EP3899083A1 - Pièce de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procédé de fabrication associé - Google Patents
Pièce de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procédé de fabrication associéInfo
- Publication number
- EP3899083A1 EP3899083A1 EP19850726.1A EP19850726A EP3899083A1 EP 3899083 A1 EP3899083 A1 EP 3899083A1 EP 19850726 A EP19850726 A EP 19850726A EP 3899083 A1 EP3899083 A1 EP 3899083A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- substrate
- layer
- chromium
- platinum
- rhenium
- 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
- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 48
- 229910052702 rhenium Inorganic materials 0.000 title claims abstract description 25
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 title claims abstract description 25
- KJTLSVCANCCWHF-UHFFFAOYSA-N Ruthenium Chemical compound [Ru] KJTLSVCANCCWHF-UHFFFAOYSA-N 0.000 title claims abstract description 21
- 229910052707 ruthenium Inorganic materials 0.000 title claims abstract description 21
- 238000004519 manufacturing process Methods 0.000 title claims description 10
- 239000000758 substrate Substances 0.000 claims abstract description 60
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 claims abstract description 50
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 42
- 239000011651 chromium Substances 0.000 claims abstract description 42
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 41
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 29
- 229910052697 platinum Inorganic materials 0.000 claims abstract description 25
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 13
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 13
- 239000010410 layer Substances 0.000 claims description 64
- 238000000034 method Methods 0.000 claims description 18
- 238000000151 deposition Methods 0.000 claims description 10
- 239000011241 protective layer Substances 0.000 claims description 10
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 9
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000005240 physical vapour deposition Methods 0.000 claims description 6
- 229910052710 silicon Inorganic materials 0.000 claims description 4
- 239000010703 silicon Substances 0.000 claims description 4
- 239000000919 ceramic Substances 0.000 claims description 3
- 230000008021 deposition Effects 0.000 claims description 3
- 238000001704 evaporation Methods 0.000 claims description 3
- 230000008020 evaporation Effects 0.000 claims description 3
- 238000000608 laser ablation Methods 0.000 claims description 3
- 238000004544 sputter deposition Methods 0.000 claims description 3
- 238000007751 thermal spraying Methods 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 abstract description 9
- 239000004411 aluminium Substances 0.000 abstract 1
- 239000012071 phase Substances 0.000 description 23
- 238000009792 diffusion process Methods 0.000 description 11
- 230000003647 oxidation Effects 0.000 description 9
- 238000007254 oxidation reaction Methods 0.000 description 9
- 229910052751 metal Inorganic materials 0.000 description 7
- 239000002184 metal Substances 0.000 description 7
- 230000015572 biosynthetic process Effects 0.000 description 6
- 238000005260 corrosion Methods 0.000 description 5
- 230000007797 corrosion Effects 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 238000001878 scanning electron micrograph Methods 0.000 description 5
- 230000004888 barrier function Effects 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 230000002035 prolonged effect Effects 0.000 description 4
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 3
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 3
- 238000010517 secondary reaction Methods 0.000 description 3
- 230000009466 transformation Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 229910000943 NiAl Inorganic materials 0.000 description 2
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 229910052735 hafnium Inorganic materials 0.000 description 2
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000002244 precipitate Substances 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 238000000844 transformation Methods 0.000 description 2
- 229910001011 CMSX-4 Inorganic materials 0.000 description 1
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000002051 biphasic effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical group FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 230000035784 germination Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 229910000907 nickel aluminide Inorganic materials 0.000 description 1
- 150000003057 platinum Chemical class 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000004626 scanning electron microscopy Methods 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000004901 spalling Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000012808 vapor phase Substances 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
- C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- 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
-
- 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
- F05D2260/00—Function
- F05D2260/95—Preventing corrosion
-
- 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
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/132—Chromium
-
- 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
- F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
- F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
-
- 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
- F05D2300/175—Superalloys
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/607—Monocrystallinity
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Definitions
- the invention relates to a turbine part, such as a turbine blade or a distributor vane for example, used in aeronautics.
- the exhaust gases generated by the combustion chamber can reach high temperatures, above 1200 ° C, or even 1600 ° C.
- the parts of the turbojet engine, in contact with these exhaust gases, such as the blades turbine, for example, must be able to maintain their mechanical properties at these high temperatures.
- Superalloys are a family of high-strength metal alloys that can work at temperatures relatively close to their melting points (typically 0.7 to 0.8 times their melting temperatures).
- rhenium and / or ruthenium into a superalloy to increase its capacity for mechanical resistance, in particular to creep, at high temperature.
- the introduction of rhenium and / or ruthenium makes it possible to increase the temperature of use of these superalloys by about 100 ° C. compared to the first polycrystalline superalloys.
- the increase in the average mass fraction of rhenium and / or ruthenium in the superalloy requires a reduction in the average mass fraction of chromium in the superalloy, so as to keep a stable allotropic structure of the superalloy, in particular a y-y 'phase.
- the chromium in the superalloy promotes the formation of Cr2Ü3 oxide, having the same crystallographic structure as CI -AI2O3 and thus allowing the germination of a layer of CI -AI2O3.
- This stable CI -AI2O3 layer helps protect the superalloy against oxidation.
- the increase in the average mass fraction of rhenium and / or ruthenium consequently results in less resistance to oxidation of the superalloy compared to a superalloy devoid of rhenium and / or ruthenium.
- Figures 1 to 3 schematically illustrate a section of a turbine part 1 of the prior art, for example a turbine blade 7 or a distributor fin.
- the part 1 comprises a substrate 2 made of monocrystalline metal superalloy covered with a coating 10, for example with an environmental barrier comprising a thermal barrier.
- the environmental barrier typically comprises a sublayer, preferably a metallic sublayer 3, a protective layer and a thermally insulating layer.
- the sub-layer 3 covers the substrate 2 in metal superalloy.
- the sublayer 3 is itself covered with the protective layer, formed by oxidation of the metallic sublayer 3.
- the protective layer protects the superalloy substrate 2 from corrosion and / or oxidation.
- the thermally insulating layer covers the protective layer.
- the thermally insulating layer can be made of ceramic, for example of yttria zirconia.
- the sublayer 3 is typically made from a simple nickel aluminide B-NiAl or modified platinum B- NiAlPt.
- the average atomic aluminum fraction (between 35% and 45%) of the sublayer 3 is sufficient to exclusively form a protective layer of aluminum oxide (AI2O3) making it possible to protect the substrate 2 in superalloy against oxidation and corrosion.
- Inter-diffusion can lead to the formation of primary and secondary reaction zones (called “SRZ” or Secondary Reaction Zone in English) in a part of the substrate 2 in contact with the sublayer 3.
- FIG. 2 is a photomicrograph of the section of an underlay 3 covering a substrate 2 of a part 1.
- the microphotography is carried out before the part is subjected to a series of thermal cycles making it possible to simulate the temperature conditions of the part 1 during its use.
- Substrate 2 is rich in rhenium, that is to say that the average mass fraction of rhenium is greater than or equal to 0.04. It is known to use rhenium in the composition of superalloys to increase the creep resistance of superalloy parts.
- the substrate 2 has a y-y ’phase, and in particular a g-Ni phase.
- the sublayer 3 is of the 6- NiAlPt type.
- the substrate 2 has a primary inter-diffusion zone 5, in the part of the substrate directly covered by the sublayer 3.
- the substrate 2 also has a secondary inter-diffusion zone 6, directly covered by the primary inter-diffusion 5.
- the scale bar corresponds to a length equal to 20 ⁇ m.
- Figure 3 is a photomicrograph of the section of the sub-layer 3 covering the substrate 2 of the part 1.
- the photomicrograph shows the sublayer 3 and the substrate 2 after having subjected them to the series of thermal cycles described above.
- the sublayer 3 covers the substrate 2.
- the substrate 2 has a primary inter-diffusion zone 5 and a secondary inter-diffusion zone 6.
- the scale bar corresponds to a length equal to 20 ⁇ m.
- An object of the invention is to provide a solution for effectively protecting a superalloy turbine part from oxidation and corrosion while increasing its service life, when in use, compared to known parts.
- Another object of the invention is to limit or prevent the formation of secondary reaction zones while allowing an aluminum oxide to be formed during the use of the part.
- Another object of the invention is to at least partially prevent the formation of cracks in the substrate of a part subjected to high temperature conditions, for example above 1000 ° C. as well as the peeling of the layer protective aluminum oxide.
- a substrate in monocrystalline nickel-based superalloy comprising chromium and at least one element chosen from rhenium and ruthenium, the substrate having a y-y 'phase, an average mass fraction of rhenium and ruthenium greater than or equal to 4% and an average mass fraction of chromium less than or equal to 5% and preferably less than or equal to 3%,
- sublayer covering at least part of a surface of the substrate, the part being characterized in that the sublayer has a y-y ’phase and an average atomic fraction:
- the undercoat has exclusively a phase y-y '
- the undercoat has an average atomic fraction of silicon lower at 2%
- the sublayer has a thickness of between 5 ⁇ m and 50 ⁇ m, and preferably between 5 ⁇ m and 15 ⁇ m
- a protective layer of aluminum oxide covers the sublayer
- a thermally insulating layer of ceramic covers the protective layer in aluminum oxide.
- the invention also relates to a turbine blade comprising a part described above.
- the invention also relates to a method for manufacturing a turbine part, comprising a substrate in monocrystalline nickel-based superalloy, comprising chromium and at least one element chosen from rhenium and ruthenium, having a phase y-y ', a average mass fraction of rhenium and ruthenium greater than or equal to 4% and an average mass fraction of chromium less than or equal to 5% and preferably less than or equal to 3%, an undercoat covering at least part of a surface of the substrate, the sublayer (4) having a phase y-y 'and an average atomic fraction: in chromium between 5% and 10%, in aluminum between 10% and 20%, in platinum between 1 5% and 25%, the method comprising at least the steps consisting in: a) depositing an enrichment layer on the substrate, the enrichment layer having at least an average atomic fraction of platinum greater than 90% and an average atomic fraction of chromium co between 3% and 10%, b) heat treating the assembly formed by the substrate and the enrich
- step a) of depositing an enrichment layer at least one layer of chromium and one layer of platinum are deposited separately, the chromium layer or layers having a total thickness of between 200 nm and 2 ⁇ m and the platinum layer or layers having a total thickness of between 3 ⁇ m and 10 ⁇ m, during step a) of depositing an enrichment layer, chromium and platinum are deposited simultaneously, during step b ), the assembly formed by the substrate and the enrichment layer is heat treated at a temperature above 1000 ° C. for more than one hour, preferably for more than
- the deposition of the enrichment layer is carried out by a method chosen from a physical vapor deposition, thermal spraying, evaporation by electron gun, pulsed laser ablation and sputtering.
- FIG. 1 schematically illustrates a section of a turbine part according to the state of the art, for example a turbine blade or a distributor fin.
- Figure 2 is a scanning electron micrograph of the microstructure of a substrate and an underlay of the turbine part, before the part has been subjected to a series of thermal cycles.
- FIG. 3 is a scanning electron micrograph of the microstructure of a substrate and an undercoat of the turbine part, after the part has been subjected to a series of thermal cycles.
- Figure 4 schematically illustrates a method of manufacturing a part comprising a substrate and an undercoat, in accordance with an embodiment of the invention.
- Figure 5 is a scanning electron micrograph of a substrate and an undercoat of the part, before the part has been subjected to a series of thermal cycles.
- Figure 6 is a scanning electron micrograph of a substrate and an undercoat of the part, before the part has been subjected to a series of thermal cycles.
- superalloy designates an alloy having, at high temperature and high pressure, very good resistance to oxidation, corrosion, creep and to cyclic stresses (in particular mechanical or thermal).
- superalloys find a particular application in the manufacture of parts used in aeronautics, for example turbine blades, because they constitute a family of high resistance alloys which can work at temperatures relatively close to their melting points (typically 0 , 7 to 0.8 times their melting temperatures).
- a superalloy may have a biphasic microstructure comprising a first phase (called phase y) forming a matrix, and a second phase (called phase y ’) forming precipitates hardening in the matrix.
- phase y a first phase
- phase y a second phase
- the coexistence of these two phases is designated by phase y- y ’.
- the base of the superalloy designates the main metal component of the matrix. In the majority of cases, the superalloys comprise an iron, cobalt or nickel base, but also sometimes a titanium or aluminum base.
- the base of the superalloy is preferably a nickel base.
- the nickel-based superalloys have the advantage of offering a good compromise between resistance to oxidation, high tensile strength temperature and weight, which justifies their use in the hottest parts of turbojets.
- Phase g ’ has an ordered L12 structure, derived from the face-centered cubic structure, consistent with the matrix, that is to say having an atomic mesh very close to it.
- phase g Due to its orderly nature, phase g ’has the remarkable property of having a mechanical resistance which increases with temperature up to approximately 800 ° C.
- a superalloy is, in all of the embodiments of the invention, rich in rhenium and or in ruthenium, that is to say that the average mass fraction of rhenium and in ruthenium of the superalloy is greater than or equal to 4 3 ⁇ 4, making it possible to increase the creep resistance of superalloy parts compared to superalloy parts without rhenium.
- a superalloy is also, in all of the embodiments of the invention, low in chromium on average, that is to say that the average mass fraction in the whole of the superalloy in chromium is less than 0.05 , preferably less than 0.03.
- the depletion of chromium during enrichment in rhenium and / or ruthenium of the superalloy makes it possible to keep a stable allotropic structure of the superalloy, in particular a g-g ’phase.
- atomic fraction refers to the molar fraction, that is, the ratio of the amount of material in an element or group of elements to the total amount.
- mass fraction refers to the ratio of the mass of an element or group of elements to the total mass.
- FIG. 4 illustrates a method of manufacturing a part 1, comprising a substrate 2 and a sublayer 4.
- the substrate 2 used is of the CMSX-4 plus type (registered trademark) and has the chemical composition, in average atomic fraction , described in Table 1.
- an enrichment layer 1 1 is deposited on the substrate 2.
- the enrichment layer 1 1 has at least an average atomic fraction of platinum greater than 90% and an average atomic fraction of chromium between 3% and 10%.
- the enrichment layer 1 1 comprises at least chromium and platinum, and preferably chromium, platinum, hafnium and silicon.
- the enrichment layer 1 1 does not include nickel. The different elements of the enrichment layer 1 1 can be combined.
- the various elements of the enrichment layer 1 1 can be deposited simultaneously.
- the enrichment layer 11 may also include several superimposed layers: each element can be deposited separately.
- at least one layer of platinum and at least one layer of chromium can be deposited separately.
- the chromium layer or layers have a total thickness of between 200 nm and 2 ⁇ m and the platinum layer or layers having a total thickness of between 3 ⁇ m and 10 ⁇ m.
- the quantity of metals diffused during the process according to an embodiment of the invention is optimized.
- the deposition of the layer or layers forming the enrichment layer 1 1 can be carried out under vacuum, for example by vapor phase (PVD process, acronym of the English term "Physical Vapor Deposition”).
- PVD process acronym of the English term "Physical Vapor Deposition”
- Different methods of PVD can be used for the manufacture of the enrichment layer 1 1, such as sputtering, electron gun evaporation, laser ablation and physical vapor deposition assisted by electron beam.
- the enrichment layer 11 can also be deposited by thermal spraying.
- the assembly formed by the substrate 2 and the enrichment layer 11 is heat treated, so that the enrichment layer 11 diffuses at least partially into the substrate 2.
- a sublayer 4 is formed on the surface of the substrate 2.
- the heat treatment is preferably carried out for more than one hour at a temperature between 1000 ° C and 1200 ° C, preferably for more than two hours at a temperature between 1000 ° C and 1200 ° C, and even more preferably substantially four hours at a temperature between 1050 ° C and 1150 ° C.
- a sufficient quantity of platinum and chromium is deposited during step 401, so that, after step 402 of heat treatment, the average atomic fraction of platinum in the sublayer 4 is between 15% and 25%, and so that the average atomic fraction of chromium in the sublayer 4 is greater than 5% and preferably between 5% and 20%.
- the amount of platinum and chromium deposited in the enrichment layer 11 is therefore higher the lower the atomic molar fraction of chromium and platinum in the substrate 2, which is typically the case for an enriched substrate 2 rhenium and / or ruthenium.
- the thickness of the enrichment layer 11 is preferably between 100 nm and 20 ⁇ m.
- FIG. 5 is a scanning electron microscopy photograph of the microstructure of a substrate 2 and a sublayer 4 of a part 1.
- the sublayer 4 is produced by the process illustrated in FIG. 4, in which is deposited an enrichment layer 11 comprising only chromium and platinum, during step 401 of the process.
- the scale bar of FIG. 5 corresponds to a length equal to 20 ⁇ m.
- the sublayer 4 generally has a phase yy 'and an average atomic fraction of chromium greater than 5%, preferably between 5% and 20%, aluminum between 10% and 20%, platinum between 15% and 25%.
- sublayer 4 has an average atomic fraction of chromium substantially equal to 5.8%, an average atomic fraction of aluminum substantially equal to 1 1%, an average atomic fraction of platinum substantially equal to 21%, an atomic fraction hafnium average less than 0.5% and an average silicon atomic fraction less than 1%.
- the sub-layer 4 preferably has exclusively a y-y 'phase. Indeed, the introduction of elements into the substrate 2 by the enrichment method described above makes it possible not to cause phase transition of the substrate 2, and thus to avoid mechanical stresses in the substrate 2 which could cause the appearance of cracks 8.
- a substantially horizontal line divides the sublayer 4 into two superimposed parts: this line corresponds to the limit between the substrate 2 and the enrichment layer 11 before the heat treatment step 402 during the manufacture of a part 1.
- the thickness of the sublayer 4 is typically between 1 ⁇ m and 100 ⁇ m, and preferably between 5 ⁇ m and 50 ⁇ m.
- the average atomic fraction of chromium in sublayer 4 makes it possible to promote the formation of a-AhCh when the part is used under working conditions.
- FIG. 6 is a scanning electron micrograph photograph of a part 1 comprising the substrate 2 and the sublayer 4, after the prolonged heat treatment. During the prolonged heat treatment, the part 1 is placed in air for 100 hours at 1050 ° C. and then for 10 hours at 1150 ° C. No crack 8 is detectable in the substrate 2 after the prolonged heat treatment.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Organic Chemistry (AREA)
- Metallurgy (AREA)
- Inorganic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Physical Vapour Deposition (AREA)
- Composite Materials (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1873972A FR3090696B1 (fr) | 2018-12-21 | 2018-12-21 | Piece de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procede de fabrication associe |
PCT/FR2019/053254 WO2020128394A1 (fr) | 2018-12-21 | 2019-12-20 | Pièce de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procédé de fabrication associé |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3899083A1 true EP3899083A1 (fr) | 2021-10-27 |
Family
ID=67107595
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19850726.1A Pending EP3899083A1 (fr) | 2018-12-21 | 2019-12-20 | Pièce de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procédé de fabrication associé |
Country Status (5)
Country | Link |
---|---|
US (1) | US11873736B2 (fr) |
EP (1) | EP3899083A1 (fr) |
CN (1) | CN113242913A (fr) |
FR (1) | FR3090696B1 (fr) |
WO (1) | WO2020128394A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3102775B1 (fr) * | 2019-11-05 | 2022-04-22 | Safran | Piece d'aeronef en superalliage comprenant un canal de refroidissement |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4526814A (en) * | 1982-11-19 | 1985-07-02 | Turbine Components Corporation | Methods of forming a protective diffusion layer on nickel, cobalt, and iron base alloys |
EP0718420B1 (fr) * | 1994-12-24 | 1999-04-21 | Rolls Royce Plc | Revêtement de barrière thermique et méthode pour l'appliquer sur un article en superalliage |
US6066405A (en) * | 1995-12-22 | 2000-05-23 | General Electric Company | Nickel-base superalloy having an optimized platinum-aluminide coating |
EP0846788A1 (fr) * | 1996-12-06 | 1998-06-10 | Siemens Aktiengesellschaft | Substrat à base de superalliage pourvu d'un revêtement d'enrichissement et méthodes de sa fabrication |
US6475642B1 (en) * | 2000-08-31 | 2002-11-05 | General Electric Company | Oxidation-resistant coatings, and related articles and processes |
US6497920B1 (en) * | 2000-09-06 | 2002-12-24 | General Electric Company | Process for applying an aluminum-containing coating using an inorganic slurry mix |
US7157151B2 (en) * | 2002-09-11 | 2007-01-02 | Rolls-Royce Corporation | Corrosion-resistant layered coatings |
US20100151125A1 (en) * | 2003-08-04 | 2010-06-17 | General Electric Company | Slurry chromizing process |
EP1524334A1 (fr) * | 2003-10-17 | 2005-04-20 | Siemens Aktiengesellschaft | Couche protectrice pour proteger un élément structurel contre la corrosion et l'oxydation aux temperatures hautes et élément structurel |
ATE433502T1 (de) * | 2004-08-18 | 2009-06-15 | Univ Iowa State Res Found Inc | Hochtemperaturbeschichtungen und massivlegierungen aus -ni+ '-ni3al-legierungen, die mit einer aus der pt gruppe modifiziert sind, und die einer hochtemperaturkorrosionsbeständigkeit aufweisen |
US7229701B2 (en) * | 2004-08-26 | 2007-06-12 | Honeywell International, Inc. | Chromium and active elements modified platinum aluminide coatings |
US20060093849A1 (en) * | 2004-11-02 | 2006-05-04 | Farmer Andrew D | Method for applying chromium-containing coating to metal substrate and coated article thereof |
US7531217B2 (en) * | 2004-12-15 | 2009-05-12 | Iowa State University Research Foundation, Inc. | Methods for making high-temperature coatings having Pt metal modified γ-Ni +γ′-Ni3Al alloy compositions and a reactive element |
US7247393B2 (en) * | 2005-09-26 | 2007-07-24 | General Electric Company | Gamma prime phase-containing nickel aluminide coating |
EP1870485A1 (fr) * | 2006-06-22 | 2007-12-26 | Siemens Aktiengesellschaft | Composition et méthode de métallisation d'un composant |
US7846243B2 (en) * | 2007-01-09 | 2010-12-07 | General Electric Company | Metal alloy compositions and articles comprising the same |
US20100159136A1 (en) * | 2008-12-19 | 2010-06-24 | Rolls-Royce Corporation | STATIC CHEMICAL VAPOR DEPOSITION OF y-Ni + y'-Ni3AI COATINGS |
GB2511768A (en) * | 2013-03-12 | 2014-09-17 | Rolls Royce Plc | Erosion Resistant Coating |
US9587302B2 (en) * | 2014-01-14 | 2017-03-07 | Praxair S.T. Technology, Inc. | Methods of applying chromium diffusion coatings onto selective regions of a component |
-
2018
- 2018-12-21 FR FR1873972A patent/FR3090696B1/fr active Active
-
2019
- 2019-12-20 CN CN201980085289.2A patent/CN113242913A/zh active Pending
- 2019-12-20 WO PCT/FR2019/053254 patent/WO2020128394A1/fr unknown
- 2019-12-20 EP EP19850726.1A patent/EP3899083A1/fr active Pending
- 2019-12-20 US US17/415,082 patent/US11873736B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3090696B1 (fr) | 2020-12-04 |
CN113242913A (zh) | 2021-08-10 |
US20220065111A1 (en) | 2022-03-03 |
FR3090696A1 (fr) | 2020-06-26 |
WO2020128394A1 (fr) | 2020-06-25 |
US11873736B2 (en) | 2024-01-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3532648B1 (fr) | Superalliage a base de nickel, aube monocristalline et turbomachine. | |
FR2503189A1 (fr) | Composition de revetement pour superalliages resistant a l'oxydation a haute temperature et superalliages revetus de cette composition | |
EP3601634B1 (fr) | Piece de turbine en superalliage et procede de fabrication associe | |
FR2718464A1 (fr) | Article en super alliage ayant un revêtement de barrière thermique et sa fabrication. | |
WO2020128394A1 (fr) | Pièce de turbine en superalliage comprenant du rhenium et/ou du ruthenium et procédé de fabrication associé | |
EP3698020B1 (fr) | Pièce de turbine en superalliage comprenant du rhénium et procédé de fabrication associé | |
EP3685018B1 (fr) | Pièce de turbine en superalliage comprenant du rhénium et/ou du ruthénium et procédé de fabrication associé | |
WO2012146864A1 (fr) | Pièce comportant un revêtement sur un substrat métallique en superalliaae, le revêtement comprenant une sous-couche métallique | |
EP3532653B1 (fr) | Pièce comprenant un substrat en superalliage monocristallin à base de nickel et son procédé de fabrication | |
FR3113255A1 (fr) | Protection contre l’oxydation ou la corrosion d’une pièce creuse en superalliage | |
FR2924129A1 (fr) | Procede pour realiser un revetement d'aluminiure de nickel modifie platine monophase | |
WO2021089945A1 (fr) | Piece d'aeronef en superalliage comprenant un canal de refroidissement | |
EP4041930A1 (fr) | Piece d'aeronef en superalliage comprenant du rhenium et/ou du ruthenium et procede de fabrication associe | |
WO2024023428A1 (fr) | Procede d'application de revetement et aube de turbine avec revetement applique suivant ce procede | |
EP4192635A1 (fr) | Protection contre l'oxydation ou la corrosion d'une piece creuse en superalliage | |
FR2999611A1 (fr) | Procede de fabrication d'un revetement et piece thermomecanique en superalliage comprenant un revetement obtenu selon ce procede |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
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: 20210622 |
|
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 |
|
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: 20240321 |