A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

A product includes a material having aluminum and at least one rare earth element (REE). The material includes the following microstructure features: at least 1 volume % particles of a phase of an aluminum-rare earth element alloy, the particles comprise at least 5 weight % of the at least one rare earth element, the particles have an average aspect ratio less than or equal to 5, and an average interparticle spacing between the particles is less than or equal to 1 μm. A method includes forming a base material, the base material having aluminum and at least one rare earth element (REE), and working the base material to form a product.

A method of fabricating an airfoil preform for a turbine engine by selective melting on a bed of powder, the preform including an airfoil and a removable support secured to the airfoil, the airfoil being fabricated layer by layer from a first edge to a second edge of the airfoil, the method including fabricating the removable support and the airfoil, the removable support being for securing to a fabrication platform and to a portion of a face of the airfoil situated near the first edge and facing the fabrication platform. The face of the airfoil facing the fabrication platform includes a flat extending away from the face, the flat being present over a portion of the face that is situated outside the first edge, the support being secured to the flat or both to the flat and to the portion of the face that is situated outside the first edge.

By melting a shaping material in which a metal powder and a binder are mixed and by carrying out injection molding (primary shaping) in an injection mold, an injection molded body, or an intermediate shaped body are produced. The injection molded body or the intermediate shaped body is placed by a transfer mold and is subjected to a gravity shaping (secondary shaping) with a transformation. A sintered body is manufactured by carrying out debindering and sintering to the injection molded body.

The present disclosure relates to a method of forming a component and at least one support structure joined to the component by additive layer manufacturing, wherein the support structure has a reduced density and/or increased porosity relative to the component. The method then comprises a subsequent heat treatment step at increased pressure on the component and support structure to separate the component and at least one support structure.

A method of manufacturing an additively manufactured object includes: checking, for an additively manufactured object including a plurality of internal passages, the presence or absence of a deposit in each inner wall surface of the plurality of internal passages; and selectively removing the deposit from the internal passage in which the deposit has been detected in the checking, among the plurality of internal passages.

An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

A method for producing a support structure in the additive manufacturing of a component, includes: a) providing a geometry for the component having a region to be supported, b) providing a support structure for the region of the component, c) defining an irradiation pattern for an irradiation of layers of a raw material for the support structure, wherein surface vectors for an irradiation for a structure of the component extend into a region of the support structure, wherein common surface vectors are defined for the component and for the support structure, and d) selective irradiation of layers of the raw material for the component and the provided support structure according to the defined irradiation pattern.

Embodiments of bladed rotors and methods for manufacturing bladed rotors are provided herein. The method for manufacturing bladed rotors includes providing a workpiece including a first rotor blade segment. The first rotor blade segment includes a first platform portion on a radially outward end portion of the first rotor blade segment. Further, the method includes forming a second rotor blade segment, by additive manufacturing, removing a side portion of the first platform portion, and removing a side portion of the second rotor blade segment, whereby a second platform portion remains on a radially outward end portion of the second rotor blade segment.