Jet deflection module for thrust reverser of aircraft turbine engine

Abstract

The invention relates to a jet deflection module (26) for a thrust reverser (10) of an aircraft turbine engine, the module (26) extending in a surface (P) and comprising: longitudinal members (32) spaced apart from each other and parallel to each other; -at least one deflection member (34) extending between and connected to the longitudinal members (32); -two attachment profiles, respectively a front profile (36) and a rear profile (38), which are connected to the longitudinal members (32) and together with two of these longitudinal members (32) form a peripheral contour of the module (26), a first of the attachment profiles (36, 38) comprising at least two U-joints (90), at least two U-joints (90) parallel to each other and parallel to the longitudinal member (32), and each U-joint comprising a bore (92), the bore (92) of the U-joint (90) being aligned with the pivot axis (A) of the module (26) and defining the pivot axis (A) of the module (26), characterized in that the U-joint (90) extends in a continuation of the longitudinal member (32).

Description

Technical Field

[0001] The present invention relates to the field of thrust reversers for aircraft turbines, and in particular to a jet deflection module for such a thrust reverser. The jet deflection module is, for example, a grid. Background Art

[0002] The technical background includes in particular documents FR-A1-2 938 878, FR-A1-2 954 410, FR-A1-3 069891, FR-A1-3 076 865, EP-A1-2 837 810, US-A1-2018 / 372024 and FR-A1-2 757 570.

[0003] Thrust reversers are now widely used in aircraft nacelles, particularly those housing turbines (e.g., twin-flow turbojets). In a known manner, such turbojets, using rotating fan blades, generate a flow of hot air (called the primary flow) from the combustion chamber and a flow of cold air (called the secondary flow) that circulates outside the turbojets through an annular channel formed between the turbojets' cowling and the inner wall of the nacelle. These two airflows are then ejected from the turbojets through the rear of the nacelle, generating thrust.

[0004] In this configuration, the thrust reverser has the function of improving the braking capability of the aircraft on the ground during the landing phase of the aircraft by redirecting forward at least part of the thrust generated by the turbojet engine. In particular, when the thrust reverser is active, it blocks the annular passage of the cold air flow (i.e., the secondary flow) and directs this flow towards the front of the nacelle, thereby generating reverse thrust.

[0005] The means used to achieve this redirection of the cold air flow vary depending on the type of reverser. However, in general, the structure of the thrust reverser includes one or more movable covers that can be moved between, on the one hand, a deployed position (also called thrust reversal position), in which the one or more movable covers open a channel in the nacelle for the steering flow, and, on the other hand, a retracted position (also called direct injection position), in which the one or more movable covers close the channel. Thus, the covers can be used to activate other deflection devices, such as flaps. In this case, the flaps activated by the movement of the movable covers at least partially block the flow channel through which the secondary flow circulates.

[0006] Furthermore, in the case of thrust reversers with deflection grids, the air flow is redirected by means of a jet reversal ring, which consists of a thrust reversal module mounted circumferentially around the thrust reverser ring and generally made of jet deflection grids. However, grids are not the only option available for deflecting the jets.

[0007] exist Figure 1 and Figure 2 1 shows a thrust reverser 10. This reverser 10 is of the grid or cascade reverser type.

[0008] This type of reverser 10 comprises at least one cover 12 movable relative to a fixed structure 14 comprising an upstream annular frame 16, the cover 12 having an outer wall 18 and an inner wall 20 intended to be positioned in the direct injection position ( Figure 1 ) defines the outer wall of the annular duct 22, wherein the secondary flow F11 flows in the annular duct 22.

[0009] The reverser 10 further comprises a wing 24 which is hingedly mounted on the movable cover 12 and which is actuated by a connecting rod 26 when the movable cover 12 moves downstream, so that in the thrust reversal position ( Figure 2 ), each vane 24 includes a region extending into the annular duct 22 to divert at least a portion of the secondary flow F11 out of the duct 22.

[0010] In the case of this type of reverser 10 , the secondary flow F11 is redirected by deflecting gratings 26 , the movable cover 12 having only a simple sliding function intended to not cover or cover these gratings 26 , the translation of the movable cover 12 occurring along a longitudinal axis substantially parallel to the axis of the nacelle and the reverser 10 .

[0011] The housing is arranged in the cover 12 so as to be in a position ... Figure 1 The direct injection position is shown, accommodating the grille 26 .

[0012] The louvers 26 are arranged adjacent to each other in an annular region around the annular duct 22 , side-to-side, with the smallest possible gaps between the louvers 26 . In this way, the majority of the secondary flow F11 deflected by the vanes 24 passes through the louvers 26 .

[0013] The thrust reverser 10 also comprises means for moving and guiding the movable cover 12, which means generally comprise actuators 28, each of which has an elongated shape and extends parallel to the axis of the thrust reverser 10. Each actuator 28 has an upstream end 28 a fastened to the fixed structure 14 comprising the frame 16 and a downstream end 28 b fastened to the cover 12.

[0014] The grille 26 is typically fastened by its upstream end to the front frame 16 and by its downstream end to the downstream annular frame 30 .

[0015] exist Figure 3 1 shows a grid 26 of a thrust reverser 10. This grid 26 extends mainly over a surface P which may be flat, curved or V-shaped. This surface is intended to be passed through by the air flow to be diverted. The grid 26 comprises:

[0016] - spars 32 spaced apart and parallel to each other,

[0017] - blades 34 extending between the spars 32 and connected to these spars 32 , these blades 34 being perpendicular to the spars 32 , and

[0018] Two fastening profiles, respectively located at the front 36 and the rear 38 , connected to the spars 32 and perpendicular to these spars 32 , these two profiles 36 , 38 forming, together with two of the spars 32 , the frame or outer contour of the grid 26 .

[0019] In the current art, each of the profiles 36, 38 includes or forms a flange 40 for fastening to the corresponding frame 16, 30. Figures 3 to 5 As shown, each flange 40 may extend into surface P and may define a flat bearing surface 42 intended to bear against the corresponding frame 16, 30. Alternatively, each flange 40 may be inclined relative to surface P, or may have a folded shape (e.g., in the form of a dihedron or V-shape) or a curved shape (in the form of a portion of a cylinder), etc. The frames 16, 30 have a complementary shape to accommodate these flanges. The flanges 40 include apertures 44 that align with apertures 46 in the frames 16, 30. These apertures 44, 46 are passed through by screws 48 to secure the grille 26 to the frames 16, 30.

[0020] However, this technique is not entirely satisfactory, as it has its drawbacks. The flanges 40 are relatively large and result in an increase in the length of the grille 26 or a reduction in the useful surface area of ​​the grille 26 occupied by the spars 32 and blades 34. Furthermore, the connection of the flanges 40 to the rest of the grille 26 is an area of ​​stress concentration that must be taken into account when defining the grille 26, and this can result in oversizing in these areas, thereby increasing the mass of the grille 26.

[0021] The present invention provides a simple, effective and economical solution to at least some of the problems of the current technology.

[0022] The invention is not limited to thrust reversal or jet deflection grids, but extends to any jet deflection module. The module can be applied to grids, thrust reversal rings consisting of jet deflection modules arranged between a circumferential front frame and a circumferential rear frame, etc. Summary of the Invention

[0023] According to a first aspect, the invention relates to a jet deflection module for a thrust reverser of an aircraft turbomachine, the module extending in a surface and comprising:

[0024] - spaced-apart and parallel spars,

[0025] at least one deflection element extending between the spars and connected to these spars,

[0026] - two fastening profiles, one at the front and one at the rear, which are connected to the spars and form, together with two of these spars, the outer contour of the module,

[0027] Characterized in that a first of the fastening profiles comprises at least one extra thickness portion in a direction parallel to the surface, said at least one extra thickness portion comprising at least one threaded hole oriented perpendicular to the surface.

[0028] Advantages of the present invention include simplifying at least one of the fastening profiles by eliminating its flange. Removing the flange reduces the length of the module and its overall dimensions in that direction. Advantageously, the remaining portion of the module, representing the useful and functional part, remains unaffected. The module is also easy to assemble and disassemble.

[0029] The jet deflection module according to the invention may comprise one or more of the following characteristics, employed separately from one another or in combination with one another:

[0030] --module covering said surface;

[0031] - the surface is flat, curved, dihedral or V-shaped;

[0032] - the deflection element is a blade;

[0033] - the deflection element is soft or flexible, or, on the contrary, rigid;

[0034] - the deflection element is a membrane;

[0035] - the at least one portion of extra thickness is oriented in a direction parallel to the spar;

[0036] --The spar is straight or curved;

[0037] --The fastening profile is perpendicular to the wing spar;

[0038] - the or each threaded hole is formed by an insert mounted in an orifice in the first profile, the orifice being oriented perpendicular to the surface;

[0039] - the first profile comprises a single portion of extra thickness extending over at least 80% of the length of the first profile;

[0040] - the first profile comprises a plurality of extra thickness portions, the plurality of extra thickness portions being spaced apart from one another, and each of the extra thickness portions comprising a threaded hole;

[0041] - said first profile comprises a first side situated inside said profile and an opposite second side situated outside said profile, the first side comprising a pressure side surface;

[0042] - the pressure side surface is positioned opposite the suction side of an adjacent blade, and the pressure side surfaces are separated from each other by a spar;

[0043] - the second side comprises the single portion of extra thickness and comprises a flat surface extending over at least 80% of the length of the first profile and perpendicular to the surface, the flat surface extending between two other flat surfaces, namely an upper flat surface and a lower flat surface, extending over at least 80% of the length of the first profile and parallel to each other and to the surface;

[0044] - the at least one threaded hole opens into the upper or lower flat surface, the upper or lower flat surface being configured to form a support surface for the module;

[0045] the or each threaded hole or the or each orifice opening out onto one of the pressure side surfaces;

[0046] - the second side comprises said portion of extra thickness formed by a boss;

[0047] the threaded holes opening into the surfaces of the bosses, the surfaces of the bosses being aligned with one another and with the surface of the first profile, this surface of the first profile extending over at least 80% of its length and being configured to form a bearing surface for the module;

[0048] - The at least one insert is completely housed in its mounting aperture.

[0049] --The insert is tubular;

[0050] the length of the or each hole or insert being between 20% and 50% of the thickness of the module, the thickness of the module being measured perpendicular to the surface;

[0051] - the first profile is the rear profile of the module;

[0052] --Modules are made of composite materials;

[0053] The module is manufactured by masking the pleats (fiber layers) and then injecting a polymerizable resin to embed and solidify the pleats (fiber layers); however, this type of construction is not restrictive, and the module may be manufactured by any type of manufacturing method, for example, by machining, casting, additive manufacturing, hot pressing, injection, etc.;

[0054] --The blades each have an aerodynamic profile and include a pressure side and a suction side;

[0055] - The module is a grid comprising a plurality of spars and blades extending between and connected to the spars, the blades being perpendicular to the spars.

[0056] The invention also relates to a thrust reverser for an aircraft turbomachine, comprising at least one module as described above.

[0057] Advantageously, the reverser has a generally annular shape around a central axis and comprises several modules distributed around this axis, each of these modules being supported radially outwards on an annular frame comprising orifices aligned with threaded holes through which screws screwed from the outside pass.

[0058] The invention also relates to an aircraft turbomachine comprising a thrust reverser or module as described above.

[0059] According to a second aspect, the invention relates to a jet deflection module for a thrust reverser of an aircraft turbomachine, the module extending in a surface and comprising:

[0060] - spaced-apart and parallel spars,

[0061] at least one deflection element extending between the spars and connected to these spars,

[0062] - two fastening profiles, one at the front and one at the rear, which are connected to the spars and form, together with two of these spars, the outer contour of the module,

[0063] It is characterized in that a first of the fastening profiles comprises at least one hook comprising at least one opening oriented perpendicular to the surface, the hook further comprising a bearing surface parallel to the surface.

[0064] Advantages of the present invention include simplifying at least one of the fastening profiles by eliminating its flange. Removing the flange reduces the length of the module and its overall dimensions in that direction. Advantageously, the remaining portion of the module, representing the useful and functional part, remains unaffected. The module is also easy to assemble and disassemble.

[0065] The module according to the invention may comprise one or more of the following characteristics, taken alone or in combination with one another:

[0066] --module covering said surface;

[0067] - the surface is flat, curved, dihedral or V-shaped;

[0068] - the deflection element is a blade;

[0069] - the deflection element is soft or flexible, or, on the contrary, rigid;

[0070] - the first section comprises a single U-shaped hook extending over at least 80% of the length of the first section;

[0071] --The spar is straight or curved;

[0072] --The fastening profile is perpendicular to the wing spar;

[0073] - the at least one hook is U-shaped;

[0074] - the first profile comprises several hooks at a certain distance from each other, the hooks being U-shaped for example;

[0075] - the support surface and the opening of the or each hook are located on the same end of the hook, or respectively on opposite ends of the hook;

[0076] - the or each hook comprises two openings perpendicular to said surface and oriented in opposite directions;

[0077] - said first profile comprises a first side situated inside said profile and an opposite second side situated outside said profile, the first side comprising a pressure-side surface and the second side comprising a hook;

[0078] - the pressure side surface is positioned opposite the suction side of an adjacent blade, and the pressure side surfaces are separated from each other by a spar;

[0079] - the or each hook comprises a flat surface located outside said profile and perpendicular to said surface;

[0080] - the or each hook has a thickness less than the thickness of the module;

[0081] - the first profile is the rear profile of the module;

[0082] --Modules are made of composite materials;

[0083] -- Manufacturing modules by masking pleats (fiber layers) and then injecting a polymerizable resin to embed and cure the pleats (fiber layers);

[0084] However, this type of design is not restrictive, and the module can be produced by any type of manufacturing method, for example, by machining, casting, additive manufacturing, hot pressing, injection molding, etc.;

[0085] --The blades each have an aerodynamic profile and include a pressure side and a suction side;

[0086] - The module is a grid comprising a plurality of spars and blades extending between and connected to the spars, the blades being perpendicular to the spars.

[0087] The invention also relates to an assembly comprising a module as previously described and at least one link for securing the module, the or each link being generally L-shaped or U-shaped and configured to be mounted on a hook of the module.

[0088] Advantageously, the or each rider comprises an edge configured to engage in the or one of the openings of the hook.

[0089] Advantageously, the or each link comprises an aperture for passing or screwing a screw, or the or each link carries a screw or a threaded rod.

[0090] The invention also relates to a thrust reverser for an aircraft turbomachine, comprising at least one module or assembly as described above.

[0091] Advantageously, the reverser has a generally annular shape around a central axis and comprises several modules distributed around this axis, each of these modules bearing radially outwardly on an annular frame having orifices for passing or screwing in screws or threaded rods.

[0092] Advantageously, the frame comprises an edge configured to engage in the opening or one of the openings of the hook.

[0093] The invention also relates to an aircraft turbomachine comprising a module, an assembly or a thrust reverser as described above.

[0094] According to a third aspect, the invention relates to a jet deflection module for a thrust reverser of an aircraft turbomachine, the module extending in a surface and comprising:

[0095] - spaced-apart and parallel spars,

[0096] at least one deflection element extending between the spars and connected to these spars,

[0097] - two fastening profiles, one at the front and one at the rear, which are connected to the spars and form, together with two of these spars, the outer contour of the module,

[0098] Characterized in that a first of the fastening profiles comprises at least two U-joints for articulation, the at least two U-joints for articulation being parallel to each other and to the spar, each of the at least two U-joints for articulation comprising an orifice, the orifice of the U-joint being aligned with and defining the pivot axis of the module.

[0099] Advantages of the present invention include simplifying at least one of the fastening profiles by eliminating its flange. Removing the flange reduces the length of the module and its overall dimensions in that direction. Advantageously, the remaining portion of the module, representing the useful and functional part, remains unaffected. The module is also easy to assemble and disassemble.

[0100] The module according to the invention may comprise one or more of the following characteristics, taken alone or in combination with one another:

[0101] --module covering said surface;

[0102] - the surface is flat, curved, dihedral or V-shaped;

[0103] - the deflection element is a blade;

[0104] - the deflection element is soft or flexible, or, on the contrary, rigid;

[0105] --The spar is straight or curved;

[0106] - Fastening profiles are perpendicular to the spar;

[0107] - The U-joint extends as an extension of the spar; this distributes the forces of the grid over the spar;

[0108] --The number of U-joints ranges from 2 to 8;

[0109] -The number of U-joints is equal to the number of spars;

[0110] - The U-shaped connector is single-ear or double-ear;

[0111] - the U-joint is integrally formed with the rest of the module or is mounted and fastened to the rest of the module;

[0112] -The metal bushing is received in the orifice in the U-joint;

[0113] - said first profile comprises a first side situated inside said profile and an opposite second side situated outside said profile, the first side comprising a suction side and the second side comprising a U-shaped joint;

[0114] - the suction side surface is located opposite the pressure side of an adjacent blade and the suction side surfaces are separated from each other by a spar;

[0115] - the first profile is a front profile;

[0116] --Modules are made of composite materials;

[0117] -- Manufacturing modules by masking pleats (fiber layers) and then injecting a polymerizable resin to embed and cure the pleats (fiber layers);

[0118] However, this type of design is not restrictive, and the module can be produced by any type of manufacturing method, for example, by machining, casting, additive manufacturing, hot pressing, injection molding, etc.;

[0119] --The blades each have an aerodynamic profile and include a pressure side and a suction side;

[0120] - the module is a grid comprising several spars and blades extending between and connected to the spars, the blades being perpendicular to the spars;

[0121] At least one or some of the U-joints are at a distance from the longitudinal ends of the profiles carrying them.

[0122] The invention also relates to an assembly comprising a module as described above and an articulation fitting for the grille, the fitting comprising a U-shaped joint configured to be fastened to the U-shaped joints of the modules, respectively.

[0123] The invention also relates to a thrust reverser for an aircraft turbomachine, comprising at least one module or assembly as described above.

[0124] Advantageously, the reverser has a substantially annular shape around a central axis and comprises several modules distributed around this axis, each of these modules being fastened and articulated to an annular frame by its U-shaped joint.

[0125] Advantageously, the U-joint of the module is fixed and hinged to a U-joint on the frame, or is fixed and hinged to a U-joint on a fitting mounted and fastened to the frame.

[0126] The invention also relates to an aircraft turbomachine comprising a module, an assembly or a thrust reverser as described above.

[0127] Features of different aspects of the invention may be combined, so that the same module may, for example, comprise a first profile according to one aspect of the invention and a second profile according to another aspect of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0128] The invention will be better understood and other details, characteristics and advantages will become apparent from the following description given by way of non-limiting example and with reference to the accompanying drawings, in which:

[0129] [ Figure 1 ] Figure 1 is a partial schematic diagram of a thrust reverser in a direct injection position in longitudinal section;

[0130] [ Figure 2 ] Figure 2 It is in thrust reverse position Figure 1 A partial schematic diagram of the thrust reverser in longitudinal section;

[0131] [ Figure 3 ] Figure 3 is a schematic perspective view of a module of a thrust reverser;

[0132] [ Figure 4 ] Figure 4 yes Figure 3 a schematic partial perspective view of the module shown and illustrating a fastening flange for the module applied to and fastened to the frame;

[0133] [ Figure 5 ] Figure 5 yes Figure 4 The schematic diagram of the module and frame is shown, the section along Figure 4 The line VV in is intercepted and passed through the fastening screw;

[0134] [ Figure 6 ] Figure 6 is a schematic partial perspective view of a thrust reverser module according to one embodiment of the present invention;

[0135] [ Figure 7 ] Figure 7 yes Figure 6 A schematic cross-sectional view of the module and frame shown, the cross section being along Figure 6 The line VII-VII is intercepted and passed through the fastening screw;

[0136] [ Figure 8 ] Figure 8 yes Figure 6Another schematic cross-sectional view of the module and frame, the cross section being along Figure 6 The line VIII-VIII is intercepted and passed between two adjacent fastening screws;

[0137] [ Figure 9 ] Figure 9 is a partial perspective view of a module for a thrust reverser according to one embodiment of the present invention;

[0138] [ Figure 10 ] Figure 10 yes Figure 9 A schematic perspective view and a cross-sectional view of the module shown, the cross section being along Figure 9 Line XX in and through the insert;

[0139] [ Figure 11 ] Figure 11 is a partial perspective view of a module for a thrust reverser according to another embodiment of the present invention;

[0140] [ Figure 12 ] Figure 12 Is used for fastening Figure 12 a schematic perspective view of the frame and linkage of the module shown;

[0141] [ Figure 13 ] Figure 13 yes Figure 11 and Figure 12 A partial schematic cross-section of the modules and frames shown;

[0142] [ Figure 14 ] Figure 14 yes Figure 12 Schematic cross section of the frame and fastening links;

[0143] [ Figure 15 ] Figure 15 is a partial perspective view of a module for a thrust reverser according to another embodiment of the present invention;

[0144] [ Figure 16 ] Figure 16 Is used for fastening Figure 15 A schematic perspective view of the frame and connecting rods of the module in FIG.

[0145] [ Figure 17 ] Figure 17 yes Figure 15 and Figure 16 A schematic partial cross section of a module, frame and connecting rod;

[0146] [ Figure 18 ] Figure 18 is a partial perspective view of a module for a thrust reverser according to another embodiment of the present invention;

[0147] [ Figure 19 ] Figure 19 It is associated with the frame and the connecting rod Figure 18 a schematic partial cross-section of the module shown;

[0148] [FIGS. 20a to 20c] FIGs. 20a to 20c are schematic cross-sectional views of several embodiments of frames and connecting rods for fastening modules according to the present invention;

[0149] [ Figure 21 ] Figure 21 is a partial perspective view of a module for a thrust reverser according to another embodiment of the present invention;

[0150] [ Figure 22 ] Figure 22 Is used for fastening Figure 21 a schematic perspective view of a frame of a grille;

[0151] [ Figure 23 ] Figure 23 yes Figure 21 and Figure 22 a schematic partial cross-sectional view of the modules and frames shown;

[0152] [ Figure 24 ] Figure 24 is a partial perspective view of a module for a thrust reverser according to another embodiment of the present invention;

[0153] [ Figure 25 ] Figure 25 Is used to fasten to Figure 24 a partial perspective view of a frame of a module of FIG, and showing a U-shaped joint for the frame; and

[0154] [ Figure 26 ] Figure 26 is a schematic partial perspective view of a frame and modules for fastening the grille module by means of fastening fittings. DETAILED DESCRIPTION

[0155] Described above Figures 1 to 5 .

[0156] Figure 6 The figures and the following figures illustrate several embodiments of the present invention.

[0157] These embodiments relate to specific features of at least one of the profiles 36, 38 of the jet deflection module for the thrust reverser 10. Although the following description focuses on modules in the form of a grid, the invention is not limited to modules of this type as mentioned above.

[0158] like Figure 3 As shown, the module or grid 26 comprises:

[0159] - (at least two) spars 32 spaced apart and parallel to each other,

[0160] at least one deflection element 34 extending between the spars 32 and connected to these spars 32 ; the deflection element or elements are, for example, blades 34 perpendicular to the spars 32 , without this being limiting, and

[0161] Two fastening profiles, respectively located at the front 36 and the rear 38 , connected to the spars 32 and perpendicular to these spars 32 , these two profiles 36 , 38 forming, together with the spar or two of these spars 32 , the outer contour of the grille 26 .

[0162] The deflection element 34 can be soft or flexible, or on the contrary rigid. A soft or flexible deflection element is for example a membrane.

[0163] For example, the spar 32 may be straight or curved.

[0164] According to the invention, at least one of the sections 36, 38 of the grid 26 may correspond to the one described below with reference to Figure 6 and one of the sections described in the following figures. For example, the front profile 36 or the rear profile 38 of the grille 26 may correspond to one of these profiles. Alternatively, the front profile may correspond to one of these profiles, while the rear profile 38 may correspond to the same profile or another of these profiles.

[0165] Advantageously, the grid 26 according to the invention comprises a grid corresponding to the grid described below with reference to Figure 6 to Figure 2 0c described one of the front profiles 36 (alternatively, the rear profile 38), and this same grille 26 comprises a corresponding to the hereinafter referenced Figures 21 to 26 The rear profile 38 (alternatively the front profile 36 ) of one of the embodiments is described.

[0166] Now, these embodiments will be described one by one.

[0167] Figures 6 to 8 A first embodiment is shown in which one of the fastening profiles 36 , 38 , for example the rear profile 38 , comprises at least one extra thickness portion 50 in which a threaded hole 51 is formed.

[0168] In the example shown, the profile 38 comprises several portions of extra thickness 50 spaced apart from one another and each portion of extra thickness 50 comprises a threaded hole 51. These threaded holes 51 are oriented perpendicular to the surface P which, as mentioned above, can be flat, curved, dihedral or V-shaped. This surface is intended to be passed through by the air flow to be diverted.

[0169] The portion of extra thickness 50 is oriented in a direction parallel to the surface P, in particular in a direction parallel to the spar 32 .

[0170] Each hole 51 may be formed by machining the profile 38, for example threading an aperture 52 in the profile 38. Alternatively, each hole 51 is formed by installing a threaded insert 54 in the aperture 52 in the profile 38.

[0171] The profile 38 comprises a first side 38a located inside the aforementioned profile and an opposite second side 38b located outside the profile. The first side 38a comprises a pressure side surface 56 that is positioned opposite the suction side 58 of the adjacent blade 34 and that is separated from each other by the spar 32, as can be seen in FIG. Figure 7 and Figure 8 Seen in.

[0172] It can be seen that the second side 38b includes a portion of extra thickness 50 formed by a boss.

[0173] The holes 51 or orifices 52 open into surfaces 60 of the bosses, which are aligned with each other and with a surface 62 of the profile 38, which extends over at least 80% of the length D of the profile 38, for example over the entire length of the profile, and which is configured to form a bearing surface for the grille 26 ( Figure 6 ). This bearing surface is designed to cooperate with the aforementioned frames 16, 30 by bearing.

[0174] The holes 51 or orifices 52 have a length L that is between 20% and 50% of the thickness E of the grid 26 , the thickness E of the grid 26 being measured in a direction perpendicular to the surface P.

[0175] also, Figure 5 and Figure 7 A comparison of the profiles 38 shows that the width R1 of the profile 38 is much smaller than the width R2 of a similar profile in the prior art.

[0176] exist Figures 6 to 8 In the embodiment shown, the threaded holes 51 may be obtained by, for example, machining or molding the grid.

[0177] Figure 9 and Figure 10 A variant is shown in which one of the fastening profiles 36 , 38 , for example the rear profile 38 , comprises a single portion of additional thickness 50 comprising at least one threaded hole 51 or in which at least one orifice 52 for mounting a threaded insert 54 is formed.

[0178] In the example shown, the portion of extra thickness 50 extends over at least 80% of the length D of the profile, for example over the entire length of the profile 38. The hole 51 or the insert 54 is oriented perpendicular to the surface P.

[0179] The extra thickness portion is generated in a direction parallel to the surface P.

[0180] The profile 38 comprises a first side 38a located inside the aforementioned profile and an opposite second side 38b located outside the profile. The first side 38a comprises a pressure side surface 56 located opposite the suction side 58 of the adjacent blade 34 and separated from each other by the spar 32 ( Figure 10 ).

[0181] It can be seen that the second side 38 b comprises a single portion of extra thickness 50 and comprises a flat surface 64 extending over at least 80% of the length D of the profile, for example over the entire length of the profile 38, and perpendicular to the surface P. This flat surface 64 extends between two other flat surfaces, an upper flat surface 66 and a lower flat surface 68, which extend over at least 80% of the length of the profile, for example over the entire length of the profile 38, and which are parallel to each other and to the surface P.

[0182] The orifice 52 for mounting the insert 54 opens onto an upper or lower flat surface 66, 68 configured to form a support surface for the grid 26. This support surface is designed to cooperate with the aforementioned frame 16, 30 by bearing.

[0183] Figure 10 The inserts 54 are shown to be completely housed in the bores 52, for example each insert is substantially tubular in shape. Furthermore, the bores 52 for mounting the inserts 54 open onto the pressure side surface 56. Thus, the bores 52 are continuous.

[0184] The insert 54 has a length L that is between 20% and 50% of the thickness E of the grid 26 , the thickness E of the grid 26 being measured in a direction perpendicular to the surface P.

[0185] also, Figure 5 and Figure 10 A comparison of the profiles 38 shows that the width R1 of the profile 38 is much smaller than the width R2 of a similar profile in the prior art.

[0186] Where the grille 26 includes a single hole 51 or a single insert 54, the single hole 51 or insert 54 may preferably be located at or near the middle of the profile's length D. In the particular case where the length is approximately 350 mm, the hole or insert may be located approximately 120 mm to 175 mm from one side of the grille (the side defined by one of the grille's spars).

[0187] exist Figure 9 and Figure 10 In the embodiment shown, the insert 54 can be secured in its aperture 52 by, for example, gluing, screwing, force fitting, or shrink fitting. Alternatively, the insert 54 can be co-molded directly with the grille 26.

[0188] Figures 6 to 10 A major advantage of the illustrated embodiments is that they do not alter the mechanical operation of securing the grille to the frame. When the grille is radially pressed against the frame by aerodynamic forces, the frame absorbs most of the radially outward forces. The primary purpose of the screws is to hold the grille in place. Reducing the length of the grille allows the radial inertia of the frame to be increased, which helps prevent grille deformation.

[0189] Figures 11 to 14 Another variant is shown in which one of the fastening profiles 36 , 38 , for example the rear profile 38 , comprises at least one U-shaped hook 70 comprising at least one opening 72 oriented perpendicular to the surface P. The or each hook 70 also comprises at least one bearing surface 74 parallel to the surface P.

[0190] In the example shown, the profile 38 comprises several U-shaped hooks 70 , here three in number, which are spaced apart from one another.

[0191] The support surface 74 and opening 72 of each hook 70 are located on opposite ends of the hook 70. For example, the support surface 74 is located at the upper end of the grille 26, while the opening 72 is located at the lower end of the grille 26.

[0192] As in the example shown, the thickness E1 of each hook 70 may be less than the thickness E2 of the remainder of the grille 26 .

[0193] The profile 38 includes a first side 38a located inside the profile and an opposite second side 38b located outside the profile. The first side 38a has a pressure side surface 56 that is located opposite the suction side 58 of the adjacent blade 34 and is separated from each other by the spar 32 ( Figure 13 ).

[0194] The second side 38b comprises a flat surface 76 perpendicular to the surface P. Advantageously, this surface 76 also forms a bearing surface for the grille 26 to rest on the frame to which it is fastened.

[0195] Figure 12 and Figure 13 There is shown a frame 30 to which the grille 26 is to be fastened. The frame 30 is generally L-shaped in cross section and comprises a cylindrical rim 30a extending around a hook 70. The hook 70 is supported radially outwardly on this rim 30a by its bearing surface 74.

[0196] Figure 13 Surface 74 is shown to be formed by a step in the grille, with rim 30a resting on the step and having a thickness that compensates for the step so that the radially outer surface of the rim is aligned with the outer or upper surface of the grille.

[0197] Figure 12 and Figure 14 Tie rods 78 are shown for securing the grille 26 , and in particular the profiles 38 , to the frame 30 .

[0198] Each link 78 is configured to be mounted on the hook 70 of the grate 26 and, in the example shown, is generally U-shaped.

[0199] Each link 78 abuts radially against the lower end of the hook 70 opposite the edge 30 a of the frame 30 , and is located on the edge 30 b of the frame 30 opposite the edge 30 a .

[0200] Each link 78 may include a first edge 78a configured to engage in the opening 72 of the hook 70. An edge 30b of the frame 30 opposite the edge 30a may be inserted between the hook 70 and a second edge 78b of each link 78.

[0201] Each link 78 may include a through-aperture or threaded hole for a screw 80 .

[0202] The screws 80 extend perpendicularly to the surface P and pass, on the one hand, through an aperture in the edge 30 a of the frame 30 and, on the other hand, through an aperture in the connecting rod 78 . Each of these screws 80 can pass through an aperture in the hook 70 .

[0203] Each screw 80 includes a head 80a and a free end, wherein the head 80a abuts against the edge 30a of the frame 30 and the free end can be screwed directly into the hole of the corresponding connecting rod 78, as long as the hole is threaded. Alternatively, a nut 80b can be screwed onto the free end and supported on the connecting rod 78.

[0204] In this variation, each hook 70 has a single opening 72 and a single bearing surface, in this case an upper surface 74 .

[0205] Figures 15 to 17 Another variant is shown in which one of the fastening profiles 36 , 38 , for example the rear profile 38 , comprises a single U-shaped hook 70 comprising an opening 72 oriented perpendicular to the surface P. This hook 70 also comprises a bearing surface 74 parallel to the surface P.

[0206] In the example shown, the U-shaped hook 70 extends over at least 80% of the length D of the profile 38 , for example over the entire length of this profile 38 .

[0207] The support surface 74 and the opening 72 of each hook 70 are located on the same end of the hook 70. For example, the support surface 74 is located at the upper end of the grille 26, and the opening 72 is also located at the upper end of the grille 26.

[0208] The profile 38 comprises a first side 38a located inside the aforementioned profile and an opposite second side 38b located outside the profile. The first side 38a comprises a pressure side surface 56 located opposite the suction side 58 of the adjacent blade 34 and separated from each other by the spar 32 ( Figure 17 ).

[0209] The second side 38 b comprises a flat surface 76 perpendicular to the surface P and extending over at least 80% of the length D of the profile 38, for example over the entire length of this profile 38. Advantageously, this surface 76 also forms a bearing surface for the grille 26 to rest on the frame to which it is fastened.

[0210] Figure 16 and Figure 17 The frame 30 to which the grille 26 is to be fastened is shown. The frame 30 is generally L-shaped in cross section and includes a cylindrical rim 30a extending around a hook 70 and including lugs 30c that engage in openings 72 of the hook 70. The hook 70 is supported radially outwardly on the rim 30a by a support surface 74. The lugs 30c engage in the opening 72 over the entire extent of the opening.

[0211] Figure 16 and Figure 17 Also shown are tie rods 78 for securing the grille 26 , and in particular the profiles 38 , to the frame 30 .

[0212] The connecting rod 78 is generally U-shaped, with its opening oriented in the direction of the surface P of the grille 26 .

[0213] The connecting rod 78 is designed to be mounted on the frame 30 and to hold the profile 38 relative to the frame 30. To achieve this, the connecting rod 78 comprises two tabs, respectively an upper tab 82 and a lower tab 84.

[0214] An upper tab 82 of the connecting rod 78 extends above or radially outside the frame 30 and comprises an aperture for the passage of a screw 80 screwed into a threaded aperture in the frame 30. The screw 80 is oriented perpendicular to the surface P.

[0215] The lower tab 84 of the link 78 extends below or radially inwardly of the frame 30 and hook 70 and thus forms a bearing surface radially inwardly for the hook 70 and, therefore, for the grille 26 .

[0216] It will therefore be appreciated that in this embodiment, the hook 70 has a single opening 72 and two bearing surfaces, namely an upper bearing surface 74 and a lower bearing surface 74'.

[0217] Figure 18 and Figure 19 Shows something like Figures 11 to 14 In another embodiment of the embodiment of the present invention, one of the fastening profiles 36, 38 (for example, the rear profile 38) includes several U-shaped hooks 70, each of which includes two openings oriented perpendicular to the surface P, namely an upper opening 72a and a lower opening 72b. Each hook 70 also includes two supporting surfaces parallel to the surface P, namely an upper supporting surface 74 and a lower supporting surface 74'.

[0218] The U-shaped hooks 70 are spaced apart.

[0219] The profile 38 comprises a first side 38a located inside the aforementioned profile and an opposite second side 38b located outside the profile. The first side 38a comprises a pressure side surface 56 facing the suction side 58 of the adjacent blade 34 and separated from each other by the spar 32.

[0220] The second side 38b comprises a flat surface 76 perpendicular to the surface P. Advantageously, this surface 76 also forms a bearing surface for the grille 26 to rest on the frame to which it is fastened.

[0221] Figure 19 Shown for fastening Figure 18 Frame 30 and connecting rod 78 of grille 26 in FIG. Frame 30 is generally L-shaped in cross section and includes a cylindrical rim 30a extending around hooks 70. Hooks 70 are supported radially outwardly on rim 30a by their bearing surfaces 74. Cylindrical rim 30a includes a first lug 30c that engages in an upper opening 72a of each hook 70.

[0222] Figure 19 Also shown is a link 78 mounted on the hook 70 of the grille 26 .

[0223] Each link 78 is configured to be mounted beneath the hook 70 of the grate 26 and, in the example shown, is generally U-shaped.

[0224] Each link 78 rests radially against a lower surface 74 ′ of the hook 70 opposite the edge 30 a of the frame 30 , and is situated on an edge 30 b of the frame 30 opposite this edge 30 a .

[0225] Each link 78 may include a first edge 78a configured to engage in the opening 72 of the hook 70. An edge 30b of the frame 30 opposite the edge 30a may be inserted between the hook 70 and a second edge 78b of each link 78.

[0226] Each link 78 may include a through-aperture or threaded hole for a screw 80 .

[0227] The screws 80 extend perpendicularly to the surface P and pass, on the one hand, through holes in the edge 30a of the frame 30 and, on the other hand, through holes in the connecting rod 78. Each of these screws 80 can be housed in a transverse space 81 between the hooks 70.

[0228] Each screw 80 includes a head 80a and a free end, wherein the head 80a abuts against the edge 30a of the frame 30 and the free end can be screwed directly into the hole of the corresponding connecting rod 78, as long as the hole is threaded. Alternatively, a nut 80b can be screwed onto the free end and supported on the connecting rod 78.

[0229] It will therefore be appreciated that in this embodiment, each hook 70 has two openings 72a, 72b and two support surfaces, namely an upper support surface 74 and a lower support surface 74'.

[0230] 20a to 20c show alternative versions of the frames 16, 30 and the links 78. FIG.

[0231] In the case of Figure 20a, the or each connecting rod 78 has a similar Figure 14 and Figure 19 30 and is fastened to at least one threaded rod 86 extending perpendicularly to the surface P. This rod 86 is intended to pass through an orifice in the cylindrical edge 30 a of the frame 30 and its free end is intended to receive a nut 88. Advantageously, this nut 88 is fixedly mounted on the frame 30.

[0232] Figure 20b corresponds to Figure 14 and Figure 19 An embodiment is shown in which the free end of the screw 80 is screwed directly into the nut.

[0233] Figure 20c corresponds to Figure 14 and Figure 19 A design is shown in which the free end of the screw 80 is screwed directly into a threaded hole in the connecting rod 78.

[0234] exist Figure 11 to Figure 2 In the embodiment shown in 0c, the threaded hole can be obtained by machining, molding or co-molding. Alternatively, the threaded hole can be obtained by an insert, which is for example accommodated and maintained in the orifice by gluing, screwing, force fitting or shrink fitting.

[0235] Figure 11 to Figure 2 The main advantage of the methods shown in Figure 0c is that they do not alter the mechanical operation of securing the grille to the frame. When the grille is radially pressed against the frame by aerodynamic forces, the frame absorbs most of the radially outward forces. The primary purpose of the screws is to hold the grille in place. Reducing the length of the grille increases the radial inertia of the frame, which helps prevent grille deformation.

[0236] Figures 21 to 23 Another variant is shown in which one of the fastening profiles 36, 38 (for example, the front profile 36) includes at least two articulation U-joints 90 extending longitudinally from the spar 32, and each articulation U-joint 90 includes an aperture 92. The apertures 92 in the U-joints 90 align or form a ball joint and define the pivot point of the grille 26. In one configuration, the U-joints 90 can be parallel to each other, which can facilitate rotation about the same axis A.

[0237] Advantageously, the U-joints 90 extend as an extension of the spars 32 and may be formed by the ends of these spars 32. This enables the forces coming from the grid 26 to be distributed over the spars 32.

[0238] Here, the U-shaped joint 90 is a single-ear type U-shaped joint.

[0239] The U-joint 90 is integrally formed with the remainder of the grille 26 , but alternatively, the U-joint 90 may be mounted and secured to the remainder of the grille.

[0240] The metal bushing may be received in the aperture 92 in the U-joint 90 .

[0241] The profile 36 includes a first side 36a located inside the aforementioned profile and an opposite second side 36b located outside the profile. The first side 36a includes a suction side surface 94 that is positioned opposite the pressure side 96 of the adjacent blade 34 and is separated from each other by the spar 32. The second side 36b includes a U-shaped joint 90 and may have a generally circular concave shape, such as Figure 23 shown.

[0242] In the example shown, each U-joint 90 has a circular outer contour.

[0243] Figure 21 and Figure 22Frame 16 is shown, to which U-joints 90 are fastened, in particular hinged, to frame 16. Frame 16 also includes complementary U-joints 98 for fastening U-joints 90 of grille 26. The number of U-joints 98 on frame 16 is equal to the number of U-joints 90 on grille 26, and in the example shown, there are two. Each U-joint 98 has a circular outer contour. A pin passes through an aperture in each of U-joints 90 and 98, respectively, to enable pivoting of U-joints 90 and 98.

[0244] The U-joint may be integrally machined or molded, or mounted and fastened to the frame 16 .

[0245] Figure 24 and Figure 25 Another variant is shown in which one of the fastening profiles 36, 38 (for example the front profile 36) comprises more than two articulation U-joints 90, which are parallel to one another and to the spar 32, and each articulation U-joint 90 comprises an orifice 92. The orifices 92 in the U-joints 90 are aligned and define the pivot axis A of the grille 26.

[0246] The number of U-joints 90 is, for example, between 2 and 8. In the example shown, the number of U-joints 90 is equal to the number of spars 32 .

[0247] Advantageously, the U-joints 90 extend as an extension of the spars 32 and may be formed by the ends of these spars 32. This distributes the forces of the grid 26 over all the spars 32.

[0248] Here, the U-shaped joint 90 is a single-ear type U-shaped joint.

[0249] The U-joint 90 is integrally formed with the remainder of the grille 26 , but alternatively, the U-joint 90 may be mounted and secured to the remainder of the grille.

[0250] The metal bushing may be received in the aperture 92 in the U-joint 90 .

[0251] The profile 36 includes a first side 36a located inside the aforementioned profile and an opposing second side 36b located outside the profile. The first side 36a includes a suction side surface 94 that is positioned opposite the pressure side 96 of the adjacent blade 34 and is separated from each other by the spar 32. The second side 36b includes a U-shaped joint 90 and may have a generally circular concave shape.

[0252] In the example shown, each U-joint 90 has a square or rectangular outer profile.

[0253] Figure 25The frame 16 is shown, to which the U-joint 90 is fastened, in particular hinged, to the frame 16. The frame 16 also includes complementary U-joints 98 for fastening the U-joints 90 of the grille 26. These U-joints 98 are of a double-eared type, which facilitates the transmission of transverse forces. The two ears of each U-joint 98 define a mounting space for the corresponding U-joint 90. Each U-joint 98 can have a circular outer contour. A pin passes through an aperture in each of the U-joints 90 and 98 to enable the U-joints 90 and 98 to pivot.

[0254] The U-joint may be integrally machined or molded, or mounted and fastened to the frame 16 .

[0255] Figure 26 Shown with Figures 21 to 25 The variation shown is similar to another variation. In this variation, the U-joint 98 on the frame 16 is supported by a fitting 100 that is added and fastened to the frame 16.

[0256] Figures 21 to 26 A particular advantage of the embodiment shown is that a pivot connection is created between the grille and its fastening frame. This change allows the grille design to be simplified, since it is not necessary to tighten the fastening elements, but only to install the pivot pin for the U-joint and fasten the U-joint in place (e.g. using pins, nuts, etc.).

Claims

1. A jet deflection module (26) for a thrust reverser (10) of an aircraft turbomachine, the module (26) extending in a surface (P) and comprising: - spaced-apart and mutually parallel spars (32), - at least one deflection element (34) extending between the spars (32) and connected to these spars (32), - two fastening profiles, respectively located at the front (36) and the rear (38), connected to the spars (32) and forming, together with two of these spars (32), the outer contour of the module (26), A first of the fastening profiles (36, 38) comprises at least two U-shaped joints (90) for articulation, the at least two U-shaped joints for articulation being parallel to each other and to the spar (32), each of the at least two U-shaped joints for articulation comprising an orifice (92), the orifice (92) of the U-shaped joint (90) being aligned with and defining the pivot axis (A) of the module (26), characterised in that the U-shaped joint (90) extends in the extension of the spar (32).

2. The module (26) according to claim 1, wherein The number of the U-joints (90) is equal to the number of the spars (32).

3. The module (26) according to any one of claims 1 and 2, wherein The U-joint (90) is integrally formed with the remainder of the module (26) or is mounted and fastened to the remainder of the module (26).

4. The module (26) according to any one of claims 1 to 3, wherein A metal bushing is received in the aperture (92) of the U-joint (90).

5. The module (26) according to any one of claims 1 to 4, wherein The first profile (36, 38) includes a first side (36a) located inside the profile and including a suction side surface (94) and an opposite second side (36b) located outside the profile, the first side (36a) including the suction side surface (94) and the second side (36b) including the U-joint (90).

6. A module (26) according to any one of the preceding claims, wherein The first profile is a front profile (36).

7. A module (26) according to any one of the preceding claims, wherein The module is a grid (26) comprising a number of spars (32) and blades (34) extending between and connected to the spars (32), the blades (34) being perpendicular to the spars (32).

8. A module (26) according to any one of the preceding claims, wherein At least one or some of the U-joints (90) are located at a distance from the longitudinal ends of the profiles (36, 38) carrying them.

9. A module (26) according to any one of the preceding claims, wherein The fastening profiles (36, 38) are perpendicular to the spar (32).

10. A module (26) according to any one of the preceding claims, wherein The number of the U-shaped joints (90) ranges from 2 to 8.

11. A module (26) according to any one of the preceding claims, wherein The U-shaped joint (90) is of a single-ear type or a double-ear type.

12. A module (26) according to any one of the preceding claims, wherein The modules are made of composite materials.

13. An assembly comprising a module (26) according to any one of the preceding claims and an articulation fitting (100) of the module (26), the fitting (100) comprising a U-joint (98) configured to be fastened to a U-joint (90) of the module (26), respectively.

14. A thrust reverser (10) for an aircraft turbomachine, comprising at least one module (26) according to any one of claims 1 to 12 or an assembly according to claim 13.

15. An aircraft turbomachine comprising a module (26) according to any one of claims 1 to 12, an assembly according to claim 13, or a thrust reverser (10) according to claim 14.

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