A casting ceramic core includes a ceramic structure having at least one through hole and a plurality of features extending from a main ceramic body. The ceramic body defines a negative space for a casting and a plurality of aligned fibers extending a substantial length of at least one casting feature.

Systems and methods in accordance with embodiments of the invention efficaciously implement robust gearbox housings. In one embodiment, a method of fabricating a gearbox housing includes: providing an alloy composition from which the gearbox housing will be fabricated from; casting the alloy composition around a solid body so as to form a part characterized by the inclusion of a cavity, where the cast part includes a metallic glass-based material; and nondestructively separating the cast part from the solid body.

Systems and methods in accordance with embodiments of the invention efficaciously implement robust gearbox housings. In one embodiment, a method of fabricating a gearbox housing includes: providing an alloy composition from which the gearbox housing will be fabricated from; casting the alloy composition around a solid body so as to form a part characterized by the inclusion of a cavity, where the cast part includes a metallic glass-based material; and nondestructively separating the cast part from the solid body.

A three-dimensional metallic foam is fabricated with an active oxide material for use as an anode for lithium batteries. The porous metal foam, which can be fabricated by a freeze-casting process, is used as the anode current collector of the lithium battery. The porous metal foam can be heat-treated to form an active oxide material to form on the surface of the metal foam. The oxide material acts as the three-dimensional active material that reacts with lithium ions during charging and discharging.

A three-dimensional metallic foam is fabricated with an active oxide material for use as an anode for lithium batteries. The porous metal foam, which can be fabricated by a freeze-casting process, is used as the anode current collector of the lithium battery. The porous metal foam can be heat-treated to form an active oxide material to form on the surface of the metal foam. The oxide material acts as the three-dimensional active material that reacts with lithium ions during charging and discharging.

A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die. A casting core and method for fabricating a gas turbine engine component is also disclosed.

A gas turbine engine according to an example of the present disclosure includes, among other things, a rotor and a vane spaced axially from the rotor, and a blade outer air seal spaced radially from the rotor. At least one of the rotor and the vane includes an airfoil section extending from a platform. At least one of the airfoil section, the platform and the blade outer air seal includes a first cavity extending in a first direction, the first cavity defining a reference plane along a parting line formed by a casting die, and a plurality of trip strips including a first set of trip strips distributed in the first direction along a surface of the first cavity and on a first side of the reference plane, each of the plurality of trip strips defining a respective groove axis extending longitudinally between a first end and an opposed, second end of a respective one the plurality of trip strips, and the groove axes being oriented with respect to a pull direction of the casting die. A casting core and method for fabricating a gas turbine engine component is also disclosed.

The present invention refers to a camshaft with a functional component as an assembly insert and the process of manufacturing said camshaft, wherein said camshaft has at least one functional component integrated in the camshaft body, taking into account that the material of the functional component and the shaft body are of different materials; and wherein one or more functional components comprises a body of A-type material having an internal bore of suitable geometry to pass through it a B-type melt in a casting process; gripping means which achieve a mechanical grip between both materials, A-type material and B-type molten material, to give mechanical grip in the longitudinal and circumferential direction with respect to the camshaft body.

A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.

A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.