EP3331657A1 - Procede de fabrication d'une piece en materiau composite - Google Patents
Procede de fabrication d'une piece en materiau compositeInfo
- Publication number
- EP3331657A1 EP3331657A1 EP16757320.3A EP16757320A EP3331657A1 EP 3331657 A1 EP3331657 A1 EP 3331657A1 EP 16757320 A EP16757320 A EP 16757320A EP 3331657 A1 EP3331657 A1 EP 3331657A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fibers
- preform
- alloy
- metal
- stacked structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 12
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 9
- 229910052751 metal Inorganic materials 0.000 claims abstract description 83
- 239000002184 metal Substances 0.000 claims abstract description 83
- 239000011159 matrix material Substances 0.000 claims abstract description 23
- 230000002787 reinforcement Effects 0.000 claims abstract description 6
- 239000000835 fiber Substances 0.000 claims description 141
- 229910045601 alloy Inorganic materials 0.000 claims description 70
- 239000000956 alloy Substances 0.000 claims description 70
- 238000000034 method Methods 0.000 claims description 37
- 239000000843 powder Substances 0.000 claims description 31
- 239000011230 binding agent Substances 0.000 claims description 24
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 22
- 239000010936 titanium Substances 0.000 claims description 19
- 238000010438 heat treatment Methods 0.000 claims description 14
- 238000002844 melting Methods 0.000 claims description 12
- 230000008018 melting Effects 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 11
- 229910052759 nickel Inorganic materials 0.000 claims description 11
- 238000009792 diffusion process Methods 0.000 claims description 10
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 9
- 238000001746 injection moulding Methods 0.000 claims description 9
- 229910052719 titanium Inorganic materials 0.000 claims description 9
- 238000003466 welding Methods 0.000 claims description 8
- 229910010293 ceramic material Inorganic materials 0.000 claims description 6
- 229910000531 Co alloy Inorganic materials 0.000 claims description 5
- 239000007769 metal material Substances 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 230000008030 elimination Effects 0.000 claims description 3
- 238000003379 elimination reaction Methods 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000005253 cladding Methods 0.000 claims description 2
- 238000002347 injection Methods 0.000 description 28
- 239000007924 injection Substances 0.000 description 28
- 239000000203 mixture Substances 0.000 description 19
- 238000000465 moulding Methods 0.000 description 12
- 238000003754 machining Methods 0.000 description 9
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 8
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 6
- 229910001026 inconel Inorganic materials 0.000 description 5
- 239000010964 304L stainless steel Substances 0.000 description 4
- 229910010038 TiAl Inorganic materials 0.000 description 4
- 229910052742 iron Inorganic materials 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 229910001092 metal group alloy Inorganic materials 0.000 description 4
- 239000011156 metal matrix composite Substances 0.000 description 4
- -1 polyethylene Polymers 0.000 description 4
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 4
- 229910010271 silicon carbide Inorganic materials 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 239000000919 ceramic Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 229910001256 stainless steel alloy Inorganic materials 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
- 239000004698 Polyethylene Substances 0.000 description 2
- 239000002202 Polyethylene glycol Substances 0.000 description 2
- 239000004743 Polypropylene Substances 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 2
- 229910052729 chemical element Inorganic materials 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000005056 compaction Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 229920000573 polyethylene Polymers 0.000 description 2
- 229920001223 polyethylene glycol Polymers 0.000 description 2
- 229920001155 polypropylene Polymers 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 238000010345 tape casting Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229920001817 Agar Polymers 0.000 description 1
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229930040373 Paraformaldehyde Natural products 0.000 description 1
- 235000021355 Stearic acid Nutrition 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 239000012300 argon atmosphere Substances 0.000 description 1
- 239000012298 atmosphere Substances 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 229920002678 cellulose Polymers 0.000 description 1
- 239000001913 cellulose Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007935 neutral effect Effects 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
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 229920006324 polyoxymethylene Polymers 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 230000003381 solubilizing effect Effects 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 238000010025 steaming Methods 0.000 description 1
- 239000008117 stearic acid Substances 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 229920005992 thermoplastic resin Polymers 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/02—Pretreatment of the fibres or filaments
- C22C47/025—Aligning or orienting the fibres
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/02—Pretreatment of the fibres or filaments
- C22C47/04—Pretreatment of the fibres or filaments by coating, e.g. with a protective or activated covering
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
- C22C47/14—Making alloys containing metallic or non-metallic fibres or filaments by powder metallurgy, i.e. by processing mixtures of metal powder and fibres or filaments
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
- C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
- C22C49/04—Light metals
- C22C49/06—Aluminium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
- C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
- C22C49/08—Iron group metals
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
- C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
- C22C49/10—Refractory metals
- C22C49/11—Titanium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
- C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2301/00—Metallic composition of the powder or its coating
- B22F2301/20—Refractory metals
- B22F2301/205—Titanium, zirconium or hafnium
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/1017—Multiple heating or additional steps
- B22F3/1021—Removal of binder or filler
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
- B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
Definitions
- the invention relates to a method for manufacturing a composite metal matrix part.
- One solution for improving the cohesion of the fibers with the metal matrix consists in using fibers consisting of a core of ceramic material and a metal sheath surrounding this core.
- the sheath may for example have been deposited by high speed coating.
- a heat diffusion welding treatment can then be performed to secure the fibers to a pre-shaped part, for example forged and / or machined.
- Such a solution is for example described in document FR 2 886 180.
- This solution works but it requires a large succession of operations: shaping of the initial part, machining of grooves to introduce the fibers, welding of a cover for close the workpiece, and heat diffusion welding treatment.
- the distribution of the fibers requires each time specific operations, making their distribution in multiple positions relatively long to achieve.
- the invention proposes, in a first aspect, a method of manufacturing a composite material part comprising a fibrous reinforcement densified by a metal matrix, the method comprising at least the following steps:
- step b) elimination of the first and second binders present in the stacked structure obtained after implementation of step b) in order to obtain a stacked structure unbound
- the melting temperatures ⁇ , T 2 and T 3 are expressed in ° C (degrees Celsius).
- first and second preforms based on powders advantageously makes it possible to significantly simplify the manufacture of the composite material part, in particular because of the possibility of using the same heat treatment step both to densify the first and second preforms and forming the metal matrix as well as to make the sheath of the fibers integral with the metal matrix.
- Obtaining parts with satisfactory mechanical properties by such a simplified process is made possible by the use of materials having particular melting temperatures to ensure efficient diffusion welding as mentioned above.
- the first binder and the second binder may be the same or different.
- the metal powder of the first alloy may be present in the first preform in a volume content of between 50% and 80% and the first binder may be present in the first preform in a volume content of between 20% and 50%.
- the metal powder of the second alloy may be present in the second preform in a volume content of between 50% and 80% and the second binder may be present in the second preform in a volume content of between 20% and 50%.
- the following two conditions can be verified:
- the first and second preforms may each be formed by implementing a metal injection molding process.
- a metal injection molding process (“Metal Injection Molding") to form the first and second preforms advantageously makes it possible to further simplify the process insofar as it is thus possible to obtain directly the first and second preforms to the desired ribs or practically to the desired ribs and therefore reduce the duration of the subsequent machining, or even to emancipate.
- the core of the fibers may, for example, be silicon carbide, zirconia or alumina.
- the metal sheath of the fibers, the first alloy and the second alloy may each consist mainly of a mass of the same metal element.
- the metal sheath of the fibers consists of at least 50% by weight of a chemical element X and that each of the first and second alloys consist of at least 50% by weight of this same element X.
- Such an embodiment advantageously makes it possible to further improve the compatibility between the metal sheath of the fibers and the metal matrix of the part obtained.
- the material forming the metal sheath of the fibers may be identical to the first alloy and / or the second alloy.
- the fibers may, in the stacked structure, be housed in grooves formed on the surface of the first preform and / or on the surface of the second preform.
- Such an exemplary embodiment advantageously makes it possible to use relatively thick fibers for the fibrous reinforcement of the part, the grooves compensating all or part of the thickness of these fibers.
- the metal sheath of all or part of the fibers may be in the form of a continuous layer of a metallic material.
- the metal sheath of all or part of the fibers may be in the form of a plurality of metal strands surrounding the core, for example helically wound around the core.
- the fibers may include a first set of fibers extending along a first direction and a second set of fibers extending along a second direction not parallel to the first direction.
- the following two conditions can be verified:
- Such an embodiment advantageously makes it possible to further improve the quality of the metal matrix obtained.
- the first alloy may be identical to the second alloy.
- the first alloy may be different from the second alloy.
- the first alloy and the second alloy may be chosen from: titanium-based alloys, nickel-based alloys, cobalt-based alloys, aluminum-based alloys or steels.
- FIGS. 1A to 1G represent different steps of an exemplary method according to the invention
- FIGS. 2A and 2B show the structure of the fibers used in the exemplary method illustrated in FIGS. 1A to 1G,
- FIGS. 3A and 3B show an alternative fiber structure that can be implemented in the context of a method according to the invention
- FIG. 4A represents an example of possible positioning of the fibers on the first preform
- FIG. 4B represents another example of possible positioning of the fibers on the first preform
- FIGS. 5A to 5D represent different steps of an alternative method according to the invention.
- FIGS. 6A to 6K represent different steps of an alternative method according to the invention, and - Figure 7 illustrates a detail of an alternative embodiment of the invention.
- FIGS. 1A to 1G show the implementation of the various steps of a first exemplary method according to the invention.
- FIG. 1A shows a molding cavity 3 which is defined between a mold 1 and a counter-mold 2 and in which a metal injection molding process is intended to be implemented in order to obtain the first or the second preform .
- the metal injection molding process is a technique known per se.
- the molding cavity 3 has the shape of the preform to be manufactured.
- An injection composition 5 is first injected under pressure into the molding cavity 3.
- the injection composition 5 comprises a powder of a metal alloy and a binder and is intended to form one of the first and second preforms.
- the metal alloy used in the injection composition 5 may, for example, be a titanium-based alloy, a nickel-based alloy, a cobalt-based alloy, an aluminum-based alloy, or an aluminum alloy. steel. Unless stated otherwise, a material said to be "based on a chemical element X" has the element X in a mass content greater than or equal to 50%.
- the binder can be chosen from: paraffins, thermoplastic resins, agar gel, cellulose, polyethylene, polyethylene glycol, polypropylene, stearic acid, polyoxy methylene and mixtures thereof.
- the volume content of the metal alloy powder in the injection composition may for example be between 50% and 80%.
- the volume content of the binder in the injection composition may for example be between 20% and 50%.
- the injection composition 5 may first be mixed at a temperature between 150 ° C and 200 ° C in a neutral atmosphere for example, and may then be injected into the molding cavity 3 at such a temperature.
- the injection composition 5 is injected into the molding cavity 3 through a single injection point 4.
- the mold 1 and the counter-mold 2 can be regulated in temperature.
- the mold 1 and the counter mold 2 can, for example, be maintained at a temperature between 30 ° C and 70 ° C to promote cooling of the blank.
- the blank thus produced is said in a "green state" or plastic. It is advantageous to perform the injection of the injection composition 5 in a molding cavity 3 in which the vacuum has been made, in order to facilitate the injection and to ensure the homogeneity of the blank that will be formed.
- each of the first and second preforms is obtained during two separate injections. These two injections can for example be performed one after the other in the same molding cavity or, alternatively, can be performed in two different molding cavities simultaneously or not.
- the blanks 6a and 6b of the first and second preforms are demolded as shown in Figure 1C.
- the blanks 6a and 6b can be machined in the green state to remove burrs or cores or injection points.
- the machining performed may, in addition, be carried out in order to modify the surfaces of the blanks 6a and 6b intended to be placed next to each other in the following process and / or to provide grooves on the surface. surface of the first and / or second preforms as will be detailed below.
- a first preform 7a of a first part of the part to be manufactured is obtained, this first preform 7a comprising at least one metal powder of a first alloy and a first binder and a second preform 7b of a second part of the workpiece comprising at least one metal powder of a second alloy and a second binder.
- the powder of the first alloy and / or the powder of the second alloy may, for example, have a grain size D90 of less than or equal to 150 ⁇ m (ie in this case at least 90% of the grains of the powder have a size less than or equal to at 150 ⁇ ).
- the present invention is not limited to the implementation of a metal injection molding process in order to obtain the first and second preforms. Indeed, one can alternatively use a tape casting process ("tape casting") or a powder compaction process.
- Tape casting a tape casting process
- a powder compaction process a powder compaction process.
- Implementing a metal injection molding process to form the first and second preforms is advantageous in order to quickly obtain a blank of said preforms having dimensions close to desired ribs, thereby simplifying the step of machining of these blanks.
- the implementation of a metal injection molding process also advantageously makes it possible to quickly obtain preforms having relatively complex shapes.
- the part intended to be formed in the context of the process of the invention may for example be a turbomachine part, for example a turbomachine blade. As a variant, said part may have an axisymmetric shape and for example constitute a turbine ring, segmented or not.
- a step a) is then carried out during which a plurality of fibers 10 are positioned on the surface of the first preform 7a as illustrated in FIG. 1E.
- the positioning of the fibers 10 on the first preform 7a may or may not be automated.
- FIGS. 2A and 2B show the structure of the fibers 10 used.
- Fig. 2A is a view of a fiber 10 in cross-section and
- Fig. 2B is a view of this fiber 10 in longitudinal section.
- the fibers 10 each comprise a core of ceramic material 10a coated with a metal sheath 10b.
- the metallic material forming the sheath 10b may be a metal or a metal alloy.
- the metal sheath 10b is in the form of a continuous layer of a metallic material, for example obtained by a high-speed coating process (EGV).
- the core of ceramic material 10a may for example be alumina, zirconia or silicon carbide.
- the core 10a may for example have a diameter (greater transverse dimension) greater than or equal to 1 ⁇ m, for example between 1 ⁇ m and 140 ⁇ m.
- the thickness of the metal sheath 10b may, for its part, be greater than or equal to 1 ⁇ m, for example between 1 ⁇ m and 140 ⁇ m.
- the metal sheath is intended to form the interface between the core 10a of the fibers 10 and the metal matrix of the piece of composite material obtained.
- the metal sheath 10'b is in the form of a plurality of metal strands 10'c surrounding the core 10'a.
- the metal strands 10'c can each be wound around the core 10'a.
- the diameter of the core 10'a and the thickness of the metal sheath 10'b may be as described above in connection with Figures 2A and 2B.
- at least six metal strands 10'c can surround the core 10'a fibers 10 '.
- the fibers 10 may, once positioned on the first preform 7a, extend over the majority (more than 50%) of the length of the first preform 7a and for example extend, as illustrated, on the the entire length of the first preform 7a.
- the fibers 10 may, once positioned on the first preform 7a extend from a first end 17a of the first preform 7a to a second end 18a of the first preform 7a located on the side opposite the first end 17a.
- the fibers 10 may, once positioned on the first preform 7a, have over-extension zones 11 and 12 extending beyond the first preform 7a. In the example illustrated in FIG. 1E, the over-length zones 11 and 12 extend from opposite ends 17a and 18a of the first preform 7a.
- the fibers 10 are positioned during step a) along the axes of mechanical stress of the part to be obtained.
- the density of fibers 10 positioned on the first preform 7a may be greater than or equal to 5 fibers per centimeter width of the first preform 7a. This fiber density may be less than or equal to 10 fibers per centimeter width of the first preform 7a and for example be between 5 and 10 fibers per centimeter width of the first preform 7a.
- FIG. 4A shows an example of possible positioning for the fibers 10 on the first preform 7a.
- Figure 4A is a top view of the fibers 10 and the first preform 7a.
- the fibers 10 may, once positioned on the first preform 7a, be spaced from one another.
- the spacing e between the fibers 10 may, for example, be constant as illustrated in FIG. 4A.
- the fibers 10 are, in the example of Figure 4A, parallel to each other once positioned on the first preform 7a.
- the fibers 10 can, once positioned on the first preform 7a, extend substantially rectilinear (in a straight line).
- the spacing between the fibers positioned on the first preform may vary.
- the fibers may, once positioned on the first preform, be in contact with each other.
- FIG. 4B shows a possible positioning variant for the fibers 10 on the first preform 7a.
- the fibers 10 comprise a first set of fibers 10 extending along a first direction X and a second set of fibers 10 extending along a second direction Y not parallel to the first direction X
- the first direction X may, for example, as illustrated in FIG. 4B be perpendicular to the second direction Y.
- FIGS. 4A and 4B illustrate possible positioning examples for the fibers 10 on the first preform 7a, any arrangement of fibers on the first preform being conceivable within the scope of the invention.
- step b) during which the second preform 7b is approaching the first preform 7a covered by the fibers 10 and is positioned on the first preform 7a as illustrated in FIG. Figure 1F.
- step b) the fibers 10 are interposed between the first preform 7a and the second preform 7b.
- the fibers 10 are in contact with the first 7a and the second preform 7b.
- the second preform 7b covers the first preform 7a and the fibers 10.
- the positioning of the fibers made during step a) is not modified during the positioning of the second preform 7b. The details described above relative to the positioning of the fibers 10 remain valid after implementation of step b).
- the first 7a and second 7b preforms are, before positioning the fibers 10, without any fibrous reinforcing element.
- the fibers 10 are indeed intended to constitute the fibrous reinforcement of the composite part to be obtained and are present at the interface between the first 7a and second 7b preforms.
- the fibers 10 may extend over the majority (more than 50%) of the length of the overlap area of the first preform 7a by the second preform 7b and for example extend, as illustrated, over the entire length of this area.
- the overlap area of the first preform 7a by the second preform 7b corresponds to the area on which the first and second preforms 7a and 7b are superimposed.
- the fibers 10 may, once step b) performed, extend from a first end 17b of the second preform 7b to a second end 18b of the second preform 7b located on the opposite side to the first end 17b.
- the oversize zones 11 and 12 of the fibers 10 may extend beyond the overlap area of the first preform 7a by the second preform 7b as illustrated.
- the melting temperature Ti of the first alloy, the melting temperature T 2 of the second alloy and the melting temperature T 3 of the metal cladding of the fibers satisfy the following two conditions:
- first and second nickel-based alloys and metallic sheath of the nickel-based fibers are first and second nickel-based alloys and metallic sheath of the nickel-based fibers
- first and second titanium-based alloys and metallic sheath of the titanium-based fibers are first and second titanium-based alloys and metallic sheath of the titanium-based fibers
- first and second cobalt-based alloys and metallic sheath of cobalt-based fibers are first and second cobalt-based alloys and metallic sheath of cobalt-based fibers
- first and second nickel-based alloys and metallic sheath of the iron-based fibers first and second cobalt-based alloys and metallic sheath of the nickel-based fibers
- first and second nickel-based alloys and metallic sheath of the cobalt-based fibers are first and second nickel-based alloys and metallic sheath of the cobalt-based fibers.
- the first and second alloys and the metal sheath of the fibers may each be based on the same metal element.
- the first and second alloys may be identical and the material constituting the metal sheath of the fibers may be identical to the material constituting the first and second alloys.
- step b) may optionally include carrying out a heating step to assemble the first preform, the second preform and the fibers via the first and second preforms. second binders.
- This assembly step makes it possible to obtain a consolidated stacked structure comprising the first and second preforms as well as that the fibers interposed between said preforms.
- a machining step of the consolidated stacked structure can be performed in order to adjust its dimensions to the desired dimensions for the final part.
- step c) The stacked structure obtained after implementation of step b) is then unbound (step c)).
- debinding there is selective removal of the first and second binders present in the stacked structure.
- step c) a chemical debinding of the stacked structure during which the stacked structure is brought into contact with one or more solvents for solubilizing all or part of the first and second binders.
- step c) thermal debinding it is possible to perform during step c) thermal debinding.
- thermal debinding can be performed in a sintering chamber so as not to have to move the stacked structure between step c) and step d).
- Thermal debinding can be performed after implementation of chemical debinding.
- the conditions for debinding used in the context of the present invention are known per se.
- step d) of heat treatment of the unbonded stacked structure is performed in order to obtain the piece 15 made of metal matrix composite material 14 (see FIG. 1G).
- the metal sheath of the fibers is assembled with the powders of the first and second alloys by diffusion welding and these powders are sintered to form the metal matrix.
- a treatment temperature greater than or equal to 1200 ° C., for example between 1250 ° C. and 1350 ° C.
- the duration during which this treatment temperature is imposed may for example be greater than or equal to 120 minutes, for example between 120 minutes and 180 minutes.
- Step d) makes it possible to densify the powders of the first and second alloys and to create bonds between the first and second preforms and the metal sheaths of the fibers.
- the fact of introducing sheathed fibers with a material compatible with the metal matrix makes it possible to improve the cohesion of the fibers with the metal matrix, thus optimizing the mechanical behavior of the part obtained.
- the over-length areas 11 and 12 of the fibers 10 have been eliminated. This elimination of the over-length zones 11 and 12 can be carried out after step d) or before step d), or even before step c).
- the part obtained in the context of the process according to the invention may comprise one or more layers of fibers.
- FIGS. 5A to 5D show an alternative method according to the invention in which the first and second preforms are formed during the same injection step. More specifically, the injection composition 25 is injected into the molding cavity 23 defined between the mold 21 and the counter-mold 22 through the injection point 24. This injection method makes it possible to form a parent blank 26 which can then undergo a machining step. A step is then made to cut the possibly machined mother blank to form the first 27a and second 27b preforms (see Figure 5D). The process is then continued in a manner similar to that described above once the first 27a and second 27b preforms obtained.
- FIGS. 6A to 6K show steps of an alternative embodiment of a method according to the invention.
- FIG. 6A (seen from above) and FIG. 6B (longitudinal sectional view) show a first preform 37a which is present on a support 30.
- the first preform 37a is present between two side walls 31 and 32 of the support 30 and fibers 10 are present on the first preform 37a and on the side walls 31 and 32.
- each of the side walls 31 and 32 has openings 31a, 31b, 32a and 32b.
- 6C (seen from above), 6D (longitudinal sectional view) and 6E (cross-sectional view), show the structure obtained after positioning on each of the lateral walls 31 and 32 of a positioning element 35 or 36
- the positioning members 35 and 36 each have a plurality of teeth 39 between which the fibers 10 are accommodated and thus allowing the fibers 10 to be held in the desired orientation.
- the positioning elements 35 and 36 each have openings 35a, 35b, 36a and 36b which are positioned facing the openings 31a, 31b, 32a and 32b of the side walls 31 and 32 of the support 30. As illustrated in FIGS.
- the positioning members 35 and 36 are then attached to the support 30 by fasteners 40a, 40b, 41a and 41b as screw-nut systems in the illustrated example.
- the second preform 37b is then positioned on the fibers 10 (see FIGS. 6H and 61) and the first preform 37a.
- the preforms 37a, 37b and the fibers 10 are then assembled by heat treatment through the binder (s) present in the preforms 37a and 37b as explained above.
- the consolidated stacked structure constituted by the first and second preforms 37a and 37b and the fibers 10 is then removed from the support 30 (see FIGS. 6J and 6K) in order to undergo debinding and heat treatment according to step d) as explained above. .
- FIG. 7 illustrates an alternative embodiment in which the fibers 10 are, in the stacked structure, housed in grooves 42a and 42b formed on the surface of the first preform 37a and / or on the surface of the second preform 37b. All or part of the thickness of the fibers 10 can be accommodated in these grooves 42a and 42b. It is not beyond the scope of the invention when only one of the first and second preforms has such grooves on its surface.
- a mixture of a metal powder and a binder is produced.
- This mixture is composed of 60% by volume of a metal powder of TA6V alloy and 40% by volume of a mixture of polyethylene glycol, polyethylene and polypropylene constituting the binder.
- the D90 size of the TA6V metal powder used was less than 35 ⁇ m and this powder was obtained by atomization under argon.
- first and second preforms were obtained.
- the mixture was injected into two injection molds.
- the injection temperature of the mixture was of the order of 190 ° C and the molds were cooled to about 50 ° C.
- First and second blanks of part of the part to be obtained were obtained after injection and molding of the mixture in the molds. The two blanks were deburred and the injection cores were removed in order to obtain a first and a second preform each constituting the preform of a half of the part to be obtained.
- Fibers were then positioned on the surface of one of the two preforms.
- the fibers used consisted of a central core of silicon carbide 80 microns in diameter and a pure titanium sheath (99% titanium content in the sheath greater than 99%) of a thickness of 10 microns.
- the titanium sheath was deposited on the ceramic cores by high speed coating.
- the fibers were deposited in a number to cover 10% of the surface of the preform by depositing 10 fibers per 10 millimeters of preform width. Tooling has been used to facilitate the positioning of the fibers and their maintenance, the use of this tooling being optional.
- the second preform has been positioned on the first preform as well as on said fibers.
- the assembly constituted by the stacking of the two preforms with the fibers interposed between these two preforms and by the holding tooling was then placed in an oven maintained at 70 ° C. for one hour. This steaming made it possible to bind the two preforms together by means of the binder present in these preforms and to obtain the consolidated stacked structure.
- the consolidated stacked structure was then separated from the holding tool.
- This structure then underwent a first chemical debinding step by immersion in a demineralized water bath while stirring the bath. The bath temperature was 60 ° C. and this debinding step was carried out for 24 hours.
- the partially debonded structure was placed on a zirconia plate and introduced into an oven in order to undergo a heat treatment to thermally finalize debinding.
- the heat treatment was then continued in order to sinter the metal powders to form the matrix of the part as well as to secure the metal sheath of the fibers to said matrix.
- An argon atmosphere at 20 mbar pressure was imposed during this heat treatment.
- the heat treatment performed had the following characteristics:
- the piece obtained was removed from the oven, the portions of the fibers protruding from the room were cut. The part can then possibly be machined to adjust its shape and dimensions to the desired application.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Manufacturing & Machinery (AREA)
- Composite Materials (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1557580A FR3039839B1 (fr) | 2015-08-06 | 2015-08-06 | Procede de fabrication d'une piece en materiau composite |
PCT/FR2016/052012 WO2017021652A1 (fr) | 2015-08-06 | 2016-08-02 | Procede de fabrication d'une piece en materiau composite |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3331657A1 true EP3331657A1 (fr) | 2018-06-13 |
EP3331657B1 EP3331657B1 (fr) | 2019-10-02 |
Family
ID=54366360
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16757320.3A Active EP3331657B1 (fr) | 2015-08-06 | 2016-08-02 | Procede de fabrication d'une piece en materiau composite |
Country Status (5)
Country | Link |
---|---|
US (1) | US11097345B2 (fr) |
EP (1) | EP3331657B1 (fr) |
CN (1) | CN107921539B (fr) |
FR (1) | FR3039839B1 (fr) |
WO (1) | WO2017021652A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3069179B1 (fr) * | 2017-07-21 | 2019-08-30 | Safran Helicopter Engines | Procede de fabrication de pieces de forme complexe par moulage par injection de poudres metalliques. |
CN110935878B (zh) * | 2019-12-30 | 2022-04-05 | 湖南英捷高科技有限责任公司 | 一种钛合金零件的注射成形方法 |
CN114619035B (zh) * | 2022-03-18 | 2023-12-08 | 湖南湘投轻材科技股份有限公司 | 异体分陶瓷增强铝基材料预制件冶金结合方法 |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB8614224D0 (en) * | 1985-06-21 | 1986-07-16 | Ici Plc | Fibre-reinforced metal matrix composites |
US5015533A (en) * | 1988-03-10 | 1991-05-14 | Texas Instruments Incorporated | Member of a refractory metal material of selected shape and method of making |
US4885214A (en) * | 1988-03-10 | 1989-12-05 | Texas Instruments Incorporated | Composite material and methods for making |
WO1999061385A2 (fr) * | 1998-05-26 | 1999-12-02 | J. Michael Richarde, Llc | Systeme et procede de fabrication d'un composite a fibres de carbone |
DE10005250B4 (de) * | 1999-02-09 | 2004-10-28 | Mtu Aero Engines Gmbh | Verfahren zur Herstellung von faserverstärkten metallischen Bauteilen |
JP4252161B2 (ja) * | 1999-06-29 | 2009-04-08 | 株式会社高田工業所 | 液相焼結を利用した金属系複合材料の製造方法 |
US6613392B2 (en) * | 2001-07-18 | 2003-09-02 | General Electric Company | Method for making a fiber reinforced composite article and product |
US7842375B2 (en) * | 2005-05-17 | 2010-11-30 | Rolls-Royce Corporation | Fiber retention system for metal matrix composite preform |
FR2886180B1 (fr) | 2005-05-27 | 2007-07-13 | Snecma Moteurs Sa | Procede de fabrication d'une nappe liee constituee de fils ceramiques a matrice metallique, dispositif de mise en oeuvre du procede nappe liee obtenue par le procede |
US7803313B2 (en) * | 2007-02-15 | 2010-09-28 | Precision Castparts Corp. | Method for bonding powder metallurgical parts |
FR2925897B1 (fr) * | 2007-12-28 | 2010-07-30 | Messier Dowty Sa | Procede de fabrication de pieces avec insert en materiau composite a matrice metallique |
FR2925896B1 (fr) * | 2007-12-28 | 2010-02-05 | Messier Dowty Sa | Procede de fabrication d'une piece metallique renforcee de fibres ceramiques |
CN101285187B (zh) * | 2008-05-15 | 2010-08-18 | 西北工业大学 | 一种颗粒增强金属基复合材料的制备方法 |
FR2935990B1 (fr) * | 2008-09-17 | 2011-05-13 | Aircelle Sa | Procede de fabrication d'une piece en materiau composite a matrice metallique |
GB201013440D0 (en) * | 2010-08-11 | 2010-09-22 | Rolls Royce Plc | A method of manufacturing a fibre reinforced metal matrix composite article |
US9291060B2 (en) * | 2013-03-14 | 2016-03-22 | Rolls-Royce Corporation | High strength joints in ceramic matrix composite preforms |
CA2926768C (fr) * | 2013-10-15 | 2018-10-23 | Ihi Corporation | Procede permettant de lier des corps moules par injection de poudres metalliques |
FR3021669B1 (fr) * | 2014-06-03 | 2017-08-25 | Sagem Defense Securite | Procede de fabrication d'une piece dans un materiau composite a matrice metallique et outillage associe |
WO2019060440A2 (fr) * | 2017-09-19 | 2019-03-28 | Riley Reese | Matériaux composites à matrice métallique, céramique et métallique/céramique renforcée par des fibres et procédés associés |
US10752556B2 (en) * | 2018-10-18 | 2020-08-25 | Rolls-Royce High Temperature Composites Inc. | Method of processing a ceramic matrix composite (CMC) component |
-
2015
- 2015-08-06 FR FR1557580A patent/FR3039839B1/fr active Active
-
2016
- 2016-08-02 CN CN201680049087.9A patent/CN107921539B/zh active Active
- 2016-08-02 WO PCT/FR2016/052012 patent/WO2017021652A1/fr active Application Filing
- 2016-08-02 US US15/750,008 patent/US11097345B2/en active Active
- 2016-08-02 EP EP16757320.3A patent/EP3331657B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR3039839B1 (fr) | 2019-12-20 |
EP3331657B1 (fr) | 2019-10-02 |
CN107921539B (zh) | 2021-01-08 |
CN107921539A (zh) | 2018-04-17 |
US11097345B2 (en) | 2021-08-24 |
FR3039839A1 (fr) | 2017-02-10 |
WO2017021652A1 (fr) | 2017-02-09 |
US20180221957A1 (en) | 2018-08-09 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2245204B1 (fr) | Procede de fabrication de pieces avec insert en materiau composite a matrice metallique | |
EP2349687B1 (fr) | Procede de fabrication de piece de forme complexe en materiau composite | |
EP0761977B1 (fr) | Turbine en matériau composite thermostructural, en particulier à petit diamètre, et procédé pour sa fabrication | |
EP3331657B1 (fr) | Procede de fabrication d'une piece en materiau composite | |
CA2824374C (fr) | Structure fibreuse tissee multicouches ayant une partie tubulaire creuse, procede de fabrication et piece composite la comportant | |
FR2944721A1 (fr) | Procede de fabrication d'un aubage par moulage par injection de poudre metallique | |
EP3860783B1 (fr) | Procede de realisation de contre-forme et procede de fabrication de piece de forme complexe utilisant une telle contre-forme | |
FR3023212B1 (fr) | Procede de fabrication d'une piece revetue par un revetement de surface comportant un alliage | |
EP2895285B1 (fr) | Modele de fonderie. | |
CA2710451C (fr) | Procede de fabrication d'une piece metallique renforcee de fibres ceramiques | |
FR2659887A1 (fr) | Procede pour ajuster le diametre interne d'objets annulaires renforces par des filaments. | |
FR2970266A1 (fr) | Procede de fabrication d'une piece metallique annulaire monobloc a insert de renfort en materiau composite, et piece obtenue | |
WO2012114053A2 (fr) | Procede de fabrication d'une piece metallique | |
EP0364360B1 (fr) | Procédé de fabrication de pièces composites constituées d'un voile et d'un renfort | |
FR2949091A1 (fr) | Procede de realisation d'un disque aubage monobloc creux | |
FR3036409B1 (fr) | Materiau composite a matrice metallique a base nickel et procede de fabrication d'un tel materiau composite | |
EP3595842B1 (fr) | Procédé de fabrication de pièces en alliage métallique de forme complexe | |
FR3039838A1 (fr) | Procede de fabrication d'une piece en materiau composite | |
WO2021023925A1 (fr) | Procede de fabrication d'une piece metallique | |
EP3980207B1 (fr) | Procede de fabrication de piece de turbomachine par moulage mim | |
FR2949366A1 (fr) | Realisation par procede mim d'un morceau de piece pour la reparation d'une aube de distributeur de turbine | |
FR3038702A1 (fr) | Outillage destine a supporter une preforme en poudre pendant un traitement thermique | |
FR3038703A1 (fr) | Outillage destine a supporter une preforme en poudre pendant un traitement thermique | |
FR3026979A1 (fr) |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20180129 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20190111 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: C22C 49/14 20060101ALI20190222BHEP Ipc: B22F 3/10 20060101ALN20190222BHEP Ipc: B22F 7/06 20060101AFI20190222BHEP Ipc: C22C 49/06 20060101ALI20190222BHEP Ipc: C22C 47/04 20060101ALI20190222BHEP Ipc: C22C 47/14 20060101ALI20190222BHEP Ipc: C22C 47/02 20060101ALI20190222BHEP Ipc: C22C 49/11 20060101ALI20190222BHEP Ipc: C22C 49/08 20060101ALI20190222BHEP Ipc: B22F 3/22 20060101ALN20190222BHEP |
|
INTG | Intention to grant announced |
Effective date: 20190329 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP Ref country code: AT Ref legal event code: REF Ref document number: 1185647 Country of ref document: AT Kind code of ref document: T Effective date: 20191015 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602016021750 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: FRENCH |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20191002 |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG4D |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1185647 Country of ref document: AT Kind code of ref document: T Effective date: 20191002 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200102 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200102 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200103 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200203 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200224 Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602016021750 Country of ref document: DE |
|
PG2D | Information on lapse in contracting state deleted |
Ref country code: IS |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20200202 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
26N | No opposition filed |
Effective date: 20200703 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200831 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200831 Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200802 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20200831 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200831 Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20200802 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20210720 Year of fee payment: 6 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20210720 Year of fee payment: 6 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20191002 |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220803 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220802 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230720 Year of fee payment: 8 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230720 Year of fee payment: 8 Ref country code: DE Payment date: 20230720 Year of fee payment: 8 |