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EP3183498A2 - Connection device comprising several curved concentric tubes - Google Patents

Connection device comprising several curved concentric tubes

Info

Publication number
EP3183498A2
EP3183498A2 EP15760219.4A EP15760219A EP3183498A2 EP 3183498 A2 EP3183498 A2 EP 3183498A2 EP 15760219 A EP15760219 A EP 15760219A EP 3183498 A2 EP3183498 A2 EP 3183498A2
Authority
EP
European Patent Office
Prior art keywords
tubes
ribs
connection device
connecting device
tube
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.)
Granted
Application number
EP15760219.4A
Other languages
German (de)
French (fr)
Other versions
EP3183498B1 (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

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 providing 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 curved identically.
  • An aircraft turbomachine comprises in particular a fuel supply system comprising an injector which is intended to inject a certain amount of fuel into the combustion chamber of the turbomachine.
  • the amount of fuel injected depends on the operating conditions of the turbomachine.
  • An injector in particular of the aeromechanical type, comprises a first, so-called primary, output which is used during a start-up phase of the turbomachine and a second, so-called secondary, output which is used after the starting of the turbomachine, and by which a large fuel flow is provided.
  • the fuel system supplied several different fuel streams to the injector. Each of these different flows is associated with and supplies an output of the injector, that is to say a primary flow supplying the primary output, and a secondary flow supplying the secondary output.
  • a connecting device is arranged between the injector and the supply system, to drive the different fuel flows through small spaces. Due to the small space available for the flow of fuel flow, the connection device comprises several concentric tubes which delimit several ducts through which fuel flows.
  • a connection device comprises three tubes which delimit three concentric ducts.
  • 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 connecting device are curved, or bent, to allow access to the location of the associated injector, taking into account the integration constraints on the turbomachine.
  • the tubes are bent simultaneously.
  • helical springs are installed between the tubes, to keep the tubes apart from one another during bending operations.
  • the object of the invention is to propose a connection device making it possible to solve these problems.
  • the invention proposes a device for connecting an organ to a system for supplying the fluid member, the connection device comprising a plurality of concentric tubes delimiting supply ducts for the organ, which are bent according to at least a direction, characterized in that it is made in one piece comprising at least the tubes.
  • the connecting device comprises at least one radial rib extending between two adjacent tubes, which extends along the central curve of the tubes over the entire length of said adjacent tubes.
  • each rib is made in one piece with said adjacent tubes.
  • the connecting device comprises three concentric tubes and two sets of ribs the 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 ribs of the second set of ribs connecting the outer surface of the radially intermediate tube to the inner surface of the radially outer tube.
  • fillets are formed at each radial end of each rib, at the connection of said radial end of the rib with the wall vis-à-vis a tube, associated.
  • the connecting device comprises a connecting body of the tubes with a fluid injection system, and said body is made in one piece with the tubes and the ribs.
  • the body comprises a fixing plate and fillets are formed at the connection between the outer surface of the radially outer tube and each surface of the plate.
  • the connecting device is made by implementing a method of direct laser melting of metal.
  • the invention also relates to a fluid supply circuit of a turbomachine member such as a fuel injector for an aircraft turbomachine combustion chamber, characterized in that it comprises a connection device according to the invention. .
  • the invention also relates to an aircraft turbomachine comprising at least one member connected to a supply system of the fluid member by a connecting device according to the invention.
  • Figure 1 is a schematic perspective view of a fuel supply circuit of an injector comprising a connecting device according to the invention
  • Figure 2 is a radial sectional view of the connecting device showing the various tubes and the radial ribs;
  • Figure 3 is an axial sectional view of the connecting device showing the body of the connecting device with the tubes.
  • FIG. 1 shows a circuit 10 for supplying fuel to a fuel injector (not shown) for an aircraft turbomachine combustion chamber.
  • This injector is designed to selectively inject two separate streams of fuel. These fuel flows are a primary flow, which is injected during a startup phase of the turbomachine and which is small, 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 from a high pressure pump, in several different flows feeding the injector, and regulates the pressure and the flow of each of these. fuel flow.
  • the supply system 12 is connected to the injector via a connection device 14.
  • This connecting 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 different fuel flows towards the injector.
  • the pipe 18 is divided into several concentric supply pipes 20, 22, 24, here three in number as can be seen in more detail in Figure 2.
  • the pipe 18 comprises a first radially inner conduit 20 which is associated with the first fuel flow, a second radially intermediate conduit 22 which is associated with the second fuel flow and a third radially external conduit 24 which is associated with a stagnant fuel flow acting as a thermal screen.
  • This stagnant fuel in the third conduit 24 is intended to protect the other two fuel streams from heat, and thus to avoid particular phenomena of coking the fuel inside the fuel injector.
  • the pipe 18 consists of several concentric tubes 26, 28, 30, three in number, which delimit the ducts 20, 22, 24.
  • the first duct 20 is thus delimited by the radially inner tube 26, the second duct 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.
  • the tubes 26, 28, 30 are connected to the body 16 of the connection device 14.
  • the pipe 18 is bent, to allow the integration of the connection device on the turbomachine taking into account the other components of the turbomachine located nearby.
  • the concentric tubes 26, 28, 30 are also bent in at least one direction.
  • the pipe 18 also has means for keeping 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 of the 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 in the second duct 22, the ribs 32 of the second set of ribs 32 extending into the third conduit 24.
  • each set of ribs has four ribs 32 distributed at 90 degrees. It will be understood that a set of ribs may comprise a different number of ribs 32 without departing from the invention.
  • the ribs 32 of the two sets of ribs are arranged 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, some ribs 32 have a thickness different from the thickness of the other ribs 32, to locally modify the mechanical strength to the pipe 18. Also, the thickness of a rib may vary along the central curve of the pipeline 18.
  • Each radial end of each rib 32 comprises a surplus of material forming leave 34 at its connection with the associated face of a tube 26, 28, 30.
  • These leaves 34 are intended to remove sharp edges that may locally weaken the connection between a rib and the wall vis-à-vis a tube 26, 28, 30.
  • the body 16 of the connecting device 14 comprises a cylindrical portion 36 which is intended to receive a complementary part of the supply system 12 and which communicates separately with each of the ducts 20, 22, 24.
  • the body 16 includes a mounting plate 38 of the connecting device 14 on the turbomachine.
  • This mounting 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 in one piece of the same material.
  • the ribs 32 are made in one piece with the tubes 26, 28, 30.
  • the body 16 of the connecting device is made in one piece with the tubes 26, 28, 30 and the ribs 32.
  • the entire connecting device 14 is made in one piece.
  • the connecting device 14 is produced by the implementation of a so-called direct metal laser melting process.
  • a so-called direct metal laser melting process consists of distributing a uniform layer of metal powder by means of a re-coating device, then melting this layer at given locations corresponding to a section of the connection device in a highly controlled inert atmosphere. These operations are repeated several times until the connection device 14 is obtained. Once completed, the connection device 14 is removed from the powder bed and subjected to heat treatment and finishing.
  • connection device 14 undergoes no formatting step that would be complex to implement and may weaken locally.
  • All parts of the connecting device 14 are made of a single material which is for example a Cobalt Chrome Molybdenum alloy or an alloy known under the name Inconel 718.
  • Such an embodiment of the connecting device 14 has the additional advantage that no sealing means is required between the different tubes 26, 28, 30 and the body 16 of the connecting device, thus reducing the risk of leakage. fueling or accidental communication of two ducts 20, 22, 24.
  • the strength of the connecting device 14 is improved since it is possible to adapt the thickness of a tube 26, 28, 30 or a rib 32 depending on the constraints that he / she undergoes.

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)

Abstract

The invention concerns a connection device (14) for connecting a turbomachine member such as an injector, to a system for supplying a fluid such as fuel, the connection device (14) comprising several concentric tubes (26, 28, 30) delimiting conduits (20, 22, 24) for supplying the member, which are curved in at least one direction, characterised in that it is made from a single part comprising at least the tubes (26, 28, 30).

Description

DISPOSITIF DE RACCORDEMENT COMPORTANT PLUSIEURS TUBES CONCENTRIQUES  CONNECTING DEVICE HAVING MULTIPLE CONCENTRIC TUBES
CINTRES  HANGER
DESCRIPTIONDESCRIPTION
DOMAINE TECHNIQUE TECHNICAL 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 providing 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 curved identically.
ÉTAT DE LA TECHNIQUE ANTÉRIEURE STATE 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 which is intended to inject a certain amount of fuel into the combustion chamber of the turbomachine. The amount 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, so-called primary, output which is used during a start-up phase of the turbomachine and a second, so-called secondary, output which is used after the starting of the turbomachine, and by which a large fuel flow is provided.
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 supplied several different fuel streams to the injector. Each of these different flows is associated with and supplies an output of the injector, that is to say a primary flow supplying the primary output, and a secondary flow 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. 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. A connecting device is arranged between the injector and the supply system, to drive the different fuel flows through small spaces. Due to the small space available for the flow of fuel flow, the connection device comprises several concentric tubes which delimit several ducts through which fuel flows.
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 delimit three concentric ducts. 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 connecting device are curved, or bent, to allow access to the location of the associated injector, taking into account the integration constraints on the turbomachine.
Selon un mode de fabrication conventionnel, les tubes sont cintrés simultanément.  According to a conventional method of manufacture, 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 apart from one another 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 follows from these bending operations that the thickness of the tubes is not constant over their entire length, manufacturing dispersions or 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 propose a connection device making it possible to solve these problems.
EXPOSÉ DE L'INVENTION STATEMENT 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 plusieurs tubes concentriques délimitant des conduits d'alimentation de l'organe, qui sont cintrés selon au moins une direction, caractérisé en ce qu'il est réalisé en une seule pièce comportant au moins les tubes. The invention proposes a device for connecting an organ to a system for supplying the fluid member, the connection device comprising a plurality of concentric tubes delimiting supply ducts for the organ, which are bent according to at least a direction, characterized in that it is made in one piece comprising at least the tubes.
De préférence, le dispositif de raccordement comporte au moins une nervure radiale s'étendant entre deux tubes adjacents, qui s'étend le long de la courbe centrale des tubes sur toute la longueur desdits tubes adjacents. De préférence, chaque nervure est réalisée d'une seule pièce avec lesdits tubes adjacents. Preferably, the connecting device comprises at least one radial rib extending between two adjacent tubes, which extends along the central curve of the tubes over the entire length of said adjacent tubes. Preferably, each rib is made in one piece with said adjacent tubes.
De préférence, le dispositif de raccordement comporte trois tubes concentriques et deux ensembles de nervures les nervures 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 du deuxième ensemble de nervures reliant la surface externe du tube radialement intermédiaire à la surface interne du tube radialement externe.  Preferably, the connecting device comprises three concentric tubes and two sets of ribs the 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 ribs of the second set of ribs connecting the outer surface of the radially intermediate tube to the inner surface of the radially outer tube.
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 connection of said radial end of the rib with the wall vis-à-vis a tube, associated.
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 connecting device comprises a connecting body of 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 comprises a fixing 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 connecting device is made by implementing a method of direct laser melting of metal.
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 caractérisé en ce qu'il comporte un dispositif de raccordement selon l'invention.  The invention also relates to a fluid supply circuit of a turbomachine member such as a fuel injector for an aircraft turbomachine combustion chamber, characterized in that it comprises 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. BRÈVE DESCRIPTION DES DESSINS The invention also relates to an aircraft turbomachine comprising at least one member connected to a supply system of the fluid member by a connecting device according to the invention. BRIEF 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 : Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended figures among which:
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 ;  Figure 1 is a schematic perspective view of a fuel supply circuit of an injector comprising a connecting device according to the invention;
la figure 2 est une vue en coupe radiale du dispositif de raccordement montrant les différents tubes et les nervures radiales ; et  Figure 2 is a radial sectional view of the connecting device showing the various tubes and the radial ribs; and
la figure 3 est une vue en coupe axiale du dispositif de raccordement montrant le corps du dispositif de raccordement avec les tubes.  Figure 3 is an axial sectional view of the connecting device showing the body of the connecting device with the tubes.
EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERS DETAILED 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. FIG. 1 shows 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 selectively inject two separate streams of fuel. These fuel flows are a primary flow, which is injected during a startup phase of the turbomachine and which is small, 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.  Since the specificities of each of the two fuel streams are different, these two flows are consequently separated as much at 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 from a high pressure pump, in several different flows feeding the injector, and regulates the pressure and the flow 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. 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. The supply system 12 is connected to the injector via a connection device 14. This connecting 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 different fuel flows towards the injector. For this, the pipe 18 is divided into several concentric supply pipes 20, 22, 24, here three in number as can be seen in more detail in 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 pipe 18 comprises a first radially inner conduit 20 which is associated with the first fuel flow, a second radially intermediate conduit 22 which is associated with the second fuel flow and a third radially external conduit 24 which is associated with a stagnant fuel flow acting as a thermal screen. This stagnant fuel in the third conduit 24 is intended to protect the other two fuel streams from heat, and thus to avoid particular phenomena of coking the fuel 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 ducts 20, 22, 24. The first duct 20 is thus delimited by the radially inner tube 26, the second duct 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 connection 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 bent, to allow the integration of the connection device on the turbomachine taking into account the other components of the turbomachine located nearby. As a result, 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. 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. The pipe 18 also has means for keeping 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 of the 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 in the second duct 22, the ribs 32 of the second set of ribs 32 extending into the third conduit 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 comprise 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 arranged 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, some ribs 32 have a thickness different from the thickness of the other ribs 32, to locally modify the mechanical strength to the pipe 18. Also, the thickness of a rib may 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 leave 34 at its connection with the associated face of a tube 26, 28, 30. These leaves 34 are intended to remove sharp edges that may locally weaken the connection between a rib and the wall vis-à-vis 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 connecting device 14 comprises a cylindrical portion 36 which is intended to receive a complementary part of the supply system 12 and which communicates separately with each of the ducts 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. De préférence, les tubes 26, 28, 30 sont tous réalisés en une seule pièce d'un même matériau. The body 16 includes a mounting plate 38 of the connecting device 14 on the turbomachine. This mounting 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. Preferably, the tubes 26, 28, 30 are all made in one 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 connecting 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 connecting device 14, the body 16 of the connecting 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 connecting 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 connecting device 14 is produced by the implementation of a so-called direct metal laser melting process. Such a method consists of distributing a uniform layer of metal powder by means of a re-coating device, then melting this layer at given locations corresponding to a section of the connection device in a highly controlled inert atmosphere. These operations are repeated several times until the connection device 14 is obtained. 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 undergoes no formatting step that would be complex to implement and may weaken 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 parts of the connecting device 14 are made of a single material which is for example a Cobalt Chrome 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 connecting device 14 has the additional advantage that no sealing means is required between the different tubes 26, 28, 30 and the body 16 of the connecting device, thus reducing the risk of leakage. fueling or accidental communication of two ducts 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 connecting device 14 is improved since it is possible to adapt the thickness of a tube 26, 28, 30 or a rib 32 depending on the constraints that he / she undergoes.

Claims

REVENDICATIONS
1. Dispositif de raccordement (14) d'un organe à un système d'alimentation de l'organe en fluide , le dispositif de raccordement (14) comportant plusieurs tubes (26, 28, 30) concentriques délimitant des conduits (20, 22, 24) d'alimentation de l'organe, qui sont cintrés selon au moins une direction, 1. A device (14) for connecting a member to a system for supplying the fluid member, the connecting device (14) comprising a plurality of concentric tubes (26, 28, 30) defining ducts (20, 22). , 24) for feeding the organ, which are bent in at least one direction,
caractérisé en ce qu'il est réalisé en une seule pièce comportant au moins les tubes (26, 28, 30).  characterized in that it is made in one piece comprising at least the tubes (26, 28, 30).
2. Dispositif de raccordement (14) selon la revendication précédente, caractérisé en ce qu'il comporte au moins une nervure (32) radiale s'étendant entre deux tubes (26, 28, 30) adjacents, qui s'étend le long de la courbe centrale des tubes (26, 28, 30) sur toute la longueur desdits tubes (26, 28, 30) adjacents. 2. Connection device (14) according to the preceding claim, characterized in that it comprises at least one radial rib (32) extending between two tubes (26, 28, 30) adjacent, which extends along the central curve of the tubes (26, 28, 30) along the entire length of said adjacent tubes (26, 28, 30).
3. Dispositif de raccordement (14) selon la revendication précédente, caractérisé en ce que chaque nervure (32) est réalisée d'une seule pièce avec lesdits tubes (26, 28, 30) adjacents. 3. Connecting device (14) according to the preceding claim, characterized in that each rib (32) is formed integrally with said tubes (26, 28, 30) adjacent.
4. Dispositif de raccordement (14) selon l'une quelconque des revendications 2 ou 3, caractérisé en ce que il comporte trois tubes (26, 28, 30) concentriques et deux ensembles de nervures (32), les nervures (32) d'un premier ensemble de nervures (32) reliant la surface externe du tube radialement interne (26) à la surface interne du tube radialement intermédiaire (28) et les nervures (32) du deuxième ensemble de nervures (32) reliant la surface externe du tube radialement intermédiaire (28) à la surface interne du tube radialement externe (30). 4. Connection device (14) according to any one of claims 2 or 3, characterized in that it comprises three concentric tubes (26, 28, 30) and two sets of ribs (32), the ribs (32) d 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 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).
5. Dispositif de raccordement (14) selon l'une quelconque des revendications 2 à 4, caractérisé en ce que des congés (34) sont formés à chaque extrémité radiale de chaque nervure (32), au niveau du raccordement de ladite extrémité radiale de la nervure (32) avec la paroi en vis-à-vis d'un tube (26, 28, 30) associé. 5. Connection device (14) according to any one of claims 2 to 4, characterized in that leaves (34) are formed at each radial end of each rib (32), at the connection of said radial end of the rib (32) with the wall vis-à-vis a tube (26, 28, 30) associated.
6. Dispositif de raccordement (14) selon l'une quelconque des revendications précédentes, caractérisé en ce que il comporte un corps (16) de raccordement des tubes (26, 28, 30) avec un système d'injection de fluide, et en ce que ledit corps (16) est réalisé d'une seule pièce avec les tubes (26, 28, 30) et les nervures (32). 6. Connection device (14) according to any one of the preceding claims, characterized in that it comprises a body (16) for connecting the tubes (26, 28, 30) with a fluid injection system, and said body (16) is formed in one piece with the tubes (26, 28, 30) and the ribs (32).
7. Dispositif de raccordement (14) selon la revendication précédente, caractérisé en ce que le corps (16) comporte une platine (38) de fixation et en ce que des congés (40) sont formés au niveau du raccordement entre la surface externe du tube radialement externe (30) et chaque surface de la platine (38). 7. Connection device (14) according to the preceding claim, characterized in that the body (16) comprises a plate (38) for fixing and in that leaves (40) are formed at the connection between the outer surface of the radially outer tube (30) and each surface of the plate (38).
8. Dispositif de raccordement (14) selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il est réalisé par mise en œuvre d'un procédé de fusion laser directe de métal. 8. Connecting device (14) according to any one of the preceding claims, characterized in that it is achieved by implementing a direct laser melting process of metal.
9. Circuit d'alimentation (10) en fluide d'un organe de turbomachine tel qu'un injecteur de carburant pour une chambre de combustion de turbomachine d'aéronef caractérisé en ce qu'il comporte un dispositif de raccordement (14) selon l'une quelconque des revendications précédentes. 9. A fluid supply circuit (10) for a turbomachine member such as a fuel injector for an aircraft turbomachine combustion chamber, characterized in that it comprises a connecting device (14) according to the invention. any preceding claim.
10. Turbomachine d'aéronef comportant au moins un organe raccordé à un système d'alimentation de l'organe en fluide par un dispositif de raccordement (14) selon l'une quelconque des revendications 1 à 8. 10. Aircraft turbomachine comprising at least one member connected to a supply system of the fluid member by a connecting device (14) according to any one of claims 1 to 8.
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)

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

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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)

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FR3091332B1 (en) 2018-12-27 2021-01-29 Safran Aircraft Engines Turbomachine injector nose comprising a secondary fuel spiral with progressive section

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Also Published As

Publication number Publication date
RU2017108764A3 (en) 2019-02-21
FR3025017B1 (en) 2016-09-30
CN106662330A (en) 2017-05-10
BR112017003212A2 (en) 2017-11-21
WO2016027034A2 (en) 2016-02-25
BR112017003212B1 (en) 2023-05-02
CA2958025C (en) 2023-05-16
EP3183498B1 (en) 2021-07-07
RU2703285C2 (en) 2019-10-16
CA2958025A1 (en) 2016-02-25
US11022312B2 (en) 2021-06-01
US20170234539A1 (en) 2017-08-17
FR3025017A1 (en) 2016-02-26
RU2017108764A (en) 2018-09-23
WO2016027034A3 (en) 2016-06-23

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