WO2008132294A1 - Device for varying the cross section of a secondary nozzle associated with a gate reverser and jet smoothing device - Google Patents

Device for varying the cross section of a secondary nozzle associated with a gate reverser and jet smoothing device Download PDF

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Publication number
WO2008132294A1
WO2008132294A1 PCT/FR2008/000234 FR2008000234W WO2008132294A1 WO 2008132294 A1 WO2008132294 A1 WO 2008132294A1 FR 2008000234 W FR2008000234 W FR 2008000234W WO 2008132294 A1 WO2008132294 A1 WO 2008132294A1
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WO
WIPO (PCT)
Prior art keywords
panel
door
cavity
nozzle
fixed structure
Prior art date
Application number
PCT/FR2008/000234
Other languages
French (fr)
Inventor
Pierre Caruel
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 EP08775588A priority Critical patent/EP2137394A1/en
Priority to CA002681354A priority patent/CA2681354A1/en
Publication of WO2008132294A1 publication Critical patent/WO2008132294A1/en

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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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Secondary nozzle section variation device associated with a gate inverter with vein smoothing device.
  • the present invention relates to a thrust reverser door (s).
  • a prior art thrust reverser (s) comprising:
  • At least one door pivotally mounted on this fixed structure between a closed position where it defines a cavity and an open position
  • At least one cavity panel slidably mounted on said door between a closed position in which it closes said cavity and an open position
  • the opening of the door makes it possible to deflect the cold air flow produced by the blower of a turbojet, and thus to generate a counter-thrust capable of reducing the braking distance of an aircraft during its landing.
  • the cavity panel smooths the contour of the cold air stream when the inverter door is closed, and thus improves the aerodynamic quality of the flow.
  • a thrust reverser door comprising a nozzle panel slidably mounted on the fixed structure of the inverter, for varying the cold air flow section to optimize the operation of the engine during the different phases of flight.
  • a door inverter not only of a cavity panel, but also of a movable nozzle panel, would be very desirable in many cases.
  • a very complex, heavy and expensive mechanism is used which makes it possible to selectively actuate the door of the inverter, the cavity panel (or both simultaneously via a complex mechanical coupling), and the nozzle panel.
  • the present invention is intended in particular to provide a simple and lightweight actuation mechanism of the three aforementioned bodies. This object of the invention is achieved with a thrust reverser with door (s) comprising:
  • At least one door pivotally mounted on this fixed structure between a closed position where it defines a cavity and an open position
  • At least one cavity panel slidably mounted on said door between a closed position in which it closes said cavity and an open position
  • means for actuating said door and said cavity panel comprises a nozzle panel slidably mounted on said fixed structure between an upstream position and a downstream position, and means for coupling said nozzle panel to said cavity panel when said door is closed, and then coupling said nozzle panel to said door as said door moves from its closed position to its open position.
  • the nozzle panel can be slid between its upstream and downstream positions through the sliding cavity panel between its closed and open positions, and once the door passes through open position, it takes over to maintain the nozzle panel in its downstream position.
  • the invention makes it possible to use actuating means only for the door and the cavity panel, the actuation of the nozzle panel being effected indirectly by the cavity panel. In this way there is obtained a thrust reverser door (s), cavity panel and movable nozzle panel, lightweight and simple design.
  • said actuating means comprise a double jack cooperating with said fixed structure, said door and a connecting rod connected to said cavity panel; this embodiment makes it possible to use only one jack, and thus to save weight;
  • said actuating means comprise on the one hand a first jack interposed between said fixed structure and said door, and on the other hand a second jack interposed between said fixed structure and said panel. cavity; this embodiment allows a total independence of the movements of the cavity panel relative to those of the door;
  • the coupling means of said nozzle panel to said cavity panel comprise a hook integral with said nozzle panel and a counter-hook integral with said cavity panel; these means make it possible to achieve in a simple manner the coupling / decoupling of the nozzle panel with respect to the cavity panel;
  • the coupling means of said nozzle panel to said door comprise a hook integral with said nozzle panel and a slideway integral with said door; these means make it possible to simply produce the coupling / decoupling of the nozzle panel with respect to the door.
  • the present invention also relates to a nacelle for an aircraft engine, remarkable in that it comprises an inverter according to the foregoing.
  • FIG. 1 is a partial view in axial section of an inverter according to the invention, in a normal section direct jet configuration;
  • FIG. 2 is a view of this inverter in an increased section jet configuration;
  • FIG. 3 is a view of this inverter in configuration immediately prior to the opening of the door;
  • FIG. 4 is a view of this invertor in an inverted jet configuration
  • FIG. 5 is a view similar to FIG. 1 of another embodiment of the inverter according to the invention.
  • FIG. 6 is a view of this inverter in a reduced section jet configuration.
  • Figure 1 shows a vein 1 of cold air likely to flow from the left to the right of the figure, between an internal structure 3 on the one hand and on the other hand a external structure 5.
  • the cold air circulating in the vein 1 is set in motion by a blower not shown and located in the upstream zone 7, and this cold air leaves the vein 1 in a downstream zone 9 defining a nozzle section.
  • the internal structure 3 is intended to envelop a turbojet engine not shown, and the external structure 5 comprises thrust reverser means, that is to say means able to deflect the cold air normally flowing in vein 1 outward and to the left of Figure 1.
  • These thrust reversal means comprise a door 11 pivotally mounted on a fixed structure 13 about an axis A, the stroke of the downstream portion of this door being represented symbolically by the circle C.
  • this door 11 comprises in particular a spoiler 15.
  • This door also includes a slide 17 whose function will be explained later.
  • a double rod cylinder 19 is pivotally mounted on the structure 13, and its first rod 21 is pivotally mounted on the door 11.
  • a cavity panel 23 is slidably mounted on the door 11 between a position visible in FIG. 1 in which this panel is joined to a deflection edge 25 mounted fixed relative to the structure 13, and other positions which will be explained more far.
  • This cavity panel 23 is connected to the second rod 27 of the cylinder 19
  • a nozzle panel 31 is coupled to the cavity panel 23 via a hook 33 and a counter-hook 35 mounted respectively on these bodies.
  • the nozzle panel 31 is joined with the door 11, and the nozzle section 9 is called "normal".
  • the second rod 27 of the cylinder 19 has elongated, thereby causing, through the rod 27, the sliding downstream (that is to say to the right of the figure) of the cavity panel 23 and thus the nozzle panel 31, thus leading to a nozzle section 9 increased with respect to the normal section of Figure 1, while the door cavity is no longer completely closed.
  • Such an increase in the nozzle section is particularly suitable for certain phases of the flight, for which the non-obstruction of the door cavity is less penalizing.
  • the second rod 27 of the ram 19 has continued to lengthen with respect to the configuration of FIG. 2, thus leading to an extreme downstream displacement of the cavity panel 23 and the control panel. 31.
  • this extreme displacement makes it possible to place the end 37 of the hook 33 at the right of the slideway 17 integral with the door 11.
  • This additional displacement with respect to the position shown in FIG. made necessary to sufficiently lower the end of the cavity panel 23 so as to release as much as possible the passage of air through the doorway in reverse jet operation, for the configuration shown here, but is not always necessary .
  • FIGS. and 6 differs from the previous embodiment in that it provides two separate cylinders, 19a, 19b, for respectively actuate the door 11 and the cavity panel 23. In this case, these cylinders are of the single rod type 21a , 21b. Note that in the case of this variant, it is no longer necessary to provide a connecting rod 29 between the actuating cylinder of the door and the cavity panel.
  • This reduced section configuration is particularly suitable for the rise and fall phases of an aircraft equipped with such a reverse thrust system.
  • nozzle panel 31 being coupled to the cavity panel 23 via the hook 33, this cavity panel moves downstream of the air stream 1, thereby increasing the cross-section of the cavity.
  • nozzle outlet 9. The cavity panel no longer closes the cavity defined by the door 11, the flight phases for which this configuration is used allowing degraded aerodynamic performance.
  • this door and the cavity panel 23 obstruct the vein 1 and thus deflect the air outwards, this deflection being improved by the presence of the spoiler 15 and possibly by the grid 39.
  • the nozzle panel 31 is held in place by the slide 17 secured to the door 11.
  • the invention thus makes it possible to actuate three members, namely the door 11, the cavity panel 23 and the nozzle panel 31, with only two actuating means, namely the rods 21, 27 of the jack 19, or the rods 21a, 21b of the cylinders 19a and 19b.
  • the invention therefore provides simplified and lightened means for selectively implementing the thrust reverser means, closing the cavity defined by the door 11, and adjust the outlet section of the cold air jet of the turbojet engine.

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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)
  • Power-Operated Mechanisms For Wings (AREA)

Abstract

The invention relates to a thrust reverser with gate(s) that comprises: a fixed structure (13); at least one gate (11) pivotally mounted on said fixed structure (13) between a closed position, in which it defines a cavity, and an open position; at least one cavity panel (23) mounted on said gate (11) so as to be capable of sliding between a closed position, in which it blocks said cavity, and an open position; and means (19; 19a, 19b) for actuating said gate (11) and said cavity panel (23). The thrust reverser is characterised in that it comprises a nozzle panel (31) slidingly mounted on said fixed structure (13), and means (33, 35) for coupling said nozzle panel (31) to said cavity panel (23) when said gate (11) is closed, and for coupling said nozzle panel (31) to said gate (11) when said gate (11) moves from the closed position to the open position.

Description

Dispositif de variation de section de tuyère secondaire associé à un inverseur à portes à dispositif de lissage de veine. Secondary nozzle section variation device associated with a gate inverter with vein smoothing device.
La présente invention se rapporte à un inverseur de poussée à porte(s).The present invention relates to a thrust reverser door (s).
On connaît de la technique antérieure un inverseur de poussée à porte(s) comprenant :A prior art thrust reverser (s) comprising:
- une structure fixe,- a fixed structure,
- au moins une porte montée pivotante sur cette structure fixe entre une position fermée où elle définit une cavité et une position ouverte,at least one door pivotally mounted on this fixed structure between a closed position where it defines a cavity and an open position,
- au moins un panneau de cavité monté coulissant sur ladite porte entre une position fermée dans laquelle il obture ladite cavité et une position ouverte, etat least one cavity panel slidably mounted on said door between a closed position in which it closes said cavity and an open position, and
- des moyens d'actionnement de ladite porte et dudit panneau de cavité.means for actuating said door and said cavity panel.
L'ouverture de la porte permet de dévier le flux d'air froid produit par la soufflante d'un turboréacteur, et ainsi d'engendrer une contre-poussée apte à réduire la distance de freinage d'un avion lors de son atterrissage.The opening of the door makes it possible to deflect the cold air flow produced by the blower of a turbojet, and thus to generate a counter-thrust capable of reducing the braking distance of an aircraft during its landing.
Le panneau de cavité permet de lisser le contour de la veine d'air froid lorsque la porte de l'inverseur est fermée, et ainsi d'améliorer la qualité aérodynamique de l'écoulement.The cavity panel smooths the contour of the cold air stream when the inverter door is closed, and thus improves the aerodynamic quality of the flow.
Par ailleurs, on connaît de la technique antérieure un inverseur de poussée à porte(s) comprenant un panneau de tuyère monté coulissant sur la structure fixe de l'inverseur, permettant de faire varier la section de flux d'air froid afin d'optimiser le fonctionnement du moteur pendant les différentes phases de vol.Furthermore, it is known from the prior art a thrust reverser door (s) comprising a nozzle panel slidably mounted on the fixed structure of the inverter, for varying the cold air flow section to optimize the operation of the engine during the different phases of flight.
La mise en œuvre dans un inverseur à porte(s) non seulement d'un panneau de cavité, mais également d'un panneau de tuyère mobile, serait fort souhaitable dans bien des cas. Toutefois, une telle combinaison n'était envisageable jusqu'à ce jour qu'à la condition de mettre en oeuvre un mécanisme très complexe, lourd et coûteux, permettant d'actionner sélectivement la porte de l'inverseur, le panneau de cavité (ou les deux simultanément par l'intermédiaire d'un couplage mécanique complexe), et le panneau de tuyère. La présente invention a notamment pour but de fournir un mécanisme simple et allégé d'actionnement des trois organes susmentionnés. On atteint ce but de l'invention avec un inverseur de poussée à porte(s) comprenant :The implementation in a door inverter (s) not only of a cavity panel, but also of a movable nozzle panel, would be very desirable in many cases. However, such a combination could be envisaged until now only if a very complex, heavy and expensive mechanism is used which makes it possible to selectively actuate the door of the inverter, the cavity panel (or both simultaneously via a complex mechanical coupling), and the nozzle panel. The present invention is intended in particular to provide a simple and lightweight actuation mechanism of the three aforementioned bodies. This object of the invention is achieved with a thrust reverser with door (s) comprising:
- une structure fixe,- a fixed structure,
- au moins une porte montée pivotante sur cette structure fixe entre une position fermée où elle définit une cavité et une position ouverte,at least one door pivotally mounted on this fixed structure between a closed position where it defines a cavity and an open position,
- au moins un panneau de cavité monté coulissant sur ladite porte entre une position fermée dans laquelle il obture ladite cavité et une position ouverte,at least one cavity panel slidably mounted on said door between a closed position in which it closes said cavity and an open position,
- des moyens d'actionnement de ladite porte et dudit panneau de cavité, cet inverseur de poussée étant remarquable en ce qu'il comprend un panneau de tuyère monté coulissant sur ladite structure fixe entre une position amont et une position aval, et des moyens pour coupler ledit panneau de tuyère audit panneau de cavité lorsque ladite porte est fermée, puis pour coupler ledit panneau de tuyère à ladite porte lorsque ladite porte passe de sa position fermée à sa position ouverte.means for actuating said door and said cavity panel, this thrust reverser being remarkable in that it comprises a nozzle panel slidably mounted on said fixed structure between an upstream position and a downstream position, and means for coupling said nozzle panel to said cavity panel when said door is closed, and then coupling said nozzle panel to said door as said door moves from its closed position to its open position.
Grâce à ces caractéristiques, tant que la porte est fermée, on peut faire coulisser le panneau de tuyère entre ses positions amont et aval par l'intermédiaire du panneau de cavité coulissant entre ses positions fermée et ouverte, et une fois que la porte passe en position ouverte, elle prend le relais pour maintenir le panneau de tuyère dans sa position aval.With these features, as long as the door is closed, the nozzle panel can be slid between its upstream and downstream positions through the sliding cavity panel between its closed and open positions, and once the door passes through open position, it takes over to maintain the nozzle panel in its downstream position.
On comprend donc que l'invention permet de n'utiliser des moyens d'actionnement que pour la porte et le panneau de cavité, l'actionnement du panneau de tuyère s'effectuant de manière indirecte par le panneau de cavité. On obtient de la sorte un inverseur de poussée à porte(s), à panneau de cavité et à panneau de tuyère mobile, de conception simple et allégée.It will thus be understood that the invention makes it possible to use actuating means only for the door and the cavity panel, the actuation of the nozzle panel being effected indirectly by the cavity panel. In this way there is obtained a thrust reverser door (s), cavity panel and movable nozzle panel, lightweight and simple design.
Suivant d'autres caractéristiques optionnelles de cet inverseur :According to other optional features of this inverter:
- lesdits moyens d'actionnement comprennent un vérin double coopérant avec ladite structure fixe, ladite porte et une bielle reliée audit panneau de cavité ; ce mode de réalisation permet de n'utiliser qu'un seul vérin, et ainsi de faire des économies de poids ;said actuating means comprise a double jack cooperating with said fixed structure, said door and a connecting rod connected to said cavity panel; this embodiment makes it possible to use only one jack, and thus to save weight;
- lesdits moyens d'actionnement comprennent d'une part un premier vérin interposé entre ladite structure fixe et ladite porte, et d'autre part un deuxième vérin interposé entre ladite structure fixe et ledit panneau de cavité ; ce mode de réalisation permet une totale indépendance des mouvements du panneau de cavité par rapport à ceux de la porte ;said actuating means comprise on the one hand a first jack interposed between said fixed structure and said door, and on the other hand a second jack interposed between said fixed structure and said panel. cavity; this embodiment allows a total independence of the movements of the cavity panel relative to those of the door;
- les moyens de couplage dudit panneau de tuyère audit panneau de cavité comprennent un crochet solidaire dudit panneau de tuyère et un contre-crochet solidaire dudit panneau de cavité ; ces moyens permettent de réaliser de manière simple le couplage/découplage du panneau de tuyère par rapport au panneau de cavité ;the coupling means of said nozzle panel to said cavity panel comprise a hook integral with said nozzle panel and a counter-hook integral with said cavity panel; these means make it possible to achieve in a simple manner the coupling / decoupling of the nozzle panel with respect to the cavity panel;
- les moyens de couplage dudit panneau de tuyère à ladite porte comprennent un crochet solidaire dudit panneau de tuyère et une glissière solidaire de ladite porte ; ces moyens permettent de réaliser de manière simple le couplage/découplage du panneau de tuyère par rapport à la porte.the coupling means of said nozzle panel to said door comprise a hook integral with said nozzle panel and a slideway integral with said door; these means make it possible to simply produce the coupling / decoupling of the nozzle panel with respect to the door.
La présente invention se rapporte également à une nacelle pour moteur d'avion, remarquable en ce qu'elle comporte un inverseur conforme à ce qui précède. D'autres caractéristiques et avantages de la présente invention apparaîtront à la lumière de la description qui va suivre, et à l'examen des figures annexées, dans lesquelles :The present invention also relates to a nacelle for an aircraft engine, remarkable in that it comprises an inverter according to the foregoing. Other features and advantages of the present invention will emerge in the light of the description which follows, and on examining the appended figures, in which:
- la figure 1 est une vue partielle en coupe axiale d'un inverseur selon l'invention, en configuration de jet direct de section normale, - la figure 2 est une vue de cet inverseur en configuration de jet de section augmentée,FIG. 1 is a partial view in axial section of an inverter according to the invention, in a normal section direct jet configuration; FIG. 2 is a view of this inverter in an increased section jet configuration;
- la figure 3 est une vue de cet inverseur en configuration immédiatement préalable à l'ouverture de la porte,FIG. 3 is a view of this inverter in configuration immediately prior to the opening of the door;
- la figure 4 est une vue de cet inverseur en configuration de jet inversé,FIG. 4 is a view of this invertor in an inverted jet configuration,
- la figure 5 est une vue analogue à la figure 1 d'un autre mode de réalisation de l'inverseur selon l'invention, etFIG. 5 is a view similar to FIG. 1 of another embodiment of the inverter according to the invention, and
- la figure 6 est une vue de cet inverseur dans une configuration de jet de section réduite. On se reporte à présent à la figure 1 , sur laquelle on a représenté une veine 1 d'air froid susceptible de circuler de la gauche vers la droite de la figure, entre d'une part une structure interne 3 et d'autre part une structure externe 5.FIG. 6 is a view of this inverter in a reduced section jet configuration. Referring now to Figure 1, which shows a vein 1 of cold air likely to flow from the left to the right of the figure, between an internal structure 3 on the one hand and on the other hand a external structure 5.
L'air froid circulant dans la veine 1 est mis en mouvement par une soufflante non représentée et située dans la zone amont 7, et cet air froid sort de la veine 1 dans une zone aval 9 définissant une section de tuyère. Comme cela est connu en soi, la structure interne 3 est destinée à envelopper un turboréacteur non représenté, et la structure externe 5 comprend des moyens d'inversion de poussée, c'est-à-dire des moyens aptes à dévier l'air froid circulant normalement dans la veine 1 vers l'extérieur et vers la gauche de la figure 1.The cold air circulating in the vein 1 is set in motion by a blower not shown and located in the upstream zone 7, and this cold air leaves the vein 1 in a downstream zone 9 defining a nozzle section. As is known per se, the internal structure 3 is intended to envelop a turbojet engine not shown, and the external structure 5 comprises thrust reverser means, that is to say means able to deflect the cold air normally flowing in vein 1 outward and to the left of Figure 1.
Ces moyens d'inversion de poussée comprennent une porte 11 montée pivotante sur une structure fixe 13 autour d'un axe A, la course de la partie aval de cette porte étant représentée de manière symbolique par le cercle C. Comme cela est connu en soi, cette porte 11 comprend notamment un becquet 15.These thrust reversal means comprise a door 11 pivotally mounted on a fixed structure 13 about an axis A, the stroke of the downstream portion of this door being represented symbolically by the circle C. As is known per se this door 11 comprises in particular a spoiler 15.
Cette porte comprend également une glissière 17 dont la fonction sera explicitée plus loin.This door also includes a slide 17 whose function will be explained later.
Un vérin à double tige 19 est monté pivotant sur la structure 13, et sa première tige 21 est montée pivotante sur la porte 11.A double rod cylinder 19 is pivotally mounted on the structure 13, and its first rod 21 is pivotally mounted on the door 11.
Un panneau de cavité 23 est monté coulissant sur la porte 11 entre une position visible sur la figure 1 dans laquelle ce panneau est jointif avec un bord de déviation 25 monté fixe par rapport à la structure 13, et d'autres postions qui seront explicitées plus loin. Ce panneau de cavité 23 est relié à la deuxième tige 27 du vérin 19A cavity panel 23 is slidably mounted on the door 11 between a position visible in FIG. 1 in which this panel is joined to a deflection edge 25 mounted fixed relative to the structure 13, and other positions which will be explained more far. This cavity panel 23 is connected to the second rod 27 of the cylinder 19
(voir figure 2) par l'intermédiaire d'une bielle 29.(see Figure 2) via a connecting rod 29.
Dans la configuration de la figure 1 , un panneau de tuyère 31 est couplé au panneau de cavité 23 par l'intermédiaire d'un crochet 33 et d'un contre-crochet 35 montés respectivement sur ces organes. Dans la configuration de la figure 1 , le panneau de tuyère 31 est jointif avec la porte 11 , et la section de tuyère 9 est dite « normale ».In the configuration of Figure 1, a nozzle panel 31 is coupled to the cavity panel 23 via a hook 33 and a counter-hook 35 mounted respectively on these bodies. In the configuration of Figure 1, the nozzle panel 31 is joined with the door 11, and the nozzle section 9 is called "normal".
Dans la configuration de la figure 2, la deuxième tige 27 du vérin 19 s'est allongée, provoquant ainsi, par l'intermédiaire de la bielle 29, le coulissement vers l'aval (c'est-à-dire vers la droite de la figure) du panneau de cavité 23 et donc du panneau de tuyère 31 , conduisant ainsi à une section de tuyère 9 augmentée par rapport à la section normale de la figure 1 , tandis que la cavité de porte n'est plus entièrement obturée.In the configuration of Figure 2, the second rod 27 of the cylinder 19 has elongated, thereby causing, through the rod 27, the sliding downstream (that is to say to the right of the figure) of the cavity panel 23 and thus the nozzle panel 31, thus leading to a nozzle section 9 increased with respect to the normal section of Figure 1, while the door cavity is no longer completely closed.
Une telle augmentation de la section de tuyère convient particulièrement à certaines phases du vol, pour lesquelles la non obstruction de la cavité de porte est moins pénalisante. Dans la configuration de la figure 3, la deuxième tige 27 du vérin 19 a continué de s'allonger par rapport à la configuration de la figure 2, conduisant ainsi à un déplacement extrême vers l'aval du panneau de cavité 23 et du panneau de tuyère 31. Comme on peut le voir sur la figure 3, ce déplacement extrême permet de placer l'extrémité 37 du crochet 33 au droit de la glissière 17 solidaire de la porte 11. Ce déplacement supplémentaire par rapport à la position représentée figure 2 est rendu nécessaire pour abaisser suffisamment l'extrémité du panneau de cavité 23 de façon à libérer au maximum le passage de l'air à travers le puit de porte en fonctionnement en jet inverse, pour la configuration dessinée ici, mais n'est pas toujours nécessaire.Such an increase in the nozzle section is particularly suitable for certain phases of the flight, for which the non-obstruction of the door cavity is less penalizing. In the configuration of FIG. 3, the second rod 27 of the ram 19 has continued to lengthen with respect to the configuration of FIG. 2, thus leading to an extreme downstream displacement of the cavity panel 23 and the control panel. 31. As can be seen in FIG. 3, this extreme displacement makes it possible to place the end 37 of the hook 33 at the right of the slideway 17 integral with the door 11. This additional displacement with respect to the position shown in FIG. made necessary to sufficiently lower the end of the cavity panel 23 so as to release as much as possible the passage of air through the doorway in reverse jet operation, for the configuration shown here, but is not always necessary .
La configuration de la figure 4 se déduit de celle de la figure 3 par allongement de la première tige 21 du vérin 19, cet allongement provoquant l'ouverture de la porte 11, cette porte emportant dans son mouvement le panneau de cavité 23, qui, il faut le rappeler, est monté coulissant sur cette porte.The configuration of Figure 4 is deduced from that of Figure 3 by elongation of the first rod 21 of the cylinder 19, this elongation causing the opening of the door 11, this door carrying in its movement the cavity panel 23, which it must be remembered, is slidably mounted on this door.
Lors du mouvement rotatif de cette porte 11 , la glissière 17 vient s'engager avec l'extrémité 37 du crochet 33 solidaire du panneau de tuyère 31 , de sorte que cette glissière maintient ce panneau dans sa position avale extrême.During the rotary movement of this door 11, the slide 17 engages with the end 37 of the hook 33 integral with the nozzle panel 31, so that this slide maintains this panel in its extreme downstream position.
Dans cette position ouverte, la porte 11 et le panneau de cavité 23 dévient l'air provenant de la zone 7 vers l'extérieur de l'inverseur de poussée, comme cela est indiqué par la flèche F visible sur la figure 4. On notera que le becquet 15 de la porte 11 contribue à la déviation du flux d'air froid provenant de la veine 1 vers l'amont de l'inverseur, c'est-à-dire vers la gauche de la figure 4.In this open position, the door 11 and the cavity panel 23 deflect the air coming from the zone 7 towards the outside of the thrust reverser, as indicated by the arrow F visible in FIG. that the spoiler 15 of the door 11 contributes to the deviation of the cold air flow from the vein 1 upstream of the inverter, that is to say to the left of Figure 4.
On notera également que l'on peut avantageusement prévoir une grille 39 reliée à la structure fixe 13, disposée de manière à contribuer à la déviation du flux d'air lors de l'ouverture de la porte 11. La variante représentée sur les figures 5 et 6 se distingue du mode de réalisation précédent en ceci que l'on prévoit deux vérins distincts, 19a, 19b, pour actionner respectivement la porte 11 et le panneau de cavité 23. Dans ce cas, ces vérins sont du type à simple tige 21a, 21b. On notera que dans le cas de cette variante, il n'est plus nécessaire de prévoir une bielle 29 entre le vérin d'actionnement de la porte et le panneau de cavité. L'avantage de cette variante par rapport à la solution précédente est qu'elle permet de passer d'une configuration normale représentée à la figure 5 (analogue à la configuration de la figure 1), à une configuration de section de tuyère réduite, visible à la figure 6, dans laquelle l'ensemble formé par le panneau de la cavité 23 et le panneau de tuyère 31 sont déplacés vers l'amont de la veine 1 (c'est-à-dire vers la gauche de la figure), permettant ainsi de réduire la section 9.It will also be noted that it is advantageous to provide a grid 39 connected to the fixed structure 13, arranged so as to contribute to the deflection of the air flow when the door 11 is opened. The variant shown in FIGS. and 6 differs from the previous embodiment in that it provides two separate cylinders, 19a, 19b, for respectively actuate the door 11 and the cavity panel 23. In this case, these cylinders are of the single rod type 21a , 21b. Note that in the case of this variant, it is no longer necessary to provide a connecting rod 29 between the actuating cylinder of the door and the cavity panel. The advantage of this variant over the previous solution is that it allows to go from a normal configuration shown in Figure 5 (similar to the configuration of Figure 1), to a reduced nozzle section configuration, visible in Figure 6, in which the assembly formed by the panel of the cavity 23 and the nozzle panel 31 are moved upstream of the vein 1 (that is to the left of the figure), thus reducing Section 9.
Cette configuration de section réduite convient particulièrement pour les phases de montée et de descente d'un avion équipé d'un tel système d'inversion de poussée.This reduced section configuration is particularly suitable for the rise and fall phases of an aircraft equipped with such a reverse thrust system.
Le mode de fonctionnement et les avantages de l'invention résultent directement de la description qui précède.The mode of operation and the advantages of the invention result directly from the foregoing description.
Lorsque l'on veut passer d'une configuration de section de tuyère normale (figures 1 et 5) à une configuration de section de tuyère augmentée (figure 2), on fait coulisser le panneau de cavité 23 par rapport à la porte 11 en agissant sur le vérin 19 ou 19a.When it is desired to change from a normal nozzle section configuration (FIGS. 1 and 5) to an enlarged nozzle section configuration (FIG. 2), the cavity panel 23 is slid with respect to the door 11 by acting on the cylinder 19 or 19a.
Ce faisant, le panneau de tuyère 31 étant couplé au panneau de cavité 23 par l'intermédiaire du crochet 33, ce panneau de cavité se déplace vers l'aval de la veine d'air 1 , ce qui permet d'augmenter la section de sortie de tuyère 9. Le panneau de cavité n'obstrue plus la cavité définie par la porte 11 , les phases de vol pour lesquelles cette configuration est utilisée autorisant des performances aérodynamiques dégradées.In doing so, the nozzle panel 31 being coupled to the cavity panel 23 via the hook 33, this cavity panel moves downstream of the air stream 1, thereby increasing the cross-section of the cavity. nozzle outlet 9. The cavity panel no longer closes the cavity defined by the door 11, the flight phases for which this configuration is used allowing degraded aerodynamic performance.
Pour réduire cette section de sortie de tuyère, on agit bien entendu en sens inverse sur le vérin 19, 19a. On notera qu'en configuration normale (figures 1 et 5) et en configuration de tuyère réduite (figure 6), le panneau de cavité 23 obture correctement la cavité définie par la porte 11 , ce qui permet de lisser le profil de la veine 1 d'air froid, et ainsi d'optimiser les caractéristiques aérodynamiques de l'écoulement d'air dans cette veine. Lorsque l'on souhaite inverser la poussée exercée par l'air circulant dans la veine 1 , on agit sur le vérin 19 ou 19a de manière à faire pivoter la porte 11 vers sa position ouverte (voir figure 4).To reduce this nozzle outlet section, it is of course in the opposite direction on the cylinder 19, 19a. Note that in normal configuration (Figures 1 and 5) and reduced nozzle configuration (Figure 6), the cavity panel 23 properly closes the cavity defined by the door 11, which smooths the profile of the vein 1 of cold air, and thus optimize the aerodynamic characteristics of the air flow in this vein. When it is desired to reverse the thrust exerted by the air flowing in the vein 1, it acts on the cylinder 19 or 19a so as to pivot the door 11 to its open position (see Figure 4).
Ce faisant, cette porte ainsi que le panneau de cavité 23 obstruent la veine 1 et dévient de la sorte l'air vers l'extérieur, cette déviation étant améliorée par la présence du becquet 15 et éventuellement par la grille 39. Pendant ce pivotement de la porte 11 , le panneau de tuyère 31 est maintenu en place grâce à la glissière 17 solidaire de la porte 11.In doing so, this door and the cavity panel 23 obstruct the vein 1 and thus deflect the air outwards, this deflection being improved by the presence of the spoiler 15 and possibly by the grid 39. During this pivoting of the door 11, the nozzle panel 31 is held in place by the slide 17 secured to the door 11.
Comme on peut le comprendre à la lumière de ce qui précède, aucun moyen spécifique d'actionnement du panneau de tuyère 31 n'est prévu : le coulissement de ce panneau de tuyère est provoqué par celui du panneau de cavité 23, et le maintien en place de ce panneau de tuyère lors de l'ouverture de la porte 11 est obtenu grâce à la glissière 17 qui coopère avec le crochet 33 de ce panneau de tuyère.As can be understood in the light of the foregoing, no specific means of actuating the nozzle panel 31 is provided: the sliding of this nozzle panel is caused by that of the cavity panel 23, and the maintenance of the place of this nozzle panel when opening the door 11 is obtained through the slide 17 which cooperates with the hook 33 of the nozzle panel.
L'invention permet donc d'actionner trois organes, à savoir la porte 11 , le panneau de cavité 23 et le panneau de tuyère 31 , avec seulement deux moyens d'actionnement, à savoir les tiges 21 , 27 du vérin 19, ou les tiges 21a, 21 b des vérins 19a et 19b.The invention thus makes it possible to actuate three members, namely the door 11, the cavity panel 23 and the nozzle panel 31, with only two actuating means, namely the rods 21, 27 of the jack 19, or the rods 21a, 21b of the cylinders 19a and 19b.
L'invention fournit donc des moyens simplifiés et allégés pour sélectivement mettre en œuvre les moyens d'inverseur de poussée, obturer la cavité définie par la porte 11 , et régler la section de sortie de la veine d'air froid du turboréacteur.The invention therefore provides simplified and lightened means for selectively implementing the thrust reverser means, closing the cavity defined by the door 11, and adjust the outlet section of the cold air jet of the turbojet engine.
Bien entendu, la présente invention n'est nullement limitée aux exemples décrits et représentés, fournis à titre purement illustratif. Of course, the present invention is not limited to the examples described and shown, provided for purely illustrative purposes.

Claims

REVENDICATIONS
1. Inverseur de poussée à porte(s) comprenant :A thrust reverser with a door (s) comprising:
- une structure fixe (13), - au moins une porte (11) montée pivotante sur cette structure fixe- a fixed structure (13), - at least one door (11) pivotally mounted on this fixed structure
(13) entre une position fermée où elle définit une cavité et une position ouverte,(13) between a closed position where it defines a cavity and an open position,
- au moins un panneau de cavité (23) monté coulissant sur ladite porte (11) entre une position fermée dans laquelle il obture ladite cavité et une position ouverte, - des moyens d'actionnement (19 ; 19a, 19b) de ladite porte (11) et dudit panneau de cavité (23), cet inverseur de poussée étant caractérisé en ce qu'il comprend un panneau de tuyère (31) monté coulissant sur ladite structure fixe (13), et des moyens (33, 35) pour coupler ledit panneau de tuyère (31) audit panneau de cavité (23) lorsque ladite porte (11) est fermée, puis pour coupler ledit panneau de tuyère (31) à ladite porte (11) lorsque ladite porte (11) passe de sa position fermée à sa position ouverte.at least one cavity panel slidably mounted on said door between a closed position in which it closes said cavity and an open position, means for actuating said door (19; 11) and said cavity panel (23), this thrust reverser being characterized in that it comprises a nozzle panel (31) slidably mounted on said fixed structure (13), and means (33, 35) for coupling said nozzle panel (31) to said cavity panel (23) when said door (11) is closed, then for coupling said nozzle panel (31) to said door (11) when said door (11) moves from its closed position in its open position.
2. Inverseur de poussée selon la revendication 1 , caractérisé en ce que lesdits moyens d'actionnement comprennent un vérin double (19) coopérant avec ladite structure fixe (13), ladite porte (11) et une bielle (29) reliée audit panneau de cavité.2. thrust reverser according to claim 1, characterized in that said actuating means comprise a double jack (19) cooperating with said fixed structure (13), said door (11) and a connecting rod (29) connected to said panel cavity.
3. Inverseur de poussée selon la revendication 1 , caractérisé en ce que lesdits moyens d'actionnement comprennent d'une part un premier vérin (19a) interposé entre ladite structure fixe (13) et ladite porte (11), et d'autre part un deuxième vérin (19b) interposé entre ladite structure fixe (13) et ledit panneau de cavité.3. thrust reverser according to claim 1, characterized in that said actuating means comprise firstly a first cylinder (19a) interposed between said fixed structure (13) and said door (11), and secondly a second jack (19b) interposed between said fixed structure (13) and said cavity panel.
4. Inverseur de poussée selon l'une quelconque des revendications précédentes, caractérisé en ce que les moyens de couplage dudit panneau de tuyère (31) audit panneau de cavité (23) comprennent un crochet (33) solidaire dudit panneau de tuyère (31) et un contre-crochet (35) solidaire dudit panneau de cavité (23).4. thrust reverser according to any one of the preceding claims, characterized in that the coupling means of said nozzle panel (31) to said cavity panel (23) comprise a hook (33) integral with said nozzle panel (31) and a counter-hook (35) integral with said cavity panel (23).
5. Inverseur de poussée selon l'une quelconque des revendications précédentes, caractérisé en ce que les moyens de couplage dudit panneau de tuyère (31) à ladite porte (11) comprennent un crochet (33) solidaire dudit panneau de tuyère (31) et une glissière (17) solidaire de ladite porte (11). 5. thrust reverser according to any one of the preceding claims, characterized in that the coupling means of said nozzle panel (31) to said door (11) comprise a hook (33) integral with said nozzle panel (31) and a slide (17) secured to said door (11).
6. Nacelle pour moteur d'avion, caractérisée en ce qu'elle comporte un inverseur de poussée conforme à l'une quelconque des revendications précédentes. 6. Nacelle for aircraft engine, characterized in that it comprises a thrust reverser according to any one of the preceding claims.
PCT/FR2008/000234 2007-04-24 2008-02-22 Device for varying the cross section of a secondary nozzle associated with a gate reverser and jet smoothing device WO2008132294A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08775588A EP2137394A1 (en) 2007-04-24 2008-02-22 Device for varying the cross section of a secondary nozzle associated with a gate reverser and jet smoothing device
CA002681354A CA2681354A1 (en) 2007-04-24 2008-02-22 Device for varying the cross section of a secondary nozzle associated with a gate reverser and jet smoothing device

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR07/02950 2007-04-24
FR0702950A FR2915526B1 (en) 2007-04-24 2007-04-24 DEVICE FOR VARIATION OF SECONDARY PIPE SECTION ASSOCIATED WITH VEHICLE SMOOTHING VEHICLE INVERTER.

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FR2959531B1 (en) * 2010-04-28 2015-12-18 Aircelle Sa DOOR INVERTER
US20120079805A1 (en) * 2010-09-30 2012-04-05 Alan Roy Stuart Thrust reverser assembly
FR3057617B1 (en) * 2016-10-17 2020-10-16 Airbus NACELLE OF A TURBOREACTOR CONTAINING A INVERTER FLAP

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EP0321993A2 (en) * 1987-12-21 1989-06-28 The Boeing Company Thrust reverser for high bypass jet engines
EP0821151A1 (en) * 1996-07-18 1998-01-28 Hispano-Suiza Thrust reverser for a jet engine with doors with a sliding panel
US5778659A (en) * 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
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EP0821151A1 (en) * 1996-07-18 1998-01-28 Hispano-Suiza Thrust reverser for a jet engine with doors with a sliding panel
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US9784213B2 (en) 2012-10-29 2017-10-10 Rolls-Royce Deutschland Ltd & Co Kg Aeroengine thrust reverser arrangement

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FR2915526B1 (en) 2009-05-29
EP2137394A1 (en) 2009-12-30
CA2681354A1 (en) 2008-11-06
FR2915526A1 (en) 2008-10-31

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