Improved method for manufacturing skin of aircraft engine

Abstract

A method of manufacturing at least one skin (12), in particular an acoustic panel (10) for an aircraft engine, comprises laying a thermoplastic material (TP) on a surface (S) of a laying tool (200) via a deposition tool (100) configured to apply a pressure on the thermoplastic material (TP) and to heat the thermoplastic material while laying the thermoplastic material, the laying tool (200) comprises a thermal conditioning device configured to locally heat a surface (S) of the laying tool (200).

Description

Technical Field

[0001] The present disclosure relates to the field of skins used in aerospace engines, in particular but not limited to the casings or acoustic panels of these engines. More specifically, the present disclosure relates to a method for manufacturing such a skin, and to the skin obtained by this method. Background Art

[0002] It is known that the skins used in aerospace engines, such as the shells of the acoustic panels present in these engines, are deposited by automatic laying of thermosetting matrix composite materials. More precisely, the skin is laid on a layup tool, more precisely on the surface (or substrate) of said tool. This laying is carried out by deposition tools known per se, such as a robot called "AFP" for "automatic fiber placement", which continuously deposits cores or pre-impregnated ("prepreg") strips parallel to each other and located on several layers called "layers", or by "ATL" for "automatic tape layer", pre-impregnated sheets that are wider than the strips deposited in the "AFP" technology. These sheets are deposited one after another. The skin is then polymerized in an autoclave for several hours.

[0003] At present, composite materials with thermoplastic matrices are also used, and they have many advantages over thermosetting materials. Specifically, the chemical bonds in thermoplastic resins are produced reversibly. It is sufficient to heat the resin to melt it, so it can be used repeatedly (on the contrary, thermosetting resins, once polymerized, cannot be used again, or can be used again with great difficulty). Therefore, thermoplastic materials can be used repeatedly "infinitely". They can also be stored at room temperature.

[0004] Among the thermoplastic resins known in the aerospace industry that are compatible with the engine environment, resins called "semi-crystalline" resins are used. Semi-crystalline materials have the advantage of being resistant to chemical agents, fire and abrasion. They also have better mechanical properties.

[0005] However, in order to obtain the targeted properties of this material, in particular the desired crystallinity, it is necessary to control the thermal cycles applied. When laying up the skin, the above-mentioned deposition tools allow providing the necessary pressure and heat to make the last layer deposited adhere to the layer currently being deposited, but do not allow the control of the thermal cycle and therefore of the crystallinity. For this reason, the management of the thermal cycle is currently achieved via a second process of applying the thermal cycle in an autoclave or an oven.

[0006] These autoclave and oven consolidation solutions are energy intensive and expensive. In addition, the manufacturing process for these skins is decentralized, which slows down the manufacturing cycle.

[0007] Therefore, there is a need to at least partially overcome the above-mentioned disadvantages. Summary of the invention

[0008] The present disclosure relates to a method for manufacturing at least one skin, in particular a method for manufacturing an acoustic panel for an aircraft engine, comprising laying down a thermoplastic material on a surface of a layup tool via a deposition tool, the deposition tool being configured to apply pressure to the thermoplastic material and to heat the thermoplastic material while laying down the thermoplastic material, wherein the layup tool comprises a heat regulating device configured to locally heat the surface of the layup tool.

[0009] It will be understood that the skin is deposited by being placed directly on the lay-up tool, more precisely on the surface (or substrate) of said tool.

[0010] The skin is laid up by successive deposition of reinforcement strips or prepreg (preimpregnated) sheets of thermoplastic material using a deposition tool, which may be an "AFP" or "ATL" robot. The deposition tool may, for example, include a deposition head for applying the pressure and heat required to adhere the strips to each other, in particular to adhere the last deposited layer to the layer currently being deposited.

[0011] In addition, the thermal regulation device of the layup tool allows local heating of the surface of the layup tool, thereby locally heating or cooling the thermoplastic material that has been deposited on the surface. This modulation and this additional heat provided in a local and targeted manner allow the cooling of the thermoplastic material that has just been deposited and, therefore, the cooling of the thermoplastic material that has just been heated by the deposition tool to be controlled. More precisely, due to the local heating, the temperature gradient during cooling is controlled. Therefore, the cooling rate of the thermoplastic material that has just been heated by the deposition tool can be controlled, in particular slower than the rate at which the thermoplastic material is immediately exposed to ambient temperature. Therefore, it can be understood that the local heating of the thermal regulation device is preferably performed at a temperature lower than the temperature of the heating of the deposition tool and higher than the ambient temperature. Before depositing the thermoplastic material, the local heating of the surface of the layup tool can also gradually heat up the surface before deposition.

[0012] Localized heating allows in particular to target areas that require more or less rapid heating or cooling, thereby obtaining the desired degree of crystallinity depending on the area of ​​the skin and its thickness, which are not necessarily uniform over its entire surface since they depend on the number of layers.

[0013] This method therefore makes it possible to control the level of crystallinity of the material, thus ensuring the health and good performance of the material, in particular by providing good adhesion between the fibers and the material matrix, without the need for additional thermal cycles in energy-intensive autoclaves. Thus, it is possible to limit costs and increase the speed of the manufacturing cycle.

[0014] In some embodiments, the layup tool comprises a plurality of unit cells disposed below a surface of the layup tool on which the skin is manufactured, and the heat regulating device is configured to heat each unit cell individually.

[0015] "Units" refer to chambers or compartments arranged below the surface of the layup tool. By heating each of these unit cells individually, the surface of the layup tool can be locally heated. This allows preheating certain areas of the surface of the layup tool before the thermoplastic material is deposited on the surface of the layup tool, to control the thermal gradient to which the thermoplastic material is subjected during heating, and also to improve the cooling control of the thermoplastic material just deposited on the surface during skinning.

[0016] In some embodiments, localized heating of the surface of the layup tool is performed via induction, heat transfer fluid, or pulsed air.

[0017] Furthermore, when the layup tool comprises a plurality of unit cells arranged below the surface of the layup tool, each unit cell can be heated individually by induction, by means of a heat transfer fluid or by pulsed air. In particular, local heating by pulsed air allows the amount and duration of heat supply to be varied significantly in each layer deposited, which is particularly advantageous at the high thermal insulation capacity of thermoplastic resins. This technology allows in particular temperature dynamic variations compatible with automated laying speeds in the range of 0.1 m / s to 60 m / s. Furthermore, low energy consumption can be achieved by pulsed air heating due to the ability of pulsed air to have local dynamic temperature variations.

[0018] In some embodiments, local heating of the surface of the lay-up tool is performed by pulsed air, each unit cell being supplied with pulsed air via ducts, each duct being equipped with a heating element individually controlled by a thermal regulating device.

[0019] In some embodiments, the thermal conditioning device comprises a control unit configured to synchronize the localized heating of the surface of the layup tool with the movement of the deposition tool.

[0020] In particular, when the deposition tool comprises a plurality of unit cells arranged below the surface of the deposition tool, the control unit can control each unit cell, in particular each heating element, individually to provide heat locally, depending on the position of the deposition tool and its movement. Such synchronization allows further improved control of the local cooling of the thermoplastic material just deposited and thus heated by the deposition tool, thereby further controlling the crystallinity of the material and thus improving the material health of the material.

[0021] In some embodiments, the deposition surface is defined as a contact surface between a surface of a deposition tool and a surface of a layup tool, the deposition tool is configured to heat a surface of the layup tool downstream of the deposition surface to a first temperature, and the heat regulating device is configured to locally heat a surface of the layup tool upstream of the deposition surface to a second temperature lower than the first temperature, and the upstream-downstream direction is defined relative to the direction of movement of the deposition tool relative to the surface of the layup tool.

[0022] It will be appreciated that during the manufacture of the skin by laying, the deposition tool moves relative to the surface of the laying tool, and therefore the deposition surface also moves accordingly. The deposition surface may in particular be the contact surface between the compaction roller and the surface of the laying tool. Thus, upstream of the deposition surface are the prepreg strip(s) of thermoplastic material just deposited by the deposition tool during its movement, and downstream of the deposition surface are the surface areas of the laying tool on which said strip(s) are to be deposited.

[0023] Heating this downstream region to a first temperature allows facilitating deposition and improving the adhesion of the thermoplastic material strips to each other. In addition, locally heating the surface of the layup tool upstream of the deposition surface where the prepreg reinforcement strip of thermoplastic material just deposited and heated by the deposition tool is located to a second temperature lower than the first temperature makes it possible to cool the material while reducing the temperature difference to which it is subjected, thus controlling its cooling.

[0024] In some embodiments, the thermal regulation device is configured to locally regulate the temperature of the layup tool surface by a local heating gradient comprised between 30° C. / minute and 100° C. / minute.

[0025] Thus, depending on the desired level of crystallinity, the thermoplastic material can be locally heated or cooled by means of a more or less rapid heating ramp.

[0026] In some embodiments, the thermoplastic material is polyetheretherketone, polyetherketoneketone or polyaryletherketone. These so-called "semi-crystalline" thermoplastic resins have the advantage of particularly high performance and compatibility with aircraft engine environments.

[0027] In some embodiments, during the manufacture of the first skin, the tool deposits continuous prepreg reinforcement strips of thermoplastic by means of compaction rollers while applying pressure to the thermoplastic material while laying it down.

[0028] Thus, the deposition tool is pressed onto the prepreg strip of thermoplastic material via the compacting roller in the same way as a roll of scotch tape is unrolled using a dispenser gun or unroller. This pressure applied by the compacting roller improves the mutual adhesion of the thermoplastic material strips from one layer to another, that is to say from one layer to another.

[0029] In some embodiments, the deposition tool uses a laser to heat the thermoplastic material during layup.

[0030] The use of a laser makes it easier to locate the heat source, in particular by directing the laser towards the compacting roller and thus towards the strip of thermoplastic material being laid. This targeted heat supply of the deposition tool allows improved adhesion between the strips, in particular between the last deposited layer and the layer being laid. Alternatively, the deposition tool can heat the thermoplastic material while laying the thermoplastic material using a lamp, a torch or any other suitable means.

[0031] The invention also relates to an acoustic panel comprising a skin obtained by a method according to any of the preceding embodiments.

[0032] The invention also relates to an aircraft engine comprising an acoustic panel according to the invention, the aircraft engine being a turbojet engine.

[0033] The invention also relates to a method for manufacturing an acoustic panel for an aircraft engine, comprising: - manufacturing the first skin by the method according to any one of the preceding embodiments; - manufacturing an acoustic composite body including a plurality of unit cells on the first skin; and - Manufacturing the second skin by laying down thermoplastic material on the acoustic composite body with the aid of a deposition tool.

[0034] It should be understood that the first skin is deposited by laying directly on a layup tool, more precisely, by being placed on the surface (or substrate) of said tool, while the second skin is deposited on the acoustic composite, which itself has been previously formed on the first skin by, for example, additive manufacturing.

[0035] In some embodiments, the acoustic composite body is made of a material that is compatible with the first skin and the second skin, preferably the same thermoplastic material as the first skin and the second skin.

[0036] In some embodiments, the acoustic composite comprises a reinforced thermoplastic material. The thermoplastic material may, for example, comprise a thermoplastic matrix and a carbon fiber filler, allowing for enhanced mechanical strength of the acoustic panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The invention and its advantages will be better understood by reading the following detailed description of different embodiments of the invention given as non-limiting examples. This description makes reference to the attached pages of the drawings, in which:

[0038] [ Figure 1 ] Figure 1shows a sectional view in a longitudinal plane of a turbojet engine comprising an acoustic panel consisting of a skin according to one embodiment of the invention;

[0039] [ Figure 2 ] Figure 2 shows a partial perspective view of an acoustic panel including a skin according to one embodiment of the present invention;

[0040] [ Figure 3 ] Figure 3 Schematically illustrates a deposition tool moving on a layup tool in a manufacturing method according to an embodiment of the present invention;

[0041] [ Figure 4 ] Figure 4 Schematically showing a bottom view of a group of unit cells of a layup tool used in a method for manufacturing a skin according to an embodiment of the present invention;

[0042] [ Figure 5 ] Figure 5 The different steps of a method of manufacturing an acoustic panel are schematically shown. DETAILED DESCRIPTION

[0043] Figure 1 A sectional view of a turbojet 1 according to an embodiment of the invention in a longitudinal plane of the turbojet 1 is shown. The turbojet 1 comprises a nacelle 2, an intermediate casing 3 and an inner casing 4. The nacelle 2 and the two casings 3, 4 are coaxial. The nacelle 2 defines an inlet channel 6 for fluid flow at a first end and an exhaust channel 6 for fluid flow at a second end opposite to the first end. The nacelle 2 and the intermediate casing 3 define a primary fluid flow path 7 between them. The intermediate casing 3 and the inner casing 4 define a secondary fluid flow path 8 between them. The primary flow path 7 and the secondary flow path 8 are arranged between the inlet channel 5 and the exhaust channel 6 in the axial direction of the turbojet.

[0044] The turbojet 1 further comprises a fan 9 configured to deliver an air flow F as a fluid flow which is divided at the fan outlet into a main flow Fp flowing in a main flow path 7 and a secondary flow Fs flowing in a secondary flow path 8. The turbojet 1 further comprises at least one acoustic panel 10 configured to attenuate the sound waves emitted by the turbojet before they escape radially outside the nacelle 2 of the turbojet 1. The acoustic panel 10 is configured to attenuate sound waves having a frequency belonging to a predetermined frequency range. Figure 1 In the embodiment shown, the panels 10 are integrated into the intermediate hull 3 and the inner hull 4. Although not shown, other acoustic panels may be integrated into the nacelle 2 and the inner hull 4.

[0045] The rest of the description describes an example in which a skin manufactured by the method according to the invention is used for an acoustic panel 10. However, it should be noted that this example is non-limiting and that the skin can be used for other parts of a turbojet engine 1, in particular the intermediate casing 3, the inner casing 4 or the nacelle 2, without necessarily being part of an acoustic panel.

[0046] Figure 2 1 shows a partial perspective view of an acoustic panel 10 comprising an outer skin (hereinafter referred to as the first skin) obtained by a method according to an embodiment of the invention. In a known manner, the acoustic panel 10 is a Helmholtz resonator. Typically, as Figure 2 The acoustic panel 10 shown comprises a honeycomb structure stage. The acoustic panel 10 specifically comprises a first perforated skin 12, a second solid skin 14 and an acoustic composite 16, which is a core having a honeycomb structure sandwiched between these skins. The acoustic composite 16 consists of an array of unit cells 18 in the shape of a honeycomb. It should be noted that this honeycomb structure is non-restrictive and other types of structures that can be manufactured by additive manufacturing as described below can be applied without departing from the scope of the invention. As for the first perforated skin 12, it is attached to the acoustic composite 16 and is arranged on one side of the main flow path 7 of the turbojet engine 1 in the context of the present invention. The skin is perforated by a plurality of orifices 20, each orifice 20 opening to a unit cell 18 of the acoustic composite 16, and several orifices can be opened to the same unit cell 18.

[0047] Then refer to Figures 3 to 5 A skinning method according to an embodiment of the present disclosure is described for use in the context of manufacturing such an acoustic panel 10 .

[0048] First, the first skin 12 is manufactured by automated laying (step S100), in particular but not limited to the "AFP" (for "Automated Fiber Placement") or "ATL" (for "Automated Tape Layer") techniques known per se, by successively depositing core or pre-impregnated ("prepreg") strips parallel to each other and in several layers called layers. The deposited strips comprise a thermoplastic material TP (more simply referred to as "material TP" in the remainder of this description), in particular but not limited to polyetheretherketone PEEK, polyetherketoneketone PEKK, polyaryletherketone PAEK or polyphenylsulfone PPSU.

[0049] These material TP strips are deposited by deposition tool 100 on layup tool 200, such as Figure 3 The deposition tool 100 comprises a deposition head 110 to which material TP is supplied in the form of a strip by a feeding device (not shown). A cutting module 120 allows the strip of material TP to be cut when the strip has reached a desired length.

[0050] The compaction roller 130 allows the strip of material TP to be applied to the surface S of the laying tool 200 described below by applying pressure to the strip of material during laying. More specifically, during laying, the deposition tool 100 moves along the surface S of the laying tool 200. Figure 3 According to the present disclosure, the displacement direction of the deposition tool 100 in the direction D defines the upstream and downstream directions, corresponding to Figure 3 The right-left direction in . Therefore, Figure 3 The area to the right of the compacting roller 130, more precisely the area to the right of the layup surface P, corresponds to the upstream area of ​​the deposited material TP, while the area to the left of the layup surface P in the figure corresponds to the downstream area of ​​the material TP to be deposited, and the layup surface P is the contact surface between the compacting roller 130 and the surface S (the layup surface P itself moves when the deposition tool 100 moves along the direction D). Therefore, during the movement of the compacting roller 130, it rolls downstream on the surface S, sandwiching the material TP strip deposited between the compacting roller 130 and the surface S.

[0051] Furthermore, a heat source, in particular a laser 140, preferably directed towards the compaction roller 130 and onto the material TP, allows heating of the strip of material TP being deposited in the downstream region. The compaction roller 130 and the laser 140 allow providing the pressure and heat required for the strips of material TP to adhere to each other, in particular the last layer deposited and the layer currently being deposited. Specifically, the laser 140 can heat the material TP to a temperature between 100° C. and 500° C. to allow the strips to adhere to each other, and the compaction roller 130 can apply a compaction force between 200N and 500N, and for an “in-situ” construction, a compaction force of up to 1200N.

[0052] The layup tool 200 includes a lower part 210 and an upper part 220. The upper surface of the upper part 220 is a surface S on which the material TP is deposited by laying during the manufacturing process of the first skin 12. The surface S has a Figure 3 The curvature shown, but generally corresponds to the final shape of the acoustic panel 10 to be manufactured. For example, if the acoustic panel to be manufactured has a toroidal shape, the surface S will have the equivalent shape of an arc of a circle.

[0053] The volume formed by the upper portion 220 is divided into a plurality of unit cells 222 (or chambers or compartments) that are independent of each other. For ease of description, Figure 3 Only four unit cells 222 are shown in the figure, and their sizes, especially widths, are intentionally exaggerated. In fact, the laying tool 200 includes a large number of unit cells 222 with a width smaller than that shown in the figure in its upper part 220.

[0054] in this regard, Figure 4An example of the distribution and shape of the unit cells 222 in a view perpendicular to the surface S (e.g., a bottom view) is schematically shown. These triangular cross-section unit cells 222 are arranged to form an array below the surface S. The dashed squares represent the material TP of at least a portion of the first skin 12 deposited on the surface S, that is, just above the unit cells 222. Therefore, by heating each unit cell 222 individually, a small area of ​​the surface S can be locally heated in a targeted manner, thereby adjusting the heat supply, and then a small area of ​​the material TP deposited on the surface S can be locally heated.

[0055] To this end, the layup tool 200 includes a heat regulating device configured to individually heat each unit body 222. The heat regulating device includes a compressed air supply unit 230, which is configured to individually supply a plurality of ducts 234 via a compressed air supply channel 232, each duct 234 being individually connected to one of the unit bodies 222. In addition, each duct 234 is equipped with a heating element 236, such as a heating resistor, allowing the air flowing in the duct 234 to be heated before being injected into the unit body 222.

[0056] The heat regulating device further comprises a control unit 240 configured to control the compressed air supply unit 230 and individually control each heating element 236. Thus, the control unit is configured to control the duct 234, thereby controlling the supply of compressed air to the unit body 222, while individually adjusting the temperature of the heating element 236 to control the temperature of the pulsed air injected into each unit body 222.

[0057] Furthermore, although such connection is not shown, the control unit 240 may also be connected to the deposition tool 100 so as to be able to synchronize the heating of the unit cells 222 with the movement of the deposition tool 100 when laying up the first skin 12 during step S100. More precisely, by detecting the position of the deposition tool 100 at a given time during its movement, in particular the position of the layup surface P, the control unit may supply the unit cells 222 arranged upstream of the layup surface P so as to target the area on the surface S where the material TP has just been deposited, thereby controlling the cooling of the latter. The control unit may also supply the unit cells 222 arranged downstream of the layup surface P so as to target the area on the surface S where the material TP is to be deposited, thereby controlling the temperature rise of the latter in order to limit the temperature gradient caused by the laser 140.

[0058] It can therefore regulate, by means of the heating element 236, the temperature of the air supplied to said unit cell 222, and the speed of the heating gradient or cooling gradient, depending on the desired final state of the material (level of crystallinity), but also on the number of layers deposited and, therefore, on the thickness of the first skin 12 during manufacture. In fact, when N strips of material TP are superimposed on one another, the strip N+1 deposited on strip N will be separated from the surface S by said N strips. Taking into account the insulating properties of the material TP, it may be necessary to adapt the local temperature of the unit cell 222 and the heating speed in order to obtain an equivalent level of crystallinity for each layer. For example, the control unit 240 can locally regulate the temperature of the surface S by a local heating gradient comprised between 30°C / min and 100°C / min.

[0059] In general, the control unit 240 may be configured to individually control the heating of each unit cell 222 depending on the position of the deposition tool 100, its movement speed, the heating temperature of the laser 140, and the number of layers deposited on the surface S. For example, when the laser 140 heats the strip of material TP being laid to a temperature T1 downstream of the layup surface P, the control unit 240 may control the heating element 236 to heat the unit cell 222 located upstream of the layup surface P to a temperature T2 lower than T1, thereby controlling the temperature gradient ΔT, where ΔT=T1-T2, while taking into account parameters such as the number of layers present at that position and time, the trajectory or movement speed of the deposition tool 100, and the like.

[0060] In the above example, the heat conditioning device uses a pulsed air system to individually heat the unit cells 222. It should be noted that this example is non-limiting and other means may be used, such as induction or heat transfer fluids.

[0061] The step S100 of manufacturing the first skin 12 is completed when all the layers allowing the desired shape and thickness of the skin to be obtained have been deposited on the surface S of the lay-up tool 200 while locally heating this surface S in the manner described above.

[0062] Then, by additive manufacturing (step S200), the acoustic composite 16 is manufactured directly on the first skin 12 with the aid of a tool provided for this purpose. The acoustic composite 16 is preferably made of the same thermoplastic material as the first skin 12 and may also be filled with carbon fibers to enhance its strength.

[0063] The second skin 14 is then deposited on the face of the acoustic composite 16 opposite to the face to which the first skin 12 is attached (step S300), so that the first skin and the second skin are substantially parallel to each other. The second skin 14 is also made of the same material TP as the first skin 12 by automatic laying using the same deposition tool 100. However, unlike the first skin 12, the strips of material TP of the second skin 14 are only heated by the laser 140 and compacted by the compaction roller 130 so that the strips adhere to each other. It should be noted that the pressure applied to the second skin 14 is compatible with the rigidity of the acoustic composite 16. Without using the thermal adjustment device of the above-mentioned layup tool 200, the second skin 14 is deposited on the acoustic composite 16, rather than on the surface S of the layup tool 100. However, it is worth noting that the crystallinity control of the second skin 14 is not as critical compared to the first skin 12, which is in contact with the mainstream Fp and performs the acoustic function.

[0064] Although the present invention has been described with reference to specific exemplary embodiments, it is apparent that these examples can be modified and altered without departing from the overall scope of the present invention as defined in the claims. In particular, the various features of the various illustrated / described embodiments may be combined in additional embodiments. Therefore, the description and drawings should be regarded as illustrative rather than restrictive.

[0065] It is also self-evident that all features described with reference to a method can be converted, individually or in combination, into a device and conversely, all features described with reference to a device can be converted, individually or in combination, into a method.

Claims

1. A method for manufacturing at least one skin (12), in particular an acoustic panel (10) for an aircraft engine, comprising laying down a thermoplastic material (TP) on a surface (S) of a layup tool (200) via a deposition tool (100), the deposition tool (100) being configured to exert pressure on the thermoplastic material (TP) and to heat the thermoplastic material (TP) while laying down the thermoplastic material (TP), wherein: The laying tool (200) comprises a heat regulating device, which is configured to locally heat the surface (S) of the laying tool (200), and the heat regulating device comprises a control unit (240), which is configured to synchronize the local heating of the surface (S) of the laying tool (200) with the movement of the deposition tool (100).

2. The method according to claim 1, characterized in that: The layup tool (200) comprises a plurality of unit bodies (222), the unit bodies being arranged below a surface (S) of the layup tool (200), the skin (12) being manufactured on the surface, and the heat regulating device being configured to heat each unit body (222) individually.

3. The method according to claim 1 or 2, characterized in that: Local heating of the surface (S) of the lay-up tool (200) is performed via induction, heat transfer fluid or via pulsed air.

4. The method according to claim 3, characterized in that Local heating of the surface (S) of the laying tool (200) is performed by pulsed air, each unit body (222) being supplied with pulsed air via a duct (234), each duct (234) being equipped with a heating element (236) individually controlled by the thermal regulation device.

5. The method according to any one of claims 1 to 4, characterized in that The deposition surface (P) is defined as a contact surface between the deposition tool (100) and the surface (S) of the stacking tool (200), the deposition tool (100) is configured to heat the surface (S) of the stacking tool (200) downstream of the deposition surface (P) to a first temperature, and the heat regulating device is configured to locally heat the surface (S) of the stacking tool (200) upstream of the deposition surface (P) to a second temperature lower than the first temperature, and the upstream-downstream direction is defined relative to the direction of movement of the deposition tool (100) relative to the surface (S) of the stacking tool (200).

6. The method according to any one of claims 1 to 5, characterized in that The thermal regulation device is configured to locally regulate the temperature of the surface (S) of the lay-up tool (200) by a local heating gradient comprised between 30°C / min and 100°C / min.

7. The method according to any one of claims 1 to 6, characterized in that The thermoplastic material (TP) is polyetheretherketone, polyetherketoneketone or polyaryletherketone.

8. The method according to any one of claims 1 to 7, characterized in that During the manufacture of the first skin (12), the deposition tool (100) deposits a continuous prepreg reinforcement strip of the thermoplastic material (TP) by applying pressure to the thermoplastic material (TP) while laying it down, by means of a compaction roller (130).

9. The method according to any one of claims 1 to 8, characterized in that The deposition tool (100) heats the thermoplastic material (TP) using a laser (140) during layup.

10. A method for manufacturing an acoustic panel (10) for an aircraft engine, comprising: - manufacturing a first skin (12) by a method according to any one of claims 1 to 9; - manufacturing an acoustic composite body (16) comprising a plurality of unit cells (18) on said first skin (12); and - producing a second skin (14) by laying down the thermoplastic material (TP) on the acoustic composite body (16) by means of the deposition tool (100).

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