Thrust reverser with anti-buckling actuation system

Abstract

The present disclosure relates to a thrust reverser (1) for a turbojet aircraft nacelle, comprising: a fixed structure (10), a movable structure (11), an actuator (2), wherein the actuator extends along a main axis (A1) and is connected to the fixed structure (10) via a first connection (P1) and is connected to the movable structure (11) via a second connection (P2), and is used to deploy the movable structure (11) between a direct injection position and a reverse injection position, wherein the actuator (2) is also connected to the fixed structure (10) via a third connection (P3) longitudinally arranged between the first connection (P1) and the second connection (P2), wherein the axis (A3) of the third connection (P3) is radially eccentric from the main axis (A1), and the third connection (P3) allows the actuator (2) to have a predetermined displacement relative to the fixed structure (10).

Description

Technical Field

[0001] The invention relates to a turbojet engine nacelle comprising a thrust reverser intended to equip such a nacelle. Background Art

[0002] The nacelle generally has a tubular structure comprising an air inlet upstream of the turbojet engine, an intermediate section for surrounding the fan of the turbojet engine, a downstream section housing thrust reversal means and surrounding the combustion chamber of the turbojet engine, and the nacelle generally terminates in a nozzle whose outlet is situated downstream of the turbojet engine.

[0003] Modern nacelles are used to house bypass turbojets capable of generating a primary hot air flow from the combustion chamber of the turbojets via rotating fan blades and a secondary cold air flow circulating outside the turbojets through an annular channel, also called a flow path, formed between the cowling of the turbojets and the inner wall of the nacelle. Both air flows are ejected backwards from the turbojets through the nacelle.

[0004] The purpose of the thrust reverser is to improve the braking capacity of the aircraft when landing by redirecting at least part of the thrust generated by the turbojet engine to the front. In this phase, the thrust reverser blocks the flow path of the cold air and directs it towards the front of the nacelle, thereby generating reverse thrust that is additional to the braking of the aircraft wheels.

[0005] The method of achieving this redirection of the cold air flow varies according to the type of thrust reverser. However, in all cases, the structure of the reverser comprises a fixed structure and a mobile structure, the mobile structure being able to move between, on the one hand, a deployed position, called the reverse jet position, in which the mobile structure opens a channel in the nacelle for the deflected flow, and, on the other hand, a retracted position, called the direct jet position, in which the mobile structure closes the channel. This mobile structure can perform a deflection function or simply activate other deflection means.

[0006] Thus, thrust reversers of the cascade type are known, in which the redirection of the airflow is achieved by means of cascade blades, the movable structure then comprising a sliding movable cowl intended to expose or cover these cascade blades, the movement of which then activates the deployment of thrust reversal flaps, thus allowing the flow path downstream of the cascade blades to be closed in order to optimize the redirection of the cold flow. This movement of the movable cowl is achieved by actuators along a longitudinal axis parallel to the axis of the nacelle. Each actuator is connected on the one hand to a fixed point of the fixed structure and on the other hand to a fixed point of the movable structure.

[0007] The movable cowl is subjected to forces in the longitudinal and radial directions borne by the fixed structure via the actuator. During the movement of the movable cowl towards its reverse jet position, each actuator linearly extends to accompany the movement of the movable cowl. During the movement of the actuator towards its reverse jet position, especially at the end of its stroke, the blocking of the thrust reverser can occur at the actuator, or even at the track and slide between the fixed structure and the movable structure. This blocking of the thrust reverser leads to a blocking of the linear extension of the actuator. In this case, the energy applied to the reverser causes a bending moment, which can be radially deformed relative to the axis of the reverser, and the actuator is therefore subjected to buckling.

[0008] The solution consists in structurally strengthening these actuators by increasing their cross section so that they can withstand a predetermined bending. Unfortunately, these solutions lead to an increase in the mass of the thrust reverser.

[0009] Document FR 2 978 800 A1 discloses a nacelle comprising a thrust reverser as described above, wherein the movable cowl is displaced translationally by a linear actuator, thereby ensuring the movement of the movable cowl and the deployment or retraction of the thrust reverser flaps.

[0010] Unlike the previous configurations of thrust reversers, each actuator also passes through an opening formed in the rear frame of the fixed structure.

[0011] If the opening of the rear frame of the fixed structure makes it possible to limit the radial displacement of the actuator relative to its axis, this does not prevent either the degradation of the actuator or the propagation of mechanical vibrations generated by repeated contacts between the actuator and the fixed structure. In addition, such a structure requires the dimensions of the rear frame structure to be adjusted to allow the integration of the actuator.

[0012] Document FR 2 907 512 A1 proposes limiting the bending phenomena of the actuator using a slide fixed to a movable structure, accompanied by a guide for the actuator's drive rod relative to the body of the actuator.

[0013] The use of such a drive rod-slider system makes it possible to integrate a bulky thrust reverser, which also leads to an increase in the resistance and mass of the reverser. Moreover, such a system prevents the rod from being fully retracted into the body of the actuator, and therefore has the disadvantage of providing an actuator of greater length, which has an impact on the axial dimensions of the movable cowl. Moreover, such a system does not protect the body of the actuator from buckling forces caused by the reverse flow. It is therefore necessary to increase the cross-section of the structure of these actuators, which increases the mass of the assembly.

[0014] Other thrust reversers are known, such as the thrust reverser in document US 2017 / 226962A1, and other actuation systems are known, such as the actuation system in US 2010 / 089029A1. Summary of the invention

[0015] The object of the present invention is to propose a thrust reverser for a turbojet aircraft nacelle comprising a system for limiting the displacement of the actuator having a simplified integration while allowing the drag and mass of the reverser to be reduced.

[0016] To this end, the present invention proposes a thrust reverser for a turbojet aircraft nacelle, comprising:

[0017] - fixed structure,

[0018] - movable structures,

[0019] an actuator extending along the main axis and connected to the fixed structure by a first connection and to the movable structure by a second connection for deploying the movable structure between a direct injection position and a reverse injection position,

[0020] The actuator is also connected to the fixed structure by a third connection portion, and the third connection portion is also arranged longitudinally between the first connection portion and the second connection portion,

[0021] It is characterized in that

[0022] The axis of the third connection portion is radially eccentric from the main axis, and the third connection portion allows a predetermined displacement of the actuator relative to the fixed structure.

[0023] The construction of the thrust reverser according to the invention makes it possible to limit the radial displacement of the actuator relative to its axis, so that the bending moment applied to the actuator around an axis perpendicular to its main axis is greatly reduced. In fact, the use of a third connection between the actuator and the fixed structure, which is offset relative to the main axis of the actuator, allows the absorption by this connection of most of the force transmitted from the movable structure to the fixed structure via the actuator. Thus, it is possible to avoid oversizing the structure of the actuator and, therefore, avoid an increase in the weight and the cost of the actuator. In addition, this solution makes it possible to standardize the use of more applications of the same actuator and, therefore, promote the concept of a product family.

[0024] Furthermore, the offset of the axis of the third connection relative to the axis of the actuator facilitates the integration of the third connection.

[0025] Furthermore, the invention allows facilitating assembly and disassembly of the actuator, unlike the known prior art where the actuator passes through an opening.

[0026] The main axis may be defined by a straight line connecting the first connection portion and the second connection portion.

[0027] It will be appreciated that the third connection forms a system for limiting the radial displacement of the actuator relative to its main axis.

[0028] Preferably, the third connection allows radial displacement of the actuator relative to an axis of the third connection.

[0029] The predetermined displacement advantageously corresponds to a radial displacement of the actuator relative to the axis of the third connection over a maximum distance corresponding to 25% of the outer diameter of the actuator.

[0030] It can be understood that the axis of the third connecting portion is fixed relative to the fixed structure.

[0031] According to another feature of the invention, the third connection comprises complementary connection elements between the actuator and the fixed structure.

[0032] According to one embodiment, the complementary connecting elements are configured to allow a predetermined displacement.

[0033] According to one embodiment, the complementary connecting element of the fixing structure is carried by the deflection device or a support structure for the deflection device.

[0034] In this last embodiment, the deflection device is fixed relative to a fixed structure, such as a fixed cascade vane.

[0035] In case of a fixed deflection device, a rear frame structure of the deflection device preferably serves as a support structure for the complementary connecting elements of the fixed structure.

[0036] According to a variant, the complementary connection element of the fixing structure is carried by an external structure of the fixing structure.

[0037] In this last variant, the deflection device is movable relative to a fixed structure, for example a movable cascade vane.

[0038] The outer structure carrying the complementary connecting elements of the fixing structure may preferably be a fan casing of the outer structure.

[0039] Alternatively, the outer structure carrying the complementary connecting element of the fixing structure may be a deflected edge of the outer structure.

[0040] According to one embodiment of the invention, the complementary connecting element comprises a pin and an opening, the pin being at least partially received in the opening.

[0041] The pins may be integrated or attached to corresponding complementary elements.

[0042] The connection formed by the pin and the opening allows limited mobility of the actuator relative to the fixed structure, thereby allowing a predetermined displacement.

[0043] In other words, the pin and the opening form between them a multi-directional radial stop which limits radial displacement of the actuator relative to its main axis. Thus, radial displacement relative to the main axis can be restored regardless of direction, thereby limiting the buckling of the actuator. The pin can be oriented parallel to the main axis of the actuator.

[0044] Advantageously, the pin can be oriented downstream or upstream of the reverser.

[0045] The predetermined displacement then corresponds to a radial displacement of the actuator relative to the axis of the third connection, the main axis being displaceable in parallel or non-parallel relative to the axis of the third connection.

[0046] In a first variant, the complementary connection element of the fixing structure comprises an opening and the complementary connection element of the actuator comprises a pin.

[0047] In this first variant, the axis of the third connection portion passes through the center of the opening.

[0048] In a second variant, the complementary connection element of the fixing structure comprises a pin and the complementary connection element of the actuator comprises an opening.

[0049] In this second variant, the axis of the third connection portion passes through the centre of the pin.

[0050] According to one embodiment, a radial gap is formed between the opening and the pin.

[0051] The radial clearance between the opening and the pin then corresponds to the predetermined displacement.

[0052] According to another embodiment, the hole and the pin are press-fitted.

[0053] A resilient damper may be positioned between the opening and the pin.

[0054] The elastic damper absorbs the mechanical stresses transmitted from the movable structure to the fixed structure.

[0055] In the case of a press fit, the elasticity of the damper allows a movement in the connection between the opening and the pin corresponding to a predetermined displacement.

[0056] In one embodiment of the invention, the axis of the opening and the axis of the pin are eccentric with respect to each other.

[0057] The eccentric axis of the opening and of the pin advantageously makes it possible to limit a predetermined displacement in a given direction.

[0058] According to one feature of the invention, the actuator comprises a body and a rod, the rod being guided by the body, the complementary connecting element of the actuator being carried by the body of the actuator.

[0059] The outer diameter of the actuator is determined by the cylinder.

[0060] Advantageously, the complementary connecting element of the actuator is carried at the end of the body of the actuator from which the rod extends.

[0061] According to one embodiment of the invention, the fixing structure and the complementary connecting element of the actuator respectively comprise flat surfaces spaced apart from each other by an axial gap.

[0062] The axial play makes it possible to avoid the transmission of axial forces from the movable structure to the fixed structure via the third connection of the actuator. According to one embodiment, the flat surfaces of the fixed structure and the actuator comprise openings and pins.

[0063] According to one embodiment of the invention, the flat surface of the complementary connecting element of the actuator is formed by a protrusion protruding from the body of the actuator.

[0064] According to one embodiment of the invention, the flat surface of the complementary connection element of the fixing structure is formed by a radial wall. The projection and the radial wall together carry the opening and the pin.

[0065] According to one embodiment of the invention, the flat surface of the complementary connection element of the actuator is formed by two protrusions extending from the body of the actuator, and the flat surface of the complementary connection element of the fixing structure is formed by two projections corresponding to said protrusions.

[0066] Advantageously, each protrusion and its complementary projection are provided with an opening and a pin.

[0067] Advantageously, the two projections of the radial wall delimit between them a hollow of circular shape.

[0068] The hollow circular shape allows at least a portion of the actuator to be integrated with a complementary connection element of the fixed structure. Such integration allows reducing the size of the thrust reverser, thereby reducing the drag and mass of the reverser.

[0069] The complementary connecting element of the fixing structure can advantageously be integrated into the fixing structure.

[0070] Advantageously, the complementary connection elements of the fixing structure are formed by angle irons.

[0071] The invention also relates to an aircraft nacelle comprising such a thrust reverser.

[0072] The term "radial" is to be understood as referring to a radial direction relative to the longitudinal axis of the nacelle.

[0073] The term "axial" is to be understood as referring to an axial direction along the longitudinal direction of the nacelle. BRIEF DESCRIPTION OF THE DRAWINGS

[0074] Other characteristics and advantages of the invention will emerge on reading the following non-limiting description and the accompanying drawings which schematically show several embodiments of a thrust reverser and its actuation system according to the invention.

[0075] Figure 1 A schematic cross-sectional view of a reverser known from the prior art is shown.

[0076] Figure 2a A portion of the rear frame structure is shown.

[0077] Figure 2b The embodiment shown in more detail is equipped with an actuator Figure 2a The rear frame structure described in .

[0078] Figure 3 An embodiment of the invention is shown applied to a fixed deflection device.

[0079] Figure 4 An embodiment of the invention applied to a movable deflection device is shown.

[0080] Figure 5a Show Figure 3 Detailed upstream stereogram of an alternative variant.

[0081] Figure 5b Shows Figure 5a Detailed downstream perspective view of an embodiment of the invention.

[0082] Figure 5c Shows Figure 5a Detailed downstream main view of an embodiment.

[0083] Figure 5d Shows Figure 5a An enlarged view of the third connection portion P3 is shown in FIG.

[0084] Figure 6 Shows Figure 5d A variation of the third connection portion shown in .

[0085] Figure 7a The arrangement of the invention is shown applied to a so-called fixed deflection device.

[0086] Figure 7b A further arrangement of the invention is shown applied to a so-called fixed deflection device.

[0087] Figure 7c A further arrangement of the invention is shown applied to a so-called fixed deflection device.

[0088] Figure 7d A further arrangement of the invention is shown applied to a so-called fixed deflection device.

[0089] Figure 8a The arrangement of the invention is shown applied to a so-called movable deflection device.

[0090] Figure 8b A further arrangement of the invention is shown applied to a so-called movable deflection device.

[0091] Figure 8c A further arrangement of the invention is shown applied to a so-called movable deflection device.

[0092] Figure 8d A further arrangement of the invention is shown applied to a so-called movable deflection device.

[0093] Fig. 9 Show Figure 3 An alternative embodiment of .

[0094] Fig.10 Show Figure 4 An alternative embodiment of .

[0095] In all drawings, the same or similar reference numerals denote the same or similar components or groups of components. DETAILED DESCRIPTION

[0096] The words “upstream” and “forward” may be used interchangeably to refer to upstream of the thrust reverser, and the words “downstream” and “aft” may be used interchangeably to refer to downstream of the thrust reverser.

[0097] The words "upstream" and "downstream" refer to the direction of airflow entering and leaving the nacelle.

[0098] Typically, the nacelle is used to form a tubular casing of a bypass turbojet engine and to guide the airflow generated by its fan blades, i.e., the hot airflow passing through the combustion chamber (called the primary flow channel) and the cold airflow circulating outside the turbojet engine (called the secondary flow channel).

[0099] The nacelle comprises an upstream section forming an air inlet, a middle section surrounding the fan of the turbojet engine, and a downstream section 1 extending the middle section and surrounding the turbojet engine. Figure 1 A part of a downstream section 1 of a nacelle known from the prior art is shown in FIG.

[0100] The downstream section 1 comprises a nacelle thrust reverser, here shown in a reverse jet configuration. The downstream section 1 comprises a fixed structure 10 and a movable structure 11 .

[0101] The movable structure 11 comprises a movable cowl 13, a reversing flap 14. The air flow deflection device 15 shown comprises an assembly of cascade vanes 15 fixed relative to the fixed structure 10. The movable structure 11 ends in an exhaust nozzle segment 16.

[0102] The fixed structure 10 comprises an outer structure 10a of the engine cowling and an inner structure 10b which, together with the outer structure 10a and the movable cowl, defines a flow path 20 for the circulation of a flow of cold air or secondary air in the case of a turbojet nacelle, as indicated by arrows F. The outer structure 10a also comprises a front frame structure 17 and a rear frame structure 18 providing support to the fixed structure 10 of the thrust reverser for the deflection device 15. The front frame structure 17 and the rear frame structure 18 are each attached to the outer structure 10a of the fixed structure 10.

[0103] The movable cowl 13 is intended to be actuated in the longitudinal direction of the nacelle between two extreme positions, namely a closed position, called direct jet position, in which the movable cowl 13 is in contact with the external structure 10 a and in which the reversing flaps 14 are retracted to ensure aerodynamic continuity of the external line of the downstream section 1 , thus allowing the secondary flow F to circulate in the flow channel 20 ; and Figure 1 The open position represented in FIG. 1 is called the reverse jet position, in which the passage in the nacelle is opened, the flow channel 20 is blocked using the deployed reverse flaps 14 , and the deflection device 15 is exposed.

[0104] The reverse jet position of the movable cowl allows the secondary flow F of the turbojet engine to escape at least partially, this part of the flow, called the steering flow, as indicated by the arrow F1, and be redirected towards the front of the nacelle by means of the cascade vanes 15, thus generating reverse thrust capable of assisting the braking of the aircraft.

[0105] The deployment of the mobile structure 11 is performed by a set of actuators 2, here schematically represented by the main axis A1 of the actuator 2, which drives the longitudinal displacement of the mobile structure 11 guided relative to the fixed structure 10 through the intermediary of a rail / slide system (not shown). The actuators 2 thus ensure the management of the thrust reversal by controlling the mobile structure 11 including the mobile cowling 13.

[0106] On the one hand, each actuator 2 is connected by a first connection P1 fixed to the fixed structure 10, here the front frame structure 17. On the other hand, each actuator 2 is connected by a second connection P2 fixed to the movable structure 11.

[0107] exist Figure 1 In the illustrated construction, the actuator 2 passes through an opening formed in the rear frame structure 18 .

[0108] exist Figure 2a and 2b This construction is shown in more detail in .

[0109] Figure 2aIt is partially shown that the rear frame structure 18 is in the shape of a circular ring, in which an opening 180 is formed, and the actuator 2 passes through the rear frame structure 18 through the opening 180 .

[0110] Figure 2b The rear frame structure 18 is shown in more detail and includes an axial wall 18a and a radial wall 18b connected together. An opening 180 is formed in the radial wall 18b of the rear frame structure 18.

[0111] Figure 2b It is also shown that the actuator 2 is mounted through the opening 180 of the rear frame structure 18. The actuator 2 comprises a hollow body 20, inside which is housed a movable translation rod 21. The hollow body 20 is connected at its upstream end to the front frame structure 17 by a first connection P1, while the rod 21 is connected at its free downstream end by a second connection P2 to the movable structure 11. The rod 21 thus passes through the rear frame structure 18 in order to be fixed to the movable structure 11.

[0112] If this solution is able to limit the buckling of the actuator 2, it has the disadvantage of a complex integration with the fixed structure 10, more particularly with its rear frame structure 18. In the construction of particularly fine aerodynamic lines, this rear frame solution is not feasible considering its dimensions.

[0113] In addition, by Figure 3 and 4 The invention, shown in the embodiment in FIG. , also makes it possible to simplify the integration of the actuator 2 into the fixed structure 10 , while limiting the risks of the actuator 2 buckling.

[0114] Figure 3 An embodiment of the invention is shown, applied to a thrust reverser 1 with fixed deflection means, for example fixed cascade blades. Figure 3 The illustration of the embodiment has been simplified to better describe the invention. In this case, the outer fixed structure 10a has been partially shown, including the fan housing 19 and the rear frame structure 18 terminating in the deflection edge 19a. The body 20 of the actuator 2 is connected to the fixed structure 10 by a first connection P1, while the rod 21 is connected to the movable structure 11 by a second connection P2. The actuator 2 extends along a main axis A1 coaxial with the hollow body 20 and the rod 21.

[0115] In addition to the first connection portion P1 and the second connection portion P2, a third connection portion P3 is provided between the actuator 2 and the fixed structure 10. The third connection portion P3 is longitudinally arranged between the first connection portion P1 and the second connection portion P2.

[0116] As shown, the axis A3 of the third connection P3 is radially off-center relative to the main axis A1 . The axis A3 of the third connection P3 is chosen to be a fixed axis relative to the fixed structure 10 .

[0117] The third connection P3 is arranged to allow a predetermined displacement of the actuator 2 in a radial direction relative to the axis A3 relative to the fixed structure 10. This predetermined displacement makes it possible to limit the amplitude of movement of the actuator 2 when it is subjected to a buckling phenomenon.

[0118] Therefore, the third connection P3 is arranged to allow radial movement of the main axis A1 of the actuator 2 and of the actuator 2 relative to the axis of the third connection A3.

[0119] As shown, the third connection P3 comprises complementary connection elements 4 , 5 between the actuator 2 and the fixed structure 10 to ensure a predetermined displacement.

[0120] The complementary connection element 4, 5 comprises an opening 40 and a pin 50, the pin 50 being at least partially housed in the opening 40. The connection formed by the pin 50 and the opening 40 allows a limited movement of the actuator 2 relative to the fixed structure 10, thereby allowing a predetermined displacement. In other words, the displacement of the actuator 2 is limited radially relative to the axis of the third connection part A3.

[0121] exist Figure 3 In the case shown, the complementary connection element 4 of the fixed structure 10 is carried by a support structure to which the deflection device 15 is fixed, here the rear frame structure 18 , and the complementary connection element 5 of the actuator 2 is carried by the body 20 of the actuator 2 .

[0122] The complementary connection element 4 of the fixing structure 10 is formed by an angle iron from which a pin 50 extends, and the complementary connection element 5 of the actuator 2 is formed by a projection of the body 20 comprising an opening 40 .

[0123] Figure 4 An embodiment of the invention is shown which is applied to a thrust reverser 1 whose deflection means are movable, for example movable cascade vanes. Figure 4 The illustrations of the embodiments are also simplified to better represent the present invention.

[0124] exist Figure 4 In the application case of the invention, the deflection device 15 is a cascade blade 15 which is movable relative to the fixed structure 10. The cascade blade is carried by the movable structure 11. The frame structure 18 is then fixed relative to the movable structure 11 and can completely carry the deflection device 15.

[0125] Figure 4 The complementary connecting elements 4, 5 shown in Figure 3 The same as in.

[0126] and Figure 3 The situation shown is different. Figure 4In the case shown, the complementary connection element 4 of the fixed structure 10 is carried by the outer structure 10 a , here a deflected edge 19 a of the fixed structure 10 or alternatively a fan housing 19 .

[0127] In the remainder of the description, the third connection P3 will be described in more detail as it applies to the case of a thrust reverser 10 with fixed blade cascades. Figure 3 as shown in .

[0128] Of course, the features described below are also applicable to a thrust reverser 10 with movable cascades.

[0129] exist Figure 5a In the figure, it is shown in detail Figure 3 An upstream view of an embodiment similar to the embodiment shown. Figure 3 Unlike the embodiment of the embodiment of FIG. 4 , the complementary connection element 4 of the fixing structure 10 comprises a pin 50 and the complementary connection element 5 of the actuator 2 comprises an opening 40 .

[0130] The complementary connecting element 4 of the fixing structure 10 or angle iron 4 comprises an axial wall 41 extended by a radial wall 42. The axial wall 41 is fixedly mounted on the rear frame structure 18, for example by welding.

[0131] The complementary connection element of the actuator 2 or the projection takes the form of a lug 5 .

[0132] The radial wall 42 and the lug 5 respectively comprise planes 42', 5' spaced apart from each other by an axial gap 9. Such an axial gap makes it possible to avoid the transmission of axial forces from the movable structure 11 to the fixed structure 10 via the third connection P3 of the actuator 2. These planes 42', 5' carry the opening 40 and the pin 50. More specifically, the plane 42' of the complementary connection element 4 of the fixed structure 10 carries the pin 50 and the plane 5' of the complementary connection element 5 of the actuator 2 carries the opening 40.

[0133] Figure 5b and 5c Shows Figure 5a Different views of an embodiment of the present invention. Figure 5b A second fixed connection P2 between the rod 21 of the actuator 2 and the movable structure 11 is also shown.

[0134] Figure 5b and 5cThe flat surface 5' of the complementary connection element 5 of the actuator 2 is shown together to include two protrusions 5 in the form of lugs, which extend from the body 20 of the actuator 2. These protrusions 5 can be spaced apart from each other at an angle of less than 180 °. The flat surface 42' of the complementary connection element 4 of the fixed structure 10 is formed by two protrusions 4 corresponding to the protrusions 5. The two protrusions 4 of the radial wall 42 define a hollow circle 43 between them, which allows a simplified integration of at least a part of the actuator with the complementary connection element of the fixed structure. This integration allows reducing the size of the thrust reverser, thereby reducing the resistance and mass of the reverser. Similar to the above, each protrusion 5 and its complementary protrusion 4 are provided with an opening 40 and a pin 50.

[0135] Figure 5d Show Figure 5a An enlarged view of the third connection P3 is shown, in which the radial gap 7 formed between the opening 40 and the pin 50 is shown. The gap between the opening and the pin then corresponds to the predetermined displacement.

[0136] exist Figure 6 In the variant shown, the opening 40 and the pin 50 are press-fitted.

[0137] In each case, an elastic damper 8 may be provided between the opening 40 and the pin 50 to allow absorption of mechanical stresses transmitted from the movable structure 11 to the fixed structure 10. Here, the damper is formed by an elastic ring housed in the opening 40 and surrounding the pin 50.

[0138] The elastic damper 8 may be connected or integrated into the opening 40 or the pin 50. The damper 8 may be provided, ensuring a press fit between the opening 40 and the pin 50.

[0139] Figures 7a to 7d Different arrangements of the third connection portion P3 used in the present invention for fixing the deflection device 15 are shown.

[0140] exist Figure 7a In the figure, two projections 5 in the form of lugs are shown extending from the body 20 of the actuator 2, each comprising an opening 40 for receiving a pin 50 extending from an angle iron 4 fixed to the rear frame 18. This structure advantageously makes it possible to limit the circumferential displacement of the actuator 2 relative to the axis of the third connection A3 and ensures better absorption of forces in the event of buckling.

[0141] exist Figure 7b In the figure, a single protrusion 5 in the form of a lug is shown, extending from the body 20 of the actuator 2 and comprising an opening 40 which receives a pin 50 protruding from an angle iron 4 fixed to the rear frame 18. This configuration advantageously makes it possible to reduce the mass of the elements forming the third connection part P3 and facilitates assembly and disassembly of the actuator 2.

[0142] exist Figure 7c In FIG. 1 , an opening 40 a is formed on an angle iron 4 a fixed to the rear frame 18 , and a pin 50 a extends from a linear protrusion 5 a fixed to the body 20 of the actuator 2 .

[0143] In the aforementioned embodiment applied to the fixed deflection device 15, the opening 40 and the pin 50 have complementary circular shapes. Figure 7d In the embodiment shown, unlike the previously shown configuration, the opening 40b and the pin 50b have a complementary rectangular shape. This rectangular shape allows for better absorption of forces in the event of flexion.

[0144] Figures 8a to 8d Different arrangements of the third connection portion P3 of the invention applied to the movable deflection device 15 are shown.

[0145] exist Figure 8a In the figure, two protrusions 5 in the form of lugs are shown extending from the body 20 of the actuator 2, each of which comprises an opening 40 receiving a pin 50 extending from an angle 4 fixed to an external structure 10a, for example a deflection edge 19a of the fixed structure 10, or alternatively the fan casing 19. This configuration also makes it possible to limit the circumferential displacements of the actuator 2 relative to the axis of the third connection A3 and ensure better restoring forces in the event of buckling.

[0146] exist Figure 8b In the embodiment of the present invention, a single protrusion 5 in the form of a lug is shown, which extends from the body 20 of the actuator 2 and includes an opening 40 that receives a pin 50 protruding from an angle iron 4 fixed to the external structure 10a. This configuration also makes it possible to reduce the mass of the elements forming the third connection part P3 and facilitates the assembly and disassembly of the actuator 2.

[0147] exist Figure 8c In FIG. 1 , an opening 40 a is formed on an iron 4 a fixed to an external structure 10 a , and a pin 50 a extends from a linear protrusion 5 a fixed to a main body 20 of the actuator 2 .

[0148] In the aforementioned embodiment applied to the movable deflection device 15 , the opening 40 and the pin 50 have complementary circular shapes.

[0149] exist Figure 8d In the embodiment shown, unlike the previously shown configuration, the opening 40b and the pin 50b have a complementary rectangular shape. This rectangular shape allows for better absorption of forces in the event of flexion.

[0150] Of course, in the aforementioned different embodiments, the arrangement of the opening and the pin of the third connecting portion may be reversed.

[0151] For example, Fig. 9 It is shown in Figure 3 , in which the complementary connection element 5 of the actuator 2 comprises a pin 50 and the complementary connection element 4 of the fixing structure 10 , here the rear frame 18 , comprises an opening 40 .

[0152] In another example, in Fig.10 It is shown in Figure 4 , in which the complementary connection element 5 of the actuator 2 comprises a pin 50 and the complementary connection element 4 of the fixing structure 10 , here the complementary connection element 4 is an outer structure 10 a , for example a deflected edge 19 a of the fixing structure 10 , comprises an opening 40 .

[0153] Of course, the examples of embodiment described above are by no means limiting and other modifications and details may be made to the nacelle according to the invention, however, without departing from the scope of the invention, for example other forms of deflection means may be possible.

[0154] Provision may be made for the actuator 2 to be a simple linear actuator, which may be electrically, hydraulically or pneumatically actuated. Alternatively, the actuator 2 may be attached to the fixed structure 10 between the two longitudinal connection lines in the deflection device 15 .

Claims

1. A thrust reverser (1) for a turbojet aircraft nacelle, comprising: - fixed structure (10), - movable structure (11), - an actuator (2), The actuator extends along a main axis (A1) and is connected to the fixed structure (10) by a first connection (P1) and to the movable structure (11) by a second connection (P2) for deploying the movable structure (11) between a direct injection position and a reverse injection position, The actuator (2) is also connected to the fixed structure (10) via a third connection (P3), the third connection (P3) being arranged longitudinally between the first connection (P1) and the second connection (P2), It is characterized in that The axis (A3) of the third connection portion (P3) is radially eccentric from the main axis (A1), and the third connection portion (P3) allows a predetermined displacement of the actuator (2) relative to the fixed structure (10), wherein the third connection (P3) comprises complementary connection elements (4, 5) between the actuator (2) and the fixed structure (10), wherein the fixing structure (10) and the complementary connecting elements (4, 5) of the actuator (2) respectively comprise flat surfaces (42', 5'), the flat surfaces (42', 5') being spaced apart from each other by an axial gap (9), wherein the flat surface (5') of the complementary connecting element (5) of the actuator (2) is formed by a protrusion (5) of the body (20) of the actuator (2), or The flat surface (5') of the complementary connection element (5) of the actuator (2) is formed by two protrusions (5) extending from the body (20) of the actuator (2), and the flat surface (42') of the complementary connection element (4) of the fixing structure (10) is formed by two protrusions (4) corresponding to the protrusions (5).

2. The thrust reverser (1) according to claim 1, characterized in that: The complementary connecting element (4, 5) comprises a pin (50) and an opening (40), the pin (50) being at least partially received in the opening (40).

3. The thrust reverser (1) according to claim 2, characterized in that: A radial gap (7) is formed between the opening (40) and the pin (50).

4. The thrust reverser (1) according to claim 2 or 3, characterized in that: The opening (40) and the pin (50) are press-fitted.

5. The thrust reverser (1) according to claim 2 or 3, characterized in that: An elastic damper (8) is positioned between the opening (40) and the pin (50).

6. The thrust reverser (1) according to claim 2 or 3, characterized in that: The direction of the pin (50) is parallel to the main axis (A1) of the actuator (2).

7. The thrust reverser (1) according to any one of claims 1 to 3, characterized in that: The complementary connection element (4) of the fixed structure (10) is carried by the deflection device (15) or a support structure of the deflection device.

8. The thrust reverser (1) according to any one of claims 1 to 3, characterized in that The complementary connection element (4) of the fixing structure (10) is carried by an outer structure (10a) of the fixing structure (10).

9. The thrust reverser (1) according to any one of claims 1 to 3, characterized in that: The actuator (2) comprises the body (20) and a rod (21), the rod (21) being guided by the body (20), the complementary connecting element (5) of the actuator (2) being carried by the body (20) of the actuator (2).

10. The thrust reverser (1) according to claim 1, characterized in that The flat surface (42') of the complementary connection element (4) of the fixing structure (10) is formed by a radial wall (42).

11. The thrust reverser (1) according to claim 9, characterized in that The body (20) of the actuator (2) is connected to the fixed structure (10) via the first connection (P1), while the rod (21) is connected to the movable structure (11) via the second connection (P2).

12. The thrust reverser (1) according to claim 1, characterized in that The third connection portion (P3) is configured to allow the actuator (2) to perform a predetermined displacement relative to the fixed structure (10) in a radial direction relative to the axis (A3), wherein the predetermined displacement enables the movement amplitude of the actuator (2) to be limited when the actuator (2) is subjected to a buckling phenomenon.

13. The thrust reverser (1) according to claim 1, characterized in that The reverse injection position allows the secondary flow (F) to escape at least partially.

14. A nacelle for an aircraft, comprising a thrust reverser (1) according to any one of claims 1 to 13.

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