EP2932078A1 - Synchronization system for a thrust reverser - Google Patents

Synchronization system for a thrust reverser

Info

Publication number
EP2932078A1
EP2932078A1 EP13818281.1A EP13818281A EP2932078A1 EP 2932078 A1 EP2932078 A1 EP 2932078A1 EP 13818281 A EP13818281 A EP 13818281A EP 2932078 A1 EP2932078 A1 EP 2932078A1
Authority
EP
European Patent Office
Prior art keywords
cable
nacelle
synchronization
upstream
covers
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.)
Withdrawn
Application number
EP13818281.1A
Other languages
German (de)
French (fr)
Inventor
Vincent Peyron
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 Nacelles SAS
Original Assignee
Aircelle SA
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 Aircelle SA filed Critical Aircelle SA
Publication of EP2932078A1 publication Critical patent/EP2932078A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
    • B64D7/02—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft the armaments being firearms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow

Definitions

  • the present invention relates to the field of thrust reversers for aircraft nacelle.
  • An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.
  • These ancillary actuating devices comprise in particular a thrust reverser device.
  • a nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section intended to surround the fuel combustion chamber of the engine and engine. possibly the thrust reverser device, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
  • the propulsion unit constituted by the nacelle and the turbojet is hooked to a fixed structure of the aircraft, such as a wing or part of a fuselage, by a pylon or mast attachment or suspension.
  • the modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle.
  • the two air flows are ejected from the turbojet engine from the rear of the nacelle.
  • a nacelle generally comprises an external structure, called Outer Fixed Structure (OFS), which defines, with a concentric internal structure of the rear section, called Inner Fixed Structure (IFS), surrounding the structure of the turbojet itself behind the fan, an annular flow channel, also called a secondary vein, for channeling a cold air flow, said secondary, which circulates outside the turbojet engine.
  • OFS Outer Fixed Structure
  • IFS Inner Fixed Structure
  • the role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine.
  • the inverter obstructs the vein of the cold flow and directs it to the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
  • an inverter comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a position retraction in which they close this passage.
  • These covers can perform a deflection function or simply activation other means of deflection.
  • a grid inverter also known as a cascade inverter
  • the reorientation of the air flow is carried out by deflection grids, the hood having a simple sliding function aimed at discover or cover these grids.
  • Complementary locking doors, also called shutters, activated by the shedding of the cowling, generally allow a closing of the vein downstream of the grids so as to optimize the reorientation of the cold flow.
  • the deflection grids are mounted on a front frame serving as a fixed part of the thrust reverser device and attached to a housing of the turbojet fan.
  • This front frame also supports actuating cylinders movable covers.
  • downstream section of the nacelle is made from two half-hemi-cylindrical half-structures located, in the upper part (called 12 hours), on either side of a reactor mast connecting the turbojet engine to the aircraft and linked to each other in the lower part (called 6 hours).
  • the demi-structures are attached to the reactor mast via an upper half-beam, and also include a lower half-beam. These lower and upper demi-beams are equipped with sliding rails for the movable reversing cowl of the corresponding half-structure.
  • the thrust reverser device thus comprises several moving covers
  • an important aspect is their synchronization. Indeed, it is important that the hoods move simultaneously and are precisely coordinated. Otherwise, any gap between the mobile covers may lead to phenomena, arching or even blocking said covers.
  • Some thrust reverser systems however use only two cylinders per movable cowl and the aerodynamic inner and outer lines of the cowls are close together, which greatly reduces their axial stiffness.
  • the present invention relates to a thrust reverser device for turbojet engine nacelle comprising at least two covers each mounted movable in translation relative to a fixed structure in a direction substantially parallel to a longitudinal axis of the nacelle between an upstream closing position in which it ensures the aerodynamic continuity of the nacelle, and a downstream opening position in which it opens a passage in the nacelle, characterized in that the thrust reverser device comprises at least one cable of synchronization stretched between the two movable hoods so as to have a first end attached to an upstream point of a first hood, a second end attached to a downstream point of the second hood, and the upstream and downstream attachment points being determined with respect to a fixed central zone of passage of the cable between the two covers.
  • the second hood can not move back more than the first hood.
  • the retreat of the first hood makes it possible to increase the length of cable available for the second hood and therefore its retreat of the same length. It is the same for the closure of said covers.
  • This cable makes it possible to obtain independent synchronization of the actuators of the thrust reverser and thus makes it possible to mitigate any failure of the latter.
  • the present invention relies on the use of reliable and simple components and does not require significant changes in the architecture of the sliding hoods. The impact on the mass of the whole is small.
  • the covers are arranged on either side of a fixed structure at which is defined the central zone of passage of the cable.
  • the fixed structure comprises a longitudinal beam.
  • the longitudinal beam is a top beam said 12 hours.
  • the fixed structure participates in a structuring structure for attachment to a connecting mast.
  • the fixed central zone of passage of the synchronization cable is defined at least partly by means of one or more return pulleys.
  • the thrust reversal device comprises two crossed synchronization cables.
  • the synchronization cable is maintained in tension using at least one tensioner roller.
  • the device comprises at least one reversing lock associated with the movable cowl to which the cable is attached upstream.
  • the present invention also relates to a turbojet engine nacelle comprising such a thrust reverser device.
  • FIG. 1 is a simplified representation of the structure of a thrust reverser device according to the invention.
  • FIG. 2 is a view from above along the axis A-A of FIG. 1 showing a first embodiment of the invention
  • FIG. 3 is a view from above along the axis AA of FIG. 1 showing a second embodiment of the invention.
  • a thrust reverser device 1 according to the invention comprises two covers 1 1, 12 mounted movable in translation on either side of an attachment structure 4 to a connecting mast (not shown).
  • the thrust reverser 1 comprises a synchronization cable 2 extending between the movable covers 1 1, 1 2, 1 ed it c ble synchronizing circuit having a first end attached to an upstream point 1 1 1 of the first cap 1 1, a second end attached to a downstream point 121 of the second cap 12.
  • the upstream attachment points 1 1 1 and downstream 121 being determined relative to a fixed central zone of passage 3 of the cable 2 between the two covers 1 1, 12.
  • the fixed central passage zone 3 of the cable 2 is defined at the attachment structure 4 by means of return pulleys 31 ensuring the passage of the cable from the left side to the right side of the attachment structure 4 through the latter.
  • hood 1 1 left is associated with a reversing lock 5 disposed on the left side of the attachment structure 4 and prohibiting the recoil of said movable cover.
  • the synchronization cable 2 then naturally blocks the recoil of the right cover 12.
  • a displacement of the left cover 1 1 reduces the length of cable 2 available on the left side of the attachment structure 4 and increases the length of cable 2 available on the right side.
  • the point of attachment 1 21 right of the cable being located downstream of the left point of attachment 1 1 1 of the cable, relative to the median passage zone 3, the additional cable distance 2 on the right side allows the displacement of the right cover 1 2 of the same length as the left cover 1 1.
  • the left cover 1 1, on the side of the reversing lock 5, constitutes a master cover, with respect to which synchronization is effected.
  • a completely reciprocal synchronization can be ensured by the installation in place of two crossed synchronization cables 2a, 2b, as shown in FIG. 3.
  • the synchronization cable 2 In order to mimic the vibrations in the synchronization cable 2 during the flight phases, it can be maintained in tension by means of a tensioner type system.
  • the same system can also be used to allow a low desynchronization between the two covers 11, 12 to prevent the system from being hyperstatic compared to the drive cylinders which already control the position of the hoods. 1 1, 1 2 in the absence of problems. This prevents the cable 2 from working in fatigue since it is only stressed when the desynchronization of the hoods 1 1, 1 2 exceeds a predicted value, this desynchronization limit value being reached only during the breakage of an element of the drive system of the cowls January 1, 12, cylinder or flexible shaft for example.
  • the length of the synchronization cable 2 must preferably be slightly greater than the desired stroke of the movable covers 1 1, 12 plus the width of the fixed median passage zone 3 (width of the attachment structure 4 in FIG. species).
  • the points of attachment 1 1 1, 121 of the synchronization cable 2 will be located on slide rails of the covers 1 1, 12 to avoid the addition of new structural parts.
  • these fasteners will be removable so as to allow the installation / removal of the covers 1 1, 12.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)

Abstract

Thrust reverser device (1) for a turbojet engine nacelle comprising at least two cowls (11, 12) each one mounted with the ability to move translationally with respect to a fixed structure between an upstream closed position in which it provides the aerodynamic continuity of the nacelle, and a downstream open position in which it opens a passage in the nacelle, the device comprising at least one synchronization cable (2) stretched between the two mobile cowls so as to have a first end (111) attached to an upstream point of a first cowl, a second end (121) attached to a downstream point of the second cowl, and the upstream and downstream attachment points being determined relative to a fixed central zone (3) where the cable passes between the two cowls.

Description

Système de synchronisation pour dispositif d'inversion de poussée  Synchronization system for thrust reversing device
La présente invention se rapporte au domaine des inverseurs de poussée pour nacelle d'aéronef. The present invention relates to the field of thrust reversers for aircraft nacelle.
Un avion est mû par plusieurs turboréacteurs logés chacun dans une nacelle abritant également un ensemble de dispositifs d'actionnement annexes liés à son fonctionnement et assurant diverses fonctions lorsque le turboréacteur est en fonctionnement ou à l'arrêt. Ces dispositifs d'actionnement annexes comprennent notamment un dispositif d'inversion de poussée.  An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped. These ancillary actuating devices comprise in particular a thrust reverser device.
Une nacelle présente généralement une structure tubulaire comprenant une entrée d'air en amont du turboréacteur, une section médiane destinée à entourer une soufflante du turboréacteur, une section aval destinée à entou rer l a cham bre de com bustion d u tu rboréacteu r et i ntég rant éventuellement le dispositif d'inversion de poussée, et est généralement terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.  A nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section intended to surround the fuel combustion chamber of the engine and engine. possibly the thrust reverser device, and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.
L'ensemble propulsif constitué par la nacelle et le turboréacteur est accroché à une structure fixe de l'aéronef, telle une aile ou une partie d'un fuselage, par un pylône ou mât d'accrochage ou de suspension.  The propulsion unit constituted by the nacelle and the turbojet is hooked to a fixed structure of the aircraft, such as a wing or part of a fuselage, by a pylon or mast attachment or suspension.
Les nacelles modernes sont destinées à abriter un turboréacteur double flux apte à générer par l'intermédiaire des pâles de la soufflante en rotation un flux d'air chaud (également appelé flux primaire) issu de la chambre de combustion du turboréacteur, et un flux d'air froid (flux secondaire) qui circule à l'extérieur du turboréacteur à travers un passage annulaire, également appelé veine, formé entre un carénage du turboréacteur et une paroi interne de la nacelle. Les deux flux d'air sont éjectés du turboréacteur par l'arrière de la nacelle.  The modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle. The two air flows are ejected from the turbojet engine from the rear of the nacelle.
Une nacelle comprend généralement une structure externe, dite Outer Fixed Structure (OFS), qui définit, avec une structure interne concentrique de la section arrière, dite Inner Fixed Structure (IFS), entourant la structure du turboréacteur proprement dite en arrière de la soufflante, un canal annulaire d'écoulement, encore appelé veine secondaire, visant à canaliser un flux d'air froid, dit secondaire, qui circule à l'extérieur du turboréacteur.  A nacelle generally comprises an external structure, called Outer Fixed Structure (OFS), which defines, with a concentric internal structure of the rear section, called Inner Fixed Structure (IFS), surrounding the structure of the turbojet itself behind the fan, an annular flow channel, also called a secondary vein, for channeling a cold air flow, said secondary, which circulates outside the turbojet engine.
Le rôle d'un inverseur de poussée est, lors de l'atterrissage d'un avion, d'améliorer la capacité de freinage de celui-ci en redirigeant vers l'avant au moins une partie de la poussée générée par le turboréacteur. Dans cette phase, l'inverseur obstrue la veine du flux froid et dirige ce dernier vers l'avant de la nacelle, générant de ce fait une contre-poussée qui vient s'ajouter au freinage des roues de l'avion. The role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine. In this phase, the inverter obstructs the vein of the cold flow and directs it to the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.
Les moyens mis en œuvre pour réaliser cette réorientation du flux froid varient suivant le type d'inverseur. Cependant, dans tous les cas, la structure d'un inverseur comprend des capots mobiles déplaçables entre, d'une part, une position déployée dans laquelle ils ouvrent dans la nacelle un passage destiné au flux dévié, et d'autre part, une position d'escamotage dans laquelle ils ferment ce passage. Ces capots peuvent remplir une fonction de déviation ou simplement d'activation d'autres moyens de déviation.  The means implemented to achieve this reorientation of the cold flow vary according to the type of inverter. However, in all cases, the structure of an inverter comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a position retraction in which they close this passage. These covers can perform a deflection function or simply activation other means of deflection.
Dans le cas d'un inverseur à grilles, également connu sous le nom d'inverseur à cascade, la réorientation du flux d'air est effectuée par des grilles de déviation, le capot n'ayant qu'une simple fonction de coulissage visant à découvrir ou recouvrir ces grilles. Des portes de blocage complémentaires, également appelées volets, activées par le coul issement du capotage, permettent généralement une fermeture de la veine en aval des grilles de manière à optimiser la réorientation du flux froid.  In the case of a grid inverter, also known as a cascade inverter, the reorientation of the air flow is carried out by deflection grids, the hood having a simple sliding function aimed at discover or cover these grids. Complementary locking doors, also called shutters, activated by the shedding of the cowling, generally allow a closing of the vein downstream of the grids so as to optimize the reorientation of the cold flow.
De façon connue, les grilles de déviation sont montées sur un cadre avant servant de partie fixe du dispositif d'inversion de poussée et rattaché à un carter de la soufflante du turboréacteur. Ce cadre avant assure également le support de vérins d'actionnement des capots mobiles.  In known manner, the deflection grids are mounted on a front frame serving as a fixed part of the thrust reverser device and attached to a housing of the turbojet fan. This front frame also supports actuating cylinders movable covers.
Le plus souvent, la section aval de nacelle est réalisée à partir de deux demi structures sensiblement hémicylindriques situées, en partie supérieure (dite 12 heures), de part et d'autre d'un mât réacteur de rattachement du turboréacteur à l'avion et liées entre elles en partie inférieure (dite 6 heures).  Most often, the downstream section of the nacelle is made from two half-hemi-cylindrical half-structures located, in the upper part (called 12 hours), on either side of a reactor mast connecting the turbojet engine to the aircraft and linked to each other in the lower part (called 6 hours).
Les dem i-structures sont rattachées au mât réacteur par l'intermédiaire d'une demi-poutre supérieure, et comprennent également une demi-poutre inférieure. Ces dem i-poutres inférieure et supérieure sont équipées de rails de coulissement pour le capot mobile d'inversion de poussée de la demi-structure correspondante.  The demi-structures are attached to the reactor mast via an upper half-beam, and also include a lower half-beam. These lower and upper demi-beams are equipped with sliding rails for the movable reversing cowl of the corresponding half-structure.
Lorsque le dispositif d'inversion de poussée comprend ainsi plusieurs capots mobiles, un aspect important est leur synchronisation. En effet, il est important que les capots se déplacent simultanément et soient précisément coordonnés. A défaut, tout décalage entre les capots mobiles peut conduire à des phénomènes, d'arc-boutement, voire de blocage desdits capots. When the thrust reverser device thus comprises several moving covers, an important aspect is their synchronization. Indeed, it is important that the hoods move simultaneously and are precisely coordinated. Otherwise, any gap between the mobile covers may lead to phenomena, arching or even blocking said covers.
Il est connu d'effectuer la synchronisation des capots mobiles au niveau d'actionneurs de ces derniers, notamment dans le cas d'actionneurs électriques dont la position de déploiement ou de rétractation peut être contrôlée de manière précise, notamment grâce à des systèmes d'arbres de transmission flexibles entre un moteur électrique et ses actionneurs.  It is known to perform the synchronization of the mobile hoods at the actuators thereof, particularly in the case of electric actuators whose deployment or retraction position can be precisely controlled, in particular by means of control systems. flexible drive shafts between an electric motor and its actuators.
Cela est en revanche plus difficilement réalisable avec des actionneurs de type pneumatique ou hydraulique.  However, this is more difficult with pneumatic or hydraulic actuators.
Actuellement, le seul système permettant de maintenir les capots synchronisés est donc cette synchronisation mécanique mise en œuvre au niveau des actionneurs. Un exemple d'un tel système est décrit dans le document WO 2009/147333.  Currently, the only system for maintaining the synchronized covers is therefore this mechanical synchronization implemented at the level of the actuators. An example of such a system is described in WO 2009/147333.
En cas de rupture d'un des éléments de ce système d'actionnement (par exemple rupture d'un vérin mais également d'un arbre flexible de transmission), la synchronisation n'est plus assurée et les capots mobiles peuvent se décaler de plusieurs centaines de millimètres sous l'effet notamment des chargements aérodynamiques et/ou inertiels, ce qui peut entraîner, comme mentionner précédemment, arc-boutement, blocage, voire rupture et casse des capots.  In case of breakage of one of the elements of this actuation system (for example rupture of a cylinder but also of a flexible transmission shaft), the synchronization is no longer ensured and the movable covers can be shifted by several hundreds of millimeters under the effect in particular aerodynamic and / or inertial loads, which may result, as mentioned above, jamming, blockage or breakage and breakage of the covers.
Sur les programmes existants, il y a généralement deux capots mobiles (gauche et droit) et trois actionneurs par capot mobile. Ces capots sont également en général plus raides dans une direction axiale du fait de lignes aérodynamiques plus épaisses entre les lignes interne et externe. Ceci rend ces capots coulissants plus tolérants à une rupture d'un élément du système d'actionnement.  On existing programs, there are usually two moving hoods (left and right) and three actuators per moving hood. These covers are also generally stiffer in an axial direction due to thicker aerodynamic lines between the inner and outer lines. This makes these sliding cowls more tolerant of a breakage of an element of the actuating system.
Certains systèmes d'inversion de poussée n'utilisent toutefois que deux vérins par capot mobile et les lignes aérodynamiques interne et externe des capots sont rapprochées, ce qui diminue fortement leur raideur axiale.  Some thrust reverser systems however use only two cylinders per movable cowl and the aerodynamic inner and outer lines of the cowls are close together, which greatly reduces their axial stiffness.
Une autre solution pour augmenter la tenue structurale des capots, et assurer leur synchronisation, est utilisée sur des dispositifs d'inversion de poussée ne comprenant qu'un unique capot mobile sensiblement périphérique, et consiste à rel ier à 1 2h, au n iveau du pylône, les deux côtés du capot coulissant par une pièce structurale traversant de part en part le mât moteur. Un inconvénient majeur de cette solution est que lorsque le capot coulisse recule pour se mettre en position d'inversion de poussée, la pièce structurale recule également ce qui oblige à prévoir une large saignée dans le mât moteur, ce qui n'est bien évidemment pas optimal pour sa tenue structurale. Another solution to increase the structural strength of the covers, and ensure their synchronization, is used on thrust reverser devices comprising only a single substantially peripheral mobile cover, and consists of rel ier at 1 2h, at the level of pylon, both sides of the sliding cowl by a structural part passing right through the engine mast. A major disadvantage of this solution is that when the cowl slides back to put in thrust reversal position, the structural part also back which requires to provide a wide bleeding in the engine mast, which is obviously not optimal for its structural strength.
Il existe donc u n besoin pour un système de synchronisation complémentaire ne reposant pas sur les actionneurs.  There is therefore a need for a complementary synchronization system not based on the actuators.
Pour ce faire, la présente invention se rapporte à un dispositif d'inversion de poussée pour nacelle de turboréacteur comportant au moins deux capots montés chacun mobile en translation par rapport à une structure fixe selon une direction sensiblement parallèle à un axe longitudinal de la nacelle entre une position amont de fermeture dans laquelle il assure la continuité aérodynamique de la nacelle, et une position aval d'ouverture dans laquelle il ouvre un passage dans la nacelle, caractérisé en ce que le dispositif d'inversion de poussée comprend au moins un câble de synchronisation tendu entre les deux capots mobiles de manière à présenter une première extrémité rattachée à un point amont d'un premier capot, une deuxième extrémité rattachée à un point aval du deuxième capot, et les points de rattachement amont et aval étant déterminés par rapport à une zone médiane fixe de passage du câble entre les deux capots.  To do this, the present invention relates to a thrust reverser device for turbojet engine nacelle comprising at least two covers each mounted movable in translation relative to a fixed structure in a direction substantially parallel to a longitudinal axis of the nacelle between an upstream closing position in which it ensures the aerodynamic continuity of the nacelle, and a downstream opening position in which it opens a passage in the nacelle, characterized in that the thrust reverser device comprises at least one cable of synchronization stretched between the two movable hoods so as to have a first end attached to an upstream point of a first hood, a second end attached to a downstream point of the second hood, and the upstream and downstream attachment points being determined with respect to a fixed central zone of passage of the cable between the two covers.
Ainsi, grâce au câble tendu, le deuxième capot ne peut pas reculer plus que le premier capot. En revanche, le recul du premier capot permet d'augmenter la longueur de câble disponible pour le deuxième capot et donc son recul de la même longueur. Il en va de même pour la fermeture desdits capots.  Thus, thanks to the tensioned cable, the second hood can not move back more than the first hood. On the other hand, the retreat of the first hood makes it possible to increase the length of cable available for the second hood and therefore its retreat of the same length. It is the same for the closure of said covers.
Ce câble permet d'obtenir une synchronisation indépendante des actionneurs de l'inverseur de poussée et permet donc de pallier toute défaillance de ces derniers.  This cable makes it possible to obtain independent synchronization of the actuators of the thrust reverser and thus makes it possible to mitigate any failure of the latter.
En outre, l a présente invention repose su r l 'util isation de composants fiables et simples et ne nécessite pas de modifications importantes de l'architecture des capots coulissant. L'impact sur la masse de l'ensemble est faible.  In addition, the present invention relies on the use of reliable and simple components and does not require significant changes in the architecture of the sliding hoods. The impact on the mass of the whole is small.
Selon un mode préféré de réalisation, les capots sont disposés de part et d'autre d'une structure fixe au niveau de laquelle est définie la zone médiane de passage du câble.  According to a preferred embodiment, the covers are arranged on either side of a fixed structure at which is defined the central zone of passage of the cable.
De manière préférentielle, que la structure fixe comprend une poutre longitudinale. Avantageusement, la poutre longitudinale est une poutre supérieure dite 12 heures. Préférentiellement, la structu re fixe participe à u ne structu re d'accrochage à un mât de rattachement. Preferably, the fixed structure comprises a longitudinal beam. Advantageously, the longitudinal beam is a top beam said 12 hours. Preferably, the fixed structure participates in a structuring structure for attachment to a connecting mast.
Selon un mode de réalisation avantageux, la zone médiane fixe de passage du câble de synchronisation est définie au moins en partie à l'aide d'une ou plusieurs poulies de renvoi.  According to an advantageous embodiment, the fixed central zone of passage of the synchronization cable is defined at least partly by means of one or more return pulleys.
De man ière avantageuse, le d ispositif d'inversion de poussée comprend deux câbles de synchronisation croisés.  Advantageously, the thrust reversal device comprises two crossed synchronization cables.
Préférentiellement, le câble de synchronisation est maintenu en tension à l'aide d'au moins un galet tendeur.  Preferably, the synchronization cable is maintained in tension using at least one tensioner roller.
Avantageusement, le dispositif comprend au moins un verrou de recul associé au capot mobile auquel le câble est rattaché en amont.  Advantageously, the device comprises at least one reversing lock associated with the movable cowl to which the cable is attached upstream.
La présente invention se rapporte également à une nacelle de turboréacteur comprenant un tel dispositif d'inversion de poussée.  The present invention also relates to a turbojet engine nacelle comprising such a thrust reverser device.
La présente invention sera mieux comprise à la lumière de la description détaillée qui suit en regard du dessin annexé dans lequel :  The present invention will be better understood in the light of the following detailed description with reference to the appended drawing in which:
- la figure 1 est une représentation simplifiée de la structure d'un dispositif d'inversion de poussée selon l'invention.  - Figure 1 is a simplified representation of the structure of a thrust reverser device according to the invention.
- la figure 2 est une vue de dessus selon l'axe A-A de la figure 1 montrant un premier mode de réalisation de l'invention,  FIG. 2 is a view from above along the axis A-A of FIG. 1 showing a first embodiment of the invention,
- la figure 3 est une vue de dessus selon l'axe A-A de la figure 1 montrant un deuxième mode de réalisation de l'invention, Comme visible sur la figure 1 , un dispositif d'inversion de poussée 1 selon l'invention comprend deux capots 1 1 , 12 montés mobiles en translation de part et d'autre d'une structure d'accrochage 4 à un mât de rattachement (non représenté).  FIG. 3 is a view from above along the axis AA of FIG. 1 showing a second embodiment of the invention. As seen in FIG. 1, a thrust reverser device 1 according to the invention comprises two covers 1 1, 12 mounted movable in translation on either side of an attachment structure 4 to a connecting mast (not shown).
Conformément à l'objet de l'invention il s'agit donc d'assurer la synchronisation des déplacements du capot mobile 1 1 , situé à gauche de la structure d'accrochage 4 par rapport à l'avant de la nacelle, et du capot mobile 12, situé à droite de ladite structure d'accrochage.  According to the object of the invention it is therefore necessary to ensure the synchronization of the movements of the movable cover 1 1, located to the left of the attachment structure 4 relative to the front of the nacelle, and the hood mobile 12, located to the right of said attachment structure.
Pour ce faire, conformément à l'invention et comme visible sur la figure 2, l'inverseur de poussée 1 comprend un câble de synchronisation 2 tend u entre l es capots mobi l es 1 1 , 1 2 , l ed it câ bl e de synch ron isation présentant une première extrémité rattachée à un point amont 1 1 1 du premier capot 1 1 , une deuxième extrémité rattachée à un point aval 121 du deuxième capot 12. Les points de rattachement amont 1 1 1 et aval 121 étant déterminés par rapport à une zone médiane fixe de passage 3 du câble 2 entre les deux capots 1 1 , 12. To do this, according to the invention and as visible in FIG. 2, the thrust reverser 1 comprises a synchronization cable 2 extending between the movable covers 1 1, 1 2, 1 ed it c ble synchronizing circuit having a first end attached to an upstream point 1 1 1 of the first cap 1 1, a second end attached to a downstream point 121 of the second cap 12. The upstream attachment points 1 1 1 and downstream 121 being determined relative to a fixed central zone of passage 3 of the cable 2 between the two covers 1 1, 12.
La zone médiane fixe de passage 3 du câble 2 est définie au niveau de la structure d'accrochage 4 à l'aide de poulies de renvoi 31 assurant le passage du câble du côté gauche au côté droit de la structure d'accrochage 4 à travers cette dernière.  The fixed central passage zone 3 of the cable 2 is defined at the attachment structure 4 by means of return pulleys 31 ensuring the passage of the cable from the left side to the right side of the attachment structure 4 through the latter.
Il convient de noter que le capot 1 1 gauche est associé à un verrou de recul 5 disposé sur le côté gauche de la structure d'accrochage 4 et interdisant le recul dudit capot mobile. Le câble de synchronisation 2 bloque alors naturellement le recul du capot droit 12.  It should be noted that the hood 1 1 left is associated with a reversing lock 5 disposed on the left side of the attachment structure 4 and prohibiting the recoil of said movable cover. The synchronization cable 2 then naturally blocks the recoil of the right cover 12.
Lorsque le capot gauche 1 1 recule vers une position d'inversion de poussée, la longueur totale du câble n'est pas modifiée et celui-ci coul isse à travers la structure d'accrochage 4.  When the left cover 1 1 back to a thrust reversal position, the total length of the cable is not changed and it is cast through the attachment structure 4.
Ainsi, un déplacement du capot gauche 1 1 réduit la longueur de câble 2 disponible du côté gauche de la structure d'accrochage 4 et augmente la longueur de câble 2 disponible du côté droit. Le point de rattachement 1 21 droit du câble étant situé en aval du point de rattachement gauche 1 1 1 du câble, par rapport à la zone médiane de passage 3, la distance de câble 2 supplémentaire du côté droit permet le déplacement du capot droit 1 2 de la même longueur que le capot gauche 1 1 .  Thus, a displacement of the left cover 1 1 reduces the length of cable 2 available on the left side of the attachment structure 4 and increases the length of cable 2 available on the right side. The point of attachment 1 21 right of the cable being located downstream of the left point of attachment 1 1 1 of the cable, relative to the median passage zone 3, the additional cable distance 2 on the right side allows the displacement of the right cover 1 2 of the same length as the left cover 1 1.
Dans le cas où le d ispositif ne comprend qu 'u n seul câble de synchronisation 2 comme décrit ci-dessus, le capot gauche 1 1 , du côté du verrou de recul 5, constitue un capot maître, par rapport auquel s'effectue la synchronisation du capot droit 12, constituant un capot esclave.  In the case where the device comprises only a single synchronization cable 2 as described above, the left cover 1 1, on the side of the reversing lock 5, constitutes a master cover, with respect to which synchronization is effected. right cover 12, constituting a slave cover.
Une synchronisation totalement réciproque peut être assurée par la m ise en place de deux câbles de synchron isation 2a, 2b croisés, comme représenté sur la figure 3.  A completely reciprocal synchronization can be ensured by the installation in place of two crossed synchronization cables 2a, 2b, as shown in FIG. 3.
Afin de l imiter les vibrations dans le câble de synchronisation 2 pendant les phases de vol, celui-ci peut être maintenu en tension à l'aide d'un système de type galet tendeur.  In order to mimic the vibrations in the synchronization cable 2 during the flight phases, it can be maintained in tension by means of a tensioner type system.
U n te l systè m e d e g a l et ten deur peut également permettre d'autoriser une faible désynchronisation entre les deux capots 1 1 , 12 afin d'éviter que le système ne soit hyperstatique par rapport aux vérins d'entraînement qui pilotent déjà la position des capots 1 1 , 1 2 en l'absence de problèmes. On évite alors ainsi de faire travailler le câble 2 en fatigue puisque celui-ci n'est soll icité que lorsque la désynchron isation des capots 1 1 , 1 2 dépasse une valeur prévue, cette valeur limite de désynchronisation n'étant atteinte que lors de la rupture d'un élément du système d'entraînement des capots 1 1 , 12, vérin ou arbre flexible par exemple. The same system can also be used to allow a low desynchronization between the two covers 11, 12 to prevent the system from being hyperstatic compared to the drive cylinders which already control the position of the hoods. 1 1, 1 2 in the absence of problems. This prevents the cable 2 from working in fatigue since it is only stressed when the desynchronization of the hoods 1 1, 1 2 exceeds a predicted value, this desynchronization limit value being reached only during the breakage of an element of the drive system of the cowls January 1, 12, cylinder or flexible shaft for example.
On notera également que la longueur du câble de synchronisation 2 doit être préférentiellement légèrement supérieure à la course souhaitée des capots mobiles 1 1 , 12 plus la largeur de la zone médiane fixe de passage 3 (largeur de la structure d'accrochage 4 en l'espèce).  It will also be noted that the length of the synchronization cable 2 must preferably be slightly greater than the desired stroke of the movable covers 1 1, 12 plus the width of the fixed median passage zone 3 (width of the attachment structure 4 in FIG. species).
Avantageusement, les points de rattachement 1 1 1 , 121 du câble 2 de synchronisation seront situés sur des glissières de coulissement des capots 1 1 , 12 afin d'éviter l'ajout de nouvelles pièces structurales. Préférentiellement, ces attaches seront démontables de manière à permettre la pose/dépose des capots 1 1 , 12.  Advantageously, the points of attachment 1 1 1, 121 of the synchronization cable 2 will be located on slide rails of the covers 1 1, 12 to avoid the addition of new structural parts. Preferably, these fasteners will be removable so as to allow the installation / removal of the covers 1 1, 12.
Dans le cas où un système de galet tendeur est utilisé, il est possible d'équiper le ou les galets de contacteurs qui se déclenchent lorsque le câble se détend ou casse.  In the case where a tensioner roller system is used, it is possible to equip the rollers or contactors which trigger when the cable relaxes or breaks.
Bien que l'invention ait été décrite avec un exemple particulier de réal isation, il est bien évident qu'elle n'y est nullement limitée et qu'elle comprend tous les équivalents techniques des moyens décrits ainsi que leurs combinaisons si celles-ci entrent dans le cadre de l'invention.  Although the invention has been described with a particular example of real isation, it is obvious that it is in no way limited and that it includes all the technical equivalents of the means described and their combinations if they enter in the context of the invention.

Claims

REVENDICATIONS
1 . Dispositif d'inversion (1 ) d e pou ssée pou r n a cel l e d e turboréacteur comportant au moins deux capots (1 1 , 1 2) montés chacun mobile en translation par rapport à une structure fixe selon une direction sensiblement parallèle à un axe longitudinal de la nacelle entre une position amont de fermeture dans laquelle il assure la continuité aérodynamique de la nacelle, et une position aval d'ouverture dans laquelle il ouvre un passage dans la nacelle, caractérisé en ce que le dispositif d'inversion de poussée comprend au moins un câble de synchronisation (2) tendu entre les deux capots mobiles de manière à présenter une première extrémité (1 1 1 ) rattachée à un point amont d'un premier capot, une deuxième extrémité (121 ) rattachée à un point aval du deuxième capot, et les points de rattachement amont et aval étant déterminés par rapport à une zone médiane fixe (3) de passage du câble entre les deux capots. 1. Device for inversion (1) of the seat for the turbojet engine comprising at least two covers (1 1, 1 2) each mounted movable in translation relative to a fixed structure in a direction substantially parallel to a longitudinal axis of the nacelle between an upstream closing position in which it ensures the aerodynamic continuity of the nacelle, and a downstream opening position in which it opens a passage in the nacelle, characterized in that the thrust reverser device comprises at least one cable synchronization device (2) stretched between the two movable hoods so as to have a first end (1 1 1) attached to an upstream point of a first hood, a second end (121) attached to a downstream point of the second hood, and the points of attachment upstream and downstream being determined with respect to a fixed central zone (3) of passage of the cable between the two covers.
2. Dispositif (1 ) selon la revendication 1 , caractérisé en ce que les capots (1 1 , 12) sont disposés de part et d'autre d'une structure fixe au niveau de laquelle est définie la zone médiane de passage (3) du câble (2). 2. Device (1) according to claim 1, characterized in that the covers (1 1, 12) are arranged on either side of a fixed structure at which is defined the median passage zone (3) cable (2).
3. Dispositif (1 ) selon la revendication 2, caractérisé en ce que la structure fixe comprend une poutre longitudinale. 3. Device (1) according to claim 2, characterized in that the fixed structure comprises a longitudinal beam.
4. Dispositif selon la revendication 3, caractérisé en ce que la poutre longitudinale est une poutre supérieure dite 12 heures. 4. Device according to claim 3, characterized in that the longitudinal beam is a top beam said 12 hours.
5. Dispositif selon la revendication 2, caractérisé en ce que la structure fixe participe à une structure d'accrochage (4) à u n m ât d e rattachement. 5. Device according to claim 2, characterized in that the fixed structure participates in a fastening structure (4) at an anchoring point.
6. Dispositif (1 ) selon l'une quelconque des revendications 1 à 5, caractérisé en ce que la zone médiane fixe (3) de passage du câble de synchronisation (2) est définie au moins en partie à l'aide d'une ou plusieurs poulies (31 ) de renvoi. 6. Device (1) according to any one of claims 1 to 5, characterized in that the fixed central zone (3) for passage of the synchronization cable (2) is defined at least partly by means of a or several return pulleys (31).
7. Dispositif (1 ) selon l'une quelconque des revendications 1 à 6, caractérisé en ce qu'il comprend deux câbles de synchronisation (2a, 2b) croisés. 7. Device (1) according to any one of claims 1 to 6, characterized in that it comprises two synchronization cables (2a, 2b) crossed.
8. Dispositif (1 ) selon l'une quelconque des revendications 1 à 7, caractérisé en ce que le câble de synchronisation (2) est maintenu en tension à l'aide d'au moins un galet tendeur. 8. Device (1) according to any one of claims 1 to 7, characterized in that the synchronization cable (2) is held in tension using at least one tensioner roller.
9. Dispositif (1 ) selon l'une quelconque des revendications 1 à 8, caractérisé en ce qu'il comprend au moins un verrou (5) de recul associé au capot mobile (1 1 ) auquel le câble (2) est rattaché en amont. 9. Device (1) according to any one of claims 1 to 8, characterized in that it comprises at least one latch (5) associated with the moving cowl (1 1) to which the cable (2) is attached in upstream.
10. Nacelle de turboréacteur comprenant au moins un dispositif d'inversion de poussée (1 ) selon l'une quelconque des revendications 1 à 9. 10. A turbojet engine nacelle comprising at least one thrust reverser device (1) according to any one of claims 1 to 9.
EP13818281.1A 2012-12-11 2013-12-10 Synchronization system for a thrust reverser Withdrawn EP2932078A1 (en)

Applications Claiming Priority (2)

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FR1261854A FR2999240B1 (en) 2012-12-11 2012-12-11 SYNCHRONIZATION SYSTEM FOR PUSH REVERSING DEVICE
PCT/FR2013/053013 WO2014091139A1 (en) 2012-12-11 2013-12-10 Synchronization system for a thrust reverser

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EP (1) EP2932078A1 (en)
CN (1) CN104854336A (en)
BR (1) BR112015011506A2 (en)
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FR (1) FR2999240B1 (en)
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DE102013226770A1 (en) * 2013-12-19 2015-06-25 Liebherr-Aerospace Lindenberg Gmbh Aircraft gas turbine with an engine cowling with thrust reverser
EP3464864B1 (en) * 2016-05-30 2022-07-27 Airbus Canada Limited Partnership Aircraft engine assembly
FR3075760B1 (en) * 2017-12-21 2020-01-31 Safran Nacelles AIRCRAFT ENGINE PLATFORM

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US4391409A (en) * 1980-09-30 1983-07-05 The Boeing Company Positioning and control system for fan thrust reverser cowls in a turbofan engine
US6519929B2 (en) * 2001-04-30 2003-02-18 Honeywell International, Inc. System and method for controlling the deployment of jet engine thrust reversers
FR2846375B1 (en) * 2002-10-25 2006-06-30 Hispano Suiza Sa ELECTROMACANIC PUSH INVERTER FOR TURBOREACTOR WITH RELEASE OF DOOR MOVEMENT
FR2932226B1 (en) * 2008-06-06 2013-08-23 Aircelle Sa METHOD FOR SYNCHRONIZING THE ACTUATORS OF A MOBILE COVER OF PUSHED INVERTER
FR2933070B1 (en) * 2008-06-25 2010-08-20 Snecma PROPULSIVE AIRCRAFT SYSTEM
FR2962978B1 (en) * 2010-07-22 2012-08-03 Aircelle Sa TURBOREACTOR NACELLE
FR2974150B1 (en) * 2011-04-14 2013-04-12 Aircelle Sa THRUST INVERTER FOR AIRCRAFT TURBOREACTOR

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US20150260125A1 (en) 2015-09-17
CA2893260A1 (en) 2014-06-19
FR2999240B1 (en) 2015-01-02
WO2014091139A1 (en) 2014-06-19
FR2999240A1 (en) 2014-06-13
BR112015011506A2 (en) 2017-07-11
RU2015128055A (en) 2017-01-18

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