Abstract: In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Abstract: In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body.

Abstract: The invention refers to a method for manufacturing a hybrid component including the following steps of manufacturing a preform as a first part of the hybrid component, then successively building up on that preform a second part of the component from a metallic powder material by means of an additive manufacturing process by scanning with an energy beam, thereby establishing a controlled grain orientation in primary and in secondary direction of at least a part of the second part of the component. The controlled secondary grain orientation is realized by applying a specific scanning pattern of the energy beam, which is aligned to the cross section profile of the component or to the local load conditions for the component.

Abstract: The application relates to the technology of producing three-dimensional articles by means of powder-based additive manufacturing, such as selective laser melting (SLM) or electron beam melting (EBM). It refers to a Nickel-base superalloy powder, wherein the superalloy powder has a chemical composition that allows establishing a gamma-prime precipitation content of 60-70 vol.-% in the superalloy in a heat treated condition. The powder has a powder size distribution between 10 and 100 ?m and a spherical morphology. The ratios of the content (in weight-%) of the alloying elements C, B, Hf, Zr, Si are the following: C/B=10-32; C/Hf>2; C/Zr>8; C/Si>1. A preferred embodiment includes of the following chemical composition (in weight-%): 7.7-8.3 Cr; 5.0-5.25 Co; 2.0-2.1 Mo;7.8-8.3 W; 5.8-6.1 Ta; 4.7-5.1 Al; 1.1-1.4 Ti; 0.08-0.16 C; 0.005-0.008 B; 0-0.04 Hf;0-0.01 Zr; 0-0.08 Si; the remainder being Ni and unavoidable impurities.

Abstract: The invention refers to a method for manufacturing a hybrid component including the following steps of manufacturing a preform as a first part of the hybrid component, then successively building up on that preform a second part of the component from a metallic powder material by means of an additive manufacturing process by scanning with an energy beam, thereby establishing a controlled grain orientation in primary and in secondary direction of at least a part of the second part of the component. The controlled secondary grain orientation is realized by applying a specific scanning pattern of the energy beam, which is aligned to the cross section profile of the component or to the local load conditions for the component.

Abstract: The invention refers to a method for manufacturing a three-dimensional metallic article/component entirely or partly. The method includes a) successively building up said article/component from a metallic base material by means of an additive manufacturing process by scanning with an energy beam, thereby b) establishing a controlled grain orientation in primary and in secondary direction of the article/component, c) wherein the secondary grain orientation is realized by applying a specific scanning pattern of the energy beam, which is aligned to the cross section profile of said article/component, or with characteristic load conditions of the article/component.

Abstract: A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7?), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7?) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

Abstract: A gas turbine (1) includes a rotor (2) which has two rotor blade rows (5) with a plurality of rotor blades (6), and also a rotor heat shield (7), which is arranged between them, with a plurality of heat shield elements (12), and with a stator (3) which has a stator blade row (8), with a plurality of stator blades (9), which is arranged axially between the two adjacent rotor blade rows (5). The stator blades (9) have a stator sealing structure (10) radially on the inside. The heat shield elements (12) have a rotor sealing structure (13) radially on the outside which interacts with the stator sealing structure (10) for forming an axial seal (14). Furthermore, a blade radial seal (15) is formed between two adjacent rotor blades (6), and also a heat shield radial seal (16) is formed between two adjacent heat shield elements (12), and in each case separates a gas path (17) from the rotor (2).

Abstract: A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1).

Abstract: A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7?), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7?) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

Abstract: A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1).

Abstract: A component, especially a hot gas component of a turbomachine, has at least one passage (7, 7?), especially a cooling passage, which is embedded in an outer wall (5) of the component (1) of the turbomachine and basically extends parallel to the surface (6) of the component (1). The component (1) has a basic body (8) and at least one coating (9) which is applied to the basic body on the outside, and the passage (7, 7?) on one hand is formed by a cavity which is formed in the basic body (8), and on the other hand is closed off towards the surface (6) of the component (1) by the coating (9).

Abstract: A method is disclosed for recovering the properties of single crystal and directionally solidified Nickel based superalloys and articles made thereof, after use in a high temperature environment. The method comprises the steps of a stress relief treatment, a ?? rejuvenation heat treatment at a temperature below the ??-solvus temperature (Tsolvus, ??) of the superalloy, a precipitation heat treatment and an aging heat treatment.

Abstract: A gas turbine (1) includes a rotor (2) which has two rotor blade rows (5) with a plurality of rotor blades (6), and also a rotor heat shield (7), which is arranged between them, with a plurality of heat shield elements (12), and with a stator (3) which has a stator blade row (8), with a plurality of stator blades (9), which is arranged axially between the two adjacent rotor blade rows (5). The stator blades (9) have a stator sealing structure (10) radially on the inside. The heat shield elements (12) have a rotor sealing structure (13) radially on the outside which interacts with the stator sealing structure (10) for forming an axial seal (14). Furthermore, a blade radial seal (15) is formed between two adjacent rotor blades (6), and also a heat shield radial seal (16) is formed between two adjacent heat shield elements (12), and in each case separates a gas path (17) from the rotor (2).

Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

Abstract: A rotating blade (1) for a gas turbine comprises an internal cooling structure having at least three cooling air passages (5, 6, 7) in fluid connection with one another by turns (9, 10). An opening (12) provides an outlet for dissolved core material to be removed from the blade following casting of the cooling structure without any residue remaining within. According to the invention, the cooling structure comprises trip strips (13, 15) in the first and second passage (5, 6) with specified ratio of height to distance between trip strips and the trip strips (13) in the first passage being arranged at 90° with respect to the direction of airflow. In a particular embodiment, the trip strips (15) in the second passage (6) are arranged at angle of 45°. The design according to the invention assures sufficient airflow through first and second air passages (5, 6).

Abstract: A method for repairing or renewing cooling holes of a coated component of a gas turbine, includes the step of removing an old coating from an outer side of the component. The cooling hole, after removing the old coating, in a longitudinal section, has an old cross section which is larger than a nominal cross section which the cooling hole has in this longitudinal section in an original new state of the finished component. The method also includes applying a new coating to the component at least in the longitudinal section of the cooling hole so that the cooling hole, in the longitudinal section, has an interim cross section which is smaller than the nominal cross section. The method also includes partially removing the new coating inside the cooling hole so that the cooling hole, in the longitudinal section, has a new cross section which is about the same size as the nominal cross section.