WO2018078246A1 - Pièce comprenant un substrat en superalliage monocristallin à base de nickel et son procédé de fabrication - Google Patents
Pièce comprenant un substrat en superalliage monocristallin à base de nickel et son procédé de fabrication Download PDFInfo
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- WO2018078246A1 WO2018078246A1 PCT/FR2017/052880 FR2017052880W WO2018078246A1 WO 2018078246 A1 WO2018078246 A1 WO 2018078246A1 FR 2017052880 W FR2017052880 W FR 2017052880W WO 2018078246 A1 WO2018078246 A1 WO 2018078246A1
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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
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
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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
- 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
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/08—Oxides
- C23C14/081—Oxides of aluminium, magnesium or beryllium
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
- C23C14/165—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon by cathodic sputtering
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/34—Sputtering
- C23C14/3407—Cathode assembly for sputtering apparatus, e.g. Target
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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
- 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
- C23C28/02—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 only coatings only including layers of metallic material
- C23C28/021—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 only coatings only including layers of metallic material including at least one metal alloy layer
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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
- 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
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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
- 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
- C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
- C23C28/42—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by the composition of the alternating layers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/04—4 layers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2250/00—Layers arrangement
- B32B2250/05—5 or more layers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2255/00—Coating on the layer surface
- B32B2255/06—Coating on the layer surface on metal layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2255/00—Coating on the layer surface
- B32B2255/20—Inorganic coating
- B32B2255/205—Metallic coating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
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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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/34—Sputtering
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- Part comprising a monocrystalline superalloy substrate based on nickel and its manufacturing method.
- the invention is in the field of monocrystalline superalloys based on nickel.
- the present invention more specifically relates to a method of manufacturing a part comprising a nickel-based monocrystalline superalloy substrate, as well as a part comprising a monocrystalline superalloy substrate based on nickel.
- superalloys complex alloys having, at high temperature and high pressure, very good resistance to oxidation, corrosion, creep and cyclic stresses (especially mechanical or thermal). These superalloys find particular application in the manufacture of parts used in aeronautics, for example turbine blades.
- a nickel-based monocrystalline superalloy substrate which comprises successively from the inside to the outside: a nickel-based monocrystalline superalloy substrate, one or more sublayer (s) and a thermal barrier.
- FIG. 1 we can see a schematic representation in section of an example of such a room.
- This comprises successively a nickel-based monocrystalline superalloy substrate A, an underlayer B of an alloy selected from NiAlPt, MCrAlY with M equal to Co and / or Ni, a layer C of an oxide, for example alumina and finally a thermal barrier D.
- the aforementioned part is for example a turbine blade, used at temperatures between 800 ° C and 1600 ° C, it is found that interdiffusion is important between the superalloy of the substrate and the different layers that cover it, because of their differences in chemical compositions.
- the aluminum of the underlayer B may diffuse to the substrate A or titanium of the substrate may diffuse to the sub-layer B.
- the diffusion flux associated with this phenomenon may have different consequences.
- the aforementioned flows cause the premature depletion of the alumina layer C, which favors the martensitic transformation of the sublayer B (phase 6-NiAl transformed into ⁇ '- ⁇ ' 3 ⁇ phase). These transformations generate cracks and promote flaking of the oxide layer.
- This diffusion barrier is constituted for example by a dense layer of alumina or a rhenium-based alloy and it has been observed that that the diffusion of certain elements of the superalloy of the substrate A (such as titanium or sulfur for example) is slowed down in this diffusion barrier.
- this diffusion barrier reduces the thermal fatigue resistance of the part, given the differences in coefficients of thermal expansion between the diffusion barrier, the underlayer B and the substrate A.
- the initiation of cracks is accentuated at the level of the diffusion barrier during mechanical fatigue stresses.
- the object of the invention is therefore to propose a technical solution for obtaining a nickel-based monocrystalline superalloy substrate covered with a coating and with a layer of alumina, and this:
- Another object of the invention is to improve the adhesion between the alumina layer and the thermal barrier.
- the invention relates to a method for manufacturing a part comprising a monocrystalline superalloy substrate based on nickel.
- this method comprises the steps of:
- a coating comprising at least one layer of a first type comprising aluminum and platinum, at least one layer of a second type comprising aluminum, silicon and platinum and a layer a third type comprising nickel, aluminum, silicon and platinum, this layer of third type being situated furthest outside the layer stack of the coating, forming a layer of silicon-doped alumina on said layer of the third type.
- the different layers of the coating limit the interdiffusion phenomena between the superalloy of the substrate and the alumina layer, and without degrading the mechanical properties of these superalloys.
- the silicon diffuses into the alumina layer, which thus constitutes an effective diffusion barrier with respect to the oxygen of the external atmosphere.
- said coating comprises at least three layers of the first type
- said coating comprises two layers of the second type
- said coating comprises a succession of layers of the first type and / or a succession of layers of the second type
- the layer in contact with the nickel-based monocrystalline superalloy substrate is a layer of the first type
- At least one of the layers of the first type layer, the second type layer and the third type layer is formed:
- the deposition of the different layers of the coating is carried out by physical vapor deposition or by chemical vapor deposition;
- the deposition of the different layers of the coating is carried out by sputtering.
- the invention also relates to a part comprising a monocrystalline superalloy substrate based on nickel.
- the part comprises successively on said substrate, a coating coated with a silicon doped alumina layer, said coating comprising at least one layer of a first type comprising aluminum and platinum, at at least one layer of a second type comprising aluminum, silicon and platinum and a layer of a third type comprising nickel, aluminum, silicon and platinum, this layer of the third type being located more on the outside of the stack of layers of the coating.
- said silicon-doped alumina layer is covered with a thermal barrier.
- FIG. 1 is a diagrammatic cross-sectional view of a piece according to the state of the art comprising a nickel-based monocrystalline superalloy substrate covered with several layers, and
- FIG. 2 is a diagrammatic sectional view of a substrate covered with a coating according to one embodiment of the invention
- FIG. 3 is a diagrammatic sectional view of a substrate covered with a coating according to another embodiment of the invention.
- FIG. 4 is a diagrammatic and sectional view of the detail of the various layers deposited to form the coating of the substrate according to a particular embodiment
- - Figure 5 is a schematic sectional view of two embodiments of a part according to the invention.
- the finished part, referenced 1 comprises a substrate 2, covered with a multilayer coating 3, itself covered with a layer of alumina 4.
- the alumina layer 4 is covered with a thermal barrier layer 5.
- the finished part is then referenced 1 '.
- the substrate 2 is made of a monocrystalline superalloy based on nickel.
- This substrate is for example obtained by casting or by additive manufacturing and has the desired final shape, for example that of a turbine blade.
- superalloys that may be used for the manufacture of the substrate 2 those mentioned in Table 1 below. They are identified by the letters A to F. Other monocrystalline superalloys based on nickel can also be used.
- the coating 3 formed on the substrate 2 comprises at least one layer 30 comprising aluminum and platinum, called a “layer of a first type", at least one layer 31 comprising aluminum, silicon and platinum, called “layer of a second type” and a layer 32 comprising nickel, aluminum, silicon and platinum, called “layer of a third type”.
- the third type layer 32 is located furthest outside the stack of layers of the coating 3. In other words, it is the furthest away from the substrate 2.
- the coating 3 comprises at least three layers of the first type. Also preferably, the coating 3 comprises two layers of second type 31. The different layers 30 and 31 can be alternated but this is not mandatory.
- the coating 3 comprises three successive first-type layers and then two successive second-type layers 31 and finally a third-type layer 32.
- the layer in contact with the substrate 2 is a layer of the first type 30.
- the various layers constituting the coating 3 are made on the same deposition frame. They can be deposited by various physical vapor deposition (PVD) or chemical vapor deposition (CVD) processes.
- PVD physical vapor deposition
- CVD chemical vapor deposition
- Physical vapor deposition includes the use of electron beam electron beam (EBPVD) physical vapor deposition, evaporation, pulsed laser ablation or sputtering. cathode. This last technique is preferably used. It has the advantage of allowing the formation of dense films, of a nanometric or micrometric thickness and which have an adhesion on the previous layer greater than that obtained with the other deposition techniques.
- EBPVD electron beam electron beam
- CVD chemical vapor deposition
- PECVD plasma-enhanced chemical vapor deposition
- LPCVD low pressure chemical vapor deposition
- platinum deposition can be done only by PVD deposition or electrodeposition.
- 30, 31, 32 of the coating 3 is formed by co-depositing the various chemical elements constituting this layer.
- This co-deposit can thus be carried out for example from a single allied target comprising the various constituent chemical elements of said layer to be formed.
- a single allied target comprising the various constituent chemical elements of said layer to be formed.
- an alloy target comprising aluminum, platinum and silicon can be used.
- This co-deposit can also be carried out for example from several different targets each comprising one of the constituent chemical elements of the layer to be formed.
- targets can be used simultaneously, namely an aluminum target, a nickel target, a silicon target and a platinum (or chromium) target.
- this technique makes it possible to obtain the layers 30, 31 and 32 in the form of alloys (respectively an Al / Pt alloy for the first-type layer 30, an Al / Pt alloy / Si for the second type layer 31 and an Al / Pt / Si / Ni alloy for the third type layer 32.
- a nanocrystalline platinum layer 301 is deposited, and then a nanocrystalline aluminum layer 302 or vice versa.
- a nanocrystalline layer of aluminum 302 is deposited in any order, a nanocrystalline layer of aluminum 302, a nanocrystalline layer of platinum 301 and a nanocrystalline layer of silicon 310.
- a nanocrystalline layer of aluminum 302 is deposited in any order, a nanocrystalline layer of platinum 301, a nanocrystalline layer of nickel 303 and a nanocrystalline layer of silicon 320.
- nanocrystalline means that the crystals (grains) that constitute these layers of polycrystalline material are of a size less than 1 micrometer (1 ⁇ ).
- the two silicon layers 310, 320 have a thickness of less than 100 nm.
- the layer 303 of nickel has a thickness of less than 100 nm.
- the layers 301 of platinum and / or the layers 302 of aluminum have a thickness of less than 1 micrometer (1 ⁇ ⁇ ).
- a diffusion treatment is carried out by heating at a temperature of preferably between 200 ° C. and 1200 ° C.
- the layer of alumina 4 is then formed on the layer of the third type 32.
- the substrate 2 coated with the coating 3 is preferably subjected to a thermal treatment under partial pressure of oxygen. or oxygen and argon.
- this heat treatment comprises a step of raising the temperature to a temperature of between 900 ° C. and 1200 ° C., a step of maintaining this temperature for less than one hour and a cooling step up to to reach the ambient temperature.
- the thermal barrier 5 is deposited on the alumina layer 4.
- This thermal barrier is for example a zirconia ytria layer or an alternation of at least one yttria-containing zirconia layer (containing yttrium) and at least one ceramic layer.
- said thermal barrier 5 is deposited by physical vapor deposition electron beam (EBPVD).
- the layers 301 of platinum and 302 of aluminum are nanocrystalline, which makes it possible to increase the total surface of the grain boundaries, which thus form a good diffusion barrier, in order to limit interdiffusions between the superalloy of the substrate 2 and its coating 3.
- the grain boundaries of these platinum and aluminum layers also limit the corrosion and oxidation of the substrate 2.
- the coating 3 comprises very many layers is the multiplication of the number of interfaces. These interfaces are potential paths for blocking oxygen and other metals and thus limit the interdiffusion phenomena between the substrate 2 and the alumina layer 4.
- the multilayer coating 3 thus increases the toughness of the assembly. from room 1 or 1 '.
- Another advantage of a multilayer coating 3 lies in its wear mechanism. At each interface between two successive layers, there are compression and tension constraints. Thus the cracks that may appear propagate preferentially along the interfaces rather than perpendicular to the layers. Due to the large number of interfaces, the life of the part 1 or 1 'is increased.
- the multiplication of the layers of the coating 3 makes it possible, on the one hand, to combine different types of coating material and, on the other hand, to increase the overall tightness of the coating 3 in the event of failure and / or cracking of the coating material. some of its layers.
- each layer 31, 32 which contains silicon has a very particular role.
- Part of the silicon of the third type layer 32 diffuses firstly into the grain boundaries of the contiguous layer of alumina 4 and secondly into the other layer which is contiguous thereto, namely the layer aluminum 302 or the platinum layer 301 in the order in which they were deposited.
- the silicon in the grain boundaries of the alumina reacts with the gases. hot products in the combustion chamber of the aircraft, such as oxygen and / or nitrogen to form silicon oxide (SiO 2 ) and / or silicon nitride (Si 3 N 4 ).
- This silicon oxide and this nitride constitute a very effective diffusion barrier with respect to oxygen because their diffusion coefficients are relatively low.
- the silicon By diffusing in the grain boundaries of the alumina layer 4, the silicon thus brakes the oxidation of the alumina layer, increases the lifetime thereof and thus the service life of the whole of the room 1, 1 '.
- the silicon of the second type of layer 31 serves for its silicon reservoir of the third type of layer 32, in the case where it would be completely consumed. When there are several layers 31, the silicon of these plays the same role.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Inorganic Chemistry (AREA)
- Ceramic Engineering (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Physical Vapour Deposition (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Chemical Vapour Deposition (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2019521819A JP7057778B2 (ja) | 2016-10-27 | 2017-10-19 | ニッケル基単結晶超合金基材を含む部品およびその製造方法 |
EP17794020.2A EP3532653B1 (fr) | 2016-10-27 | 2017-10-19 | Pièce comprenant un substrat en superalliage monocristallin à base de nickel et son procédé de fabrication |
BR112019008297-2A BR112019008297B1 (pt) | 2016-10-27 | 2017-10-19 | Processo para fabricar uma peça que compreende um substrato de superliga de cristal único à base de níquel e peça que compreende um substrato de superliga de cristal único à base de níquel |
RU2019115879A RU2738628C2 (ru) | 2016-10-27 | 2017-10-19 | Деталь с подложкой из монокристаллического суперсплава на основе никеля и способ её изготовления |
CA3040769A CA3040769A1 (fr) | 2016-10-27 | 2017-10-19 | Piece comprenant un substrat en superalliage monocristallin a base de nickel et son procede de fabrication |
US16/345,189 US10982333B2 (en) | 2016-10-27 | 2017-10-19 | Part comprising a nickel-based monocrystalline superalloy substrate and method for manufacturing same |
CN201780066439.6A CN109891001B (zh) | 2016-10-27 | 2017-10-19 | 包括镍基单晶超合金基板的部件及其制造方法 |
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FR1660417 | 2016-10-27 | ||
FR1660417A FR3058164B1 (fr) | 2016-10-27 | 2016-10-27 | Piece comprenant un substrat en superalliage monocristallin a base de nickel et son procede de fabrication. |
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WO2018078246A1 true WO2018078246A1 (fr) | 2018-05-03 |
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PCT/FR2017/052880 WO2018078246A1 (fr) | 2016-10-27 | 2017-10-19 | Pièce comprenant un substrat en superalliage monocristallin à base de nickel et son procédé de fabrication |
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US (1) | US10982333B2 (fr) |
EP (1) | EP3532653B1 (fr) |
JP (1) | JP7057778B2 (fr) |
CN (1) | CN109891001B (fr) |
CA (1) | CA3040769A1 (fr) |
FR (1) | FR3058164B1 (fr) |
RU (1) | RU2738628C2 (fr) |
WO (1) | WO2018078246A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3081883A1 (fr) * | 2018-06-04 | 2019-12-06 | Safran | Superalliage a base de nickel, aube monocristalline et turbomachine |
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EP1191125A1 (fr) * | 2000-09-25 | 2002-03-27 | Snecma Moteurs | Procédé de réalisation d'un revêtement de barrière thermique |
EP1528118A2 (fr) * | 2003-10-28 | 2005-05-04 | Sneca Moteurs | Pièce de turbine à gaz muni d'un revêtement de protection et procédé de sa réalisation |
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US5989733A (en) * | 1996-07-23 | 1999-11-23 | Howmet Research Corporation | Active element modified platinum aluminide diffusion coating and CVD coating method |
US6533875B1 (en) * | 2000-10-20 | 2003-03-18 | General Electric Co. | Protecting a surface of a nickel-based article with a corrosion-resistant aluminum-alloy layer |
SG127768A1 (en) * | 2005-05-27 | 2006-12-29 | Turbine Overhaul Services Priv | Thermal barrier coating |
US7527877B2 (en) | 2006-10-27 | 2009-05-05 | General Electric Company | Platinum group bond coat modified for diffusion control |
CN101358351A (zh) * | 2008-09-19 | 2009-02-04 | 昆明贵金属研究所 | 一种高温合金用纳米铂铝抗氧化涂层的制备方法 |
FR2941963B1 (fr) * | 2009-02-10 | 2011-03-04 | Snecma | Methode de fabrication d'une barriere thermique recouvrant un substrat metallique en superalliage et piece thermomecanique resultant de cette methode de fabrication |
EP2435595B1 (fr) * | 2009-05-26 | 2020-07-29 | Siemens Aktiengesellschaft | Système de revêtement stratifié présentant une couche de mcralx et une couche riche en chrome, ainsi que procédé pour sa production |
EP2557201A1 (fr) * | 2011-08-09 | 2013-02-13 | Siemens Aktiengesellschaft | Alliage, couche de protection et composant |
-
2016
- 2016-10-27 FR FR1660417A patent/FR3058164B1/fr active Active
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2017
- 2017-10-19 EP EP17794020.2A patent/EP3532653B1/fr active Active
- 2017-10-19 CN CN201780066439.6A patent/CN109891001B/zh active Active
- 2017-10-19 CA CA3040769A patent/CA3040769A1/fr active Pending
- 2017-10-19 JP JP2019521819A patent/JP7057778B2/ja active Active
- 2017-10-19 US US16/345,189 patent/US10982333B2/en active Active
- 2017-10-19 RU RU2019115879A patent/RU2738628C2/ru active
- 2017-10-19 WO PCT/FR2017/052880 patent/WO2018078246A1/fr unknown
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1191125A1 (fr) * | 2000-09-25 | 2002-03-27 | Snecma Moteurs | Procédé de réalisation d'un revêtement de barrière thermique |
EP1528118A2 (fr) * | 2003-10-28 | 2005-05-04 | Sneca Moteurs | Pièce de turbine à gaz muni d'un revêtement de protection et procédé de sa réalisation |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3081883A1 (fr) * | 2018-06-04 | 2019-12-06 | Safran | Superalliage a base de nickel, aube monocristalline et turbomachine |
WO2019234345A1 (fr) * | 2018-06-04 | 2019-12-12 | Safran | Superalliage a base de nickel, aube monocristalline et turbomachine |
US11396686B2 (en) | 2018-06-04 | 2022-07-26 | Safran | Nickel-based superalloy, single-crystal blade and turbomachine |
Also Published As
Publication number | Publication date |
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BR112019008297A2 (pt) | 2019-07-09 |
EP3532653A1 (fr) | 2019-09-04 |
CN109891001A (zh) | 2019-06-14 |
CA3040769A1 (fr) | 2018-05-03 |
US20190284703A1 (en) | 2019-09-19 |
EP3532653B1 (fr) | 2023-03-15 |
JP2019536905A (ja) | 2019-12-19 |
FR3058164B1 (fr) | 2020-02-07 |
RU2019115879A (ru) | 2020-11-27 |
JP7057778B2 (ja) | 2022-04-20 |
FR3058164A1 (fr) | 2018-05-04 |
US10982333B2 (en) | 2021-04-20 |
RU2738628C2 (ru) | 2020-12-15 |
RU2019115879A3 (fr) | 2020-11-27 |
CN109891001B (zh) | 2021-01-05 |
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