• 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:
    â METHOD OF FIXING STRUCTURAL METAL REINFORCEMENT, USE OF A METHOD, AND, INJECTION MOLDâ The invention refers to a method of fixing structural metal reinforcement (10) on a portion (2) of a gas turbine blade (1) made of composite material, the method comprising positioning the structural metal reinforcement within an injection mold (20) , position the portion of the foot, on which the structural metal reinforcement must be fixed, within the injection mold, the portion of the foot and the metal reinforcement structural being positioned in relation to each other in its final relative position while leaving an interstice (26) between them, injecting adhesive in the intersection between the structural metal reinforcement and the basement § of the pole on which the structural metal reinforcement must be fixed, and polymerize the adhesive. The invention also provides an injection mold for the execution of such a method (...).
    公开号:BR112015000312B1
    申请号:R112015000312-5
    申请日:2013-07-03
    公开日:2020-07-21
    发明作者:Thierry Godon；Bruno Jacques Gérard Dambrine；Franck Bernard Léon Varin
    申请人:Snecma；
    IPC主号:
    专利说明:

    [0001] [001] The present invention relates to the general domain of gas turbine blades for aeronautical engines, which are made of composite material and which have a leading edge and / or trailing edge, provided with structural metal reinforcement.
    [0002] [002] A field of application of the invention is that of fan blades of turbine engines or propeller blades. Another field of application of the invention is that of output guide blades (OGV) for turbine engines.
    [0003] [003] It is known that fan turbine blades that are made of composite material are provided with structural metal reinforcement extending over the total height of the blades and beyond their leading edges. The same applies to exit guide blades.
    [0004] [004] Such structural reinforcement allows a set of composite blades to be protected against the fan being hit by a foreign body, such as a bird being ingested by the engine, for example. In particular, the structural reinforcement of metal serves to protect the leading edge (or trailing edge) of a composite material shovel by preventing risks of delamination, fibers breaking, or, more specifically, damage as a result of loss of cohesion between fibers and the matrix.
    [0005] [005] In general, the structural reinforcement comprises titanium parts made by milling from a block of material, and those parts are bonded directly on the external profile of the blade to be protected.
    [0006] [006] Nevertheless, bonding a structural metal reinforcement piece adhesive poses several problems. In particular, it is difficult to obtain a satisfactory adhesive thickness over all areas of contact areas between the metal reinforcement and the blade. In addition, with varying viscosity between different batches of adhesive, it is impossible to ensure the same thickness for the adhesive layer under constant manufacturing conditions.
    [0007] [007] Therefore, there is a need to have a method that makes it possible to ensure that the structural metal reinforcement can be adhesively bonded to the blade, in a reproducible manner, in particular in terms of the adhesive layer having a well controlled thickness. Purpose and Summary of the Invention
    [0008] [008] In accordance with the invention, this objective is achieved by a method of fixing structural metal reinforcement on a portion of a gas turbine blade made of composite material having fiber reinforcement densified by a matrix, the method comprising positioning the structural metal reinforcement inside an injection mold, position the blade portion, on which the structural metal reinforcement must be fixed, inside the injection mold, the blade portion and the structural metal reinforcement being positioned one in relative to the other in its final relative position while leaving an interstice between them, inject adhesive into the interstice between the structural metal reinforcement and the blade portion, on which the structural metal reinforcement must be fixed, and polymerize the adhesive.
    [0009] [009] The method of fixing the invention has the advantage of being based on a method of filling with resin by using a liquid technique of the type of liquid composite molding (LCM), and more particularly a method of injecting resin of the type of resin transfer molding (RTM) or vacuum assisted resin transfer molding (VARTM), in order to bond the structural metal reinforcement adhesive to the shovel. Such methods are properly well known, thus making it possible to ensure good control over the method of fixing structural metal reinforcement. With this method, it is possible in particular to have good control over the final thickness of the adhesive layer at all points in the contact area between the metal reinforcement and the blade. This makes it easy to obtain reproducible metal reinforcement adhesive bonding over all of the blades of a gas turbine.
    [0010] [0010] The blade can be positioned horizontally or vertically inside the injection mold. In the same way, the blade can be positioned partly or completely inside the injection mold. As a result, the method of the invention presents great freedom in use.
    [0011] [0011] Preferably, the method further comprises establishing a vacuum in the interstice between the structural metal reinforcement and the blade portion, on which the structural metal reinforcement must be attached, before injecting the adhesive. The establishment of a vacuum makes it possible to ensure that the adhesive is distributed completely evenly within the interstice.
    [0012] [0012] Also preferably, the structural metal reinforcement maintained within the injection mold by a vacuum or a suction cup effect. It is thus possible to have an injection mold made of two portions that are articulated to each other, each portion of the mold receiving a respective lateral flank of the structural metal reinforcement.
    [0013] [0013] The invention also provides for the use of the method as defined above for fixing structural metal reinforcement on the leading edge, trailing edge, or the tip of a fan blade, a propeller blade, or a output guide blade made of composite material and for use in a turbine engine.
    [0014] [0014] The invention also provides an injection mold for carrying out the method as defined above, the mold including a location for receiving structural metal reinforcement that must be fixed over a portion of the blade, and means for maintaining the structural metal reinforcement inside the mold. The mold may comprise two portions which are jointly articulated by a joint. Brief Description of Drawings
    [0015] [0015] Other characteristics and advantages of the present invention will appear from the following description made with reference to the attached drawings, which show modalities that are not limited in character. In the figures: figure 1 is a schematic view of a section of a turbine engine fan blade, made of composite material, with its leading edge covered with structural metal reinforcement; figures 2 to 5 show different steps of the method according to the invention for fixing the structural metal reinforcement to the leading edge of the blade of figure 1; figure 6 is a schematic sectional view of a structural guide blade made of composite material and its leading edge covered with structural metal reinforcement; and figure 7 shows the step of the method according to the invention for fixing the structural metal reinforcement on the leading edge of the blade of figure 6. Detailed Description of the Invention
    [0016] [0016] The invention applies to any gas turbine blade made of composite material for aircraft engines, and in particular refers to fan blades for turbine engines, as shown in the section in figure 1.
    [0017] [0017] In a known manner, the fan blade 1 has an aerodynamic surface that extends in particular between a leading edge 2 and a trailing edge 3. The aerodynamic surface of the fan blade also has a lateral pressure face 4 and a suction side face 5 forming the side faces of the blade interconnecting the leading edge and the trailing edge.
    [0018] [0018] Fan blade 1 is made of composite material with fiber reinforcement densified by a matrix. For example, the shovel can be made by three-dimensional weaving of a fiber preform and impregnating the preform with a matrix, the whole being formed by molding using a vacuum assisted resin injection method of the VARTM type .
    [0019] [0019] The fan blade 1 has structural metal reinforcement 10 which is adhesively attached to its leading edge 2 and which extends both axially beyond the leading edge of the blade and radially over the entire height of the leading edge (ie , from the root to the tip of the blade - not shown in figure 1).
    [0020] [0020] More precisely, the structural metal reinforcement 10 closely matches the shape of the blade leading edge 2, which extends to form a metal leading edge 2a. In addition to the leading edge of the blade, the structural metal reinforcement closely adjusts to portions of the face profiles on the pressure side and the suction side 4 and 5 of the blade.
    [0021] [0021] The structural metal reinforcement 10 has a straight section which is substantially in the form of a rounded V-shape having a base 11 which fits closely to the leading edge 2 of the blade and which is extended by two side flanks 12 and 13 which closely fit the pressure side 4 and the suction side 5 of the blade. Each of the lateral flanks 12 and 13 of the structural metal reinforcement has a profile that tapers towards the trailing edge of the blade.
    [0022] [0022] The structural metal reinforcement 10 is a one-piece part which is preferably based on titanium. This material has a great capacity for absorbing energy due to impacts.
    [0023] [0023] It should be noted that the structural metal reinforcement can be fixed in the same way to the trailing edge of the blade or the tip of the blade, instead of, or in addition to, the structural metal reinforcement fixed to the leading edge.
    [0024] [0024] The structural metal reinforcement 10 is fixed to the leading edge 2 of the fan blade 1 by a method of fixing the invention, as described below with reference to figures 2 to 5.
    [0025] [0025] Initially, the structural metal reinforcement 10 for fixing to the leading edge of the fan blade is positioned inside an injection mold 20.
    [0026] [0026] As shown in figure 2, the injection mold 20 has an internal profile surface that substantially corresponds to the external profile of the structural metal reinforcement 10, in particular having a base 21 that receives the base 11 of the structural metal reinforcement and two edges 22 and 23 respectively receiving the lateral flanks 12 and 13 of the reinforcement.
    [0027] [0027] In the example shown in figures 2 to 5, the structural metal reinforcement 10 is maintained within the injection mold 20 by establishing a vacuum. For this purpose, the edges 22 and 23 of the injection mold have channels 24 to establish a vacuum between the inner surface of the injection mold and the outer surface of the structural metal reinforcement in order to ensure that the reinforcement is kept inside the injection mold. injection.
    [0028] [0028] Of course, other means of providing such retention could be envisaged. For example, the inner surface of the injection mold could be provided with suction cups, against which the structural metal reinforcement is pressed.
    [0029] [0029] Furthermore, in the modality currently described, the injection mold is made up of two portions that are articulated to each other by a joint 25. In particular, the two articulated portions correspond to the two edges 22 and 23 of the injection mold. Naturally, it is possible to contemplate any other type of closure for the injection mold.
    [0030] [0030] Once when the structural metal reinforcement 10 has been properly positioned and retained within the injection mold, the leading edge of the fan blade, which must be covered, is placed in position. For this purpose, and as shown in figure 3, the injection mold 20 is opened (by moving the edges 22, 23 away so as to allow the leading edge 2 of the blade to be inserted into the injection mold.
    [0031] [0031] The leading edge 2 of the blade is retained or maintained in this position by engaging the blade in a stationary portion of the tool by means of its root and / or its trailing edge, for example. The injection mold 20 can then be closed by returning its edges 22 and 23 to their initial position.
    [0032] [0032] In this position (figure 4), the leading edge 2 of the blade and the structural metal reinforcement are retained relative to each other in their final relative position, that is, leaving between them an interstice 26 that is calibrated as a depending on the amount of adhesive to be injected.
    [0033] [0033] The subsequent step of the method, as shown in figure 5, consists of injecting the adhesive into the interstice 26 created between the structural metal reinforcement 10 and the leading edge 2 of the blade. For this purpose, a gasket 27 is positioned over the injection mold around the ends of the two lateral flanks 12 and 13 of the structural metal reinforcement, and the adhesive can be injected via any peripheral point of the leading edge of the blade ( this adhesive injection point is represented by the arrow 28 in figure 5). The adhesive fills the entire volume of the interstice 26.
    [0034] [0034] Preferably, the adhesive is injected after initially establishing a vacuum in the interstice 26 between the structural metal reinforcement 10 and the leading edge 2 of the blade in order to ensure that the adhesive is distributed evenly.
    [0035] [0035] For this purpose, it is possible to suck out air from the interstice via any peripheral portion of the leading edge of the blade (which is distinct from the adhesive injection point 28). It should be noted that the degree of vacuum within the interstice should not interfere with retention of the structural metal reinforcement within the injection mold. In particular, this air vacuum must be established while maintaining a pressure gradient between the interstice and the defined space between the injection mold and the structural metal reinforcement, and while ensuring that the gradient is sufficient to prevent the reinforcement of structural metal separate from the injection mold.
    [0036] [0036] The adhesive that is injected into the interstice 26 between the structural metal reinforcement 10 and the leading edge 2 of the paddle can be a polymer of the type polyester, polyurethane, polypoxy, bismaleimide, and / or phenolic, and it can be in the form of a folder.
    [0037] [0037] The adhesive is then polymerized. For example, with an epoxy type adhesive of the 180 ° C class, polymerization is carried out by raising the temperature to 140 ° C for 2 hours after injection.
    [0038] [0038] Then, the leading edge of the blade can be removed from the injection mold. For this purpose, it may be useful to open the injection mold again by moving its edges 22 and 23 away from each other, as described with reference to figure 3.
    [0039] [0039] With reference to figures 6 and 7, a description of another implementation of the method of the invention follows.
    [0040] [0040] In this example, the blade that must be provided with structural metal reinforcement is a turbine engine outlet guide blade (OGV).
    [0041] [0041] As shown in figure 6, OGV 1 'has an aerodynamic surface that extends in particular between a leading edge 2' and a trailing edge 3 '.
    [0042] [0042] As for the fan blade described above, OGV 1 'is made of composite material and features the structural metal reinforcement 10' which is adhesively bonded to its leading edge 2 'and which extends both axially beyond the leading edge of the blade and radially over the full height of the leading edge.
    [0043] [0043] The method of fixing the structural metal reinforcement 10 'on the leading edge 2' of the blade 1 'is identical to that described above. In particular, it mainly consists of positioning the structural metal reinforcement 10 'within an injection mold 20', then positioning the leading edge 2 'of the blade within the injection mold so that the blade and the metal reinforcement structural are positioned relative to each other in their final relative position, while an interstice 26 'is left between them. The adhesive can then be injected through an adhesive injection point 28 'positioned on the periphery of the leading edge of the blade. After the adhesive has polymerized, the blade and its leading edge can be demoulded from the injection mold.
    [0044] [0044] Compared to the implementation described with the fan blade, the injection mold used in this implementation is not necessarily made using two portions that are jointly articulated. Given the OGV's unshaped shape, it is not essential that you are able to open the injection mold in order to put the leading edge of the blade in position.
    [0045] [0045] Below is a description of characteristics that are common to both implementations described above.
    [0046] [0046] The blade (a fan blade or an OGV) can be positioned inside the injection mold vertically or horizontally depending on the requirements. It can also be positioned partly or completely inside the injection mold.
    [0047] [0047] Adhesive can be injected into the interstice left between the structural metal reinforcement and the leading edge of the blade via the periphery of the leading edge, as shown in the figures, or via one of the two radial ends of the structural metal reinforcement. It is also possible to design the injection of adhesive via one or more holes drilled through the base of the structural metal reinforcement, with these holes subsequently being plugged (for example, by laser forming).
    [0048] [0048] In addition, during the step of injecting adhesive into the injection mold, it is possible to bond a polyurethane film adhesive on the pressure and / or suction side sides of the blade. Such a film has the function of protecting the face of the shovel it covers against erosion.
    [0049] [0049] In the examples described, structural metal reinforcement is positioned on the leading edge of the blade. Naturally, the same element can also be applied to the fixation of structural metal reinforcement to the trailing edge or the tip of the blade. In particular, if it is necessary to attach such reinforcement to both the leading edge and the trailing edge of the blade, these operations can be carried out simultaneously using the same injection method. Likewise, the method of the invention applies equally well to propeller blades of turbo-propelled aeronautical engines.
    权利要求:
    Claims (7)
    [0001]
    Method of fixing structural metal reinforcement (10; 10 ') on a portion (2; 2') of a gas turbine blade (1; 1 ') made of composite material having fiber reinforcement densified by a matrix, the method characterized by the fact that it comprises: positioning the structural metal reinforcement inside an injection mold (20; 20 '); position the blade portion, on which the structural metal reinforcement must be attached, within the injection mold, the blade portion and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them an interstice (26; 26 '); injecting adhesive into the interstice between the structural metal reinforcement and the portion of the blade on which the structural metal reinforcement must be fixed; and polymerize the adhesive.
    [0002]
    Method according to claim 1, characterized in that it additionally comprises establishing a vacuum in the interstice between the structural metal reinforcement and the blade portion, on which the structural metal reinforcement must be fixed, before injecting the adhesive.
    [0003]
    Method according to either of claims 1 or 2, characterized in that the structural metal reinforcement is maintained within the injection mold by a vacuum or by a suction cup effect.
    [0004]
    Method according to any of claims 1 to 3, characterized in that the adhesive is a polymer.
    [0005]
    Use of a method as defined in any one of claims 1 to 4, characterized in that it is for fixing structural metal reinforcement (10; 10 ') on a leading edge (2; 2'), a trailing edge (3; 3 '), or the tip of a fan blade (1), a propeller blade, or an output guide blade (1') made of composite material and for use in a turbine engine.
    [0006]
    Injection mold (20; 20 ') for carrying out the method as defined in any one of claims 1 to 4, characterized by the fact that it includes a place for receiving structural metal reinforcement that must be fixed on a portion of the blade, and means (24) to maintain the structural metal reinforcement within the mold.
    [0007]
    Mold according to claim 6, characterized in that it comprises two portions (22, 23) which are jointly articulated by a joint.
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    同族专利:
    公开号 | 公开日
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    FR2992887A1|2014-01-10|
    CA2877214C|2020-08-04|
    EP2869985B1|2016-12-07|
    CA2877214A1|2014-01-16|
    WO2014009635A1|2014-01-16|
    US10259169B2|2019-04-16|
    CN104428128B|2017-01-18|
    US20150151485A1|2015-06-04|
    BR112015000312A2|2017-06-27|
    FR2992887B1|2015-05-01|
    RU2638401C2|2017-12-13|
    引用文献:
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    FR2892339B1|2005-10-21|2009-08-21|Snecma Sa|PROCESS FOR MANUFACTURING A COMPOSITE TURBOMACHINE BLADE, AND BLADE OBTAINED BY THIS PROCESS|
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    DE102009033164A1|2009-07-13|2011-01-27|Repower Systems Ag|Rotor blade of a wind energy plant and method for manufacturing a rotor blade of a wind turbine|
    US8419374B2|2009-08-14|2013-04-16|Hamilton Sundstrand Corporation|Gas turbine engine composite blade|
    US20110194941A1|2010-02-05|2011-08-11|United Technologies Corporation|Co-cured sheath for composite blade|US10907609B2|2014-07-15|2021-02-02|Ge Renewable Technologies|Apparatus and method for modifying a geometry of a turbine part|
    CA2857297C|2014-07-21|2021-08-17|Alstom Renewable Technologies|Apparatus and method for modifying a geometry of a turbine part|
    FR3025248B1|2014-08-27|2019-08-23|Safran|DRAWING VANE OF COMPOSITE MATERIAL FOR GAS TURBINE ENGINE AND METHOD FOR MANUFACTURING THE SAME|
    CN104787282A|2015-04-03|2015-07-22|郑伟|Propeller with metal leading edge and manufacturing technology|
    FR3040902B1|2015-09-10|2017-09-01|Snecma|METHOD FOR MANUFACTURING A PROTECTIVE REINFORCEMENT FOR A BLADEHAVING A CURVED ATTACK OR LEAK EDGE|
    US10677259B2|2016-05-06|2020-06-09|General Electric Company|Apparatus and system for composite fan blade with fused metal lead edge|
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    JP6735299B2|2018-03-09|2020-08-05|三菱重工業株式会社|Composite blade, leading edge metal cover forming unit, method for manufacturing composite blade|
    FR3079445B1|2018-03-28|2020-04-24|Safran|PROCESS FOR MANUFACTURING A BLADE OF COMPOSITE MATERIAL ON BOARD OF AN ADDED METAL ATTACK FOR GAS TURBINE|
    US10822969B2|2018-10-18|2020-11-03|Raytheon Technologies Corporation|Hybrid airfoil for gas turbine engines|
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    法律状态:
    2018-03-06| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2018-03-13| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2018-03-20| B06I| Technical and formal requirements: publication cancelled|Free format text: ANULADA A PUBLICACAO CODIGO 6.6.1 NA RPI NO 2462 DE 13/03/2018 POR TER SIDO INDEVIDA. |
    2019-11-12| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-05-19| B09A| Decision: intention to grant|
    2020-07-21| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 03/07/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1256597|2012-07-09|
    FR1256597A|FR2992887B1|2012-07-09|2012-07-09|METHOD FOR FASTENING A STRUCTURAL METAL REINFORCEMENT ON A PART OF A GAS TURBINE BLADE IN COMPOSITE MATERIAL AND INJECTION MOLD FOR IMPLEMENTING SUCH A METHOD|
    PCT/FR2013/051576|WO2014009635A1|2012-07-09|2013-07-03|Method for fixing a metal structural reinforcement to a part of a gas turbine vane consisting of a composite material, and injection mould for implementing such a method|
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