The disclosure provides for a layered metal with resistance to hydrogen induced cracking and method of production thereof, comprising a core metal alloy and a skin metal alloy. The core metal alloy comprises twinned boundaries. The core metal alloy has undergone plastic deformation and a heat treatment. The core metal alloy comprises nickel and cobalt. The skin metal alloy is disposed on the core metal alloy, wherein the skin metal alloy comprises an entropy greater than the core metal alloy. The core metal alloy comprises a greater density of twinned boundaries than the skin metal alloy. The skin metal alloy comprises a stacking fault energy of at least about 50 mJ/m.sup.2, and the skin metal alloy comprises iron, aluminum, and boron.

A casting method includes forming a seed. The seed has a first end and a second end. The forming includes bending a seed precursor. The seed second end is placed in contact or spaced facing relation a chill plate. The first end is contacted with molten material. The molten material is cooled and solidifies so that a crystalline structure of the seed propagates into the solidifying material. The forming further includes inserting the bent seed precursor into a sleeve leaving the bent seed precursor protruding from a first end of the sleeve.

A composition of a nickel based alloy mixture which can be used for welding via especially liquid metal deposition or as a powder bed of an additive manufacturing method. A metallic powder mixture includes (in wt %): a cobalt (Co) or nickel (Ni) based super alloy with a content of 20% to 60%, a NiCoCrAlY-composition with a content of 70% to 30% and a metallic braze material with a content between 10% to 5%. The melting point of the braze material is at least 10K lower than the melting point of the nickel or cobalt based superalloy.

The specification relates to a high gamma prim nickel based superalloy, its use and a method of manufacturing of turbine engine components by welding, 3D additive manufacturing, casting and hot forming, and the superalloy comprises by wt %: from 9.0 to 10.5% Cr, from 16 to 22% Co, from 1.0 to 1.4% Mo, from 5.0 to 5.8% W, from 2.0 to 6.0% Ta, from 1.0 to 4.0% Nb provided that total content of Ta and Nb remains with a range from 3.0 to 7.0%, from 3.0 to 6.5% Al, from 0.2 to 1.5% Hf, from 0.01 to 0.2% C, from 0 to 1.0% Ge, from 0 to 1.0 wt. % Si, from 0 to 0.2 wt. % Y, from 0 to 0.015 wt. % B, from 1.5 to 3.5 wt. % Re, and nickel with impurities to balance.

A composition of a nickel-based alloy mixture which can be used for welding via especially liquid metal deposition or as a powder bed of an additive manufacturing method. The metallic powder mixture includes a cobalt (Co) or nickel (Ni) based super alloy, a NiCoCrAlY—X-composition wherein X=Silicon (Si), Tantalum (Ta), Rhenium (Re) and/or Iron (Fe), a metallic braze material, wherein the melting point of the braze material is at least 10K lower than the melting point of the cobalt (Co) or nickel (Ni) based superalloy.

Provided are a Ni-based alloy for hot die having a high high-temperature compressive strength and a good oxidation resistance and being capable of suppressing the deterioration in the working environment and the shape deterioration, and a hot forging die made of the Ni-based alloy for hot die. The Ni-based alloy for hot die comprises, in mass %, W: 7.0 to 15.0%, Mo: 2.5 to 11.0%, Al: 5.0 to 7.5%, Cr: 0.5 to 3.0%, Ta: 0.5 to 7.0%, S: 0.0010% or less, one or two or more selected from rare-earth elements, Y, and Mg in a total amount of 0 to 0.020%, and the balance of Ni with inevitable impurities. In addition to the composition described above, one or two elements selected from Zr and Hf can further be contained in a total amount of 0.5% or less.

A nickel-based superalloy without titanium and a corresponding powder. A process for producing a component, wherein the alloy or the powder is used, in particular for a process for additive manufacture, especially selective laser sintering or selective laser melting. A component having an alloy or produced from the powder or produced by the process.

The invention concerns a method for manufacturing an aircraft part, the part comprising a monocrystalline nickel-based superalloy substrate, the method consecutively implementing the steps of moulding the part at a moulding temperature greater than the melting temperature of the superalloy, and cooling the part, such that the monocrystalline superalloy has a γ phase and a γ phase, solution heat treatment of the part at a first temperature between the solves temperature of the γ′ phase and the melting temperature of the superalloy, homogenising the crystalline structure or the part, cooling the part to ambient temperature, first tempering and second tempering.

An objective of the invention is to provide a Ni-based forged alloy article based on a superhigh precipitation-strengthening Ni-based alloy material that has mechanical properties balanced at higher level than before, and a turbine high-temperature member formed of the forged alloy article. There is provided a Ni-based forged alloy article comprising crystal grains of the γ phase and precipitation particles of the γ′ phase, and having a chemical composition enabling to precipitate a γ′ phase in an amount of 50-70 volume % at 700° C. within a matrix of a γ phase. The γ′ phase comprises: aging precipitation γ′ phase particles precipitating within the γ phase grains; and eutectic reaction γ′ phase particles precipitating between/among the γ phase grains. The eutectic reaction γ′ phase particles comprise a higher content of Ni and Al than the aging precipitation γ′ phase particles and have an average particle size of 2 to 40 μm.

Nickel-cobalt alloy for powder, wherein the contents (in wt %) are defined as follows: C>0-max. 0.1% S max. 0.015% Cr 13-23% Ni the rest (>30%) Mn max. 1.0% Si max. 1.0% Mo 1-6% Ti>0-3% Nb+Ta 3-8% Cu max. 0.5% Fe>0-max. 10% Al>0-<4.0% V up to 4% Zr>0-max. 0.1% Co>12-<35% W up to 4% Hf up to 3.0% O max. 0.1% N>0-max. 0.1% Mg>0-max. 0.01% B>0-max. 0.02% P>0-max. 0.03% Ar 0-max. 0.08% Se max. 0.0005% Bi max. 0.00005% Pb max. 0.002%