• 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 invention relates to a method for manufacturing a turbomachine blade (100) of composite material comprising a fiber reinforcement densified by a matrix, the method comprising: - the production of a multilayer weave in order to obtain a first fibrous preform ( 1) in one piece, said first preform (1) comprising a first portion (2) forming a blade root preform and extended by a second portion (3) having a thickness less than the thickness of the first portion (2). ), said second portion (3) forming a tenon preform, - the realization of a multilayer weave to obtain a second fibrous preform (4; 14; 14 ') in one piece, said second preform (4; 14; 14 ') comprising a first portion (5; 15; 15') formed of two skins (5a; 5b; 15a; 15b; 15'a; 15'b) delimiting between them an inner housing (6), said first part ( 5; 15; 15 ') forming a blade preform, and at least a second part (7; 17; 17 ') extending from the outer surface of said skins (5a; 5b; 15a; 15b; 15'a; 15'b), said at least second part (7; 17; 17 ') forming a platform preform; - assembling the first preform (1) in the consolidated or unconsolidated state with the second preform (4; 14 ') in the unconsolidated state by engagement of the second part (3) of the first preform (1) in the inner housing (6) of the first part (5; 15; 15') of the second preform ( 4; 14; 14 '), and - the co-densification of the first (1) and second (4; 14; 14') preforms thus assembled to obtain a turbomachine blade (100).
    公开号:FR3032648A1
    申请号:FR1551258
    申请日:2015-02-16
    公开日:2016-08-19
    发明作者:David Marsal；Clement Roussille；Jeremy Blachier
    申请人:SNECMA SAS；Herakles SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to a method for manufacturing a turbomachine blade of composite material. It is known to implement in the turbomachines mobile blades formed of a metallic material. It is desirable to replace these blades of metal material with blades formed of a composite material to reduce the weight of the turbomachines. Such a replacement is all the more advantageous as certain composite materials such as ceramic matrix composite materials are compatible with exposure to an increased operating temperature, thus making it possible to improve the performance of the engine. Currently, the blades of metal material may be made by a molding process in which the upper surface (heel) and the lower surface (platform) are molded together with the blade and the foot of the blade. The inventors have sought to replace a blade made of metallic material with a blade of composite material having a fibrous reinforcement formed in one piece by weaving. However, the realization of a blade having all the secondary functions required from a single textile preform presents a number of problems due in particular to the difficulties encountered in producing and shaping the textile preform. There is therefore a need to have new processes for making a simple way a turbomachine blade composite material having the desired properties. OBJECT AND SUMMARY OF THE INVENTION For this purpose, the invention proposes a method for manufacturing a turbomachine blade of composite material comprising a fiber reinforcement densified by a matrix, the method comprising: - producing a weave multilayer in order to obtain a first fibrous preform in one piece, said first preform comprising a first part forming a blade root preform and extended by a second part having a thickness less than the thickness of the first part, said second part tenon preform part, - the realization of a multilayer weave to obtain a second fibrous preform in one piece, said second preform comprising a first portion formed of two skins delimiting between them an inner housing, said first part forming blade preform, and at least a second portion extending from the outer surface of said skins, said at least one second platform preform part, - the assembly of the first preform in the consolidated or unconsolidated state with the second preform in the unconsolidated state by engagement of the second part of the first preform in the inner housing. of the first part of the second preform, and - the co-densification of the first and second preforms thus assembled to obtain a turbomachine blade.
    [0002] Unless otherwise stated, the thickness of a portion corresponds to the smallest transverse dimension of this portion. A preform is said to be in the consolidated state when it has undergone a consolidation step during which its initial porosity has been partially filled by a deposition of a consolidation phase, this preform in the consolidated state retaining a residual porosity which may be completely or partially filled during the subsequent co-densification step. Various examples of consolidation methods are detailed below. A preform is said to be unconsolidated when it lacks such a consolidation phase. A preform in the unbound state may be in the dry state or be impregnated with a precursor of a material of a consolidation phase, the consolidation being in the latter case not finalized because of non-consolidation. transformation of the precursor into a consolidation phase. The invention is based on separately making a first and a second preform each supporting a limited number of functions so as to render both of them easily formable and to assemble these two preforms to form the preform constituting the reinforcement. fibrous dawn to make. By separating the functions of the blade on two fibrous preforms, it becomes possible to simplify the textile definition of each of the first and second preforms and to facilitate their eventual formatting. Thus, compared to the case where the blade is manufactured from a single-piece fiber preform, the invention significantly simplifies the manufacturing process of the blade. In addition, the second fibrous preform takes up the extremums of effort at the level of the leading and trailing edges, and for example at the level of the foot vein platform. This platform being textilement linked to the skin forming blade preform its mechanical strength is improved which thus confers good mechanical properties to the manufactured dawn. The first preform may advantageously consist exclusively of a blade root preform and a stud preform. The blade foot part is in itself a part subject to particularly demanding dimensional constraints and it is therefore particularly advantageous for a preform, in this case the first preform, to be intended almost exclusively for the production of the part of the blade. 20 feet of dawn whose realization is relatively difficult. The blade thus manufactured can be used in a turbine or a turbomachine compressor. In an exemplary embodiment, once the first and second preforms are assembled, the second preform may not extend along the first portion of the first blade root preform. Alternatively, once the first and second preforms are assembled, the second preform may extend along all or part of the first portion of the first blade root preform preform.
    [0003] As will be detailed below, the first and second preforms are not necessarily at the same stage of their respective ranges during assembly. In an exemplary embodiment, the first preform can be consolidated before the assembly step and the first preform in the consolidated state can be assembled with the second preform in the unconsolidated state during the assembly step. .
    [0004] In a variant, the first preform in the unconsolidated state can be assembled with the second preform in the unconsolidated state during the assembly step. In an exemplary embodiment, said at least second portion of the second preform forming a platform preform can be made by weaving two sets of layers of son each passing through respectively one of the skins of the first portion of the second preform forming a preform. . Alternatively, said at least second portion of the second platform preform preform may be made by weaving oversize in the lower portion of the first portion of said second blade preform preform. In an exemplary embodiment, the method may comprise, after the step of co-densification of the first and second preforms, a step of machining the blade preform so as to reduce the thickness of the skins. In an exemplary embodiment, the first preform can be obtained after multilayer weaving of a plurality of carbon fiber threads and the second preform can be obtained after multilayer weaving of a plurality of silicon carbide threads. In this case, the first preform can be consolidated by a carbon-based consolidation phase before the assembly step and the first preform thus consolidated can be assembled with the second preform in the unconsolidated state during the step assembly.
    [0005] In an exemplary embodiment, the co-densification of the first and second preforms may be carried out using at least one of the following methods: chemical vapor infiltration, liquid densification and infiltration method. melted state.
    [0006] In an exemplary embodiment, the method may comprise, after the step of assembling the first and second fibrous preforms and before co-densification, a step of reinforcing the assembly of introducing or forming mechanical links between the first and second preforms at their assembled portions.
    [0007] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the invention will emerge from the following description of particular embodiments of the invention given by way of non-limiting example with reference to the accompanying drawings, in which: FIG. 1 shows an example of an assembly of first and second fibrous preforms before and after assembly in the context of a process according to the invention; FIG. 2 represents another example of structure that can be obtained by assembling first and second fibrous preforms in the context of a method according to the invention; FIG. 3 is a detail of the structure illustrated in FIG. 2; FIG. 4 is a partial sectional view of FIG. 5 shows another example of a structure that can be obtained by assembling first and second fibrous preforms in the context of a process. According to the invention, FIGS. 6 and 7 are flowcharts detailing the different steps of implementation of examples of processes according to the invention; FIG. 8 is a perspective view of a turbomachine blade manufactured by a method according to the invention, and - Figure 9 is a perspective view of a turbomachine wheel equipped with a plurality of blades manufactured by implementing the method according to the invention. DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows a first example of an assembly 30 of first and second fibrous preforms 1 and 4. The first fibrous preform 1 consists of a single piece obtained by multilayer weaving and comprises a first part 2 forming a blade root preform extended by a second portion 3 having a thickness less than the thickness of the first portion 2, said second portion 35 forming a tenon preform. The second fibrous preform 4 consists of a single piece obtained by multilayer weaving and comprises a first part 5 formed of two skins 5a and 5b delimiting between them an inner housing 6, said first part 5 forming a blade preform, and a second portion 7 extending from the outer surface of said skins 5a and 5b, said second portion 7 forming a platform preform. In the example illustrated in FIG. 1, the second part 7 of the second preform 4 forming a platform preform is made by weaving excess lengths 7a and 7b in the lower part of the first part 5 of the second preform 4 forming a blade preform. . Irrespective of the embodiment envisaged and as illustrated in FIG. 1, the thickness e 1 of the first skin 5 a and / or the thickness e b of the second skin 5 b may be substantially constant along all or part of the first part. 5 of the second preform 4 forming blade preform. Once the first 1 and second 4 fibrous preforms obtained 15, they are then assembled by engagement of the second portion 3 of the first preform 1 in the inner housing 6 of the first portion 5 of the second preform 4, the sense of The assembly being illustrated by an arrow in FIG. 1. As will be detailed below, the first fiber preform 1 may or may not be in the consolidated state during assembly. In the illustrated example, once the first 1 and second 4 preforms assembled, the second preform 4 does not extend along the first portion 2 of the first preform 1 forming a blade root preform. In other words, in the illustrated example, once the first 1 and second 4 assembled preforms, the first part 2 of the first preform 1 forming a blade root preform is not housed in the inner housing 6 of the second preform 4. The structure obtained after assembly illustrated in FIG. 2 differs from that illustrated in FIG. 1 insofar as the second part 17 of the second platform preform preform 14 is made by weaving two sets of layers of son 17a and 17b each respectively passing through one of the skins 15a or 15b of the first portion 15 of the second preform 14 forming blade preform. As in the example of FIG. 1, once the first 1 and second 14 preforms have been assembled, the second preform 14 does not extend along the first part 2 of the first preform 1 forming a dawn foot preform .
    [0008] FIG. 3 shows a detail of the structure shown in FIG. 2. In order to produce the platform preform, debinding is performed at the point of debonding point D in order to allow the separation of a set of layers of yarn 17b forming part of the platform of a set of layers of yarn forming one of the skins 15b of the first portion 15 of the second preform 14. The set of yarn layers 17b and the set of layers of yarns forming one of the skins 15b are not interconnected at the level of the debonding zone. As illustrated in FIG. 3, the set of layers of threads 17b passes through the skin 15b at a crossing zone T. A sectional view at the crossing zone T is given in FIG. The same characteristics apply to the set of layers of threads 17a forming part of the platform and to the set of layers of threads forming the skin 15a.
    [0009] FIG. 5 shows an alternative embodiment which differs from the example illustrated in FIG. 2 only in that, once the first 1 and second 14 'preforms have been assembled, the second preform 14' extends along the entirety of the first portion 2 of the first preform 1 forming preform of blade root. In this case, the first portion 2 of the first preform 1 is fully housed in the inner housing of the second preform 14 '. The numbering of the elements of the second preform 14 'of FIG. 5 corresponds to that of FIG. 2 to which a "'" has been added. The details given in FIGS. 3 and 4 are valid for the embodiment of FIG. 5.
    [0010] Whatever the embodiment envisaged, it is possible to form in the context of a method according to the invention a plurality of platforms and possibly walls and spoilers. In particular, it is possible to obtain, after use of a method according to the invention, a turbomachine blade having a first platform located on the side of the blade root and a second platform forming a blade root. Examples of processes according to the invention will now be described. The description below relates to the exemplary method according to the invention illustrated in FIG.
    [0011] In a first step, the first and second fibrous preforms are each made by multilayer weaving between a plurality of warp layers and a plurality of weft layers, optionally followed by a shaping step ( step 10). It is not beyond the scope of the invention when the first fiber preform is obtained after a multilayer weave between a plurality of warp layers and a plurality of weft yarn layers and the second fiber preform is obtained after the production. a braiding. The multilayer weave produced may be in particular an "interlock" weave weave, that is to say a weave weave in which each layer of weft threads binds several layers of warp threads with all the threads of the same thread. weft column having the same movement in the plane of the armor. Other types of multilayer weaving may be used. Various multilayer weave modes that can be used are described in particular in document WO 2006/136755.
    [0012] The weaving can be carried out with warp yarns extending in the longitudinal direction of the preforms, being noted that weaving with weft yarns in this direction is also possible. In an exemplary embodiment, the first and second fibrous preforms may each comprise, in particular, be formed of carbon son. Alternatively, the first fiber preform may comprise, in particular, be formed of carbon son and the second fiber preform may comprise, in particular be formed of ceramic son such as silicon carbide son. In another variant, the first and second fibrous preforms may each comprise, in particular be formed of ceramic son such as silicon carbide son. Thus, in an exemplary embodiment, the son used may be silicon carbide (SiC) son provided under the name "Nicalon", "Hi-Nicalon" or "Hi-Nicalon-S" by the Japanese company 30 Nippon Carbon or "Tyranno SA3" by the company UBE and having for example a title (number of filaments) of 0.5K (500 filaments). The first fibrous preform is then consolidated by deposition of a consolidation phase in the porosity of the first fibrous preform, this consolidation phase being deposited by gaseous or liquid way in a manner known per se (step 20).
    [0013] The liquid process consists in impregnating the preform with a liquid composition containing a precursor of the material of the consolidation phase. The precursor is usually in the form of a polymer, such as a resin, optionally diluted in a solvent. The preform is placed in a mold that can be sealed. Then, the mold is closed and the liquid phase precursor consolidation (eg a resin) is injected into the mold to impregnate the preform. The conversion of the precursor into the consolidation phase is carried out by heat treatment, generally by heating the mold, after removal of the optional solvent and crosslinking of the polymer. In the case of the formation of a consolidation phase made of ceramic material, the heat treatment comprises a step of pyrolysis of the precursor to form the ceramic material consolidation phase. By way of example, liquid precursors of ceramics, in particular of SiC, may be polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type resins. Several consecutive cycles, from the impregnation to the heat treatment, can be carried out to achieve the desired consolidation.
    [0014] In the gaseous process (chemical vapor infiltration of the consolidation phase, "CVI" process), the fibrous preform is placed in an oven in which a reaction gas phase is admitted. The pressure and the temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform to form the consolidation phase by deposition, at the heart of the material in contact with the fibers, of a solid material resulting from a decomposition of a constituent of the gas phase or a reaction between several constituents.
    [0015] The formation of an SiC consolidation phase can be achieved with methyltrichlorosilane (MTS) giving SiC by decomposition of MTS. Once the first fibrous preform has been consolidated, it may possibly be shaped, for example by machining (optional step).
    [0016] The first fibrous preform in the consolidated state is then assembled with the second fibrous preform in the unconsolidated state by engagement of the second portion of the first preform into the inner housing of the first portion of the second preform (step 5). 40). Once the first and second preforms have been assembled, it is possible to carry out a forming step, for example by deformation molding, in particular in order to reproduce the curved profile of the blade of the blade, the first preform constituting in this case a counter-molding. mold for the second preform.
    [0017] Co-densification of the first and second preforms thus assembled is then performed. In an exemplary embodiment, the co-densification can be carried out by a melt infiltration process (step 50). In this process, firstly, there is introduced, in the porosity of the first and second assembled preforms, fillers, for example reactive fillers, the fillers being chosen for example from SiC, Si3N4, C, B, and mixtures thereof. . The introduction of fillers may, for example, be carried out by slurry casting, by sub-micron powders suction (APS) or by an injection molding process of the resin injection molding method ( "Resin Transfer Molding" or "RTM") in which a heat treatment is performed after the injection to evaporate the liquid medium. Once the charges are introduced, the first and second preforms are then infiltrated with a melt infiltration composition comprising, for example, silicon in order to form a matrix and thus obtain the turbomachine blade. The infiltration composition may consist of molten silicon or alternatively may be in the form of a molten silicon alloy and one or more other components. The constituent (s) present within the silicon alloy may be selected from B, Al, Mo, Ti, and mixtures thereof. When reactive charges are used, substantially all of the reactive charges may be consumed during the reaction between the infiltration composition and the reactive charges. Alternatively, only a portion of the reactive charges are consumed during this reaction.
    [0018] In one exemplary embodiment, the melt infiltration carried out can make it possible to obtain a matrix by reaction between solid charges, for example of C, SiC or Si 3 N 4 introduced by slip or prepregs. , and a molten alloy based on silicon. The reaction can occur at a temperature greater than or equal to 1420 ° C. Given the high temperatures used, it can be advantageous for at least a portion of the first and second preforms to be made of thermostable fibers, for example of the Hi-Nicalon or even Hi-Nicalon S type.
    [0019] The yarns of the first and second preforms may, before infiltration of the infiltration composition, have been coated with an interphase layer, for example silicon-doped BN or BN, as well as with a carbide layer. for example SiC and / or Si3N4, for example made by gas.
    [0020] Alternatively, it is first possible to perform a first co-densification step of the first and second preforms assembled by liquid densification (step 51), this type of process being as described above with respect to the step of consolidation of the first fibrous preform. Step 51 can then be followed by a second co-densification step by chemical vapor infiltration (step 51a) (this type of process being as described above with respect to the consolidation step of the first preform fibrous) or by infiltration in the molten state (step 51b). The second co-densification step is carried out in order to fill all or part of the residual porosity resulting after implementation of the first co-densification step. Co-densification combining the liquid route and gaseous route can advantageously facilitate the implementation, limit costs and production cycles while obtaining satisfactory characteristics for the intended use.
    [0021] As a further variant, it is first possible to perform a first co-densification step of the first and second preforms assembled by chemical vapor infiltration (step 52). Step 52 may be followed by a shaping step, for example by machining (step 53 optional). A second co-densification step may then be performed by a melt infiltration process (step 54).
    [0022] It will now be described an alternative method according to the invention in connection with Figure 7. In a first step, a step 10 as described above is carried out. The first fibrous preform in the unconsolidated state is then assembled with the second fibrous preform in the unconsolidated state by engagement of the second portion of the first preform in the inner housing of the first portion of the second preform (step 41 ). Once the first and second preforms have been assembled, it is possible to carry out a shaping step, for example by deformation molding, in particular in order to reproduce the curved profile of the blade of the blade. It is then possible to carry out a step of reinforcing the assembly by introducing or forming mechanical bonds between the first and second preforms at their assembled portions (optional step 60). This reinforcing step of the assembly may, for example, be performed by needling if the son constituting the first and second preforms are carbon son. As a variant, the step of reinforcing the assembly can be carried out by a Z pinning technique ("Zpinning") whatever the type of wire constituting the first and second preforms.
    [0023] Co-densification is then carried out in the same manner as that described with reference to FIG. 6. Whatever the example of the method of manufacturing the chosen turbomachine blade, there may be after co-densification an additional forming step for example by making cuts and / or a step of performing finishing treatments such as depositing at least one coating on the surface of the blade formed. FIG. 8 shows the structure of a turbomachine blade 100 that can be obtained by implementing the method according to the invention. The blade 100 of FIG. 8 comprises, in a well-known manner, a blade 101, a foot 102 formed by a portion of greater thickness, for example with a bulbous section, extended by a stilt 103, a platform inner 110 located between the stilt 103 and the blade 101 and an outer platform or heel 120 adjacent the free end of the blade. The foot 102 may be made of a thermostructural material of ceramic or carbon / carbon matrix composite type. It may be advantageous for the fibrous reinforcement of the root of the blade 100 to be formed of carbon threads, which are lighter than the silicon carbide threads, thus making it possible to lighten the overall mass of the FIG. 9 shows a turbomachine wheel 200 comprising a hub 130 on which are mounted a plurality of blades 100 produced by a method according to the invention, each blade 100 including a foot 102 formed by a further portion. large thickness, for example with a bulbous section, which is engaged in a corresponding housing 131 formed at the periphery of the hub 130 and a blade 101.
    [0024] The wheel 200 further comprises a plurality of blade heel elements 120 present on each of the blades 100. Blades manufactured by a method according to the invention can be attached to turbines of low or high pressure turbojets. The blades made by a method according to the invention can also equip gas turbines. The expression "understood between ... and ..." or "from ... to" must be understood as including boundaries.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of manufacturing a turbomachine blade (100) of composite material comprising a matrix-densified fiber reinforcement, the method comprising: - producing a multilayer weave to obtain a first fibrous preform (1) in a single piece, said first preform (1) comprising a first portion (2) forming a blade root preform and extended by a second portion (3) having a thickness less than the thickness of the first portion (2), said second part (3) forming a preform of tenon, - the realization of a multilayer weave to obtain a second fibrous preform (4; 14; 14 ') in one piece, said second preform (4; 14; 14') comprising a first portion (5; 15; 15 ') formed of two skins (5a; 5b; 15a; 15b; 15'a; 15'b) delimiting between them an inner housing (6), said first portion (5; 15; ') forming blade preform, and at least a second portion (7; 17; 17') s extending from the outer surface of said skins (5a; 5b; 15a; 15b; 15'a; 15'b), said at least second part (7; 17; 17 ') forming a platform preform; - assembling the first preform (1) in the consolidated or unconsolidated state with the second preform (4; 14 ') in the unconsolidated state by engagement of the second part (3) of the first preform (1) in the inner housing (6) of the first part (5; 15; 15') of the second preform ( 4; 14; 14 '), and - the co-densification of the first (1) and second (4; 14; 14') preforms thus assembled to obtain a turbomachine blade (100).
    [0002]
    2. Method according to claim 1, characterized in that the first preform is consolidated before the assembly step and in that the first preform in the consolidated state is assembled with the second preform (4; 14; 14 '). in the unconsolidated state during the assembly step. 3032648 15
    [0003]
    3. Method according to claim 1, characterized in that the first preform in the unconsolidated state is assembled with the second preform (4; 14; 14 ') in the unconsolidated state during the assembly step. 5
    [0004]
    4. Method according to any one of claims 1 to 3, characterized in that said at least second portion (17; 17 ') of the second preform (14; 14') forming platform preform is made by weaving two sets layers of yarns (17a; 17b; 17'a; 17'b) each passing through one of the skins (15a; 15b; 15'a; 15'b) of the first portion (15; 15 ') of the second portion; preform (14; 14 ') forming a blade preform.
    [0005]
    5. Method according to any one of claims 1 to 3, characterized in that said at least second portion (7) of the second preform (4) forming platform preform is made by weaving excess lengths (7a, 7b) in the lower part of the first part (5) of said second preform (4) forming blade preform.
    [0006]
    6. Method according to any one of claims 1 to 5, characterized in that it comprises, after the step of co-densification of the first (1) and second (4; 14; 14 ') preforms, a step machining the blade preform (5; 15; 15 ') so as to reduce the thickness of the skins (5a; 5b; 15a; 15b; 15'a; 15'b). 25
    [0007]
    7. Method according to any one of claims 1 to 6, characterized in that the first preform is obtained after multilayer weaving of a plurality of carbon fiber son and in that the second preform is obtained after multilayer weaving of a plurality of silicon carbide wires. 30
    [0008]
    8. Method according to claim 7, characterized in that the first preform is consolidated by a carbon-based consolidation phase before the assembly step and in that the first preform thus consolidated is assembled with the second preform to the unconsolidated state during the assembly step. 3032648 16
    [0009]
    9. Process according to any one of claims 1 to 8, characterized in that the co-densification of the first (1) and second (4; 14; 14 ') preforms is carried out using at least one following methods: chemical vapor infiltration, liquid densification and melt infiltration method.
    [0010]
    10. Process according to any one of claims 1 to 9, characterized in that it comprises, after the step of assembling the first and second fibrous preforms and before co-densification, a step 10 of reinforcing the assembly comprising introducing or forming mechanical connections between the first and second preforms at their assembled portions.
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP3259123B1|2018-12-12|
    CA2976858A1|2016-08-25|
    WO2016132042A1|2016-08-25|
    CN107428103A|2017-12-01|
    US20180036914A1|2018-02-08|
    BR112017017389A2|2018-04-03|
    RU2689618C2|2019-05-28|
    RU2017132208A|2019-03-18|
    CN107428103B|2019-10-11|
    EP3259123A1|2017-12-27|
    US10046482B2|2018-08-14|
    RU2017132208A3|2019-03-27|
    FR3032648B1|2017-03-03|
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    法律状态:
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    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20170717 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1551258A|FR3032648B1|2015-02-16|2015-02-16|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE OF COMPOSITE MATERIAL|FR1551258A| FR3032648B1|2015-02-16|2015-02-16|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE OF COMPOSITE MATERIAL|
    BR112017017389-1A| BR112017017389B1|2015-02-16|2016-02-09|METHOD FOR MANUFACTURING A TURBO MACHINE BLADE|
    RU2017132208A| RU2689618C2|2015-02-16|2016-02-09|Method of making gas turbine engine blade from composite material|
    PCT/FR2016/050281| WO2016132042A1|2015-02-16|2016-02-09|Method for manufacturing a turbomachine blade made of composite material|
    CA2976858A| CA2976858A1|2015-02-16|2016-02-09|Method for manufacturing a turbomachine blade made of composite material|
    EP16707885.6A| EP3259123B1|2015-02-16|2016-02-09|Method for manufacturing a turbomachine blade made of composite material|
    CN201680010502.XA| CN107428103B|2015-02-16|2016-02-09|Method for manufacturing the turbine blade made of composite material|
    US15/551,424| US10046482B2|2015-02-16|2016-02-09|Method for manufacturing a turbomachine blade made of composite material|
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