• 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:
    The present invention relates to a method of making a metal reinforcement (30) for the leading edge, or trailing edge, of a turbomachine blade (10) , metal reinforcement (30) which comprises a base (32) and a top (34). said method successively comprises: a step of producing a plurality of v-tapered elements (30a,30b,30c,30d) constituting different parts of said metal reinforcement (30), thereby dividing said metal reinforcement (30) into several parts distributed between said base (32) and said top (34); a step of positioning said parts on equipment in the form of said leading edge, or said trailing edge, of said turbomachinery blade; and a step of firmly connecting the different parts in order to form said complete profile of said one-piece metal reinforcement (30) joining the different parts.
    公开号:BR112012015720B1
    申请号:R112012015720-5
    申请日:2010-12-22
    公开日:2021-08-17
    发明作者:Jean-François Fromentin；Stéphane André Leveque；Laetitia Sanchez；Thierry Jean Emile Flesch
    申请人:Snecma；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method and an installation for filling containers by weight.
    [0002] The present invention relates to a method for manufacturing a metal reinforcement for a composite or metal blade of a turbomachine.
    [0003] More specifically, the present invention relates to a method for manufacturing a metal reinforcement for the leading edge of a turbomachine blade.
    [0004] The field of the invention is that of turbo-propeller engines and, more specifically, that of turbomachinery blades made of composite or metallic material and whose leading edge comprises a structural metal reinforcement.
    [0005] However, the invention also applies to the fabrication of a metal reinforcement intended to reinforce the trailing edge of a turbomachinery blade.
    [0006] It is worth remembering that the leading edge corresponds to the front part of an aerodynamic profile, which turns to the airflow and divides it into an airflow on the lower surface and an airflow on the upper surface. The trailing edge corresponds to the rear of an aerodynamic profile where the flows from the lower and upper surfaces meet.
    [0007] It is known how to equip a turbomachinery blade made of composite material with a structural metal reinforcement that extends over its entire height and beyond its leading edge, as mentioned in document EP 1908919. protect the composite shovel during the impact of a foreign body against it, such as, for example, a bird, hail or even stones.
    [0008] In particular, the structural metal reinforcement protects the leading edge of the composite blade, thus preventing risks of delamination, fiber breakage or damage due to fiber disconnection with the matrix.
    [0009] By convention, a turbomachinery blade comprises an aerodynamic surface that extends, in a first direction, between the leading edge and the trailing edge, and in a second direction essentially perpendicular to the first, between the base and the top of the shovel. The structural metal reinforcement takes the form of the leading edge of the aerodynamic surface of the blade and extends, in the first direction, beyond the leading edge of the aerodynamic surface of the blade, taking the shape of the profile of the lower surface and the upper surface of the blade. blade, and, in the second direction, between the base and the top of the blade.
    [0010] In a known manner, the structural reinforcement of metal is a metal part produced entirely by milling a block of material.
    [0011] However, the metal reinforcement for the leading edge of a blade is a complex piece to manufacture, as it requires several complex reworking and machining operations that incur high manufacturing costs.
    [0012] In this context, the invention aims to solve the aforementioned problems by proposing a method to manufacture a metal reinforcement for the leading edge, or trailing edge, of a turbomachinery blade that allows to significantly reduce the manufacturing costs of this part and simplify the manufacturing range.
    [0013] Therefore, the invention proposes a method for manufacturing a metal reinforcement for the leading edge, or trailing edge, of a turbomachine blade, this metal reinforcement comprising a base and a top, said method comprising successively: - a step of producing several V tapered elements that constitute different sectors of said metal reinforcement, thus dividing said metal reinforcement into several sectors distributed between said base and said top; - a step of positioning said sectors on a tool in the form of said leading edge, or said trailing edge, of said turbomachinery blade; - a step of joining or solidarizing the different sectors in order to form said complete profile of said one-piece metal reinforcement joining the different sectors.
    [0014] Thanks to the invention, it is possible to manufacture structural metal reinforcement quickly and directly from various sectors which are then joined together to form a complete one-piece reinforcement.
    [0015] The fabrication of the metal reinforcement uniting the various sectors produced independently makes it possible to avoid the divergences associated with the entire fabrication of this part, in particular, on the thin sides of the reinforcement, which tend to twist.
    [0016] Indeed, the step of producing the various sectors of reinforcement makes it possible to limit the stresses accumulated in the part during the manufacturing process and, therefore, the deformation of the thin-walled sides during removal of the part from the tool.
    [0017] Thus, the manufacturing method deprives us of the complex fabrication of reinforcement by milling the body from one-piece flat bars, which requires the use of a large volume of material and, therefore, incurs high costs for the provision of the starting material.
    [0018] The method according to the invention also makes it possible to considerably reduce the manufacturing costs of a part of this type.
    [0019] The method for manufacturing a metal reinforcement for a turbomachinery blade according to the invention also comprises one or more of the characteristics mentioned below, considered separately or in all possible technical combinations: - during said step of producing the several elements that constitute the referred sectors of the referred metal reinforcement, each sector is produced by means of a laser fusion process; - said step of joining the different sectors is carried out by means of a diffusion brazing process; - the method comprises a heat forming step carried out at the same time as said joining step; - the method comprises a step of demolding said metal reinforcement from said tool, which is composed of several removable sections, said demolding being carried out by successive removal of said removable sections; - the method comprises a step for finishing said metal reinforcement consisting of a sub-step of polishing the surface of said reinforcement and/or a sub-step of reworking the sides of said reinforcement; - said step of joining the different sectors is carried out through a welding process; in this case, said step of joining the different sectors is advantageously followed successively by: - a step of positioning said joined sectors that form said reinforcement on a tool in the form of said leading edge, or said edge leakage, of said turbomachine blade; - a heat treatment step to relieve tension; - a hot forming step; - a step of demolding said metal reinforcement from said tool, which is composed of several removable sections distributed between said base and said top of said reinforcement; - a step of finishing said metal reinforcement consisting of a sub-step of polishing the surface of said reinforcement and/or a sub-step of reworking the sides of said reinforcement.
    [0020] The inventive matter also includes a method for repairing a turbomachine blade comprising a worn metal reinforcement on its leading edge or trailing edge, said method comprising: - a step of disconnecting said worn metal reinforcement from the said shovel; - a step of producing a metal reinforcement for the leading edge, or trailing edge, of a turbomachinery blade according to the invention, - a step of rigidly connecting said metal reinforcement manufactured in the previous step to said blade of turbomachine.
    [0021] The inventive matter also includes a tool for practicing the method for fabricating a metal reinforcement for a turbomachinery blade according to the invention, which tool comprises several removable sections.
    [0022] The tool according to the invention may also include one or more of the following characteristics, considered separately or in all possible technical combinations: - said tool comprises several removable sections in greater number than the reinforcement sectors; - said tool is made of a material with an expansion coefficient greater than that of the material of said reinforcement.
    [0023] Other characteristics and advantages of the invention will be better understood by reading the description below, given by way of elucidation and, therefore, in no way limiting, with reference to the attached drawings, among which: - Figure 1 illustrates a side view a blade with a metal structural reinforcement for the leading edge obtained by means of the manufacturing method according to the invention; figure 2 illustrates a partial view, in cross-section and in plan of figure 1 along section A-A; Figure 3 illustrates a block diagram representing the main steps for manufacturing a metal structural reinforcement for the leading edge of a turbomachine blade of the manufacturing method according to the invention; figure 4 shows a view of the metal reinforcement for the leading edge of a turbomachine blade during the first step of the method illustrated in figure 3; figure 5 shows a view of the metal reinforcement for the leading edge of a turbomachine blade during the second step of the method illustrated in figure 3; and - figure 6 illustrates a view of the metal reinforcement for the leading edge of a turbomachinery blade in its final condition obtained by the manufacturing method according to the invention illustrated in figure 3.
    [0024] Throughout the drawings, common elements have the same reference numbers, unless otherwise indicated.
    [0025] Figure 1 illustrates a side view of a blade with a structural metal reinforcement for the leading edge obtained by means of the manufacturing method according to the invention.
    [0026] The illustrated blade 10 is, for example, a mobile blade of a turbomachine (not illustrated).
    [0027] The blade 10 comprises an aerodynamic surface 12 that extends, in a first axial direction 14, between the leading edge 16 and the trailing edge 18 and, in a second radial direction 20 essentially perpendicular to the first, between the base 22 and the top 24.
    [0028] The aerodynamic surface 12 forms an upper surface 13 and a lower surface 11 of the blade 10, the upper surface 13 being shown in Figure 1. The lower 11 and upper surfaces 13 form the side faces of the blade 10, which connect the leading edge 16 to trailing edge 18.
    [0029] In this embodiment, the paddle 10 is a composite paddle typically obtained by draping a woven composite material. By way of example, the composite material used may comprise a mixture of woven carbon fibers and resin matrix, the mixture being molded by means of a vacuum resin injection process of the RTM type ("resin transfer molding").
    [0030] The blade 10 comprises a structural reinforcement of metal 30 glued to its leading edge 16 and extending, in the first direction 14, beyond the leading edge 16 of the aerodynamic surface 12 of the blade 10 and, in the second direction 20, between the base 22 and the top 24 of the blade.
    [0031] As shown in Figure 2, the structural reinforcement 30 takes the form of the leading edge 16 of the aerodynamic surface 12 of the blade 10, which extends forming a leading edge 31, the so-called reinforcement leading edge.
    [0032] By convention, the structural reinforcement 30 is a one-piece piece comprising an essentially V-section, with a base 39 that forms the leading edge 31 and bifurcates into two lateral sides 35 and 37 that assume the shape, respectively, the lower surface 11 and the upper surface 13 of the aerodynamic surface 12 of the blade. Sides 35, 37 have a profile that tapers or tapers towards the trailing edge of the blade.
    [0033] The base 39 has a rounded internal profile 33 capable of assuming the rounded shape of the leading edge 16 of the blade 10.
    [0034] The structural reinforcement 30 is metallic and preferably titanium based. Indeed, this material has a great capacity for absorbing energy due to impacts. The reinforcement is glued to the paddle 10 by means of a glue known to those skilled in the art, such as, for example, a cyanoacrylic or epoxy glue.
    [0035] This type of metal structural reinforcement 30 used to reinforce a composite blade of a turbomachine is described in more detail, namely, in patent application EP 1908919.
    [0036] The method according to the invention makes it possible to manufacture a structural reinforcement as shown in figures 1, 2 and 6, and figures 2 and 6 illustrate the reinforcement 30 in its final condition.
    [0037] Figure 3 illustrates a block diagram representing the main principles of a method 100 for fabricating a metal structural reinforcement 30 for the leading edge of a blade 10 as shown in Figures 1 and 2.
    [0038] The first step 110 of fabrication method 100 is a step of producing several sectors 30a, 30b, 30c, 30d of a metal reinforcement 30.
    [0039] Figure 4 illustrates, in particular, the different sectors 30a, 30b, 30c, 30d obtained during the first step 110.
    [0040] For this purpose, the metal reinforcement 30 is previously divided into several sectors during the design or during the construction of a numerical model.
    [0041] According to an advantageous embodiment of the invention, the different sectors of a reinforcement 30 are produced independently by a rapid prototyping process and, more specifically, by a laser fusion process. In fact, laser fusion is a process that makes it possible to create each sector of reinforcement 30 by deposition of several successive layers of material, which makes it possible to easily create the complex shapes and, in particular, the tapered V-shape of the reinforcement. metal 30 with low thicknesses on sides 35, 37.
    [0042] The laser fusion process, or laser fusion sintering process, is a process known to those skilled in the art and dealt with in several patents, such as, in particular, in patents EP 2060343 or EP 2125339; therefore, we will not describe in more detail the working principle of this manufacturing method.
    [0043] The fabrication of the metal reinforcement 30 by joining several sectors 30a, 30b, 30c, 30d makes it possible to avoid the divergences associated with the fabrication of this part in a one-piece way from a one-piece flat bar and, in particular, to avoid twisting on the sides 35, 37 low thickness.
    [0044] Each sector 30a, 30b, 30c, 30d produced in the first step 110 constitutes a part of the base 39 of the leading edge 31 and sides 35, 37 of the final reinforcement 30.
    [0045] The second step 120 of the manufacturing method 100 is a step of positioning the different sectors 30a, 30b, 30c, 30d on a specific molding tool 40 in order to unite them. Figure 5 illustrates this second positioning step 120.
    [0046] The tool 40 is made by associating several sections 40a, 40b, 40c, 40d, 40e, 40f that cooperate with each other to form a mold cavity 43 complementary to the internal profile 33 of the reinforcement 30. The mold cavity 43 of the tool 40 essentially corresponds to the profile of the blade 10 when the different sections 40b, 40c, 40d, 40e, 40f are brought together.
    [0047] Thus, during the second stage, the different sectors 30a, 30b, 30c, 30d of the reinforcement 30 are positioned sector by sector on the tool 40 in order to build, in its entirety, the profile of the reinforcement on the tool. The shape of the tool 40 and, in particular, the profile of the mold cavity 43 are constructed in order to form the desired shape and profile of the lower and upper surfaces of the metal reinforcement 30.
    [0048] For greater advantage, the tool 40 comprises several sections in greater number than the sectors of the reinforcement 30.
    [0049] The third step 130 of the manufacturing method 100 is a step of joining, or joining, the different sectors 30a, 30b, 30c, 30d of the reinforcement 30 by means of a diffusion brazing process. For this purpose, joints 31 present between each adjacent sector 30a, 30b, 30c, 30d are filled by brazing cords obtained by brazing by diffusion of a filler metal in the form of a tape or powder. This filler metal makes it possible to join the different sectors 30a, 30b, 30c, 30d in order to form a reinforcement 30 integral with its final profile.
    [0050] It is worth remembering that diffusion brazing is an operation that consists in making the filler metal completely migrate to the base material until the disappearance of the molten filler metal part.
    [0051] Diffusion brazing makes it possible, in particular, to obtain excellent results for the joining of machined parts that are relatively small and with complex profiles.
    [0052] The fourth step 140 of the manufacturing method 100 is a hot forming step performed on the same molding tool 40 as the previous steps, the tool then being taken to an oven heated to the forging temperature of the materials used.
    [0053] This hot forming step makes it possible to conform the reinforcement 30 in order to obtain its final shape.
    [0054] Preferably, the tool 40 is made of a material with a coefficient of expansion greater than that of the reinforcement material. As an example, when the reinforcement is based on titanium, the tool 40 can be made of steel. The profile and dimensions of tool 40 are designed taking into account the removal of different materials used.
    [0055] According to a preferred embodiment of the invention, the hot forming step 140 is performed during the diffusion brazing step 130.
    [0056] The fifth step 150 is a step of demolding said reinforcement 30 of tool 40. For this purpose, the different sections 40a, 40b, 40c, 40d, 40e, 40f of tool 40 are removable and can be disassembled individually, thus facilitating the release of the reinforcement 30.
    [0057] In order to facilitate demoulding, it is possible to prepare the tool 40 by first depositing a protective layer in its mold cavity 43, thus preventing the reinforcement 30 from sticking to it. By way of example, this protective layer can be an aluminum layer.
    [0058] Finally, the sixth step 160 of fabrication method 100 is a step for finishing and reworking the reinforcement 30 by machining. This finishing step 160 consists in particular of: - reworking the sides 35, 37; the step consists in particular of trimming the sides 35, 37 and thinning the lower and upper surfaces of the sides 35, 37; - polishing the reinforcement 30 in order to obtain the desired surface condition.
    [0059] Figure 6 illustrates the reinforcement 30 in its final condition obtained by the manufacturing method according to the invention.
    [0060] In relation to these main manufacturing steps, the method according to the invention may also comprise steps for the non-destructive control of the reinforcement 30, thus allowing to ensure the geometric and metallurgical conformity of the unit obtained. As an example, non-destructive control can be performed by an x-ray method.
    [0061] According to a second embodiment of the invention, the step of joining, or joining, the various reinforcements by diffusion brazing is replaced by a step of joining the various reinforcements by welding, for example, by means of an electron beam .
    [0062] In this second embodiment, the step of joining by welding is performed without the use of a molding tool. This step takes place after the step of producing the different sectors of reinforcement.
    [0063] Therefore, in this second embodiment, the method for manufacturing a metal structural reinforcement 30 for the leading edge of a blade 10, as shown in figures 1 and 2, comprises: - a first stage of production of the various sectors 30a , 30b, 30c, 30d of the metal reinforcement, for example, by a laser melting process; - a second stage of joining by welding the different sectors 30a, 30b, 30c, 30d that constitute different parts of the reinforcement; - a third step of positioning said sectors 30a, 30b, 30c, 30d joined together on a tool forming the internal mold cavity of the reinforcement and having the profile of the leading edge of the turbomachine blade; - a fourth stage of heat treatment to relieve stress; - a fifth step of hot forming; - a sixth step of demolding the metal reinforcement 30 from the tool, the tool being divided into different removable sections in order to facilitate the demolding of the reinforcement 30; - a step of finishing said metal reinforcement 30 consisting of a sub-step of polishing the surface of said reinforcement and/or a sub-step of reworking the sides of the reinforcement 30.
    [0064] We describe the method according to the invention mainly for a titanium-based metal structural reinforcement; although; the method according to the invention also applies to materials based on nickel or steel.
    [0065] We describe the invention, in particular, for the manufacture of a metal reinforcement for a composite blade of a turbomachine; however, it also applies to the fabrication of a metal reinforcement for a metal turbomachine blade.
    [0066] We describe the invention, in particular, for the manufacture of a metal reinforcement for the leading edge of a turbomachine blade; however, it also applies to the fabrication of a metal reinforcement for the trailing edge of a turbomachinery blade.
    [0067] We describe the invention, in specific, with a laser fusion process in the implementation of the first step; however, it is possible to implement the first step, for example, by another prototyping process or by a machining process.
    [0068] The interest in laser fusion implementation of reinforcement through several independent sectors makes it possible to limit the stresses accumulated in the part during the laser fusion manufacturing method and, therefore, the deformation of the thin wall sides during removal of the tool part. Indeed, the reinforcement has thin-walled sides that, the larger the part size, the more it tends to deform during tool removal.
    [0069] The method for fabricating a metal reinforcement according to the invention can be perfectly incorporated into a general process for repairing a composite or metal blade of a turbomachine. A method for repairing a turbomachinery blade, therefore, consists of: - a first step of disconnecting the worn metal reinforcement by means of pyrolysis, which allows heating the glue or resin to a temperature in the order of 100 to 400°C at in order to soften and/or degenerate the glue used to join the metal reinforcement to the turbomachine blade; - a second step of manufacturing a new metal reinforcement according to the invention; - and finally a third step of joining the metal reinforcement manufactured in the previous step to the blade using a glue known to those skilled in the art to glue the reinforcement onto the blade, such as, for example, a cyanoacrylic or epoxy glue.
    [0070] The other advantages of the invention are, in particular, the following: - reduction of manufacturing costs; - reduced manufacturing time; - simplification of the manufacturing range; - reduction of material costs.
    权利要求:
    Claims (11)
    [0001]
    1. Method for fabricating a metal reinforcement (30) for the leading edge or trailing edge of a turbomachine blade (10) comprising a base (32) and a reinforcement top (34) from a plurality of elements ( 30a, 30b, 30c, 30d) which form different sectors of said metal reinforcement (30), so that said metal reinforcement (30) is divided into several sectors distributed between said base (32) and said top ( 34), said method characterized in that it comprises successively: - a step (110) of producing a plurality of V-shaped tapered elements (30a, 30b, 30c, 30d); - a step (120) of positioning said sectors (30a, 30b, 30c, 30d) on a tool (40) in the form of said leading edge or said trailing edge of said turbomachine blade (10); - a step (130) of joining the different sectors so as to form said complete profile of said one-piece metal reinforcement (30) by recombining the different sectors (30a, 30b, 30c, 30d).
    [0002]
    2. Method for manufacturing a metal reinforcement (30) of a turbomachinery blade, according to claim 1, characterized in that, during said step (110) of producing a plurality of elements that form said sectors ( 30a, 30b, 30c, 30d) of said metal reinforcement (30), each sector (30a, 30b, 30c, 30d) is produced by means of a laser fusion process.
    [0003]
    3. Method for manufacturing a metal reinforcement (30) of a turbomachine blade, according to any one of claims 1 or 2, characterized in that said step (130) of joining different sectors (30a, 30b, 30c , 30d) is carried out by means of a diffusion brazing process.
    [0004]
    A method for manufacturing a metal reinforcement (30) of a turbomachine blade, according to claim 3, characterized in that it comprises a step (140) of hot forming performed together with said step of joining (130).
    [0005]
    A method for manufacturing a metal reinforcement (30) of a turbomachinery blade, according to any one of claims 3 or 4, characterized in that it comprises a step (150) of demolding said metal reinforcement (30) from said tool. (40), said tool (40) being formed by a plurality of removable sections (40a, 40b, 40c, 40d, 40e, 40f), said demolding being carried out by successive removal of said removable sections (40a, 40b, 40c , 40d, 40e, 40f).
    [0006]
    A method for manufacturing a metal reinforcement (30) of a turbomachine blade, according to claim 5, characterized in that it comprises a step (160) of finishing said metal reinforcement (30) consisting of a sub-step of polishing the surface of said reinforcement and/or in a sub-step of reworking the sides (35, 37) of said reinforcement (30).
    [0007]
    7. Method for manufacturing a metal reinforcement (30) of a turbomachinery blade, according to any one of claims 1 or 2, characterized in that said step (130) of joining different sectors (30a, 30b, 30c , 30d) is carried out through a welding process.
    [0008]
    8. Method for manufacturing a metal reinforcement (30) of a turbomachine blade, according to claim 7, characterized in that said step (110) of joining different sectors (30a, 30b, 30c, 30d) is followed successively by: - a step of positioning said joined sectors (30a, 30b, 30c, 30d) forming said reinforcement on a tool in the form of said leading edge (31) or said trailing edge of said blade (10 ) of turbomachine; - a heat treatment step to relieve tension; - a hot forming step; - a step of demolding said metal reinforcement (30) from said tool, said tool being formed by a plurality of removable sections distributed between said base (32) and said top (34) of said reinforcement; - a step of finishing said metal reinforcement (30) consisting of a sub-step of polishing the surface of said reinforcement (30) and/or a sub-step of reworking the sides (35, 36) of said reinforcement. (30).
    [0009]
    9. A method for repairing a turbomachinery blade comprising a worn metal reinforcement from the leading edge or the trailing edge, said method characterized by comprising: - a step of disconnecting said worn metal reinforcement from said blade; - a step of fabricating a metal reinforcement (30) for a leading edge or a trailing edge of a turbomachine blade (10) as defined in any one of claims 1 to 8, - a step of securing said reinforcement to metal (30) manufactured in the step prior to said turbomachine blade (10).
    [0010]
    Tool (40) for implementing the method for fabricating a metal reinforcement (30) of a turbomachinery blade as defined in any one of claims 1 to 9, said tool (40) characterized by being composed of a plurality of sections removable (40a, 40b, 40c, 40d, 40e, 40f), the number of removable sections (40a, 40b, 40c, 40d, 40e, 40f) being greater than the number of sectors (30a, 30b, 30c, 30d) of the reinforcement (30).
    [0011]
    Tool (40) according to claim 10, characterized in that it is made of a material with a coefficient of expansion greater than the coefficient of expansion of the material of said reinforcement (30).
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    同族专利:
    公开号 | 公开日
    EP2516107A1|2012-10-31|
    RU2551741C2|2015-05-27|
    US9199345B2|2015-12-01|
    CA2785374A1|2011-06-30|
    US20120255176A1|2012-10-11|
    FR2954200A1|2011-06-24|
    JP5628342B2|2014-11-19|
    RU2012130953A|2014-01-27|
    CA2785374C|2018-02-27|
    CN102686356A|2012-09-19|
    JP2013527359A|2013-06-27|
    FR2954200B1|2012-03-02|
    BR112012015720A2|2021-01-26|
    EP2516107B1|2016-07-06|
    CN102686356B|2016-05-11|
    WO2011076890A1|2011-06-30|
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    法律状态:
    2021-02-09| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-02-17| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2021-07-27| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-08-17| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 22/12/2010, OBSERVADAS AS CONDICOES LEGAIS. PATENTE CONCEDIDA CONFORME ADI 5.529/DF, QUE DETERMINA A ALTERACAO DO PRAZO DE CONCESSAO. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR0959551A|FR2954200B1|2009-12-23|2009-12-23|PROCESS FOR MAKING A TURBOMACHINE METAL TURBINE REINFORCEMENT|
    FR0959551|2009-12-23|
    PCT/EP2010/070576|WO2011076890A1|2009-12-23|2010-12-22|Method for creating metal reinforcement for a turbine engine blade|
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