Abstract: A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 1.0 to 3.0 ruthenium, 2.0 to 14.0% cobalt, 0.3 to 1.0% molybdenum, 3.0 to 5.0% chromium, 2.5 to 4.0% tungsten, 4.5 to 6.5% aluminum, 0.50 to 1.50% titanium, 8.0 to 9.0% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.

Abstract: The invention relates to a process for manufacturing a part made of nickel-based monocrystalline superalloy containing hafnium. This process is noteworthy in that it comprises the following successive steps consisting in: —manufacturing a nickel-based monocrystalline superalloy that is not doped with hafnium, —manufacturing a part from this superalloy, —directly depositing on said part a layer of hafnium having a thickness of between 50 nm and 800 nm, —carrying out a diffusion treatment of the hafnium so as to form an interdiffusion layer at the surface of said part and to thus obtain a part made of nickel-based monocrystalline superalloy containing hafnium.

Abstract: A turbine component includes a substrate made from monocrystalline nickel-based superalloy including rhenium, which has a ?-?? Ni phase, and an average weight faction of chromium of less than 0.08, a sublayer made from nickel-based metal superalloy covering the substrate, in which the sublayer made from metal superalloy includes at least aluminium, nickel, chromium, silicon, hafnium and has, predominantly by volume, a ??-Ni 3 Al phase.

Abstract: The invention relates to a method for manufacturing a part (1) comprising a nickel-based monocrystalline superalloy substrate (2). This method is characterised in that it comprises the steps that consist of: manufacturing a nickel-based monocrystalline superalloy substrate (2); forming a coating (3) on said substrate (2), comprising at least one layer (30) of a first type comprising aluminum and platinum, at least one layer (31) of a second type comprising aluminium, silicon, platinum and a layer (32) of a third type comprising nickel, aluminium, silicon and platinum, said layer (32) of the third type being the outermost layer of the stack of coating layers (3); and forming a layer (4) of silicon-doped alumina on said layer (32) of the third type.

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 ??-Ni3Al phase, and optionally a ?-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.

Abstract: A nickel-based superalloy comprises, in percentages by mass, 4.0 to 5.5% rhenium, 3.5 to 12.5% cobalt, 0.30 to 1.50% molybdenum, 3.5 to 5.5% chromium, 3.5 to 5.5% tungsten, 4.5 to 6.0% aluminum, 0.35 to 1.50% titanium, 8.0 to 10.5% tantalum, 0.15 to 0.30% hafnium, 0.05 to 0.15% silicon, the balance being nickel and unavoidable impurities. A single-crystal blade comprises such an alloy and a turbomachine comprising such a blade.

Abstract: A turbine part, such as a turbine blade or a distributor fin, for example, including a substrate made of superalloy based on monocrystalline nickel, including rhenium and/or ruthenium, and having a ??-NisAI phase that is predominant by volume and a ?-Ni phase, the part also including a sublayer made of metal superalloy based on nickel covering the substrate, wherein the sublayer has a ??-NisAI phase that is predominant by volume and wherein the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part including a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a ??-NisAI phase, on a substrate made of superalloy based on nickel including rhenium and/or ruthenium.

Abstract: The invention relates to a turbine part, such as a turbine blade or a distributor fin, for example, comprising a substrate made of a monocrystalline nickel superalloy, a metal sublayer covering the substrate, and a protective layer of metal oxide covering the sublayer, characterised in that the metal sublayer has one surface in contact with the protective layer and the surface has a mean roughness of less than 1 ?m.

Abstract: A nickel-based superalloy comprises in mass percent: 4.0% to 6.0% chromium; 0.4% to 0.8% molybdenum; 2.5% to 3.5% rhenium; 6.2% to 6.6% tungsten; 5.2% to 5.7% aluminum; 0.0 to 1.6% titanium; 6.0% to 9.9% tantalum; 0.0 to 0.7% hafnium; and 0.0 to 0.3% silicon; the balance being constituted by nickel and any impurities. A monocrystalline blade comprises such an alloy and a turbomachine including such a blade.

Abstract: The invention relates to a method for manufacturing a part (1) comprising a nickel-based monocrystalline superalloy substrate (2). This method is characterised in that it comprises the steps that consist of: manufacturing a nickel-based monocrystalline superalloy substrate (2); forming a coating (3) on said substrate (2), comprising at least one layer (30) of a first type comprising aluminum and platinum, at least one layer (31) of a second type comprising aluminium, silicon, platinum and a layer (32) of a third type comprising nickel, aluminium, silicon and platinum, said layer (32) of the third type being the outermost layer of the stack of coating layers (3); and forming a layer (4) of silicon-doped alumina on said layer (32) of the third type.

Abstract: The invention relates to a method tor protecting a hafnium-free, nickel-based monocrystalline superalloy part (1) against corrosion and oxidation. Said method is characterized in that it involves at least the steps of: -manufacturing a hafnium-free, nickel-based monocrystalline superalloy part (1); -depositing a first hafnium-containing layer (2), an undercoat made of an alloy containing at least 10 atom % aluminum, and a second hafnium-containing layer on the part (1) such that a mixed layer (3) is formed, and depositing a third hafnium-containing layer (4) on the part (1); -performing a diffusion treatment in order for the first (2) and third (4) layers to diffuse such that a first interdiffusion region (21) is formed on the top portion of the part (1) and a second interdiffusion region (41) is formed on the surface of the mixed layer (3); -subjecting the second interdiffusion region (41) to an oxidation treatment so as to obtain a hafnium-doped alumina layer (42).

Abstract: The invention relates to a process for manufacturing a part made of nickel-based monocrystalline superalloy containing hafnium. This process is noteworthy in that it comprises the following successive steps consisting in:—manufacturing a nickel-based monocrystalline superalloy that is not doped with hafnium,—manufacturing a part from this superalloy,—directly depositing on said part a layer of hafnium having a thickness of between 50 nm and 800 nm,—carrying out a diffusion treatment of the hafnium so as to form an interdiffusion layer at the surface of said part and to thus obtain a part made of nickel-based monocrystalline superalloy containing hafnium.