• 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 composite material part comprising a fiber reinforcement densified by a ceramic matrix, the part having an external surface and being coated on at least a part of its outer surface by a surface coating under solid form comprising an alloy, the process comprising the following steps: a) forming the ceramic matrix of the composite material part by infiltration of the fibrous preform with a melt infiltration composition, the infiltration composition comprising silicon and having a first melting temperature, the infiltration composition being contacted with all or part of a first set of fillers present in the fiber preform, and b) forming the surface coating of the composite material part. infiltrating a second set of fillers and / or a preceramic resin with a coating composition melt the coating composition having a second melting temperature lower than the first melting temperature and a composition different from that of the ceramic matrix.
    公开号:FR3023212A1
    申请号:FR1456392
    申请日:2014-07-03
    公开日:2016-01-08
    发明作者:Emilie Courcot；Eric Philippe；Eric Bouillon；Sebastien Jimenez
    申请人:Herakles SA；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to methods for manufacturing ceramic matrix composite (CMC) parts having a surface coating. Composite materials CMC are able to constitute parts intended to be exposed in service at high temperatures and have the advantage of maintaining good mechanical properties at high temperatures. It is known to treat the surface of CMC materials according to the applications envisaged for the latter. For example, the following coatings can be produced on the surface of the CMC: - smoothing coating for the turbine blade pale area in order to improve the aerodynamic character, - environmental barrier for protecting the silicon carbide (SiC) the phenomenon of wet corrosion at high temperature, or - coating to limit the phenomena of wear and fretting at the interfaces. Currently, the functional coatings are made on the composite material in its final stage of elaboration. There is therefore a total decoupling between the manufacture of the CMC and the formation of its coating. Oxide coatings used to improve corrosion resistance and smooth the surface can be developed by plasma spraying or flash sintering. Carbide type coatings can, for their part, be made by powder coating technologies (paint, dipping dip-coating, injection or overmoulding, for example) followed by consolidation by gas. Current processes for producing coated CMC parts have two main disadvantages. On the one hand, these methods can comprise a large number of steps and can therefore be relatively complex and expensive. On the other hand, the attachment to the composite material of the coating obtained may not be entirely satisfactory because of the decoupling existing between the manufacture of the CMC and the formation of its coating. In addition, another problem is to be considered for CMC parts which concerns the chemical interactions that these parts can undergo with the support on which they are mounted during their use. Such interactions can be problematic in that they can lead to damage to CMC parts and / or metal parts. There is therefore a need for simpler and less expensive methods of preparing CMC parts coated with a coating. There is also a need for new CMC parts with limited interactions with the medium on which they are intended to be mounted during use.
    [0002] There is still a need for new CMC parts with increased resistance to fretting. OBJECT AND SUMMARY OF THE INVENTION For this purpose, the invention proposes a process for manufacturing a composite material part comprising a fiber reinforcement densified by a ceramic matrix, the part having an external surface and being coated on at least one part of its outer surface by a surface coating in solid form comprising an alloy, the method comprising the following steps: a) forming the ceramic matrix of the composite material part by infiltration of the fibrous preform with an infiltration composition to the molten state, the infiltration composition comprising silicon and having a first melting temperature, the infiltration composition being brought into contact with all or part of a first set of fillers present in the fibrous preform, and b) formation of the surface coating of the composite material part by infiltration of a second set of charges and / or a precured resin ceramics with a coating composition in the molten state, the coating composition having a second melting temperature lower than the first melting temperature and a composition different from that of the ceramic matrix. The process according to the invention therefore involves two steps of melt infiltration ("meit-infiltration"), the first to form the ceramic matrix and the second to form the surface coating at the same time. using a coating composition comprising an alloy. The fact of using both for obtaining the ceramic matrix and the surface coating the same type of process advantageously contributes to simplify the preparation of the coated part. The fact of using a melting temperature coating composition lower than the melting temperature of the infiltration composition advantageously makes it possible, if step b) is initiated after step a), not to melt, at again, the infiltration composition possibly still present in the composite material part. "Surface coating" means a coating whose majority of the mass is present on the outer surface of the part. In other words, at least 50%, preferably at least 60%, preferably at least 70%, preferably at least 80%, preferably at least 90%, preferably at least 95%, preferably at least 100%. %, the mass of the surface coating is present on the outer surface of the part (thus outside the room). It is possible that the surface coating penetrates slightly into the room, for example to ensure its attachment to the latter. However, the surface coating preferably does not penetrate the room. The surface coating is attached to the outer surface of the workpiece and can penetrate the pores of the outer surface of the workpiece.
    [0003] On the other hand, the surface coating does not densify, preferably, the fibrous reinforcement. The surface coating can take the shape of the part it covers. Thus, the surface of the surface coating on the opposite side of the workpiece may have the same shape as the outer surface of the workpiece. The second melting point may advantageously be less than or equal to 1400 ° C. The alloy present in the surface coating may, for example, be in contact with the ceramic matrix. In an exemplary embodiment, the infiltration composition may, during step a), be brought into contact with reactive fillers present in the fibrous preform, a chemical reaction that may take place between the infiltration composition and the reactive charges during step a). These reactive fillers may, for example, be selected from: C, B4C, SiB6, and mixtures thereof. In an exemplary embodiment, the alloy of the surface coating may be a silicon alloy. In this case, the coating composition comprises a silicon alloy. In an exemplary embodiment, the alloy of the surface coating may be an alloy of silicon and nickel or an alloy of silicon and cobalt. In this case, the coating composition comprises an alloy of silicon and nickel or an alloy of silicon and cobalt. The use of this type of alloys within the coating advantageously makes it possible to limit the interactions, in particular the chemical reactions, between the part, on the one hand, and the constituent material of the support on which the piece is intended to be mounted during use, on the other hand. Thus, the inventors have found that the presence, within the surface coating, of these particular alloys advantageously makes it possible to limit the interactions between the part and the support. Thus, the part manufactured by the process according to the invention advantageously has limited interactions with the nickel-based and / or cobalt-based superalloy of the fixing support, thanks to the saturation of silicon by nickel or cobalt present within coating. In an exemplary embodiment, the surface coating may comprise a NiSi 2 phase and / or a NiSi phase. In particular, the surface coating may comprise: a NiSi.sub.2 phase and optionally an Si phase, and / or a NiSi phase and optionally a Si.sub.2 phase. In an exemplary embodiment, the surface coating may comprise a CoSi 2 phase and optionally an Si phase. When a silicon and nickel alloy is used, the mass content of silicon in the alloy may be between 29% and 45%. %, preferably between 40% and 45%. When using an alloy of silicon and cobalt, the mass content of silicon in the alloy may be between 34% and 90%, for example between 40% and 90%, for example between 42% and 70%. %, for example between 45% and 60%. In an exemplary embodiment, the alloy of the surface coating may be present in a mass content greater than or equal to 5%, preferably greater than or equal to 50%, relative to the weight of the surface coating. The thickness of the surface coating may, over all or part of the external surface of the coated part, be between 20 μm and 1000 μm, preferably between 50 μm and 300 μm. In particular, when the part constitutes an aeronautical engine blade, the thickness of the surface coating may, for example, be less than or equal to 300 μm in the blade root area and / or be less than or equal to 100 μm. pm in the area of the blade. The thickness of the surface coating may vary as one moves along the outer surface of the workpiece. Such a variation of the thickness advantageously makes it possible to have a part whose coating has different functions depending on the zone considered. Alternatively, the thickness of the surface coating may be substantially constant as one moves along the outer surface of the workpiece. The surface coating may further comprise fillers and / or ceramic material. The charges present within the surface coating may be chosen from: SiC, Si3N4 or BN, and mixtures thereof. The ceramic material present in the surface coating may be chosen from ceramic materials derived from the pyrolysis of preceramic resins, the preceramic resins being for example chosen from: polycarbosilanes, polysilazanes, polyborosilanes, and mixtures thereof. The surface coating may, in an exemplary embodiment, have substantially the same composition when moving along the outer surface of the workpiece. Alternatively, the composition of the surface coating varies as one moves along the outer surface of the workpiece. Such a variation of the composition advantageously allows to have a room whose coating has different functions depending on the area. In an exemplary embodiment, the surface coating may be present on a first and a second region of the outer surface of the part and the composition and / or the thickness of the surface coating may differ between the first region and the second region. .
    [0004] As explained above, such a feature advantageously allows to have a room whose coating has different functions depending on the area. The fibers of the fibrous reinforcement are advantageously coated with an interphase layer.
    [0005] The use of an interphase is advantageous insofar as it makes it possible to increase the mechanical strength of the fibers constituting the fibrous reinforcement by allowing in particular a deflection of the possible cracks of the matrix so that these do not affect the integrity fibers.
    [0006] The interphase layer may comprise, in particular, pyrocarbon (PyC), boron doped pyrocarbon or BN. The interphase layer may be multi-sequenced or not, for example comprising a repetition of [PyC / Carbide], [BC / Carbide] or [BN / Carbide] sequences.
    [0007] The fibers of the fibrous reinforcement are advantageously coated with a barrier layer, which is, for example, in the form of a self-healing carbide matrix. The use of such a barrier layer advantageously makes it possible to protect the fibers against oxidation and to generate a cracking network remote from the fibrous reinforcement. In an exemplary embodiment, step b) can be initiated after completion of step a). In an exemplary embodiment, step b) may further include applying the melt coating composition to a deposit of the second set of fillers and / or preceramic resin present on the surface. outer part of the composite material. In an exemplary embodiment, the second set of charges and / or the preceramic resin have been deposited, after step a), on the outer surface of the composite material part. The charges of the second set of charges may or may not be reactive. The nonreactive charges of the second set of charges may, for example, be selected from: SiC, Si3N4 or BN, and mixtures thereof. The reactive charges of the second set of charges may, for example, be selected from: C, B4C, SiB6, and mixtures thereof. The melt coating composition can react chemically with the reactive fillers upon contacting therewith. Alternatively, the coating composition may, once solidified, participate in bonding the charges present on the outer surface of the composite material part. The charge deposition of the second set of charges and / or the pre-ceramic resin may advantageously be of variable thickness and / or of variable composition as one moves along the outer surface of the part, for example according to the different functional areas of the room. Such a deposit advantageously makes it possible to obtain a coating having different functions depending on the position on the outer surface of the part. In an exemplary embodiment, the melt coating composition may be present on the fibrous preform prior to infiltration of the fibrous preform by the melt infiltration composition. In this case, a heat treatment of the fibrous preform can be carried out, the heat treatment comprising subjecting the fibrous preform to: a first temperature which makes it possible to obtain, on the external surface of the preform, 302 3 2 1 2 8 the molten coating composition layer, then at a second temperature, higher than the first temperature, during the infiltration of the fibrous preform with the melt infiltration composition, and then cooling the assembly obtained after infiltration of the fiber preform. The first temperature may, for example, be maintained for a period greater than or equal to 15 minutes, for example for a period of between 15 minutes and 60 minutes. The second temperature may, for example, be maintained for a period greater than or equal to 15 minutes, for example for a period of between 15 minutes and 60 minutes. The heat treatment may, for example, comprise the production of a first temperature plateau at the first temperature, then an increase in temperature monotonously, or even strictly monotonically, up to the second temperature, and then the production of a temperature. second temperature level at the second temperature. In an exemplary embodiment, the outer surface of the fiber preform may have been coated, prior to being submitted to the first temperature, by the solid state coating composition. In this case, the first-temperature submission melts the solid-state coating composition deposited on the outer surface of the fiber preform. More specifically, a precursor surface coating layer may, prior to being submitted to the first temperature, have been deposited on the outer surface of the fibrous preform, the precursor surface coating layer comprising, on the one hand, the coating composition. in the solid state and, secondly, the second set of charges and / or the preceramic resin. The second set of fillers and / or preceramic resin present in the surface coating precursor layer may be as described above. As explained above, the melt coating composition can react chemically with fillers or, alternatively, the coating composition can, once solidified, participate in bonding the fillers. In an exemplary embodiment, before the fibrous preform is submitted to the first temperature, the second set of fillers can be applied to the outer surface of the fibrous preform by slip casting ("slurry cast"), these fillers being chosen, for example, from SiC, Si3N4, C, B, and mixtures thereof, these fillers being intended to be contacted with the melt coating composition.
    [0008] The presence of these charges on the outer surface advantageously makes it possible to fill the porosity of the preform in order to limit or even to prevent penetration into the preform of the melt coating composition. In an exemplary embodiment, the manufactured part may constitute an aeronautical engine blade having at least one blade root and a blade and the surface coating may cover at least the blade root. BRIEF DESCRIPTION OF THE DRAWINGS Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, in which: FIG. 1 represents a schematic and partial section of a part obtained by a method according to the invention; FIG. 2 is a flow diagram of an exemplary method for preparing a part according to the invention; FIG. FIG. 4 is a flowchart of a variant of a method for preparing a part according to the invention, FIG. 5 is a diagram of an example of a method for preparing a part according to the invention, FIG. perspective view of a turbomachine blade manufactured by a method according to the invention, and - Figure 6 is a perspective view of a turbomachine wheel having blades manufactured by the methods according to the invention.
    [0009] DETAILED DESCRIPTION OF EMBODIMENTS FIG. 1 shows a section of a composite material part 1 comprising a fibrous reinforcement (not shown) densified by a ceramic matrix 2. The component 1 has on its outer surface 3 a Surface coating in solid form 4. The surface coating 4 may further comprise fillers and / or ceramic material. As illustrated, the surface coating 4 does not penetrate within the matrix 2. The surface coating 4 remains, in fact, in the example shown entirely on the outer surface 3 of the piece 1. We do not leave the frame of the invention if the surface coating penetrates within the matrix as the majority of the mass of the latter remains on the outer surface of the part (and therefore outside thereof).
    [0010] The thickness e of the surface coating 4 may, as illustrated, be substantially constant as one moves along the outer surface 3 of the part. In a variant not shown, the thickness e of the surface coating varies as one moves along the outer surface of the part.
    [0011] The surface coating 4 can, as illustrated, take the shape of the piece 1. In the example illustrated, the surface S of the surface coating located on the side opposite the piece 1 has the same shape as the external surface 3 of the piece 1 We will now describe in more detail some elements relating to the manufacture of composite materials comprising a fiber reinforcement densified by a ceramic matrix used in the context of the present invention. The fibrous preform intended to form the fibrous reinforcement of the part according to the invention can be obtained by multilayer weaving between a plurality of warp layers and a plurality of weft layers. The multilayer weave produced can be in particular an "interlock" weave, that is to say a weave weave in which each layer of weft son binds several layers of warp son with all the son of the same column weft with the same movement in the plane of the armor. 302 3 2 1 2 11 Other types of multilayer weaving may of course be used. When the fiber preform is woven, the weaving can be performed with warp yarns extending in the longitudinal direction of the preform, being noted that weaving with weft yarns in this direction is also possible. 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 Nippon Carbon 10 or " Tyranno SA3 "by the company UBE and having a title (number of filaments) of 0.5K (500 filaments). Various multilayer weaving modes are described in particular in document WO 2006/136755. The fibrous reinforcement of the piece according to the invention can also be formed from a fibrous preform obtained by assembling two fibrous textures. In this case, the two fibrous textures can be bonded together, for example by sewing or needling. The two fibrous textures may in particular be each obtained from a layer or a stack of several layers of: one-dimensional fabric (UD), two-dimensional fabric (2D), braid, knit, felt, tablecloth unidirectional (UD) son or cables or multidirectional plies (nD) obtained by superposition of several UD plies in different directions and UD plies binding between them for example by sewing, by chemical bonding agent or by needling. In the case of a stack of several layers, these are bonded together, for example by sewing, by implantation of threads or rigid elements or by needling. As described above, a fibrous preform intended to form the fibrous reinforcement of a part according to the invention can be obtained by multilayer weaving, or by stacking fibrous structures. For turbomachine blades intended for use at high temperature and in particular in a corrosive environment (especially moisture), it is advantageously used for weaving son formed of ceramic fibers, especially silicon carbide (SiC) fibers. For parts with shorter durations of use, carbon fibers can also be used.
    [0012] The part may comprise a reinforcement made of carbon fibers and / or ceramic densified by a ceramic matrix, for example chosen from SiC / Si, Si3N4 / SiC / Si, SiB or SiMo matrices. With reference to FIGS. 2 to 4, processes of preparation according to the invention will now be described.
    [0013] FIG. 2 is a flow chart showing the steps of a first exemplary embodiment of a method according to the invention. A fibrous preform having fillers, for example selected from SiC, Si3N4, C, B and mixtures thereof, is first infiltrated by a melt infiltration composition comprising silicon (step 10). After contact between the infiltration composition and the charges, a piece of composite material comprising a ceramic matrix is obtained. When there is reaction between the infiltration composition and reactive charges present in the fibrous preform, substantially all the reactive charges can be consumed. Alternatively, only a portion of the reactive charges are consumed during this reaction. 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 (s) within the silicon alloy may be selected from B, Al, Mo, Ti, and mixtures thereof. The fibers of the fibrous reinforcement 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 made of SiC and / or Si3N4, for example made by gaseous means. The matrix may be obtained by reaction between solid fillers, for example of C, SiC, introduced by slip or prepreg, and a molten alloy based on silicon. The reaction can occur at a temperature greater than or equal to 1420 ° C. In view of the high temperatures used, it may be advantageous for the fiber reinforcement to consist of thermostable fibers, for example of the Hi-Nicalon or even Hi-Nicalon S type. Once the ceramic matrix has been obtained, depositing charges and / or preceramic resin on the outer surface of the workpiece (step 20). The subsequent step 30 is to apply to the outer surface of the CMC part a melt coating composition, which coating composition has a melt temperature below the melt temperature of the melt composition. infiltration having made it possible to form the ceramic matrix of densification of the fibrous reinforcement. The melt coating composition infiltrates, during step 30, within the charges and / or preceramic resin deposited on the outer surface of the workpiece.
    [0014] Thus, two successive steps of melt-infiltration are performed, the first to make the ceramic matrix (step 10) and then the second to achieve the surface coating (step 30). FIG. 3 shows a more detailed flow chart of a manufacturing method according to the invention according to the exemplary embodiment shown in FIG. 2. This process may comprise the following steps: - preparation of a fibrous preform, for example based on Hi-Nicalon S fibers (step 5), for example by liquid and / or gaseous weaving and preforming, the fibers of the fiber preform being coated with an interphase layer (step 6), for example PyC or BN, and a coating for (i) avoiding a reaction between the infiltration composition, on the one hand, and fibers and interphase on the other hand and (ii) to consolidate the fiber preform (step 7), the coating being for example made of carbide, for example SiC, B4C and / or SiBC, and which may comprise a self-healing matrix, the coating being deposited by CVI, machining of the preform fibrous (step 8, this step is optional in the example of realization considered), - introduction into the fiber preform of a first set of charges, for example of reactive charges, slip way ("Slurry cast") (step 9), the charges being for example 302 3 2 1 2 14 selected from SiC, Si3N4, C, B, and mixtures thereof, and the excess of surface charges being optionally totally or partially eliminated after the "slurry cast", - infiltration of the fibrous preform with the melt infiltration composition (step 10; melt infiltration process) to form the ceramic matrix, this infiltration possibly being preceded by a step of deoxidation of the fibrous preform and the infiltration composition, the infiltration making it possible for example to form predominantly carbide of silicon with a minimum of residual silicon, - cleaning of the composite for example by simple operation of sanding or peeling (this step is optional in the embodiment considered), - deposition on the outer surface of the composite material part 15 a second set of charges (step 20), for example chosen from: SiC, Si3N4, C, Mo2C, 134C and mixtures thereof, and / or a preceramic resin, for example PCS, PSZ or a resin phenol, the deposit being for example carried out by soaking ("dipcoating"), overmoulding or RTM, the deposit being made which may be of variable thickness and / or of variable composition when moving ace along the outer surface of the part, for example according to the different functional areas of the part, in the example illustrated in FIG. 3, a deposition of SiC charges has been achieved, - infiltration of the external surface of the piece by a melt coating composition having a melting point lower than that of the infiltration composition (step 30), this infiltration possibly being preceded by a step of deoxidizing the piece and the composition of the composition. coating, - finishing machining (step 31; this step is optional in the embodiment considered). A flow chart showing the steps of a variant of a manufacturing method according to the invention will now be described with reference to FIG. The solid state coating composition present on the outer surface of a fibrous preform is first melted by subjecting it to a first temperature (step 40). The melt coating composition then infiltrates charges and / or preceramic resin present on the outer surface of the fibrous preform (step 50). Subsequently, after melting the coating composition, the fibrous preform is infiltrated with a melt infiltration composition comprising silicon by subjecting the preform to a second temperature above the first temperature (step 60). The whole obtained after step 60 is then cooled (step 70). As in the process embodiment described above, the fiber preform comprises fillers, for example chosen from SiC, Si3N4, C, B and their mixtures, at the time of infiltration by the infiltration composition. When reactive fillers are present in the fiber preform, all of the reactive charges can be consumed during step a). As a variant, only a part of the reactive charges is consumed during step a). The infiltration composition used in this embodiment to densify the fiber reinforcement may be as described above. The following is a more detailed example of a method for preparing a part according to the invention according to the variant shown in FIG. 4. The method may comprise the following steps: preparation of a fibrous preform, for example based on Hi-Nicalon S fibers, for example by weaving and preforming by liquid and / or gaseous means, the fibers of the fibrous preform being coated with an interphase layer, for example PyC or BN, and a coating (i) to avoid a reaction between the infiltration composition, on the one hand, and the fibers and the interphase on the other hand and (ii) to consolidate the fiber preform, the coating being for example carbide , for example SiC, B4C and / or SiBC, and may comprise a self-healing matrix, the coating may be deposited by CVI, - introduction, within the fibrous preform, of first charges, for example reactive charges, by slipway ("Slurry cast"), fillers being chosen, for example, from SiC, Si3N4, C, B, and mixtures thereof, and the excess of surface charges being optionally totally or partially eliminated after slurry casting, 302 3 2 1 2 16 - deposit on the outer surface of the fibrous preform, second fillers, for example selected from SIC, C, Si3N4, Mo2C, B4C and mixtures thereof, and / or a preceramic resin, for example PCS, PSZ or a phenol resin, and solid state coating composition, the deposition being for example carried out by soaking ("dip-coating"), overmolding or RTM, the deposition carried out being of variable thickness and / or of composition variable when moving along the outer surface of the fibrous preform, for example according to the different functional areas of the part to be obtained, 10 - melt infiltration heat treatment ("melt-infiltration") involving the submission of the preform at a first temperature for melting the solid-state coating composition present on the outer surface of the fibrous preform and that it infiltrates the second fillers and / or the preceramic resin, and then - second temperature, higher than the first temperature, during the infiltration of the fibrous preform with the melt infiltration composition to obtain a densification by a ceramic matrix of the fibrous preform, this infiltration possibly being preceded by a step of deoxidation of the fibrous preform and the infiltration composition, followed by cooling of the assembly obtained. The invention is applicable to various types of turbomachine blades, in particular compressor and turbine blades of different gas turbine bodies, for example a low-pressure turbine wheel vane, such as that illustrated in FIG. 5. The blade 100 of FIG. 5 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, an inner platform 110 located between the stilt 103 and the blade 101 and an outer platform or heel 120 in the vicinity of the free end of the blade. The blade root 102 is, in the example shown, covered by a surface coating (not shown). Of course, it is not beyond the scope of the present invention if the blade root is coated with a first surface coating and the blade is coated with a second surface coating, identical to or different from the first surface coating, for example to smooth the surface of said blade. FIG. 6 shows an example of a turbomachine wheel 200 comprising blades manufactured by a method according to the invention according to the invention. The parts produced by the processes according to the invention can be fastened to different types of turbine rotors, in particular compressor and turbine rotors of different gas turbine bodies, for example a low pressure turbine (LP) impeller. 6 shows a turbomachine wheel 200 comprising a hub 130 on which are mounted a plurality of blades 100 made by a method according to the invention, each blade 100 including a foot 102. formed by a portion of greater 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. The wall of the housing 131 comprises nickel and / or cobalt. The wheel 200 further comprises a plurality of blade heel elements 120 mounted on each of the blades 100. Parts made by the methods of the invention may be attached to turbines of low or high pressure turbojets. The parts manufactured by the processes according to the invention can equip turbojet engines, for example of the CFM 56, LEAP X or M88 type.
    [0015] The parts manufactured by the processes according to the invention can also equip gas turbines. The expression "containing / containing a" must be understood as "containing / containing at least one".
    [0016] 30 The expression "understood between ... and ..." or "from ... to" must be understood as including boundaries.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Process for the manufacture of a composite material part (1) comprising a fibrous reinforcement densified by a ceramic matrix (2), the part (1) having an external surface (3) and being coated on at least a part of its surface external (3) by a surface coating (4) in solid form comprising an alloy, the method comprising the following steps: a) formation of the ceramic matrix (2) of the piece (1) of composite material by infiltration of the preform fibrous material with a melt infiltration composition, the infiltration composition comprising silicon and having a first melting temperature, the infiltration composition being brought into contact with all or part of a first set of present charges in the fiber preform, and b) forming the surface coating (4) of the composite material part (1) by infiltrating a second set of fillers and / or a preceramic resin with a composition melt coating composition, the coating composition having a second melting temperature lower than the first melting temperature and a composition different from that of the ceramic matrix (2).
    [0002]
    2. Method according to claim 1, characterized in that the alloy of the surface coating (4) is a silicon alloy.
    [0003]
    3. Method according to any one of claims 1 and 2, characterized in that the alloy of the surface coating (4) is an alloy of silicon and nickel or an alloy of silicon and cobalt.
    [0004]
    4. Method according to any one of claims 1 to 3, characterized in that the alloy of the surface coating (4) is present in a mass content greater than or equal to 5% relative to the mass of the surface coating ( 4) .35
    [0005]
    5. Method according to any one of claims 1 to 4, characterized in that the thickness (e) of the surface coating (4) is on all or part of the outer surface (3) of the part (1) coated, between 20 pm and 1000 pm.
    [0006]
    6. Method according to any one of claims 1 to 5, characterized in that the surface coating (4) is present on a first and a second region of the outer surface (3) of the part (1) and in that the composition and / or the thickness (e) of the surface coating (4) differs between the first region and the second region.
    [0007]
    7. Method according to any one of claims 1 to 6, characterized in that the infiltration composition is, during step a), brought into contact with reactive charges present in the fiber preform, a chemical reaction having place between the infiltration composition and the reactive charges during step a).
    [0008]
    8. Method according to any one of claims 1 to 7, characterized in that step b) is initiated after completion of step a). 20
    [0009]
    9. The method of claim 8, characterized in that step b) further comprises applying the melt coating composition to a deposit of the second set of fillers and / or the pre-ceramic resin. present on the outer surface (3) of the part (1) made of composite material.
    [0010]
    10. Method according to any one of claims 1 to 9, characterized in that the manufactured part constitutes a blade (100) of an aeronautical engine comprising at least one blade root (102) and a blade (101) and in the surface coating (4) covers at least the blade root (102).
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    WO2019122760A1|2019-06-27|Method for producing a composite part containing a ceramic matrix
    EP3830056A1|2021-06-09|Method for manufacturing a part made from cmc
    EP3592716B1|2021-08-18|Method for producing a consolidated fibrous preform
    FR3055625A1|2018-03-09|FIBROUS PREFORM FOR MANUFACTURING A COMPOSITE MATERIAL PART AND ASSOCIATED METHOD
    WO2019220057A1|2019-11-21|Method for manufacturing a cmc part
    FR3081156A1|2019-11-22|PROCESS FOR MANUFACTURING A COATED CMC PART
    FR3071246A1|2019-03-22|PROCESS FOR MANUFACTURING A CMC PIECE
    同族专利:
    公开号 | 公开日
    FR3023212B1|2019-10-11|
    WO2016001343A1|2016-01-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2939430A1|2008-12-04|2010-06-11|Snecma Propulsion Solide|METHOD FOR SMOOTHING THE SURFACE OF A PIECE OF CMC MATERIAL|
    FR3053328B1|2016-06-29|2022-01-21|Herakles|METHOD FOR MANUFACTURING A COMPOSITE MATERIAL PART WITH A CERAMIC MATRIX|
    US10138168B2|2017-01-12|2018-11-27|Rolls-Royce High Temperature Composites Inc.|Method of melt infiltration utilizing a non-wetting coating for producing a ceramic matrix composite|
    FR3063724A1|2017-03-08|2018-09-14|Safran Ceramics|PROCESS FOR INFILTRATION OF A POROUS PREFORM AND ASSOCIATED FURNACE|
    FR3071247B1|2017-09-21|2019-09-20|Safran Ceramics|PROCESS FOR MANUFACTURING A CMC PIECE|
    法律状态:
    2015-06-22| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-08| PLSC| Search report ready|Effective date: 20160108 |
    2016-06-10| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-26| PLFP| Fee payment|Year of fee payment: 4 |
    2017-08-25| CD| Change of name or company name|Owner name: HERAKLES, FR Effective date: 20170725 |
    2018-06-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1456392|2014-07-03|
    FR1456392A|FR3023212B1|2014-07-03|2014-07-03|METHOD FOR MANUFACTURING A COATED PART BY A SURFACE COATING COMPRISING AN ALLOY|FR1456392A| FR3023212B1|2014-07-03|2014-07-03|METHOD FOR MANUFACTURING A COATED PART BY A SURFACE COATING COMPRISING AN ALLOY|
    PCT/EP2015/065059| WO2016001343A1|2014-07-03|2015-07-02|Method for producing a part coated with a surface coating comprising an alloy|
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