EP3899090A1 - Revetement pour noyau de conformage a chaud - Google Patents
Revetement pour noyau de conformage a chaudInfo
- Publication number
- EP3899090A1 EP3899090A1 EP19848973.4A EP19848973A EP3899090A1 EP 3899090 A1 EP3899090 A1 EP 3899090A1 EP 19848973 A EP19848973 A EP 19848973A EP 3899090 A1 EP3899090 A1 EP 3899090A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- core
- coating
- component
- sheet
- solution
- 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.)
- Pending
Links
- 238000000576 coating method Methods 0.000 title claims abstract description 41
- 239000011248 coating agent Substances 0.000 title claims abstract description 31
- 238000007493 shaping process Methods 0.000 title description 6
- 238000000034 method Methods 0.000 claims abstract description 26
- 238000010438 heat treatment Methods 0.000 claims abstract description 13
- 239000011230 binding agent Substances 0.000 claims abstract description 12
- 238000009792 diffusion process Methods 0.000 claims abstract description 11
- 229910044991 metal oxide Inorganic materials 0.000 claims abstract description 8
- 150000004706 metal oxides Chemical class 0.000 claims abstract description 8
- 239000000463 material Substances 0.000 claims description 17
- 239000000084 colloidal system Substances 0.000 claims description 14
- 238000004519 manufacturing process Methods 0.000 claims description 14
- 238000005056 compaction Methods 0.000 claims description 10
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 8
- 229910052684 Cerium Inorganic materials 0.000 claims description 7
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 claims description 7
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 claims description 7
- 239000000843 powder Substances 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 6
- 238000000605 extraction Methods 0.000 claims description 4
- 229910052747 lanthanoid Inorganic materials 0.000 claims description 3
- 150000002602 lanthanoids Chemical class 0.000 claims description 3
- 229910052723 transition metal Inorganic materials 0.000 claims description 3
- 150000003624 transition metals Chemical class 0.000 claims description 3
- 229910052727 yttrium Inorganic materials 0.000 claims description 3
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims description 2
- 229910052500 inorganic mineral Inorganic materials 0.000 abstract description 3
- 239000011707 mineral Substances 0.000 abstract description 3
- 239000000243 solution Substances 0.000 description 14
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 12
- 239000010936 titanium Substances 0.000 description 12
- 229910052719 titanium Inorganic materials 0.000 description 12
- 230000015572 biosynthetic process Effects 0.000 description 7
- 238000003754 machining Methods 0.000 description 6
- 238000011109 contamination Methods 0.000 description 5
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 description 3
- 239000000047 product Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 229910052729 chemical element Inorganic materials 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 229910000753 refractory alloy Inorganic materials 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000000930 thermomechanical effect Effects 0.000 description 2
- OGIDPMRJRNCKJF-UHFFFAOYSA-N titanium oxide Inorganic materials [Ti]=O OGIDPMRJRNCKJF-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000002378 acidificating effect Effects 0.000 description 1
- 239000003570 air Substances 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 239000012736 aqueous medium Substances 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 229910000420 cerium oxide Inorganic materials 0.000 description 1
- 238000009390 chemical decontamination Methods 0.000 description 1
- 229910000428 cobalt oxide Inorganic materials 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 239000007857 degradation product Substances 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000005137 deposition process Methods 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000007970 homogeneous dispersion Substances 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910000476 molybdenum oxide Inorganic materials 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 239000002105 nanoparticle Substances 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 229910001887 tin oxide Inorganic materials 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 229910000314 transition metal oxide Inorganic materials 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Classifications
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- 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
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/62222—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products obtaining ceramic coatings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- 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
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/50—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare-earth compounds
- C04B35/505—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare-earth compounds based on yttrium oxide
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- 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
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/64—Burning or sintering processes
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/082—Coating starting from inorganic powder by application of heat or pressure and heat without intermediate formation of a liquid in the layer
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3217—Aluminum oxide or oxide forming salts thereof, e.g. bauxite, alpha-alumina
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
- C04B2235/3225—Yttrium oxide or oxide-forming salts thereof
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
- C04B2235/3229—Cerium oxides or oxide-forming salts thereof
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3231—Refractory metal oxides, their mixed metal oxides, or oxide-forming salts thereof
- C04B2235/3232—Titanium oxides or titanates, e.g. rutile or anatase
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3231—Refractory metal oxides, their mixed metal oxides, or oxide-forming salts thereof
- C04B2235/3256—Molybdenum oxides, molybdates or oxide forming salts thereof, e.g. cadmium molybdate
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/327—Iron group oxides, their mixed metal oxides, or oxide-forming salts thereof
- C04B2235/3275—Cobalt oxides, cobaltates or cobaltites or oxide forming salts thereof, e.g. bismuth cobaltate, zinc cobaltite
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3284—Zinc oxides, zincates, cadmium oxides, cadmiates, mercury oxides, mercurates or oxide forming salts thereof
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3293—Tin oxides, stannates or oxide forming salts thereof, e.g. indium tin oxide [ITO]
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/34—Non-metal oxides, non-metal mixed oxides, or salts thereof that form the non-metal oxides upon heating, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3418—Silicon oxide, silicic acids or oxide forming salts thereof, e.g. silica sol, fused silica, silica fume, cristobalite, quartz or flint
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- 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
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/34—Non-metal oxides, non-metal mixed oxides, or salts thereof that form the non-metal oxides upon heating, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3427—Silicates other than clay, e.g. water glass
- C04B2235/3463—Alumino-silicates other than clay, e.g. mullite
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
- F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/40—Heat treatment
- F05D2230/42—Heat treatment by hot isostatic pressing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/174—Titanium alloys, e.g. TiAl
Definitions
- the invention relates to the general technical field of methods for manufacturing parts 2 comprising cavities, in particular methods using cores 1 for production operations by conforming.
- the invention relates to the cores 1 of refractory alloy for the processes for producing a part 2, for example a blade of a composite turbomachine fan, by isostatic compaction.
- such blades have a carbon matrix composite body and a leading edge made of titanium or a titanium alloy.
- Two sheets, intrados and extrados, previously formed, are shaped, via an isostatic hot compaction operation, around a core 1 of refractory alloy whose geometry corresponds to the desired internal geometry of the leading edge of the blade.
- the core 1 which is a reusable tool, is removed and the leading edge is machined on its outer surfaces to obtain the final geometry of the part 2.
- the shaping step is carried out via a thermomechanical cycle at high temperature, of the order of 800 ° C. to 1000 ° C., during which the core 1 is in contact with the elements of the 'dawn, and therefore from the leading edge, for several hours.
- the core 1 has three main characteristics:
- the core 1 must be non-deformable in the thermomechanical range of manufacture of the leading edge in order to ensure the shape of the internal cavity of the leading edge; this allows in particular not to machine the internal cavity of the leading edge, which simplifies the manufacturing process;
- the material making up the core 1 is chosen in order to avoid any chemical reaction between the material of the core 1 and the material of the leading edge; this makes it possible to avoid or minimize chemical decontamination of the surfaces of the internal cavity of the leading edge, which simplifies the process;
- Stop-Off type products are well known and used in hot titanium forming processes with generally the double objective of protecting the titanium against contamination of the air or tools in contact with the titanium and of facilitating the demoulding of part 2. They are systematically composed of an anti-diffusion refractory charge and an organic binder.
- the coating is "enclosed” in a sealed cavity formed by the upper and lower sheets.
- the organic binder will degrade and the degradation residues will contaminate the sheet / sheet contact areas on the periphery of the assembly and prevent diffusion welding between the two sheets, sought in these areas .
- An object of the invention is to allow the reuse of the core 1 for processes for forming several pieces 2.
- Another object of the invention is to limit the phenomenon of diffusion of species between the core and the part.
- Another object is to limit the phenomena of heat transfer between the core and the part.
- Another aim is to limit the phenomena of chemical reaction between the part and the core.
- the invention provides a method of coating a core for the manufacture of a part for a turbomachine by isostatic compaction, for example a blade leading edge shield, the coating method comprising the steps of:
- - S2 Coating of the core by means of a second solution comprising a second component configured to bond the first component so as to form a homogeneous layer, the second component comprising an inorganic binder;
- Steps S1 to S3 are repeated at least once;
- the first component comprises an oxide of a transition metal, and in which the second component comprises a colloid of a lanthanide;
- the first solution is aqueous and the first component comprises a charge of yttrium oxide in powder form;
- the second component comprises a colloid binder of cerium
- Step S3 of heat treatment is carried out at a temperature between 40 ° C and 120 ° C for a period between 15 minutes and 60 minutes, and preferably at a temperature between 70 ° C and 90 ° C for a period between 25 and 35 minutes;
- the method further comprises, between steps S1 and S2, a step S4 of heat treatment of the core;
- the solution comprises a mass proportion of water of between 40% and 60%, and a mass proportion of between 40% and 60% of metal oxide;
- the coating steps S1 and S2 are carried out simultaneously by applying a single solution comprising the first component and the second component.
- the invention provides a core for a turbomachine part, for example a blade leading edge shield, the core comprising a coating produced according to a method according to the invention.
- the invention provides a method of manufacturing a part for a turbomachine, for example a blade leading edge shield, said part comprising an internal cavity, a first sheet and a second sheet, in which the method comprises the steps of:
- one of the first sheet and the second sheet comprises a first material
- the core comprises a second material
- the first material comprising a titanium alloy
- the second material comprising a metal alloy of transition, for example of yttrium.
- FIG. 1 shows different stages of a hot shaping process of a turbomachine blade according to the invention
- Figure 1a shows the pressure sheet previously formed
- FIG. 1 b represents the lower surface sheet in which the core 1 is positioned
- FIG. 1 c represents the upper surface sheet, positioned on the core 1 itself positioned on the lower surface sheet.
- the assembly constituting the assembly to conform.
- Figure 1 d shows a section of the assembly, revealing the core 1, the lower and upper sheets being fixed to each other prior to hot forming
- Figure 1 e shows a section of the assembly, revealing the core 1 and the part 2 formed after hot shaping step
- FIG. 1 f represents the part 2 formed, with the core 1 in the cavity of the part 2
- Figure 1 g shows the final part 2 after extraction of the core 1;
- the invention relates to a method of coating a core 1 for the manufacture of a blade for a turbomachine by isostatic compacting, the coating method comprising the steps of:
- - S2 Coating of the core (1) by means of a solution comprising a second component configured to bond the first component so as to form a homogeneous layer, the second component comprising an inorganic binder;
- - S3 Application of a heat treatment to the coated core (1) so as to dry the solution and solidify the coating.
- the core 1 is thus coated with a non-permanent coating, anti-diffusion, which comprises a first component, or filler, refractory and thermodynamically very stable, anti-diffusion, non-reactive with the material of the part 2, even under temperature of l 'order of 1000 ° C, and a second component, or binder, mineral so as not to contaminate, during hot isostatic compaction, the material of part 2.
- a non-permanent coating, anti-diffusion which comprises a first component, or filler, refractory and thermodynamically very stable, anti-diffusion, non-reactive with the material of the part 2, even under temperature of l 'order of 1000 ° C, and a second component, or binder, mineral so as not to contaminate, during hot isostatic compaction, the material of part 2.
- the method can optionally include a repetition of steps S1 to S3, which makes it possible to adapt the coating thickness obtained according to the need.
- the first component has a very negative free enthalpy of formation at 25 ° C. for the formation of its oxide.
- This oxide will therefore be extremely stable.
- the free enthalpy of formation of the oxide of the component will advantageously be less than that of the titanium oxide (TiO 2), titanium being the main chemical element of the material of part 2.
- Such a coating makes it possible to avoid inter-diffusion of the species between a part 2 and the core 1, which makes it possible to greatly limit the adhesion between the part 2 and the core 1 and promotes the extraction and the reuse of the core 1 to the during a subsequent manufacturing process of a part 2.
- Such a method can in one embodiment include a step, not illustrated, of cutting and then machining of sheets intended to form the part 2.
- a first sheet comprises a sheet intended to form the lower surface of the blade
- a second sheet comprises a sheet intended to form the lower surface of the blade
- Such a process can also include a hot forming step, during which the sheets intended to form the lower and upper surfaces are stamped hot in order to give them a preform making it possible to approach the shape of the core in order to simplify the assembly of the sheets around the core.
- An assembly step is then carried out, during which the first sheet, the second sheet and the core 1 are positioned relative to each other and held together, as illustrated in FIGS. 1 a to 1c .
- the lower and upper sheets are fixed to each other, for example by welding at the side edges of said sheets, in order to guarantee the positioning of the sheets around the core and ensured the tightness of the assembly, such as 'illustrated in figure 1 d.
- An isostatic compaction step is then carried out, during which the sheets and the core are heated to a temperature of the order of 800 ° C. to 1000 ° C. and compacted by an external pressure so as to join the sheets together by diffusion welding, conform them around the core and thus form the part 2, as illustrated in FIG. 1 e, comprising an internal cavity with the exact geometry of the core.
- the part 2 formed is obtained by removing the core.
- an additional machining step can be performed, for example the machining of the leading edges in the case of a turbomachine blade.
- the machining step is carried out with the core 1 in the cavity of the part 2, as illustrated in FIG. 1 f.
- This makes it possible to stiffen the assembly, in particular avoiding deformation of the part 2 under the machining forces, and to have integrated dimensional reference frames which makes it possible to avoid having to resort to complex machining tools.
- the core 1 is then removed, as illustrated in FIG. 1 g, and can be reused during a production operation of another part 2. This makes it possible to greatly limit the unit manufacturing cost of a part 2 .
- the first component comprises an yttrium oxide and optionally another oxide chosen from one or a plurality of metal oxide powders, which can for example comprise an oxide or a combination of oxides chosen from:
- Ti02 titanium oxide
- Mo03 molybdenum oxide
- the first component notably comprises one or a combination of transition metal oxides.
- the first component comprises yttrium oxide powder (Y203). This allows, in particular when the part 2 comprises titanium or a titanium alloy, to very strongly limit, or even avoid, contamination of the titanium during a thermal cycle according to the process.
- the part 2 is made of titanium alloy.
- Figure 2 shows the free enthalpies of formation of different oxides.
- yttrium oxide appears to be the best candidate among the oxides shown, exhibiting a free enthalpy of formation much lower than the free enthalpy of formation of titanium oxide.
- Titanium being the main chemical element in part 2, yttruim oxide will be inert towards titanium.
- the second component comprises a mineral colloid in an aqueous medium.
- Colloid is understood to mean a suspension of one or more substances, regularly dispersed in another substance, forming a system with two separate phases. In a fluid, it forms a homogeneous dispersion of particles whose dimensions range from nanometer to micrometer. These particles are therefore the size of a nanoparticle, even if they are not specifically considered as such.
- the second component comprises a lanthanide colloid, for example one or a combination of colloids chosen from a yttrium colloid, a titanium colloid (basic or acidic) and a cerium colloid.
- a lanthanide colloid for example one or a combination of colloids chosen from a yttrium colloid, a titanium colloid (basic or acidic) and a cerium colloid.
- the part 2 is made of titanium alloy, and the second component comprises a colloid of cerium. This makes it possible to greatly limit, or even avoid, any contamination of part 2 by cerium.
- the solution used for the coating therefore comprises:
- the coating is deposited in two passes, the deposition process comprising:
- the first solution includes a mass proportion of water between 40% and 60%, and a mass proportion between 40% and 60% of metal oxide, preferably a mass proportion of water between 50% and 55% , and a mass proportion of between 45% and 50% of metal oxide, for example a mass proportion of water of 53% and a mass proportion of yttrium oxide (Y203) of 47%.
- the second solution includes a colloid of cerium (Ce02).
- the first heating step is carried out at a temperature between 40 ° C and 120 ° C for a period between 15 minutes and 60 minutes, preferably at a temperature between 70 ° C and 90 ° C for a period between 25 minutes and 35 minutes, for example at a temperature of 80 ° C for a period of 30 minutes.
- the second heating step is carried out at a temperature between 40 ° C and 120 ° C for a period between 15 minutes and 60 minutes, preferably at a temperature between 70 ° C and 90 ° C for a period between 25 minutes and 35 minutes, for example at a temperature of 80 ° C for a period of 30 minutes.
- the coating has a thickness of between 10m ⁇ ti and 30mm, for example 20pm. This makes it possible to isolate the core 1 from the part 2 effectively, by having a thickness which makes it possible to resist possible wear or scratches which may occur during the operations of removing the core 1 when the part 2 is formed. Such a thickness also makes it possible to avoid excessively modifying the dimensions of the core 1, and therefore of the cavity formed.
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- Engineering & Computer Science (AREA)
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- Ceramic Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Structural Engineering (AREA)
- Inorganic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- General Engineering & Computer Science (AREA)
- Powder Metallurgy (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1873943A FR3090695B1 (fr) | 2018-12-21 | 2018-12-21 | revetement pour noyau de conformage a chaud |
PCT/FR2019/053262 WO2020128398A1 (fr) | 2018-12-21 | 2019-12-20 | Revetement pour noyau de conformage a chaud |
Publications (1)
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EP3899090A1 true EP3899090A1 (fr) | 2021-10-27 |
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Application Number | Title | Priority Date | Filing Date |
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EP19848973.4A Pending EP3899090A1 (fr) | 2018-12-21 | 2019-12-20 | Revetement pour noyau de conformage a chaud |
Country Status (5)
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US (1) | US11702371B2 (fr) |
EP (1) | EP3899090A1 (fr) |
CN (1) | CN113166949A (fr) |
FR (1) | FR3090695B1 (fr) |
WO (1) | WO2020128398A1 (fr) |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5316203A (en) * | 1993-04-27 | 1994-05-31 | General Electric Company | Encapsulated stop-off coating for diffusion bonding |
FR2735055B1 (fr) * | 1995-06-08 | 1997-07-18 | Snecma | Revetement inorganique resistant a haute temperature et son utilisation dans un procede de fabrication de pieces par soudage-diffusion et formage superplastique |
FR2853572B1 (fr) * | 2003-04-10 | 2005-05-27 | Snecma Moteurs | Procede de fabrication d'une piece mecanique creuse par soudage-diffusion et formage superplastique |
US7579087B2 (en) * | 2006-01-10 | 2009-08-25 | United Technologies Corporation | Thermal barrier coating compositions, processes for applying same and articles coated with same |
US20070207330A1 (en) * | 2006-03-01 | 2007-09-06 | Sonia Tulyani | Adhesive protective coatings, non-line of sight methods for their preparation, and coated articles |
EP1850412A1 (fr) * | 2006-04-26 | 2007-10-31 | Technical University of Denmark | Un retêvement multicouche |
CN101660115B (zh) * | 2009-09-18 | 2011-08-31 | 武汉理工大学 | 纳米氧化锆热障涂层的制备方法 |
FR2957358B1 (fr) * | 2010-03-12 | 2012-04-13 | Snecma | Methode de fabrication d'une protection de barriere thermique et revetement multicouche apte a former une barriere thermique |
FR2957545B1 (fr) * | 2010-03-19 | 2012-07-27 | Snecma | Procede de realisation d'un insert metallique pour la protection d'un bord d'attaque en materiau composite |
FR2970196B1 (fr) | 2011-01-10 | 2012-12-28 | Snecma | Procede de realisation d'un renfort metallique |
FR2970668B1 (fr) | 2011-01-24 | 2013-01-18 | Snecma | Procede de realisation d'un renfort metallique |
BE1020692A3 (fr) * | 2012-05-16 | 2014-03-04 | Prayon Sa | Procede de fabrication d'un materiau composite. |
FR2991206B1 (fr) | 2012-06-01 | 2014-06-20 | Snecma | Procede de realisation d'un renfort metallique d'une aube de turbomachine |
TW201441177A (zh) * | 2013-03-14 | 2014-11-01 | Vesuvius Crucible Co | 用於耐火元件的氧化鋯系鍍膜及包含此鍍膜的耐火元件 |
CN105499499B (zh) * | 2015-12-08 | 2017-10-03 | 中国航空工业集团公司北京航空材料研究院 | 一种钛铝系金属间化合物铸件精密成型方法 |
-
2018
- 2018-12-21 FR FR1873943A patent/FR3090695B1/fr active Active
-
2019
- 2019-12-20 WO PCT/FR2019/053262 patent/WO2020128398A1/fr unknown
- 2019-12-20 EP EP19848973.4A patent/EP3899090A1/fr active Pending
- 2019-12-20 US US17/416,799 patent/US11702371B2/en active Active
- 2019-12-20 CN CN201980076818.2A patent/CN113166949A/zh active Pending
Also Published As
Publication number | Publication date |
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US20220064073A1 (en) | 2022-03-03 |
CN113166949A (zh) | 2021-07-23 |
WO2020128398A1 (fr) | 2020-06-25 |
FR3090695A1 (fr) | 2020-06-26 |
FR3090695B1 (fr) | 2020-12-04 |
US11702371B2 (en) | 2023-07-18 |
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