GUIDE ASSEMBLY FOR AN AIRCRAFT PROPULSION ASSEMBLY

Abstract

The present invention relates to a guide assembly (9) for an aircraft propulsion assembly (10), the guide assembly (9) comprising a first element (6) and at least one guide element (8) fixed on the first element (6), the guide element (8) comprising: - a bottom wall (83), - two side walls (84, 85) connected to each other by the bottom wall (83), and - an opening (86) delimited between the bottom wall (83) and the side walls (84, 85), the opening (86) is intended to receive at least in part a second element (7) configured to move relative to the guide element, the guide element further comprises at least one pair of gripping tabs (80) cooperating with holding members (62) of the first element to retain the guide element on the first element. Figure for abstract: Figure 6

Description

Title of the invention: GUIDE ASSEMBLY FOR AN AIRCRAFT PROPULSION ASSEMBLY Technical field

[0001] The present invention relates to the field of propulsion systems, in particular aircraft systems.

[0002] More particularly, the present invention relates to a guide assembly for an aircraft propulsion unit. The present invention also relates to a thrust reverser for a nacelle of an aircraft propulsion unit comprising this guide assembly, and a method of assembling this guide assembly. Technical background

[0003] A propulsion unit, in particular for an aircraft, comprises a turbomachine type engine which is surrounded by a nacelle.

[0004] The nacelle generally has a tubular structure comprising an air inlet upstream of the turbomachine, a middle section intended to surround a fan of the turbomachine, a downstream section integrating thrust reversal means and intended to surround a combustion chamber of the turbomachine, and is generally terminated by an ejection nozzle whose outlet is located downstream of the turbomachine.

[0005] It is known that the nacelle may be intended to house a dual-flow turbomachine capable of generating, via the rotating fan blades, a hot air flow (otherwise called primary flow) and a cold air flow (otherwise called secondary flow). This cold air flow circulates outside the turbomachine through an annular vein formed between a fairing of the turbomachine and an internal wall of the nacelle. These two hot and cold flows are ejected from the turbomachine through the rear of the nacelle.

[0006] A thrust reverser is thus mounted in the downstream section of the nacelle.

[0007] The role of a thrust reverser is, when an aircraft lands, to improve the braking capacity of the latter by redirecting forward at least part of the thrust generated by the turbomachine. In this phase, the reverser obstructs at least part of the cold flow vein and directs this flow towards the front of the nacelle, thereby generating a counter-thrust which adds to the braking of the aircraft's wheels.

[0008] The means implemented to achieve this orientation of the cold flow vary depending on the type of thrust reverser.

[0009] A common thrust reverser structure includes in particular a cowl in which an opening is provided for the diverted flow which, in a reversal situation thrust, is released by translational movement downstream (with reference to the direction of gas flow in the propulsion unit), by means of cowl movement cylinders.

[0010] This sliding hood can be formed of two half-hoods, of substantially semi-cylindrical shape, which are articulated in the upper part (at 12 o'clock, by analogy with the dial of a clock) on hinges parallel to the direction of translation of the sliding hood, and which are closed by locks in the lower part (at 6 o'clock).

[0011] This arrangement allows, for maintenance operations, access to the interior of the nacelle, and in particular to the turbomachine or to an internal structure of the thrust reverser by opening these half-cowls.

[0012] Another possible thrust reverser structure comprises a single-part outer cowl without a break in the lower part. Such a structure is called an O-structure.

[0013] The displacement cylinders are in particular mounted on a front frame of the hood upstream of the opening. This hood of the nacelle, called the external hood, is fixed. The movement of the front frame relative to the fixed hood is carried out along a guide assembly.

[0014] [Fig. 1] illustrates an example of this guide assembly 9 for moving in particular by translation a first element 6 of the thrust reverser of the nacelle 1 (forming a guided element) relative to a second element 7 of the thrust reverser (forming a guiding element). The first element 6 may be a fixed beam of the front frame 52. The second element 7 may be a slider (also designated by the English term “slider”) of the external cowl 5.

[0015] The guide assembly 9 also comprises at least one guide element 8. This guide element 8 may be a rail or a guide track.

[0016] As illustrated in [Fig.l], the guide element 8 is fixed to the first element 6. For example, the guide element 8 is assembled by sliding, in particular from the rear to the front (relative to the direction of gas flow in the propulsion unit), in a guide housing 60 of the first element 6.

[0017] With reference to figures 2, 3a and 3b, the guide element 8 has a general elongated shape along a longitudinal axis A between a first longitudinal end 81 and a second longitudinal end 82.

[0018] This guide element 8 comprises: - a back wall 83, - two side walls 84, 85 connected to each other by the bottom wall 83, and - an opening 86 delimited between the bottom wall 83 and the side walls 84, 85.

[0019] The opening 86 makes it possible in particular to receive at least part of the second element 7. This second element 7 is thus able to move in this opening 86.

[0020] The guide element 8 is currently retained, on the one hand, by a fixing device 90 located upstream of the guide element 8 (namely on the first longitudinal end 81), and on the other hand, by a friction-type contact portion between the guide element 8 and the first element 6. This friction at the interface of the guide element 8 and the first element 6 can induce friction during their assembly (for example, assembly of the first element 6 by force) and / or disassembly (for example, dissociation of the parts 6, 8 by pulling) which can damage these parts 6, 8, and in particular protective coatings which can be applied to these parts 6, 8.

[0021] Furthermore, the frictional contact between the guide element 8 (in particular via the side walls 84, 85 of the guide element) and the first element 6 may have a variable coefficient of friction which may restrict the holding of the guide element 8 inside the first element.

[0022] In this context, it is interesting to overcome the drawbacks of the prior art, by proposing a guide assembly (comprising the first element and the guide element) which is robust and easy to assemble and / or disassemble in an aircraft propulsion assembly. Statement of the invention

[0023] The present invention provides a simple, effective and economical solution to at least some of the aforementioned problems.

[0024] To this end, the invention proposes a guide assembly for an aircraft propulsion assembly, the guide assembly comprising a first element and at least one guide element fixed to the first element, the guide element having a general elongated shape along a longitudinal axis A between a first longitudinal end and a second longitudinal end, the guide element comprising: - a back wall, - two side walls connected to each other by the bottom wall, and - an opening defined between the bottom wall and the side walls, the opening being intended to receive at least in part a second element configured to move relative to the guide element.

[0025] According to the invention, the guide element further comprises at least one pair of gripping tabs cooperating with holding members of the first element to retain the guide element on the first element.

[0026] The integration of at least one pair of gripping tabs generally makes it possible to improve the retention of the guide element on the first element. More particularly, when the guide element is installed on the first element, each tab is in abutment with the corresponding holding member of the first element. Unlike the frictional contact between the guide element and the first element of the prior art, the abutment between the pair of gripping tabs and the holding members makes it possible to more effectively and easily stop the movement of the guide element installed in the first element.

[0027] Furthermore, the absence of friction between the guide element (in particular at the level of the side walls) and the first element in the configuration of the invention makes it possible to reduce the risks of damage to the parts (namely the guide element and the first element) during their assembly and / or disassembly. Indeed, a simple bringing together of the tabs by compression makes it possible to elastically deform the guide element (in particular the pair of tabs and the side walls) so that it can be inserted (for example by translation) into a guide housing of the first element. This therefore makes it possible to eliminate friction during the installation and disinstallation of these parts. Thus, the pair of gripping tabs makes it easier to assemble and disassemble the guide element on the first element.

[0028] The invention therefore has the advantage of proposing a simple design, offering great reliability, and with little penalty in terms of cost and size of the guidance assembly in an aircraft propulsion assembly.

[0029] The guide assembly according to the invention may comprise one or more of the following characteristics, taken in isolation from one another or in comparison with one another:

[0030] - the pair of gripping tabs extends substantially in a parallel plane or in a plane perpendicular to axis A;

[0031] - the tabs of the pair of gripping tabs and the walls are deformable elastically between a first position, in which the tabs and the walls are brought together, and a second position, in which said tabs cooperate with the holding members to retain the guide element on the first element;

[0032] - said at least one pair of gripping tabs extends projecting towards the outside from a free end of the side walls;

[0033] - the guide assembly comprises several pairs of gripping tabs distributed regularly along axis A;

[0034] - the holding members are grooves, each groove receiving a tab of the pair of gripping tabs of the guide element;

[0035] - the guide assembly further comprises at least one fixing device at at least one of the first and second longitudinal ends of the guide element and / or on said at least one pair of gripping tabs, the fixing device being intended to secure the guide element to the first element;

[0036] - the first element comprises at least one pair of bearing surfaces complementary to the corresponding support faces of the pair of gripping tabs;

[0037] — said bearing faces have a flat or curved shape

[0038] — the guide element is a rail;

[0039] — the first element is a slider;

[0040] — the guide assembly comprises the second element which is assembled at least in part in the opening of the guide member for the second member to move relative to the guide member;

[0041] — the second element is a fixed beam;

[0042] — each groove has a shape complementary to or substantially to that of the corresponding tab of the pair of gripping tabs;

[0043] — the pair of gripping tabs is made in one piece with the side walls;

[0044] — each tab of the pair of gripping tabs comprises at least one flat or curved L-shaped portion;

[0045] — the guide assembly comprises at least one fixing device configured to fix the guide element on the first element;

[0046] — the fixing device comprises a screw, a wedge and an interposed shoulder ring between a screw head and the wedge.

[0047] The present invention also relates to a thrust reverser for a nacelle of an aircraft propulsion unit, the thrust reverser comprising at least one external cover movable between a so-called closed position of the thrust reverser and a so-called open position of the thrust reverser, and a front frame, in which the external cover is mounted so as to move in translation along at least one guide assembly according to one of the particularities of the invention.

[0048] The first element of the guide assembly may be secured to the front frame of the thrust reverser.

[0049] The second element may be integral with the external cover of the thrust reverser.

[0050] The present invention may also relate to a propulsion assembly, in particular for an aircraft, comprising at least one guidance assembly according to one of the particularities of the invention or a thrust reverser according to the invention.

[0051] The present invention also relates to a method of assembling at least one guide assembly according to one of the features of the invention. The method comprises the steps of: (a) providing the first element and said at least one guide element, (b) compressing the gripping tabs of the guide element, (c) translating the guide element into a guide housing of the first element along the longitudinal axis A, (d) releasing the gripping tabs so that each tab of said at least one pair of gripping tabs cooperates in abutment with the corresponding holding member to retain the guide element on the first element.

[0052] Step (d) allows the pair of gripping tabs and the side walls (and consequently the entire guide element) to return to its initial shape before compression in step (b). The assembly method may further comprise, after step (d), a step (e) of adding at least one fixing device to at least one of the first and second longitudinal ends of the guide element and / or to said at least one pair of gripping tabs.

[0053] Advantageously, the assembly method comprises a step (f) of inserting a second element at least partly into the opening of the guide element, for example by translation. Description of figures

[0054] The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the appended drawings in which:

[0055] [Fig.l] is a partial schematic view in axial section of a guide assembly according to the prior art,

[0056] [Fig.2] is a schematic perspective view of a guide element of the guide assembly of [Fig.l],

[0057] [Fig.3a] is a partial schematic perspective view of the guide assembly of [Fig.l],

[0058] [Fig.3b] is a partial schematic front view of the guide assembly of [Fig.3a],

[0059] [Fig.4] is a schematic perspective view of a nacelle of an aircraft propulsion unit comprising a thrust reverser in the open position having a guide assembly according to the invention,

[0060] [Fig.5] is a schematic axial sectional view of the thrust reverser of [Fig.4],

[0061] [Fig.6] is a partial schematic front view of the guide assembly of [Fig.4] according to a first embodiment of the invention, this guide assembly comprising a guide element according to a first variant,

[0062] [Fig.7] is a partial schematic perspective view of a first element of the guide assembly of [Fig.6],

[0063] [Fig.8] is a partial schematic front view of the guide assembly of [Fig.6] comprising a guide element according to a second variant,

[0064] [Fig.9] is a partial schematic front view of the guide assembly of [Fig.4] according to a second embodiment of the invention,

[0065] [Fig. 10] is a partial schematic perspective view of the guide assembly of [Fig.4] according to a third embodiment of the invention, this guide assembly comprising a second element according to a first variant,

[0066] [Fig. 1 1] is a partial schematic cross-sectional view of the guide assembly of [Fig. 10] comprising a second element according to a second variant,

[0067] [Fig. 12a] is a partial schematic cross-sectional view of the steps of compression and translation of the gripping tabs of the guide assembly of [Fig. 10],

[0068] [Fig. 12b] is a partial schematic cross-sectional view of a step of releasing the gripping tabs of [Fig. 12a],

[0069] [Fig. 13a] is a partial schematic perspective view of the guide element of [Fig.6] installed in the first element by a first example of tooling,

[0070] [Fig. 13b] is a partial schematic front view of [Fig. 12a],

[0071] [Fig. 14] is a partial schematic perspective view of the guide element of [Fig. 6] installed in the first element by a second example of tooling,

[0072] [Fig. 15] is a partial schematic perspective view of the guide element of [Fig.6] installed in the first element by a third example of tooling.

[0073] Elements having the same functions in different implementations have the same references in the figures. Detailed description

[0074] By convention, in the description below, the terms “longitudinal” and “axial” describe the orientation of structural elements extending in the direction of a longitudinal axis, such as a longitudinal axis of the engine of a turbomachine. The terms “radial” or “vertical” describe an orientation of structural elements extending in a direction perpendicular to the longitudinal axis. The terms “inner” and “outer”, and “internal” and “external” are used with reference to a positioning relative to the longitudinal axis. Thus, a structural element extending along the longitudinal axis has an inner face facing the longitudinal axis and an outer surface, opposite its inner surface.

[0075] Similarly, by convention in the present application, the terms “upstream” and “downstream” are defined in relation to the direction of circulation of the gases in the turbomachine of an aircraft propulsion unit.

[0076] Figures 1, 2, 3a and 3b have been described in the above and illustrate a guide element 8 and a guide assembly 9 according to the prior art.

[0077] The invention applies in a non-limiting manner to an aircraft propulsion unit 10. [Fig. 4] illustrates this aircraft propulsion unit 10 comprising a turbomachine 3 which is surrounded by a nacelle 1.

[0078] The aircraft propulsion assembly 10 may be suspended from a fixed structure of an aircraft, for example under a wing or on a fuselage, by means of a pylon 2 (or mast) attached to the turbomachine 3 or to the nacelle 1 in the case of the example in [Fig.4],

[0079] The turbomachine 3 may be a double-flow turbomachine which comprises, from upstream to downstream (depending on the direction of gas flow), a fan, a low-pressure compressor, a high-pressure compressor, an annular combustion chamber, a high-pressure turbine and a low-pressure turbine, which define a flow path for a primary air flow (called a hot air flow).

[0080] The nacelle 1 extends along a longitudinal axis X coincident with the longitudinal axis of the turbomachine 3.

[0081] The nacelle 1 may comprise, from upstream to downstream, an upstream air intake section 4, a middle section (not visible in [Fig.4]), a downstream section housing a thrust reverser and possibly a terminal nozzle section. The sections of the nacelle are connected together so as to extend around the turbomachine 3 and define around it an annular flow vein for a secondary air flow (or cold air flow).

[0082] The thrust reverser comprises an external cowl 5 and a front frame 52. The thrust reverser may comprise members 50 for deflecting an air flow (in particular that of the cold air flow). These deflecting members 50 may be movably connected to the external cowl 5 (not illustrated in the figures) or the deflecting members 50 may be fixedly connected to the front frame 52 ([Fig.5]).

[0083] The external cowl 5 is in a single part, i.e. an O-shaped structure, in the example shown. The external cowl 5 is movable between a so-called closed position and a so-called open position. The closed position of the thrust reverser (not shown) is a position in which the external cowl ensures the external aerodynamic continuity of the nacelle with the upstream and middle section. The external cowl 5 can thus cover the deflection members 50.

[0084] In [Fig. 4], the thrust reverser is shown in the open position, in which position the external cowl 5 of the downstream section is deployed downstream of the nacelle 1 so as to clear an opening in the external structure of the nacelle and uncover the deflection members 50.

[0085] The deflection members 50 may be in the form of grids. These deflection members 50 are supported by the front frame 52.

[0086] In the example, the front frame 52 closes the nacelle upstream of the external cowl 5 and is intended to be mechanically connected to a casing of the fan of the turbomachine by connecting means 54. These connecting means 54 can be detachable from the casing of the fan.

[0087] As described above, the outer cover 5 moves relative to the fixed front frame 52 along a guide assembly 9. For this, the front frame 52 may comprise a first element 6, such as a fixed beam, and the outer cover 5 may comprise a second element 7, such as a moving part. This moving part may be a slider. The first element 6 makes it possible to form a fixed element capable of receiving a guide element 8, and the second element 7 makes it possible to form a moving element capable of moving along the guide element 8.

[0088] The guide assembly 9 therefore comprises the first element 6 and at least one guide element 8.

[0089] The guide element 8 is configured to be fixed on the first element 6.

[0090] The guide element 8 has a general elongated shape along a longitudinal axis A. This axis A can be confused with the axis X. The guide element 8 extends between a first longitudinal end 81 and a second longitudinal end 82.

[0091] The guide element 8 may be a rail (also referred to by the English term “trackliner”). The guide element 8 may be elastically deformable. The guide element 8 may have a substantially omega “Q” shape.

[0092] The guide element 8 comprises: - a back wall 83, - two side walls 84, 85, called first wall 84 and second wall 85, connected to each other by the bottom wall 83, and - an opening 86 delimited between the bottom wall 83 and the first and second side walls 84, 85.

[0093] Each of the first and second side walls 84, 85 may be curved, a concave portion of each of the first and second side walls 84, 85 being directed in particular towards the opening 86. In the examples of FIGS. 6, 8, 9 to 11, the first and second side walls 84, 85 are symmetrical with respect to each other by a median plane of symmetry B. This plane B is substantially perpendicular to the axis A.

[0094] Each of the first and second side walls 84, 85 has, respectively, a free end 840, 850. These free ends 840, 850 extend in particular the along the axis A. In the examples of figures 6, 8, 9 and 13, the free ends 840, 850 are separated from each other symmetrically with respect to the plane B.

[0095] The opening 86 is intended to receive at least in part the second element 7. This second element 7 is thus able to move, in particular by translation along the axis A, in this opening 86.

[0096] The bottom wall 83, the first and second side walls 84, 85 and the opening 86 extend in particular along the axis A.

[0097] The bottom wall 83 and the first and second side walls 84, 85 may be formed from a single piece (i.e., integrally).

[0098] One of the particularities of the invention lies in the fact that the guide element 8 further comprises at least one pair of gripping tabs 80. This pair of gripping tabs 80 participates in the retention of the guide element 8 on the first element 6. In addition, the pair of gripping tabs makes it possible to facilitate the assembly and / or disassembly of the guide element 8 in the first element 6, in particular by elastically deforming the guide element 8 at the pair of gripping tabs 80. This elastic deformation can be achieved by compression (or bringing together) of the two tabs of the pair of gripping tabs 80. The elastic deformation of the guide element 8 can be achieved for a short time, namely the time necessary to install and / or uninstall the guide element 8 on the first element 6.The guide element 8, in particular the pair of gripping tabs 80, can return to its initial shape after its installation.

[0099] It will be noted that the compression of the tabs also causes the elastic deformation of the first and second walls 84, 85. These walls 84, 85 (and in particular the pair of gripping tabs 80) can thus be deformed into a first position, called compression, in which the walls 84, 85 are brought together to allow the displacement (in particular by translation) of the guide element 8 in the guide housing 60 of the first element 6. The walls 84, 85 (and in particular the pair of gripping tabs 80) can also take a second position, called rest, in which the walls 84, 85 return to their initial shapes. In this second position, the tabs 80 cooperate with the holding members 62 so that the guide element 8 is held fixedly on the first element 6.

[0100] Advantageously, the pair of gripping tabs 80 extends outwardly (relative to the axis A) from a respective free end 840, 850 of the first and second side walls 84, 85. This configuration is illustrated in FIGS. 6 and 8 to 15. In a variant not illustrated, the pair of gripping tabs 80 extends projecting inwardly (relative to axis A) from the free ends 840, 850.

[0101] The pair of gripping tabs 80 may be integral with the first and second side walls 84, 85. In other words, the pair of gripping tabs 80 and the first and second side walls 84, 85 may be formed as a single piece (or in other words in a single piece).

[0102] The pair of gripping tabs 80 may extend substantially in a plane parallel to the axis A (as illustrated in FIGS. 6, 8, 9, 13a, 13b, 14 and 15) and / or in a plane perpendicular to the axis A (as illustrated in FIGS. 10, 11, 12a and 12b).

[0103] Each gripping tab 80 may comprise at least one flat portion (as illustrated in Figures 10, 11, 12a and 12b) or at least one L-shaped curved portion (as illustrated in Figures 6, 8, 9, 13a, 13b, 14 and 15).

[0104] The guide element 8 may comprise one or more pairs of gripping tabs 80.

[0105] When the guide element 8 comprises a pair of gripping tabs 80, this pair of tabs is preferably located at a median portion of the guide element 8, in particular between the first and second longitudinal ends 81, 82.

[0106] When the guide element 8 comprises several pairs of gripping tabs 80, these pairs of tabs are preferably distributed regularly along the axis A. By way of example, at least one pair of gripping tabs 80 is located upstream of the guide element 8, in particular at the first longitudinal end 81, and at least one pair of gripping tabs 80 is located downstream, in particular at the second longitudinal end 82.

[0107] Each gripping tab 80 may have a first length L80 ([Fig.13a]) which is measured along the axis A. This first length L80 may vary depending on the so-called gripping size (for example of the hole(s) 87 described below) particularly necessary to compress the pair of tabs during installation and / or uninstallation of the guide element. For example, the first length L80 is between 3 and 10 cm for a total length of the guide element of 100 cm. Preferably, the first length L80 is between 4 and 5 cm for a total length of the guide element of 100 cm. This makes it possible in particular to limit the size of the pair of gripping tabs in the guide assembly 9.

[0108] When the pair of gripping tabs 80 extends substantially in the plane parallel to the axis A, each gripping tab 80 may have a first width l80 which is measured relative to a plane transverse to the axis A. This first width l80 can be between 30 and 70% relative to a total width 183 of the bottom wall 83. For example, the first width l80 is between 7 and 18 mm for a total width 183 of 25 mm.

[0109] Advantageously, the pair of gripping tabs 80 is made of a material identical to that of the guide element 8.

[0110] For example, the pair of gripping tabs 80 is made of metal (such as aluminum), composite or thermoplastic.

[0111] Figures 6 to 15a and 15b show several embodiments of the guide assembly 9, and in particular of the guide element 8 and the second element 6, of the invention.

[0112] Another of the particularities of the invention is that the first element 6 comprises holding members 62. These holding members 62 are configured to receive a corresponding tab 80 of the pair of gripping tabs 80. Thus, these holding members 62 also participate in the retention of the guide element 8 on the first element 6.

[0113] Each holding member 62 may have a shape complementary to or substantially similar to that of the corresponding tab of the pair of gripping tabs 80.

[0114] These holding members 62 can be grooves ([Fig. 6] to 9), recesses ([Fig. 10]) or chamfers ([Fig. 11]).

[0115] With reference to [Fig.7], these holding members 62 can be arranged in pairs of holding members 62 in the guide assembly 9, in a similar manner to the pair of gripping tabs 80. Thus, two holding members 62 of a pair of holding members 62 are symmetrical with respect to each other by a median plane of symmetry C. This plane C is substantially perpendicular to the axis A.

[0116] Advantageously, the guide assembly 9 can also comprise the second element 7.

[0117] As described above, the second element 7 can be assembled at least partly in the opening 86 of the guide element 8. In this way, the second element 7 is configured to move, in particular by translation, along the guide element 8.

[0118] Figures 6 to 8 illustrate a first embodiment of the guide assembly 9 for retaining the guide element 8 on the first element 6.

[0119] The guide assembly 9 of the first embodiment comprises the first element 6 and at least one guide element 8 as described above.

[0120] The first element 6 may be integral with the front frame 52. For example, the first element 6 is the fixed beam (illustrated in [Fig.l]). This first element 6 may comprise a guide housing 60, for example a longitudinal slot along a longitudinal axis which is parallel to the axis A.

[0121] The guide housing 60 may be delimited between third and fourth side walls 64, 65 and a bottom 63 of the first element 6. The third and fourth side walls 64, 65 are connected to each other by the bottom 63.

[0122] The holding members 62 of the guide assembly 9 of the first embodiment are grooves. Each groove is configured to receive a corresponding tab of the pair of gripping tabs 80.

[0123] The grooves are notably provided on an external surface of the third and fourth side walls 64, 65.

[0124] Each groove may comprise a first bearing surface 62a. This first bearing surface 62a extends substantially in a plane parallel to the guide housing 60 (or to the axis A).

[0125] The third and fourth side walls 64, 65 may each comprise at least one second bearing surface 64a, 65a. These second bearing surfaces 64a, 65a extend substantially in a plane perpendicular to the guide housing 60 (or to the axis A).

[0126] One of the second bearing surfaces 64a, 65a extends in particular from one of the corresponding free ends 840, 850 of the third and fourth side walls 84, 85, and the first bearing surface 62a extends from this corresponding second bearing surface 64a, 65a.

[0127] [Fig.7] illustrates grooves which each extend in a plane parallel to the guide housing 60.

[0128] In the example of [Fig.7], the grooves are symmetrical with respect to each other by plan C.

[0129] Each groove may have a second length L62 (measured relative to a plane transverse to plane C or relative to axis A). This second length L62 may be identical to the first length L80.

[0130] Each groove 62 may have a second width 162 (measured relative to a plane perpendicular to plane C or relative to a plane transverse to axis A). This second width 180 may be identical to the first width 180.

[0131] One of the particularities of the guide element 8 of [Fig.6] is that the pair of gripping tabs 80 extends substantially in a plane parallel to the axis A.

[0132] Each gripping tab 80 comprises an L-shaped curved portion. This L-shaped curved portion may comprise a first bearing face 89a which extends substantially in a plane perpendicular to the axis A, and a second bearing face 89b which extends substantially in a plane parallel to the axis A.

[0133] The first bearing face 89a extends in particular from one of the free ends 840, 850 of the side walls 84, 85, and the second bearing face 89a extends from this first bearing face 89a. In the example of [Fig.6], the first and second bearing faces 89a, 89b have a planar shape.

[0134] When the guide element 8 is installed on the second element 6, the first bearing face 89a is configured to come into abutment against the corresponding second bearing surface 64a, 65a, and the second bearing face 89b is configured to come into abutment against the corresponding first bearing surface 62a.

[0135] [Fig. 8] illustrates a variant of the guide element 8 of [Fig. 6], in which the first bearing faces 89a of the pair of gripping tabs 80 have a curved shape. This curved shape makes it possible to reinforce the contact at the interface between the first bearing faces 89a and the second bearing surfaces 64a, 65a in the event of rotational movement of the guide assembly 9 in operation.

[0136] In this example of [Fig.8], the curved shape of the first bearing faces 89a comprises a concave part oriented towards the second bearing surfaces 64a, 65a.

[0137] As a variant (not illustrated) of [Fig.8], the second bearing surfaces 64a, 65a of the second element 6 also have a curved shape, preferably complementary to that of the first bearing faces 89a of the pair of gripping tabs 80.

[0138] In the examples of Figures 6 and 8, the two gripping tabs 80 of the pair of gripping tabs 80 have the same second width l80. The second width l80 of each gripping tab 80 may vary depending on the gripping size (in particular of the turn(s) 87) in particular necessary to compress the pair of tabs during installation and / or uninstallation of the guide element, and / or the so-called fixing size of a fixing device 90 (described below).

[0139] Another of the particularities of the guide assembly 9 of the first embodiment is that it further comprises at least one fixing device 90.

[0140] The fixing device 90 may be located upstream of the guide element, in particular on the first longitudinal end 81. Preferably, the fixing device 90 is on the bottom wall 83 of the first longitudinal end 81 (as shown in [Fig. 3a] of the prior art). This fixing device 90 thus makes it possible to secure the guide element 8 and the first element 6.

[0141] The fixing device 90 may comprise a screw 91, a shim 92 and a shouldered ring 93. The shouldered ring 93 may be interposed between a screw head 91 and the shim 92. In the example of FIGS. 6 and 8, the shouldered ring 93 extends through the shim 92, the bottom wall 83 and the bottom 63 to allow a solid fixing between the guide element 8 and the first element 6.

[0142] Alternatively (not shown), the fixing device 90 may also be located at the pair of gripping tabs 80 in the guide assembly 1 of the first embodiment. In this case, the fixing device 90 may comprise the screw 91, the shim 92 and the shouldered ring 93 according to the configuration illustrated in [Fig. 6], or may be simplified by having only one bolt for example.

[0143] The guide assembly 9 can also move the second element 7 relative to the first element 6 via the guide element 8. For this, the guide assembly 9 of the first embodiment can comprise the second element 7 (as in the configuration of [Fig.l]).

[0144] The second element 7 can be secured to the external cover 5.

[0145] For example, the second element is the slider (illustrated in [Fig.l]) which is able to move in, in particular the opening 86, the guide element 8.

[0146] [Fig.9] illustrates a second embodiment of the guide assembly 9 for retain the guide element 8 on the first element 6.

[0147] This guide assembly 9 of the second embodiment differs from the guide assembly 9 of the first embodiment by the absence of a fixing device 90 at the first longitudinal end 81 of the guide element 8.

[0148] The fastening device(s) 90 of the second embodiment are preferably located at the pair of gripping tabs 80. In this case, the fastening device 90 may comprise the screw 91, the shim 92 and the shouldered ring 93 according to the configuration illustrated in [Fig.6] or [Fig.8], or may be simplified by having only one bolt for example.

[0149] Figures 10 and 11 illustrate a third embodiment of the guide assembly 9 for retaining the guide element 8 on the first element 6. This guide assembly 9 of the third embodiment differs from the guide assembly 9 of the first and second embodiments by the pair of gripping tabs 80.

[0150] One of the particularities of the guide element 8 of figures 10 and 11 is that the pair of gripping tabs 80 extends substantially in the plane perpendicular to the axis A.

[0151] Each gripping tab 80 comprises a flat portion. This flat portion extends from one of the corresponding free ends 840, 850 of the first and second side walls 84, 85.

[0152] Each gripping tab 80 may comprise the first bearing face 89a which extends substantially in the plane perpendicular to the axis A. This first bearing face 89a has a planar shape in the examples of FIGS. 10 and 11. Alternatively (not shown), the first bearing faces 89a of the pair of gripping tabs 80 have a curved shape. The curved shape of the first bearing faces 89a comprises a concave portion oriented towards the second bearing surfaces 64a, 65a of the first element 6. In this variant, the second bearing surfaces 64a, 65a of the first element 6 may also have a curved shape, preferably complementary to that of the first bearing faces 89a of the pair of gripping tabs 80.

[0153] In a manner almost similar to the first and second embodiments, when the guide element 8 is installed on the first element 6, the first bearing face 89a of the third embodiment is configured to come into abutment against the corresponding second bearing surface 64a, 65a.

[0154] [Fig. 10] illustrates holding members 62 of the first element 6 which are similar to those of [Fig.7] (namely grooves or recesses of planar shape and extending in a plane parallel to the axis A).

[0155] Alternatively, the holding members 62 of [Fig. 11] are inclined (or in other words have a chamfer). This makes it possible in particular to facilitate the assembly and / or disassembly of the pair of gripping tabs 80 without damaging the first element 6. Thus, the first bearing surfaces 62a are inclined at an angle α. This angle α is measured between a plane transverse to the axis A and a plane perpendicular to the axis A which passes through the first bearing faces 89a. The angle α can be between 45° and 90°. In the example of [Fig. 11], the angle α is approximately 60° to form holding members 62 in the form of a chamfer. In the example of [Fig. 10], the angle a (not shown) is approximately 90° to form holding members 62 in the form of a recess or groove.

[0156] With reference to figures 12a, 12b, 13a, 13b, 14 and 15, we will now describe a method of assembling the guide assembly 9 described above.

[0157] The assembly method generally comprises the steps of: (a) providing the first element 6 and the guide element(s) 8 (as described above, in particular with reference to FIGS. 6 to 11), (b) compressing the gripping tabs 80, (c) translating the guide element 8 in the guide housing 60 of the first element 6 along the axis A, (d) releasing (or loosening) the gripping tabs 80 so that each tab of the pair of gripping tabs 80 cooperates in abutment with the corresponding holding member 62 to retain the guide element 8 on the first element 6.

[0158] This assembly method applies to the three embodiments described above.

[0159] Figures 12a and 12b illustrate, by way of example, steps (b) to (d) in the case of the guide assembly 9 according to the third embodiment.

[0160] The compression step (b) makes it possible in particular to bring the gripping tabs 80 closer together to facilitate the insertion of the guide element. 8 in the guide housing 60 of the first element. This makes it possible to reduce the dimension between the side walls 84, 85 and facilitate the assembly process.

[0161] Step (d) allows the pair of gripping tabs and the side walls 84, 85 (and consequently the entire guide element) to return to its initial shape before compression in step (b). The state of the guide element 8 before compression (or after step (d)) is called the “rest state”. Steps (b) to (d) can be carried out manually by an operator (in particular for the assembly of the guide assembly 9 of the third embodiment).

[0162] Alternatively, steps (b) to (d) may be carried out using one or more suitable tools T. The tool T may be a clamp, for example a thumbwheel or circlip clamp. For this purpose, each gripping tab 80 may comprise at least one orifice 88. The tool T is adapted to be removably fixed in the orifice 88 so as to compress and / or loosen the pair of gripping tabs 80, one relative to the other.

[0163] Figures 13a and 13b illustrate a first example of tooling T for assembling the guide element 8 in the second element 6. Each gripping tab 80 comprises two orifices 88 located on an upstream end and a downstream end of the gripping tab 80. The tooling T comprises a first rod T1, a second rod T2 opposite this first rod T1, and a wheel T3 connecting the first and second rods T1, T2 together. The first and second rods T1, T2 of the two tools T are inserted and fixed in the orifices 88 of the upstream and downstream ends of the pair of gripping tabs 80. The wheel T3 thus makes it possible to bring the gripping tabs 80 closer to and / or further away from each other. Advantageously, the second rod T2 may include a reverse thread to reinforce the action of the wheel T3.

[0164] Each gripping tab 80 may also comprise at least one hole 87. In the examples of Figures 13a, 14 and 15, each tab 80 comprises one or more holes 87 which are located between the orifices 88 of the upstream and downstream ends of the gripping tab 80. This hole 87 may serve as the main fixing (as produced by the fixing device 90 illustrated in Figures 6 and 8) of the guide element 8 on the first element 6

[0165] [Fig. 14] illustrates a second example of tooling T for assembling the guide element 8 in the second element 6. The tooling T of the second example differs from the tooling T of the first example by the presence of a single wheel T3 which connects the first and second rods T1, T2. Each of these first and second rods T1, T2 is connected to a third rod T3 which is inserted and fixed both in the orifices 88 of the upstream and downstream ends of the corresponding tab of the pair of gripping tabs 80.

[0166] [Fig. 15] illustrates a third example of tooling T for assembling the guide element 8 in the first element 6. The tooling T of the third example also comprises the first and second rods T1, T2 connected to each other by a clamp T5. Fourth rods T6 are also connected to the clamp T5 to be able to actuate this clamp T5 and thus bring the gripping tabs 80 closer to and / or further away from each other.

[0167] The tools T of figures 13a, 13b, 14 and 15 can also be used to disassemble the guide element 8 from the first element 6.

[0168] The assembly method may further comprise, after step (d), a step (e) of adding at least one fixing device 90 on at least one of the first 81 and second 82 longitudinal ends of the guide element and / or on the pair of gripping tabs 80.

[0169] Advantageously, the assembly method comprises a step (f) of inserting the second element 7 at least partly into the opening 86 of the guide element 8, for example by translation.

Claims

Claims

1. A guide assembly (9) for an aircraft propulsion assembly (10), the guide assembly (9) comprising a first element (6) and at least one guide element (8) fixed to the first element (6), the guide element (8) having a generally elongated shape along a longitudinal axis (A) between a first longitudinal end (81) and a second longitudinal end (82), the guide element (8) comprising: - a bottom wall (83), - two side walls (84, 85) connected to each other by the bottom wall (83), and - an opening (86) delimited between the bottom wall (83) and the side walls (84, 85), the opening (86) being intended to receive at least in part a second element (7) configured to move relative to the guide element (8),characterized in that the guide element (8) further comprises at least one pair of gripping tabs (80) cooperating with holding members (62) of the first element (6) to retain the guide element (8) on the first element (6), and in that the guide element (8) comprises several pairs of gripping tabs (80) distributed regularly along the axis (A).,

2. Guide assembly according to claim 1, characterized in that the pair of gripping tabs (80) extends substantially in a plane parallel or in a plane perpendicular to the axis (A).

3. A guide assembly according to claim 1 or 2, characterized in that the tabs of the pair of gripping tabs (80) and the walls (84, 85) are elastically deformable between a first position, in which the tabs and the walls (84, 85) are brought together, and a second position, in which said tabs cooperate with the holding members (62) to retain the guide element (8) on the first element (6).

4. A guide assembly according to any preceding claim, characterized in that said at least one pair of gripping tabs (80) extend outwardly from a free end (840, 850) of the side walls (84, 85).

5. A guide assembly according to any preceding claim, characterized in that each tab of the pair of gripping tabs (80) comprises at least one L-shaped curved portion.

6. Guide assembly according to any one of the preceding claims, characterized in that the holding members (62) are grooves (62), each groove (62) receiving a tab (80) of the pair of gripping tabs (80) of the guide element (8).

7. Guide assembly according to any one of the preceding claims, characterized in that it further comprises at least one fixing device (90) to at least one of the first and second longitudinal ends (81, 82) of the guide element and / or on said at least one pair of gripping tabs (80), the fixing device (90) being intended to secure the guide element (8) to the first element (6).

8. Guide assembly according to any one of the preceding claims, characterized in that the first element (6) comprises at least one pair of bearing surfaces (62a, 64a, 65a) complementary to the corresponding bearing faces (89a, 89b) of the pair of gripping tabs (80).

9. Thrust reverser for a nacelle (1) of an aircraft propulsion unit (10), the thrust reverser comprising at least one external cover (5) movable between a so-called closed position of the thrust reverser and a so-called open position of the thrust reverser, and a front frame (52), in which the external cover (5) is mounted so as to be movable in translation along at least one guide assembly (9) according to any one of the preceding claims.

10. A method of assembling at least one guide assembly (9) according to any one of claims 1 to 8, the method being characterized in that it comprises the steps of: (a) providing the first element (6) and said at least one guide element (8), (b) compressing the gripping tabs (80) of the guide element (8), (c) translating the guide element (8) into a guide housing (60) of the first element (6) along the longitudinal axis (A), (d) releasing the gripping tabs (80) so that each tab (80) of said at least one pair of gripping tabs cooperates in abutment with the holding member (62) corresponding to retain the guide element (8) on the first element (6).

Images