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.

An airfoil component for attaching to a cropped airfoil is provided. The cropped airfoil comprises a cropped airfoil attachment section and a cropped first side opposite a cropped second side, which each extend axially between a cropped first edge and a cropped second edge to define a cropped chord length. The airfoil component comprises a body having a component first side opposite a component second side. The body defines an attachment section for attaching the airfoil component to the cropped airfoil at the cropped airfoil attachment section. The attachment section extends axially between a component first edge and a component second edge to define a component chord length, and the attachment section is oversized with respect to the cropped airfoil attachment section such that the component chord length is longer than the cropped chord length. Systems and methods also are provided.

In a method of operating an irradiation system (10) for irradiating layers of a raw material powder with electromagnetic or particle radiation in order to produce a three-dimensional work piece (110) it is determined whether a region of a raw material powder layer (11) to be selectively irradiated with electromagnetic or particle radiation in accordance with a geometry of a corresponding layer of the work piece (110) to be produced is affected or substantially unaffected by particulate impurities. Upon selectively irradiating the region of the raw material powder layer (11) with electromagnetic or particle radiation, an energy density applied to the region of the raw material powder layer (11) by a radiation beam (14a, 14b) is controlled in such a manner that the energy density is higher in case it is determined that the region of the raw material powder layer (11) is affected by particulate impurities than in case it is determined that the region of the raw material powder layer (11) is substantially unaffected by particulate impurities.

A method of repair for a metallic part of an aircraft engine includes detecting a defect inside a bore of the metallic part wherein the defect represents a departure from an intended geometry of the bore, the bore having a diameter and defining a longitudinal axis, and wherein the defect is located within the bore at a depth of at least greater than one diameter along the longitudinal axis. The method also includes measuring a geometry of the defect, preparing a patch with a complementary geometry to fill the geometry of the defect, placing the patch in the bore with the complementary geometry of the patch seated against the geometry of the defect, directing a welding beam from outside the bore, through the bore and onto the patch to weld the patch to the bore, and removing a portion of the patch to provide the intended geometry for the bore.

A method of making a transaction instrument comprising making a transaction instrument by three-dimensional (3D) printing or additive manufacturing. The transaction instrument such as a transaction card may have many features or components made by or using three-dimensional (3D) printing or additive manufacturing.

A method of manufacturing an outer joint member of a constant velocity universal includes forming cup and shaft members of medium carbon steel, preparing, as the cup member, a cup member having cylindrical and bottom portions integrally formed by forging, and a joining end surface formed on an outer surface of the bottom portion after the forging, preparing, as the shaft member, a shaft member having a joining end surface to be joined to the bottom portion of the cup member, and bringing the joining end surfaces of the cup and shaft members into abutment against each other. The method also includes welding the cup and shaft members from an outer side of the cup member to an abutment portion between the cup and shaft members in a radial direction of the cup member.

A method of manufacturing an outer joint member of a constant velocity universal includes forming cup and shaft members of medium carbon steel, preparing, as the cup member, a cup member having cylindrical and bottom portions integrally formed by forging, and a joining end surface formed on an outer surface of the bottom portion after the forging, preparing, as the shaft member, a shaft member having a joining end surface to be joined to the bottom portion of the cup member, and bringing the joining end surfaces of the cup and shaft members into abutment against each other. The method also includes welding the cup and shaft members from an outer side of the cup member to an abutment portion between the cup and shaft members in a radial direction of the cup member.

Generally described, a hybrid additive manufacturing method may be used to produce complex parts using additive manufacturing technologies. The methods may include manufacturing one or more first portions of the part with a first additive manufacturing process, such as a powder bed fusion process using a metallic powder source material. The first portion of the part is then transferred to an operating bed of a second additive manufacturing process, such as a direct deposition process using a solid metallic source material. In this regard, the first additive manufacturing process is different from the second additive manufacturing process. Next, another portion of the part is manufactured, coupled to, and partially surrounding the first portion of the part using the second additive manufacturing process, portions of which may be machined with a tool to provide a finished part.

A method of manufacturing an airfoil includes creating a plurality of cavities separated by a plurality of internal ribs in an airfoil forging. At least one hole is drilled in at least one of the plurality of internal ribs with a waterjet drilling tool. At least one hole extends perpendicularly to a wall of the rib.

This disclosure describes various methods and apparatus for characterizing an additive manufacturing process. A method for characterizing the additive manufacturing process can include generating scans of an energy source across a build plane; measuring an amount of energy radiated from the build plane during each of the scans using an optical sensor; determining an area of the build plane traversed during the scans; determining a thermal energy density for the area of the build plane traversed by the scans based upon the amount of energy radiated and the area of the build plane traversed by the scans; mapping the thermal energy density to one or more location of the build plane; determining that the thermal energy density is characterized by a density outside a range of density values; and thereafter, adjusting subsequent scans of the energy source across or proximate the one or more locations of the build plane.