• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A method of treating a composite part (10) having a metal shield (12) attached to a core (11) with a binder (14) to separate the shield from the core, comprising the steps of: a) subjecting the metal shield to compression stresses tending to lengthen it; b) if necessary, heating the workpiece or cooling it to soften or weaken the binder.
    公开号:FR3025735A1
    申请号:FR1458776
    申请日:2014-09-17
    公开日:2016-03-18
    发明作者:Patrick Gascher；Eric Mangeard；Vincent Desfontaine
    申请人:Europ Technologies；Scaleo Chip SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to processes for treating composite parts and more particularly those comprising a metal protective shield attached to a support core using a binder. The invention particularly relates to the separation of a metal element attached to a composite part.
    [0002] Many composite parts, for example carbon fiber, are coated on the surface of a metal shield, especially ti e, to protect them against abrasion phenomena and increase their resilience. Thus, it is known to make blades or blades of turbines with a core of composite material, monolithic or sandwich, on which a shield in ti. e is glued to serve as a surface and / or structural reinforcement. EP 1908 919 Bi and EP 0854 208 Bi disclose examples of such parts. During the use of the turbomachine, the metal shield is likely to wear or receive shocks that can damage it. The repair of the part encounters the difficulty of removing the metal shield without degrading the composite core, the glue used being particularly powerful. B1 proposes to eliminate the metal shield by electroerosion, which involves the use of chemicals, with the corresponding listr and environmental constraints. The invention aims to solve this problem of separation of the metal shield and the soul without damaging the latter, so as to allow reuse with a new metal shield. The invention achieves this through a method of treating a composite part comprising a metal shield fixed to a core with a binder, in order to separate the shield from the core, comprising the steps t a) subjecting the metal shield to compressive stresses tending to lengthen it, b) if necessary, heating the workpiece or cooling it to soften or weaken the binder. The method may comprise a step (c) of separating the shield and the core. The invention makes it possible to subject, because of the tendency of the shield to lengthen in response to the introduction of compression stresses, the binder and / or the interface thereof with the core or the shield to shear or tearing stresses and to facilitate the detachment of the shield of the soul and thus to avoid exposing the soul, during the removal of the shield to actions likely to deteriorate. The invention makes it possible to repair numerous parts used in particular in the aeronautics, which hitherto was completely replaced, because of the difficulty encountered in separating the shield from the core without damaging the latter or of costs. excessive operation, related to the use of chemicals. Step a) is preferably performed before step b). Alternatively, step b) is performed before step a). In another variant, steps a) and b) take place simultaneously. If necessary, step a) is applied exclusively, when the introduction of compressive stresses is sufficient to release the shield, particularly in the case of thin binder and / or weak binder. In this case, the shear stress generated by the elongation of the metal part is greater than the limit allowed by the binder, especially at the interface with the core or the shield. Preferably, steps a) and b) are carried out when the workpiece is heated. This makes it possible to heat to the temperature necessary for a given input stress ratio, which makes it possible to optimize the heating parameters and the parameters related to the introduction of stresses. No. In the case where the part is cooled, it is possible to do step b) before step a). The cold causes a hardening of the binder and therefore an increase in shear stresses. Preferably, in this case, the operations a) and b) are very close together in time, leaving no time for the part to warm excessively between them. The introduction of compression stresses in step a) can be done mechanically or by shock wave. The introduction of compressive stresses can be carried out in particular by conventional or ultrasonic preload blasting, straightening, hammering, burnishing, flappeening, laser shock, cavitation peening and / or self-shrinking. Preferably, the introduction of compressive stresses is carried out by shot blasting or hammering, better by shot blasting or ultrasonic hammering, the blasting being preferably carried out using a captive projectile apparatus (s). The intensity of treatment generating compressive stresses is preferably at least FION F70C ALMEN, better F3ON F1 OC. The introduction of compressive stresses can be made locally to a device moved on the workpiece or a movement of the workpiece relative to the apparatus, which can then be static. The supply of heat or cold in step b) can be achieved by conduction and / or convection and / or radiation. The supply of heat or cold can be made by placing the room in an oven or an oven or in a refrigerated enclosure. The supply of heat or cold can still be made locally by means of a device moved on the part, or with the part moving under the means of application of the method. One can have a source of heat or cold coupled with the tool used to apply compression stresses, including a straightening tool. The supply of heat or cold can be carried out so as to bring, at least locally, the binder at a temperature between -273.15 ° C and 450 ° C. The metal shield may be machined prior to the introduction of compression stresses, preferably to remove a front portion thereof, particularly when defining a leading edge of the relatively narrow piece. The part may be a blade or a blade of a turbomachine and the shield define the leading edge of this blade or blade. The shield can be, after separation of the soul, replaced by a new metal shield stuck on the soul. The invention will be better understood on reading the following detailed description, nonlimiting exemplary embodiments thereof, and on examining the appended drawing, in which: FIG. perspective an example of a composite part that can be treated with the method according to the invention for taking off the shield of the core, FIG. 2 is a cross section of the part of FIG. 1, in the plane II of FIG. 1, and Figure 3 illustrates the shield portion to be removed by pre-machining, in an exemplary implementation. The part 10 shown in FIGS. 1 and 2 is a blade of a turbomachine fan. The blade 10 comprises a composite core 11, being for example obtained by draping or weaving a thermoplastic or thermosetting composite material. The latter may be an assembly of woven and molded carbon fibers by a RTM (Resin Transfer Molding) vacuum injection process. The core 11 is formed with an aerodynamic shape and is covered on its leading edge by a shielding metal skin which is attached by a binder 14 to the core. The skin 12 defines by its front p the leading edge 13 of the piece 10. The invention consists in lengthening the metal shield by the implementation of a compression technique consisting in the introduction of compressive stresses since 5 the outer face 18 of the shield. Introduction of compression constraints Many techniques can be used to introduce these compression constraints. It may be preferred to use a technique that allows for local processing of the workpiece without having to disassemble it from the rest of the machine. It can also be preferred a technique ii allows treatment on the entire shield by moving for example a treatment device along it. A first technique that can be used to introduce compressive stresses is conventional shot peening.
    [0003] This technique consists in projecting on the shield projectiles which can be various, for example balls or cut wires, whose size can range from 0.3 mm to 10 mm, and preferably from 1 mm to 4 mm, the projectiles being made of metals, ceramic, glass or composite materials, and preferably steel or ceramic. The projectiles can be projected on the surface to be treated with an angle of incidence relative to the normal which goes from 0 ° to 90 °, and preferably from 0 ° to 45 °. The intensity of ALMEN treatment can reach F1 ON to F70C, and preferentially F3ON to FIOC. Another technique that can be used to introduce compressive stresses is ultrasonic shot blasting, as disclosed for example in WO 2008 25 047 048. The projectiles may be the same as in the case of conventional prestressing shot blasting, and for example be formed beads, cut son, ..., their size preferably from 0.3mm to 1mm, and preferably from 1mm to 4mm. The materials used are preferably selected from metals, ceramics, glass, composites, and preferably steel and ceramics. Compression stresses can also be introduced by a straightening method, using needles or other projectiles that acquire velocity in contact with a vibrating surface and impact the surface to be treated. These projectiles act coriurd, a network of small hammers striking the surface to be treated at high frequency and independently of each other. Superficial compressive stresses are thus created. The difference in stress between the surface and the core of the shield causes changes in the curvature of the latter. The vibrating surface may in particular be vibrated by pneumatic means or by one or more linear motors or by one or more sonotrodes. . Compression stresses can be introduced by a hammering technique, for example using a hammer gun as described in US 6343495. In this technique, one or more projectiles are projected onto the surface to be treated. 10 needles or hammers, preferably having a spherical head, thanks to the vibration of a sonotrode. The impact of the projectiles on the surface to be treated generates the compression stresses sought. The size of the head which impacts the surface to be treated is, for example, from 0.5 mm to 20 nm in diameter or in width, and more preferably from 1 to 6 mm; the projectiles length goes for example from 2 to 50mm. Any material selected from metals, ceramics, plastics, composites, and preferably steel may be used to make the projectiles. The projectiles are confined between the vibrating surface that transmits energy to them and the surface to be treated. The vibration amplitude of the vibrating surface is, for example, from 10 microns c / c to 200 micrometers c / c, and more preferably from 30 to 80 micrometers cic.
    [0004] The frequency of the vibrating surface is for example between 15 kHz and 80 kHz, better between 20 kHz and 40 kHz. The intensity AL I N of treatment may range from FION to F70C, preferentially F3ON to F10C. The technique used to introduce compressive stresses may still be flap peening. Flap peening uses a lamella equipped at its ends of media embedded in a matrix, as described in patent US3638464 A. The blade is installed on an axis and rotated using a pneumatic or electric grinding wheel. The coverslip is applied to the workpiece and the media strike the workpiece. The media are for example a size of 0.3 to 10, preferably 1 to 4 mm. They can be made of metals, ceramics, glass or composites, preferably in steel or ceramic. The rotational speed ranges, for example, from 0 to 10,000 revolutions per minute, preferably between 1500 revolutions per minute and 6000 revolutions per minute. The angle of incidence of the media relative to the normal to the surface to be treated can range from 0 ° to 90 °. The intensity ALMEN of the treatment is preferably F 1 ON to F70C, more preferably from F3ON to 5 FlOC. Compression stresses can still be introduced by a laser shock technique, as described in US Patent 6670577 B2. The shock waves are generated by an explosion due to very high power laser pulses, which make it possible to obtain sufficient pressures to exceed the limit of elasticity of the materials and a plastic deformation of the superficial layers of the shield. is performed with a laser beam directed on the surface to be treated creates a plasma. The compression stresses can be introduced by roller burnishing or similar process, in particular by the so-called LPB (low plasticity browning) method is a method similar to roller burnishing using a ball in place of a roller. The surface layer of the part is then deformed plastically by rolling on its surface a roller or a ball under heavy load. The compression constraints can still be applied by autofrettage. This amounts to applying on the shield a pressure greater than. the operating pressure, in order to cause a heterogeneous plastic deformation through its thickness. When the applied pressure is released, there appear residual compression stresses known as autofrettage. This pressure is applied for a short time using a fluid (liquid, gas) or a conical tool, similar to the mandrinage. Compression stresses can also be exerted with so-called cavitation peening techniques or with a water jet. Heat Treatment The heat treatment may include a heat input to soften the binder used to attach the shield to the core, typically is an epoxy or cyano acrylic glue.
    [0005] The heat input can be achieved by conduction or convection or radiation or induction, or a combination of at least two of these modes of heat transfer.
    [0006] The temperatures reached can be between a few degrees (20 ° C.) and several hundred degrees while remaining below the melting temperature) of degradation of the core and skin, and usually between 20 ° C. and 20 ° C. 200 ° C. A device blowing hot air can be used. Alternatively, the part can be placed in an oven, oven or installation comprising radiating panels or induction heating systems. In the case of the production of cold, it is possible to use a refrigerator, freezer, freezer, liquid nitrogen, a vortex tube or vacuum to cool the part to be treated at a temperature of preferably between -273.degree. 0 ° C.
    [0007] Soul Generally, the core can be composite with all types of materials, not limited to carbon fibers, for example glass fiber, aramid fiber, and / or silicon carbide, among other possibilities. The soul can be monolithic or sandwich. The processes for manufacturing these parts can be various and cover all thermoset and thermoplastic manufacturing processes, including draping, weaving, RTM, LRI, stamping, thermoforming, thermocompression, among others. The matrix of the core may be a polyester, epoxy, vinylester, phenolic or polyimide resin, this list not being limiting. The core may still be metallic, for example aluminum or magnesium.
    [0008] In general, the core may comprise a matrix loaded or reinforced in various ways. Binder Any type of glue can be used, the binder is not limited to an epoxy or cyanoacrylic glue.
    [0009] Shield The shield is preferably metallic, and may especially be made of titanium or one of its alloys. The shield is for example of 'material selected from Ta6V, Ti550, 7075, 2024, 2017, Inconel 4, Invar®.
    [0010] Advance Operation of Shield Machining In order to facilitate the detachment of the shield, an upstream machining operation can be performed to remove a front part of the metal shield. This machining can be achieved by various material removal processes including milling, water jet cutting, grinding, sanding, among others. This operation is preferably carried out before any other operation. In FIG. 3, the boundary of p is indicated by a broken line. e removed by machining. It can be seen that this only concerns the front part 20 and part of the binder 14, the core 11 does not. t not affected. After machining, the shield 12 is in two disjoint pieces, which can be treated individually to separate them from the core. EXAMPLE A turbomachine blade as shown in FIGS. 1 and 2 is treated with a composite core of 3D woven carbon fibers and a titanium skin glued to the core, forming a shield. The skin is treated using a STRESS VOYAGER4I shot blasting gun from the company SONATS equipped with an ER18-2 nozzle equipped with 3mm diameter needles so as to obtain a stress level AL N of F20A. The tip is moved along the dawn, on the skin. Then, the skin thus treated is exposed to the heat of a hot-air gun delivering air at 350 ° C. It is found that the skin is deformed due to compression stresses previously introduced, and can be peeled easily enough without damaging the core.
    [0011] The invention is not limited to this example and applies to multiple pieces having a core of a first material on which is bonded a skin serving as a structural reinforcement. The expression "having one" shall be understood as being synonymous with "comprising at least one" unless the contrary is specified.
    权利要求:
    Claims (28)
    [0001]
    REVENDICATIONS1. A method of treating a composite part (10) having a metal shield (12) attached to a core (11) with a binder (14) to separate the shield from the core, comprising the steps of: a) subjecting the metal shield to compression stresses to lengthen it, b) if necessary, heating the workpiece or cooling it to soften or weaken the binder.
    [0002]
    2. Method according to claim 1, step a) being carried out before step b).
    [0003]
    3. Method according to claim 1, step b) being performed before step a).
    [0004]
    4. The method of claim 1, wherein steps a) and b) occur simultaneously, step a) taking place in an oven, an oven or in a refrigerated enclosure, or using a heat or cold source twinned with a tool used to exert compressive stresses, no. a straightening tool.
    [0005]
    5. Method according to claim 1, step a) is applied exclusively.
    [0006]
    6. Method according to any one of the preceding claims, the introduction of compressive stresses in step a) being carried out mechanically or by shock wave.
    [0007]
    7. Method according to claim 6, the introduction of the compressive stresses being carried out by conventional or ultrasonic preload blasting, straightening, hammering, roller burnishing, including LPB, flap-peening, laser shock, self-shrinking, cavitation shot blasting, spray jet. water and / or magnetic shock.
    [0008]
    8. The method of claim 7, the introduction of compressive stresses being carried out by shot blasting.
    [0009]
    9. The method of claim 8, the introduction of compressive stresses being carried out by ultrasonic blasting.
    [0010]
    10. Method according to one of claims 8 and 9, the shot blasting being carried out using a projectile apparatus (s) captive (s).
    [0011]
    11. The method of claim 7, the introduction of compression stresses eff ected by flap-peening.
    [0012]
    12. The method of claim 7, the introduction of compressive stresses being performed by roller burnishing. I. ten 3025735 10
    [0013]
    13. The method of claim 7, the introduction of compressive stresses e effected by autofrettage.
    [0014]
    14. A method according to any one of claims 1 to 7, wherein the compression stresses being effected by a shock wave.
    [0015]
    15. The method of claim 14, the introduction of compressive stresses being effected by laser shock.
    [0016]
    16. The method of claim 14, the introduction of compression stresses being performed by cavitation peening.
    [0017]
    17. The method of claim 14, the introduction of compressive stresses being effected by magnetic shock.
    [0018]
    18. A method according to any one of the preceding claims, the processing intensity generating compressive stresses being at least FION F70C AL N, better F3ON FlOC.
    [0019]
    19. A method according to any one of the preceding claims, the introduction of compressive stresses being effected locally by means of a device moved on the workpiece or a movement of the workpiece relative to the apparatus.
    [0020]
    20. Method according to any one of the preceding claims, the supply of heat or cold in step b) being carried out by conduction and / or convection and / or radiation and / or induction. 20
    [0021]
    21. The method of claim 19, the supply of heat or cold being performed locally with the aid of a device moved on the workpiece, or the piece moving under the method of application of the method.
    [0022]
    22. A method according to any preceding claim, the supply of heat or cold being effected so as to bring, locally at least, the binder 25 at a temperature between -200 and 450 ° C.
    [0023]
    23. A method according to any one of the preceding claims, the shield being made of titanium or one of its alloys, Inconel®, Invar®.
    [0024]
    24. A method according to any one of the preceding claims, the core (11) comprising fibers and a matrix, namely glass fibers, carbon, aramid, silicon carbide, the matrix campo .t resin , especially polyester, epoxy, vinylester, phenolic, or polyamide.
    [0025]
    25. A method according to any one of claims 1 to 22, the core (11) being metallic, no. steel, aluminum, magnesium, and their alloys. 3025735 11
    [0026]
    26. A method according to any one of claims 1 to 24, the piece (10) being a blade or a blade of a turbine engine and the shield (12) defining the etching (13) of the blade or blade.
    [0027]
    27. A method according to any one of the preceding claims, the shield being separated from the core, and preferably after detachment of the core, replaced by a new metal shield glued to the core.
    [0028]
    28. A method according to any one of the preceding claims, the metal shield being machined before the introduction of compression stresses, preferably to remove a front portion (20) of the metal shield.
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    同族专利:
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    EP3194724B1|2018-11-28|
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    WO2016041957A1|2016-03-24|
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    引用文献:
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    法律状态:
    2015-07-31| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-18| PLSC| Search report ready|Effective date: 20160318 |
    2016-07-29| PLFP| Fee payment|Year of fee payment: 3 |
    2017-07-31| PLFP| Fee payment|Year of fee payment: 4 |
    2018-07-30| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-27| PLFP| Fee payment|Year of fee payment: 6 |
    2020-09-29| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458776A|FR3025735B1|2014-09-17|2014-09-17|PROCESS FOR PROCESSING A COMPOSITE PIECE|FR1458776A| FR3025735B1|2014-09-17|2014-09-17|PROCESS FOR PROCESSING A COMPOSITE PIECE|
    EP15763020.3A| EP3194724B1|2014-09-17|2015-09-15|Method for treating a composite part|
    US15/512,215| US20170252896A1|2014-09-17|2015-09-15|Method for treating a composite part|
    PCT/EP2015/071092| WO2016041957A1|2014-09-17|2015-09-15|Method for treating a composite part|
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