A method of manufacturing of a component having the steps of manufacturing of a first segment for the component by a powder-bed manufacturing process, and the manufacturing of a second segment for the component originating from the first segment by an additive manufacturing process, such that the second segment projects by a projecting distance over at least one side face of the first segment. Furthermore, a component has the first segment being manufactured by the powder-bed manufacturing process and the second segment being manufactured by the additive manufacturing process, wherein the second segment projects by a projecting distance over at least one side face of the first segment.

A method of manufacturing of a component having the steps of manufacturing of a first segment for the component by a powder-bed manufacturing process, and the manufacturing of a second segment for the component originating from the first segment by an additive manufacturing process, such that the second segment projects by a projecting distance over at least one side face of the first segment. Furthermore, a component has the first segment being manufactured by the powder-bed manufacturing process and the second segment being manufactured by the additive manufacturing process, wherein the second segment projects by a projecting distance over at least one side face of the first segment.

Disclosed is a method for producing a blade for a turbomachine, which method comprises: providing a blade root, having a first platform region, from a first material; providing on the first platform region at least one capsule that is filled with a metallic and/or ceramic powder that comprises at least one second material which is different from the first material, for producing a blade airfoil having a second platform region; producing and shaping a blade airfoil from the capsule that is filled with the powder by at least one thermal input method, thereby connecting the blade root to the blade airfoil in respective platform regions.

Also disclosed is a blade which is obtainable and/or obtained by this method.

A system may include a current source; a first metal or alloy component with a first major surface electrically coupled to the current source; a second metal or alloy component with a second major surface electrically coupled in series to the first component and the current source via an external electrical conductor, where the first and second major surfaces are positioned adjacent to each other to define a joint region; a metal or alloy powder disposed in at least a portion of the joint region; and a controller. The controller may be configured to cause the current source to output an alternating current that conducts through the first component and the second component to induce magnetic eddy currents, magnetic hysteresis, or both within at least a portion of the metal or alloy powder disposed in at least the first portion of the joint region.

A turbine blade having a casing and having an inner module, wherein a cooling medium can flow through the inner module both in a longitudinal direction and in a radial direction, and the inner module is attached to the casing by fixed bearings and floating bearings. A method for producing a turbine blade having an inner module and having a casing is produced by selective laser melting.

Methods are provided that include depositing a nickel-base superalloy powder including gamma nickel solid solution and gamma prime (Ni.sub.3Al) solid solution phases onto a seed crystal having a predetermined primary orientation, fully melting the powder and a portion of the seed crystal at a superliquidus temperature to form an initial layer having the predetermined primary orientation, heat treating the layer at subsolvus temperatures to precipitate gamma prime solid solution phase particles, depositing additional powder over the layer, melting the deposited powder and a portion of the initial layer at a superliquidus temperature to form a successive layer having the predetermined primary orientation, heat treating the layer at a subsolvus temperature to precipitate gamma prime solid solution phase particles, and repeating depositing additional powder, melting the additional powder and the portion of the successive layer at the superliquidus temperature, and heat treating the successive layer at a subsolvus temperature.

Methods are provided that include depositing a nickel-base superalloy powder including gamma nickel solid solution and gamma prime (Ni.sub.3Al) solid solution phases onto a seed crystal having a predetermined primary orientation, fully melting the powder and a portion of the seed crystal at a superliquidus temperature to form an initial layer having the predetermined primary orientation, heat treating the layer at subsolvus temperatures to precipitate gamma prime solid solution phase particles, depositing additional powder over the layer, melting the deposited powder and a portion of the initial layer at a superliquidus temperature to form a successive layer having the predetermined primary orientation, heat treating the layer at a subsolvus temperature to precipitate gamma prime solid solution phase particles, and repeating depositing additional powder, melting the additional powder and the portion of the successive layer at the superliquidus temperature, and heat treating the successive layer at a subsolvus temperature.

The present disclosure relates to new materials comprising Al, Co, Ni and Ti. The new materials may realize a single phase field of a face-centered cubic (fcc) solid solution structure immediately below the solidus temperature of the material. The new materials may include at least one precipitate phase and have a solvus temperature of at least 1100° C. The new materials may include 2.1-8.4 wt. % Al, 4.7-60.6 wt. % Co, 29.6-89.3 wt. % Ni, and 3.9-9.4 wt. % Ti. In one embodiment, the precipitate is selected from the group consisting of the L1.sub.2 phase, the B2 phase, the Ni.sub.3Ti phase, and combinations thereof. The new alloys may realize improved high temperature properties.

The present disclosure relates to new materials comprising Al, Co, Cr, and Ni. The new materials may realize a single phase field of a face-centered cubic (fcc) solid solution structure immediately below the solidus temperature of the material. The new materials may include at least one precipitate phase and have a solvus temperature of at least 1000° C. The new materials may include 2.2-8.6 wt. % Al, 4.9-65.0 wt. % Co, 4.3-42.0 wt. % Cr, and 4.8-88.6 wt. % Ni. In one embodiment, the precipitate is selected from the group consisting of the L1.sub.2 phase, the B2 phase, the sigma phase, the bcc phase, and combinations thereof. The new alloys may realize improved high temperature properties.

The present disclosure relates to new materials comprising Al, Co, Fe, and Ni. The new materials may realize a single phase field of a face-centered cubic (fcc) solid solution structure immediately below the solidus temperature of the material. The new materials may include at least one precipitate phase and have a solvus temperature of at least 1000° C. The new materials may include 4.4-11.4 wt. % Al, 4.9-42.2 wt. % Co, 4.6-28.9 wt. % Fe, and 44.1-86.1 wt. % Ni. In one embodiment, the precipitate is selected from the group consisting of the L1.sub.2 phase, the B2 phase, and combinations thereof. The new alloys may realize improved high temperature properties.