Installation for assembling the core of a panel and associated method

Abstract

The invention relates to an installation for assembling the core of a panel of an aircraft turbine engine, comprising a bonding system (100) comprising: - a member (102) for storing and dispensing the adhesive (25), and - a nozzle (104) for ejecting the adhesive (25), the nozzle (104) extending between a first open end (106) connected to the storing and dispensing member (102) and a second open opposite end (108) for discharging the adhesive (25), the nozzle (104) further comprising an internal passage (105) for the adhesive (25), extending between the first and second ends (106, 108).

Description

[0001] DESCRIPTION

[0002] TITLE: INSTALLATION FOR ASSEMBLING A PANEL CORE AND ASSOCIATED METHOD

[0003] Technical field of the invention

[0004] The invention relates to the field of installations for assembling a core of a panel for aircraft turbomachines.

[0005] The invention relates in particular to installations for the assembly, by gluing, of cores having a honeycomb structure.

[0006] The invention also relates to the field of methods for assembling a core for a panel of an aircraft turbomachine.

[0007] Technical background

[0008] The state of the art is illustrated by document EP-A1-4122695.

[0009] 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.

[0010] The blower allows the suction of an air flow divided 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.

[0011] The primary flow is compressed within the compressors. The compressed air is then mixed with fuel and burned within the combustion chamber. The gases 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. The fan typically comprises a mobile disc rotating around the longitudinal axis and blades mounted on the disc. The blades are surrounded by a fan casing centered on the longitudinal axis and designed to retain the blades in the event of damage, for example, to the blades.

[0012] The fan casing is typically surrounded by a nacelle that protects the fan. Such a fan is called a shrouded fan, as opposed to unshrouded fans, whose blades are not surrounded by a shroud.

[0013] Turbomachinery, particularly fans, is 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 fan casings, for example, with acoustic panels to reduce the noise generated by the fans.

[0014] A panel, such as an acoustic panel, typically has a sandwich structure comprising first and second skins, and between which is arranged a core having a cellular structure, for example a honeycomb, intended to attenuate sound waves. In the case of an acoustic panel, the second skin typically has holes allowing sound waves to propagate in the core through which they are absorbed.

[0015] 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.

[0016] 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. 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.

[0017] Therefore, there is a need to provide a solution that enables the manufacture of a core of a panel for an aircraft turbomachine, quickly, simply and accurately.

[0018] Summary of the invention

[0019] 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:

[0020] - a storage station for the first and second structures, and

[0021] - a gluing station for the first and second structures.

[0022] The invention is remarkable in that the gluing station comprises a gluing system comprising:

[0023] - an adhesive storage and distribution device, and

[0024] - an adhesive ejection nozzle, the nozzle extending between a first open end connected to the dispensing storage member and a second opposite open adhesive outlet end, the nozzle further comprising an internal adhesive passage extending between the first and second ends, the second end of the nozzle being beveled.

[0025] Thanks to the gluing system of the invention, it is now possible to apply the adhesive simply, precisely and quickly. The assembly rates of the panel core are higher, thus allowing a considerable economic gain. The invention may include one or more of the following features, taken in isolation from each other or in combination with each other:

[0026] - the nozzle extends along an elongation axis which forms an angle with a plane containing the second end of less than 45°, preferably less than 25°,

[0027] - the second end has a circular or elliptical section,

[0028] - the internal passage has a first channel and at least one second channel for the passage of the adhesive,

[0029] - the system includes a device for heat treatment of the adhesive,

[0030] - the heat treatment device comprises a nozzle heating device and / or an adhesive cooling device connected to the storage and distribution member,

[0031] - the system includes an adhesive application device mounted on the nozzle,

[0032] - the application device comprises a squeegee mounted on the second end of the nozzle and configured to guide and apply the adhesive to the first and / or second joining edge.

[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) provide the first structure,

[0035] (b) provide the second structure.

[0036] The method is remarkable in that it further comprises the following step (e) applying an adhesive to the first edge and / or the second joining edge so as to bond the first and second structures together, the adhesive being applied using the system.

[0037] The method may comprise one or more of the following features, taken in isolation from each other or in combination with each other:

[0038] - before step (e), the method comprises the following steps:

[0039] (c) provide a first skin,

[0040] (d) placing the first and second structures on the first skin so that the first joining edge faces the second joining edge,

[0041] - it comprises between steps (d) and (e), a step of spacing the first and second joining edges,

[0042] - it includes the following steps carried out before step (e):

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

[0044] (d) placing the first structure on the first skin, and the next step carried out after step (e):

[0045] (f') placing the second structure on the first skin and edge to edge with the first structure so that the first joining edge is opposite the second joining edge,

[0046] - it also includes the following step:

[0047] (g) cure the adhesive,

[0048] - the adhesive includes an intumescent material.

[0049] 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: Figure 1 is a schematic representation in longitudinal section of a half-turbomachine of an aircraft, Figure 2 is a schematic representation in perspective of a panel according to the invention, Figure 3 is a schematic top view of the core of the panel of Figure 2, Figure 4 is a schematic side and sectional view of a system for bonding a core according to the invention, Figure 5 is a schematic top and sectional view of the system for bonding a core according to the invention, Figure 6 is a perspective view of a nozzle equipping the system of Figure 5, Figure 7 is a perspective view of a nozzle according to another embodiment, Figure 8 is a longitudinal sectional view of a nozzle according to another embodiment,Figure 9 is a side view and in longitudinal section of a nozzle equipped with an application device, Figure 10 is a side view and in longitudinal section of a nozzle equipped with an application device according to another embodiment, Figure 11 is a longitudinal section view of a nozzle equipped with an adjustment and stabilization device, Figure 12 is a longitudinal section view of a nozzle equipped with an adjustment and stabilization device according to another embodiment, Figure 13 is a flowchart of the assembly method of the invention according to a first embodiment, Figure 14 is a flowchart of the assembly method of the invention according to a second embodiment, Figure 15 is a side view and in longitudinal section of a nozzle during step (e) of the method, Figure 16 is a perspective view of the core during the manufacturing method according to the first embodiment,Figure 17 is a perspective view of a portion of the acoustic panel in one step of the manufacturing method according to the second embodiment, Figure 18 is a perspective view of a portion of the acoustic panel in another step of the manufacturing method according to the second embodiment, Figure 19 is a perspective view of a portion of the acoustic panel in another step of the manufacturing method according to the second embodiment.,

[0051] Detailed description of the invention

[0052] An example of a turbomachine 1 for an aircraft is shown in Figure 1. The turbomachine 1 extends around and along a longitudinal axis A.

[0053] In this 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.

[0054] The terms "axial", "axially", "radial", "radially" are defined in relation to the longitudinal axis A.

[0055] The terms "internal", "interior", "internally", "external", "externally", "externally", are defined with respect to the distance from the longitudinal axis A along an axis Z perpendicular to the longitudinal axis A. 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.

[0056] 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.

[0057] 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.

[0058] The blower 2 allows the suction of an air flow F dividing into a primary flow F1 and a secondary flow F2. The primary flow F1 passes through a primary vein v1 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 v1.

[0059] The primary flow F1 is compressed within the low pressure compressor 3 then the high pressure compressor 4. The compressed air is then mixed with a fuel and burned within the combustion chamber 5. The gases formed by the combustion pass through the high pressure and low pressure turbines 6, 7. The gases finally escape through the nozzle, the section of which allows the acceleration of these gases to generate propulsion.

[0060] The fan 2 is of the shrouded 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.

[0061] The turbomachine 1 further comprises an intermediate casing 12. The intermediate casing 12 is arranged downstream of the fan casing 11. 11 is connected to the fan casing 11, for example, by flanges.

[0062] 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.

[0063] The turbomachine 1 further comprises a nacelle 16. The nacelle 16 is arranged around the fan and intermediate casings 11, 12.

[0064] 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.

[0065] 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.

[0066] Referring to Figure 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 external. The second skin 20 faces the secondary vein v2, and the first skin 19 is located opposite the secondary vein v2.

[0067] A plurality of cores may be superimposed in the acoustic panel 17 between the first and second skins 19, 20.

[0068] 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 thermoset such as an epoxy resin or a thermoplastic such as polyethylene, polypropylene or a fluoropolymer. The fibers are, for example, carbon, polyamide, polyester or glass fibers.

[0069] The first and second skins 19, 20 have a thickness for example between 1 mm and 10 mm. The second skin 20 comprises holes (not visible) for the passage of sound waves. The holes are regularly distributed on the second skin 20. The holes are through and have a diameter for example between 0.5 mm and 2 mm.

[0070] Advantageously, the core 18 has a thickness generally between 5 mm and 100 mm, and more advantageously between 10 mm and 40 mm.

[0071] The core 18 is composed of thin strips deployed over the thickness of the core 18 and formed and arranged together 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 that may comprise a polymeric matrix and optionally fibers. The polymeric matrix is ​​chosen, for example, from thermoplastics such as a polyphenylene sulfide (PPS), a polyetherimide (PEI), a polyetheretherketone (PEEK), thermosets such as epoxy or phenolic resins. The fibers are, for example, glass, aramid or carbon fibers.

[0072] With reference to Figure 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 honeycomb cellular cells 21a, 22a. For an acoustic sandwich panel, the first and second cellular cells 21a, 22a form Helmholtz resonators. The first and second cellular cells 21a, 22a are delimited from each other by peripheral walls 21b, 22b. Each cellular cell 21a, 22a has, for example, a polygonal cross-section, for example square, rectangular or hexagonal. The cross-section of the alveolar cells 21a, 22a may differ from one alveolar 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.

[0073] 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.

[0074] The first and second structures 21, 22 have a height H as measured along the direction of propagation of the P waves in the core 18 equal to the thickness of the core 18.

[0075] The core 18 further comprises an adhesive 25 connecting the first and second joining edges 23, 24.

[0076] 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.

[0077] For the assembly of the first and second structures 21 and 22 of the core 18 of the sandwich panel 17, the invention proposes an installation comprising a storage station and a station for gluing the first and second structures 21, 22 together.

[0078] 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.

[0079] According to the invention, the gluing station comprises a gluing system 100 illustrated for example in Figures 4 and 5.

[0080] The system 100 comprises a storage and distribution member 102 for the adhesive 25 and a nozzle 104 for ejecting the adhesive 25. The storage and distribution member 102 has a body 102a defining an internal storage space 102b in which the adhesive 25 is located. The internal storage space 102b may be under pressure. The body 102a has an inlet and an outlet for the adhesive 25. A piston (not shown) may be located in the body 102a to allow the adhesive 25 to be moved to the outlet.

[0081] The nozzle 104 is connected to the body 102a. The nozzle 104 is tubular. It extends along an elongation axis X between a first end 106 and an opposite second end 108. Advantageously, the nozzle 104 has a length L as measured along the elongation axis X of between 5 mm and 200 mm.

[0082] The nozzle 104 further has an internal passage 105 for the adhesive 25 extending between the first and second ends 106, 108.

[0083] The first end 106 is fixed to the body 102a of the storage and distribution member 102 and the second end 108 is free. The first and second ends 106, 108 are open and the internal passage opens into the first and second ends 106, 108.

[0084] As best seen in Figure 6, the first end 106 has a circular or elliptical cross-section. It has a large diameter D of between 1 mm and 40 mm and a small diameter less than the large diameter D. The small diameter is for example between 0.5 mm and 4 mm, preferably between 0.8 mm and 2 mm. The large diameter D is advantageously between 70% and 120% of the height H of the first and second structures 21, 22, preferably between 75% and 95% of this height H.

[0085] According to an advantageous embodiment of the invention illustrated in Figure 6, the second end 108 is beveled. According to this example, the elongation axis X forms an angle α with a plane P containing the second end 108 less than 90°, preferably less than 45°, even more preferably less than 25°. According to another advantageous embodiment of the invention illustrated in Figures 7 and 8, the second end 108 has a cross-section of elliptical or circular shape. According to this example, the second end 108 has a large diameter D' of between 5 mm and 40 mm and a small diameter less than the large diameter D' and of between 0.5 mm and 2 mm.

[0086] The internal passage has, for example, an internal diameter of between 0.5 mm and 3 mm and advantageously between 0.7 mm and 1.5 mm.

[0087] According to an advantageous embodiment illustrated in FIG. 8, the internal passage has a first channel 110 and at least one second channel 112 for the flow of the adhesive 25. The first and second channels 110, 112 advantageously extend between the first and second ends 106, 108 and open onto the first and second ends 106, 108. Such an embodiment makes it possible to create several distribution zones for the adhesive 25. Thus, it is possible to modulate the quantity of adhesive 25 distributed in each channel 110, 112 in order to distribute a quantity of adhesive 25 specific to the zone in which the adhesive 25 is applied.

[0088] Preferably, the system 100 further comprises a device 114 for heat treatment of the adhesive 25. The heat treatment device 114 is for example fixed to the storage and distribution member 102.

[0089] The heat treatment device 114 comprises, for example, a device for heating the nozzle 104. It comprises, for example, a laser emitting rays in the direction of the nozzle 104. The heating device makes it possible to heat the adhesive 25 in the nozzle 104 in order to adjust its viscosity and promote its flow in the nozzle 102.

[0090] The heat treatment device 114 further or alternatively comprises a cooling device. It comprises, for example, a venturi tube for delivering air towards the second end 108 of the nozzle 104. The cooling device makes it possible to cool the adhesive 25 at the outlet of the nozzle 104 in order to limit thermal damage during the deposition of the adhesive 25, for example, on the first or second skins 19, 20.

[0091] Advantageously, the system 100 further comprises a detection device 116 for the adhesive 25 attached to the storage and dispensing member 102. The detection device 116 comprises, for example, a sensor making it possible to detect the presence, absence, and possibly the volume of adhesive 25 present in the storage and dispensing member 102.

[0092] Advantageously, the system 100 further comprises a location device 118 attached to the storage and distribution member 102. The location device 118 comprises, for example, a camera making it possible to view the injection zone of the adhesive 25 and to measure the width, for example, of the injection zone. The location device 118 can be connected to an image analysis station. Such a feature allows more precise bonding of the core 18.

[0093] Preferably, with reference to Figures 9 and 10, the system 100 further comprises an application device 120 for the adhesive 25 mounted on the nozzle 104. The application device 120 comprises a squeegee 120a mounted on the second end 108 of the nozzle 104. The squeegee 120a is configured to guide and apply the adhesive 25 to the first and / or second joining edge 23, 24 at the outlet of the nozzle 104.

[0094] According to the example of Figure 9, the squeegee 120a extends in the extension of the nozzle 104 along the elongation axis X. In certain configurations, the first and second alveolar cells 21a, 22a are nested within each other and the nozzle 104 cannot be positioned between the first and second structures 21, 22 to apply the adhesive 25 over the entire height H of the first and second structures 21, 22. Such a squeegee 120a can be inserted between the first and second structures 21, 22 to apply the adhesive 25 over this entire height H.

[0095] In the example of Figure 10, the squeegee 120a is oriented parallel to the first or second joining edge 23, 24. In the case where the adhesive 25 is in a viscous state, the squeegee 120a makes it easier to deposit the adhesive 25 on the first or second joining edge 23, 24.

[0096] The squeegee 120a comprises a polymer material chosen for example from fluorinated polymers such as polytetrafluoroethylene. Such a material makes it possible to limit the adhesion between the squeegee 120a and the adhesive 25. According to an advantageous embodiment of the invention illustrated in FIGS. 11 and 12, the system 100 further comprises a device 122 for adjusting and stabilizing the position of the nozzle 104 along its elongation axis X relative to the first and second structures 23, 24. The adjustment and stabilization device 122 is connected to the nozzle 104 and configured to bear on at least one of the first and second structures 23, 24.

[0097] According to a first example illustrated in FIG. 11, the adjustment and stabilization device 122 comprises at least one foot 124 connected to the nozzle 104. The foot 124 has a connecting end 124a connected to the nozzle 104 and an opposite positioning end 124b intended to rest on the first or second structure 23, 24. Preferably, the positioning end 124b has a U or J shape. This makes it possible to promote the movement of the adjustment and stabilization device 122 on the first or second structure 23, 24 during the movement of the system 100 during the application of the adhesive 25.

[0098] According to a second example illustrated in Figure 12 (also visible in Figure 7), the adjustment and stabilization device 122 comprises first and second rollers 126. The first and second rollers 126 are arranged on either side of the nozzle 104. The first and second rollers 126 each have an axis extending perpendicular to the elongation axis X of the nozzle 104. The first and second rollers 126 are preferably movable in rotation about their axis. This makes it possible to promote the movement of the system 100 during the application of the adhesive 25. In order to facilitate and accelerate the deposition of the adhesive 25, the system 100 advantageously comprises a robot 130 which is capable of moving the nozzle 104 and the storage and distribution member 102 in at least three directions perpendicular to each other. The robot 130 comprises, for example, an articulated arm 132 at the end of which the storage and distribution member 102 is mounted.The 130 robot is, for example, a standard six-axis robot, placed on the ground or mounted on a linear axis.

[0099] The installation may further comprise a spacing device comprising, for example, shims positioned between the first and second structures 21, 22 in order to fix the width of the injection zone of the adhesive 25. The shims have a width, for example, between 0.2 mm and 2 mm, preferably between 0.2 mm and 1 mm.

[0100] A method of assembling the core 18 of the acoustic panel 17 will now be described with reference to Figures 13 and 14. The method comprises the following steps:

[0101] (a) provide the first structure 21,

[0102] (b) providing the second structure 22,

[0103] (e) applying, using the bonding system 100, the adhesive 25 to the first edge and / or the second joining edge 23, 24 so as to bond the first and second structures 21, 22 together, and

[0104] (g) advantageously polymerizing the adhesive 25.

[0105] 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.

[0106] Step (e) may include the following sub-steps:

[0107] (eO) filling the storage member 102 with adhesive 25,

[0108] (e1) possibly heat the nozzle 104,

[0109] (e2) possibly detecting the injection zone of the adhesive 25, and

[0110] (e3) position nozzle 104.

[0111] With reference to Figure 15, during step (e3), the orientation £ of the second end 108 of the nozzle 104 can be adjusted relative to the first and second edges 23, 24 and the height h' of the nozzle 104 can be adjusted relative to the height H of the first and second structures 21, 22.

[0112] With reference to Figure 16, according to a first embodiment of the method, before step (e), the method comprises the following steps:

[0113] (c) provide the first or second skin 19, 20,

[0114] (d) placing the first and second structures 21, 22 on the first skin 19 or the second skin 20 so that the first joining edge 23 is opposite the second joining edge 24.

[0115] Step (c) can be carried out by additive manufacturing, or by draping or even by molding.

[0116] According to this embodiment, during step (e), the system 100 is placed above the junctions and the nozzle 104 and the second end 108 are inserted between the first and second junction edges 23, 24 as illustrated in FIG. 16. The system 100 is then moved in a direction D allowing the application of the adhesive 25 on the first and second junction edges 23, 24 simultaneously.

[0117] According to one embodiment, the first and second joining edges 23, 24 are juxtaposed. In this configuration, the nozzle 104 penetrates between the first and second structures 21, 22 by deforming the peripheral walls 21b, 22b of the alveolar cells 21a, 22a.

[0118] According to another embodiment, between steps (d) and (e), the method comprises a step of spacing the first and second joining edges 23, 24. The spacing device is positioned between the first and second structures 21, 22 so as to define a spacing between the joining edges 23, 24. The spacing device is then removed in order to allow the nozzle 104 to pass between the first and second structures 21, 22.

[0119] With reference to figures 17 to 19, according to a second embodiment of the method, the method comprises the following steps carried out before step

[0120] (e):

[0121] (c') provide the first or second skin 19, 20,

[0122] (d') placing the first structure 21 on the first second skin 19, 20. Step (c') can be carried out by additive manufacturing, or by draping or even by molding.

[0123] According to this second embodiment, as illustrated in FIG. 18, during step (e), the adhesive 25 is applied to the first or second joining edge 23, 24 and advantageously to all the edges of the first or second structure 21, 22 using the system 100.

[0124] According to this second embodiment, as illustrated in Figure 19, after step (e), the method comprises the following step:

[0125] (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.

[0126] The polymerization step (g) can be carried out by heat treatment of the adhesive 25. The heat treatment is carried out for example at a temperature between 50°C and 200°C.

[0127] The polymerization step (g) can be carried out before or after a step of depositing the first or second skin 19, 20 on the core 18.

[0128] The first or second skin 19, 20 can be produced by additive manufacturing, or by draping or even by molding.

[0129] 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.

[0130] Thanks to the gluing system 100 according to the invention, it is now possible to deposit the adhesive 25 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 storage station for the first and second structures (21, 22), and - a gluing station for the first and second structures (21, 22), characterized in that the gluing station comprises a gluing system (100) comprising: - a storage and distribution member (102) for the adhesive (25), and - a nozzle (104) for ejecting the adhesive (25), the nozzle (104) extending between a first open end (106) connected to the dispensing storage member (102) and a second open opposite end (108) for ejecting the adhesive (25), the nozzle (104) further comprising an internal passage (105) for the adhesive (25) extending between the first and second ends (106, 108), the second end (108) being beveled.

2. Installation according to the preceding claim, characterized in that the nozzle (104) extends along an elongation axis (X) which forms an angle (a) with a plane (P) containing the second end (108) less than 45°, preferably less than 25°.

3. Installation according to any one of the preceding claims, characterized in that the second end (108) has a circular or elliptical section.

4. Installation according to any one of the preceding claims, characterized in that the internal passage (105) has a first channel (110) and at least one second channel (112) for the passage of the adhesive (25).

5. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a device (114) for heat treatment of the adhesive (25).

6. Installation according to the preceding claim, characterized in that the heat treatment device (114) comprises a nozzle heating device (104) and / or an adhesive cooling device (25) connected to the storage and distribution member (102).

7. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a device (120) for applying the adhesive (25) mounted on the nozzle (102).

8. Installation according to the preceding claim, characterized in that the application device (120) comprises a squeegee (120a) mounted on the second end (108) of the nozzle (104) and configured to guide and apply the adhesive (25) to the first and / or second joining edge (23, 24).

9. Method for assembling a core (18) for a panel (17) of an aircraft turbomachine (1), the core (18) comprising at least a first and 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 an adhesive (25) to the first edge and / or the second joining edge (23, 24) so ​​as to bond the first and second structures (21, 22) together, the adhesive (25) being applied using the system (100).

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

11. Method according to any one of claims 9 to 10, characterized in that it comprises between steps (d) and (e), a step of spacing the first and second joining edges (23, 24).

12. Method according to claim 9, characterized in that it comprises the following steps carried out before step (e): (c') provide a first skin (19, 20), (d') placing the first structure (21) on the first skin (19, 20), and the following step carried out after step (e): (f') placing the second structure (22) on the first 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 9 to 12, characterized in that it further comprises the following step: (g) polymerize the adhesive (25).

14. Method according to any one of claims 9 to 13, characterized in that the adhesive (25) comprises an intumescent material.

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