A thrust reverser including a pivoting half-module and a connecting beam for the half-module located at the six o'clock position

Abstract

The present invention relates to a thrust reverser for a propulsion unit, the thrust reverser comprising a movable cascade, two half-components forming part of a secondary flow, and a connecting beam (60) located at the six o'clock position, the connecting beam being intended to be mounted in a cantilever manner relative to the fan casing. The half-components are articulated at the twelve o'clock position so as to be able to perform a "butterfly" movement between a flight configuration and a maintenance configuration. The connecting beam (60) comprises a connecting member (70) configured to cooperate with the half-components in the form of a tenon and mortise connection when the half-components are in the flight configuration. The thrust reverser further comprises locking members (91, 92) downstream of the connecting member (70), the locking members being able to lock the half-components in the flight configuration.

Description

Technical Field

[0001] The present invention relates to the field of thrust reversers for aircraft propulsion units and more particularly to thrust reversers having a “D” shaped structure such as that described in document FR 3 074 853 A1.

[0002] The invention is of particular interest when the thrust reverser comprises movable cascade blades. Background Art

[0003] In a manner known per se, the thrust reverser of D-shaped structure comprises two half-assemblies articulated on beams extending on either side of the strut of the propulsion unit in order to be able to open or close them, i.e. to switch them from the flight configuration to the maintenance configuration and vice versa.

[0004] Document FR 3 074 853 A1 discloses a thrust reverser of this type, which also comprises an assembly box with locking means for locking the half assemblies in the flight configuration.

[0005] During the opening / closing of the half assemblies, each half assembly is placed to bear on a corresponding surface of the assembly box and then locked in this position independently of the other half assembly using the locking device. The half assemblies are then connected to each other using a locking piece.

[0006] Each half assembly is therefore locked with the assembly box on the one hand and with the other half assembly on the other hand, thus forming a hyperstatic assembly.

[0007] Furthermore, the locking device described in the aforementioned document complicates the process for locking the half-assemblies and is not very robust. Summary of the invention

[0008] The present invention aims to provide a thrust reverser with cascades making it possible to simplify and improve the positioning and locking of the half assemblies in the flight configuration.

[0009] The present invention is also directed to a thrust reverser having an architecture that enables the cascades to move when the thrust reverser switches from a direct thrust configuration to a reverse thrust configuration.

[0010] To this end, the object of the present invention is a thrust reverser for an aircraft propulsion unit, the thrust reverser comprising two half-assemblies, each half-assembly comprising a movable fairing and a fixed structure, the fixed structure comprising a first connecting element and a second connecting element, the connecting beam comprising a connecting member. For each half-assembly:

[0011] - The first connecting element is configured to hinge the half-module on the fixed part of the propulsion unit so as to enable the half-module to move between a flight configuration and a maintenance configuration, in which flight configuration the second connecting element cooperates with the connecting member, and in which maintenance configuration the second connecting element is separated from the connecting member.

[0012] - In the flight configuration, the movable fairing is able to translate relative to the fixed structure along the longitudinal central axis between a direct thrust position and a reverse thrust position, in which direct thrust position the fixed structure and the movable fairing radially delimit a corresponding part of the duct therebetween to direct a fluid flow towards the rear of the propulsion unit to generate thrust, and in which reverse thrust position the movable fairing exposes a space for receiving the cascade such that a part of the fluid flowing in the duct can pass through the cascade while being deflected thereby to generate reverse thrust.

[0013] According to the invention, one of the connecting member and the second connecting element of each half-module includes a groove, and the other includes a tenon, which tenon is configured to fit into the groove when the half-module moves from the maintenance configuration to the flight configuration to position each half-module in the flight configuration, and the reverse thrust device includes one or more locking members, which one or more locking members are configured to be connected together and lock the half-module in the flight configuration.

[0014] Such a groove and such a tenon enable precise and robust embedding while ensuring a compact connection, which compact connection reduces the volume of the components in the flight configuration.

[0015] In addition, such embedding does not require locking each half-module independently to the connecting beam, which simplifies the locking process and enables the use of only conventional locking members.

[0016] The architecture of the reverse thrust device is compatible with the use of a movable cascade, which movable cascade can be connected to the connecting beam according to a sliding connection element for example.

[0017] The connecting beam enables the transfer of forces from the half-module to the fixed part of the propulsion unit, and the connecting beam can be fastened to the fixed part.

[0018] Furthermore, such an architecture enables providing a passage for accessories.

[0019] In one embodiment, when the half-module is in the flight configuration, the second connecting element of each half-module forms a half-cavity that encloses a corresponding half-part of the connecting member.

[0020] In one embodiment, the connecting beam extends along the axis around which the groove extends.

[0021] According to a first variant, the recess is formed by a connecting member, and each second connecting element of the half-module includes a corresponding tenon, which is configured to be received in a corresponding part of the recess when the half-module is in the flight configuration.

[0022] According to a second variant, the connecting member forms the tenon, and each second connecting element of the half-module includes a corresponding recess, which is configured to receive a corresponding part of the tenon when the half-module is in the flight configuration.

[0023] These variants can be combined. For example, the connecting member may include a first recess and a first tenon, and each second connecting element of the half-module may include, on the one hand, a second tenon and, on the other hand, a second recess, the second tenon being configured to be received in a corresponding part of the first recess when the half-module is in the flight configuration, the second recess being configured to receive a corresponding part of the first tenon when the half-module is in the flight configuration.

[0024] In one embodiment, one of the locking members is an internal locking member and the other of the locking members is an external locking member.

[0025] Preferably, the internal locking member can be connected to the fixed structure of one half-module and is configured to cooperate with a first hook element fixed to the fixed structure of the other half-module, the hook element extending radially between the longitudinal central axis and the axis along which the connecting beam extends.

[0026] Preferably, the external locking member can be connected to the fixed structure of one half-module and is configured to cooperate with a second hook element fixed to the fixed structure of the other half-module, the axis along which the connecting beam extends extending radially between the second hook element and the longitudinal central axis.

[0027] In one embodiment, the connecting beam includes a first track, and the fixed structure of each half-module includes a second track, the cascade being movable between a first position and a second position and being configured to cooperate with the first track at least on a first part of the movement performed between the first position and the second position and with the second track at least on a second part of the movement.

[0028] Preferably, the first connecting element of each half-module is located on one side of the longitudinal intermediate plane passing through the longitudinal central axis, wherein the connecting beam is located on the other side of the longitudinal intermediate plane.

[0029] The invention also relates to a nacelle for an aircraft propulsion unit, the nacelle comprising a reverse thrust device as defined above.

[0030] The invention also relates to an aircraft propulsion unit comprising such a nacelle.

[0031] In one embodiment, the propulsion unit includes a fan casing, and a connecting beam extends axially in a manner suspended relative to the fan casing.

[0032] Finally, the object of the present invention is an aircraft including such a propulsion unit.

[0033] According to another aspect, the object of the present invention is a method for placing the half-components of the above reverse thrust device in a flight configuration.

[0034] The method includes the step of inserting the tenon into the groove.

[0035] Preferably, after the insertion step, the method includes a locking step in which the half-components are connected to each other by the locking member.

[0036] Other advantages and features of the present invention will become apparent upon reading the following detailed and non-limiting description. Description of the Drawings

[0037] The following detailed description refers to the accompanying drawings, in which:

[0038] Figure 1 is a schematic longitudinal sectional view of an aircraft propulsion unit including a turbofan engine;

[0039] Figure 2 is Figure 1 a schematic perspective view of the propulsion unit of

[0040] Figure 3 is a schematic perspective view of a half-component of a reverse thrust device having a D-shaped structure;

[0041] Figure 4 is Figure 1 a schematic perspective view of the propulsion unit of

[0042] Figure 5 is a schematic perspective view of the propulsion unit of Figure 1 in a maintenance configuration;

[0043] Figure 6 is a schematic perspective view of the propulsion unit of Figure 1 in a reverse thrust configuration;

[0044] Figure 7 is Figure 1 a schematic perspective view of a part of the propulsion unit of

[0045] Figure 8 is Figure 7 a schematic exploded perspective view of the connecting beam of​​​​​​​​

[0046] [ Figure 9 ] is in flight configuration Figure 8 Schematic diagram of beams, which are connected to each other in this flight configuration;

[0047] [ Figure 10 ] is in flight configuration Figure 8 A schematic diagram of a half assembly and a portion of a connecting beam;

[0048] [ Figure 11 ] is in flight configuration Figure 8 A schematic diagram of a half assembly and a portion of a connecting beam;

[0049] [ Figure 12 ] is a schematic diagram of a locking member according to a first embodiment, the locking member is intended to lock Figure 8 two half assemblies of the present invention, wherein the locking member is in a locked position;

[0050] [ Figure 13 ]yes Figure 12 A schematic diagram of a locking member of the embodiment of the present invention, wherein the locking member is in an unlocked position;

[0051] [ Figure 14 ] is a schematic diagram of a locking member according to a second embodiment, the locking member is intended to lock Figure 8 two half assemblies of the present invention, wherein the locking member is in a locked position;

[0052] [ Figure 15 ]yes Figure 14 Schematic diagram of a locking member of the embodiment of the present invention, wherein the locking member is in an unlocked position. DETAILED DESCRIPTION

[0053] The drawings comprise relative reference frames X1 , X2 and X3 respectively defining a longitudinal (or axial) direction, a vertical direction and a lateral direction which are orthogonal to each other.

[0054] Figure 1 and Figure 2 A propulsion unit 1 is shown having a longitudinal centre axis A1 .

[0055] In the following, the terms “upstream”, “downstream”, “front” and “rear” are defined relative to the direction S1 of the air flow flowing through the propulsion unit 1 along the longitudinal centre axis A1 .

[0056] The propulsion unit 1 comprises a turbine engine 2 (in Figure 1 ), nacelle 3 and strut 4 (visible in Figure 2 ), which strut enables the propulsion unit 1 to be connected to the wing of the aircraft (not shown).

[0057] exist Figure 1In the example, the turbine engine 2 is a turbofan engine which includes, from upstream to downstream, a fan 5, a low-pressure compressor 6, a high-pressure compressor 7, a combustion chamber 8, a high-pressure turbine 9, and a low-pressure turbine 10. The compressors 6 and 7, the combustion chamber 8, and the turbines 9 and 10 form a gas generator.

[0058] The turbojet engine 2 includes a fan casing 11 connected to the gas generator by a structural arm 12.

[0059] The nacelle 3 includes: an upstream section 15 which forms an air inlet; an intermediate section 16 which includes a fan cowl enclosing the fan casing 11; and a downstream section 17 which forms an outlet for discharging the gases generated by the turbojet engine 2 downstream of the propulsion unit 1.

[0060] In a manner known per se, during the operation of the turbojet engine 2, an air flow 20 enters the propulsion unit 1 through the air inlet 15, passes through the fan 5, and then divides into a central main flow 20M and a secondary flow 20N. The main flow 20M flows in a main gas flow duct 21M within the gas generator. Further, the secondary flow 20N flows in a secondary duct 21N which surrounds the gas generator and is radially bounded externally by the fan casing 11 and the downstream section 17 of the nacelle 3.

[0061] Figure 3 and Figure 4 The downstream section 17 of the nacelle 3 is shown in more detail.

[0062] Referring Figure 4 , the downstream section 17 includes two half-components 25A and 25B which have a semi-cylindrical shape and are symmetric with respect to a longitudinal intermediate plane P1 passing through the longitudinal central axis A1 and parallel to the vertical direction X2. Thus, the half-components 25A and 25B extend laterally on both sides of the plane P1, particularly on both sides of the strut 4.

[0063] In the following description and some of the figures, reference numerals are used so as to be able to distinguish elements located on one side of the plane P1 and symmetric elements located on the other side of the plane. This distinction is achieved by adding a suffix "A" to these reference numerals to denote elements located on one side of the plane P1 and adding a suffix "B" to denote elements located on the other side. Generally, all symmetric elements are not shown in all the figures. Further, when a part of the propulsion unit 1 has two halves which are symmetric with respect to the plane P1, the following description in most cases only details one of these halves in detail. Unless otherwise stated, this specification applies by analogy to the other corresponding halves.

[0064] In particular, hereinafter referring Figure 3Describe the half-component 25A. Thus, the following description of the half-component 25A applies by analogy to the half-component 25B.

[0065] The half-component 25A includes two parts that are movable relative to each other. One of these parts forms a structure 30A herein referred to as the "fixed structure", which remains in the same position relative to the strut 4 in the flight configuration. The other part of the half-component 25A forms a fairing 31A that is movable relative to the fixed structure 30A (see further below).

[0066] The fixed structure 30A includes, on the one hand, an inner shroud portion 33A that radially inwardly delimits a circumferential sector of a longitudinal portion of the secondary duct 21N.

[0067] The inner shroud portion 33A, commonly referred to as the "inner fixed structure", includes, in Figure 3 a vertical direction from bottom to top, a lower joint wall 34A (also referred to as the "six o'clock piece", "island piece", or "bifurcation piece"), a semi-circular central wall 35A, and an upper joint wall 36A (also referred to as the "twelve o'clock piece", "island piece", or "bifurcation piece").

[0068] In addition, the fixed structure 30A includes a lower beam 37A fixed to the radial end of the lower joint wall 34A and an upper beam 38A fixed to the radial end of the upper joint wall 36A.

[0069] The upper beam 38A includes a first connecting element 41A capable of connecting the half-component 25A to the propulsion unit 1.

[0070] In this example, the first connecting element 41A includes eyelets that are configured to cooperate with an axis (not shown) connected to a beam (not shown) fixed to the strut 4, such that the half-component 25A can rotate and move about a rotation axis A2A passing through the center of the eyelets 41A.

[0071] Thus, the first connecting element 41A enables the half-component 25A to move between Figure 4 the flight configuration shown and Figure 5 the maintenance configuration shown.

[0072] In this example, the rotation axis A2A is substantially parallel to the longitudinal central axis A1. Generally, the axes A1 and A2A can form an angle between 0° and 3°.

[0073] As for the movable fairing 31A, the movable fairing extends radially outward from the central wall 35A of the fixed structure 30A and also has a semi-circular shape.

[0074] Thus, the central wall 35A of the fixed structure 30A and the movable fairing 31A radially delimit therebetween the circumferential sector of the longitudinal portion of the secondary duct 21N, which sector extends circumferentially about the longitudinal central axis A1 between the lower joining wall 34A and the upper joining wall 36A of the cowl portion 33A.

[0075] In this example, the fixed structure 30A includes a wall 45A which is connected to the central wall 35A and extends behind the central wall 35A so as to form Figure 4 half of the exhaust nozzle 46 visible in

[0076] In a manner known per se, the movable fairing 31A is connected to the lower beam 37A and the upper beam 38A of the fixed structure 30A according to a sliding connection.

[0077] In this example, such connection is achieved by sliders (not shown) fixed to the lower beam 37A and the upper beam 38A and tracks (not shown) fixed to the movable fairing 31A and cooperating with these sliders.

[0078] Figure 10 The sliding connection between the movable fairing 31A and the lower beam 37A is schematically shown.

[0079] Such sliding connection enables the movable fairing 31A to move translationally relative to the fixed structure 30A, for example using a cylinder (not shown), between Figure 1 , Figure 2 and Figure 4 the extended position shown in Figure 6 and the retracted position shown in

[0080] In the extended position, the front end of the movable fairing 31A is flush with the rear end of the fan cowl on the same side of the plane P1 as the movable fairing 31A, so as to reduce the discontinuity between these cowls and thus reduce the aerodynamic disturbances outside the nacelle 3.

[0081] In the retracted position, the front end of the movable fairing 31A and the rear end of the corresponding fan cowl of the intermediate section 16 are separated from each other by a distance Y1, which distance Y1 delimits a space forming a radial opening (see Figure 6 ).

[0082] In this example, the nacelle 3 includes cascades 50A and 50B extending respectively on one side and the other side of the plane P1.

[0083] When the movable fairing 31A is in the retracted position, the cascade 50A extends through the aforementioned radial opening.

[0084] In addition, with reference to Figure 3, the half-module 25A includes a flap 52A and a connecting rod 54A.

[0085] In a manner known per se, each flap 52A is hinged to the movable cowl 31A, and each connecting rod 54A is connected on the one hand to a respective one of the flaps 52A and on the other hand to the central wall 35A of the cowl portion 33A of the fixed structure 30A, such that when the movable cowl 31A switches from the extended position to the retracted position, the flaps 52A unfold radially in the secondary duct 21N to seal this duct 21N.

[0086] Thus, the downstream section 17 of the nacelle 3 forms a thrust reverser.

[0087] When the movable cowls 31A and 31B of each of the half-modules 25A and 25B are in the extended position (also referred to as the "direct thrust position"), the secondary flow 20N flows through the longitudinal portion of the secondary duct 21N defined by the downstream section 17 towards the rear of the propulsion unit 1. In this direct thrust configuration, the flaps 52A of the half-module 25A and the flaps (not shown) of the half-module 25B fold down against the inner wall of the corresponding movable cowl 31A or 31B. Thus, the secondary flow 20N contributes to the generation of thrust.

[0088] When the movable cowls 31A and 31B of each of the half-modules 25A and 25B are in the retracted position (also referred to as the "thrust reverse position"), the flaps 52A of the half-module 25A and the flaps of the half-module 25B seal the secondary duct 21N to redirect the secondary flow 20N towards the radial openings. Thus, the secondary flow 20N passes through the cascades 50A and 50B while being thereby turned towards the front of the propulsion unit 1. Thus, the secondary flow 20N enables the generation of reverse thrust.

[0089] Referring Figure 7 , the nacelle 3 includes a connecting beam 60 extending along the longitudinal axis A3.

[0090] In this example, the axis A3 is parallel to the longitudinal central axis A1 of the propulsion unit 1 and passes through the longitudinal intermediate plane P1.

[0091] Referring to the longitudinal intermediate plane P2 perpendicular to the plane P1 and passing through the longitudinal central axis A1, the connecting beam 60 is located on one side of the plane P2, opposite the strut 4 located on the other side of this plane P2.

[0092] In other words, the connecting beam 60 is located at the six o'clock position, while the strut 4 is located at the twelve o'clock position.

[0093] The connecting beam 60 is mounted on the intermediate section 16 to be fixed to the fan casing 11.

[0094] The connecting beam 60 includes a downstream portion that extends in a manner suspended relative to the rear end of the fan housing 11.

[0095] In Figure 7 the example, the intermediate section 16 includes inner shroud portions 62A and 62B on both sides of the longitudinal intermediate plane P1, and the inner shroud portions 62A and 62B have a shape similar to the inner shroud portion 33A described above with reference to Figure 3 description.

[0096] For each of the inner shroud portions 62A and 62B, Figure 7 a part of the inner shroud portion including the central wall 63A or 63B is shown.

[0097] The inner shroud portions 62A and 62B are respectively connected to the connecting beam 60 through lower joining walls 64A and 64B.

[0098] Of course, each of the inner shroud portions 62A and 62B includes an upper joining wall (not shown), so that the inner shroud portions 62A and 62B can be connected to a fixed part (not shown) of the propulsion unit 1.

[0099] Each of the inner shroud portions 62A and 62B has a groove 65A or 65B, and the groove 65A or 65B is configured to receive a part of the inner shroud portion 33A or 33B of the semi-assembly 25A or 25B in the flight configuration. The grooves 65A and 65B form an interface, enabling the aerodynamic continuity to be ensured between the inner shroud portion 62A and the inner shroud portion 33A on the one hand, and between the inner shroud portion 62B and the inner shroud portion (not shown) of the semi-assembly 25B on the other hand.

[0100] In this example, the cascades 50A and 50B can be translated longitudinally along the central axis A1.

[0101] For this purpose, each of the cascades 50A and 50B is connected to the fixed part of the propulsion unit at the 12 o'clock position according to a sliding connection on the one hand, and to the connecting beam 60 on the other hand.

[0102] In Figure 7 the embodiment, the sliders 66A and 66B are fastened to the lateral portions of the connecting beam 60, and the cascades 50A and 50B have tracks (not visible in Figure 7 ) that cooperate with the sliders 66A and 66B.

[0103] In Figure 7 , the cascades 50A and 50B are in the extended position.

[0104] In this example, the cascades 50A and 50B are translationally fixed to the movable cowls of the half - assemblies 25A and 25B along the longitudinal central axis A1, respectively, such that when these movable cowls are in the direct - thrust position, the cascades 50A and 50B are in the extended position, and when the movable cowls are in the thrust - reverse position, the cascades 50A and 50B are in the retracted position.

[0105] In this example, when the half - assemblies 25A and 25B are in the flight configuration, the movable cowls cooperate with the cascades 50A and 50B through a tenon - and - groove connection similar to the connection between the connecting member 70 and the second connecting elements of the half - assemblies 25A and 25B.

[0106] In the extended position, the cascades 50A and 50B are at least partially received in a space that extends radially between the fan housing 11 and the corresponding fan cowl of the intermediate section 16.

[0107] In the retracted position, the cascades 50A and 50B extend into a radial opening that extends longitudinally between the movable cowls of the half - assemblies 25A and 25B and the fan cowl of the intermediate section 16 (see above and Figure 6 ).

[0108] More specifically, the present invention relates to the cooperation of the half - assemblies 25A and 25B with the connecting beam 60.

[0109] The visible part of the connecting beam 60 in Figure 7 has an end that forms a connecting member 70 which, when the half - assemblies 25A and 25B are in the flight configuration, cooperates with the second connecting elements of the half - assemblies 25A and 25B.

[0110] Geometrically, the connecting member 70 extends between the following planes:

[0111] - between two transverse planes perpendicular to the longitudinal central axis A1,

[0112] - between two longitudinal planes parallel to the longitudinal intermediate plane P1 and extending on both sides of the longitudinal axis A3,

[0113] - between two longitudinal planes parallel to the longitudinal intermediate plane P2 and extending on both sides of the longitudinal axis A3.

[0114] Referring to Figure 8 , the connecting member 70 has two lateral vertices 71A and 71B, a lower base 72, and an upper base 73, which are configured such that a longitudinal plane parallel to the plane P2 can pass through the longitudinal axis A3 and the two lateral vertices 71A and 71B simultaneously, and such that the plane P1 passes through the lower base 72 and the upper base 73.

[0115] The connecting member 70 includes four branches 74 that respectively connect the upper base 73 and the lateral apex 71A to each other, connect the lateral apex 71A and the lower base 72 to each other, connect the lower base 72 and the lateral apex 71B to each other, and connect the lateral apex 71B and the upper base 73 to each other.

[0116] The branches 74 are inclined with respect to the longitudinal intermediate planes P1 and P2.

[0117] The connecting member 70 is symmetric with respect to the plane P1.

[0118] On both sides of the symmetry plane P1, the connecting member 70 has a C-shaped cross-section, and the lower base 72 and the upper base 73 form the free ends of the C-shape.

[0119] The connecting member 70 includes a groove 75 that extends circumferentially around the axis A3.

[0120] In this example, the groove 75 is formed on the four branches 74, on the lateral apices 71A and 71B, and on the lower base 72, and forms a unique continuous groove.

[0121] Figure 8 The lower beams 37A and 37B of the half-assemblies 25A and 25B are respectively shown, and the connecting beam 60 is shown in an exploded view.

[0122] Figure 8 The beam 37A of... includes an end that forms the second connecting element 80A of the half-assembly 25A.

[0123] The second connecting element 80A includes a wall 81A that has a shape complementary to a half of the connecting member 70 that extends on the same side of the plane P1 as the half-assembly 25A. Thus, the wall 81A also has a C-shaped-like shape.

[0124] As Figure 9 and Figure 10 shown, the wall 81A forms a half-cavity that is configured to enclose that half of the connecting member 70 when the half-assembly 25A is in the flight configuration.

[0125] The second connecting element 80A includes a tenon 82A that, in this example, extends on the wall 81A within the half-cavity formed by the wall 81A.

[0126] The tenon 82A is configured to be assembled into the groove 75 when the half-assembly 25A moves from the maintenance configuration to the flight configuration, more specifically into the half of the groove 75 that extends on the same side of the plane P1 as the half-assembly 25A, to position the fixed structure 30A of the half-assembly 25A with respect to the connecting member 70 and thus with respect to the connecting beam 60.

[0127] In this example, the recess 75 has a trapezoidal shape. More specifically, the recess 75 has a bottom surface and side surfaces that are inclined relative to the bottom surface such that the width of the recess 75 at the outer surface of the connecting member 70 to which it leads is greater than the width at the bottom surface.

[0128] The tenon 82A has a complementary shape and has a trapezoidal cross-section.

[0129] This geometry of the tenon 82A and the recess 75 enables an increase in positioning accuracy when the half-assemblies 25A approach the flight configuration, while facilitating the insertion of the tenon 82A into the recess 75, taking into particular account the clearances in the mechanism.

[0130] The foregoing description of the mating of the second connecting element 80A of the half-assembly 25A applies by analogy to the connecting element 80B of the half-assembly 25B.

[0131] From the foregoing, it can be concluded that when the half-assemblies 25A and 25B are in the maintenance configuration, these half-assemblies are separated from the connecting member 70, and when the half-assemblies 25A and 25B are in the flight configuration, these half-assemblies are connected to each other via the connecting member 70 with which they mate, so as to be correctly positioned relative to the beam 60.

[0132] In this example, in the flight configuration, the locking of the half-assemblies 25A and 25B is ensured by two locking members 91 and 92.

[0133] Referring Figure 9 and Figure 11 , the locking members 91 and 92 are mounted one behind the other downstream of the second connecting elements 80A and 80B, close to the connecting member 70.

[0134] Figure 12 and Figure 13 show the locking member 91 in the locked position and the unlocked position, respectively.

[0135] In this example, the locking member 91 includes a hook 95, an actuating handle 96, and a connecting rod 97 that connects the hook 95 and the handle 96 to each other.

[0136] The locking member 91 is configured such that when the half-assemblies 25A and 25B are in the flight configuration and the locking member 91 is in the locked position, the handle 96 is flush with the outer surfaces of the lower beams 37A and 37B of the half-assemblies 25A and 25B. This enables the handle 96 to be actuated manually while preventing the handle 96 from protruding relative to the outer surfaces of the lower beams 37A and 37B.

[0137] In this example, the locking member 91 is mounted on the lower beam 37B of the half-assembly 25B. When the locking member 91 is in the locked position, the hook 95 cooperates with the hook element 98 fixed to the lower beam 37A of the half-assembly 25A to apply a tension on the lower beam 37A that tends to bring the lower beam 37A closer to the lower beam 37B according to the lateral direction X3.

[0138] The movement of the locking member 91 between the locked position and the unlocked position is ensured by the connecting rod 97 and the guiding element 94 (such as a cam) fixed to the lower beam 37B.

[0139] The locking member 91 is referred to as an "internal locking member" because the hook 95 is radially inwardly offset relative to the handle 96.

[0140] In fact, the hook 95 and the hook element 98 extend radially between the longitudinal central axis A1 of the propulsion unit 1 and the longitudinal axis A3 of the beam 60 (see Figure 11 ).

[0141] In other words, in the locked position, the active part of the internal locking member 91 extends radially inwardly relative to the longitudinal axis A3, while the actuating part of the internal locking member 91 extends radially outwardly relative to the longitudinal axis A3.

[0142] Figure 14 and Figure 15 shows another embodiment, in which the internal locking member 91 differs from the internal locking member of Figure 12 and Figure 13 in that it includes an additional connecting rod 97X, thus enabling the guiding element 94 to be dispensed with.

[0143] The locking member 92, not shown in detail, is a conventional locking member that operates according to the same general principle as the internal locking member 91.

[0144] However, the active part of the locking member 92 is not radially inwardly offset relative to the longitudinal axis A3.

[0145] Therefore, in contrast to the internal locking member 91, the locking member 92 forms an "external locking member", and the locking member 92 extends and acts on a part of the beams 37A and 37B that is radially outwardly positioned relative to the longitudinal axis A3.

[0146] By inserting one or more seals between these different elements, the positioning and / or holding in place and / or sealing of the beams 37A and 37B relative to the connecting member 70 can be improved.

[0147] In Figure 11In the example, the first seal 77 is received in a groove (not shown) formed in the connecting beam 60 upstream of the groove 75, and the second seal 78 is received in the groove 75. The nacelle may include a sealing system formed by a series of seals, the series of seals including, for example, seals 77 and 78 and / or other seals.

[0148] Referring Figure 7 、 Figure 8 and Figure 10 , the connecting beam 60 provides a hollow internal space that forms a passage for the accessory 100 of the turbojet engine 2.

[0149] A part of this internal space is defined by two partitions 102 extending in a straight line with the upper base 73 of the connecting member 70 (see Figure 8 ).

[0150] In Figure 4 the example, the nacelle 3 includes a box 110 that houses the connecting beam 60 and the lower beams 37A and 37B of the semi-assemblies 25A and 25B.

[0151] Of course, the foregoing description is not restrictive. For example, the groove 75 may be discontinuous and / or have a rectangular geometry or any other shape. As another example, the second connecting elements 80A and / or 80B may include one or more grooves (not shown) that cooperate with one or more tenons (not shown) fixed to the connecting member 70, instead of or complementary to the tenons 82A or 82B.

Claims

1. A thrust reverser (17) for an aircraft propulsion unit (1), the thrust reverser comprising two half - assemblies (25A, 25B), a connecting beam (60) and cascades (50A, 50B), each half - assembly (25A, 25B) comprising a movable fairing (31A, 31B) and a fixed structure (30A, 30B), the fixed structure comprising a first connecting element (41A) and second connecting elements (80A, 80B), the connecting beam (60) comprising a connecting member (70), for each half - assembly (25A, 25B): - The first connecting element (41A) is configured to hinge the half - assembly (25A) to a fixed part of the propulsion unit (1) so as to enable the half - assembly (25A) to move between a flight configuration and a maintenance configuration, in which flight configuration, the second connecting element (80A) cooperates with the connecting member (70), and in which maintenance configuration, the second connecting element (80A) is separated from the connecting member (70). - In the flight configuration, the movable fairing (31A) is able to translate relative to the fixed structure (30A) along a longitudinal central axis (A1) between a direct - thrust position and a thrust - reverse position, in which direct - thrust position, the fixed structure (30A) and the movable fairing (31A) radially delimit between them a corresponding part of a duct (21N) for directing a fluid flow (20N) towards the rear of the propulsion unit (1) to generate thrust, and in which thrust - reverse position, the movable fairing (31A) exposes a space for receiving the cascade (50A) such that a part of the fluid (20N) flowing in the duct (21N) can pass through the cascade (50A) while being deflected thereby to generate reverse thrust. It is characterized in that The connecting member (70) and one of the second connecting elements (80A, 80B) of each half - assembly (25A, 25B) comprise a groove (75), and the other comprises a tenon (82A, 82B), the tenon being configured to fit into the groove (75) when the half - assembly (25A, 25B) moves from the maintenance configuration to the flight configuration so as to position each half - assembly (25A, 25B) in the flight configuration, the thrust reverser (17) comprising one or more locking elements (91, 92) configured to be connected together and lock the half - assemblies (25A, 25B) in the flight configuration.

2. The thrust reverser device (17) according to claim 1, wherein, When the half - assemblies (25A, 25B) are in the flight configuration, the second connecting elements (80A, 80B) of each half - assembly (25A, 25B) form half - cavities that enclose corresponding half - parts of the connecting member (70).

3. The thrust reverser device (17) according to claim 1, wherein, The connecting beam (60) extends along the axis (A3) around which the groove (75) extends.

4. The reverse thrust device (17) according to claim 1, wherein, One of the locking elements is an internal locking element (91) and the other of the locking elements is an external locking element (92): - The internal locking member (91) is connected to a fixed structure (30B) of a half-component (25B) and is configured to cooperate with a first hook element (98) fixed to a fixed structure (30A) of the other half-component (25A), the hook element (98) extending radially between the longitudinal central axis (A1) and the axis (A3) along which the connecting beam (60) extends. - The external locking member (92) is connected to a fixed structure (30B) of a half-component (25B) and is configured to cooperate with a second hook element fixed to a fixed structure (30A) of the other half-component (25A), the axis (A3) along which the connecting beam (60) extends extending radially between the second hook element and the longitudinal central axis (A1).

5. The thrust reverser device (17) according to claim 1, wherein, The first connecting element (41A) of each half-component (25A, 25B) is located on one side of a longitudinal intermediate plane (P2) passing through the longitudinal central axis (A1), and wherein the connecting beam (60) is located on the other side of the longitudinal intermediate plane (P2).

6. A nacelle (3) for an aircraft propulsion unit (1), the nacelle including the thrust reverser (17) according to claim 1.

7. A propulsion unit (1) for an aircraft, the propulsion unit including the nacelle (3) according to claim 6.

8. The propulsion unit (1) according to claim 7, the propulsion unit including a fan casing (11), the connecting beam (60) extending axially in a suspended manner relative to the fan casing (11).

9. An aircraft, the aircraft including the propulsion unit (1) according to claim 7.

Images