METHOD FOR TREATMENT OF A TURBOMACHINE PART MADE OF COMPOSITE MATERIAL

Abstract

The present invention relates to a method for treating a part made of composite material, in particular for an aircraft turbomachine or for an aircraft, the part comprising at least one layer covering a surface of the part, this method comprising a step (a) of stripping at least one layer of the part so as to prepare at least part of said layer, wherein prior to the stripping step (b), the method comprises a step (a) of scarifying at least one layer of the part. Figure for the abstract: Fig. 3

Description

Title of the invention: METHOD FOR TREATMENT OF A TURBOMACHINE PART MADE OF COMPOSITE MATERIAL Technical field of the invention

[0001] The present invention relates to the field of treatments of a part made of composite material, in particular for an aircraft turbomachine.

[0002] In particular, the present invention relates to a method for treating a part made of composite material. Technical background

[0003] Generally speaking, every part is designed to meet specific functions and environmental constraints. This is particularly true for both metallic and composite materials. To meet these environmental constraints, surface treatments that offer protective properties are commonly used, notably through the application of one or more protective layers. These protective layers are generally very sensitive to external aggressions and require touch-ups or repairs.

[0004] Furthermore, composite parts can be formed from different materials and often in a non-homogeneous manner (for example: a carbon fiber composite part with a polymer matrix and a metallic part) in order to meet functional specifications. Surface treatments may be identical or different depending on the base material of the part.

[0005] In the industrial field, it is therefore known to provide for a treatment of metal or composite parts to prepare the external surface of these parts in order to clean, repair and / or touch up this part.

[0006] In the aeronautical field, in particular aircraft turbomachinery, more and more parts are made of composite material to obtain a lower overall mass than the same parts when made of a metallic material, while exhibiting at least equivalent if not superior mechanical resistance.

[0007] A composite material part is generally repaired or reworked by manually performing a stripping step, notably by sanding or polishing. This can be a long and tedious process. Indeed, manual stripping can require physical effort from an operator and can cause musculoskeletal disorders (MSDs). Furthermore, stripping can present a risk of damaging parts of the piece that should be retained (for example, during cleaning to remove contamination). to an abrasive medium) and / or a risk of damaging a surface beneath the layer being removed by stripping, or even surrounding components. Furthermore, material removal by manual stripping may not be uniform over a given surface, and thus present inaccuracies in the thickness removed.

[0008] The composite material part may be subjected to a surface preparation operation (particularly before the application of an additional coating), which is traditionally carried out by sandblasting. Sandblasting may have the disadvantage of contaminating the surface of the part with blasting media and may also require an additional cleaning step to remove the blasting media.

[0009] There is therefore a need to provide an effective treatment of parts made of composite material, in particular for an aircraft turbomachine, which allows at least one layer of the part to be stripped without damaging and altering the properties of that part. Summary of the invention

[0010] The invention aims to provide a simple, effective and economical solution to at least one of the aforementioned disadvantages.

[0011] To this end, the invention relates to a method for treating a part made of composite material, in particular for an aircraft turbomachine or for an aircraft, the part comprising at least one layer covering a surface of this part, this method comprising a step (b) of stripping at least one layer of the part so as to prepare at least part of said at least one layer.

[0012] According to the invention, before the stripping step (b), the process includes a scarification step (a) of at least one layer of the part.

[0013] Thus, this solution makes it possible to achieve the aforementioned objective. In general, the process according to the invention makes it possible to obtain at least one stripped layer (or in other words, a stripped external surface of the part) without damaging the part made of composite material.

[0014] Indeed, the process according to the invention makes it possible to prepare (for example by removal and / or cleaning) the necessary quantity (such as a layer thickness) and in a homogeneous manner of material to be removed from the layer to be treated, in particular before implementing reconstruction solutions (such as touch-ups, repairs, deposits of additional coatings, etc.).

[0015] In particular, scarification upstream of the layer to be stripped makes it possible to create controlled incisions (or notches, or in other words, cracks) on this layer to initiate the stripping process. This facilitates crack propagation and enhances material removal at the level of the layer to be treated without altering the other components and / or properties of the part.

[0016] Furthermore, scarification also enhances the removal of contaminants that may be particularly resistant to pickling. For example, the composite material part may have an anti-erosion layer that offers good resistance to the initiation of damage. Thus, the incisions made by scarification in this anti-erosion layer facilitate the propagation of cracks and their removal during pickling.

[0017] In addition, the scarification and stripping steps can be adapted for automated processing (for example by a suitable machine).

[0018] Finally, the process according to the invention is less harmful to the health of operators than manual and / or chemical stripping, less energy-intensive and does not pollute the part.

[0019] The term "stripping" or "stripped" means a removal (or machining) which may be partial or total of a layer (or in other words a surface, in particular external) of the composite part.

[0020] The term "scarification" or "scarified" means an operation to initiate stripping by preparing the layer to be treated, for example by creating incisions on the layer to be treated (or part of the layer to be treated or removed).

[0021] The treatment process according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0022] - step (a) of scarification is carried out on the entire surface of at least one layer of the piece ;

[0023] - the steps (a, b) of scarification and stripping are carried out by projecting a water jet at, respectively, a first predetermined pressure and a second pressure;

[0024] — the steps (a, b) of scarification and stripping are carried out by projecting a jet water to, respectively, a first parameter and a second parameter;

[0025] - the first pressure is greater than the second pressure;

[0026] - the first pressure is between 1500 and 2000 bars, and the second pressure is between 1000 and 2000 bars;

[0027] - the water jet is demineralized and without abrasive;

[0028] - the water jet is projected by a single nozzle, a multi-nozzle or a nozzle containing several sapphires;

[0029] - before and / or after step (b) of pickling, the process further comprises a step (i) inspection of at least one layer of the part;

[0030] - a measuring device, for example a camera or a sensor, is connected to the nozzle or the multi-nozzle, so as to check at least one layer of the part;

[0031] - the turbomachine or aircraft part is a blade, for example of a fan, or a crankcase;

[0032] — step (b) of stripping at least one layer of the part so as to remove at least in part said at least one layer;

[0033] — step (b) of stripping at least one layer of the part so as to clean at least in part said at least one layer;

[0034] — a predetermined thickness is scarified during the scarification step;

[0035] — the predetermined thickness is 2.00 mm;

[0036] — the composite material comprises an organic or ceramic matrix;

[0037] — the part comprises fibers embedded in a resin;

[0038] — the fibres are woven, preferably in three dimensions;

[0039] — the fibers are glass fibers, carbon fibers, aramid fibers, polyamide fibers, ceramic fibers, metallic fibers, or a mixture of at least two of these fibers;

[0040] — the resin is a thermosetting material, for example chosen from polyurethane, epoxy, polybismaleimide, polyimides or phthalonitrile, or resin is a thermoplastic, for example chosen from polyether-ether-ketone, polyarylether-ketone or poly-ether-imide;

[0041] — the stripping step is followed by a deposition step, for example of a coating additional or a protective shield on the stripped surface;

[0042] — the part is multi-component and / or multi-material;

[0043] — the anti-erosion layer is a multilayer comprising, for example, a first an epoxy primer (known as the bonding primer) and a second polyurethane primer (known as the anti-erosion primer), the second primer extending above or below the first primer;

[0044] — the blade comprises a blade having an intrados face and an extrados face extending transversely between a leading edge and a trailing edge of this blade, in which a protective shield is placed on the surface stripped at the deposition stage, for example by gluing;

[0045] — the part made of composite material is a compressor blade or the aircraft turbomachine.

[0046] The invention may relate to the use of a treatment process according to one of the features of the invention, for preparing one or more surfaces of the part made of composite material, for example of a turbomachine blade before application (for example by sizing) or reconstruction of a coating or a protective shield (such as a metallic foil).

[0047] The invention may also relate to the use of a treatment process according to one of the features of the invention, for repairing one or more damaged areas of the part made of composite material, for example of a turbomachine blade.

[0048] The invention may also relate to the use of a treatment process according to one of the features of the invention, for retouching one or more areas of the part made of composite material.

[0049] The invention may further relate to the use of a treatment process according to one of the features of the invention, for cleaning at least one component of the part, such as a metallic protective shield of a turbomachine blade or a polyurethane film of a turbomachine blade. Brief description of the figures

[0050] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0051] [Fig.1] is a half view schematically representing in axial section an aircraft turbomachine;

[0052] [Fig.2] is a schematically perspective view of a blade for a blower of the turbomachine of [Fig.1];

[0053] [Fig.3] is a block diagram of the steps of a process for treating a part made of composite material, such as the blade of the [Fig.2];

[0054] [Fig.4] schematically represents a treatment of the part in composite material;

[0055] [Fig.5] schematically and partially represents an axial cross-sectional view of an example of a blade from [Fig.2];

[0056] [Fig.6] schematically and partially represents an axial cross-sectional view of another example of a blade from [Fig.2].

[0057] Elements having the same functions in the different implementations have the same references in the figures. Detailed description of the invention

[0058] By convention, in the following description, the terms "longitudinal" and "axial" refer to the orientation of structural elements extending along a longitudinal axis (such as the longitudinal axis of a turbomachine). The terms "radial" or "vertical" refer to the orientation of structural elements extending in a direction perpendicular to the longitudinal axis. The terms "interior" and "exterior," and "internal" and "external," are used with reference to positioning relative to the longitudinal axis. Thus, a structural element extending along the longitudinal axis has an interior face facing the longitudinal axis and an exterior surface opposite its interior surface.

[0059] The invention relates to a treatment of a part 10 made of composite material, in particular for an aircraft turbomachine 1 or for an aircraft.

[0060] Part 10 can be multi-component and / or multi-material. For example, part 10 can be a 2, 2a, 2b made of composite material of the turbomachine 1 which includes a protective shield 3 made of metallic material on its leading edge.

[0061] In the following description, the invention will be described in the context of its application to a blade 2, 2a, 2b made of composite material, in particular for a blower la of the turbomachine 1.

[0062] Fig. 1 illustrates a non-limiting example of a turbomachine 1 that is enclosed.

[0063] The turbomachine 1 can be a turbojet or turboprop.

[0064] The turbomachine 1 extends around a longitudinal axis X. It may include, from upstream to downstream in the direction of gas flow F along the longitudinal axis X, the blower la, at least one compressor (such as a low pressure compressor 1b and a high pressure compressor le), a combustion chamber Id, at least one turbine le (such as a high pressure turbine and a low pressure turbine), and a nozzle (not shown).

[0065] The turbomachine 1 may also include a rectifier If which allows the flow at the outlet of an upstream rotor to be rectified in order to provide maximum thrust at the outlet of the turbomachine 1. In the particular example of [Fig.1], the rectifier If is located downstream of the fan la and allows a secondary flow F2 to be rectified.

[0066] The blower allows the aspiration of an airflow which divides into a primary flow Fl and a secondary flow F2. The primary flow Fl passes through a primary channel of the turbomachine 1 while the secondary flow F2 is directed towards a secondary channel surrounding the primary channel.

[0067] The primary flow Fl is compressed within the low-pressure compressor 1b and then the high-pressure compressor le. The compressed air is then mixed with fuel and burned within the combustion chamber Id. The gases formed by combustion pass through the high-pressure turbine and the low-pressure turbine. The gases finally escape through the nozzle, the cross-section of which allows the acceleration of these gases to generate thrust. The secondary flow F2 passes through the rectifier If, which accelerates the circulation of the secondary flow F2 to generate propulsion.

[0068] The blower 1a, the low pressure compressor 1b, the high pressure compressor 1, the high pressure and / or low pressure turbine 1, and the rectifier 1f include blades 2. The blades 2 can be movable (for example, blade 2a of [Fig. 2]) in rotation around the X axis, or fixed (blade 2b called OGV for "Outlet Guide Vane" of rectifier 1f of [Fig. 1]) relative to the X axis.

[0069] The blade 2, 2a, 2b can be made of composite material. In particular, the blade 2a can comprise fibers embedded in a resin.

[0070] The resin can thus form a densification matrix for the composite material. The composite material can be an organic or ceramic matrix. In other words, the resin can be organic or ceramic.

[0071] The resin can be a thermoset or a thermoplastic. For example, the thermoset resin can be selected from polyurethane, epoxy, polybismaleiimide (BMI), polyimides, or phthalonitrile. The thermoplastic resin can be selected from polyetheretherketone (PEEK), polyaryletherketone (PAEK), or polyetherimide (PEI).

[0072] The fibers may be glass fibers, carbon fibers, aramid fibers, polyamide fibers, ceramic-type fibers (e.g., silicon carbide SiC), or metallic fibers (e.g., titanium Ti). The fibers may be a mixture of at least two of the aforementioned fibers (e.g., silicon carbide titanium SiC-Ti).

[0073] The fibers can be woven, preferably in three dimensions.

[0074] The fibers can also be woven in two dimensions to form one or more fabrics that can be used by draping them to make the alb.

[0075] Alternatively, the fibers can be laminated. By definition, a laminated fiber is formed by stacking several layers adhering to one another. Laminated fibers are configured to form a web of nonwoven fibers.

[0076] The blade 2, 2a, 2b may include carbon fibers embedded in epoxy.

[0077] With reference to [Fig. 2], the blade 2a can extend, on the one hand, along a longitudinal axis A (arranged horizontally in [Fig. 2]), and on the other hand, along an elongation axis B (arranged vertically in [Fig. 2]). This axis A is substantially perpendicular to the axis B. The axis A is substantially parallel to the X-axis of the turbomachine 1.

[0078] The blade 2a may comprise a blade 20 having an intrados face 21 and an extrados face 22 extending transversely between a leading edge 23 and a trailing edge 24. The blade 20 may have an aerodynamic profile to form the aerodynamic part of the blade 2a. For this purpose, the blade 20 may have a curved profile of variable thickness between its leading edge 23 and its trailing edge 24.

[0079] Dawn 2a may include a foot 26.

[0080] The blade 20 may include a first longitudinal end connected to the blade foot 26 and a second longitudinal end, opposite the first longitudinal end, free and configured to form a blade apex 25 (or head).

[0081] The blade 2a may also include a reinforcement or shield 3 for the protection of the leading edge 23, in the form of a metallic plate. In the example, the shield 3 extends vertically (relative to axis A) and over a portion longitudinally (relative to the axis B) of the intrados face 21 and the extrados face 22 from the leading edge 23 of the blade 20.

[0082] The protective shield 3 can be made of titanium or any other metallic material.

[0083] Part 10 of the invention is not limited to the fan blade 2, 2a, 2b of the shrouded turbomachine 1, and can also be applied to other types of blades made of composite material (such as fixed or moving blades of the low pressure compressors 1b and high pressure 1e, of the high pressure and low pressure turbines of the turbomachine 1).

[0084] In general, the invention can be applied to any composite material parts requiring treatment and / or having one or more components made of different materials (such as metallic foil on the leading edge or a "wear strip" type coating for a turbomachine blade). By way of example, these parts could be propellers of an unfaired turbomachine, turbomachine casings, a turbomachine or aircraft panel, etc.

[0085] The treatment process according to the invention includes a step (b) of stripping at least one layer 100 of the part 10 (which may be the blade 2, 2a, 2b), so as to prepare (in particular so as to remove and / or clean) at least a part of this layer 100.

[0086] According to one of the features of the invention, the treatment process includes, prior to the pickling step (b), a scarification step (a) of at least one layer 100 of the part 10. In particular, a portion of the thickness of layer 100 can be scarified in step (a). Figure 3 summarizes the steps of the treatment process of the invention, with optional steps indicated by dashed lines.

[0087] The scarification step (a) initiates the stripping process, facilitating the removal of material (namely from layer 100) during the stripping step (b). For example, scarification creates incisions in layer 100 of part 10.

[0088] Step (a) of scarification can be carried out over the entire layer 100 to be treated. This makes it possible, in particular, to distribute the incisions over the entire layer to be treated in order to facilitate and speed up the removal of material during stripping.

[0089] Step (a) can be carried out by projecting a water jet 54 at a first parameter (such as a first predetermined pressure Pi). The water jet can be an effective material removal (or machining) method for removing the necessary material without damaging the workpiece.

[0090] The water jet 54 can be projected at high pressure.

[0091] The first pressure Pi can be between 1500 and 2000 bar. Preferably, this first pressure Pi can be between 1500 and 1800 bar.

[0092] During step (a), a predetermined thickness can be scarified. This thickness can be a maximum of 2.00 mm. In other words, the thickness of each of the incisions formed by the scarification on layer 100 can be a maximum of 2.00 mm. The thickness of the incisions can vary depending on the composite material, the layer(s) to be removed, and / or the dimensions of the layer 100 to be treated.

[0093] Advantageously, the scarified thickness of layer 100 can be at most the thickness of an anti-erosion layer 214 covering part 10. For example, the scarified thickness of layer 100 can be at most about 150 pm.

[0094] After carrying out step (a), step (b) of stripping allows for example to easily and quickly remove the material of the layer 100 to be treated, without altering the part 10 and / or the components of this part 10 (such as an adhesion layer 210, a polyurethane film 212 and / or the protective shield 3 in the case of the blade 2 in particular with reference to [Fig.5] or [Fig.6]).

[0095] Step (b) can be carried out by projecting the water jet 54 at a second parameter (such as a second pressure P2). The second parameter can vary and / or adjust according to, in particular, the indication at an inspection step (i).

[0096] The second pressure P2 can be between 1000 and 2000 bar. Preferably, this second pressure P2 can be between 1000 and 1500 bar.

[0097] The first pressure Pi may be different from the second pressure P2. In particular, the first pressure Pi may be greater than the second pressure P2. This makes it possible, in particular, to efficiently form incisions on the layer 100 to be treated during step (a) and then allow, for example, the simple and rapid removal of material from this layer during step (b).

[0098] The first Pi and second P2 pressures may vary depending on the composite material, the layer(s) to be removed and / or the dimensions (such as thickness, profile, etc.) of the layer to be treated.

[0099] The water jet 54 can be demineralized (or tap water) and abrasive-free. For example, the water jet can have a conductivity less than or equal to 2500 qS / cm at a temperature of 20°C.

[0100] The water jet 54 projected during step (a) may be similar to that projected during step (b).

[0101] With reference to [Fig. 4], the present application will now describe an example of an apparatus (or machine) for carrying out steps (a) and (b). This apparatus may include the water jet 54 projected onto the layer 100 to be treated.

[0102] The water jet 54 can pass through a high-pressure pump 50 to be compressed through a nozzle 52 and projected onto the part 100 to be treated.

[0103] In particular, the water jet 54 can be projected by a single nozzle 52, a multi-nozzle (or in other words, a nozzle with several projection heads), or a nozzle comprising several sapphire nozzles. The multi-nozzle allows, in particular, the simultaneous treatment of the same layer 100 or several layers 100 of the part. For example, the water jet 54 can be projected, preferably simultaneously, onto the intrados 21 and extrados 22 faces of the blade 2.

[0104] By way of example, a sapphire type nozzle can be marketed under the reference "KMT 4000 bar Water Jet Aqualine Heads Sapphire Nozzles".

[0105] The nozzle 52 can be moved by a numerically controlled device 56 (such as a computer).

[0106] The nozzle 52 can be positioned at a distance D from the layer 100 to be treated. This distance D can vary and / or be adjusted, in particular according to the indication in step (i).

[0107] The distance D can be between 50 and 100 mm. Preferably, this distance D can be between 50 and 80 mm. Even more preferably, the distance D can be between 60 and 80 mm or between 50 and 70 mm.

[0108] A measuring element 58 can be connected to the nozzle 52 or the multi-nozzle to check the layer 100 of the part. This measuring element 58 can be a camera or a sensor (for example, for measuring the thickness to be scarified and / or stripped).

[0109] Before or after step (b), the treatment process according to the invention may further include a step (i) of inspecting layer 100. This step (i) may allow for several checks to be carried out, such as: - the presence or absence of any residue from layer 100, - the quantity of material removed and / or scarified, and / or - the presence or absence of damage to the final layer 100 of part 10.

[0110] The term "final layer" means the treated surface of the part after scarification and pickling.

[0111] Step (i) can be carried out by the measuring device 58. Alternatively, step (i) can be carried out manually by the operator, for example by a visual check.

[0112] The treatment process according to the invention may include, after the stripping step (b), a deposition step (c), for example, of an additional coating 4 or of the shield 3 onto the stripped layer 100. The addition of this coating 4 may allow, for example, the retouching or repair of a damaged area of ​​the part, or the integration of an additional function into the part (such as a protective function, for example, with the protective shield 3).

[0113] Scarification and / or stripping can be optimized by varying at least one of the following parameters: - the Pb P2 pressure of the water jet 54, - the speed of movement of nozzle 52, - the scarification and / or stripping strategy, such as the machining path (straight, curved, crenellated or zigzag path; with or without sweeping; rotation or translation of nozzle 52, etc.), - the number of passes of nozzle 52 on the same layer 100, - the distance D between nozzle 52 and layer 100, - the flow rate of the water jet 54, - the pitch or feed rate of nozzle 52 relative to the workpiece, - the dimensions of nozzle 52 (such as its diameter), and / or - the angle of orientation of the nozzle 52 relative to the layer 100 to be treated.

[0114] Figure 5 illustrates a first example of a turbine blade 2 of a turbomachine 1 comprising the intrados 21 and extrados 22 faces to be treated. This blade 2 may include carbon fibers embedded in epoxy.

[0115] The blade 2 may include a polyurethane film 212 located on the intrados face 21 and an anti-erosion layer 214 around the polyurethane film 212, and optionally an adhesion layer 210 interposed between the polyurethane film 212 and the anti-erosion layer 214. This blade 2 may include the adhesion layer 210 located on the extrados face 22 and the anti-erosion layer 214 around this adhesion layer 210.

[0116] In particular, the anti-erosion layer 214 is located on the tack layer 210 on the side of the intrados 21 and extrados 22 faces ([Fig. 5]). According to another variant not shown in the figures, the anti-erosion layer 214 is located, on the one hand, on the tack layer 210 on the side of the extrados face 22, and on the other hand, on the polyurethane film 212 on the side of the intrados face 21.

[0117] On [Fig.5], the different layers 210, 214 and the polyurethane film 212 can each have a homogeneous and uniform thickness along the intrados 21 and extrados 22 faces.

[0118] The bonding layer 210 can be a resin, such as epoxy.

[0119] The anti-erosion layer 214 can be a multi-layer, for example applied by painting. This anti-erosion layer 214 can comprise a first, so-called base layer, made of epoxy, and a second, so-called top layer, made of polyurethane.

[0120] The anti-erosion layer 214 may have an anti-erosion function in particular with a "wear strip" type coating and possibly a damping function in particular by polyurethane.

[0121] The anti-erosion layer 214 can have a maximum thickness of 150 pm.

[0122] The first table (Table 1) summarizes the parameters of steps (a) and (b) by water jet projection which can be used on the extrados face 22 side of the blade 2 of [Fig.5], for example to carry out a removal of layer 100 which can be the anti-erosion layer 214.

[0123] [Tables 1] Step (a) Scarification Step (b) Stripping Nozzle travel speed (mm.s) between 100 and 200 between 100 and 200 Water jet pressure (bars) between 1500 and 1800 between 1000 and 1500 Distance between nozzle and layer to be treated (mm) between 50 and 70 between 50 and 70 Number of nozzle passes 1 1 or 2

[0124] The second table (Table 2) summarizes the parameters of steps (a) and (b) which can be used on the intrados face 21 of the blade 2 of [Fig.5], for example to also carry out a removal of layer 100 which can be the anti-erosion layer 214.

[0125] [Tables2] Step (a) Scarification Step (b) Stripping Nozzle travel speed (mm / s) between 200 and 500 between 100 and 500 Water jet pressure (bars) between 1500 and 2000 between 1000 and 2000 Distance between nozzle and layer to be treated (mm) between 60 and 80 between 60 and 80 Number of nozzle passes 1 or 2 between 1 and 10

[0126] The parameters of the first and second tables can make it possible to obtain a final cleaned layer, without residues and without altering the blade 2.

[0127] At the end of step (b), the condition of the final layer 100 of the blade 2 on the side of the intrados face 21 and / or extrados face 22 can be checked by carrying out step (i).

[0128] Fig. 6 illustrates a second example of a turbine blade 2 of a turbomachine 1 comprising the intrados 21 and extrados 22 faces to be treated.

[0129] The blade 2 according to this second example differs from the blade 2 of the first example ([Fig.5]) by a heterogeneous profile of the layers covering the intrados 21 and extrados 22 faces. This blade 2 may include carbon fibers embedded in epoxy.

[0130] On the underside, the blade 2 according to this second example can include an adhesive layer 209 of the polyurethane film 212 located on the underside 21, the polyurethane film 212 around this adhesive layer 209, and a finishing layer 216 (such as the anti-erosion layer 214), and optionally the tack layer 210 intercalated between the finishing layer 216 and the polyurethane film 212.

[0131] On the extrados side, the blade 2 of the second example may include the tack layer 210 located on the extrados face 22 and the finishing layer 216 (such as the anti-erosion layer 214) around this tack layer 210.

[0132] The different layers 209, 210, 214, 216 and the polyurethane film 212 can each have a different thickness from that of the other layers 209, 210, 214, 216 and / or be heterogeneous and irregular along the intrados 21 and extrados 22 faces.

[0133] Advantageously, the treatment process can be carried out on part 10, which may be blade 2, in particular for at least one of the following uses: - prepare one or more layers 100 of part 10, in particular before applying the coating 4 or the protective shield 3, - repair one or more damaged areas of layer 100, - retouch one or more 100 layers of the piece, and - clean at least one component of part 10 (such as the protective shield 3, the polyurethane film 214, etc.).

Claims

Demands

1. A method for treating a part (10) made of composite material, in particular for an aircraft turbomachine (1) or for an aircraft, the part (10) having at least one layer (100) covering a surface of this part (10), this method comprising a step (b) of stripping the at least one layer (100) of the part (10) so as to prepare at least part of said at least one layer (100), characterized in that prior to the stripping step (b), the method comprises a step (a) of scarifying the at least one layer (100) of the part (10).

2. A treatment method according to claim 1, characterized in that the scarification step (a) is carried out over the entirety of at least one layer of the part.

3. Processing method according to claim 1 or 2, characterized in that the steps (a, b) of scarification and stripping are carried out by projecting a jet of water (54) at, respectively, a first predetermined pressure (Pi) and a second pressure (P2).

4. Processing method according to claim 3, characterized in that the first pressure (PJ) is greater than the second pressure (P2).

5. Processing method according to claim 3 or 4, characterized in that the first pressure (Pi) is between 1500 and 2000 bars, and the second pressure (P2) is between 1000 and 2000 bars.

6. A treatment method according to any one of claims 3 to 5, characterized in that the water jet (54) is demineralized and abrasive-free.

7. A treatment method according to any one of claims 3 to 6, characterized in that the water jet (54) is projected by a single nozzle (52), a multi-nozzle or a nozzle comprising several sapphires.

8. Processing method according to any one of claims 1 to 7, characterized in that before and / or after the pickling step (b), the process further comprises a step (i) of inspecting at least one layer (100) of the part.

9. Processing method according to claims 7 and 8, characterized in that a measuring device (58), for example a camera or a sensor, is connected to the nozzle (52) or multi-nozzles, so as to check at least one layer (100) of the part.

10. Processing method according to any one of claims 1 to 9, characterized in that the part (10) of turbomachine (1) or aircraft is a blade (2), for example of a blower, or a casing.

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