• 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 manufacturing a blade of composite material with an attached metal leading edge comprises: - the successive draping, on a template (211) of the leading edge of the blade to be manufactured, a first layer of a base material (20) and a second layer of an adhesive material (30), - the transfer of the first and second layers (20, 30) draped in the cavity (141) of a metal foil (140) - docking the foil (140) comprising the first and second layers (20, 30) draped over the leading edge of a blade preform comprising a fibrous reinforcement impregnated with a precursor of a matrix, - the cocuisson dawn preform and the first and second layers draped to obtain a dawn composite material having on its leading edge a glued metal foil.
    公开号:FR3079445A1
    申请号:FR1852675
    申请日:2018-03-28
    公开日:2019-10-04
    发明作者:Magalie Blanquart；Maximilien Farrands；Romain Picon
    申请人:Safran SA；
    IPC主号:
    专利说明:

    Invention background
    The present invention relates to the general field of the manufacture of blades for an aeronautical engine with a gas turbine made of composite material comprising a metal leading edge.
    The presence of a metallic foil on the leading edge of a gas turbine aeronautical engine blade made of composite material makes it possible to protect the composite blade from abrasion / erosion and during the impact of a foreign body. This is particularly the case for the mobile fan blades of an aeronautical turbomachine which are exposed to the ingestion of a bird, hail, ice, etc. but also for stationary vanes or gas turbine distributor vanes.
    There are many methods for making a gas turbine engine blade from composite material. We can cite for example the manual laminate / draping process, the injection molding process of a fibrous preform, the embroidery process, the thermo-compression process, etc. These processes are mainly based on the use of a thermosetting resin (TD) or thermoplastic (TP).
    Once the composite material blade has been obtained, it is then necessary to assemble the protective metal foil on its leading edge. To this end, the metal foil, which is produced by mechanical processes such as stamping, forming or electroforming for example, is bonded to the leading edge of the blade made of composite material. This operation can be carried out in a mold ensuring the bonding of the metal foil. Examples of blades made of composite material provided with a metal foil on their leading edge are notably described in documents US2007092379 and US20160167269.
    However, bonding the metal foil to the leading edge of the composite material blade is a delicate operation, in particular as regards the control of the reproducibility of the positioning and of the distribution of the adhesive material between the 'dawn and tinsel. If the layer of adhesive material is not uniformly present between the blade and the foil, the quality of the bonding is degraded, which leads to a reduction in the mechanical strength of the foil and, consequently, a risk of loss of the foil by case of impact with an object or under the load of delamination efforts.
    Subject and summary of the invention
    The main object of the present invention is therefore to propose a method of manufacturing a blade made of composite material provided with a metal leading edge which does not have the aforementioned drawbacks.
    According to the invention, this object is achieved by a method of manufacturing a blade made of composite material with an attached metal leading edge for an aeronautical gas turbine engine, the method comprising:
    the successive layup, on a template of the leading edge of the blade to be manufactured, of a first layer of a base material and of a second layer of an adhesive material,
    - the transfer of the first and second draped layers into the cavity of a metallic foil,
    - docking of the foil comprising the first and second layers draped over the leading edge of a blade preform comprising a fibrous reinforcement impregnated with a precursor of a matrix,
    - the co-cooking of the blade preform and of the first and second layers draped so as to obtain a blade of composite material comprising on its leading edge a glued metallic foil.
    By conforming the first layer of base material and the second layer of adhesive material on a template corresponding to the shape of the leading edge of the blade to be manufactured and by transferring these layers from the template to the foil, a fixing interface is provided. continues between the foil and the leading edge of the preform. This avoids the appearance of porosities at the bottom of the cavity or spout formed by the foil, which improves the holding of the foil on the blade while ensuring very good reproducibility of the positioning of the assembly attached to the blade formed by the foil, the base material layer and the adhesive material layer.
    According to a first particular characteristic of the method of the invention, the step of transferring the first and second draped layers into the cavity of the metallic foil comprises placing the metallic foil on the layer of adhesive material and removing the assembly formed by the foil and the first and second layers of the template of the leading edge.
    According to a second particular characteristic of the method of the invention, it further comprises, after the placement of the metal foil on the layer of adhesive material and before the removal of the assembly formed by the foil and the first and second draped layers , the cutting of the parts of said first and second draped layers extending beyond the foil.
    According to a third particular characteristic of the method of the invention, it further comprises, before the layup of the first and second layers on the template of the leading edge, the deposition of a non-stick layer on the template. This makes it easier to remove the assembly consisting of the foil, the layer of base material and the layer of adhesive material.
    According to a fourth particular characteristic of the method of the invention, it further comprises, before the layup of the first and second layers on the template of the leading edge, the adjustment of the foil on the template.
    According to a fifth particular characteristic of the process of the invention, the base material of the first layer is chosen from: glass fibers, fine bronze wires, carbon fibers.
    According to a sixth particular characteristic of the process of the invention, the adhesive material of the second layer is chosen from: epoxy adhesive, reinforced epoxy adhesive, epoxy adhesive film, reinforced epoxy adhesive film.
    The method of the present invention is particularly applicable to the manufacture of a fan blade, an outlet guide vane, an inlet guide vane, or a vane with variable setting angle.
    Brief description of the drawings
    Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate exemplary embodiments thereof without any limiting character. In the figures:
    - Figure 1 is a schematic perspective view of an outlet guide vane according to one embodiment of the invention;
    - Figure 2 is a schematic perspective view showing the layup of a base layer and an adhesive layer on a template;
    - Figure 3 is a schematic perspective view showing the docking of a metal foil on the template of Figure 2;
    - Figure 4 is a schematic perspective view showing the compaction of the base layer and the adhesive layer with the metal foil;
    - Figure 5 is a schematic perspective view showing the cutting of the portions of the base layer and the adhesive layer which protrude from the metal foil;
    - Figure 6 is a schematic perspective view showing the removal of the metal foil provided with the base layer and the adhesive layer of the template;
    - Figure 7 is a schematic perspective view showing the docking of the metal foil provided with the base layer and the adhesive layer on an outlet guide vane preform and then the molding of the assembly;
    - Figure 8 is a schematic view showing the curing of the blade preform of Figure 7 with the metal foil provided with the base layer and the adhesive layer in a mold.
    Detailed description of the invention
    The invention applies to the production of blades of composite material for an aeronautical gas turbine engine having a metal leading edge.
    Non-limiting examples of such blades are in particular the fan blades, the outlet guide vanes (called OGV for “Outlet Guide Vane”), the inlet guide vanes (called IGV for “Inlet Guide Vane”), the vanes for variable setting angle (called VSV for “Variable Stator Vane”), etc.
    A method according to the invention will be described in relation to the manufacture of an outlet guide vane such as the vane 100 illustrated in FIG. 1 which comprises a vane body 110 extending in a longitudinal direction Dl between an internal platform 120 and an external platform 130 and in a transverse direction Dr between a leading edge 111 and a trailing edge 112. The blade body 110 also includes a lower face 113 and an upper face 114. A foil in metallic material 140 is also glued to the blade body 120 at the leading edge 111.
    The method of manufacturing the blade 100 begins with the successive layup on a template of the leading edge of the blade to be manufactured, with a first layer of a base material and a second layer of a material adhesive as illustrated in FIG. 2. More precisely, as shown in FIG. 2, a template 200 is used comprising at least one portion 211 reproducing the shape and the dimensions of the leading edge 111 of the blade 100 to be manufactured. The template 200 can be a part made especially for the implementation of the method of the invention or correspond to a rejected part or even correspond to a test part.
    Before layup, the portion 211 of the template 200 is preferably covered with a layer 10 made of a non-stick material, for example polytetrafluoroethylene (PTFE). A first layer of base material 20 is first of all draped over the portion 211 covered or not with the layer 10. The first layer 20 can be a stratum or a bidirectional fold (2D woven) of a material chosen from one of the materials glass fibers, fine bronze threads as used in the Bronze Mesh product manufactured by the company Lumicor®, carbon fibers. A second layer of adhesive material 30 is then draped over the layer 20. The second layer 20 may consist of an epoxy-based adhesive, reinforced or not, or a film of epoxy-based adhesive material, reinforced or not. The adhesive material may for example correspond to the epoxy resin EA914 manufactured by the company Hysol®, to the adhesive film AF191 manufactured by the company 3M®, to the adhesive film FM300 manufactured by the company Cytec®, or to the epoxy resin EA9396 manufactured by the company Hysol® company.
    By draping the layers 20 and 30 on the template 200, they are conformed according to a geometry corresponding exactly to that of the leading edge of the blade to be produced.
    Once the first and second layers 20 and 30 are draped over the portion 211 of the template 200, a foil of metallic material 140 is placed on the second layer of adhesive material 30 as illustrated in FIG. 3. The foil 140 can be produced for example stainless steel. The foil 140 has a shape and dimensions corresponding to the trailing edge of the blade to be manufactured. The foil 140 has a beak shape which defines a cavity 141 on the wall 141a from which the first and second draped layers 20 and 30 will be fixed.
    Before draping the first and second layers 20 and 30 on the template 200, the foil 140 can be adjusted on the template 200. The adjustment of the tinsel 140 on the template 200 may correspond to an adjustment of the dimensions of the foil, for example its length, and / or the shape of the foil, for example its curvature or its twist. The thickness of the metal foil being very small, its conformation on the template is achieved by manual pressures.
    The first and second layers 20 and 30 can be compacted by applying a compaction pressure Pc on the foil 140 as shown in FIG. 4. For this purpose, the template 200 provided with the first and second layers 20 and 30 and the foil 140 are arranged in a tool (not shown in Figure 4) capable of exerting on the foil 140 the compaction pressure Pc.
    As shown in FIG. 5, the parts of the first and second layers 20 and 30 which extend outside the foil 140 are then cut, the edges 140a and 140b of the foil being used to draw the cutting line on the template 200. This operation is optional and, according to an implementation variant, the first and second layers 20 and 30 of the foil 140 are allowed to exceed.
    The assembly formed by the foil 140 and the first and second layers 20 and 30 fixed on the surface 141a of the cavity 141 of the foil is removed from the template 200 (FIG. 6). This assembly is then approached on the leading edge 311 of an outlet guide vane preform 300 (FIG. 7). The layers 20 and 30 having been shaped to the exact shape of the trailing edge of the blade to be manufactured and transferred from the template into the cavity 141 of the foil 140, a continuous fixing interface is provided between the foil 140 and the edge attack 311 of the preform 300.
    The blade of composite material is obtained from a fibrous reinforcement densified by a matrix. In this case, it is made from a fibrous preform which can be obtained in various ways known to those skilled in the art. Typically, the preform can be obtained directly by three-dimensional (3D) weaving of threads (formed for example from carbon fibers) or by draping two-dimensional fibrous fabrics. The manufacture of an outlet guide vane made of composite material obtained from a fibrous reinforcement produced by three-dimensional weaving and densified by a matrix is described in particular in document WO2013088040. In the example described here, the outlet guide vane preform 300 is obtained from a plurality of two-dimensional layers or plies (2D fabric) made of prepreg and draped carbon fibers. The outlet guide vane preform can also be obtained from a fibrous carbon fiber reinforcement produced by three-dimensional weaving, the reinforcement having been impregnated with a thermosetting resin, for example an epoxy type resin.
    Alternatively, these blades made of composite material can be obtained directly by injection into a mold of a thermoplastic resin (TP) reinforced by short, long loads, etc. In this case the resin is not completely transformed (polymerized) so to allow its co-cooking with the assembly formed by the foil and the first and second layers fixed on the surface of the cavity of the foil.
    The dawn manufacturing process continues by placing the preform 300 and the assembly formed by the foil 140 and the first and second layers 20 and 30 positioned on the leading edge 311 of the preform 300 in a baking mold. 50. In a known manner, the baking mold 50 comprises two shells 51 and 52 each comprising an imprint 510 and 520 respectively, the imprints 510 and 520 forming, once joined together (ie after the mold has been closed), a molding cavity 530 corresponding to the shape of the blade to be manufactured (Figure 8).
    The mold 50 is then heated to a temperature which makes it possible to obtain the curing of the preform 300 with the assembly formed by the foil 140 and the first and second layers 20 and 30. The different layers, namely the pre-impregnated and the second layer (adhesive layer), have compatible curing cycles allowing the polymerization of the elements at the same time. The mold can be heated via the press plates, in an autoclave, or be provided with heating means, the heating being carried out according to a defined temperature ramp up to a temperature allowing the polymerization of the various polymers, a pressure being applied to the during this temperature rise in order to control the creep. A polymerization level is then applied followed by a decrease in temperature following a new defined ramp. The polymerization of the layers 20 and 30 takes place at the same time as the polymerization of the resin of the preform 300. The resins being compatible, the layers 20, 30 and the preform 300 become integral during cooking.
    After the cocooking, the dawn is unmolded. It can possibly undergo a post-curing cycle to improve its thermomechanical characteristics (increase in the glass transition temperature). No machining is necessary since, the part being molded, it respects the required dimensions. The blade 100 is then obtained, illustrated in FIG. 1 which comprises a blade body 110 provided with internal 120 and external 130 platforms made of composite material with the metallic foil 140 bonded to the leading edge 111 of the blade 100.
    The method of the invention also applies in particular to the manufacture of moving blades with or without platforms such as fan blades and blades with variable pitch angle used on non-faired motors ("open rotor").
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. A method of manufacturing a blade (100) of composite material with an attached metal leading edge for an aeronautical gas turbine engine, the method comprising:
    - The successive layup, on a template (211) of the leading edge (111) of the blade (100) to be manufactured, with a first layer of a base material (20) and a second layer d 'an adhesive material (30),
    the transfer of the first and second layers (20, 30) draped in the cavity (141) of a metallic foil (140),
    - docking of the foil (140) comprising the first and second layers (20, 30) draped over the leading edge (311) of a blade preform (300) comprising a fibrous reinforcement impregnated with a precursor of a matrix,
    - the co-cooking of the blade preform (300) and of the first and second layers (20, 30) draped so as to obtain a blade of composite material (100) comprising on its leading edge (111) a glued metallic foil (140).
    [2" id="c-fr-0002]
    2. The method of claim 1, wherein the step of transferring the first and second layers (20, 30) draped in the cavity (414) of the metal foil (140) comprises placing the metal foil on the layer of adhesive material (30) and the withdrawal of the assembly formed by the foil (140) and the first and second layers (20, 30) of the template (211) from the leading edge.
    [3" id="c-fr-0003]
    3. The method of claim 2, further comprising, after placing the metal foil (140) on the layer of adhesive material (30) and before removing the assembly formed by the foil and the first and second draped layers ( 20, 30), the cutting of the parts of said first and second draped layers extending beyond the foil.
    [4" id="c-fr-0004]
    4. Method according to any one of claims 1 to 3, further comprising, before draping the first and second layers (20, 30) on the template (211) of the leading edge, the deposition of a non-stick layer on the template.
    [5" id="c-fr-0005]
    5. Method according to any one of claims 1 to 4, further comprising, before draping the first and second layers (20, 30) on the template (211) of the leading edge, adjusting the foil on the template.
    [6" id="c-fr-0006]
    6. Method according to any one of claims 1 to 5, in which the base material of the first layer (20) is chosen from: glass fibers, fine bronze wires, carbon fibers.
    [7" id="c-fr-0007]
    7. Method according to any one of claims 1 to 6, in which the adhesive material of the second layer (30) is chosen from: epoxy adhesive, reinforced epoxy adhesive, epoxy adhesive film, reinforced epoxy adhesive film.
    [8" id="c-fr-0008]
    8. Application of the method according to any one of claims 1 to 7 to the manufacture of a fan blade, an outlet guide vane, an inlet guide vane, or an angle vane of variable timing.
    类似技术:
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    同族专利:
    公开号 | 公开日
    WO2019186029A1|2019-10-03|
    US20210010377A1|2021-01-14|
    EP3776682A1|2021-02-17|
    CN111936303A|2020-11-13|
    FR3079445B1|2020-04-24|
    EP3776682B1|2022-02-09|
    US11208904B2|2021-12-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR1230668A|1958-04-24|1960-09-19|Goodrich Co B F|Process and apparatus for the manufacture of heating laminates, applicable in particular to aircraft de-icing elements|
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    FR3008920B1|2013-07-29|2015-12-25|Safran|METHOD FOR MANUFACTURING A BLADE IN COMPOSITE MATERIAL WITH INTEGRATED METAL ATTACK FRAME FOR AERONAUTICAL GAS TURBINE ENGINE|
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    FR3111658A1|2020-06-18|2021-12-24|Safran Aircraft Engines|Blade made of composite material with three-dimensional woven fiber reinforcement and two-dimensional woven skin and its manufacturing process|
    法律状态:
    2019-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2019-10-04| PLSC| Publication of the preliminary search report|Effective date: 20191004 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-02-18| PLFP| Fee payment|Year of fee payment: 4 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1852675A|FR3079445B1|2018-03-28|2018-03-28|PROCESS FOR MANUFACTURING A BLADE OF COMPOSITE MATERIAL ON BOARD OF AN ADDED METAL ATTACK FOR GAS TURBINE|
    FR1852675|2018-03-28|FR1852675A| FR3079445B1|2018-03-28|2018-03-28|PROCESS FOR MANUFACTURING A BLADE OF COMPOSITE MATERIAL ON BOARD OF AN ADDED METAL ATTACK FOR GAS TURBINE|
    CN201980022718.1A| CN111936303A|2018-03-28|2019-03-20|Method of manufacturing a blade for a gas turbine engine with a fitted metal leading edge from a composite material|
    EP19718436.9A| EP3776682B1|2018-03-28|2019-03-20|Method of manufacturing a composite blade with a metallic leading edge for a gas turbine|
    US17/041,878| US11208904B2|2018-03-28|2019-03-20|Method for manufacturing a vane from a composite material with a fitted metal leading edge for a gas turbine|
    PCT/FR2019/050640| WO2019186029A1|2018-03-28|2019-03-20|Method for manufacturing a vane from a composite material with a fitted metal leading edge for a gas turbine|
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