The inventive concept relates to method for manufacturing a metal based component comprising at least one protrusion. The method comprises: providing a metal based substrate comprising a surface having at least one cavity; providing a metal based protrusion element comprising a first portion and a second portion, wherein said first portion has a shape that conforms to a shape of the cavity; arranging the first portion of the protrusion element in said cavity such that at least the second portion of the protrusion element protrudes at least 5 mm from a surface of the metal based substrate, to form a substrate comprising a protrusion; placing said substrate comprising a protrusion in a canister such that a void is formed between the canister and the surface of the substrate comprising the protrusion; filling at least a portion of the void with a diamond powder such that the surface of the substrate comprising the protrusion is covered by the inert filler material; removing gas from the interface between said diamond powder and said substrate comprising

The proposed solution relates, in particular, to an engine component having at least one first loading zone, which is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating, and a second loading zone, which is provided spaced at a distance from the first loading zone on the engine component and likewise is designed for dynamic loads arising at the engine component when the engine component is correctly built into an engine and when the engine is operating.

The proposal is, in particular, that at least one spatially delimited modification zone with introduced internal tensile stress is formed on the engine component, via which zone a crack propagating in the engine component is guided to the and/or within the second loading zone.

The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:—S1: covering the core (1) by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,—S2: covering the core (1) by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;—S3: applying a heat treatment to the covered core (1) in such a way as to dry the solution and solidify the coating.

A method of repairing a superalloy component includes subjecting the superalloy component, including a repair area, to a phase agglomeration cycle, which includes stepped heating and controlled cooling of the component. The method further includes applying weld material to the repair area to create a weld surface; and covering the weld surface with brazing material. The component is then subjected to a braze cycle to produce a brazed component. The brazed component is cleaned, and the cleaned component is subjected to a restorative heat treatment to restore the microcrystalline structure and mechanical properties of the component.

A method for manufacturing a component of a rotating machine comprises the steps of forming a structural inner portion by additive manufacturing from a first material; covering the structural inner portion with a protective outer portion made of a second material; the first material has a melting point higher than a second material.

A connection element providing a first ring and a second ring, the two rings rotating relative to one another about a central axis, the first ring having a contact portion with a contact surface interacting with the second ring for the relative rotation, and a fastening portion configured to be rigidly secured to a support. The contact portion is made of a first material and the fastening portion is made of a second material, different to the first material, the first material having a hardness strictly greater than that of the second material, and the second material having a structural fatigue strength strictly greater than that of the first material.

The invention relates to a method for producing a rotor of a flow engine, namely an integrally bladed rotor with an integral outer shroud, comprising at least the following steps: a rotor blank comprising the integral rotor blades and the integral outer shroud is first produced by means of a generative production method; the rotor blank is then subjected to a separating surface treatment at flow-guiding sections and is subjected, separately therefrom, to a machining surface treatment at non-flow-guiding sections.

A method of manufacturing a metal member including a first part and a second part includes a first fabrication process of fabricating the first part through a three-dimensional metal stack fabrication by a powder bed method, and a second fabrication process of fabricating an outer circumference of the second part through the three-dimensional metal stack fabrication by the powder bed method, and then sintering metallic powder remaining in an inner portion of the second part by hot isostatic pressing so as to fabricate the second part.

A method of producing an abrasive tip for a turbine blade includes producing or obtaining a metal powder that is mixed with an abrasive ceramic powder and producing or obtaining a metallic mold that is in the shape of an airfoil. The metallic mold includes a hollow interior portion. The method further includes sealing the metal and ceramic powder mixture within the hollow interior portion of the metallic mold under vacuum and subjecting the sealed mold to a hot isostatic pressing process. The hot isostatic pressing process compacts and binds the metal and ceramic powder mixture together into a solid article in the shape of the airfoil. Still further, the method includes slicing the solid article into a plurality of airfoil-shaped slices and bonding one slice of the plurality of airfoil-shaped slices to a tip portion of a turbine blade.

A method of producing an abrasive tip for a turbine blade includes producing or obtaining a metal powder that is mixed with an abrasive ceramic powder and producing or obtaining a metallic mold that is in the shape of an airfoil. The metallic mold includes a hollow interior portion. The method further includes sealing the metal and ceramic powder mixture within the hollow interior portion of the metallic mold under vacuum and subjecting the sealed mold to a hot isostatic pressing process. The hot isostatic pressing process compacts and binds the metal and ceramic powder mixture together into a solid article in the shape of the airfoil. Still further, the method includes slicing the solid article into a plurality of airfoil-shaped slices and bonding one slice of the plurality of airfoil-shaped slices to a tip portion of a turbine blade.