• 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:
    production method of a metallic insert for the protection of a leading edge in composite material. the present invention relates to a method of producing a metallic insert for the protection of a leading or trailing edge of a compressor blade of an aeronautical engine produced in composite material, through the stamping of blades (1) and welding among them by diffusion, characterized by the fact that it comprises the steps of: giving an initial shape to the blades by stamping to bring them closer to the shape of the top (1e) and the bottom (1l) of said insert; production of a core (3) that has the shape of the internal cavity of the metallic insert to be produced, one of its faces reproducing the internal shape of the insert's extrados and the other face reproducing the internal shape of the insert's soffits; positioning said blades around said core and integrating the set; apply vacuum and close the assembly by welding; assemble the assembly by hot isostatic compression; cut the set to extract the core (3) and separate the insert; produce the external profile of the insert through final machining.
    公开号:BR112012023423B1
    申请号:R112012023423-4
    申请日:2011-03-18
    公开日:2020-09-08
    发明作者:Jean-Michel Patrick Maurice Franchet；Gilles Charles Casimir Klein
    申请人:Snecma；
    IPC主号:
    专利说明:

    [0001] [0001] The present invention is inserted in the field of manufacture of metallic parts, and, more particularly, in the field of manufacture of leading edges or trailing edges in titanium for aeronautics, such as, for example, the leading edges for the wide blades of turbine engines, which are produced in composite material.
    [0002] [0002] Currently, turbo-blades' blades, for reasons of weight and cost, are mostly produced in composite material. These parts, which are subjected to significant mechanical stresses due to their rotation speed and the aerodynamic load supported by them, still need to withstand the possible impacts of particles or foreign bodies that penetrate the air shaft. For this purpose, the leading edge and / or the trailing edge of the propellers is protected by a metal part that covers their ends and is adhered to the composite material of the blade.
    [0003] [0003] The current range of manufacturing titanium leading edges for blades produced in composites is complex and heavy, which implies relevant costs. Indeed, manufacturing is based mainly on hot forming operations, which require tools capable of withstanding the temperatures practiced. It also requires considerable machining to be carried out, both in the intermediate parts stage and in the final production stage.
    [0004] [0004] For reasons of weight and mechanical resistance, in general the leading or trailing edges are produced in titanium and their thickness is relatively low. Taking into account this low thickness, it was naturally suggested to use a manufacturing method that includes the assembly of blades by a method of superplastic forming and diffusion welding (SPFDB for Super Plastic Forming and Diffusion Bonding). A method with these characteristics is described in the applicant's patent application EP 157427070.
    [0005] [0005] However, this method has the inconvenience of allowing, even with difficulty, to control only the internal shape of the cavity and, in particular, the method limits the possibilities of an ideal joining of the blades at the end of the cavity. In fact, it is important, for the mechanical resistance of the leading edge, to make a joint between the two blades that has a common tangent, transversal to the longitudinal geometric axis of the cavity and, if possible, that has a large radius of curvature, facts that do not enable the SPFDB method.
    [0006] [0006] The objective of the present invention is to remedy these drawbacks by suggesting a method of manufacturing leading edges or trailing edges produced in titanium that offers greater possibilities for the production of the leading and / or trailing edge cavity and that their production costs are moderate.
    [0007] - dar uma forma inicial às lâminas por matrizagem para aproximá-las da forma do extradorso e do intradorso do dito inserto, - produzir um núcleo que tem a forma da cavidade interna do inserto metálico a ser produzido, uma de suas faces reproduzindo a forma interna do extradorso do inserto e a outra face reproduzindo a forma interna do intradorso do inserto, as duas faces se unindo em uma ponta reproduzindo a forma interna do bordo de ataque ou de fuga, - posicionar as ditas lâminas ao redor do dito núcleo, as duas lâminas se unindo paralelamente na ponta do núcleo, e integrar o conjunto, - aplicar vácuo e fechar o conjunto por soldagem, - montar o conjunto por compressão isostática a quente, - cortar o conjunto para extração do núcleo e separação do inserto, - produzir o perfil externo do inserto através de uma usinagem final. [0007] For this purpose, the object of the invention is a method of producing a metallic insert for the protection of an leading or trailing edge of an aeronautical engine compressor blade produced in composite material, by blades and welding between them by diffusion, characterized by the fact that it comprises the steps of: - give an initial shape to the slides by matrix to bring them closer to the shape of the extruder and the soffit of said insert, - produce a core that has the shape of the internal cavity of the metallic insert to be produced, one of its faces reproducing the internal shape of the insert's extrados and the other face reproducing the internal shape of the insert's soffits, the two faces joining in one tip reproducing the internal shape of the leading or trailing edge, - position said blades around said core, the two blades joining in parallel at the tip of the core, and integrate the set, - apply vacuum and close the assembly by welding, - assemble the assembly by hot isostatic compression, - cut the set to extract the core and separate the insert, - produce the external profile of the insert through final machining.
    [0008] [0008] The use of hot isostatic compression associated with a core makes it possible to obtain continuity in the curvature of the internal cavity of the metallic insert and, in addition, to avoid stress concentrations in the upper part of the cavity.
    [0009] [0009] Preferably, the core has, in the half of each face, the shape to be given to the extrados of the blades and in its other half the shape to be given to the soffits of the blades, in order to produce two inserts for each operation.
    [0010] [0010] In this way, the production speed of leading and / or trailing edge inserts is doubled and the productivity of the workstation is improved.
    [0011] [0011] In advantageous terms, the core presents a longitudinal depression in the half of each of the faces, in order to make visible, after the hot isostatic compression, the cut lines that separate the two inserts.
    [0012] [0012] As this depression is visible externally, the technician realizes where to cut the set to separate the two attack edges produced.
    [0013] [0013] In a production mode, the initial matrix of the blades generates a housing at the tip of the leading or trailing edge.
    [0014] [0014] This housing serves as a place for inserting a reinforcement that will diffuse into the insert material at the time of the hot isostatic compression, increasing the mechanical resistance.
    [0015] [0015] As an advantage, in this mode of production, a reinforcement of composite fibers is installed in the housing at the moment of positioning the blades around said core.
    [0016] [0016] Preferably, the core is produced in refractory material.
    [0017] [0017] In another mode of production, the core is produced in a metallic material whose expansion coefficient is different from the expansion coefficient of the blades.
    [0018] [0018] In this mode of production, the core is favorably coated with a non-contaminating anti-diffusion barrier for the metallic material of the blades.
    [0019] [0019] Preferably, the metallic material of the core is a titanium or nickel alloy and the barrier is yttrium oxide.
    [0020] [0020] The invention will be better understood, and other objectives, details, characteristics and advantages will appear more clearly in the course of the detailed descriptive report that will follow, in a way of producing the invention carried out by way of example, purely illustrative and not restrictive , making reference to the attached schematic drawings.
    [0021] - a Figura 1 é uma vista esquemática de uma etapa de conformação das lâminas, durante a produção de um bordo de ataque através de um método de acordo com um modo de produção da invenção; - a Figura 2 é uma vista esquemática de uma etapa de pré-montagem das lâminas durante a produção de um bordo de ataque através de um método de acordo com um modo de produção da invenção; - a Figura 3 é uma vista esquemática de uma etapa de montagem das lâminas durante a produção de um bordo de ataque através de um método de acordo com um modo de produção da invenção; - a Figura 4 é uma vista esquemática de uma etapa de corte das lâminas durante a produção de um bordo de ataque através de um método de acordo com um modo de produção da invenção; - a Figura 5 é uma vista esquemática de um bordo de ataque realizado com o uso de um método de acordo com um modo de produção da invenção; - a Figura 6 é uma vista da parte frontal de um bordo de ataque no momento da etapa de conformação das lâminas de acordo com um variante do método de acordo com a invenção. [0021] In the drawings: Figure 1 is a schematic view of a blade forming step, during the production of a leading edge using a method according to a production method of the invention; Figure 2 is a schematic view of a step of pre-assembling the blades during the production of a leading edge using a method according to a production method of the invention; Figure 3 is a schematic view of a blade assembly step during the production of a leading edge using a method according to a production method of the invention; Figure 4 is a schematic view of a step of cutting the blades during the production of a leading edge using a method according to a production method of the invention; Figure 5 is a schematic view of a leading edge made using a method according to a production method of the invention; Figure 6 is a view of the front part of a leading edge at the moment of the blade forming step according to a variant of the method according to the invention.
    [0022] [0022] Referring to Figure 1, it is observed, in two stages, a hot forming operation of a titanium blade 1 to confer its internal shape that corresponds approximately to the external shape of a refractory core, said core having the precise shape to be given to the leading edge internal cavity. Two blades are successively formed in this way, one will become the leading edge extractor 1E and the other will become its IL soffit.
    [0023] [0023] Figure 2 shows a core 3, in refractory material (or in a metallic alloy, as well as ΙΝ100, which has a dilation coefficient quite different from the titanium expansion coefficient of the leading edge), surrounded by two blades 1E and 1I preformed, as already indicated, to adapt to the core over a large part of its length. We emphasize that the two blades are not shaped so that they come together, after assembly, with one facing the other according to a flat angle at the tip of the leading edge, but that they end in parts that are substantially parallel and aligned accordingly with the median plane of the nucleus. As a result, the two blades do not precisely involve the core on which they will be mounted at the tip of the leading edge. A residual space 4 is left which will be eliminated in the following steps.
    [0024] [0024] In this configuration, the blades are assembled by punctuation (not visible in the Figure) and TIG welding (welding by welding arc with a non-fusible tungsten electrode, under an inert atmosphere), so that the blades are joined together and remain installed in core 3.
    [0025] [0025] Figure 3 shows the result of an assembly step of the two blades 1E and 1I, around the refractory core, by means of an electron beam (FE) welding. This welding is carried out along a bead 5, parallel to the lateral edges of the blades, as shown in Figure 3, but also at the transverse ends of the piece (not shown).
    [0026] [0026] Figure 4 shows the leading edge realized after the blades were assembled using a hot isostatic compression method (or HIP for high isostatic pressure). The HIP method generates a deformation of the blades 1 that flatten against the core 3 whose shape is perfectly acquired by them. At the end of this stage, residual spaces 4 were removed.
    [0027] [0027] Figure 4 also shows how to perform some of the steps following the HIP compression step. First of all, it is interesting to note that each blade 1 was preformed in order to approach the leading edge of the leading edge in the first half and the lower edge of the leading edge in the other half. In the same way, the core 3 is shaped to present a longitudinal geometric axis of symmetry, representing the internal shape of the leading edge in one of these halves 3 'and the same shape in the other half 3 ", but this time positioned on the face opposite the The two internal shapes face each other through the median transverse plane of the core 3, which allows the two leading edges to be produced simultaneously.
    [0028] [0028] The right part of the Figure, thus, shows a first leading edge produced by the association of the half-blade of the extrapore 1'E positioned on the upper face of the nucleus with the half-blade of the soffit 1'I positioned on the lower face , while the left part shows a second leading edge produced from the half blade of the soffit 1 "I and the half blade of the soffit 1" E.
    [0029] [0029] Figure 4 also shows two cut lines 6 and 6 'that extend along the transverse median plane of the set formed by blades 1 and the core 3. They allow to separate the two leading edges from each other after production HIP compression. The Figure finally shows two detachment lines 7 and 7 'along which the excess material is removed on the side faces of the two leading edges.
    [0030] [0030] Figure 5 shows a leading edge at the end of production, after the separation of its twin part and the finishing of the profile through appropriate machining.
    [0031] [0031] Figure 6 shows a variant of the method according to the invention in which the forming step is carried out by handling a housing 8 between the two blades at the end of the residual space 4, on each side of the core 3. The housing is positioned in order to remain at the leading edge after HIP compression. This housing, as shown, but not necessarily, has a tubular shape that allows the insertion of a cylindrical reinforcement of composite fibers.
    [0032] [0032] It will now be described the development of the simultaneous manufacture of two leading edges using a method according to a production method of the invention.
    [0033] [0033] The operation is initiated by a classic matrixing operation that gives the blades a shape close to that desired for the leading edge. Whereas in the prior art the conformation should be precise to result in a part with virtually definitive dimensions, in this case, the conformation is used only as a means of resembling the intended shape, with the objective of simplifying the next task of conformation to hot. In addition, in the prior art, the matrix could be accompanied by the appearance of undulations on the surface of the blade after forming, especially if the objective was to produce a piece that had a high winding rate. With the invention, this phenomenon ceases to exist, the deformation during conformation becomes less severe.
    [0034] [0034] The shape given to the matrix allows to give the shape of the extrados to one half of the blade and the shape of the soffits to its other half. Two blades are then formed, one to be positioned at the top of the core and the second to be positioned at its bottom, facing the first.
    [0035] [0035] The two blades are mounted around the core through a scoring and TIG welding operation, along the side edges of the blades. Then the assembly is placed in a vacuum application enclosure to produce electron beam welding. An uninterrupted weld bead 5 is produced at the same time along the lateral edges of the blades, but also on their transverse edges, which allows to completely surround the core 3 and close the assembly again. The vacuum is then maintained between the blades 1 and the core 3, and in particular in the residual spaces 4 left between the blades 1E, 1I and the tips of the core 3. It is interesting to note that the operation of applying the vacuum, which is necessary to electron beam welding would also be necessary to carry out the next step of the method according to the invention. The combination of these two vacuum application operations results in the simplification of the method and also participates in the attempt to reduce the leading edge production cost.
    [0036] [0036] The set formed by the core 3 and the two blades 1E and 1I is then subjected to a hot isostatic compression operation, conducted at a temperature of about 940 ° C, in the case of a propeller made of titanium alloy TA6V. At this temperature, the metal is relatively molten and can flow under the pressure of about 1000 bars, which is applied to it. The two blades deform so that they take on the shape of the core 3 perfectly and suppress the residual spaces 4. In particular, the two blades join at the tip of the core according to a flat angle. At the same time, under the effect of heat, the two blades are welded together by diffusion. The combination of the two phenomena leads to the formation of an internal cavity in the leading edge that is exactly the shape of the core and that, at its tip, has a radius of curvature of the desired size. Due to the temperature adopted, the radius of curvature is produced without the appearance of a stress rate at this point, as was the case in the prior art.
    [0037] [0037] The continuity of operations consists of dismantling the two leading edges produced during the execution of cuts 6 and 6 'along the transverse median plane of the set that closes the core 3. To facilitate this operation, the core preferably presents along the cut lines, a longitudinal depression, not shown in the Figures, which marks the location of the cut lines. Throughout the HIP compression, the metal of the blades flows and fills the depression of the core 3 and recreates a depression on the outer face of the blades that can be viewed externally. The operator then knows where to practice the two cuts 6 and 6 '.
    [0038] [0038] In addition, the core is produced in a chosen material so that there is no adherence of the blades to itself. In general, the material is a refractory material, and with it there is no diffusion of titanium, or a metallic material that has a different expansion coefficient than that used for blades. These expansion differences prevent, in this case, the adhesion of blades 1 to the core 3 during the HIP compression operation. In a particular production mode, the metallic core is furthermore coated with a non-contaminating anti-diffusion barrier for titanium, such as yttrium oxide, which avoids any risk of adhesion during the HIP compression step.
    [0039] [0039] Whatever the core used, the invention allows its reuse, as it is not degraded or consumed during the implementation of the method according to the invention. This allows, therefore, a reduction in the production cost of a leading edge, regardless of the quality obtained for the production of its internal cavity.
    [0040] [0040] The completion of the method comprises a step of removing the excess material along the lateral edges of the two leading edges, by means of a cut according to the detachment lines 7 and 7 '. A final machining allows to check the external shape of the leading edge.
    [0041] [0041] In the variant illustrated in Figure 6, the pre-forming matrix of the blades is formed so as to generate a housing 8, at the end of the residual space 4. A composite fiber reinforcement is installed in that housing at the time of the installation of the blades 1 in core 3, before scoring and TIG welding. The fiber trapped in this housing diffuses through the metal of the blades during the HIP compression operation and creates a fibrous reinforcement at the tip of the leading edge. The resistance of the leading edge to erosion and impacts is also improved.
    [0042] [0042] Although the invention has been described in relation to a particular mode of production, it is quite evident that the invention includes all the technical equivalents of the described resources, as well as their combinations, if any, inserted in the context of the invention.
    权利要求:
    Claims (9)
    [0001]
    Method of production of a metallic insert for the protection of a leading edge or trailing edge of a compressor blade in composite material of an aeronautical engine, by blades' matrix (1) and diffusion welding between them, comprising the steps of: - give an initial shape to the slides by matrix to bring them closer to the shape of the extruder (1E) and the soffit (11) of said insert, - producing a core (3) that has the shape of the internal cavity of the metallic insert to be produced, one of its faces reproducing the internal shape of the insert's extrados and the other face reproducing the internal shape of the insert's soffits, - position said blades around said core, and fix the set in a fixed way, - place the assembly under vacuum and close the assembly by welding, - join the assembly, - cut the core extraction set (3) and separate the insert, - produce the external profile of the insert using a final machining operation, characterized by the fact that the two faces of the core meet at one end, reproducing the internal shape of the leading or trailing edge, in which the two blades that meet at the core tips are parallel and where the joint is joined by means of hot isostatic compression.
    [0002]
    Method, according to claim 1, characterized by the fact that the core (3) has, in the half of each face, the shape to be given to the extrados (1'E) of the blades and, in its other half, the shape to be given to the soffit (1'I) of the blades, in order to produce two inserts in each operation.
    [0003]
    Method, according to claim 2, characterized by the fact that the core (3) has a longitudinal intermediate depression in each of the faces, in order to produce, after hot isostatic compression, visible cut lines (6) separating the two inserts.
    [0004]
    Method according to any one of claims 1 to 3, characterized by the fact that the initial matrix of the blades generates a housing (8) at the tip of the leading or trailing edge.
    [0005]
    Method, according to claim 4, characterized by the fact that a reinforcement of composite fibers is placed in the housing (8) when the blades (1) are positioned around said core (3).
    [0006]
    Method according to any one of claims 1 to 5, characterized in that the core is produced in refractory material.
    [0007]
    Method according to any one of claims 1 to 5, characterized in that the core (3) is produced in a metallic material whose expansion coefficient is different from the expansion coefficient of the blades (1).
    [0008]
    Method according to claim 7, characterized in that the core (3) is coated with a non-contaminating anti-diffusion barrier for the metallic material of the blades (1).
    [0009]
    Method according to claim 8, characterized in that the metallic material of the core is a titanium or nickel alloy and the barrier is yttrium oxide.
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    同族专利:
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    法律状态:
    2019-01-08| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-10-29| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-07-21| B09A| Decision: intention to grant|
    2020-09-08| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 18/03/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1051992A|FR2957545B1|2010-03-19|2010-03-19|METHOD FOR MAKING A METALLIC INSERT FOR PROTECTING AN ATTACK EDGE IN COMPOSITE MATERIAL|
    FR1051992|2010-03-19|
    PCT/FR2011/050554|WO2011114073A1|2010-03-19|2011-03-18|Method for producing a metal insert to protect a leading edge made of a composite material|
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