WO2014207410A1

WO2014207410A1 - Dual-grid reverser without rods in the duct

Info

Publication number: WO2014207410A1
Application number: PCT/FR2014/051653
Authority: WO
Inventors: Guy Bernard Vauchel
Original assignee: Aircelle
Priority date: 2013-06-27
Filing date: 2014-06-27
Publication date: 2014-12-31
Also published as: FR3007799A1

Abstract

A dual-grid reverser without rods in the duct. A thrust reverser device 1 for an aircraft nacelle comprising a fixed outer structure (2) provided with a front frame, said device comprising: • - a movable cowl (3) slidably mounted relative to said fixed outer structure (2) between a direct jet position in which no thrust reverse takes place, and a reversed jet position in which thrust reverse takes place, • - radially external thrust reverse grids (5), uncovered when said movable cowl (3) slides from the direct jet position of same to the reversed jet position of same, and • - radially internal thrust reverser components (4), each mounted pivoting on said front frame, and linked to said movable cowl (3) by at least one rod (6).

Description

Inverter with double grids without connecting rods in the vein

The invention lies in the field of thrust reversers with gates for aircraft nacelles and more particularly relates to thrust reversers grids without connecting rods in the vein.

An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped. These ancillary actuating devices comprise in particular a mechanical thrust reversal system.

A nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing the thrust reverser means and intended to surround the combustion chamber of the turbojet engine. , and is generally terminated by an ejection nozzle whose output is located downstream of the turbojet engine.

Modern nacelles are intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air (also called primary flow) from the combustion chamber of the turbojet engine, and a flow of cold air (secondary flow) flowing outside the turbojet through an annular passage, also called vein, formed between a shroud of the turbojet engine and an inner wall of the nacelle. The two air flows are ejected from the turbojet engine from the rear of the nacelle.

The role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine. In this phase, the inverter obstructs the cold flow vein and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft.

The means implemented to achieve this reorientation of the cold flow vary according to the type of inverter. However, in all cases, the structure of an inverter comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a position of retraction in which they close this passage. These covers can perform a deflection function or simply activation other means of deflection.

In the case of a gate inverter, the reorientation of the air flow is performed by deflection grids, the hood having a simple sliding function to discover or cover these grids. Complementary locking doors, also called shutters, activated by the sliding of the cowling, generally allow a closure of the vein downstream of the grids so as to allow the reorientation of the cold flow to the grids.

These flaps are pivotally mounted on the sliding cowl between a retracted position in which they provide, with said movable cowl, aerodynamic continuity of the inner wall of the nacelle and a deployed position in which, in reverse thrust situation, they come at least partially closing the annular channel to deflect an air flow to the deflection grids discovered by the sliding of the movable cowl.

The pivoting of the flaps is guided by rods attached, on the one hand, to the flap, and on the other hand, to a fixed point of the internal structure delimiting the annular channel.

Knuckle thrust reverser element hinge mechanisms are known for aircraft nacelles.

Document EP 1 462 642, which relates to a sliding linkage mechanism of thrust reverser elements, more particularly discloses a dual mechanism for actuating a thrust reverser, one for driving one outer shell of the thrust reverser, and the other to actuate the thrust reversing flaps.

The document FR 2 907 512 discloses a drive mechanism for both the thrust reversing flaps and the movable cowling covering the thrust reversal grids in the direct thrust position, in this configuration each flap is attached to a thrust reverser. actuating cylinder and articulation.

The document GB 1 259 045 discloses a multi-linkage mechanism, each component is actuated by several rods having a low lever arm; the shutter opens in the direction of scooping increasing the risk of breakage of parts of the mechanism. The pivot connection allowing the rotation of the flap consists of two rollers each running along a guide rail of a roller, this rotation system has weaknesses in term reliability especially due to the slippery movement of the shutter rollers.

GB 1 345 337 discloses a flap drive by a mechanism of chains actuated by gears, such a mechanism also comprises guide rails. Such structures particularly affect the reliability of the training assembly thus formed.

The document US Pat. No. 3,262,268 discloses a mechanism of sliding double links in a thrust reverser flap, these connecting rods being pivotally connected to the thrust reversal flap, and the pivot link can itself translate along the flap. via a sliding rail whose axis is substantially that of the flap.

Document US Pat. No. 4,030,291 discusses a complex thrust reversing shutter actuation mechanism combining the use of ramps, sliders, a plurality of articulated external panels, the complexity of this mechanism does not allow any make it reliable.

The document US Pat. No. 4,356,973 discloses a mechanism for articulating a thrust reverser flap by means of a gear, a pinion of which is fixed to a connecting rod in pivot connection, the rod is connected to the thrust reverser flap. . The pinion translates with the displacement of the movable cowl of the nacelle, thus causing the shutter in its race, a member slides along a guide rail of the movement of the shutter.

The document FR 2 757 570 discloses a device comprising rotating grids that can additionally be rotated. In this document, the grids act both as jet reversal gates, but also as connecting rods for deploying thrust reversing flaps both outwardly of a double-flow nacelle in which the device is implanted and to obstruct the cold air stream of the nacelle in order to more effectively reverse the jet of air circulating in the cold air vein. In general, the mechanisms disclosed in the prior art are complex and have reliability defects thus leading to risks of malfunction of the thrust reversal and therefore the risk of accident. In addition, most of these mechanisms are penalizing in terms of weight thus generating additional cost to use and, the complexity, can be expensive to manufacture. An object of the present invention is to provide a thrust reverser device without connecting rods through the vein, such rods generating aerodynamic losses, freed from the aforementioned drawbacks.

Another object of the present invention is to provide a simple thrust reverser mechanism, robust, lightweight, inexpensive, reliable, and independent of the engine cover.

For this purpose, the present invention relates to a thrust reverser device for a nacelle of an aircraft comprising a fixed external structure provided with a front frame, this device comprising:

a movable cowl slidably mounted relative to said fixed external structure between a direct jet position for which there is no thrust reversal, and an inverted jet position for which thrust reversal occurs,

radially external thrust reversing grids, discovered during the sliding of said movable cowl from its direct jet position to its inverted jet position, and

- Radially inner thrust reversing elements, each mounted pivoting on said front frame, and connected to said movable hood by at least one connecting rod.

According to other features of the invention, the thrust reverser device comprises one or more of the following optional features considered alone or according to all the possible combinations:

- The radially inner thrust reversing elements have a generally trapezoidal general shape so as to be joined to each other in the inverted jet position;

- The rod is attached to a movable end of the radially inner thrust reverser elements located opposite their fixed end by a pivot connection;

- The rod is actuated by the translation of the movable cowl;

- the connecting rod is telescopic;

- The radially inner thrust reversing elements are arranged in the thickness of the movable hood in the direct jet position; - The radially external thrust reversing grids are disposed in the thickness of the movable cowl in the direct jet position;

the radially external thrust reversing grids are arranged in the thickness of the external structure in the direct jet position;

the movable cowl covers a portion of the radially inner thrust inversion elements in the vicinity of the movable end of the radially inner thrust reverser elements, in the direct jet position, by means of a safety tab;

- The radially outer thrust reversing grids are mounted substantially in sliding connection with the external structure;

- The radially external thrust reversing grids are driven by the translation of the movable cowl;

- The radially external thrust reversing grids are mounted fixed relative to the outer structure;

a damping device is disposed between the downstream end zone of each of the radially inner thrust reverser elements and the movable thrust reverser cowl so that the radially inner thrust reverser elements do not do not collide with the moving hood in the direct throw position;

the damping device is a spring;

a sealing device makes it possible to seal, in the direct jet position, the junction zone between the mobile cowl and the external structure;

- The sealing device is disposed under the radially outer thrust reversing grids, upstream of the upstream edge of the movable cowl;

- The sealing device is disposed above the radially outer thrust reversal grids, upstream of the upstream edge of the movable cowl;

the radially inner thrust reversing elements are radially inner thrust reversing grids;

the radially inner thrust inversion elements may each comprise at least one deflector covering a cavity formed by the thrust reverser device in the direct jet position; - The baffles are movable in rotation along an axis substantially parallel to the axis of rotation of the rods. This solution allows a quick implementation of the thrust reverser device by its simplicity, while allowing a control of deformed structures; moreover, the simplicity of such a device is also guarantor saving both in terms of production cost and installation in terms of mass and therefore of use, in particular thanks to the absence of connecting rods in the vein secondary of the aircraft nacelle. In addition, such a solution makes it possible to substantially reduce or even eliminate the reliability and therefore safety defects such as can be encountered in the devices of the prior art.

The invention also relates to an aircraft nacelle equipped with a thrust reverser device according to the invention. Finally, the invention relates to an aircraft comprising a nacelle equipped with a thrust reverser device according to the invention.

In the present description, the longitudinal axis of the longitudinal axis of a nacelle and radial axis any axis orthogonal to the main axis and passing through the main axis (each correspond to a radius of the substantially tubular nacelle). Radial plan is any plane containing two orthogonal radial axes, and at last longitudinal plane is any plane containing the main axis of the nacelle and longitudinal section any section along the longitudinal plane.

What is meant by upstream is what comes before the point or element considered, in the direction of the flow of air in a turbojet, and downstream what comes after the point or element considered, in the direction of the flow of the air in a turbojet.

In the figures, appended to the description, the flow direction of the different air flows is represented by simple arrows, and the air flows in the direct jet position from left to right in the figures.

In general, in the figures, the flow of air flows from left to right.

The term "upper", "above" and "outside" is that which is farthest from the longitudinal axis in relation to the point or element considered, and below, below and inside which is closest to the longitudinal axis relative to the point or element considered.

Several possible embodiments of the invention will now be described by way of nonlimiting examples, with reference to the appended figures; in the set of figures, identical or similar references denote identical or similar organs or sets of members:

Figure 1 is a schematic partial sectional view of a thrust reverser device according to a first embodiment of the present invention in the direct jet position; Figure 2 is a schematic partial sectional view of the thrust reverser device according to the first embodiment of the present invention in a first intermediate configuration;

Figure 3 is a schematic partial sectional view of the thrust reverser device according to the first embodiment of the present invention in a second intermediate configuration;

Figure 4 is a schematic partial sectional view of the thrust reverser device according to the first embodiment of the present invention in the inverted jet position; Figure 5 is a schematic view of the radially inner thrust reversing elements in the retracted position in the movable cowl of a thrust reverser according to the invention; Figures 6 to 8 are similar to Figures 1 to 4 illustrating a second embodiment of the present invention;

Figures 9 to 12 are similar to Figures 1 to 4 illustrating a third embodiment of the present invention;

Figures 13 to 15 are similar to Figures 1 to 4 illustrating a fourth embodiment of the present invention; Figures 16 to 18 are similar to Figures 1 to 4 illustrating a fifth embodiment of the present invention.

With reference to FIGS. 1 to 4, the thrust reverser device according to the first embodiment of the present invention is described. The thrust reverser device 1 comprises an external structure 2, a movable cowl 3, radially inner thrust reversal grids 4, radially outer thrust reverser grids 5, a connecting rod 6, a seal 7 of seal.

The thrust reverser device may also comprise, as illustrated in Figure 1, a spring 8 (not shown in Figures 2, 3 and 4 as optional in this embodiment).

The radially outer thrust reversing grids 5 are fixed substantially in recess connection on the upstream end of the movable cowl 3 so that they extend substantially in the continuity of the general shape of the movable cowl 3.

The radially external thrust reversal grids 5 are disposed within the outer structure 2 and are slidably connected to it so that when the movable cowl 3 slides downstream of an aircraft nacelle on which the device 1 is mounted, the moving cowl 3 drives in movement the radially outer thrust reversing grids 5 which slide in the outer structure 2 downstream of the outer structure 2.

The movable cowl 3 comprises an upstream spoiler 9 on which the radially external thrust reverser grids 5 are fixed so that the spoiler 9 is in plane-to-plane contact with the edges of the radially outer thrust reversal grids 5.

The seal 7 has a substantially circular shape disposed under the radially external thrust reversal grids 5, substantially downstream of the external structure 2. The seal 7 reduces the imbalances in opening or closing sensitivity due to to the internal pressure of the cold air stream of the aircraft nacelle in the configuration where the movable cowl 3 is retracted.

As can be seen in particular in FIG. 1, the seal 7 is in contact with one end of the spoiler 9 when the thrust reverser device 1 is in the direct jet position so as to seal, thus the seal 7 is compressed between the spoiler 9 and the external structure 2.

The radially inner thrust reversing grids 4 are in pivot connection with the external structure 2 substantially at the downstream end of the external structure 2, that is to say on the front frame of the external structure 2. direct jet position, visible in Figure 1, the radially inner thrust reversal grids 4 extend substantially in the continuity of the outer structure 2 downstream of the outer structure 2 and are housed within the movable hood 3.

Each radially inner thrust reversing radially inner thrust gate 4 is in pivot connection January 1 with a connecting rod 6 on a first end of each connecting rod 6. This pivot connection January 1 is located on the upper face of each inversion grid radially inner thrust

4 and substantially at the downstream end of each radially inner thrust reversal gate 4 as is particularly visible in FIG. 1.

Each connecting rod 6 extends above the radially inner thrust reversal grille 4 with which it is in pivot connection, the connecting rod 6 being arranged facing the radially inner thrust reversal grille 4.

Each link 6 is in pivot connection with the movable cover 3 on the second end of each link 6 as is particularly visible in FIG.

In the configuration just described, each pivot connection 1 1 between each connecting rod 6 and each corresponding radially inner thrust reversal grille 4 can be integrated in the thickness of each radially inner thrust reversal grille 4 and not on the upper face of each radially inner thrust reversal grille 4. This arrangement makes it possible to increase the angle of attack between each connecting rod 6 and their corresponding radially inner thrust reversal grille 4.

The movable cowl 3 also comprises at least one safety tongue 12 making it possible to retain the radially inner thrust reversal grids 4 when the thrust reverser device 1 is in the direct jet position 1 as represented in FIG. .

The springs 8 serve to damp the shocks that could occur between the movable cowl 3 and the radially inner thrust reversal grids 4.

With reference to FIG. 1, the direct jet position of the thrust reverser device 1 according to the first embodiment of the present invention is described. The radially external thrust reversal grids

5 are located within the outer structure 2 in the thickness of the structure 2, upstream of the movable cowl 3, and the radially inner thrust reversing grids 4 are housed in the thickness of the movable cowl 3, the gasket 7 is compressed between the spoiler 9 and the front frame of the external structure 2 .

In order to bring the thrust reverser device 1 into its inverted jet position, the movable cowl 3 is moved by cylinders not shown in a translation movement of the longitudinal axis axis, it causes in its stroke the radially outer thrust reversing grids 5. Simultaneously, and with reference to FIGS. 2 and 3 showing two intermediate configurations, the movable cowl 3 exerts a force on each link 6 which, being in pivot connection with the movable cowl 3, pivot in Consequently, the radially inner thrust reversal grids 4 to which they are attached in pivot connection 1 1 pivot towards the center of the nacelle, thus obstructing the cold air stream of the nacelle for thrust reversal.

FIG. 3 represents the configuration of the thrust reverser device 1 when the connecting rods 6 have substantially completed a quarter of a turn, that is to say when their first end in pivot connection with the thrust reversal grids radially inner 4 is as close as possible to the longitudinal axis.

Figure 4 shows the thrust reverser device 1 in its inverted jet position. Driven by the movable cowl 3, the rods 6 have then rotated more than a quarter turn; the moving cowl can thus fully discover the radially outer thrust reversal grids 5 in order to increase the effectiveness of the thrust reverser device 1.

With reference to FIG. 5, the particular shape of the radially inner thrust reversal grids 4 is described. Indeed, as can be guessed from FIG. 5, the radially inner thrust reversal grids 4 have a trapezoidal shape so that they can be joined together when the thrust reverser device 1 is in the inverted jet position.

When the thrust reverser device 1 is in the direct thrust position, the distance between the radially inner thrust reversing grids 4 varies along the longitudinal axis so that the tabs 12 also have a particular shape in order to correctly retain, if necessary, the radially inner thrust reversal grilles 4 in the thickness of the movable cover 3 as is particularly visible in FIG.

This trapezoidal shape radially inner thrust reversal grids 4 is common to all embodiments of the present invention explained in the present description.

With reference to FIGS. 6, 7 and 8, the thrust reverser device 1 according to the second embodiment of the present invention is described.

The thrust reverser device 1 according to the second embodiment is similar to that according to the first embodiment of the present invention.

The only difference between these two embodiments lies in the fact that the radially external thrust reversal grids 5 are arranged, in the direct thrust position of the thrust reverser device 1, within the movable cowl 3.

The radially outer thrust reversing grids 5 are in connection with the external structure 2, and more precisely with the front frame of the external structure 2 so that the radially outer thrust reversal grids 5 extend in the thickness of the movable cover 3, downstream and substantially in continuity with the external structure 2.

Thus, the radially outer thrust reversal grids 5 are stationary relative to the outer structure 2 during the passage of the thrust reverser device 1 from its inverted jet position to its direct jet position and vice versa.

Given this difference, it goes without saying that the seal 7 is no longer arranged under the radially external thrust reversal grids 5 but above. Thus, it is the upper part of the spoiler 9 of the movable cowl 3 which is in contact with the gasket 7 in the direct jet position of the thrust reverser device 1.

FIG. 7 represents the thrust reverser device 1 in the intermediate configuration and FIG. 8 represents it in the inverted jet position.

With reference to FIGS. 9 to 12, the thrust reverser device 1 according to the third embodiment of the present invention is described. In this third embodiment, the thrust reverser device is similar to that of the second embodiment.

The only difference between these two embodiments lies in the fact that the connecting rods 6 are race-catching rods, in other words telescopic rods.

Such telescopic connecting rods 6 comprise a main body 13 connected pivotally 1 1 with the corresponding radially inner thrust reversal grille 5, a secondary body 14 pivotally connected to the movable cover 3 and a thrust spring 15 disposed in the body secondary 14. The main body 13 is substantially in sliding connection with the secondary body 14 and the spring surrounds the portion of the main body 13 which is in the secondary body 14.

The thrust spring 15 is preferably a spiral spring, and is fixedly attached at one of its ends to the distal end of the secondary body relative to that used to make the pivot connection of the secondary body 14 with the movable cover 3 , ie the end of the secondary body closest to the pivot connection 1 1 between the main body 13 and its corresponding radially inner thrust reversal grill 4.

The thrust spring 15 is fixedly attached by the other of its ends to the distal end of the main body 13 relative to that used to make the pivot connection 1 1 between the main body 13 and its thrust reversal grid radially. interior 4 corresponding.

This configuration of the spring is particularly visible in FIGS. 9 to 12.

In the direct thrust position of the thrust reverser device 1, the end of the main body 13 located in the secondary body 14 is not in abutment, as is particularly visible in FIG. 9.

In the transition from the direct jet position to the deployed one of the thrust reverser device 1, the spring 15 tends to push the main body 13 towards the inside of the secondary body 14. The fact that the main body 13 enters into the secondary body 14 during movement of the movable cover 3 downstream of the nacelle to bring the thrust reverser device 1 from its direct jet position to its inverted jet position implies that during a first phase of the movement of the hood mobile 3, the grids radially inner thrust reversers 4 remain stationary. The movable cowl 3 thus performs a "dead stroke".

The term "dead stroke" is then understood to mean the travel carried out by the moving cowl 3 during which the main body 13 of the rods 6 slides inwardly of the corresponding secondary body, and during which the thrust reversal grids radially interior 4 are therefore immobile.

Such a connecting rod structure 6 makes it possible to delay the driving of the radially inner thrust reversal grids 4, thus to enlarge the overlap of the tongues 12 and thus to reduce the length of the cavity situated between the front frame of the external structure 2 and the tabs 12 relative to the longitudinal axis accordingly.

During the dead stroke, the rods 6 are reduced in length so that at a given intermediate configuration of the thrust reverser device 1, the radially inner thrust reverser grids 4 according to the present embodiment (third embodiment) see their deployment less advanced than that of the radially inner thrust reversal grids 4 according to the previously described embodiments. This is particularly visible in FIG. 11, which shows the deployment of the radially inner thrust reversal grids 4 according to the present embodiment (third embodiment) and the deployment of the thrust reversal grids radially. interior according to the other embodiments referenced under the number 4 'for the occasion.

With reference to FIG. 12, the inverted jet position of the thrust reverser device 1 according to the third embodiment is described. In this inverted jet position, the rods 6 as described above are contained in the casing radially inner thrust reversal grids 4 and deflection 5 along the longitudinal axis. With reference to FIGS. 13 to 15, the fourth embodiment of the present invention is described.

As is particularly visible in Figures 1, 6 and 9, in the direct jet position the thrust reverser device 1 has an opening 16 significantly reduces the aerodynamic performance of the thrust reverser device 1. In the fourth embodiment of the invention, there is provided a thrust reverser device 1 having radially inner thrust reverser elements 4 comprising deflectors 17 instead of the vanes of the thrust reversal grids. radially inner 4.

In Figures 13 to 15, these deflectors 17 have two in number but can be installed in greater numbers in the thrust reverser device 1.

The deflectors 17 are rotatably mounted on a frame 18, itself arranged in the thrust reverser device 1 in the same manner as the radially inner thrust reversal grids 4, as described in the previous embodiments; thus, the armature 18 is moved in the same way as the radially inner thrust reversing grids 4 when the thrust reverser device 1 passes from its direct jet position to its inverted jet position and vice versa.

It will be noted that in FIGS. 13 to 15, the armature 18 has a bent shape in its end zone attached to the connecting rod 6, the connecting rod 6 being in these FIGS. 13 to 15 preferentially as described in the first and second modes. of realization.

As is particularly visible in FIG. 13, representing the thrust reverser device 1 in the direct jet position, the deflectors 17 on the one hand also have a bent shape in their downstream end zone in FIG. to allow thrust reversal; and on the other hand are shaped to fill the cavity 16 in order to maintain as much as possible the aerodynamic continuity with the internal wall of the external structure 2.

Thus, the deflectors 17 are shaped to cover the cavity 16 in the direct jet position of the thrust reverser device 1.

Preferably, the baffles 17 are in pivot connection with the armature 18 at their bending zone.

The thrust reverser device 1 according to the fourth embodiment of the present invention comprises two additional links, with respect to the other embodiments previously described, dedicated to the setting in motion of the deflectors 17 during the passage of the position of direct jet to the inverted jet position of the thrust reverser device 1 and vice versa.

Indeed, with reference to Figure 13, it is noted the presence of two connecting rods 19 and 20 of articulation of the deflectors 17. At one of its ends, the rod 19 is pivotally connected to one end of the rod 20. The rod 20 is pivotally connected to the other of its ends with the movable cover 3, and this link is slightly offset from that of the rod 6, more precisely, it is located downstream of the connection between the rod 6 and the movable cowl 3. The baffles 17 are in pivot connection with the rod 19 substantially at their downstream end as visible on the figure 13.

Thus, the rods 19 and 20 are, like the connecting rod 6 and the armature 18, moved by the movable cowl 3 when it is translated as is particularly visible in all of Figures 13 to 15.

When the movable cowl 3 is translated from its direct jet position to its inverted jet position, the link 20 then in motion exerts a force on the connecting rod 19 at their pivot connection, the rod 19 then pushes the ends of the deflectors 17 so that these deflectors 17 come into a rotational movement relative to the frame 18 on which they are mounted in pivot connection, the rotation of each of the deflectors 17 has for axis an axis passing the connecting rod 18 and which is orthogonal to it as can be seen in all of Figures 13 to 15.

Simultaneously, the armature 18 deploys through the connecting rod 6 in the same manner as explained in the previous embodiments.

The radially outer thrust reversing grids 5 are arranged in the same manner as described in the second and third embodiments of the present invention, i.e., within the outer structure 2 when the device of FIG. 1 is in the direct jet position and, driven by the mobile cowl 3 in a translational movement, the radially outer thrust reversal grids are deployed above the deflectors 17.

Arrived in the inverted jet position, the deflectors 17 deflect the flow of air to the radially external thrust reversal grids 5 which themselves return it upstream of the thrust reverser device 1, so the thrust is reversed.

As can be seen in FIG. 15, at least one flow straightening blade 21 can be added to the reinforcement 18 to optimize the action of the radially inner thrust reverser elements 4.

A sealing device 7 similar to that described in the second embodiment of the present invention may also be installed in the thrust reverser device 1 of the present fourth embodiment. Referring to Figures 16 to 18, a fifth embodiment of the present invention is described.

The fifth embodiment of the present invention results from a combination of the means used in the various embodiments of the present invention already described.

In particular, the thrust reverser device 1 according to the fifth embodiment of the present invention is similar in structure to that described in the fourth embodiment.

Indeed, we find the frame 18, the rod 6 and the rod 20, and a deflector 17.

However, the armature 18 carries a plurality of flow rectification vanes 21 parallel to each other and arranged in such a way that the air passing through these vanes 21 is deflected towards the radially outer thrust reversal grids 5. Thus, the assembly comprising the armature 18 and the flux rectification vanes 21 is similar in its structure and its arrangement in the thrust reverser device 1 to the radially inner thrust reversal grids 4 described in the first, second and third modes of realization.

In the zone of bending of the armature 18, a deflector 17 is installed in pivot connection with the armature 18, at the downstream end of the armature 18 as visible in FIG. 16. This baffle 17 is shaped to cover the cavity 16 substantially in its entirety. The deflector 17 is also at its downstream end 22 particularly visible in Figure 16 in pivot connection with a downstream end of the rod 20. The movement mechanism is substantially deflector 17 is substantially the same as that of the deflectors 17 described in the fourth embodiment. However, the thrust reverser device 1 of this fifth embodiment does not include a connecting rod 19 as present in the fourth embodiment. This is why the deflector 17 is directly in pivot connection with the connecting rod 20 which sets it in motion.

The deflector 17 has a tongue 23 which makes it possible to plug the entire cavity 16.

The radially external thrust reversal grids 5 are housed in the external structure 2 when the thrust reverser device 1 is in the direct jet position and is driven by the movable cowl 3 in translation. when the device goes into the inverted jet position until they are substantially above the radially outer thrust reversing elements 4. It goes without saying that the invention is not limited to the embodiments described above by way of example, but that it includes all technical equivalents and all variants of the means described above and their possible combinations.

Claims

1. Thrust reversal device 1 for a nacelle of an aircraft comprising a fixed external structure 2 provided with a front frame, this device 1 comprising:

a movable cowl 3 slidably mounted relative to said fixed external structure 2 between a direct jet position for which there is no thrust reversal, and an inverted jet position for which there is thrust reversal,

radially external thrust reversal grids 5, discovered during the sliding of said movable cowl 3 from its direct jet position to its inverted jet position, and

- Radially inner thrust reversing elements 4, each mounted pivoting on said front frame, and connected to said movable cover 3 by at least one connecting rod (6, 19, 20).

2. Thrust reversal device 1 according to claim 1 characterized in that the radially inner thrust reverser elements 4 have a generally trapezoidal general shape so as to be joined to each other in the inverted jet position.

3. thrust reverser device 1 according to any one of claims 1 or 2 characterized in that the rod 6 is actuated by the translation of the movable cowl 3.

4. thrust reverser device 1 according to any one of the preceding claims characterized in that the rod 6 is telescopic.

5. thrust reverser device 1 according to any one of the preceding claims characterized in that the radially inner thrust reversing elements 4 are arranged in the thickness of the movable cowl 3 in the direct jet position.

6. thrust reverser device 1 according to any one of the preceding claims characterized in that the radially outer thrust reversing grids 5 are arranged in the thickness of the outer structure 2 in the direct jet position.

7. Thrust reversal device 1 according to claim 6 characterized in that the radially outer thrust reversal grids 5 are mounted substantially in sliding connection with the external structure 2.

8. thrust reverser device 1 according to any one of claims 6 or 7 characterized in that the radially external thrust reversing grids 5 are driven by the translation of the movable cowl 3.

9. thrust reverser device 1 according to any one of claims 1 to 5 characterized in that the radially external thrust reversal grids 5 are disposed in the thickness of the movable cowl 3 in the direct jet position.

10. Thrust reversal device 1 according to claim 9 characterized in that the radially outer thrust reversal grids 5 are fixedly mounted relative to the outer structure 2.

1 1. Thrust reversal device 1 according to any one of the preceding claims, characterized in that the movable cover 3 covers a part of the radially inner thrust reverser elements 4 in the vicinity of the movable end of the thrust reverser elements. radially inner 4, in the direct jet position, by means of a tab 12 security.

12. thrust reverser device 1 according to any one of claims 6 to 8 characterized in that a sealing device 7 for sealing, in the direct jet position, the junction area between the movable cowl 3 and the outer structure 2 is disposed under the radially outer thrust reversing grids 5, upstream of the upstream edge of the movable cowl 3.

13. thrust reverser device 1 according to any one of claims 1 to 1 1 characterized in that the sealing device 7 is disposed above the radially external thrust reversal grids 5, upstream of the singing upstream of the moving cowl 3.

14. Thrust reversal device 1 according to any one of the preceding claims characterized in that the radially inner thrust reversing elements 4 may each comprise at least one deflector 17 covering a cavity 16 formed by the inversion device thrust 1 in direct thrust position

15. thrust reverser device 1 according to claim 14 characterized in that the baffles 17 are rotatable about an axis substantially parallel to the axis of rotation of the rods.

16. Thrust reversal device 1 according to any one of the preceding claims, characterized in that the reversing elements of radially inner thrusts 4 are radially inner thrust reversal grids 4.

17. An aircraft nacelle characterized in that it is equipped with a thrust reverser device 1 according to any one of the preceding claims.

18. Aircraft characterized in that it is equipped with a nacelle according to claim 17.