WO2022084602A1 - Procede de fabrication d'une piece creuse en materiau composite a matrice metallique ou ceramique renforcee avec des fibres courtes - Google Patents
Procede de fabrication d'une piece creuse en materiau composite a matrice metallique ou ceramique renforcee avec des fibres courtes Download PDFInfo
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- WO2022084602A1 WO2022084602A1 PCT/FR2021/051767 FR2021051767W WO2022084602A1 WO 2022084602 A1 WO2022084602 A1 WO 2022084602A1 FR 2021051767 W FR2021051767 W FR 2021051767W WO 2022084602 A1 WO2022084602 A1 WO 2022084602A1
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- WIPO (PCT)
- Prior art keywords
- raw material
- sacrificial core
- metal matrix
- ceramic
- injection
- Prior art date
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- 238000000034 method Methods 0.000 title claims abstract description 30
- 239000000835 fiber Substances 0.000 title claims abstract description 29
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 23
- 239000011153 ceramic matrix composite Substances 0.000 title abstract description 4
- 239000011156 metal matrix composite Substances 0.000 title abstract description 4
- 239000002994 raw material Substances 0.000 claims abstract description 53
- 239000011159 matrix material Substances 0.000 claims abstract description 39
- 239000000919 ceramic Substances 0.000 claims abstract description 24
- 229910052751 metal Inorganic materials 0.000 claims abstract description 22
- 239000002184 metal Substances 0.000 claims abstract description 22
- 238000005245 sintering Methods 0.000 claims abstract description 20
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 15
- 239000010439 graphite Substances 0.000 claims abstract description 15
- 238000000465 moulding Methods 0.000 claims abstract description 13
- 239000002243 precursor Substances 0.000 claims abstract description 13
- 238000001746 injection moulding Methods 0.000 claims abstract description 9
- 229910052582 BN Inorganic materials 0.000 claims abstract description 7
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000003973 paint Substances 0.000 claims abstract description 5
- 238000007493 shaping process Methods 0.000 claims abstract description 5
- 239000002131 composite material Substances 0.000 claims description 26
- 239000000463 material Substances 0.000 claims description 26
- 238000002347 injection Methods 0.000 claims description 17
- 239000007924 injection Substances 0.000 claims description 17
- 238000000280 densification Methods 0.000 claims description 12
- 239000000945 filler Substances 0.000 claims description 11
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 10
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 7
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 7
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 6
- 239000011230 binding agent Substances 0.000 claims description 6
- 230000004888 barrier function Effects 0.000 claims description 5
- 238000009792 diffusion process Methods 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 230000008030 elimination Effects 0.000 claims description 3
- 238000003379 elimination reaction Methods 0.000 claims description 3
- 238000000605 extraction Methods 0.000 claims description 3
- 238000005507 spraying Methods 0.000 abstract description 3
- 239000011162 core material Substances 0.000 description 54
- 239000010410 layer Substances 0.000 description 11
- 230000002787 reinforcement Effects 0.000 description 5
- 239000002245 particle Substances 0.000 description 4
- 239000000843 powder Substances 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 238000002490 spark plasma sintering Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- CPLXHLVBOLITMK-UHFFFAOYSA-N Magnesium oxide Chemical compound [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 2
- 229930040373 Paraformaldehyde Natural products 0.000 description 2
- 239000002202 Polyethylene glycol Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000004020 conductor Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
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- 239000000203 mixture Substances 0.000 description 2
- 229920001223 polyethylene glycol Polymers 0.000 description 2
- 229920006324 polyoxymethylene Polymers 0.000 description 2
- -1 polypropylene Polymers 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 239000004743 Polypropylene Substances 0.000 description 1
- 235000021355 Stearic acid Nutrition 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 238000007596 consolidation process Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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- 239000007789 gas Substances 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000395 magnesium oxide Substances 0.000 description 1
- 239000002923 metal particle Substances 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- QIQXTHQIDYTFRH-UHFFFAOYSA-N octadecanoic acid Chemical compound CCCCCCCCCCCCCCCCCC(O)=O QIQXTHQIDYTFRH-UHFFFAOYSA-N 0.000 description 1
- OQCDKBAXFALNLD-UHFFFAOYSA-N octadecanoic acid Natural products CCCCCCCC(C)CCCCCCCCC(O)=O OQCDKBAXFALNLD-UHFFFAOYSA-N 0.000 description 1
- 239000011368 organic material Substances 0.000 description 1
- 239000005416 organic matter Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 229920001155 polypropylene Polymers 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 238000010926 purge Methods 0.000 description 1
- 239000011214 refractory ceramic Substances 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 239000008117 stearic acid Substances 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 238000009941 weaving Methods 0.000 description 1
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- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/526—Fibers characterised by the length of the fibers
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/602—Making the green bodies or pre-forms by moulding
- C04B2235/6022—Injection moulding
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/602—Making the green bodies or pre-forms by moulding
- C04B2235/6028—Shaping around a core which is removed later
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
- C04B2235/66—Specific sintering techniques, e.g. centrifugal sintering
- C04B2235/666—Applying a current during sintering, e.g. plasma sintering [SPS], electrical resistance heating or pulse electric current sintering [PECS]
Definitions
- the present invention relates to the general field of the manufacture of hollow parts made of composite material with a metal or ceramic matrix.
- Ceramic (CMC) or metallic (CMM) matrix composite materials are materials consisting of a fibrous reinforcement densified by a ceramic or metallic matrix. These materials have a high level of performance in terms of stiffness and resistance at high temperature.
- a field of application of the invention is the manufacture of hollow parts used in the hot parts of a turbomachine, for example parts of the turbine, rear body or secondary nozzles of the turbomachine. More specifically, the invention can be used for producing distributors or hollow turbine blades.
- a turbine stage consists of a fixed blade or distributor belonging to a stator, followed by a mobile blade belonging to a rotor.
- the first stages of the distributor are generally hollow in order to route air radially from the outside to the inside of the turbine, so as to supply the hub with air to ensure its pressurization and purging as well as its possible cooling. . Part of this air can be intended for cooling the distributor.
- the moving blades can also be hollow so that cooling air can pass through them.
- the use of hollow parts also makes it possible to reduce the mass of the turbomachine.
- Document US2020270180 discloses a process for manufacturing hollow CMC parts which consists of forming a fibrous preform around a core, consolidating the preform and eliminating the core.
- the fibrous preform is formed with continuous fibers by draping fibrous textures around the core or by weaving a preform comprising a hollow zone intended for the insertion of the core.
- Short fibers make it possible to obtain small parts. Short fibers also allow the manufacture of composite material parts directly in their final shape (“net shape”) or near final shape (“near net shape”).
- the object of the present invention is therefore to overcome the aforementioned drawbacks by proposing a method for manufacturing a hollow part made of composite material with a ceramic or metallic matrix comprising the following steps: preparation of a raw material comprising at least short fibers and a ceramic matrix or metal matrix precursor loading, positioning of a sacrificial core in a molding cavity of an injection tool, the molding cavity having dimensions greater than the dimensions of the sacrificial core, shaping of the raw material by injection molding said raw material into the free space between the sacrificial core and an internal wall of the molding cavity so as to obtain a green part comprising the sacrificial core and the shaped raw material , extraction of the green part from the injection tooling, densification of the raw material by flash sintering of the green part so as to transform the charge into a ceramic matrix or a metal matrix, removal or elimination of the sacrificial core so as to obtain a hollow part made of composite material with a ceramic or metal matrix.
- the manufacturing method of the invention advantageously combines the use of a sacrificial core with the techniques of injection molding and densification by flash sintering.
- the sacrificial core serves both as a counter-mold during the shaping step to define the shape and dimensions of the cavity to be formed and of the final part ("net shape") and as a conductor which participates in the sintering of the particles of the matrix precursor filler.
- the method of the invention makes it possible to manufacture hollow parts in CMC or CMM composite material with short fiber reinforcement, even for parts of small dimensions and/or having a complex geometry.
- the sacrificial core has a geometry capable of being unmolded from the densified raw material after the densification step.
- the sacrificial core can be coated with a sheet of flexible graphite, a layer of graphite deposited by spraying or a layer of boron nitride paint before the step of injecting the raw material in order to facilitate its mechanical removal.
- the sacrificial core is eliminated by chemical treatment. This makes it possible to use cores that have complex geometries that cannot be demolded (undercuts) and to form parts with any shape of cavity.
- the sacrificial core is made with one of the following materials: graphite, zirconia and alumina.
- the raw material comprises a ceramic matrix precursor filler and short fibers made of a material chosen from one of the following materials: carbon, silicon carbide and alumina.
- the raw material comprises a metal matrix precursor filler and short fibers made of a material chosen from one of the following materials: silicon carbide and alumina.
- a load metal typically silicon, can also be added to the raw material to promote final densification.
- At least one diffusion barrier layer is deposited on the sacrificial core before the injection of the raw material. This avoids possible chemical interactions between the sacrificial core material and the material(s) used in the raw material to form the matrix.
- the raw material further comprises a binder, the process further comprising a step of debinding the raw material before or during the densification of the raw material. This eliminates the presence of organic matter in the composite material of the final part.
- Figure 1 is a flowchart showing the steps of a method of manufacturing a hollow part made of composite material with a ceramic or metal matrix with short fiber reinforcement according to the invention
- Figure 2 is a schematic perspective view of a sacrificial core in accordance with one embodiment of the invention.
- Figure 3 is a schematic exploded perspective view showing the positioning of a sacrificial core in an injection molding tool according to one embodiment of the invention
- Figure 4 is a sectional view of the tooling of figure 3 once closed
- Figure 5 is another sectional view of the tooling of figure 3 once closed
- Figure 6 is a schematic exploded perspective view showing the extraction of a green part of the tooling of Figures 3, 4 and 5,
- Figure 7 is a schematic sectional view of a flash sintering tool in which the green part of Figure 6 is placed
- Figure 8 is a schematic perspective view of a hollow part made of composite material with a ceramic or metal matrix with short fiber reinforcement after removal of the sacrificial core.
- the process for manufacturing a part made of ceramic matrix composite material (CMC) or of metal matrix composite material (CMM) according to the invention begins with the production of a sacrificial core 10 (step S1 , Figure 2).
- the sacrificial core is made of a material compatible with the manufacturing steps of the method of the invention and of the desired final material, the material of the core preferably having thermochemical compatibilities with the composite material of the part.
- the constituent material of the sacrificial core also has mechanical and thermal properties allowing it to withstand the pressures and temperatures used during the manufacture of the part as described below.
- the sacrificial core can also be electrically conductive to participate in the heating of the green part during the SPS flash sintering step.
- the sacrificial core material must also be easily removable or removable without damaging the final part.
- the sacrificial core can be made of graphite, alumina or zirconia.
- the sacrificial core 10 comprises a body 11 which has a geometry and dimensions corresponding to those of the hollow or the cavity which it is desired to form in the final CMC or CMM part.
- the core 10 further comprises positioning pins or extra lengths 12 which extend from the body 11 and which are intended to facilitate holding the sacrificial core in position in an injection tool as explained below.
- the sacrificial core can be obtained by machining or any other means known to those skilled in the art.
- the next step consists in preparing a raw material (also called “feedstock” in English) comprising (step S2) at least short fibers and a precursor filler of ceramic matrix or metal matrix.
- the raw material may further comprise a binder, which is the case in the example described here.
- the short fibers here have a length of between 50 mm and 100 mm.
- Short fibers allow the manufacture of CMC or CMM parts directly in their final shape ("net shape”) or near final shape ("near net shape”).
- the short fibers provide isotropic or transverse isotropic reinforcement which improves the creep resistance of the metal matrix of the part. This improves the rigidity of the CMM part at high temperature while reducing its density, which makes it possible to increase the specific mechanical properties.
- the raw material comprises a ceramic matrix precursor filler and short fibers made of a material chosen from one of the following materials: carbon, silicon carbide, alumina, mullite and magnesia.
- the ceramic matrix precursor filler consists of a powder of refractory ceramic particles, for example particles of silicon carbide, boron nitride (Si 3 N 4 ) or any mixture of ceramic powders.
- the raw material comprises a metal matrix precursor filler and short fibers in a material chosen from one of the following materials: silicon carbide and alumina.
- the metal matrix precursor filler consists of a powder of metal particles, in particular particles of titanium alloy, nickel alloy or aluminum alloy.
- the binder consists of at least one polymeric binder such as polyethylene glycol (PEG), stearic acid, polypropylene, or even a formulation based on polyoxymethylene (POM).
- PEG polyethylene glycol
- POM polyoxymethylene
- the injection tool 20 comprises a first half-shell 21 comprising an imprint 210 and a second half-shell 22 comprising an imprint 220.
- the cavities 210 and 220 delimit a molding cavity 23 having dimensions greater than the dimensions of the sacrificial core 10 in order to provide an injection space between the external surface of the core and the wall of the mold cavity.
- Housings 211 and 221 also extend respectively from cavities 210 and 220.
- Housings 211 and 221 are intended to cooperate with overlengths 12 of sacrificial core 10 so as to hold the core in position in the cavity of molding to form an injection space 230 between the core and the wall of the cavities 210 and 220 for the raw material (FIGS. 4 and 5).
- the injection space 230 is sized as a function of the final thickness of the material of the target part, taking account in particular of the influence of sintering and of any debinding on the geometric variation of the part.
- step S4 The raw material is then shaped by the injection molding technique. More specifically, once the injection tool 20 is closed with the sacrificial core 10 positioned inside, a raw material 30 prepared in step S2 is injected into the free space 230 between the sacrificial core 10 and the wall. inside the mold cavity 23 via an injection port 30 (FIGS. 4 and 5).
- a green part 40 is obtained, also called a “green body”, comprising the sacrificial core 10 coated on its outer surface with a layer of shaped raw material 30 (figure 6).
- the green part 40 is then extracted (stripped) from the injection tooling (FIG. 6, step S5).
- a step of debinding the raw material is carried out before the step of placing the green part in the flash sintering tool so as to eliminate the organic material from the composite material to be manufactured (step S6 ).
- the debinding step can be carried out by solvent route, thermal route under inert gas, a combination of these two routes, etc. Debinding can also be carried out directly in-situ in the flash sintering tooling by a suitable treatment carried out before the flash sintering.
- the green part 40 is placed in a flash sintering tool or SPS (“Spark Plasma Sintering”) 50 (FIG. 7, step S7).
- SPS Spark Plasma Sintering
- the difference between conventional hot pressing and flash sintering is that the heat source is not external but an electric current (direct - pulsed direct - or alternating) applied via electrodes passes through a conductive mold.
- flash sintering consists of heat treatment under mechanical stress using a tool to enclose the green part. The application of the heat is carried out by Joule effect as close as possible to the green part by the passage of an electric current, which makes it possible to quickly close the porosity and to very quickly reach a maximum rate of densification (formation of bonds between grains without total fusion of these).
- the flash sintering tool 50 makes it possible to subject the raw material 30 to pulses (3.3 ms) of direct electric current (typically 0-25 V, 1-20 kA) while applying a pressure of several tens of MPa ( up to 300 MPa) and this in a range of temperatures varying from ambient temperature to 2500°C. Flash sintering is generally carried out under vacuum but it is possible to work under an inert atmosphere (nitrogen, argon).
- the flash sintering tool 50 comprises for this purpose a mold formed by two half-shells 51 and 52 made of an electrically conductive material such as graphite.
- the two half-shells 51 and 52 define between them a molding cavity, which may have a complex shape, the dimensions of which are defined according to the dimensions of the final part to be produced.
- the sacrificial core plays here the role of counter-mold to ensure the densification of the internal walls of the final part.
- the tool 50 comprises first and second electrodes 55 and 56 connected, on the one hand, to a current generator 57 and, on the other hand, to the half-shells 51 and 52 of the mold respectively via a first piston 53 and a second piston 54.
- a key tool can be used.
- the generator 57 emits a current I which circulates through all the tooling 50, namely the electrodes 56 and 57, the pistons 53 and 54 and the half-shells 51 and 52, but also the charge of the raw material 30 and the sacrificial core 10.
- a mechanical stress P is also applied to the half-shells 51 and 52 by the pistons 53 and 54 during sintering.
- the parameters of the densification cycle namely mainly the intensity of the electric current, the value of the mechanical stress applied and the nature of the treatment atmosphere, are defined by the nature of the elements to be sintered of the raw material and are well known to those skilled in the art.
- the electric current is controlled according to the defined thermal cycles (temperature rise/fall ramps, stages, etc.).
- the mechanical constraint can also be controlled if necessary (release/application of constraint).
- the molds used are preferably made of graphite and are separated from the powder by a sheet of graphite to avoid any sticking or by any other means known to those skilled in the art, such as in particular a layer of graphite deposited by spraying or a layer of paint of boron nitride.
- the preform obtained is extracted from the tool 50.
- the next step consists in removing or eliminating the sacrificial core (step S9). If its geometry allows it, i.e. if the core has no undercut, the core can be removed mechanically. In order to facilitate mechanical removal, the sacrificial core may be wrapped or coated with a sheet of flexible graphite, a layer of spray-deposited graphite or a layer of boron nitride paint before the shaping step. raw material by injection molding.
- the sacrificial core can also be removed by thermochemical treatment.
- thermochemical oxidation treatment carried out, for example, in air at a temperature between 400° C. and 600° C. if the material of the part allows it. .
- a part 60 is obtained in composite material with a ceramic or metal matrix reinforced with short fibres, the part comprising an internal recess 61 whose shape and dimensions have been defined by the sacrificial core. 10.
- a diffusion barrier layer can be formed on the outer surface of the core before the injection of the raw material.
- the diffusion barrier can consist of a layer of boron nitride.
- metallic bases it is possible to deposit alumina or tungsten as a barrier layer).
- the method of the invention makes it possible to easily and reproducibly produce hollow parts made of composite material with a short fiber ceramic matrix (CMC-FC), the fibers being coated with an interphase and optionally with a protective layer of the interphase.
- CCM -FC short fiber metal matrix material
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Ceramic Engineering (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Structural Engineering (AREA)
- Mechanical Engineering (AREA)
- Inorganic Chemistry (AREA)
- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Producing Shaped Articles From Materials (AREA)
Abstract
Description
Claims
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CN202180071534.1A CN116547253A (zh) | 2020-10-20 | 2021-10-12 | 一种由短纤维增强的金属基体或陶瓷基体复合材料制成的空心部件的制造方法 |
EP21810068.3A EP4373796A1 (fr) | 2020-10-20 | 2021-10-12 | Procede de fabrication d'une piece creuse en materiau composite a matrice metallique ou ceramique renforcee avec des fibres courtes |
US18/248,652 US20230382813A1 (en) | 2020-10-20 | 2021-10-12 | Method for manufacturing a hollow part made of metal matrix or ceramic matrix composite reinforced with short fibers |
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FR2010738A FR3115280B1 (fr) | 2020-10-20 | 2020-10-20 | Procédé de fabrication d’une pièce creuse en matériau composite à matrice métallique ou céramique renforcée avec des fibres courtes |
FRFR2010738 | 2020-10-20 |
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PCT/FR2021/051767 WO2022084602A1 (fr) | 2020-10-20 | 2021-10-12 | Procede de fabrication d'une piece creuse en materiau composite a matrice metallique ou ceramique renforcee avec des fibres courtes |
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US (1) | US20230382813A1 (fr) |
EP (1) | EP4373796A1 (fr) |
CN (1) | CN116547253A (fr) |
FR (1) | FR3115280B1 (fr) |
WO (1) | WO2022084602A1 (fr) |
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CN115745640A (zh) * | 2022-11-02 | 2023-03-07 | 西安鑫垚陶瓷复合材料股份有限公司 | 一种陶瓷基复合材料细长薄壁管成型工艺 |
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FR2996549A1 (fr) * | 2012-10-04 | 2014-04-11 | Herakles | Procede de fabrication d'une piece aerodynamique par surmoulage d'une enveloppe ceramique sur une preforme composite |
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FR3086566A1 (fr) * | 2018-10-02 | 2020-04-03 | Norimat | Procede de fabrication de piece de forme complexe par frittage sous pression a partir d'une preforme |
US20200270180A1 (en) | 2017-10-02 | 2020-08-27 | Safran Ceramics | Method for producing a hollow part made of a ceramic matrix composite material |
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US10486378B2 (en) * | 2016-08-01 | 2019-11-26 | GM Global Technology Operations LLC | Methods of manufacturing vehicle assemblies |
CN110590374A (zh) * | 2019-10-28 | 2019-12-20 | 中原工学院 | 一种Flashing法制备MoSi2-SiC复合材料的方法 |
-
2020
- 2020-10-20 FR FR2010738A patent/FR3115280B1/fr active Active
-
2021
- 2021-10-12 EP EP21810068.3A patent/EP4373796A1/fr active Pending
- 2021-10-12 US US18/248,652 patent/US20230382813A1/en active Pending
- 2021-10-12 CN CN202180071534.1A patent/CN116547253A/zh active Pending
- 2021-10-12 WO PCT/FR2021/051767 patent/WO2022084602A1/fr active Application Filing
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US5910095A (en) * | 1997-02-21 | 1999-06-08 | Northrop Grumman Corporation | Fiber reinforced ceramic matrix composite marine engine riser elbow |
FR2996549A1 (fr) * | 2012-10-04 | 2014-04-11 | Herakles | Procede de fabrication d'une piece aerodynamique par surmoulage d'une enveloppe ceramique sur une preforme composite |
WO2019016447A1 (fr) * | 2017-07-21 | 2019-01-24 | Safran Helicopter Engines | Procédé de fabrication de pièces de forme complexe par moulage par injection de poudres métalliques |
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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CN115745640A (zh) * | 2022-11-02 | 2023-03-07 | 西安鑫垚陶瓷复合材料股份有限公司 | 一种陶瓷基复合材料细长薄壁管成型工艺 |
CN115745640B (zh) * | 2022-11-02 | 2023-09-01 | 西安鑫垚陶瓷复合材料股份有限公司 | 一种陶瓷基复合材料细长薄壁管成型工艺 |
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US20230382813A1 (en) | 2023-11-30 |
FR3115280B1 (fr) | 2023-07-21 |
CN116547253A (zh) | 2023-08-04 |
EP4373796A1 (fr) | 2024-05-29 |
FR3115280A1 (fr) | 2022-04-22 |
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