WO2014195646A1 - Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls - Google Patents

Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls Download PDF

Info

Publication number
WO2014195646A1
WO2014195646A1 PCT/FR2014/051349 FR2014051349W WO2014195646A1 WO 2014195646 A1 WO2014195646 A1 WO 2014195646A1 FR 2014051349 W FR2014051349 W FR 2014051349W WO 2014195646 A1 WO2014195646 A1 WO 2014195646A1
Authority
WO
WIPO (PCT)
Prior art keywords
thrust reverser
flap
cylinder
fixed
grids
Prior art date
Application number
PCT/FR2014/051349
Other languages
French (fr)
Inventor
Guy Bernard Vauchel
Original Assignee
Aircelle
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 filed Critical Aircelle
Priority to EP14733272.0A priority Critical patent/EP3004614A1/en
Priority to CA2908678A priority patent/CA2908678A1/en
Publication of WO2014195646A1 publication Critical patent/WO2014195646A1/en

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
    • F02K1/76—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
    • 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
    • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
    • F02K1/625—Reversing jet main flow by blocking the rearward discharge by means of flaps the aft end of the engine cowling being movable to uncover openings 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
    • F02K1/54—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
    • 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
    • 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

  • Thrust reverser of a turbojet engine nacelle comprising grids fixed to the movable hoods
  • the present invention relates to a thrust reverser for an aircraft nacelle receiving a turbojet, and an aircraft nacelle equipped with such a thrust reverser.
  • the engine sets for the aircraft comprise a nacelle forming a generally circular outer envelope, comprising inside a turbojet arranged along the longitudinal axis of this nacelle.
  • the turbojet engine receives fresh air from the upstream or front side, and rejects on the downstream or rear side hot gases from the combustion of fuel, which give a certain thrust.
  • fan blades arranged around this turbojet generate a large secondary flow of cold air along an annular vein passing between the engine and the nacelle, which adds a high thrust.
  • Some nacelles include a thrust reversal system that closes at least part of the annular cold air duct, and rejects the secondary flow forward to generate a braking thrust of the aircraft.
  • a known type of thrust reverser presented in particular by the document EP-A2-0321993, comprises rear movable covers that can slide axially backwards under the effect of actuators, by deploying flaps in the annular vein so to at least partially close this vein. These flaps return the flow of cold air radially outward through grids discovered during this sliding, comprising blades that direct the flow forward.
  • the grids are integrated in the thickness of the movable covers, the flaps being folded below these grids, under their lower faces facing the axis of the nacelle.
  • Each grid is fixed by a hinge to the front frame located upstream of these movable pots.
  • Telescopic telescopes that are longitudinally located in the annular vein, have their front ends secured to the inside of the front frame, and their rear ends fixed inside a flap.
  • a problem with this type of thrust reverser is that the cylinders remaining in the annular vein during normal operation of the turbojet engine, slow the flow of cold air and increase consumption.
  • Another type of known thrust reverser presented in particular by US-A-5228641, comprises grids fixed to the front frame, which are integrated in the thickness of the movable covers when the inverter is closed.
  • the flaps disposed below the grids have a front end connected to the movable cowl by a hinge, and a rear end connected by a rod running backwards, to a connecting arm which returns forward in order to be fixed. on the front frame.
  • the present invention is intended to avoid these disadvantages of the prior art.
  • a thrust reverser of a turbojet engine nacelle comprising movable covers which recoil with respect to a front frame by driving by the cylinders the tilting flaps initially located folded inside these hoods, for substantially close the annular cold air duct, and opening grids arranged around this vein which receive the cold air flow to return it forward, remarkable in that the grids are fixed to the movable hoods and slide with them.
  • An advantage of this thrust reverser is that the grids being outside the movable covers, it can easily achieve hoods comprising a reduced radial thickness, which receive in an integrated manner the flaps and their control mechanisms comprising the cylinders.
  • this vein may include a good aerodynamic profile ensuring the performance of the propulsion system.
  • the grid having a less limited space may have a shape that is better adapted to the deflection of the flow.
  • the thrust reverser according to the invention may further comprise one or more of the following features, which may be combined with one another.
  • the flaps comprise a front end connected by a hinge to a movable cover, and a jack comprising a front end fixed to the frame, and the other end fixed to the rear of this flap.
  • the cylinder is at the limit of the outer surface of the annular channel, the flap being connected to the movable cowl by a hinge which is remote from this cylinder radially outwardly. This is obtained by this distance when the flap is folded, a thrust of the cylinder giving a torque of effort on the flap that keeps it pressed on its limit stop.
  • the jack disposed in the longitudinal axis of the flap is integrated in a longitudinal recess of the face of the flap turned radially towards the inside of the nacelle, which avoids leaving this cylinder protruding into the annular vein.
  • the cylinder comprises below a closure plate fixed flat along the length, which adjusts to the face of the flap when it is folded to substantially close the longitudinal recess of the flap.
  • This plate improves the aerodynamic surface of the annular vein.
  • the closure plate comprises its rear end fixed to the rear part of the cylinder rod, and its front end slidingly attached to the body of this cylinder by a linear guide. In thrust reversal, this plate is spaced from the air flow to not slow it down.
  • the rear portion of the flap bears radially outwardly when the inverter is closed, on an adjustable end stop that i can adjust the alignment of this flap with the neighboring surfaces.
  • the rear end of the grilles is fixed to a spoiler located in front of the movable covers, a seal bearing on the front frame, which is located radially inside the grids.
  • the thrust reverser comprises at the front of the movable covers, a seal bearing on the front frame. This seal gives a pressure balance facilitating the opening or closing of the covers.
  • the front ends of grids are interconnected by a circular structure located upstream of the front frame, this structure providing a high rigidity with a reduced mass.
  • the invention also relates to a turbojet engine nacelle comprising a thrust reverser comprising any one of the preceding features.
  • FIG. 1 is a partial view in axial section passing through the center of a flap, an inverter according to the invention which is closed;
  • FIG. 2 is a cross-sectional view of this shutter
  • FIG. 3 is a longitudinal sectional detail view showing the sealing system of movable covers
  • FIG. 4 shows the inverter at the beginning of opening, including the jack being extended
  • FIG. 5 shows the inverter more open, including the cylinder in full extension
  • Figures 1 and 2 present pa rti e behind a nacel l e turbojet, comprising a front frame 2 fixed on the structure located upstream of this part, and movable covers 10 fitted behind this frame.
  • the rear part of the nacelle is covered by two movable covers 10, each forming a semicircle in a transverse plane.
  • Each cover 10 is guided axially by longitudinal guiding means, which allow a sliding backwards under the effect of actuators not shown, bearing on the fixed structure upstream of the movable covers 1 0.
  • the covers 1 0 comprise a locking system in the closed position, which is not shown.
  • the nacel may have an annular movable cowl 10 which likewise slides backward to open the thrust reverser.
  • the secondary annular vein 4 comprises a radially outer contour comprising flaps 8 fitted inside the movable hoods 10 so as to give an aerodynamic continuity, and a radially internal contour formed by the fixed internal structure 6.
  • the rear end of the grids 1 2 is fixed to a spoiler 14 located in front of the movable covers 1 0, that i form a retou r from the outer surface of these covers, towards the center of the nacelle.
  • the grids can slide freely through openings in the front frame 2, in order to follow the movement of the covers 10 when the inverter opens.
  • the cap drive system 10 including the actuators may be attached to the upstream portion of the grid structure 12, to move the assembly including the gills and covers. This disposition frees entirely the passage of air in the structure of the grids 12 in reverse thrust, but impinges on the front cover of the engine.
  • the drive system of the hoods 10 can be fixed to the grids 12 either in the plane of the grids or radially above or below their structure.
  • the drive system of the hoods 10 can also be fixed on the upstream part of the structure of these hoods, by integrating between them em ents of the grids 12. In these of them va ria nts the system of drive is in the air passage in reverse thrust.
  • Each flap 8 comprises an arm extending forwardly inside the movable hood 1 0, ending at its front end by a hinge 1 6 connected to the movable hood, which is arranged just behind the spoiler return 14.
  • the rear portion of the flap 8 bears radially outwardly on a limit stop 18, which positions the flap so as to adjust its face in continuity with the inner surfaces of the front frame 2 and the movable flap 10.
  • the end stops 18 may be adjustable, in order to refine the position of the flaps 8 in the aerodynamic flow.
  • Each flap 8 comprises a telescopic jack 20 disposed in the longitudinal axis of this flap, which is fully integrated in a longitudinal recess of the face of the shutter facing the inside of the nacelle, so as to adjust to the surface outside of the annular vein 4 without exceeding in this vein.
  • the front end of the jack 20 is fixed by a pivot to the front frame 2, the rear end is fixed by a pivot also to a rear part of the flap 8.
  • Each telescopic jack 20 comprises a body containing on the front side a helical compression spring, which exerts a permanent pressure on the front end of its rod 22, to push it backwards to tend to put this cylinder in extension.
  • This optional closure plate 32 is shown in FIGS. 8 and 9. It will be noted that the flaps 8 are kept permanently tensioned by the pressure of the springs of the jacks 20 which tend to push them on their limit stops 1 8, with a certain torque depending on the radial distance between the axis of this end. cylinder and the hinge 1 6 flaps. This pressure avoids flutter flaps 8 which would slow the flow of secondary air.
  • Figure 3 shows a hood 1 0 in its forward position, the thrust reverser being completely closed.
  • the radially inner end of the return spoiler 14 is pressed forward on a seal 30, which is itself resting on the front frame 2, radially inside the grids 1 2.
  • a seal 30 which is itself resting on the front frame 2, radially inside the grids 1 2.
  • Arrangement of the grids 8 integrated upstream of the structure of the movable hoods 1 0, allows this arrangement of the seal that i realizes a pressure eeg uil facilitating the opening or closing of these covers.
  • FIG. 4 shows the inverter at the beginning of opening, the movable covers 10 having begun to move back under the effect of their actuators.
  • the grids 12 begin to leave the front frame 2.
  • the cylinders 20 are being extended. Since the rods 22 are not fully extended, these jacks 20 can continue to deploy without exerting a retaining force on the rear part of the flaps 8 which do not tilt, and remain plated inside the movable covers 10.
  • Figure 5 shows the inverter more open with the moving hoods 10 which continue to move back.
  • the cylinders 20 arrive at full extension with the rods 22 fully out, but the flaps 8 still do not rock.
  • Figure 6 shows the inverter more open still, the rod 22 which can not move back, began to tilt the flap 8 by pulling its rear part down.
  • FIG. 7 shows the fully open inverter, the movable covers 10 are in their maximum rear positions, the shutters 8 are completely lowered when arriving near the fixed internal structure 6.
  • the grids 12 come out more and more of the front frame 2, to finish completely. outlets so as to clear their entire surfaces that allow to deflect the secondary flow.
  • the front ends of all the grids 12 are connected together by a continuous circular structure which is upstream of the front frame 2, which allows a simple way with a reduced mass to obtain a particularly rigid grid assembly.
  • the length of the grids 1 2 is adapted accordingly, so that their front ends remain upstream of the frame 2 when the inverter is fully open.
  • the inner and outer aerodynamic profiles of this vein can be optimized, the fuel consumption is improved.
  • the gap in the movable hoods 1 0 not including the grids 1 2 makes it possible to optimize the position of the hinge before the flaps 8, which can be close to the outer surface of these covers to obtain with the choice of anchor points of the cylinders 20, a good kinematics for the deployment of the flaps.
  • a rather large radial gap between the jacks 20 and the hinge points before 16 of the flaps 8 makes it possible for these jacks to maintain high torque on the folded flaps. It also provides a good distribution of effort and better maneuverability.
  • FIGS. 8 and 9 show the closure plate 32 comprising its rear end fastened to the rear part of the rod of the jack 22, and its front end slidingly attached to the body of this jack by linear guiding, such as a guide rail.
  • the longitudinal hollow of the flap 8 is closed by the plate 32 forming a fairing to improve the aerodynamic performance.
  • the body of the jack 20 is generally disengaged from the closure plate 32 which is cast forwardly with the rod 22, allowing a smooth flow of the flow of the fluid. inversion, and thus an improvement in inversion performance.

Abstract

Turbojet engine nacelle thrust reverser comprising mobile cowls (10) which retreat with respect to a front frame (2), causing, through the intermediary of actuating cylinders (20), flaps (8) that are initially folded up inside these cowls to pivot in order to substantially close off the annular cold air duct (4), and opening cascades of vanes (12) positioned around this duct which receive the stream of cold air and deflect it forward, characterized in that the cascades of vanes (12) are fixed to the mobile cowls (10) and slide therewith.

Description

Inverseur de poussée d'une nacelle de turboréacteur, comprenant des grilles fixées aux capots mobiles  Thrust reverser of a turbojet engine nacelle, comprising grids fixed to the movable hoods
La présente invention concerne un inverseur de poussée pour une nacelle d'aéronef recevant un turboréacteur, ainsi qu'une nacelle d'aéronef équipée d'un tel inverseur de poussée. The present invention relates to a thrust reverser for an aircraft nacelle receiving a turbojet, and an aircraft nacelle equipped with such a thrust reverser.
Les ensembles de motorisation pour les aéronefs comportent une nacelle formant une enveloppe extérieure globalement circulaire, comprenant à l'intérieur un turboréacteur disposé suivant l'axe longitudinal de cette nacelle.  The engine sets for the aircraft comprise a nacelle forming a generally circular outer envelope, comprising inside a turbojet arranged along the longitudinal axis of this nacelle.
Le turboréacteur reçoit de l'air frais venant du côté amont ou avant, et rejette du côté aval ou arrière les gaz chauds issus de la combustion du carburant, qui donnent une certaine poussée. Pour les turboréacteurs à double flux, des aubes de soufflante disposées autour de ce turboréacteur génèrent un flux secondaire important d'air froid le long d'une veine annulaire passant entre le moteur et la nacelle, qui ajoute une poussée élevée.  The turbojet engine receives fresh air from the upstream or front side, and rejects on the downstream or rear side hot gases from the combustion of fuel, which give a certain thrust. For turbofan engines, fan blades arranged around this turbojet generate a large secondary flow of cold air along an annular vein passing between the engine and the nacelle, which adds a high thrust.
Certaines nacelles comportent un système d'inversion de poussée qui ferme au moins en partie la veine annulaire d'air froid, et rejette le flux secondaire vers l'avant afin de générer une poussée de freinage de l'aéronef.  Some nacelles include a thrust reversal system that closes at least part of the annular cold air duct, and rejects the secondary flow forward to generate a braking thrust of the aircraft.
Un type d'inverseur de poussée connu, présenté notamment par le document EP-A2-0321993, comporte des capots mobiles arrière qui peuvent coulisser axialement vers l'arrière sous l'effet d'actionneurs, en déployant des volets dans la veine annulaire afin de fermer au moins partiellement cette veine. Ces volets renvoient le flux d'air froid radialement vers l'extérieur en passant par des grilles découvertes lors de ce coulissement, comprenant des aubes qui dirigent ce flux vers l'avant.  A known type of thrust reverser, presented in particular by the document EP-A2-0321993, comprises rear movable covers that can slide axially backwards under the effect of actuators, by deploying flaps in the annular vein so to at least partially close this vein. These flaps return the flow of cold air radially outward through grids discovered during this sliding, comprising blades that direct the flow forward.
Quand l'inverseur de poussée est fermé, les grilles sont intégrées dans l'épaisseur des capots mobiles, les volets étant repliés en dessous de ces grilles, sous leurs faces inférieures tournées vers l'axe de la nacelle.  When the thrust reverser is closed, the grids are integrated in the thickness of the movable covers, the flaps being folded below these grids, under their lower faces facing the axis of the nacelle.
Chaque grille est fixée par une articulation au cadre avant se trouvant en a m o n t d es ca pots m o b i l e s . Des véri n s tél escop iq u es d i sposés longitudinalennent dans la veine annulaire, comportent leurs extrémités avant fixées à l'intérieur du cadre avant, et leurs extrémités arrière fixées à l'intérieur d'un volet. Each grid is fixed by a hinge to the front frame located upstream of these movable pots. Telescopic telescopes that are longitudinally located in the annular vein, have their front ends secured to the inside of the front frame, and their rear ends fixed inside a flap.
Quand les capots mobiles reculent les vérins télescopiques commencent par s'étendre, et arrivés en bout de course tirent les volets vers l'intérieur de la nacelle afin de les déployer dans la veine annulaire.  When the mobile hoods retract the telescopic cylinders begin to expand, and arrived at the end of the race pull the shutters inwardly of the nacelle to deploy them in the annular vein.
Un problème qui se pose avec ce type d'inverseur de poussée, est que les vérins restant dans la veine annulaire lors du fonctionnement normal du turboréacteur, freinent le flux d'air froid et augmentent la consommation.  A problem with this type of thrust reverser is that the cylinders remaining in the annular vein during normal operation of the turbojet engine, slow the flow of cold air and increase consumption.
Un autre type d'inverseur de poussée connu, présenté notamment par le document US-A-5228641 , comporte des grilles fixées au cadre avant, qui sont intégrées dans l'épaisseur des capots mobiles quand l'inverseur est fermé. Les volets disposés en dessous des grilles, comportent une extrémité avant reliée au capot mobile par une articulation, et une extrémité arrière reliée par une biellette partant vers l'arrière, à un bras de liaison qui revient vers l'avant afin d'être fixé sur le cadre avant.  Another type of known thrust reverser, presented in particular by US-A-5228641, comprises grids fixed to the front frame, which are integrated in the thickness of the movable covers when the inverter is closed. The flaps disposed below the grids, have a front end connected to the movable cowl by a hinge, and a rear end connected by a rod running backwards, to a connecting arm which returns forward in order to be fixed. on the front frame.
Le recul des capots mobiles entraîne une bascule des biellettes et de leurs volets, qui descendent dans la veine annulaire afin de la fermer  The retreat of the movable hoods causes a rocking of the rods and their shutters, which go down into the annular vein in order to close it
Ces types d'inverseur comprenant les grilles et les volets avec leurs systèmes de commande, intégrés dans les capots mobiles quand l'inverseur est fermé, posent des problèmes d'encombrement qui nécessitent de limiter les d imensions des g ril les pour pouvoir les insérer dans ces capots. La performance aérodynamique de ces grilles n'est pas optimisée.  These types of inverter including the grids and the shutters with their control systems, integrated into the mobile covers when the inverter is closed, pose congestion problems that require limiting the dimensions of the g ril to insert them in these hoods. The aerodynamic performance of these grids is not optimized.
La présente invention a notamment pour but d'éviter ces inconvénients de la technique antérieure.  The present invention is intended to avoid these disadvantages of the prior art.
Elle propose à cet effet un inverseur de poussée d'une nacelle de turboréacteur, comprenant des capots mobiles qui reculent par rapport à un cadre avant en entraînant par des vérins le basculement de volets se trouvant initialement repliés à l'intérieur de ces capots, pour fermer sensiblement la veine annulaire d'air froid, et en ouvrant des grilles disposées autour de cette veine qui reçoivent le flux d'air froid pour le renvoyer vers l'avant, remarquable en ce que les grilles sont fixées aux capots mobiles et coulissent avec eux. Un avantage de cet inverseur de poussée est que les grilles étant en dehors des capots mobiles, on peut réaliser facilement des capots comprenant une épaisseur radiale réduite, qui reçoivent de manière intégrée les volets ainsi que leurs mécanismes de commande comprenant les vérins. Ces mécanismes de commande avec les vérins ne dépassent alors pas dans la veine annulaire d'air froid, cette veine peut comporter un bon profil aérodynamique assurant les performances du système de propulsion. De plus la grille disposant d'une place moins limitée, peut comporter une forme mieux adaptée pour la déviation du flux. It proposes for this purpose a thrust reverser of a turbojet engine nacelle, comprising movable covers which recoil with respect to a front frame by driving by the cylinders the tilting flaps initially located folded inside these hoods, for substantially close the annular cold air duct, and opening grids arranged around this vein which receive the cold air flow to return it forward, remarkable in that the grids are fixed to the movable hoods and slide with them. An advantage of this thrust reverser is that the grids being outside the movable covers, it can easily achieve hoods comprising a reduced radial thickness, which receive in an integrated manner the flaps and their control mechanisms comprising the cylinders. These control mechanisms with the cylinders do not then exceed in the annular duct of cold air, this vein may include a good aerodynamic profile ensuring the performance of the propulsion system. In addition, the grid having a less limited space may have a shape that is better adapted to the deflection of the flow.
L'inverseur de poussée selon l'invention peut comporter de plus une ou plusieurs des caractéristiques suivantes, qui peuvent être combinées entre elles.  The thrust reverser according to the invention may further comprise one or more of the following features, which may be combined with one another.
Selon un mode de réalisation, les volets comportent une extrémité avant reliée par une articulation à un capot mobile, et un vérin comprenant une extrémité avant fixée au cadre, et l'autre extrémité fixée à l'arrière de ce volet.  According to one embodiment, the flaps comprise a front end connected by a hinge to a movable cover, and a jack comprising a front end fixed to the frame, and the other end fixed to the rear of this flap.
Avantageusement, le vérin se trouve en limite de la surface extérieure de la veine annulaire, le volet étant relié au capot mobile par une articulation qui est éloignée de ce vérin radialement vers l'extérieur. On obtient ainsi par cet éloignement quand le volet est replié, une poussée du vérin donnant un couple d'effort sur ce volet qui le maintient appuyé sur sa butée de fin de course.  Advantageously, the cylinder is at the limit of the outer surface of the annular channel, the flap being connected to the movable cowl by a hinge which is remote from this cylinder radially outwardly. This is obtained by this distance when the flap is folded, a thrust of the cylinder giving a torque of effort on the flap that keeps it pressed on its limit stop.
Avantageusement, le vérin disposé dans l'axe longitudinal du volet, est intégré dans un creux longitudinal de la face du volet tournée radialement vers l'intérieur de la nacelle, ce qui évite de laisser ce vérin dépasser dans la veine annulaire.  Advantageously, the jack disposed in the longitudinal axis of the flap, is integrated in a longitudinal recess of the face of the flap turned radially towards the inside of the nacelle, which avoids leaving this cylinder protruding into the annular vein.
Avantageusement, le vérin comporte en dessous une plaque de fermeture fixée à plat suivant la longueur, qui s'ajuste sur la face du volet quand il est replié pour fermer sensiblement le creux longitudinal de ce volet. Cette plaque améliore la surface aérodynamique de la veine annulaire.  Advantageously, the cylinder comprises below a closure plate fixed flat along the length, which adjusts to the face of the flap when it is folded to substantially close the longitudinal recess of the flap. This plate improves the aerodynamic surface of the annular vein.
Avantageusement, la plaque de fermeture comprend son extrémité arrière fixée à la partie arrière de la tige du vérin, et son extrémité avant fixée de manière coulissante sur le corps de ce vérin par un guidage linéaire. En inversion de poussée, cette plaque se trouve écartée du flux d'air pour ne pas le freiner. Advantageously, the closure plate comprises its rear end fixed to the rear part of the cylinder rod, and its front end slidingly attached to the body of this cylinder by a linear guide. In thrust reversal, this plate is spaced from the air flow to not slow it down.
Avantageusement, la partie arrière du volet vient en appui radialement vers l'extérieur quand l'inverseur est fermé, sur une butée de fin de course réglable qu i permet d'ajuster l'alignement de ce volet avec les surfaces voisines.  Advantageously, the rear portion of the flap bears radially outwardly when the inverter is closed, on an adjustable end stop that i can adjust the alignment of this flap with the neighboring surfaces.
Avantageusement, l'extrémité arrière des grilles est fixée à un béquet se trouvant à l'avant des capots mobiles, un joint d'étanchéité venant en appui sur le cadre avant, qui se trouve radialement à l'intérieur des grilles.  Advantageously, the rear end of the grilles is fixed to a spoiler located in front of the movable covers, a seal bearing on the front frame, which is located radially inside the grids.
Avantageusement, l'inverseur de poussée comporte à l'avant des capots mobiles, un joint d'étanchéité venant en appui sur le cadre avant. Ce joint donne un équilibre de pression facilitant l'ouverture ou la fermeture des capots.  Advantageously, the thrust reverser comprises at the front of the movable covers, a seal bearing on the front frame. This seal gives a pressure balance facilitating the opening or closing of the covers.
Avantageusement, les extrémités avant de grilles sont reliées entre elles par une structure circulaire se trouvant en amont du cadre avant, cette structure apportant une forte rigidité avec une masse réduite.  Advantageously, the front ends of grids are interconnected by a circular structure located upstream of the front frame, this structure providing a high rigidity with a reduced mass.
L'invention a aussi pour objet une nacelle de turboréacteur comportant un inverseur de poussée comprenant l'une quelconque des caractéristiques précédentes.  The invention also relates to a turbojet engine nacelle comprising a thrust reverser comprising any one of the preceding features.
L'invention sera mieux comprise et d'autres caractéristiques et avantages apparaîtront plus clairement à la lecture de la description ci-après, donnée à titre d'exemple en référence aux dessins annexés dans lesquels :  The invention will be better understood and other features and advantages will appear more clearly on reading the description below, given by way of example with reference to the accompanying drawings in which:
- la figure 1 est une vue partielle en coupe axiale passant par le centre d'un volet, d'un inverseur selon l'invention qui est fermé ;  - Figure 1 is a partial view in axial section passing through the center of a flap, an inverter according to the invention which is closed;
- la figure 2 est une vue en coupe transversale de ce volet ;  FIG. 2 is a cross-sectional view of this shutter;
- la figure 3 est une vue en coupe longitudinale de détail présentant le système d'étanchéité des capots mobiles ;  - Figure 3 is a longitudinal sectional detail view showing the sealing system of movable covers;
- la figure 4 présente l'inverseur en début d'ouverture, comprenant le vérin en cours d'extension ;  - Figure 4 shows the inverter at the beginning of opening, including the jack being extended;
- la figure 5 présente l'inverseur plus ouvert, comprenant le vérin en extension complète ;  - Figure 5 shows the inverter more open, including the cylinder in full extension;
- la figure 6 présente l'inverseur encore plus ouvert, comprenant le volet en train de se déployer ; - la figure 7 présente l'inverseur complètement ouvert, comprenant le volet entièrement déployé ; et - Figure 6 shows the inverter even more open, including the flap unfolding; - Figure 7 shows the fully open inverter, including the fully deployed flap; and
- les figures 8 et 9 présentent l'inverseur de poussée respectivement fermé et complètement ouvert, comprenant un carénage de vérin coulisant.  - Figures 8 and 9 show the thrust reverser respectively closed and fully open, comprising a sliding jack fairing.
Les figures 1 et 2 présenten t l a pa rti e a rrière d ' u ne nacel l e de turboréacteur, comprenant un cadre avant 2 fixé sur la structure se trouvant en amont de cette partie, et des capots mobiles 10 ajustés en arrière de ce cadre.  Figures 1 and 2 present pa rti e behind a nacel l e turbojet, comprising a front frame 2 fixed on the structure located upstream of this part, and movable covers 10 fitted behind this frame.
La partie arrière de la nacelle est recouverte par deux capots mobiles 10, formant chacun dans un plan transversal un demi-cercle. Chaque capot 10 est guidé axialement par des moyens de guidage longitudinaux, qui permettent un coulissement vers l'arrière sous l'effet d'actionneurs non représentés, prenant appui sur la structure fixe en amont des capots mobiles 1 0. Les capots 1 0 comportent un système de verrou illage en position fermée, qu i n 'est pas représenté.  The rear part of the nacelle is covered by two movable covers 10, each forming a semicircle in a transverse plane. Each cover 10 is guided axially by longitudinal guiding means, which allow a sliding backwards under the effect of actuators not shown, bearing on the fixed structure upstream of the movable covers 1 0. The covers 1 0 comprise a locking system in the closed position, which is not shown.
En variante, la nacel le peut com porter u n u n iq ue capot mobile 1 0 annulaire, qui de la même manière coulisse vers l'arrière pour ouvrir l'inverseur de poussée.  Alternatively, the nacel may have an annular movable cowl 10 which likewise slides backward to open the thrust reverser.
La veine annulaire secondaire 4 comporte un contour radialement externe comprenant des volets 8 ajustés à l'intérieur des capots mobiles 10 de manière à donner une continu ité aérodynam ique, et un contour radialement interne formé par la structure interne fixe 6.  The secondary annular vein 4 comprises a radially outer contour comprising flaps 8 fitted inside the movable hoods 10 so as to give an aerodynamic continuity, and a radially internal contour formed by the fixed internal structure 6.
Des grilles 12 disposées à plat autour de la veine annulaire 4, forment une couronne entièrement intégrée dans le cadre avant 2 quand l'inverseur est fermé.  Grids 12 arranged flat around the annular vein 4, form a fully integrated crown in the front frame 2 when the inverter is closed.
L'extrémité arrière des grilles 1 2 est fixée à un béquet 14 se trouvant à l 'avant des capots mobiles 1 0, qu i forme un retou r à partir de la su rface extérieure de ces capots, vers le centre de la nacelle. Les grilles peuvent coulisser librement à travers des ouvertures du cadre avant 2, afin de suivre le mouvement des capots 10 quand l'inverseur s'ouvre.  The rear end of the grids 1 2 is fixed to a spoiler 14 located in front of the movable covers 1 0, that i form a retou r from the outer surface of these covers, towards the center of the nacelle. The grids can slide freely through openings in the front frame 2, in order to follow the movement of the covers 10 when the inverter opens.
Le système d'entraînement des capots 1 0 comprenant les actionneurs peut être fixé sur la partie amont de la structure des grilles 12, pour déplacer l 'ensem ble comprenant les g ril les et les capots. Cette d isposition libère entièrement le passage de l'air dans la structure des grilles 12 en inversion de poussée, mais empiète sur le capot avant du moteur. The cap drive system 10 including the actuators may be attached to the upstream portion of the grid structure 12, to move the assembly including the gills and covers. This disposition frees entirely the passage of air in the structure of the grids 12 in reverse thrust, but impinges on the front cover of the engine.
En variante le système d'entraînement des capots 10 peut être fixé sur les grilles 12, soit dans le plan des grilles, soit radialement au dessus ou en dessous de leur structure. Le système d'entraînement des capots 10 peut aussi être fixé sur la partie amont de la structure de ces capots, en s'intégrant entre d eux él ém ents d es grilles 12. Da ns ces d eux va ria ntes le système d'entraînement se trouve dans le passage de l'air en inversion de poussée.  As a variant, the drive system of the hoods 10 can be fixed to the grids 12 either in the plane of the grids or radially above or below their structure. The drive system of the hoods 10 can also be fixed on the upstream part of the structure of these hoods, by integrating between them em ents of the grids 12. In these of them va ria nts the system of drive is in the air passage in reverse thrust.
Chaque volet 8 comporte un bras s'étendant vers l'avant à l'intérieur du capot mobile 1 0, se terminant à son extrémité avant par une articulation 1 6 reliée à ce capot mobile, qui est disposée juste en arrière du becquet de retour 14.  Each flap 8 comprises an arm extending forwardly inside the movable hood 1 0, ending at its front end by a hinge 1 6 connected to the movable hood, which is arranged just behind the spoiler return 14.
La partie arrière du volet 8 est en appui radialement vers l'extérieur sur une butée de fin de course 1 8, qui positionne ce volet de manière à ajuster sa face dans la continuité des surfaces intérieures du cadre avant 2 et du volet mobile 10. Les butées de fin de course 18 peuvent être réglables, afin d'affiner la position des volets 8 dans le flux aérodynamique.  The rear portion of the flap 8 bears radially outwardly on a limit stop 18, which positions the flap so as to adjust its face in continuity with the inner surfaces of the front frame 2 and the movable flap 10. The end stops 18 may be adjustable, in order to refine the position of the flaps 8 in the aerodynamic flow.
Chaque volet 8 comporte un vérin télescopique 20 d isposé dans l'axe longitudinal de ce volet, qui est entièrement intégré dans un creux longitudinal de la face du volet tournée vers l'intérieur de la nacelle, de manière à s'ajuster sur la surface extérieure de la veine annulaire 4 sans dépasser dans cette veine. L'extrémité avant du vérin 20 est fixée par un pivot au cadre avant 2, l'extrémité arrière est fixée par un pivot aussi, à une partie arrière du volet 8.  Each flap 8 comprises a telescopic jack 20 disposed in the longitudinal axis of this flap, which is fully integrated in a longitudinal recess of the face of the shutter facing the inside of the nacelle, so as to adjust to the surface outside of the annular vein 4 without exceeding in this vein. The front end of the jack 20 is fixed by a pivot to the front frame 2, the rear end is fixed by a pivot also to a rear part of the flap 8.
Chaque vérin télescopique 20 comporte un corps contenant du côté avant un ressort hélicoïdal de compression, qui exerce une pression permanente sur l'extrémité avant de sa tige 22, afin de la pousser vers l'arrière pour tendre à mettre ce vérin en extension.  Each telescopic jack 20 comprises a body containing on the front side a helical compression spring, which exerts a permanent pressure on the front end of its rod 22, to push it backwards to tend to put this cylinder in extension.
U ne plaque de fermeture 32 fixée à plat sous le vérin 20 su ivant sa longueur, forme un carénage coulissant ajusté sur la face du volet 8 quand il est repl ié, fermant le creux longitudinal de ce volet afin d'améliorer le profil aérodynamique extérieur de la veine annulaire 4. Cette plaque de fermeture 32 montée en option, est présentée sur les figures 8 et 9. On notera que les volets 8 sont maintenus en permanence sous tension par la pression des ressorts des vérins 20 qui tendent à les pousser sur leurs butées de fin de course 1 8, avec un certain couple dépendant de la distance radiale entre l'axe de ce vérin et l'articulation 1 6 des volets. Cette pression évite des flottements des volets 8 qui freineraient le débit d'air secondaire. A closure plate 32 fixed flat under the cylinder 20 along its length, forms a sliding fairing fitted to the face of the flap 8 when it is folded, closing the longitudinal recess of this flap to improve the external airfoil. of the annular vein 4. This optional closure plate 32 is shown in FIGS. 8 and 9. It will be noted that the flaps 8 are kept permanently tensioned by the pressure of the springs of the jacks 20 which tend to push them on their limit stops 1 8, with a certain torque depending on the radial distance between the axis of this end. cylinder and the hinge 1 6 flaps. This pressure avoids flutter flaps 8 which would slow the flow of secondary air.
La figure 3 présente un capot 1 0 dans sa position avant, l'inverseur de poussée étant complètement fermé.  Figure 3 shows a hood 1 0 in its forward position, the thrust reverser being completely closed.
L'extrémité radialement intérieure du béquet de retour 14 est en appu i vers l'avant sur un joint d'étanchéité 30, qui est lui-même en appui sur le cadre avant 2, radialement à l'intérieur des grilles 1 2. La disposition des grilles 8 intég rées en amont de la structu re des capots mobiles 1 0, permet cette disposition de l 'étanchéité qu i réal ise u n éq u il ibre de pression facil itant l'ouverture ou la fermeture de ces capots.  The radially inner end of the return spoiler 14 is pressed forward on a seal 30, which is itself resting on the front frame 2, radially inside the grids 1 2. Arrangement of the grids 8 integrated upstream of the structure of the movable hoods 1 0, allows this arrangement of the seal that i realizes a pressure eeg uil facilitating the opening or closing of these covers.
La figure 4 présente l'inverseur en début d'ouverture, les capots mobiles 1 0 ayant commencé à reculer sous l'effet de leurs actionneurs. Les grilles 12 commencent à sortir du cadre avant 2.  FIG. 4 shows the inverter at the beginning of opening, the movable covers 10 having begun to move back under the effect of their actuators. The grids 12 begin to leave the front frame 2.
Les vérins 20 sont en cours d 'extension . Leu rs tiges 22 n 'étant pas complètement sorties, ces vérins 20 peuvent continuer à se déployer sans exercer de force de retenue sur la partie arrière des volets 8 qui ne basculent pas, et restent plaqués à l'intérieur des capots mobiles 10.  The cylinders 20 are being extended. Since the rods 22 are not fully extended, these jacks 20 can continue to deploy without exerting a retaining force on the rear part of the flaps 8 which do not tilt, and remain plated inside the movable covers 10.
La figure 5 présente l'inverseur plus ouvert avec les capots mobiles 10 qui continuent à reculer. Les vérins 20 arrivent à leur extension complète avec les tiges 22 entièrement sorties, mais les volets 8 ne basculent toujours pas.  Figure 5 shows the inverter more open with the moving hoods 10 which continue to move back. The cylinders 20 arrive at full extension with the rods 22 fully out, but the flaps 8 still do not rock.
La figure 6 présente l'inverseur plus ouvert encore, la tige 22 qui ne peut plus reculer, a commencé à basculer le volet 8 en tirant sa partie arrière vers le bas.  Figure 6 shows the inverter more open still, the rod 22 which can not move back, began to tilt the flap 8 by pulling its rear part down.
La figure 7 présente l'inverseur complètement ouvert, les capots mobiles 10 sont dans leurs positions arrière maximum, les volets 8 sont complètement abaissés en arrivant près de la structure interne fixe 6.  FIG. 7 shows the fully open inverter, the movable covers 10 are in their maximum rear positions, the shutters 8 are completely lowered when arriving near the fixed internal structure 6.
Pendant ces différentes étapes présentées par les figures 5, 6 et 7, les grilles 12 sortent de plus en plus du cadre avant 2, pour finir complètement sorties de manière à dégager leurs surfaces complètes qu i permettent de dévier le flux secondaire. During these different steps presented in FIGS. 5, 6 and 7, the grids 12 come out more and more of the front frame 2, to finish completely. outlets so as to clear their entire surfaces that allow to deflect the secondary flow.
Avantageusement, les extrémités avant de l'ensemble des grilles 12 sont reliées ensemble par une structure circulaire continue qui se trouve en amont du cadre avant 2, ce qui permet de manière simple avec une masse réduite d'obtenir un ensemble de grilles particulièrement rigide. La longueur des grilles 1 2 est adaptée en conséquence, pour que leurs extrémités avant restent en amont de ce cadre 2 quand l'inverseur est complètement ouvert.  Advantageously, the front ends of all the grids 12 are connected together by a continuous circular structure which is upstream of the front frame 2, which allows a simple way with a reduced mass to obtain a particularly rigid grid assembly. The length of the grids 1 2 is adapted accordingly, so that their front ends remain upstream of the frame 2 when the inverter is fully open.
Pour la fermeture de l'inverseur de poussée, la compression des ressorts des vérins 20 ainsi que le flux d'air dans la veine secondaire 4, repoussent les volets 8 en permanence vers l'arrière. On a les mouvements inverses avec d'abord un repl i des volets 8 à l'intérieur des capots mobiles 1 0, avant la compression des ressorts.  For the closing of the thrust reverser, the compression of the springs of the cylinders 20 as well as the air flow in the secondary vein 4, push the flaps 8 permanently towards the rear. We have the reverse movements with first a ref i flaps 8 inside the movable covers 1 0, before the compression of the springs.
On obtient ainsi un système simple comprenant un coût faible, disposant de capots mobiles 1 0 qui peuvent comporter une épaisseur réduite car d'une part l es g ril les 1 2 , et d 'autre part les volets 8 avec leu rs systèmes de manœuvre comprenant les vérins 20, sont axialement les uns après les autres sans se superposer. De plus il n'est pas nécessaire de prévoir un espace dans ces capots mobiles 10 pour loger les grilles 12.  Thus, a simple system with a low cost is obtained, with movable covers 10 which may have a reduced thickness because on the one hand the g ril 1 2, and on the other hand the flaps 8 with their maneuvering systems comprising the cylinders 20, are axially one after the other without being superimposed. In addition it is not necessary to provide space in these movable covers 10 to accommodate the grids 12.
Avec l'intégration des vérins 20 dans les volets 8, qui ne dépassent pas dans la veine annulaire 4, les profils aérodynamiques intérieur et extérieur de cette veine peuvent être optimisés, la consommation de carburant est améliorée.  With the integration of the cylinders 20 in the flaps 8, which do not exceed in the annular vein 4, the inner and outer aerodynamic profiles of this vein can be optimized, the fuel consumption is improved.
On notera q ue l 'espace d ispon ibl e dans l es capots mobil es 1 0 ne comportant pas les grilles 1 2, permet d'optimiser la position de l'articulation avant 1 6 des volets 8, qu i peut être proche de la surface extérieure de ces capots afin d'obtenir avec le choix des points d'ancrage des vérins 20, une bonne cinématique pour le déploiement des volets. En particul ier un écart radial assez important entre les vérins 20 et les points d'articulation avant 16 des volets 8, permet à ces vérins de maintenir un couple élevé sur les volets repl iés. On assure aussi une bonne répartition des efforts et une meilleure fiabilité de manœuvre. Par ailleurs il est plus facile pour les capots mobiles 10 ne comprenant pas de volume intérieur laissé libre pour les grilles, de réaliser une structure rigide. It will be noted that the gap in the movable hoods 1 0 not including the grids 1 2, makes it possible to optimize the position of the hinge before the flaps 8, which can be close to the outer surface of these covers to obtain with the choice of anchor points of the cylinders 20, a good kinematics for the deployment of the flaps. In particular, a rather large radial gap between the jacks 20 and the hinge points before 16 of the flaps 8 makes it possible for these jacks to maintain high torque on the folded flaps. It also provides a good distribution of effort and better maneuverability. Furthermore it is easier for the movable hoods 10 not including an interior volume left free for the grids, to achieve a rigid structure.
Les figures 8 et 9 présentent la plaque de fermeture 32 comprenant son extrémité arrière fixée à la partie arrière de la tige du vérin 22, et son extrémité avant fixée de man ière coul issante sur le corps de ce vérin par un gu idage linéaire, comme un rail de guidage.  FIGS. 8 and 9 show the closure plate 32 comprising its rear end fastened to the rear part of the rod of the jack 22, and its front end slidingly attached to the body of this jack by linear guiding, such as a guide rail.
En jet direct pour la propulsion de l'aéronef, présenté par la figure 8, le creux longitudinal du volet 8 est fermé par la plaque 32 formant un carénage pour améliorer les performances aérodynamiques.  In direct jet for the propulsion of the aircraft, shown in FIG. 8, the longitudinal hollow of the flap 8 is closed by the plate 32 forming a fairing to improve the aerodynamic performance.
En jet inversé pour le freinage, présenté par la figure 9, le corps du vérin 20 est globalement dégagé de la plaque de fermeture 32 qui coul isse vers l 'avant avec la tige 22 , permetta nt u n m eil leu r contou rnement d u flux d'inversion, et donc une amélioration des performances d'inversion.  In an inverted jet for braking, shown in FIG. 9, the body of the jack 20 is generally disengaged from the closure plate 32 which is cast forwardly with the rod 22, allowing a smooth flow of the flow of the fluid. inversion, and thus an improvement in inversion performance.

Claims

REVENDICATIONS
1 - Inverseur de poussée d'une nacelle de turboréacteur, comprenant des capots mobiles (10) qui reculent par rapport à un cadre avant (2) en entraînant par des vérins (20) le basculement de volets (8) se trouvant initialement repliés à l'intérieur de ces capots, pour fermer sensiblement la veine annulaire d'air froid (4), et en ouvrant des grilles (1 2) disposées autour de cette veine qu i reçoivent le flux d'air froid pour le renvoyer vers l'avant, caractérisé en ce que les grilles (12) sont fixées aux capots mobiles (10) et coulissent avec eux. 1 - Thrust reverser of a turbojet nacelle, comprising movable covers (10) which move back relative to a front frame (2) by causing, through cylinders (20), the tilting of flaps (8) which are initially folded to inside these covers, to substantially close the annular vein of cold air (4), and by opening grilles (1 2) arranged around this vein which receive the flow of cold air to return it towards the front, characterized in that the grilles (12) are fixed to the movable covers (10) and slide with them.
2 - Inverseur de poussée selon la revendication 1 , caractérisé en ce que les volets (8) comportent une extrémité avant reliée par une articulation (1 6) à un capot mobile (10), et un vérin (20) comprenant une extrémité avant fixée au cadre (2), et l'autre extrémité fixée à l'arrière de ce volet. 2 - Thrust reverser according to claim 1, characterized in that the flaps (8) comprise a front end connected by a hinge (1 6) to a movable cover (10), and a cylinder (20) comprising a fixed front end to the frame (2), and the other end fixed to the rear of this shutter.
3 - Inverseur de poussée selon la revendication 2, caractérisé en ce que le vérin (20) se trouve en limite de la surface extérieure de la veine annulaire 3 - Thrust reverser according to claim 2, characterized in that the cylinder (20) is located at the limit of the external surface of the annular vein
(4), le volet (8) étant relié au capot mobile (10) par une articulation (16) qui est éloignée de ce vérin radialement vers l'extérieur. (4), the flap (8) being connected to the movable cover (10) by a joint (16) which is moved away from this cylinder radially outwards.
4 - Inverseur de poussée selon la revendication 3, caractérisé en ce que le vérin (20) disposé dans l'axe longitudinal du volet (8), est intégré dans un creux longitudinal de la face de ce volet tournée radialement vers l'intérieur de la nacelle. 4 - Thrust reverser according to claim 3, characterized in that the cylinder (20) disposed in the longitudinal axis of the flap (8), is integrated in a longitudinal hollow of the face of this flap facing radially towards the inside of Platform.
5 - Inverseur de poussée selon la revendication 4, caractérisé en ce que le vérin (20) comporte en dessous une plaque de fermeture (32) fixée à plat suivant la longueur, qui s'ajuste sur la face du volet (8) quand il est replié pour fermer sensiblement le creux longitudinal de ce volet. 5 - Thrust reverser according to claim 4, characterized in that the cylinder (20) comprises below a closing plate (32) fixed flat along the length, which fits on the face of the flap (8) when it is folded to substantially close the longitudinal hollow of this flap.
6 - Inverseur de poussée selon la revendication 5, caractérisé en ce que la plaque de fermeture (32) comprend son extrémité arrière fixée à la partie arrière de la tige (22) du vérin (20), et son extrémité avant fixée de manière coulissante sur le corps de ce vérin par un guidage linéaire. 6 - Thrust reverser according to claim 5, characterized in that the closing plate (32) comprises its rear end fixed to the rear part of the rod (22) of the cylinder (20), and its front end fixed in a sliding manner on the body of this cylinder by a linear guide.
7 - Inverseur de poussée selon l'une quelconque des revendications précédentes, caractérisé en ce que la partie arrière du volet (8) vient en appui radialement vers l'extérieur quand l'inverseur est fermé, sur une butée de fin de course réglable (18). 7 - Thrust reverser according to any one of the preceding claims, characterized in that the rear part of the flap (8) comes to rest radially outwards when the reverser is closed, on an adjustable end stop (18).
8 - Inverseur de poussée selon l'une quelconque des revendications précédentes, caractérisé en ce que l'extrémité arrière des grilles (12) est fixée à un béquet (14) se trouvant à l'avant des capots mobiles (10), qui forme un retour vers le centre de la nacelle à partir de la surface extérieure de ces capots. 8 - Thrust reverser according to any one of the preceding claims, characterized in that the rear end of the grids (12) is fixed to a spoiler (14) located at the front of the movable covers (10), which forms a return towards the center of the nacelle from the exterior surface of these covers.
9 - Inverseur de poussée selon l'une quelconque des revendications précédentes, caractérisé en ce qu'il comporte à l'avant des capots mobiles (10), un joint d'étanchéité (30) venant en appui sur le cadre avant (2), qui se trouve radialement à l'intérieur des grilles (8). 9 - Thrust reverser according to any one of the preceding claims, characterized in that it comprises at the front movable covers (10), a seal (30) bearing on the front frame (2) , which is located radially inside the grids (8).
10 - Inverseur de poussée selon l'une quelconque des revendications précédentes, caractérisé en ce que les extrémités avant de grilles (12) sont reliées entre elles par une structure circulaire qui se trouve en amont du cadre avant (2). 10 - Thrust reverser according to any one of the preceding claims, characterized in that the front ends of the grids (12) are interconnected by a circular structure which is located upstream of the front frame (2).
1 1 - Nacelle de turboréacteur comportant un inverseur de poussée, caractérisée en ce que cet inverseur est réalisé selon l'une quelconque des revendications précédentes. 1 1 - Turbojet nacelle comprising a thrust reverser, characterized in that this reverser is produced according to any one of the preceding claims.
PCT/FR2014/051349 2013-06-07 2014-06-05 Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls WO2014195646A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14733272.0A EP3004614A1 (en) 2013-06-07 2014-06-05 Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls
CA2908678A CA2908678A1 (en) 2013-06-07 2014-06-05 Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1355279A FR3006715B1 (en) 2013-06-07 2013-06-07 THRUST INVERTER OF A TURBOJET NACELLE COMPRISING GRIDS FIXED TO MOBILE HOODS
FR1355279 2013-06-07

Publications (1)

Publication Number Publication Date
WO2014195646A1 true WO2014195646A1 (en) 2014-12-11

Family

ID=49003888

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2014/051349 WO2014195646A1 (en) 2013-06-07 2014-06-05 Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls

Country Status (4)

Country Link
EP (1) EP3004614A1 (en)
CA (1) CA2908678A1 (en)
FR (1) FR3006715B1 (en)
WO (1) WO2014195646A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3141731A1 (en) * 2015-09-10 2017-03-15 Honeywell International Inc. System and method for reducing idle thrust in a translating cowl thrust reverser

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3347467A (en) * 1963-08-07 1967-10-17 Gen Electric Combination jet exhaust nozzle and thrust reverser
US3500645A (en) * 1968-04-10 1970-03-17 Rohr Corp Thrust reverser
GB2156004A (en) * 1984-03-15 1985-10-02 Gen Electric Thrust modulation device for a gas turbine engine
EP0321993A2 (en) 1987-12-21 1989-06-28 The Boeing Company Thrust reverser for high bypass jet engines
US5228641A (en) 1991-08-15 1993-07-20 Rohr, Inc. Cascade type aircraft engine thrust reverser with hidden link actuator
US20090151320A1 (en) * 2007-12-12 2009-06-18 Spirit Aerosystems, Inc. Partial cascade thrust reverser

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3347467A (en) * 1963-08-07 1967-10-17 Gen Electric Combination jet exhaust nozzle and thrust reverser
US3500645A (en) * 1968-04-10 1970-03-17 Rohr Corp Thrust reverser
GB2156004A (en) * 1984-03-15 1985-10-02 Gen Electric Thrust modulation device for a gas turbine engine
EP0321993A2 (en) 1987-12-21 1989-06-28 The Boeing Company Thrust reverser for high bypass jet engines
US5228641A (en) 1991-08-15 1993-07-20 Rohr, Inc. Cascade type aircraft engine thrust reverser with hidden link actuator
US20090151320A1 (en) * 2007-12-12 2009-06-18 Spirit Aerosystems, Inc. Partial cascade thrust reverser

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3141731A1 (en) * 2015-09-10 2017-03-15 Honeywell International Inc. System and method for reducing idle thrust in a translating cowl thrust reverser
US10344709B2 (en) 2015-09-10 2019-07-09 Honeywell International Inc. System and method for reducing idle thrust in a translating cowl thrust reverser

Also Published As

Publication number Publication date
CA2908678A1 (en) 2014-12-11
EP3004614A1 (en) 2016-04-13
FR3006715B1 (en) 2015-06-05
FR3006715A1 (en) 2014-12-12

Similar Documents

Publication Publication Date Title
EP2776699B1 (en) Thrust reverser device
EP2651764B1 (en) Nacelle for a bypass turbojet engine
CA2719155A1 (en) Bypass turbojet engine nacelle
EP0806563B1 (en) Doors with deflector vanes for a thrust reverser of a turbofan engine
CA2776262A1 (en) Reverse thrust device
EP3164589B1 (en) Turbojet nacelle provided with a thrust reverser, including cut-outs to avoid the movable slat of an aircraft wing
EP3017171B1 (en) Turbofan engine nacelle thrust reverser comprising cascades partially integrated into the moving cowl
FR2966882A1 (en) THRUST INVERTER FOR AIRCRAFT TURBOJET ENGINE WITH REDUCED ACTUATOR NUMBERS
WO2018115731A1 (en) Aircraft jet engine nacelle, propulsion assembly and aircraft comprising such a nacelle
WO2015001276A1 (en) Turbofan nacelle having a variable nozzle
EP2591224A1 (en) Thrust reverser having an aerodynamic coupling for a front frame
EP2881569A1 (en) Thrust reverser for jet engine nacelle comprising two pivotable flaps which close the annular section
FR3006716A1 (en) THRUST INVERTER WITH THREADED JOINT LOCKING PAD THREE POINTS
EP3719293B1 (en) Turbojet engine comprising a nacelle provided with an inverser system and a mobile cascade grid
WO2015028735A1 (en) Thrust reverser of a turbojet nacelle, comprising grids and cylinders fixed upstream of mobile hoods
WO2014195646A1 (en) Turbojet engine nacelle thrust reverser comprising cascades of vanes fixed to the mobile cowls
WO2018020111A1 (en) System for actuating a panel of a turbojet engine pod
EP3645855B1 (en) Nacelle for a turbojet comprising a cascade-type thrust reverser
EP3717766B1 (en) Thrust reverser for an aircraft engine nacelle, comprising a panel for avoiding a movable slat of the wing, and nacelle associated therewith

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14733272

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2908678

Country of ref document: CA

REEP Request for entry into the european phase

Ref document number: 2014733272

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 2014733272

Country of ref document: EP

NENP Non-entry into the national phase

Ref country code: DE