Installation for assembling a panel core and associated method

Abstract

The invention relates to an installation for assembling a core of a panel of a turbomachine comprising: - a fairing (12) having an exit slot (112) of an adhesive tape (106), - a first reel (104) for storing and distributing the adhesive tape (106) to the exit slot (112), the adhesive tape (106) being intended to be stored around the first reel (104) and having at least one face in contact with a first protective film (114, 116), - a second reel (108, 110) for retrieving the first protective film (114) mounted outside the fairing (12), - the second reel (108, 110) being configured to wind the protective film (114, 116) as the adhesive tape (106) is unwound from the first reel (104) towards the exit slot (112). Abbreviated figure: Figure 4

Description

Title of the invention: INSTALLATION FOR ASSEMBLING A CORE OF A PANEL AND ASSOCIATED METHOD Technical field of the invention

[0001] The invention relates to the field of installations for assembling a core of a panel for aircraft turbomachines.

[0002] The invention relates in particular to installations for the assembly, by gluing, of cores having a honeycomb structure.

[0003] The invention also relates to the field of methods for assembling a core for a panel of an aircraft turbomachine. Technical background

[0004] An aircraft turbomachine comprises, for example, from upstream to downstream in the direction of gas flow along a longitudinal axis, a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and a gas exhaust nozzle.

[0005] The blower allows the suction of an air flow dividing into a primary flow and a secondary flow. The primary flow passes through a primary vein of the turbomachine while the secondary flow is directed towards a secondary vein surrounding the primary vein.

[0006] The primary flow is compressed within the compressors. The compressed air is then mixed with a fuel and burned within the combustion chamber. The gases resulting from the combustion pass through the turbines and then escape through the nozzle, the cross-section of which allows the acceleration of these gases to generate propulsion.

[0007] The fan typically comprises a movable disc rotating about the longitudinal axis and blades mounted on the disc. The blades are surrounded by a fan casing centered on the longitudinal axis and intended to retain the blades in the event of damage, for example, to the blades.

[0008] The fan casing is typically surrounded by a nacelle which protects the fan. Such a fan is called ducted as opposed to unducted fans whose blades are not surrounded by a casing.

[0009] Turbomachines, and in particular blowers, are a significant source of noise pollution and there is a strong demand to reduce this type of pollution. To this end, it has been proposed to equip turbomachines with acoustic panels in order to reduce the noise generated by the blowers.

[0010] A panel, such as an acoustic panel, typically has a sandwich structure comprising first and second skins, and between which is arranged a core with a cellular structure, for example honeycomb, intended to attenuate sound waves. In the case of an acoustic panel, the second skin typically has holes allowing sound waves to propagate into the core through which they are absorbed.

[0011] The core typically comprises at least first and second structures, at least one of which may comprise alveolar cells, organized for example in a honeycomb, the structures being connected together by gluing during assembly of the core as part of the manufacture of the panel.

[0012] According to known techniques for assembling such a core, the first structure is deposited on the first skin and an adhesive strip is manually deposited on one edge of the first structure. Then, the second structure is deposited on the first skin, edge to edge with the first structure, thus forming the core of the panel.

[0013] Such a method of manufacturing the core has disadvantages. Indeed, the step of manually depositing the adhesive strip is tedious, long and therefore expensive. In addition, this manual deposit step is imprecise and leads to numerous non-conformities.

[0014] Therefore, there is a need to provide a solution allowing the manufacture of a core of a panel for an aircraft turbomachine, in a rapid, simple and precise manner. Summary of the invention

[0015] To this end, the invention proposes an installation for assembling a core of a panel of an aircraft turbomachine, the core comprising at least first and second structures, the first structure comprising a first joining edge bonded by an adhesive to a second joining edge of the second structure, the first and second structures respectively having first and second honeycomb cells, the installation comprising:

[0016] - a storage station for the first and second structures, and

[0017] - a station for bonding the first and second structures.

[0018] The installation is remarkable in that the gluing station comprises a gluing system comprising:

[0019] - a fairing having an exit slot for an adhesive tape,

[0020] - a first reel for storing and dispensing the adhesive tape to the slot output, the adhesive tape being intended to be stored around the first reel and having at least one contact face with a first protective film,

[0021] - a second return coil of the first protective film mounted on the outside of the fairing,

[0022] - the second reel being configured to wind the first protective film to the as the tape is unwound from the first spool to the exit slot.

[0023] Thanks to the gluing system of the invention, it is now possible to apply the adhesive tape simply, precisely and quickly. The assembly rates of the panel core are higher, thus allowing a considerable economic gain.

[0024] The invention may comprise one or more of the following features, taken in isolation from one another or in combination with one another:

[0025] - a third return reel of a second protective film, the adhesive tape having a second opposite face for contact with the second protective film, the second and third coils being mounted on either side of the fairing,

[0026] - the first, second and optionally third coils are rotatable around respectively of a first, second and third axis which are parallel to each other,

[0027] - the fairing is tapered towards the exit slot,

[0028] - the system comprises a device for cutting the adhesive tape,

[0029] - the system comprises an adhesive tape heating device mounted on the fairing,

[0030] - the system comprises an adhesive tape application device mounted on the fairing,

[0031] - the application device comprises a squeegee or roller configured to guide and apply the adhesive tape to the first and / or second joining edge at the exit of the fairing,

[0032] - the system comprises an adhesive tape cooling device arranged in the fairing.

[0033] The invention also relates to a method of assembling a core for a panel of an aircraft turbomachine, the core comprising at least a first and second structure, the first structure comprising a first joining edge bonded by an adhesive to a second joining edge of the second structure, the first and second structures respectively having first and second honeycomb cells, the assembly method implementing the installation according to any one of the preceding characteristics and comprising the following steps:

[0034] (a) providing the first structure,

[0035] (b) providing the second structure.

[0036] The method being remarkable in that it further comprises the following step:

[0037] (e) applying the adhesive tape to the first edge and / or the second joining edge of way of bonding the first and second structures together, the adhesive tape being applied using the system.

[0038] The method may comprise one or more of the following features, taken in isolation from each other or in combination with each other:

[0039] - before step (e), the method comprises the following steps:

[0040] (c) providing a first or second skin,

[0041] (d) placing the first and second structures on the first skin or second skin of so that the first joining edge is opposite the second joining edge,

[0042] - the method comprises the following steps carried out before step (e):

[0043] (c') provide a first or second skin,

[0044] (d') placing the first structure on the first or second skin,

[0045] and the following step carried out after step (e):

[0046] (f') placing the second structure on the first or second skin and edge to edge with the first structure so that the first joining edge is opposite the second joining edge,

[0047] - after step (e), the method comprises the following step:

[0048] (g) polymerizing the adhesive tape,

[0049] - the adhesive tape comprises an intumescent material. Brief description of the figures

[0050] Other characteristics and advantages will emerge from the following description of non-limiting embodiments of the invention with reference to the appended drawings in which:

[0051] [Fig.l] is a schematic representation in longitudinal section of a half aircraft turbomachine,

[0052] [Fig.2] is a schematic perspective representation of a panel according to the invention,

[0053] [Fig.3] is a schematic top view of the core of the panel of [Fig.2],

[0054] [Fig.4] is a schematic side and sectional view of a system for bonding of a soul according to an embodiment of the invention,

[0055] [Fig.5] is a schematic side and sectional view of a system for bonding a core according to another embodiment of the invention,

[0056] [Fig.6] is a schematic top and sectional view of the system of [Fig.5],

[0057] [Fig.7] is a flowchart of the assembly method of the invention according to a first embodiment,

[0058] [Fig.8] is a flowchart of the assembly method of the invention according to a second embodiment,

[0059] [Fig.9] is a perspective view of the core during the manufacturing process according to the first embodiment,

[0060] [Fig. 10] is a perspective view of a portion of the panel in a step of the manufacturing method according to the second embodiment,

[0061] [Fig.l 1] is a perspective view of a part of the panel in another step of the manufacturing method according to the second embodiment,

[0062] [Fig. 12] is a perspective view of a portion of the panel in another step of the manufacturing process according to the second embodiment. Detailed description of the invention

[0063] An example of a turbomachine 1 for an aircraft is shown in [Fig.l]. The turbomachine 1 extends around and along a longitudinal axis A.

[0064] In the present application, unless otherwise indicated, the terms “upstream” and “downstream” are defined in relation to the direction of circulation of the gases in the turbomachine 1 along the longitudinal axis A.

[0065] The terms “axial”, “axially”, “radial”, “radially” are defined with respect to the longitudinal axis A.

[0066] The terms “internal”, “interior”, “internally”, “external”, “exterior”, “externally”, are defined in relation to the distance from the longitudinal axis A along an axis Z perpendicular to the longitudinal axis A.

[0067] The turbomachine 1 is preferably a turbojet, for example a twin-spool, twin-flow turbojet. It comprises, from upstream to downstream, a fan 2, at least one compressor such as a low-pressure compressor 3 and a high-pressure compressor 4, a combustion chamber 5, at least one turbine such as a high-pressure turbine 6 and a low-pressure turbine 7, and a gas exhaust nozzle.

[0068] The low and high pressure compressors 3, 4 and the high and low pressure turbines 6, 7 each comprise at least one rotor. The rotor of the low pressure compressor 3 is connected to the rotor of the low pressure turbine 7 by a low pressure shaft 8 and the rotor of the high pressure compressor 4 is connected to the rotor of the high pressure turbine 6 by a high pressure shaft 9. The high pressure shaft 9 is arranged coaxially around the low pressure shaft 8. The low and high pressure shafts 8, 9 are centered on the longitudinal axis A.

[0069] The fan 2 comprises a disk movable in rotation about the longitudinal axis A and blades 10 extending radially from the disk. The fan 2 further comprises a fan shaft (not shown) connected to the low pressure shaft 8 via a speed reducer for example.

[0070] The blower 2 allows the suction of an air flow F dividing into a primary flow Fl and a secondary flow F2. The primary flow Fl passes through a primary vein vl of the turbomachine 1 and the secondary flow F2 flows into a secondary vein v2 of the turbomachine 1. The secondary vein v2 surrounds the primary vein vl.

[0071] The primary flow Fl is compressed within the low pressure compressor 3 then the high pressure compressor 4. The compressed air is then mixed with fuel and burned in the combustion chamber 5. The gases formed by the combustion pass through the high and low pressure turbines 6, 7. The gases finally escape through the nozzle, the cross-section of which allows the acceleration of these gases to generate propulsion.

[0072] The fan 2 is of the ducted type. The turbomachine 1 thus further comprises a fan casing 11. The fan casing 11 is annular and centered on the longitudinal axis A. It is arranged around the blades 10. The fan casing 11 forms a portion of the secondary vein v2.

[0073] The turbomachine 1 further comprises an intermediate casing 12. The intermediate casing 12 is arranged downstream of the fan casing 11. It is connected to the fan casing 11 for example by flanges.

[0074] The intermediate casing 12 is centered on the longitudinal axis A and comprises an inner shell 13 and an outer shell 14 connected by arms 15. The outer shell 14 is annular and centered on the longitudinal axis A. It is arranged coaxially around the inner shell 13. The outer shell 14 delimits with the inner shell 13 a portion of the secondary vein v2.

[0075] The turbomachine 1 further comprises a nacelle 16. The nacelle 16 is arranged around the fan and intermediate casings 11, 12.

[0076] In order to reduce the noise pollution generated by the turbomachine 1, the turbomachine 1 comprises at least one and advantageously acoustic panels 17 having a sandwich structure.

[0077] Each acoustic panel 17 extends over an angular sector or has an annular shape centered on the longitudinal axis A. Each acoustic panel 17 can be attached and fixed inside the fan casing 11 and / or inside the external shroud 14 of the intermediate casing 12 and / or inside the nacelle 16.

[0078] With reference to [Fig. 2], each acoustic panel 17 has a sandwich structure. Each acoustic panel 17 comprises at least one core 18, a first skin 19 and a second skin 20. The core 18 is sandwiched between the first and second skins 19, 20. When the acoustic panel 17 is mounted in the turbomachine 1, the second skin 20 is internal and the first skin 19 is external. The second skin 20 faces the secondary vein v2, and the first skin 19 is located opposite the secondary vein v2.

[0079] A plurality of cores may be superimposed in the acoustic panel 17 between the first and second skins 19, 20.

[0080] The first and second skins 19, 20 advantageously comprise a composite material. The composite material comprises, for example, a polymer matrix and fibers embedded in the matrix. The polymer of the matrix is, for example, a thermoplastic elastomer (TPE). Modurable such as epoxy resin or a thermoplastic such as polyethylene, polypropylene or fluoropolymer. Fibers are for example carbon, polyamide, polyester or glass fibers.

[0081] The first and second skins 19, 20 have a thickness for example between 1 mm and 10 mm.

[0082] The second skin 20 comprises holes (not visible) for the passage of sound waves. The holes are regularly distributed over the second skin 20. The holes are through holes and have a diameter for example between 0.5 mm and 2 mm.

[0083] Advantageously, the core 18 has a thickness of between 5 mm and 100 mm, and more advantageously between 10 mm and 40 mm.

[0084] The core 18 is composed of thin strips deployed over the thickness of the core 18 and formed and arranged between them to form the cellular core 18. The initial thickness of the strips is advantageously between 0.07 mm and 0.5 mm so that the core 18 is light and deformable to take the shape of the first and second skins 19, 20. The strips comprise for example a polymeric or metallic material such as aluminum, in particular an aluminum alloy chosen from the 3000, 5000, or 6000 series or a composite material which may comprise a polymeric matrix and possibly fibers. The polymer matrix is ​​chosen, for example, from thermoplastics such as polyphenylene sulfide (PPS), polyetherimide (PEI), polyetheretherketone (PEEK) or thermosets such as epoxy or phenolic resins. The fibers are, for example, glass, aramid or carbon fibers.

[0085] With reference to [Fig. 3], the core 18 comprises a plurality of cellular structures, in particular at least a first cellular structure 21 and a second cellular structure 22. The first and second cellular structures 21, 22 respectively have first and second cellular cells 21a, 22a advantageously organized in honeycombs. The first and second cellular cells 21a, 22a are delimited from one another by peripheral walls 21b, 22b. Each cellular cell 21a, 22a has, for example, a polygonal cross-section, for example square, rectangular or even hexagonal. The cross-section of the cellular cells 21a, 22a may differ from one cellular cell 21a, 22a to another. Each alveolar cell 21a, 22a is hollow and has an internal cavity 21c, 22c. The internal cavities 21c, 22c are delimited by the peripheral walls 21b, 22b.

[0086] The first and second structures 21, 22 advantageously have a polygonal shape. They are arranged edge to edge with each other. They respectively comprise at least a first and second joining edge 23, 24. The first and second joining edges 23, 24 are connected to each other by gluing. Thus, the core 18 further comprises an adhesive 25 connecting the first and second joining edges 23, 24.

[0087] The adhesive 25 advantageously comprises an organic matrix chosen for example from thermosetting polymers such as epoxy polymers. The adhesive 25 may advantageously further comprise an intumescent material. The intumescent material has the effect of causing the organic matrix to swell by foaming under the effect of a rise in temperature in order to promote the bond between the first and second structures 21, 22.

[0088] For the assembly of the core 18 of the acoustic panel 17, the invention proposes an installation comprising a storage station and a station for gluing the first and second structures 21, 22.

[0089] The storage station is for example located at the manufacturing station of the first and second structures 21, 22. It is for example merged with this manufacturing station.

[0090] According to the invention, the gluing station comprises a gluing system 100 illustrated for example in Figures 4 and 5.

[0091] The system 100 comprises a fairing 102, a first reel 104 for storing and dispensing an adhesive tape 106 and a second reel 108.

[0092] The fairing 102 is for example made of plastic or metallic material. It makes it possible to protect the various elements of the system 100. The fairing 102 extends between a first end 102a and a second end 102b. It comprises an exit slot 112 for the adhesive tape 106. The exit slot 112 is for example provided on the second end 102b.

[0093] Advantageously, the fairing 102 is tapered towards the second end 102b.

[0094] The fairing 102c is hollow and thus has an internal space 102c.

[0095] The first coil 104 is advantageously located in the internal space 102c of the fairing 102. The first coil 104 is cylindrical and has a first axis XL. It is advantageously movable in rotation around its first axis XL. The first coil 104 is located on the side of the first end 102a, therefore opposite the slot 112.

[0096] According to one embodiment, the first coil 104 is advantageously connected to a motor (not shown) making it possible to drive the first coil 104 in rotation.

[0097] The adhesive tape 106 comprises the uncured adhesive 25. The adhesive tape 106 has a thickness of between 0.1 mm and 10 mm and a width of between 5 mm and 100 mm.

[0098] With reference to [Fig.4], the adhesive tape 106 has at least a first contact face with a first protective film 114. The first protective film 114 makes it possible to limit the risks of the adhesive tape 106 sticking to itself and thus facilitates its deployment.

[0099] According to an advantageous embodiment of the invention illustrated in [Fig. 5], the adhesive tape 106 has a second opposite face for contact with a second protective film 116. The adhesive tape 106 is wound around the first reel 104 between the first and second protective films 114, 116. The first and second protective films 114, 116 further prevent the adhesive tape 106 from sticking to itself when it is stored around the first reel 104.

[0100] The first and second protective films 114, 116 comprise a polymeric or paper material. The first and second protective films 114, 116 have a thickness and / or a width, for example, identical to the thickness and width of the adhesive tape 106 or greater than the thicknesses and / or width of the adhesive tape 106.

[0101] The adhesive tape 106 and the first and second protective films 114, 116 are unwound tangentially from the first reel 104 towards the slot 112.

[0102] The first and second protective films 114, 116 are respectively recalled by second and third reels 108, 110. The second and third reels 108, 110 make it possible to recall the first and second protective films 114, 116 respectively as the adhesive tape 106 is unwound from the first reel 104 towards the exit slot 112.

[0103] The second and third coils 108, 110 are cylindrical and respectively have second and third axes X2, X3 around which they are respectively movable in rotation. The second and third axes X2, X3 are parallel to each other and to the first axis XL. The first coil 104 is movable in a first direction of rotation SI opposite to the direction of rotation S2 of the second and third coils 108, 110.

[0104] The second coil 108 is mounted outside the fairing 102 and is secured to this fairing 102. The second and third coils 108, 110 are advantageously mounted outside the fairing 102, on either side of the fairing 102. They are advantageously located on the side of the second end 102b. The second and third coils 108, 110 are located at an equal distance from the slot 112. Fasteners may be connected to the second and third coils 108, 110 in order to hold the first and second protective films 114, 116 on the second and third coils 108, 110. The fasteners are for example pins, clamps, clips or an adhesive.

[0105] Advantageously, the system 100 further comprises a gripping member 118 and a trigger 120 for actuating the first coil 104. The gripping member 118 and the trigger 120 are connected to the fairing 102 and are located on the side of the first end 102a.

[0106] Preferably, the system 100 further comprises a device 122 for cutting the adhesive tape 106 at the outlet of the fairing 102. The cutting device 112 is connected to the second end 102b of the fairing 102. It comprises, for example, a knife ultrasonic, a guillotine or a rotating disk configured to cut the adhesive tape 106 at the exit of the fairing 102.

[0107] Preferably, the system 100 further comprises a heating device 124. The heating device 124 is for example connected to the fairing 102. It comprises for example a laser 124a emitting R rays in the direction of the adhesive tape 106 at the outlet of the fairing 102. The heating device 124 makes it possible to heat the adhesive tape 106 in order to promote its adhesion to the core 18.

[0108] Preferably, the system 100 further comprises a device 126 for applying the adhesive tape 106. The application device 126 makes it possible to exert a force on the adhesive tape 106 at the outlet of the fairing 102 to promote its deposition and adhesion to the first and / or second structures 21, 22. The application device 126 is connected to the fairing 102. Advantageously, the application device 126 comprises a squeegee or a roller 126a located on the side of the second end 102b and upstream of the slot 112 relative to the direction of movement of the system 100, from left to right in particular in [Fig. 4]. The squeegee or roller 126a is configured to guide and apply the adhesive tape 106 to the first and / or second joining edge 23, 24 at the exit of the slot 112. The squeegee or roller 126a comprises a polymer material selected for example from fluoropolymers such as polytetrafluoroethylene.Such a material makes it possible to limit the adhesion between the squeegee or roller 126a and the adhesive tape 106.

[0109] Advantageously, the system 100 further comprises a cooling device 128 for the adhesive tape 106. The cooling device 128 makes it possible to promote the detachment of the first and second protective films 114, 116. The cooling device 128 is located inside the fairing 102. The cooling device 128 may for example be a venturi tube.

[0110] In order to facilitate and accelerate the deposition of the adhesive tape 106, the system 100 advantageously comprises a robot which is capable of moving the fairing 102 in at least three directions perpendicular to each other. The robot comprises, for example, an articulated arm at the end of which the fairing 102 is mounted. The robot is, for example, a standard six-axis robot, placed on the ground or mounted on a linear axis.

[0111] A method of assembling the core 18 of the acoustic panel 17 will now be described with reference to FIGS. 7 and 8. The method comprises the following steps:

[0112] (a) providing the first structure 21,

[0113] (b) providing the second structure 22,

[0114] (e) applying the adhesive tape 106 using the bonding system 100, on the first edge and / or the second joining edge 23, 24 so as to bond the first and second structures 21, 22 together, and

[0115] (g) advantageously, polymerizing the adhesive tape 106.

[0116] Steps (a) and (b) can be carried out simultaneously. The first and second structures 21, 22 can be manufactured by additive manufacturing or by folding the strips.

[0117] Step (e) may comprise the following sub-steps:

[0118] (eO) loading the first reel 104 with the adhesive tape 106 and the first and possibly second protective films 114, 116,

[0119] (el) winding the first and second protective films 114, 116 respectively around the second and possibly third reels 108, 110,

[0120] (e2) unroll the adhesive tape 106, and

[0121] (e3) optionally cut the adhesive tape 106.

[0122] According to a first example, sub-step (e2) can be carried out by traction. According to this example, the operator positions the system 100 on one of the joining edges 23, 24 or on the first or second skin 19, 20 and pulls on the system 100 to actuate the first coil 104.

[0123] According to a second example, sub-step (e2) can be carried out in an automated manner. According to this example, the operator actuates the trigger 120 to actuate the first reel 104 and unwind the adhesive tape 106.

[0124] With reference to [Fig.7], according to a first embodiment of the method, before step (e), the method comprises the following steps:

[0125] (c) providing the first or second skin 19, 20,

[0126] (d) placing the first and second structures 21, 22 on the first skin or the second skin 19, 20 so that the first joining edge 23 is opposite the second joining edge 24.

[0127] Step (c) can be carried out by additive manufacturing, or by draping or even by molding.

[0128] According to this embodiment, as illustrated in [Fig.9], during step (e), the system 100 is placed between the first and second joining edges 23, 24. The system 100 is then moved in a direction D parallel to the plane of the first or second skin 19, 20 and allowing the application of the adhesive tape 106 on the first and second joining edges 23, 24 simultaneously.

[0129] With reference to Figures 8 and 10, according to a second embodiment of the method, the method comprises the following steps carried out before step (e):

[0130] (c') provide the first or second skin 19, 20,

[0131] (d') placing the first structure 21 on the first second skin 19, 20.

[0132] Step (c') can be carried out by additive manufacturing, or by draping or even by molding.

[0133] According to this second embodiment, as illustrated in [Fig.l 1], during step (e), the adhesive tape 106 is applied to the first or second joining edge 23, 24 and advantageously on all the edges of the first or second structure 21, 22 using the system 100.

[0134] According to this second embodiment, as illustrated in [Fig. 12], after step (e), the method comprises the following step:

[0135] (f') placing the second structure 22 on the first second skin 19, 20 and edge to edge with the first structure 21 so that the first joining edge 23 is opposite the second joining edge 24.

[0136] The polymerization step (g) can be carried out by heat treatment of the adhesive tape 106. The heat treatment is carried out for example at a temperature between 50°C and 150°C.

[0137] Step (g) can be carried out with or after the deposition of the first or second skin 19, 20 on the core 18.

[0138] The invention has been described with reference to an acoustic type panel but can be applied to the assembly of any panel core having at least two structures assembled by gluing.

[0139] Thanks to the gluing system 100 of the invention, it is now possible to apply the adhesive tape 106 simply, precisely and quickly. The assembly rates of the core 18 of the acoustic panel 17 are higher, thus allowing a considerable economic gain.

Claims

Claims

1. Installation for assembling a core (18) of a panel (17) of an aircraft turbomachine (1), the core (18) comprising at least first and second structures (21, 22), the first structure (21) comprising a first joining edge (23) bonded by an adhesive (25) to a second joining edge (24) of the second structure (22), the first and second structures (21, 22) respectively having first and second honeycomb cells (21a, 22a), the installation comprising: - a station for storing the first and second structures (21, 22), and - a station for bonding the first and second structures (21, 22), characterized in that the bonding station comprises a bonding system (100) comprising: - a fairing (12) having an outlet slot (112) for an adhesive tape (106), - a first reel (104) for storing and dispensing the adhesive tape (106) to the exit slot (112),the adhesive tape (106) being intended to be stored around the first reel (104) and having at least one contact face with a first protective film (114, 116), - a second reel (108, 110) for returning the first protective film (114) mounted outside the fairing (12), - the second reel (108, 110) being configured to wind the first protective film (114, 116) as the adhesive tape (106) is unwound from the first reel (104) towards the exit slot (112).,

2. Installation according to the preceding claim, characterized in that the system (100) further comprises a third reel (110) for returning a second protective film (116), the adhesive tape (106) having a second opposite face for contact with the second protective film (116), the second and third reels (108, 110) being mounted on either side of the fairing (102).

3. Installation according to any one of the preceding claims, characterized in that the first, second and optionally third coils (104, 108, 110) are rotatable around respectively a first, second and third axis (XI, X2, X3) which are parallel to each other.

4. Installation according to any one of the preceding claims, characterized in that the fairing (102) is tapered towards the outlet slot (112).

5. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a device (122) for cutting the adhesive tape (106).

6. Installation according to any one of the preceding claims, characterized in that the system (102) comprises a heating device (124) for the adhesive tape (106) mounted on the fairing (102).

7. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a device (126) for applying the adhesive tape (106) mounted on the fairing (102).

8. Installation according to the preceding claim, characterized in that the application device (126) comprises a squeegee or roller (126a) configured to guide and apply the adhesive tape (106) to the first and / or second joining edge (23, 24) at the outlet of the fairing (102).

9. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a cooling device (128) for the adhesive tape (106) arranged in the fairing (102).

10. A method of assembling a core (18) for a panel (17) of an aircraft turbomachine (1), the core (18) comprising at least a first and a second structure (21, 22), the first structure (21) comprising a first joining edge (23) bonded by an adhesive (25) to a second joining edge (24) of the second structure (22), the first and second structures (21, 22) respectively having first and second honeycomb cells (21a, 22a), the assembly method implementing the installation according to any one of the preceding claims and comprising the following steps: (a) providing the first structure (21), (b) providing the second structure (22), characterized in that the method further comprises the following step: (e) applying the adhesive tape (106) to the first edge and / or the second joining edge (23, 24) so ​​as to bond the first and second structures (21, 22) between them,the adhesive tape (106) being applied using the system (100).,

11. Method according to the preceding claim, characterized in that before step (e), the method comprises the following steps: (c) providing a first or second skin (19, 20), (d) placing the first and second structures on the first skin (19) or second skin (20) so that the first joining edge (23) faces the second joining edge (24).

12. Method according to claim 10, characterized in that it comprises the following steps carried out before step (e): (c') providing a first or second skin (19, 20), (d') placing the first structure (21) on the first or second skin (19, 20), and the following step carried out after step (e): (f') placing the second structure (22) on the first or second skin (19, 20) and edge to edge with the first structure (21) so that the first joining edge (23) is opposite the second joining edge (24).

13. Method according to any one of claims 10 to 12, characterized in that it further comprises after step (e), the following step: (g) polymerizing the adhesive tape (106).

14. A method according to any one of claims 10 to 13, characterized in that the adhesive tape (106) comprises an intumescent material.

Images