting process.
  • the invention also relates to a fluid supply circuit for a turbomachine member such as a fuel injector for an aircraft turbomachine combustion chamber comprising a connection device according to the invention.
  • the invention also relates to an aircraft turbomachine comprising at least one member connected to a system for supplying the member with fluid by a connection device according to the invention.
  • circuit 10 for supplying fuel to a fuel injector (not shown) for an aircraft turbomachine combustion chamber.
  • This injector is designed to be able to selectively inject two separate streams of fuel. These fuel flows are a primary flow, which is injected during a start-up phase of the turbomachine and which is not very significant, and a larger secondary flow, which is injected when the turbomachine is in operation.
  • the supply circuit 10 also comprises a supply system 12 which distributes a single flow of fuel coming from a high pressure pump, into several different flows supplying the injector, and regulates the pressure and the flow rate of each of these. fuel flow.
  • the supply system 12 is connected to the injector by means of a connection device 14.
  • This connection device 14 comprises a body 16 which is connected to the supply system 12 and a pipe 18 extending from the body 16 to the injector.
  • the pipe 18 is shaped to circulate the various fuel flows in the direction of the injector.
  • the pipe 18 is divided into several concentric supply conduits 20, 22, 24, here three in number as can be seen in more detail at figure 2 .
  • the line 18 comprises a first radially internal duct 20 which is associated with the first fuel flow, a second radially intermediate duct 22 which is associated with the second fuel flow and a third radially external duct 24 which is associated with a stagnant fuel flow acting as a heat shield.
  • the purpose of this stagnant fuel in the third pipe 24 is to protect the other two fuel streams from heat, and thus in particular to avoid fuel coking phenomena inside the fuel injector.
  • the pipe 18 consists of several concentric tubes 26, 28, 30, three in number, which delimit the conduits 20, 22, 24.
  • the first conduit 20 is thus delimited by the radially internal tube 26
  • the second conduit 22 is delimited by the radially inner tube 26 and the intermediate tube 28
  • the third conduit 24 is delimited by the intermediate tube 28 and the radially outer tube 30.
  • the tubes 26, 28, 30 are connected to the body 16 of the connecting device 14.
  • the pipe 18 is curved, to allow the integration of the connection device on the turbomachine, taking into account the other components of the turbomachine located nearby. Consequently, the concentric tubes 26, 28, 30 are also bent in at least one direction.
  • the pipe 18 also comprises means for maintaining the tubes 26, 28, 30 at a distance from each other, which consist of a plurality of radial ribs 32.
  • Each rib 32 is bent identically to the pipe 18, that is to say it extends radially and along the central curve of the pipe 18 and the tubes 26, 28, 30, over the entire length. length of tubes 26, 28, 30.
  • the ribs 32 are located in the second duct 22 and in the third duct 24, thus forming two sets of ribs, the ribs 32 of the first set of ribs extending into the second duct 22, the ribs 32 of the second set of ribs 32 extending into the third duct 24.
  • each set of ribs has four ribs 32 distributed at 90 degrees. It will be understood that a set of ribs may include a different number of ribs 32 without departing from the invention.
  • the ribs 32 of the two sets of ribs are disposed around the central curve of the pipe 18 with two adjacent ribs 32 aligned.
  • the ribs 32 are all of the same thickness. According to an alternative embodiment, certain ribs 32 have a different thickness from the thickness of the other ribs 32, in order to locally modify the mechanical resistance to the pipe 18. Also, the thickness of a rib can vary along the central curve. of the pipeline 18.
  • Each radial end of each rib 32 comprises a surplus of material forming a fillet 34 at its connection with the associated face of a tube 26, 28, 30.
  • the purpose of these fillets 34 is to eliminate the sharp edges that may locally weaken the connection. between a rib and the wall facing a tube 26, 28, 30.
  • the body 16 of the connection device 14 comprises a cylindrical part 36 which is intended to receive a complementary part of the supply system 12 and which communicates separately with each of the conduits 20, 22, 24.
  • the body 16 comprises a mounting plate 38 for the connection device 14 on the turbomachine.
  • This fixing plate 38 extends around the radially outer tube 30 and fillets 40 are formed at the connection between the fixing plate 38 and the outer tube 30.
  • the tubes 26, 28, 30 are all made from a single piece of the same material.
  • connection device 14 the ribs 32 are made in one piece with the tubes 26, 28, 30.
  • the body 16 of the connection device is made in one piece with the tubes 26, 28, 30 and the ribs 32.
  • connection device 14 is made in one piece.
  • connection device 14 is produced by implementing a so-called direct laser metal melting process.
  • a so-called direct laser metal melting process consists in distributing a uniform layer of metal powder by means of a re-coating device, then in melting this layer at given locations corresponding to a section of the connecting device in a very controlled inert atmosphere. These operations are repeated several times until the connection device 14. Once completed, the connection device 14 is removed from the powder bed and subjected to heat treatment and finishing.
  • connection device 14 does not undergo any shaping step which would be complex to implement and would risk weakening it locally.
  • connection device 14 All the parts of the connection device 14 are made from a single material which is for example a Cobalt Chromium Molybdenum alloy or an alloy known under the name Inconel 718.
  • connection device 14 has the additional advantage that no sealing means is necessary between the different tubes 26, 28, 30 and the body 16 of the connection device, thus reducing the risk of leaks. fuel or accidental connection of two conduits 20, 22, 24.
  • connection device 14 is improved since it is possible to adapt the thickness of a tube 26, 28, 30 or of a rib 32 as a function of the stresses that it is subjected to.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Laser Beam Processing (AREA)
  • Quick-Acting Or Multi-Walled Pipe Joints (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Joints Allowing Movement (AREA)

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention concerne un dispositif réalisant le raccordement d'un organe de turbomachine, tel qu'un injecteur d'une turbomachine d'aéronef, avec un système d'alimentation en carburant.The invention relates to a device making the connection of a turbomachine member, such as an injector of an aircraft turbomachine, with a fuel supply system.

L'invention concerne plus particulièrement un dispositif de raccordement comportant plusieurs tubes concentriques cintrés à l'identique.The invention relates more particularly to a connection device comprising several concentric tubes bent identically.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

Une turbomachine d'aéronef comporte notamment un système d'alimentation en carburant comprenant un injecteur qui a pour but d'injecter une certaine quantité de carburant dans la chambre de combustion de la turbomachine. La quantité de carburant injectée dépend des conditions de fonctionnement de la turbomachine.An aircraft turbomachine comprises in particular a fuel supply system comprising an injector the purpose of which is to inject a certain quantity of fuel into the combustion chamber of the turbomachine. The quantity of fuel injected depends on the operating conditions of the turbomachine.

Un injecteur, en particulier de type aéromécanique, comprend une première sortie, dite primaire, qui est utilisée lors d'une phase de démarrage de la turbomachine et une deuxième sortie, dite secondaire, qui est utilisée après le démarrage de la turbomachine, et par laquelle un débit de carburant important est fourni.An injector, in particular of the aeromechanical type, comprises a first outlet, called primary, which is used during a starting phase of the turbomachine and a second outlet, called secondary, which is used after starting the turbomachine, and by which a large fuel flow is supplied.

Le système d'alimentation fourni plusieurs flux de carburant différents à l'injecteur. Chacun de ces différents flux est associé à et alimente une sortie de l'injecteur, c'est-à-dire un flux primaire alimentant la sortie primaire, et un flux secondaire alimentant la sortie secondaire.The fuel system supplies several different fuel streams to the injector. Each of these different streams is associated with and supplies an output of the injector, that is to say a primary stream supplying the primary output, and a secondary stream supplying the secondary output.

Un dispositif de raccordement est agencé entre l'injecteur et le système d'alimentation, pour conduire les différents flux de carburant au travers d'espaces réduits.A connection device is arranged between the injector and the supply system, to lead the various fuel flows through small spaces.

Du fait du faible espace disponible pour le cheminement des flux de carburant, le dispositif de raccordement comprend plusieurs tubes concentriques qui délimitent plusieurs conduits au travers desquels les flux de carburant circulent.Due to the small space available for the routing of the fuel flows, the connection device comprises several concentric tubes which delimit several conduits through which the fuel flows circulate.

De manière générale, un dispositif de raccordement comprend trois tubes qui délimitent trois conduits concentriques. Un premier conduit central est associé au flux primaire, un deuxième conduit radialement intermédiaire est associé au flux secondaire et un troisième conduit radialement externe est associé à un flux de carburant réalisant une protection thermique des flux de carburants primaire et secondaire.In general, a connection device comprises three tubes which define three concentric conduits. A first central duct is associated with the primary flow, a second radially intermediate duct is associated with the secondary flow and a third radially outer duct is associated with a fuel flow providing thermal protection of the primary and secondary fuel flows.

Les tubes du dispositif de raccordement sont courbés, ou cintrés, pour permettre d'accéder à l'emplacement de l'injecteur associé, en tenant compte des contraintes d'intégration sur la turbomachine.The tubes of the connection device are curved, or bent, to allow access to the location of the associated injector, taking into account the constraints of integration on the turbomachine.

Selon un mode de fabrication conventionnel, les tubes sont cintrés simultanément.According to a conventional manufacturing method, the tubes are bent simultaneously.

Pour cela, des ressorts hélicoïdaux sont installés entre les tubes, pour maintenir les tubes à distance les uns des autres lors des opérations de cintrage.For this, helical springs are installed between the tubes, to keep the tubes at a distance from each other during bending operations.

Cependant, il résulte de ces opérations de cintrage que l'épaisseur des tubes n'est pas constante sur toute leur longueur, des dispersions de fabrication ou bien des problèmes d'étanchéité.However, it results from these bending operations that the thickness of the tubes is not constant over their entire length, manufacturing dispersions or else sealing problems.

L'invention a pour but de proposer un dispositif de raccordement permettant de résoudre ces problèmes.The object of the invention is to provide a connection device making it possible to solve these problems.

US 2003/0182945 A1 montre un injecteur de carburant pour turbomachine comportant deux tubes concentriques alimentant l'injecteur en carburant, le tube radialement interne comprenant des ailettes longitudinales d'étendant radialement jusqu'au tube radialement externe. Ces deux tubes concentriques s'étendent à l'intérieur d'un troisième tube concentrique servant de support à l'injecteur et de protection thermique pour les tubes concentriques. US 2003/0182945 A1 shows a fuel injector for a turbomachine comprising two concentric tubes supplying the injector with fuel, the radially inner tube comprising longitudinal fins extending radially to the radially outer tube. These two concentric tubes extend inside a third concentric tube serving as a support for the injector and thermal protection for the concentric tubes.

US 2011/0247590 A1 et US 2009/0255602 A1 montrent des injecteurs de carburant pour turbomachine dont les dispositifs d'alimentation sont réalisés en une seule pièce à l'aide d'un procédé de fusion laser directe de métal. US 2011/0247590 A1 and US 2009/0255602 A1 show fuel injectors for a turbomachine whose feed devices are made in one piece using a direct metal laser melting process.

EXPOSÉ DE L'INVENTIONDISCLOSURE OF THE INVENTION

L'invention propose un dispositif de raccordement d'un organe à un système d'alimentation de l'organe en fluide, le dispositif de raccordement comportant trois tubes concentriques délimitant des conduits d'alimentation de l'organe, qui sont cintrés selon au moins une direction, dans lequel le dispositif de raccordement est réalisé en une seule pièce comportant au moins les tubes, le dispositif de raccordement comportant en outre deux ensembles de nervures radiales, les nervures radiales d'un premier ensemble de nervures reliant la surface externe du tube radialement interne à la surface interne du tube radialement intermédiaire et les nervures radiales du deuxième ensemble de nervures reliant la surface externe du tube radialement intermédiaire à la surface interne du tube radialement externe, les nervures radiales entre deux tubes adjacents s'étendant le long de la courbe centrale des tubes sur toute la longueur desdits tubes adjacents et étant réalisées d'une seule pièce avec lesdits tubes adjacents.The invention proposes a device for connecting an organ to a system for supplying the organ with fluid, the connecting device comprising three concentric tubes delimiting supply ducts for the organ, which are bent along at least a direction, in which the connection device is made in one piece comprising at least the tubes, the connection device further comprising two sets of radial ribs, the radial ribs of a first set of ribs connecting the outer surface of the radially inner tube to the inner surface of the radially intermediate tube and the radial ribs of the second set of ribs connecting the outer surface of the radially intermediate tube to the inner surface of the radially intermediate tube external, the radial ribs between two adjacent tubes extending along the central curve of the tubes over the entire length of said adjacent tubes and being made in one piece with said adjacent tubes.

De préférence, des congés sont formés à chaque extrémité radiale de chaque nervure, au niveau du raccordement de ladite extrémité radiale de la nervure avec la paroi en vis-à-vis d'un tube, associé.Preferably, fillets are formed at each radial end of each rib, at the level of the connection of said radial end of the rib with the facing wall of an associated tube.

De préférence, le dispositif de raccordement comporte un corps de raccordement des tubes avec un système d'injection de fluide, et ledit corps est réalisé d'une seule pièce avec les tubes et les nervures.Preferably, the connection device comprises a body for connecting the tubes with a fluid injection system, and said body is made in one piece with the tubes and the ribs.

De préférence, le corps comporte une platine de fixation et des congés sont formés au niveau du raccordement entre la surface externe du tube radialement externe et chaque surface de la platine.Preferably, the body has a mounting plate and fillets are formed at the connection between the outer surface of the radially outer tube and each surface of the plate.

De préférence, le dispositif de raccordement est réalisé par mise en œuvre d'un procédé de fusion laser directe de métal.Preferably, the connection device is produced by implementing a direct laser metal melting process.

L'invention concerne aussi un circuit d'alimentation en fluide d'un organe de turbomachine tel qu'un injecteur de carburant pour une chambre de combustion de turbomachine d'aéronef comportant un dispositif de raccordement selon l'invention.The invention also relates to a fluid supply circuit for a turbomachine member such as a fuel injector for an aircraft turbomachine combustion chamber comprising a connection device according to the invention.

L'invention concerne aussi une turbomachine d'aéronef comportant au moins un organe raccordé à un système d'alimentation de l'organe en fluide par un dispositif de raccordement selon l'invention.The invention also relates to an aircraft turbomachine comprising at least one member connected to a system for supplying the member with fluid by a connection device according to the invention.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée qui suit pour la compréhension de laquelle on se reportera aux figures annexées parmi lesquelles :

  • la figure 1 est une représentation schématique en perspective d'un circuit d'alimentation en carburant d'un injecteur comportant un dispositif de raccordement selon l'invention ;
  • la figure 2 est une vue en coupe radiale du dispositif de raccordement montrant les différents tubes et les nervures radiales ; et
  • la figure 3 est une vue en coupe axiale du dispositif de raccordement montrant le corps du dispositif de raccordement avec les tubes.
Other characteristics and advantages of the invention will become apparent on reading the detailed description which follows, for the understanding of which reference is made to the appended figures, among which:
  • the figure 1 is a schematic perspective representation of a fuel supply circuit for an injector comprising a connection device according to the invention;
  • the figure 2 is a radial sectional view of the connecting device showing the various tubes and the radial ribs; and
  • the figure 3 is an axial sectional view of the connection device showing the body of the connection device with the tubes.

EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

On a représenté à la figure 1 un circuit 10 d'alimentation en carburant d'un injecteur de carburant (non représenté) pour une chambre de combustion de turbomachine d'aéronef.We have represented at the figure 1 a circuit 10 for supplying fuel to a fuel injector (not shown) for an aircraft turbomachine combustion chamber.

Cet injecteur est conçu pour pouvoir injecteur de manière sélective deux flux distincts de carburant. Ces flux de carburant sont un flux primaire, qui est injecté lors d'une phase de démarrage de la turbomachine et qui est peu important, et un flux secondaire plus important, qui est injecté lorsque la turbomachine est en fonctionnement.This injector is designed to be able to selectively inject two separate streams of fuel. These fuel flows are a primary flow, which is injected during a start-up phase of the turbomachine and which is not very significant, and a larger secondary flow, which is injected when the turbomachine is in operation.

Les spécificités de chacun des deux flux de carburant étant différentes, ces deux flux sont par conséquent séparés autant au niveau de la sortie de l'injecteur que dans tout le circuit d'alimentation 10.The specificities of each of the two fuel flows being different, these two flows are consequently separated as much at the level of the outlet of the injector as in the entire supply circuit 10.

Le circuit d'alimentation 10 comporte aussi un système d'alimentation 12 qui répartit un flux unique de carburant en provenance d'une pompe haute pression, en plusieurs flux différents alimentant l'injecteur, et régule la pression et le débit de chacun de ces flux de carburant.The supply circuit 10 also comprises a supply system 12 which distributes a single flow of fuel coming from a high pressure pump, into several different flows supplying the injector, and regulates the pressure and the flow rate of each of these. fuel flow.

Le système d'alimentation 12 est relié à l'injecteur par l'intermédiaire d'un dispositif de raccordement 14.The supply system 12 is connected to the injector by means of a connection device 14.

Ce dispositif de raccordement 14 comporte un corps 16 qui est relié au système d'alimentation 12 et une canalisation 18 s'étendant depuis le corps 16 jusqu'à l'injecteur.This connection device 14 comprises a body 16 which is connected to the supply system 12 and a pipe 18 extending from the body 16 to the injector.

La canalisation 18 est conformée pour faire circuler les différents flux de carburant en direction de l'injecteur. Pour cela, la canalisation 18 est divisée en plusieurs conduits d'alimentation concentriques 20, 22, 24, ici au nombre de trois comme on peut le voir plus en détails à la figure 2.The pipe 18 is shaped to circulate the various fuel flows in the direction of the injector. For this, the pipe 18 is divided into several concentric supply conduits 20, 22, 24, here three in number as can be seen in more detail at figure 2 .

La canalisation 18 comporte un premier conduit 20 radialement interne qui est associé au premier flux de carburant, un deuxième conduit 22 radialement intermédiaire qui est associé au deuxième flux de carburant et un troisième conduit 24 radialement externe qui est associé à un flux de carburant stagnant agissant en tant qu'écran thermique. Ce carburant stagnant dans le troisième conduit 24 a pour but de protéger les deux autres flux de carburant de la chaleur, et ainsi d'éviter notamment des phénomènes de cokéfaction du carburant à l'intérieur de l'injecteur carburant.The line 18 comprises a first radially internal duct 20 which is associated with the first fuel flow, a second radially intermediate duct 22 which is associated with the second fuel flow and a third radially external duct 24 which is associated with a stagnant fuel flow acting as a heat shield. The purpose of this stagnant fuel in the third pipe 24 is to protect the other two fuel streams from heat, and thus in particular to avoid fuel coking phenomena inside the fuel injector.

La canalisation 18 est constituée de plusieurs tubes concentriques 26, 28, 30, au nombre de trois, qui délimitent les conduits 20, 22, 24. Le premier conduit 20 est ainsi délimité par le tube 26 radialement interne, le deuxième conduit 22 est délimité par le tube 26 radialement interne et le tube 28 intermédiaire et le troisième conduit 24 est délimité par le tube intermédiaire 28 et le tube radialement externe 30.The pipe 18 consists of several concentric tubes 26, 28, 30, three in number, which delimit the conduits 20, 22, 24. The first conduit 20 is thus delimited by the radially internal tube 26, the second conduit 22 is delimited by the radially inner tube 26 and the intermediate tube 28 and the third conduit 24 is delimited by the intermediate tube 28 and the radially outer tube 30.

Les tubes 26, 28, 30 sont reliés au corps 16 du dispositif de raccordement 14.The tubes 26, 28, 30 are connected to the body 16 of the connecting device 14.

La canalisation 18 est cintrée, pour permettre l'intégration du dispositif de raccordement sur la turbomachine en tenant compte des autres composants de la turbomachine situés à proximité. Par conséquent les tubes concentriques 26, 28, 30 sont cintrés eux aussi selon au moins une direction.The pipe 18 is curved, to allow the integration of the connection device on the turbomachine, taking into account the other components of the turbomachine located nearby. Consequently, the concentric tubes 26, 28, 30 are also bent in at least one direction.

La canalisation 18 comporte aussi des moyens pour maintenir les tubes 26, 28, 30 à distance les uns des autres, qui consistent en une pluralité de nervures radiales 32.The pipe 18 also comprises means for maintaining the tubes 26, 28, 30 at a distance from each other, which consist of a plurality of radial ribs 32.

Chaque nervure 32 est cintrée de manière identique à la canalisation 18, c'est-à-dire qu'elle s'étend radialement et le long de la courbe centrale de la canalisation 18 et des tubes 26, 28, 30, sur toute la longueur des tubes 26, 28, 30.Each rib 32 is bent identically to the pipe 18, that is to say it extends radially and along the central curve of the pipe 18 and the tubes 26, 28, 30, over the entire length. length of tubes 26, 28, 30.

Les nervures 32 sont situées dans le deuxième conduit 22 et dans le troisième conduit 24, formant ainsi deux ensembles de nervures, les nervures 32 du premier ensemble de nervures s'étendant dans le deuxième conduit 22, les nervures 32 du deuxième ensemble de nervures 32 s'étendant dans le troisième conduit 24.The ribs 32 are located in the second duct 22 and in the third duct 24, thus forming two sets of ribs, the ribs 32 of the first set of ribs extending into the second duct 22, the ribs 32 of the second set of ribs 32 extending into the third duct 24.

Ici, chaque ensemble de nervures comporte quatre nervures 32 réparties à 90 degrés. Il sera compris qu'un ensemble de nervures peut comporter un nombre différent de nervures 32 sans s'éloigner de l'invention.Here, each set of ribs has four ribs 32 distributed at 90 degrees. It will be understood that a set of ribs may include a different number of ribs 32 without departing from the invention.

Aussi, les nervures 32 des deux ensembles de nervures sont disposées autour de la courbe centrale de la canalisation 18 avec deux nervures 32 adjacentes alignées.Also, the ribs 32 of the two sets of ribs are disposed around the central curve of the pipe 18 with two adjacent ribs 32 aligned.

Selon le mode de réalisation représenté aux figures, les nervures 32 sont toutes de même épaisseur. Selon une variante de réalisation, certaines nervures 32 ont une épaisseur différente de l'épaisseur des autres nervures 32, pour modifier localement la résistance mécanique à la canalisation 18. Aussi, l'épaisseur d'une nervure peut varier le long de la courbe centrale de la canalisation 18.According to the embodiment shown in the figures, the ribs 32 are all of the same thickness. According to an alternative embodiment, certain ribs 32 have a different thickness from the thickness of the other ribs 32, in order to locally modify the mechanical resistance to the pipe 18. Also, the thickness of a rib can vary along the central curve. of the pipeline 18.

Chaque extrémité radiale de chaque nervure 32 comprend un surplus de matière formant congé 34 au niveau de sa liaison avec la face associée d'un tube 26, 28, 30. Ces congés 34 ont pour but de supprimer les arêtes vives pouvant fragiliser localement la liaison entre une nervure et la paroi en vis-à-vis d'un tube 26, 28, 30.Each radial end of each rib 32 comprises a surplus of material forming a fillet 34 at its connection with the associated face of a tube 26, 28, 30. The purpose of these fillets 34 is to eliminate the sharp edges that may locally weaken the connection. between a rib and the wall facing a tube 26, 28, 30.

Le corps 16 du dispositif de raccordement 14 comprend une partie cylindrique 36 qui est destinée à recevoir une partie complémentaire du système d'alimentation 12 et qui communique de manière séparée avec chacun des conduits 20, 22, 24.The body 16 of the connection device 14 comprises a cylindrical part 36 which is intended to receive a complementary part of the supply system 12 and which communicates separately with each of the conduits 20, 22, 24.

Le corps 16 comporte une platine de fixation 38 du dispositif de raccordement 14 sur la turbomachine. Cette platine de fixation 38 s'étend autour du tube 30 radialement externe et des congés 40 sont formés au niveau du raccordement entre la platine de fixation 38 et le tube externe 30.The body 16 comprises a mounting plate 38 for the connection device 14 on the turbomachine. This fixing plate 38 extends around the radially outer tube 30 and fillets 40 are formed at the connection between the fixing plate 38 and the outer tube 30.

De préférence, les tubes 26, 28, 30 sont tous réalisés en une seule pièce d'un même matériau.Preferably, the tubes 26, 28, 30 are all made from a single piece of the same material.

Selon un autre aspect du dispositif de raccordement 14, les nervures 32 sont réalisées en une pièce avec les tubes 26, 28, 30.According to another aspect of the connection device 14, the ribs 32 are made in one piece with the tubes 26, 28, 30.

Selon encore un autre aspect du dispositif de raccordement 14, le corps 16 du dispositif de raccordement, est réalisé en une pièce avec les tubes 26, 28, 30 et les nervures 32.According to yet another aspect of the connection device 14, the body 16 of the connection device is made in one piece with the tubes 26, 28, 30 and the ribs 32.

Ainsi, selon un mode de réalisation préféré de l'invention, la totalité du dispositif de raccordement 14 est réalisé en une seule pièce.Thus, according to a preferred embodiment of the invention, the entire connection device 14 is made in one piece.

Selon un mode de réalisation préféré, le dispositif de raccordement 14 est réalisé par la mise en œuvre d'un procédé dit de fusion laser directe de métal. Un tel procédé consiste à répartir une couche uniforme de poudre métallique au moyen d'un dispositif de ré-enduction, puis à faire fondre cette couche à des emplacements donnés correspondant à une section du dispositif de raccordement dans une atmosphère inerte très contrôlée. Ces opérations sont répétées plusieurs fois jusqu'à l'obtention du dispositif de raccordement 14. Une fois terminé, le dispositif de raccordement 14 est retiré du lit de poudre et soumis à un traitement thermique et à une finition.According to a preferred embodiment, the connection device 14 is produced by implementing a so-called direct laser metal melting process. Such a method consists in distributing a uniform layer of metal powder by means of a re-coating device, then in melting this layer at given locations corresponding to a section of the connecting device in a very controlled inert atmosphere. These operations are repeated several times until the connection device 14. Once completed, the connection device 14 is removed from the powder bed and subjected to heat treatment and finishing.

Ainsi, le dispositif de raccordement 14 ne subit aucune étape de mise en forme qui serait complexe à mettre en œuvre et risquerait de le fragiliser localement.Thus, the connection device 14 does not undergo any shaping step which would be complex to implement and would risk weakening it locally.

Toutes les parties du dispositif de raccordement 14 sont réalisées dans un seul matériau qui est par exemple un alliage Cobalt Chrome Molybdène ou un alliage connu sous la dénomination Inconel 718.All the parts of the connection device 14 are made from a single material which is for example a Cobalt Chromium Molybdenum alloy or an alloy known under the name Inconel 718.

Un tel mode de réalisation du dispositif de raccordement 14 présente l'avantage supplémentaire qu'aucun moyen d'étanchéité n'est nécessaire entre les différents tubes 26, 28, 30 et le corps 16 du dispositif de raccordement, réduisant ainsi les risques de fuites de carburant ou de mise en communication accidentelle de deux conduits 20, 22, 24.Such an embodiment of the connection device 14 has the additional advantage that no sealing means is necessary between the different tubes 26, 28, 30 and the body 16 of the connection device, thus reducing the risk of leaks. fuel or accidental connection of two conduits 20, 22, 24.

Aussi, la solidité du dispositif de raccordement 14 est améliorée puisqu'il est possible d'adapter l'épaisseur d'un tube 26, 28, 30 ou d'une nervure 32 en fonction des contraintes qu'il/elle subit.Also, the strength of the connection device 14 is improved since it is possible to adapt the thickness of a tube 26, 28, 30 or of a rib 32 as a function of the stresses that it is subjected to.

Claims (7)

  1. A connection device (14) for connecting a member to a system for supplying the member with fluid, the connection device (14) including three concentric tubes (26, 28, 30) delimiting conduits (20, 22, 24) for supplying the member, which are curved along at least one direction,
    wherein the connection (14) device is made as a single piece including at least the tubes (26, 28, 30),
    the connection device (14) further two sets of radial ribs (32), the radial ribs (32) of a first set of ribs (32) connecting the outer surface of the radially inner tube (26) to the inner surface of the radially intermediate tube (28) and the radial ribs (32) of the second set of ribs (32) connecting the outer surface of the radially intermediate tube (28) to the inner surface of the radially outer tube (30),
    the radial ribs (32) between two adjacent tubes (26, 28, 30) extending along the central curve of the tubes (26, 28, 30) over the entire length of said adjacent tubes (26, 28, 30) and being made as a single piece with said adjacent tubes (26, 28, 30).
  2. The connection device (14) according to claim 1, wherein fillets (34) are formed at each radial end of each rib (32), at the connection of said radial end of the rib (32) with the facing wall of an associated tube (26, 28, 30).
  3. The connection device (14) according to any of the preceding claims, including a body (16) for connecting the tubes (26, 28, 30) with a fluid injecting system, said body (16) being made as a single piece with the tubes (26, 28, 30) and the ribs (32).
  4. The connection device (14) according to the preceding claim, wherein the body (16) includes a securing plate (38) and fillets (40) are formed at the connection between the outer surface of the radially outer tube (30) and each surface of the plate (38).
  5. The connection device (14) according to any of the preceding claims, said connection device (14) being made by implementing a direct metal laser fusion method.
  6. A circuit (10) for supplying with fluid a turbomachine member such as a fuel injector for a combustion chamber of an aircraft turbomachine including a connection device (14) according to any of the preceding claims.
  7. An aircraft turbomachine including at least one member connected to a system for supplying the member with fluid by a connection device (14) according to any of claims 1 to 5.
EP15760219.4A 2014-08-20 2015-08-19 Connection device comprising several curved concentric tubes Active EP3183498B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1457895A FR3025017B1 (en) 2014-08-20 2014-08-20 CONNECTING DEVICE COMPRISING SEVERAL CONCENTRIC TUBES HANGERS
PCT/FR2015/052224 WO2016027034A2 (en) 2014-08-20 2015-08-19 Connection device comprising several curved concentric tubes

Publications (2)

Publication Number Publication Date
EP3183498A2 EP3183498A2 (en) 2017-06-28
EP3183498B1 true EP3183498B1 (en) 2021-07-07

Family

ID=52003975

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15760219.4A Active EP3183498B1 (en) 2014-08-20 2015-08-19 Connection device comprising several curved concentric tubes

Country Status (8)

Country Link
US (1) US11022312B2 (en)
EP (1) EP3183498B1 (en)
CN (1) CN106662330A (en)
BR (1) BR112017003212B1 (en)
CA (1) CA2958025C (en)
FR (1) FR3025017B1 (en)
RU (1) RU2703285C2 (en)
WO (1) WO2016027034A2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3078142B1 (en) 2018-02-22 2020-03-20 Safran Aircraft Engines COMBUSTION CHAMBER COMPRISING TWO TYPES OF INJECTORS IN WHICH THE SEALING COMPONENTS HAVE A DIFFERENT OPENING THRESHOLD
FR3091332B1 (en) 2018-12-27 2021-01-29 Safran Aircraft Engines Turbomachine injector nose comprising a secondary fuel spiral with progressive section

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440546A (en) * 2006-08-04 2008-02-06 Rolls Royce Plc Fluid carrying arrangement and its manufacture using a solid freeform fabrication process
US20090255262A1 (en) * 2008-04-11 2009-10-15 General Electric Company Fuel nozzle
EP2963347A1 (en) * 2014-07-03 2016-01-06 United Technologies Corporation Tube assembly
EP2962790A1 (en) * 2014-07-03 2016-01-06 United Technologies Corporation Additive manufactured tube assembly

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2700720C2 (en) * 1976-08-27 1982-06-24 Mitsubishi Denki K.K., Tokyo Arc joint welding method
US4735044A (en) * 1980-11-25 1988-04-05 General Electric Company Dual fuel path stem for a gas turbine engine
IL70892A (en) * 1984-02-07 1988-08-31 Rinkewich Isaac Water irrigation apparatus and pipe construction particularly useful therein
DE19712591A1 (en) * 1997-03-26 1998-10-01 Bosch Gmbh Robert Fuel injector and method for manufacturing and using a fuel injector
US5918628A (en) * 1997-06-17 1999-07-06 Parker-Hannifin Corporation Multi-stage check valve
CN1232721C (en) * 1998-12-28 2005-12-21 陈伯禄 Turbine engine utilizing both fuel gas and steam and its heat exchanger
US6358041B1 (en) * 2000-04-21 2002-03-19 Eastman Chemical Company Threaded heat shield for burner nozzle face
US6915638B2 (en) * 2002-03-28 2005-07-12 Parker-Hannifin Corporation Nozzle with fluted tube
CN2597804Y (en) * 2002-10-15 2004-01-07 许文芳 Gas pipeline jointing part with elastic pressing spacer
US8443608B2 (en) * 2008-02-26 2013-05-21 Delavan Inc Feed arm for a multiple circuit fuel injector
US8061142B2 (en) * 2008-04-11 2011-11-22 General Electric Company Mixer for a combustor
US7832377B2 (en) * 2008-09-19 2010-11-16 Woodward Governor Company Thermal protection for fuel injectors
US20110247590A1 (en) * 2010-04-07 2011-10-13 Delavan Inc Injectors utilizing lattice support structure
CN101812404B (en) * 2010-04-27 2013-09-04 惠识瑶 Fluidized bed type cell reactor circulating outside tank and method for cultivating animal cells
CN102654079A (en) * 2012-04-18 2012-09-05 周耀瑜 Technical scheme of intermittent inflating turbine engine
US20130312946A1 (en) * 2012-05-24 2013-11-28 Kellogg Brown & Root Llc Methods and Systems for Cooling Hot Particulates
FR3003013B1 (en) 2013-03-05 2016-07-29 Snecma COMPACT DOSING DEVICE FOR TWO FUEL CIRCUIT INJECTOR, PREFERABLY FOR AIRCRAFT TURBOMACHINE

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440546A (en) * 2006-08-04 2008-02-06 Rolls Royce Plc Fluid carrying arrangement and its manufacture using a solid freeform fabrication process
US20090255262A1 (en) * 2008-04-11 2009-10-15 General Electric Company Fuel nozzle
EP2963347A1 (en) * 2014-07-03 2016-01-06 United Technologies Corporation Tube assembly
EP2962790A1 (en) * 2014-07-03 2016-01-06 United Technologies Corporation Additive manufactured tube assembly

Also Published As

Publication number Publication date
RU2017108764A (en) 2018-09-23
WO2016027034A3 (en) 2016-06-23
FR3025017A1 (en) 2016-02-26
FR3025017B1 (en) 2016-09-30
EP3183498A2 (en) 2017-06-28
CN106662330A (en) 2017-05-10
RU2017108764A3 (en) 2019-02-21
BR112017003212B1 (en) 2023-05-02
WO2016027034A2 (en) 2016-02-25
CA2958025C (en) 2023-05-16
RU2703285C2 (en) 2019-10-16
US20170234539A1 (en) 2017-08-17
US11022312B2 (en) 2021-06-01
BR112017003212A2 (en) 2017-11-21
CA2958025A1 (en) 2016-02-25

Similar Documents

Publication Publication Date Title
EP2026002B1 (en) Multi-point injector for turbomachine
FR3078550A1 (en) POWER SUPPLY ARM FOR FUEL INJECTOR WITH MULTIPLE CIRCUITS
CA2864629C (en) Fuel injector for a turbomachine
CA2776843C (en) Multi-point injector for a turbine engine combustion chamber
FR3036437A1 (en) TURBOMACHINE ASSEMBLY FOR LUBRICATING A BEARING SUPPORT
EP1911936B1 (en) Transition channel between two turbine stages
EP3183498B1 (en) Connection device comprising several curved concentric tubes
FR3058460A1 (en) CONNECTION ASSEMBLY FOR COOLING TURBOMACHINE TURBINE
FR2733581A1 (en) COMBUSTION ENCLOSURE WITH COOLING BY TRANSPIRATION
EP3465010B1 (en) Fuel injector for turbo-machine
EP3052861B1 (en) Fuel injector for a turbomachine
EP1482127A1 (en) Sealing system for the bypass flow at the inlet of the afterburner nozzle of a turbomachine
CA2952329C (en) Assembly for turbomachine combustion chamber comprising a boss and an annular element
CA2576704C (en) Manufacture of a combustion chamber
FR3021351B1 (en) TURBOMACHINE WALL HAVING AT LEAST ONE PORTION OF COOLING ORIFICES OBSTRUCTIONS
EP1538306A1 (en) Joining device between a vane and its cooling fluid supply in a turbomachine
FR3054000A1 (en) DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE
FR3072448B1 (en) TURBOMACHINE COMBUSTION CHAMBER
FR3017928B1 (en) TURBOMACHINE WITH EXTERNAL FLANGE OF "SANDWICH" COMBUSTION CHAMBER
WO2016193596A1 (en) Device for cooling a rolling bearing for a turbine engine
EP3847342B1 (en) Pressurized-air supply unit for an air-jet cooling device
FR3033598A1 (en) PREHEATING CANDLE FOR A FLEX FUEL SUPPLY SYSTEM
WO2023105146A1 (en) Fuel distribution assembly for a turbomachine
FR3084698A1 (en) HEAT EXCHANGER FOR TURBOMACHINE
FR3047768A1 (en) DEVICE FOR CONNECTING AND SEALING BETWEEN TWO MODULES OF AN EXHAUST DUCT FROM A TURBOMACHINE

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170223

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20190725

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20210205

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1408956

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210715

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602015071101

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210707

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1408956

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210707

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211007

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211007

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211108

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211008

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602015071101

Country of ref document: DE

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210819

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

26N No opposition filed

Effective date: 20220408

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210819

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150819

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230720

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230720

Year of fee payment: 9

Ref country code: DE

Payment date: 20230720

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210707