EP2961974A1 - Thrust reverser device - Google Patents

Thrust reverser device

Info

Publication number
EP2961974A1
EP2961974A1 EP14711834.3A EP14711834A EP2961974A1 EP 2961974 A1 EP2961974 A1 EP 2961974A1 EP 14711834 A EP14711834 A EP 14711834A EP 2961974 A1 EP2961974 A1 EP 2961974A1
Authority
EP
European Patent Office
Prior art keywords
mast
grids
spacer
movable
connecting member
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Withdrawn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
EP14711834.3A
Other languages
German (de)
French (fr)
Inventor
Patrick BOILEAU
Peter Segat
Pierre Caruel
Sarah TISSOT
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 EP2961974A1 publication Critical patent/EP2961974A1/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Withdrawn legal-status Critical Current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
    • F02K1/64—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
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
    • 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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/90—Mounting on supporting structures or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated

Definitions

  • the invention lies in the field of turbojet engine nacelles and more specifically relates to a thrust reverser device.
  • An aircraft is propelled by one or more propulsion units comprising a turbojet engine housed in a tubular nacelle.
  • Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
  • a nacelle generally has a structure comprising an upstream air intake section, upstream of the engine, a median section intended to surround a fan of the turbojet engine, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing a device. reverse thrust.
  • the displacement device is able to comprise a cowl that is movable in translation along the axis of the nacelle, this translation being effected most often by means of a sliding connection made between the mobile cowl and the mast of attachment of a propulsion unit to the aircraft.
  • the thrust reverser device can implement translational grids which are retracted on the fan casing (or fan casing) in the direct jet position and which, at the moment of passing into the reverse thrust position, slide towards downstream of the nacelle in concert with the movable thrust reverser hood (or transcowl) to deploy and reach their thrust reversal position.
  • the translating grids are slideably connected to the fan casing, but they are also connected to the movable thrust reverser cowl which brings them to their thrust reversal position.
  • This type of device has drawbacks in particular in that, in operation of the turbojet, there are relative displacements between the fan casing and the movable thrust reverser cowl which induces unwanted forces on the slide connection between the fan casing and the translating grids.
  • the object of the invention is to provide a thrust reversal device freed from the aforementioned drawbacks.
  • the present invention relates to a thrust reverser device for an aircraft turbojet engine comprising:
  • translating grids connected to the movable cowl moved between a jet position in which they are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they are out said fan casing,
  • a front suspension means of said turbojet engine remarkable in that the translating grids are slidably connected to the mast via at least one strut connected to the mast downstream of the front suspension.
  • the thrust reverser device comprises one or more of the following optional features considered alone or according to all the possible combinations:
  • the spacer is removably attached to the mast;
  • the spacer comprises fixed grids;
  • the translating grids comprise a rear frame downstream of which is embedded a ring of flaps of inversion of thrust whose dimensions relative to a main axis of the thrust reversal device is enlarged to the downstream end of the thrust reversing flaps, the shutter ring allows to extend the guide distance of the translating grids on the spacer;
  • the assembly formed by the rear frame and the flap shell is in slide connection with the mast;
  • the assembly formed by the rear frame and the flap shell is in sliding connection directly with the mast;
  • a second spacer located between the mast and the translating grids is attached to the main course of the translatant gyrules on which they come to rest on the one hand and is linked to a connecting member connected to the mast somewhere else ;
  • the second spacer is located between the first spacer and the axis of the thrust reverser device;
  • the second spacer has a bead, extending radially outwardly of the thrust reverser device, substantially straight, parallel to the
  • An acoustic panel capable of cooperating with the recessed portion of the inner wall of the movable cowl is fixed on the shutter ring and located under the fixed grids so that the acoustic panel does not rotate with the rest of the movable cowl when an opening thereof in a maintenance position;
  • the acoustic panel attached to the shutter ring is also fixed on a translation slide, in slide connection with the fixed grids, translational grids, so as to keep with it a stress path in the deployed position;
  • the acoustic panel has an angle of 45 ° between its downstream edge and its edge farthest from the mast in order to optimize the transmission of forces towards the hinges of the beam, the inner wall of the movable cowl being hollowed so that the wall inside the mobile hood and the acoustic panel have a complementary shape;
  • the rear frame and the flap shell are relaxed, in particular so as not to transmit parasitic bending moment between the mast and the assembly formed by the rear frame and the flap shell;
  • an area to be relaxed is the area of the flap shell located under the fixed gates when the movable cowl is in the direct jet position;
  • the invention also relates to a nacelle comprising such a thrust reversal device.
  • the invention also relates to a method for respectively detaching (attaching) an engine from an aircraft to (the) mast including a dismantling step (mounting) of the fixed grids of the (to) mast and a dismantling step (mounting) of the suspensions which connect the engine to the mast.
  • FIG. 1 is a perspective view of a thrust reverser device according to a preferred embodiment of the present invention, the outer covers having been removed,
  • FIG. 2 is a perspective view of the zone (II) defined in FIG. 1 of the thrust reverser device according to the preferred embodiment of the present invention
  • FIG. 3 is a partial sectional view of the thrust reverser device according to the preferred embodiment of the present invention taken along the direction (III) defined in FIG. 2;
  • FIG. 4 is a partial sectional view of the thrust reverser device according to another preferred embodiment of the present invention taken in a similar manner to FIG. 3;
  • FIG. 5 is a perspective view of the device in an intermediate disassembly / assembly phase
  • FIG. 6 is a schematic partial view of the device in an intermediate disassembly / assembly phase taken along the direction (VI) of FIG. 5.
  • a thrust reverser device for an aircraft turbojet engine comprising: a mobile cover (not shown),
  • translational grids 1 connected to the movable cowl, movable between a positron de j and di rect in which the elements are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they came out of said fan case,
  • the translating grids 1 are slidably connected to the mast 2 via fixed grids 3 connected to the mast 2 downstream of the front suspension 4.
  • the front suspension 4 is the upstream suspension of the engine or turbojet engine of the aircraft.
  • An airplane may comprise two means of suspensions for a turbojet engine, one before and one behind.
  • Upstream means what comes before the point or element considered, in the direction of the flow of air in a turbojet, and downstream which comes after the point or element considered, in the direction of flow air in a turbojet.
  • the fixed grids 3 are removably mounted on the mast 2 via a set 5 of fittings 5a and 5b, the brackets 5b preferably being integrated in the mast 2, the brackets 5a being integrated with the edge of the fixed grids 3 closest to the mast 2 when positioned relative to the mast 2 in a manner suitable for thrust reversal.
  • the fixed grids 3 form a rectangle and are extended on the upstream edge of the rectangle by a bracket 6, the bracket 6 and the rectangle having a common edge and being manufactured in a monolithic manner; orthogonal to this common song is another song of the square 6 q u i fits in the continuity of the singing of the rectangle farthest from the mast 2.
  • chanting 7 we will call these last two songs chanting 7.
  • the translating grids are located substantially in the fan casing (also called in the English terminology “fan casing”). ").
  • the link between the translating gates 1 and the fixed gates 3 is described: the translating gates 1 and the fixed gates 3 are in slide connection.
  • the edge 7 has a rail 8 (FIG 3) for this purpose shaped in such a way as to be able to hold the translating gates 1 in sliding connection.
  • the translating grids 1 are situated substantially upstream of the fixed grids 3 on the part of the edge 7 forming one side of the bracket 6, whereas in the reverse thrust position, they are located substantially in the extension of the blades of the fixed gates 3.
  • a spacer 9 is described between the mast 2 and the translating gates 1, and fixed on a lateral frame 10 of the translating gates 1 on which they come to rest on the one hand and linked to a connecting member 1 1 linked to the mast 2 on the other hand.
  • the spacer 9 is situated between the fixed grids 3 and the axis ⁇ (FIG.1) of the thrust reverser device.
  • the spacer 9 has a bead 1 2, extending radially outwardly of the thrust reverser device, substantially rectilinear, parallel to the axis ⁇ of the thrust reverser device, and located on the edge of the spacer 9 closest to the mast 2.
  • the spacer 9 is in sliding connection with the connecting member 1 1 through a groove 13 of the connecting member 1 1, and the bead 12.
  • the bead 12 has a substantially half-moon shaped contour and the groove 13 has an outline of a substantially complementary shape.
  • the connecting member 1 1 is fixed relative to the mast 2 and it is integrated aum t 2, grassilau rs s hird ibs can be ra p po rt surlem 2 2.
  • the connecting member 1 1 falls within the continuity of a primary rail 14, to which it is integrated, for guiding in translation of the movable reverse thrust cover (or transcowl), the primary rail 14 being integrated in the mast 2.
  • the connecting member 1 1 is integrated with the edge 15 of the movable cover to be inserted in the primary rail 14.
  • the connecting member 1 1 is in sliding connection by report to the mast 2.
  • the thrust reverser device when the thrust reverser device is actuated in deployment to its inverted jet position (in reverse thrust mode), the movable cowl translates from a retracted position to an extended position downstream of the mast. 2 and along this mast 2 through the primary rail 14 in which its edge 15 is inserted.
  • the movable cowl As the movable cowl is in connection with the translational grids 1, it pulls the translatant grids 1 at least over part of its travel in order to bring them into the inverted downstream position of the inverted jet.
  • the translating grids 1 then translate downstream of the mast 2 and along the mast 2 thanks to the edge rail 7 of the fixed grids 3.
  • the spacer 9 translates along the connecting groove 13.
  • the spacer 9 serves not only to optimize the translational guidance of the translational grids 1, but also to take up the radial forces induced in the translational grids 1.
  • the modus operandi is the same as in the previously described, except that the connecting member 1 1 translate in concert with the movable cover (not shown).
  • the invention also relates to a nacelle (not shown) comprising a thrust reverser device as described above.
  • a method for detaching is described above.
  • an aircraft engine (respectively) to the mast 2 comprising a step of disassembling (respectively mounting) the fixed grids 3 of (re s pect i ve mentau) m et 2 and a sta ded d eted my tag e (respectively mounting) suspensions 4 which connect the engine to the mast 2.
  • the device as described above is particularly visible in the disassembled position in Figure 6 where the connection between the fixed grids 3 and the mast 2 has been dismantled and where the spacer 9 is disengaged from the connecting member January 1.

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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)

Abstract

The subject of the present invention is a thrust reverser device for an aircraft turbojet engine comprising: - a mobile cowl, translating cascades of vanes 1, connected to the mobile cowl able to be moved between a direct-jet position in which they are retracted inside a fan casing, on the one hand, and on the other hand an indirect-jet position in which they are deployed out of said fan casing, - a strut 2, - a front suspension means 4 of said turbojet engine, notable in that the translating cascades of vanes 1 have a sliding connection with the strut 2 via at least one spacer piece 3 connected to the strut 2 downstream of the front suspension 4.

Description

DISPOSITIF D'INVERSION DE POUSSEE  PUSH REVERSING DEVICE
L'invention se situe dans le domaine des nacelles de turboréacteur et plus précisément concerne un dispositif d'inversion de poussée. The invention lies in the field of turbojet engine nacelles and more specifically relates to a thrust reverser device.
Un avion est propulsé par un ou plusieurs ensembles propulsifs comprenant un turboréacteur logeant dans une nacelle tubulaire. Chaque ensemble propulsif est rattaché à l'avion par un mât situé généralement sous une aile ou au niveau du fuselage.  An aircraft is propelled by one or more propulsion units comprising a turbojet engine housed in a tubular nacelle. Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
Une nacelle présente généralement une structure comprenant une section amont d'entrée d'air, en amont du moteur, une section médiane destinée à entourer une soufflante du turboréacteur, et une section aval destinée à entourer la chambre de combustion du turboréacteur et abritant un dispositif d'inversion de poussée.  A nacelle generally has a structure comprising an upstream air intake section, upstream of the engine, a median section intended to surround a fan of the turbojet engine, and a downstream section intended to surround the combustion chamber of the turbojet engine and housing a device. reverse thrust.
Classiquement, le d ispos itif d ' i nvers ion d e pou ssée peut comprendre un capot mobile en translation le long de l'axe de la nacelle, cette translation s'effectuant le plus souvent grâce à une liaison glissière réalisée entre le capot mobile et le mât de rattachement d'un ensemble propulsif à l'avion.  Conventionally, the displacement device is able to comprise a cowl that is movable in translation along the axis of the nacelle, this translation being effected most often by means of a sliding connection made between the mobile cowl and the mast of attachment of a propulsion unit to the aircraft.
Classiquement, le dispositif d'inversion de poussée peut mettre en œuvre des grilles translatantes qui sont escamotées sur le carter de soufflante (ou carter fan) en position de jet direct et qui, au moment du passage en position d'inversion de poussée coulissent vers l'aval de la nacelle de concert avec le capot mobile d'inverseur de poussée (ou transcowl) pour se déployer et atteindre leur position d'inversion de poussée.  Conventionally, the thrust reverser device can implement translational grids which are retracted on the fan casing (or fan casing) in the direct jet position and which, at the moment of passing into the reverse thrust position, slide towards downstream of the nacelle in concert with the movable thrust reverser hood (or transcowl) to deploy and reach their thrust reversal position.
Dans ce dispositif, les grilles translatantes sont en liaison glissière avec le carter de soufflante, mais elles sont aussi l iées au capot mobile d'inverseur de poussée qu i les amène vers leur position d'inversion de poussée.  In this device, the translating grids are slideably connected to the fan casing, but they are also connected to the movable thrust reverser cowl which brings them to their thrust reversal position.
Dans ce type de dispositif, il peut exister une zone de suspension entre le mât et le carter de soufflante, située en amont du mat. Les grilles translatantes ne peuvent être fixées dans cette zone de suspension avant pour cause d'interférences.  In this type of device, there may be a suspension zone between the mast and the fan casing, located upstream of the mast. Translational grids can not be fixed in this forward suspension zone due to interference.
Ce type de dispositif présente des inconvénients notamment en ce que, en fonctionnement du turboréacteur, il existe des déplacements relatifs entre le carter de soufflante et le capot mobile d'inverseur de poussée qui induit des efforts non désirés sur la liaison glissière entre le carter de soufflante et les grilles translatantes. This type of device has drawbacks in particular in that, in operation of the turbojet, there are relative displacements between the fan casing and the movable thrust reverser cowl which induces unwanted forces on the slide connection between the fan casing and the translating grids.
Ces efforts non désirés non seulement fragilisent l'ensemble du dispositif, mais aussi provoquent des désalignements des grilles translatantes au niveau de leur liaison glissière avec le carter avant, fragilisant ainsi la fiabilité d'un tel dispositif.  These undesired efforts not only weaken the entire device, but also cause misalignment of the translating grids at their slide connection with the front casing, thus weakening the reliability of such a device.
Le but de l'invention est de fournir un dispositif d'inversion de poussée affranchi des inconvénients précités. The object of the invention is to provide a thrust reversal device freed from the aforementioned drawbacks.
A cet effet, la présente invention a pour objet un dispositif d'inversion de poussée pour turboréacteur d'avion comprenant : For this purpose, the present invention relates to a thrust reverser device for an aircraft turbojet engine comprising:
- un capot mobile,  - a mobile hood,
- des grilles translatantes reliées au capot mobile, déplaçâmes entre u ne position de jet d irect dans laq uel le el les sont escamotées dans un carter de soufflante d'une part, et d'autre part une position de jet indirect où elles sont sorties du dit carter de soufflante,  translating grids connected to the movable cowl, moved between a jet position in which they are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they are out said fan casing,
- un mât,  - Matt,
- un moyen de suspension avant du dit turboréacteur, remarquable en ce q ue les grilles translatantes sont en liaison glissière avec le mât par l'intermédiaire d'au moins une entretoise liée au mât en aval de la suspension avant.  a front suspension means of said turbojet engine, remarkable in that the translating grids are slidably connected to the mast via at least one strut connected to the mast downstream of the front suspension.
Selon d'autres caractéristiques de l'invention, le dispositif d'inversion de poussée comporte l'une ou plusieurs des caractéristiques optionnelles suivantes considérées seules ou selon toutes les combinaisons possibles : According to other features of the invention, the thrust reverser device comprises one or more of the following optional features considered alone or according to all the possible combinations:
- l'entretoise est fixée de manière amovible sur le mât ; the spacer is removably attached to the mast;
- l'entretoise comprend des grilles fixes ; les grilles translatantes comprennent un cadre arrière en aval duquel est encastrée u ne virole de volets d' inversion de poussée dont les dimensions par rapport à un axe principal du d ispositif d'inversion de poussée sont agrandies jusqu'à l'extrémité aval des volets d'inversion de poussée, la virole de volets permet d'allonger la distance de guidage des grilles translatantes sur l'entretoise ; l'ensemble formé par le cadre arrière et la virole de volets est en liaison glissière avec le mât ; l'ensemble formé par le cadre arrière et la virole de volets est en liaison glissière directement avec le mât ; une deuxième entretoise située entre le mât et les grilles translatantes est fixée su r u n cad re l atéral d es g ri l l es translatantes sur laquelle elles viennent s'appuyer d'une part et est liée à un organe de liaison lié au mât d'autre part ; la deuxième entretoise est située entre la première entretoise et l'axe du dispositif d'inversion de poussée ; la deuxième entretoise présente un bou rrelet, s'étendant radialement vers l'extérieur du dispositif d'inversion de poussée, sensiblement rectiligne, parallèle à l'axe du dispositif d'inversion de poussée, et situé sur le chant de la deuxième entretoise le plus près du mât ; la deuxième entretoise est en liaison glissière avec l'organe de liaison par l'intermédiaire de la gorge et du bourrelet ; le bourrelet présente un contour sensiblement en forme de demi-lune et l a go rg e présente un contou r d 'une forme sensiblement complémentaire ; l'organe de liaison est fixe par rapport au mât auquel il est intégré ou rapporté ; l'organe de liaison est en liaison glissière par rapport au mât ; l'organe de liaison est en liaison glissière par rapport au mât par l'intermédiaire d'un rail primaire de guidage en translation du capot mobile d'inverseur de poussée ; l'organe de l ia ison est intég ré au chant du capot mobile d'inverseur de poussée ; l e ca pot mobi l e est en l iaison gl issière avec le mât par l'intermédiaire d'une poutre sur laquelle le capot mobile est articulé de sorte que le capot mobile coulisse selon l'axe du dispositif d'inversion de poussée, ainsi, l'ensemble formé par les grilles translatantes et le capot mobile est solidaire du mât, permettant ainsi un guidage et une reprise d'effort optimale vers celui-ci ; la poutre est en liaison glissière avec le rail primaire et un rail secondaire ; le rail secondaire est situé radialement entre une paroi externe du capot mobile et les grilles fixes ; une glissière primaire en liaison glissière avec le rail primaire présente une découpe sensiblement située au niveau de l'extrémité aval des grilles fixes ; la partie de la gl issière prima ire en amont de la découpe supporte le cadre arrière et la virole de volets et la partie de la glissière primaire en aval de la découpe supporte la poutre, de façon à permettre une rotation de l'ensemble formé par le cadre arrière et la virole de volets autour du mât et empêcher ainsi le passage de moments de flexion parasites entre le mât et l'ensemble cadre formé par le cadre arrière et la virole de volets ; le capot mobile est articulé sur la poutre par des charnières ; des moyens de reprise discrets des efforts axial et radial sont disposés sur l'extrémité aval de la virole de volets et l'extrémité amont d'une paroi interne du capot mobile ; les moyens de reprise discrets sont des secteurs de couteaux- cannelures ; la poutre comprend des raidisseurs ; la poutre présente un évidement de sorte que la poutre et les grilles fixes soient imbriquées une fois montées ; la poutre est liée directement avec la seconde entretoise ; la poutre est encastrée directement sur la seconde entretoise ; les grilles translatantes, le cadre arrière et la virole de volets sont liés à la poutre ; les grilles translatantes, le cadre arrière et la virole de volets sont encastrés sur la poutre du côté de leurs chants situés en regard du mât, ainsi la poutre les grilles translatantes, la virole de volets forment un ensemble monolithique en liaison glissière avec le mât ; les grilles translatantes, le cadre arrière et la virole de volets sont encastrés sur la poutre du côté de leurs chants situés en regard du mât, ainsi la poutre les grilles translatantes, la virole de volets et la seconde entretoise forment un ensemble monolithique en liaison glissière avec le mât ; le cadre arrière présente un évidement de passage des grilles fixes durant la translation de l'ensemble mobile ; le capot mobile peut tourner autour de la poutre pour permettre au capot mobile de passer en position de maintenance. - la paroi interne du capot mobile comprend une partie évidée de façon à permettre au capot mobile de tourner autour du mât par l'intermédiaire de la poutre pour les opérations de maintenance moteur sans en être empêché par les grilles fixes ; the spacer comprises fixed grids; the translating grids comprise a rear frame downstream of which is embedded a ring of flaps of inversion of thrust whose dimensions relative to a main axis of the thrust reversal device is enlarged to the downstream end of the thrust reversing flaps, the shutter ring allows to extend the guide distance of the translating grids on the spacer; the assembly formed by the rear frame and the flap shell is in slide connection with the mast; the assembly formed by the rear frame and the flap shell is in sliding connection directly with the mast; a second spacer located between the mast and the translating grids is attached to the main course of the translatant gyrules on which they come to rest on the one hand and is linked to a connecting member connected to the mast somewhere else ; the second spacer is located between the first spacer and the axis of the thrust reverser device; the second spacer has a bead, extending radially outwardly of the thrust reverser device, substantially straight, parallel to the axis of the thrust reverser device, and located on the edge of the second spacer the closer to the mast; the second spacer is in sliding connection with the connecting member via the groove and the bead; the bead has a contour substantially in the shape of a half-moon and the ridge has a contour of a substantially complementary shape; the connecting member is fixed relative to the mast to which it is integrated or reported; the connecting member is in sliding connection relative to the mast; the connecting member is slidably connected relative to the mast by means of a primary guide rail in translation of the movable thrust reverser cowl; the Ion member is integral with the edge of the moving thrust reverser cowl; the movable pot is in the glissière laison with the mast via a beam on which the movable cowl is articulated so that the movable cowling slides along the axis of the thrust reverser device, thus, the assembly formed by the translating grids and the movable cowl is secured to the mast, thus allowing guidance and recovery of optimum effort towards it; the beam is in slide connection with the primary rail and a secondary rail; the secondary rail is located radially between an outer wall of the movable cowl and the fixed grids; a primary slide in sliding connection with the primary rail has a cutout substantially located at the downstream end of the fixed gates; the portion of the primary slide upstream of the cutout supports the rear frame and the flap shell and the portion of the primary slide downstream of the cutout supports the beam, so as to allow rotation of the assembly formed by the rear frame and the shutter ring around the mast and thus prevent the passage of parasitic bending moments between the mast and the frame assembly formed by the rear frame and the flap shell; the movable cowl is hinged to the beam by hinges; discrete recovery means axial and radial forces are arranged on the downstream end of the flap shell and the upstream end of an inner wall of the movable cowl; the discrete recovery means are sectors of knives-flutes; the beam comprises stiffeners; the beam has a recess so that the beam and fixed gates are nested once mounted; the beam is directly connected with the second spacer; the beam is embedded directly on the second spacer; the translating grids, the rear frame and the flap shell are connected to the beam; the translating grids, the rear frame and the flap shell are recessed on the beam on the side of their edges located opposite the mast, and the beam translating grids, the flap shell form a monolithic assembly in sliding connection with the mast; the translating grids, the rear frame and the flap shell are recessed on the beam on the side of their edges facing the mast, so the beam translating grids, the flap shell and the second spacer form a monolithic assembly in slide connection with the mast; the rear frame has a passage recess fixed grids during the translation of the movable assembly; the movable hood can rotate around the beam to allow the movable hood to move to the maintenance position. - The inner wall of the movable cowl comprises a recessed portion so as to allow the movable cowl to rotate around the mast via the beam for the engine maintenance operations without being prevented by the fixed grids;
- un panneau acoustique apte à coopérer avec la partie évidée de la paroi interne du capot mobile est fixé sur la virole de volets et situé sous les grilles fixes de telle sorte que le panneau acoustique ne pivote pas avec le reste du capot mobile lors d'une ouverture de celui-ci dans une position de maintenance ; - An acoustic panel capable of cooperating with the recessed portion of the inner wall of the movable cowl is fixed on the shutter ring and located under the fixed grids so that the acoustic panel does not rotate with the rest of the movable cowl when an opening thereof in a maintenance position;
- le panneau acoustique fixé à la virole de volets est aussi fixé sur une glissière de translation, en liaison glissière avec les grilles fixes, des grilles translatantes, de façon à conserver avec elle un chemin d'effort en position déployée ; - The acoustic panel attached to the shutter ring is also fixed on a translation slide, in slide connection with the fixed grids, translational grids, so as to keep with it a stress path in the deployed position;
- le panneau acoustique présente un angle de 45° entre son bord aval et son bord le plus éloigné du mât afin d'optimiser la transmission des efforts vers les charnières de la poutre, la paroi interne du capot mobile étant évidée de manière que la paroi interne d u capot mobile et le pan neau acoustiq ue présentent une forme complémentaire ; the acoustic panel has an angle of 45 ° between its downstream edge and its edge farthest from the mast in order to optimize the transmission of forces towards the hinges of the beam, the inner wall of the movable cowl being hollowed so that the wall inside the mobile hood and the acoustic panel have a complementary shape;
- le cadre arrière et la virole de volets sont assouplis, notamment de façon à ne pas transmettre de moment de flexion parasite entre le mât et l'ensemble formé par le cadre arrière et la virole de volets ; - The rear frame and the flap shell are relaxed, in particular so as not to transmit parasitic bending moment between the mast and the assembly formed by the rear frame and the flap shell;
- une zone à assoupl ir est la zone de la virole de volets se trouvant sous les grilles fixes lorsque le capot mobile est en position de jet direct ; an area to be relaxed is the area of the flap shell located under the fixed gates when the movable cowl is in the direct jet position;
L'invention concerne aussi à une nacelle comprenant un tel dispositif d'inversion de poussée. The invention also relates to a nacelle comprising such a thrust reversal device.
Cette solution permet d'éviter tout guidage des grilles translatantes sur le carter de soufflante. Ainsi les efforts du moteur passent intégralement vers le mât via le moyen de suspension avant. Autrement, les grilles feraient office de suspension et cela dépasserait leur capacité structurale. This solution makes it possible to avoid guiding the translating grids on the fan casing. Thus the efforts of the motor pass entirely towards the mast via the front suspension means. Otherwise, the grids would serve as a suspension and this would exceed their structural capacity.
L'invention concerne aussi un procédé pour respectivement détacher (attacher) un moteur d'un avion du (au) mât comprenant une étape de démontage (montage) des grilles fixes du (au) mât et une étape de démontage (montage) des suspensions qui relient le moteur au mât. The invention also relates to a method for respectively detaching (attaching) an engine from an aircraft to (the) mast including a dismantling step (mounting) of the fixed grids of the (to) mast and a dismantling step (mounting) of the suspensions which connect the engine to the mast.
On décrit à présent, à titre d'exemple non limitatif, un mode de réalisation possible de l'invention, en référence aux figures annexées ; sur l'ensemble des figures, des références identiques ou analogues désignent des organes ou ensembles d'organes identiques ou analogues : We will now describe, by way of nonlimiting example, a possible embodiment of the invention, with reference to the appended figures; in the set of figures, identical or similar references denote identical or similar organs or sets of members:
- la figure 1 est une vue en perspective d'un dispositif d'inversion de poussée selon un mode de réalisation préféré de la présente invention les capots extérieurs ayant été retirés, FIG. 1 is a perspective view of a thrust reverser device according to a preferred embodiment of the present invention, the outer covers having been removed,
- la figure 2 est une vue en perspective de la zone (II) définie sur la figure 1 du dispositif d'inversion de poussée selon le mode de réalisation préféré de la présente invention, FIG. 2 is a perspective view of the zone (II) defined in FIG. 1 of the thrust reverser device according to the preferred embodiment of the present invention,
- la figure 3 est une vue en coupe partielle du dispositif d'inversion de poussée selon le mode de réalisation préféré de la présente invention prise selon la direction (III) définie sur la figure 2,  FIG. 3 is a partial sectional view of the thrust reverser device according to the preferred embodiment of the present invention taken along the direction (III) defined in FIG. 2;
- la figure 4 est une vue en coupe partielle du dispositif d'inversion de poussée selon un autre mode de réalisation préféré de la présente invention prise de manière analogue à la figure 3,  FIG. 4 is a partial sectional view of the thrust reverser device according to another preferred embodiment of the present invention taken in a similar manner to FIG. 3;
- la figure 5 est une vue en perspective du dispositif dans une phase intermédiaire de démontage / montage, et - la figure 6 est une vue partielle schématique du dispositif dans une phase intermédiaire de démontage / montage prise selon la direction (VI) de la figure 5.  FIG. 5 is a perspective view of the device in an intermediate disassembly / assembly phase, and FIG. 6 is a schematic partial view of the device in an intermediate disassembly / assembly phase taken along the direction (VI) of FIG. 5.
En référence à la figure 1 , on décrit un dispositif d'inversion de poussée pour turboréacteur d'avion comprenant : - un capot mobile (non représenté), Referring to Figure 1, there is described a thrust reverser device for an aircraft turbojet engine comprising: a mobile cover (not shown),
- des grilles translatantes 1 reliées au capot mobile, déplaçables entre u ne pos ition d e j et d i rect da n s l aq uel l e el l es sont escamotées dans un carter de soufflante d'une part, et d'autre part une position de jet indirect où elles sont sorties du dit carter de soufflante,  translational grids 1 connected to the movable cowl, movable between a positron de j and di rect in which the elements are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they came out of said fan case,
- un mât 2,  - a mast 2,
- un moyen de suspension avant 4 du dit turboréacteur, les grilles translatantes 1 sont en liaison glissière avec le mât 2 par l'intermédiaire de grilles fixes 3 liée au mât 2 en aval de la suspension avant 4.  a front suspension means 4 of said turbojet engine, the translating grids 1 are slidably connected to the mast 2 via fixed grids 3 connected to the mast 2 downstream of the front suspension 4.
La suspension avant 4 est la suspension amont du moteur ou turboréacteur de l'avion.  The front suspension 4 is the upstream suspension of the engine or turbojet engine of the aircraft.
Un avion peut comprendre deux moyens de suspensions pour un turboréacteur, l'un avant et l'autre arrière.  An airplane may comprise two means of suspensions for a turbojet engine, one before and one behind.
On entend par amont ce qui vient avant le point ou élément considéré, dans le sens de l'écoulement de l'air dans un turboréacteur, et par aval ce q u i vient après le point ou él ément considéré, dans le sens de l'écoulement de l'air dans un turboréacteur.  Upstream means what comes before the point or element considered, in the direction of the flow of air in a turbojet, and downstream which comes after the point or element considered, in the direction of flow air in a turbojet.
Les grilles fixes 3 sont montées de manière amovible sur le mât 2 par l'intermédiaire d'un ensemble 5 de ferrures 5a et 5b, les ferrures 5b étant de préférence intégrées au mât 2, les ferrures 5a étant intégrées au chant des grilles fixes 3 le plus proche du mât 2 lorsqu'elles sont positionnées par rapport au mât 2 d'une manière adaptée pour l'inversion de poussée.  The fixed grids 3 are removably mounted on the mast 2 via a set 5 of fittings 5a and 5b, the brackets 5b preferably being integrated in the mast 2, the brackets 5a being integrated with the edge of the fixed grids 3 closest to the mast 2 when positioned relative to the mast 2 in a manner suitable for thrust reversal.
Préférentiellement, mais non exclusivement, les grilles fixes 3 forment un rectangle et sont prolongées sur le chant amont du rectangle par une équerre 6, l'équerre 6 et le rectangle présentant un chant commun et étant fabriqués de manière monolithique ; orthogonal à ce chant commun se trouve un autre chant de l 'équerre 6 q u i s'inscrit dans la continu ité du chant du rectangle le plus éloigné du mât 2. Par soucis de simplification, on appellera ces deux derniers chants le chant 7.  Preferentially, but not exclusively, the fixed grids 3 form a rectangle and are extended on the upstream edge of the rectangle by a bracket 6, the bracket 6 and the rectangle having a common edge and being manufactured in a monolithic manner; orthogonal to this common song is another song of the square 6 q u i fits in the continuity of the singing of the rectangle farthest from the mast 2. For the sake of simplification, we will call these last two songs chanting 7.
En position de jet direct, c'est-à-dire quand le dispositif d'inversion de poussée n'est pas opérationnel, les grilles translatantes se trouvent sensiblement dans le carter de soufflante (appelé aussi selon la terminologie anglo-saxonne « carter fan »). En référence à la figure 2, on décrit la liaison entre les grilles translatantes 1 et les grilles fixes 3 : les grilles translatantes 1 et les grilles fixes 3 sont en liaison glissière. Le chant 7 présente un rail 8 (Fig . 3) à cet effet conformé de man ière à pourvoir maintenir en liaison glissière les grilles translatantes 1 . En position de jet direct, les grilles translatantes 1 sont situées sensiblement en amont des grilles fixes 3 sur la partie du chant 7 formant un côté de l'équerre 6, tandis qu'en position d'inversion de poussée, elles sont situées sensiblement dans le prolongement des aubes des grilles fixes 3. En référence à la figure 3, on décrit une entretoise 9 située entre le mât 2 et les grilles translatantes 1 , et fixée sur un cadre latéral 10 des grilles translatantes 1 sur laquelle elles viennent s'appuyer d'une part et liée à un organe de liaison 1 1 lié au mât 2 d'autre part. In the direct jet position, that is to say when the thrust reverser device is not operational, the translating grids are located substantially in the fan casing (also called in the English terminology "fan casing"). "). With reference to FIG. 2, the link between the translating gates 1 and the fixed gates 3 is described: the translating gates 1 and the fixed gates 3 are in slide connection. The edge 7 has a rail 8 (FIG 3) for this purpose shaped in such a way as to be able to hold the translating gates 1 in sliding connection. In the direct jet position, the translating grids 1 are situated substantially upstream of the fixed grids 3 on the part of the edge 7 forming one side of the bracket 6, whereas in the reverse thrust position, they are located substantially in the extension of the blades of the fixed gates 3. With reference to FIG. 3, a spacer 9 is described between the mast 2 and the translating gates 1, and fixed on a lateral frame 10 of the translating gates 1 on which they come to rest on the one hand and linked to a connecting member 1 1 linked to the mast 2 on the other hand.
L'entretoise 9 est située entre les grilles fixes 3 et l'axe Δ (Fig. 1 ) du dispositif d'inversion de poussée.  The spacer 9 is situated between the fixed grids 3 and the axis Δ (FIG.1) of the thrust reverser device.
L'entretoise 9 présente un bourrelet 1 2, s'étendant radialement vers l'extérieur du dispositif d'inversion de poussée, sensiblement rectiligne, parallèle à l'axe Δ du dispositif d'inversion de poussée, et situé sur le chant de l'entretoise 9 le plus près du mât 2.  The spacer 9 has a bead 1 2, extending radially outwardly of the thrust reverser device, substantially rectilinear, parallel to the axis Δ of the thrust reverser device, and located on the edge of the spacer 9 closest to the mast 2.
L'entretoise 9 est en liaison glissière avec l'organe de liaison 1 1 par l'intermédiaire d'une gorge 13 de l'organe de liaison 1 1 , et du bourrelet 12.  The spacer 9 is in sliding connection with the connecting member 1 1 through a groove 13 of the connecting member 1 1, and the bead 12.
Le bourrelet 12 présente un contour sensiblement en forme de demi-lune et la gorge 13 présente un contour d'une forme sensiblement complémentaire.  The bead 12 has a substantially half-moon shaped contour and the groove 13 has an outline of a substantially complementary shape.
L'organe de liaison 1 1 est fixe par rapport au mât 2 et il est intégré a u m â t 2, m a i s i l a u ra i t a u ss i b i e n p u être ra p po rté s u r l e m ât 2. Préférentiellement, l'organe de liaison 1 1 s'inscrit dans la continuité d'un rail primaire 14, auquel il est intégré, de guidage en translation du capot mobile d'inversion de poussée (ou transcowl), le rail primaire 14 étant intégré au mât 2.  The connecting member 1 1 is fixed relative to the mast 2 and it is integrated aum t 2, maisilau rs s hird ibs can be ra p po rt surlem 2 2. Preferably, the connecting member 1 1 falls within the continuity of a primary rail 14, to which it is integrated, for guiding in translation of the movable reverse thrust cover (or transcowl), the primary rail 14 being integrated in the mast 2.
En référence à la figure 4, on décrit un autre mode de réalisation de l'organe de liaison 1 1 . Dans ce mode de réalisation, l'organe de liaison 1 1 est intégré au chant 15 du capot mobile devant s'insérer dans le rail primaire 14. Dans ce mode de réalisation, l'organe de liaison 1 1 est donc en liaison glissière par rapport au mât 2. En fonctionnement, lorsque le dispositif d'inversion de poussée est actionné en déploiement vers sa position de jet inversé (en mode d'inversion de poussée), le capot mobile translate d'une position escamotée à une position déployée vers l'aval du mât 2 et le long de ce mât 2 grâce au rail primaire 14 dans lequel son chant 15 est inséré. With reference to FIG. 4, another embodiment of the connecting member 11 is described. In this embodiment, the connecting member 1 1 is integrated with the edge 15 of the movable cover to be inserted in the primary rail 14. In this embodiment, the connecting member 1 1 is in sliding connection by report to the mast 2. In operation, when the thrust reverser device is actuated in deployment to its inverted jet position (in reverse thrust mode), the movable cowl translates from a retracted position to an extended position downstream of the mast. 2 and along this mast 2 through the primary rail 14 in which its edge 15 is inserted.
Le capot mobile étant en liaison avec les grilles translatantes 1 , il tire les grilles translatantes 1 au moins sur une partie de sa course afin de les a m en er d a n s l eur position déployée aval de jet inversé. Les grilles translatantes 1 translatent alors vers l 'aval du mât 2 et le long de ce mât 2 grâce au rail du chant 7 des grilles fixes 3.  As the movable cowl is in connection with the translational grids 1, it pulls the translatant grids 1 at least over part of its travel in order to bring them into the inverted downstream position of the inverted jet. The translating grids 1 then translate downstream of the mast 2 and along the mast 2 thanks to the edge rail 7 of the fixed grids 3.
Parallèlement, l'entretoise 9 translate le long de la gorge de liaison 13. L'entretoise 9 sert non seulement à optimiser le guidage en translation des grilles translatantes 1 , mais aussi à reprendre les efforts radiaux induits dans les grilles translatantes 1 .  Meanwhile, the spacer 9 translates along the connecting groove 13. The spacer 9 serves not only to optimize the translational guidance of the translational grids 1, but also to take up the radial forces induced in the translational grids 1.
L'opération inverse se produit lors de l'escamotage des grilles translatantes 1 dans le carter de soufflante en position de jet direct, c'est-à-dire de croisière. The opposite operation occurs when retracting the translating grids 1 in the fan casing in the direct jet position, that is to say cruising.
Selon un autre mode de réalisation préféré de l'invention où l'organe de liaison 1 1 est intégré au chant 15 du capot mobile (non représenté), le modus operandi est le même que dans le précédemment décrit, à cela près que l'organe de liaison 1 1 translate de concert avec le capot mobile (non représenté). According to another preferred embodiment of the invention in which the connecting member 1 1 is integrated with the edge 15 of the movable cover (not shown), the modus operandi is the same as in the previously described, except that the connecting member 1 1 translate in concert with the movable cover (not shown).
L'invention concerne aussi une nacelle (non représentée) comportant un dispositif d'inversion de poussée tel que décrit ci-dessus. En référence aux figures 5 et 6, on décrit un procédé pour détacherThe invention also relates to a nacelle (not shown) comprising a thrust reverser device as described above. With reference to FIGS. 5 and 6, a method for detaching
(respectivement attacher) un moteur d'avion du (respectivement au) mât 2 comprenant une étape de démontage (respectivement montage) des grilles fi xes 3 d u ( re s pect i ve m e n t a u ) m ât 2 et u n e éta pe d e d é m o n tag e (respectivement montage) des suspensions 4 qui relient le moteur au mât 2. Le dispositif tel que décrit plus haut est particulièrement visible en position démonté sur la figure 6 où la liaison entre les grilles fixes 3 et le mât 2 a été démontée et où l'entretoise 9 est désengagée de l'organe de liaison 1 1 . (respectively attach) an aircraft engine (respectively) to the mast 2 comprising a step of disassembling (respectively mounting) the fixed grids 3 of (re s pect i ve mentau) m et 2 and a sta ded d eted my tag e (respectively mounting) suspensions 4 which connect the engine to the mast 2. The device as described above is particularly visible in the disassembled position in Figure 6 where the connection between the fixed grids 3 and the mast 2 has been dismantled and where the spacer 9 is disengaged from the connecting member January 1.
Il va de soi que l'invention n'est pas limitée au mode de réalisation décrit ci-dessus à titre d'exemple, mais qu'elle comprend tous les équivalents techniques et toutes les variantes des moyens décrits ainsi que leurs combinaisons possibles. It goes without saying that the invention is not limited to the embodiment described above by way of example, but that it includes all technical equivalents and all variants of the means described and their possible combinations.

Claims

REVENDICATIONS
1 . Dispositif d'inversion de poussée pour turboréacteur d'avion comprenant :  1. Thrust reversing device for an aircraft turbojet engine comprising:
un capot mobile,  a mobile hood,
- des grilles translatantes (1 ) rel iées au capot mobile, déplaçables entre une position de jet direct dans laquelle elles sont escamotées dans un carter de soufflante d'une part, et d'autre part une position de jet indirect où elles sont sorties du dit carter de soufflante,  translational grids (1) connected to the movable cowl, movable between a direct jet position in which they are retracted in a fan casing on the one hand, and on the other hand an indirect jet position where they are released from the said blower housing,
- un mât (2),  - a mast (2),
- un moyen de suspension avant (4) du dit turboréacteur, caractérisé en ce que les grilles translatantes (1 ) sont en liaison glissière avec le mât (2) par l'intermédiaire d'au moins une entretoise (3) liée au mât (2) en aval de la suspension avant (4).  - A front suspension means (4) of said turbojet, characterized in that the translating grids (1) are slidably connected to the mast (2) via at least one spacer (3) connected to the mast ( 2) downstream of the front suspension (4).
2. Dispositif selon la revend ication 1 , caractérisé en ce q u e l'entretoise (3) est fixée de manière amovible sur le mât (2).  2. Device according to revendication 1, characterized in that the spacer (3) is removably attached to the mast (2).
3. Dispositif selon l'une quelconque des revendications 1 ou 2, caractérisé en ce que l'entretoise (3) comprend des grilles fixes.  3. Device according to any one of claims 1 or 2, characterized in that the spacer (3) comprises fixed grids.
4. D ispos itif sel on l ' u n e q u el con q u e d es revend i catio n s précédentes, caractérisé en ce qu'une deuxième entretoise (9) située entre le mât (2) et les grilles translatantes (2) est fixée sur un cadre latéral (10) des grilles translatantes (1 ) sur laquelle elles viennent s'appuyer d'une part et est lié à un organe de liaison (1 1 ) liée au mât (2) d'autre part.  4. D ispos itif sel it con con qued the previous revendi catio ns, characterized in that a second spacer (9) located between the mast (2) and the translating grids (2) is fixed on a frame lateral (10) translational grids (1) on which they come to bear on the one hand and is connected to a connecting member (1 1) connected to the mast (2) on the other.
5. Dispositif selon la revendication 4, caractérisé en ce que la deuxième entretoise (9) est située entre la première entretoise (3) et l'axe (Δ) du dispositif d'inversion de poussée.  5. Device according to claim 4, characterized in that the second spacer (9) is located between the first spacer (3) and the axis (Δ) of the thrust reverser device.
6. Dispositif selon l'une quelconque des revend ications 4 ou 5 caractérisé en ce que la deuxième entretoise (9) présente un bourrelet (12), s'étendant radialement vers l'extérieur du dispositif d'inversion de poussée, sensiblement rectiligne, parallèle à l'axe (Δ) du dispositif d'inversion de poussée, et situé sur le chant de la deuxième entretoise (9) le plus près du mât (2).  6. Device according to any one of claims 4 or 5 characterized in that the second spacer (9) has a bead (12), extending radially outwardly of the thrust reverser device substantially rectilinear, parallel to the axis (Δ) of the thrust reverser device, and located on the edge of the second spacer (9) closest to the mast (2).
7. Dispositif selon la revend ication 6 caractérisé en ce que la deuxième entretoise (9) est en liaison glissière avec l'organe de liaison (1 1 ) par l'intermédiaire d'une gorge (13) de l'organe de liaison (1 1 ) et du bourrelet (12). 7. Device according to revendication 6 characterized in that the second spacer (9) is in sliding connection with the connecting member (1 1) via a groove (13) of the connecting member ( 1 1) and the bead (12).
8. Dispositif selon la revendication 7 caractérisé en ce que le bourrelet (12) présente un contour sensiblement en forme de demi-lune et la gorge (13) présente un contour d'une forme sensiblement complémentaire. 8. Device according to claim 7 characterized in that the bead (12) has a contour substantially in the form of a half moon and the groove (13) has an outline of a substantially complementary shape.
9. Dispositif selon l'une quelconque des revendications 4 à 8 caractérisé en ce que l'organe de liaison (11 ) est fixe par rapport au mât (2) auquel il est intégré ou rapporté.  9. Device according to any one of claims 4 to 8 characterized in that the connecting member (11) is fixed relative to the mast (2) which it is integrated or reported.
10. Dispositif selon l'une quelconque des revendications 4 à 8 caractérisé en ce que l'organe de liaison (11) est en liaison glissière par rapport au mât (2).  10. Device according to any one of claims 4 to 8 characterized in that the connecting member (11) is slidably connected relative to the mast (2).
11. Dispositif selon la revendication 10 caractérisé en ce que l'organe de liaison (11) est en liaison glissière par rapport au mât (2) par l'intermédiaire d'un rail primaire (14) de guidage en translation du capot mobile d'inverseur de poussée.  11. Device according to claim 10 characterized in that the connecting member (11) is slidably connected relative to the mast (2) by means of a primary rail (14) for guiding the mobile cowl thrust reverser.
12. Dispositif selon la revendication 11 caractérisé en ce que l'organe de liaison (11) est intégré au chant (15) du capot mobile d'inverseur de poussée.  12. Device according to claim 11 characterized in that the connecting member (11) is integrated in the edge (15) of the movable thrust reverser cowl.
13. Dispositif selon l'une quelconque des revendications précédentes caractérisé en ce que les grilles translatantes comprennent un cadre arrière en aval duquel est encastrée une virole de volets d'inversion de poussée dont les dimensions par rapport à un axe principal du dispositif d'inversion de poussée sont agrandies jusqu'à l'extrémité aval des volets d'inversion de poussée  13. Device according to any one of the preceding claims, characterized in that the translating grids comprise a rear frame downstream of which is embedded a flange of thrust reversing flaps whose dimensions relative to a main axis of the inverting device. thrust are enlarged to the downstream end of the thrust reversing flaps
14. Dispositif selon la revendication 13 caractérisé en ce que l'ensemble formé par le cadre arrière et la virole de volets est en liaison glissière avec le mât.  14. Device according to claim 13 characterized in that the assembly formed by the rear frame and the flap shell is in sliding connection with the mast.
15. Dispositif selon l'une quelconque des revendications précédentes caractérisé en ce que le capot mobile est en liaison glissière avec le mât (2) par l'intermédiaire d'une poutre sur laquelle le capot mobile est articulé de sorte que le capot mobile coulisse selon l'axe du dispositif d'inversion de poussée.  15. Device according to any one of the preceding claims, characterized in that the movable cowl is slidably connected to the mast (2) via a beam on which the movable cowl is articulated so that the movable cowling slides. along the axis of the thrust reverser device.
16. Dispositif selon la revendication 15 caractérisé en ce que la poutre est en liaison glissière avec le rail primaire et un rail secondaire.  16. Device according to claim 15 characterized in that the beam is slidably connected to the primary rail and a secondary rail.
17. Dispositif selon la revendication 16 caractérisé en ce que le rail secondaire est situé radialement entre une paroi externe du capot mobile et les grilles fixes. 17. Device according to claim 16 characterized in that the secondary rail is located radially between an outer wall of the movable hood and the fixed grids.
18. Dispositif selon l'une quelconque des revendications 15 à 17 caractérisé en ce q ue le capot mobile est articulé sur la poutre par des charnières. 18. Device according to any one of claims 15 to 17 characterized in that q ue the movable cowl is hinged to the beam by hinges.
19. Dispositif selon l'une quelconque des revendications 15 à 18 caractérisé en ce que les grilles translatantes (1 ), le cadre arrière et la virole de volets sont liés à la poutre.  19. Device according to any one of claims 15 to 18 characterized in that the translating grids (1), the rear frame and the flap shell are connected to the beam.
20. Dispositif selon l'une quelconque des revendications 15 à 19 caractérisé en ce que la paroi interne du capot mobile comprend une partie évidée de façon à permettre au capot mobile de tourner autour du mât par l'intermédiaire de la poutre pour les opérations de maintenance moteur sans en être empêché par les grilles fixes.  20. Device according to any one of claims 15 to 19 characterized in that the inner wall of the movable cowl comprises a recessed portion so as to allow the movable cowl to rotate around the mast through the beam for the operations of engine maintenance without being prevented by the fixed grids.
21 . Dispositif selon la revendication 20 caractérisé en ce qu'un panneau acoustique apte à coopérer avec la partie évidée de la paroi interne du capot mobile est fixé sur la virole de volets et situé radialement sous les grilles fixes de telle sorte que le panneau acoustique ne pivote pas avec le reste du capot mobile lors d'une ouverture de celui-ci dans une position de maintenance.  21. Device according to claim 20 characterized in that an acoustic panel adapted to cooperate with the recessed portion of the inner wall of the movable cowl is fixed on the flap shell and located radially under the fixed grids so that the acoustic panel does not rotate not with the rest of the movable hood when opening it in a maintenance position.
22. Nacelle caractérisée en ce qu'elle comporte un dispositif d'inversion d e pou ssée selon l ' u ne q uel conq ue des revend ications précédentes.  22. Nacelle characterized in that it comprises a reversal device po ssée according q uel conq ue previous claims ications.
EP14711834.3A 2013-03-01 2014-03-03 Thrust reverser device Withdrawn EP2961974A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1351833A FR3002785B1 (en) 2013-03-01 2013-03-01 TRANSLATANT AND FIXED GRIDS WITH A T / R O-DUCT.
PCT/FR2014/050460 WO2014132011A1 (en) 2013-03-01 2014-03-03 Thrust reverser device

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EP2961974A1 true EP2961974A1 (en) 2016-01-06

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EP14711834.3A Withdrawn EP2961974A1 (en) 2013-03-01 2014-03-03 Thrust reverser device

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US (1) US10190538B2 (en)
EP (1) EP2961974A1 (en)
CN (1) CN105026741A (en)
FR (1) FR3002785B1 (en)
RU (1) RU2015141367A (en)
WO (1) WO2014132011A1 (en)

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CN105026741A (en) 2015-11-04
FR3002785A1 (en) 2014-09-05
FR3002785B1 (en) 2015-03-27
US20160025039A1 (en) 2016-01-28
WO2014132011A1 (en) 2014-09-04
US10190538B2 (en) 2019-01-29
RU2015141367A (en) 2017-04-06

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