# US 11,306,599 B2 · Turbine component made from superalloy and associated manufacturing method > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,306,599 B2 - Document ID: US11306599B2 - Status: Granted - Kind: B2 - Application number: 16/498,836 - Filed: 2018-03-30 - Published: 2021-03-04 - Granted: 2022-04-19 - Earliest claimed: 2017-03-30 - Assignees: Safran - Applicants: Safran - Inventors: Amar Saboundji; Virginie Jaquet - Web page: https://patentgrep.com/patent/US11306599B2 ## CPC - F01D 5/288: {Protective coatings for blades} - C23C 14/027: {Graded interfaces} - C23C 14/16: on metallic substrates or on substrates of boron or silicon - C23C 28/321: {with at least one metal alloy layer} - C23C 28/3455: {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} - C23C 28/36: {including layers graded in composition or physical properties} - F05D 2300/132: Chromium - F05D 2300/143: Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd - F05D 2300/175: Superalloys - F05D 2300/2281: of aluminium - F05D 2300/607: Monocrystallinity - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 (making metal-coated products by extrusion B21C23/22; covering with metal by connecting pre-existing layers to articles, see the relevant places, e.g. B21D39/00, B23K; metallising of glass C03C; metallising mortars, concrete, artificial stone, ceramics or natural stone C04B41/00; enamelling of, or applying a vitreous layer to, metals C23D; treating metal surfaces or coating of metals by electrolysis or electrophoresis C25D; single-crystal film growth C30B; by metallising textiles D06M11/83; decorating textiles by locally metallising D06Q1/04) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract The invention concerns a turbine component, such as a turbine blade or a distributor fin, for example, comprising a substrate made from single-crystal nickel superalloy, and a metal sublayer covering the substrate, characterised in that the metal sublayer comprises at least two elementary layers, including a first elementary layer and a second elementary layer, the first elementary layer being arranged between the substrate and the second elementary layer, each elementary layer comprising a γ′-Ni3Al phase, and optionally a γ-Ni phase, and in that the average atomic fraction of aluminum in the second elementary layer is strictly greater than the average atomic fraction of aluminum in the first elementary layer. ## Claims ### Claim 1 A turbine component comprising: a single-crystal nickel-based superalloy substrate, and a metallic bond coat covering the substrate, the metallic bond coat comprising at least two elemental layers, including a first elemental layer and a second elemental layer, the first elemental layer being disposed between the substrate and the second elemental layer, each elemental layer comprising a γ′-Ni3Al phase and in that the average atomic fraction of aluminium in the second elemental layer is strictly higher than the average atomic fraction of aluminium in the first elemental layer. ### Claim 2 (depends on 1) The turbine component of claim 1, wherein at least one elemental layer comprises a γ-Ni phase. ### Claim 3 (depends on 1) The turbine component of claim 1, wherein the average atomic fraction of aluminium in the first elemental layer is strictly higher than the average atomic fraction of aluminium in the substrate. ### Claim 4 (depends on 1) The turbine component of claim 1, wherein the first elemental layer comprises a γ′-Ni3Al phase and a γ-Ni phase, and the metallic bond coat comprises at least one further elemental layer comprising only a γ-Ni phase. ### Claim 5 (depends on 1) The turbine component of claim 1, wherein the metallic bond coat comprises a plurality of elemental layers, each elemental layer comprising a γ′-Ni3Al phase, and possibly a γ-Ni phase, and wherein the average atomic fraction of aluminium in the elemental layers increases with distance from the substrate. ### Claim 6 (depends on 1) The turbine component of claim 1, wherein the average atomic fraction of aluminium in the elemental layer furthest from the substrate is between 0.22 and 0.35. ### Claim 7 (depends on 1) The turbine component of claim 1, wherein the average atomic fraction of aluminium in the elemental layer closest to the substrate is less than 0.2. ### Claim 8 (depends on 1) The turbine component of claim 1, wherein the difference between the average atomic fraction of aluminium in the substrate and the average atomic fraction of aluminium in the elemental layer closest to the substrate is less than 0.08. ### Claim 9 (depends on 1) The turbine component of claim 1, wherein the difference between the average atomic fraction of aluminium in two successive elemental layers is less than 0.06. ### Claim 10 (depends on 1) The turbine component of claim 1, wherein each elemental layer comprises at least one additive selected from chromium and hafnium, and wherein the average atomic fraction of additive in the elemental layers increases with distance from the substrate. ### Claim 11 (depends on 10) The turbine component of claim 10, wherein each elemental layer comprises hafnium, and wherein the difference between the average atomic fraction of hafnium in two successive elemental layers is less than 0.001. ### Claim 12 (depends on 10) The turbine component of claim 10, wherein the average atomic fraction of hafnium in the elemental layer furthest from the substrate is less than 0.03 and the average atomic fraction of hafnium in the elemental layer nearest the substrate is greater than 0.0005. ### Claim 13 Process for fabricating a turbine component comprising steps of: a) deposition of a first elemental layer comprising a γ′-Ni3Al phase, and possibly a γ-Ni phase, and having an average atomic fraction of aluminium x1, on a single-crystal nickel-based metallic superalloy substrate; b) deposition of a second elemental layer comprising a γ′-Ni3Al phase, and possibly a γ-Ni phase, and having an average atomic fraction of aluminium x2 strictly greater than x1 on the first elemental layer. ### Claim 14 (depends on 13) The process of claim 13, wherein the first elemental layer has an average atomic fraction of aluminium x1 strictly higher than the average atomic fraction of aluminium x0 in the nickel-based superalloy of the substrate.