In some examples, a method for additively manufacturing a heat pipe, the method including depositing, via a filament delivery device, a filament to form a heat pipe preform, wherein the filament includes a binder and a metal or alloy powder; and sintering the heat pipe preform to form the heat pipe, the heat pipe including an outer shell, a wicking region, and a vapor transport region defined by the metal or alloy.

An insert holder includes a cutting portion and a shank portion. The insert holder further includes a cavity which includes a cavity chamber and a plurality of cavity through recesses which serve to reduce the weight of the insert holder. The plurality of cavity through recesses open out to the cavity chamber and to the periphery of the shank portion. A cutting tool is provided having a cutting insert releasably attached to the insert holder.

An insert holder includes a cutting portion and a shank portion. The insert holder further includes a cavity which includes a cavity chamber and a plurality of cavity through recesses which serve to reduce the weight of the insert holder. The plurality of cavity through recesses open out to the cavity chamber and to the periphery of the shank portion. A cutting tool is provided having a cutting insert releasably attached to the insert holder.

A method includes designing a part. The part includes at least one internal structure. The internal structure is designed to provide strain mitigation, energy dissipation, or impact resistance for the part during an emergency condition. The part is built by a layer-by-layer additive manufacturing process. While building the part, the internal structure is connected to the part.

Disclosed is a blade for a turbomachine, comprising an outer shell and an inner core which is at least partially enclosed by the outer shell and has a higher porosity than the outer shell. The outer shell is formed by a ceramic body or a body made of a ceramic matrix composite material, and the inner core is formed by a fiber-reinforced ceramic or a fiber-reinforced ceramic matrix composite material.

A method of forming a rotor blade, including forming at least one of a partial upper skin, a partial lower skin, and a partial support network using an additive manufacturing process; and forming a first receptacle in at least a one of the partial upper skin, the partial lower skin, and the partial support network using the additive manufacturing process. The first receptacle is configured to receive of at least one of an electronic component and a mechanical component. In some embodiments, there is a method of manufacturing a rotor blade that includes forming a first locating receptacle in at least one of the upper skin, the lower skin, and the support network using the additive manufacturing process; and positioning at least one of the upper skin, the lower skin, and the support network in a desired position on a fixture based, in part, on the first locating receptacle.

Provided is a method of manufacturing a machine part having a radial crushing strength of 120 MPa or more, including: a compression molding step of compressing raw material powder including, as a main component, metal powder that is capable of forming an oxide coating and has a pure iron powder content ratio of 95 mass % or more, to thereby obtain a green compact (10) having a predetermined shape; and a coating forming step of causing the metal powder to react with an oxidizing gas while heating the green compact (10) at a temperature lower than a sintering temperature of the metal powder in an oxidizing gas atmosphere, to thereby obtain a reinforced green compact (11) in which the oxide coating (5) is formed between particles of the metal powder.

Foamable semifinished product (1) in the form of granules produced from the metal alloy and the foam agent is inserted into the cavity of the closable mould (2) and the liquid (3) with the density that is higher than the apparent (or bulk) density of the resulting foam is led to it. The liquid has a temperature which is higher than the temperature of the melting of the metal alloy; the transfer of the heat to the particles of the foamable semifinished product (1) takes place; it subsequently expands, whereby it is supported by the liquid (3). During the expansion at least part of the liquid (3) is pushed by the expansion itself out of the mould (2) through the opening. The liquid (3) allows the regulation of the pressure of the environment of the foam agent, too, which helps to set exactly the moment of expansion. The metal melt can be advantageously used as liquid (3). The melt can partially remain in the mould (2) so the hybrid structure of the component is created. The new method makes the foaming significantly quicker, it secures the homogeneity of the metal foam, simplifies the moulds and diminishes the energy demands for the whole process.

According to one aspect, embodiments herein provide a method of reducing distortion in an additively manufactured part comprising forming a shrinking platform from a composite including metal particles embedded in a first matrix, forming shrinking supports from the composite, forming a part from the composite upon the shrinking platform and shrinking supports, forming an interior structure in at least one of the shrinking platform, the shrinking supports, and the part having a plurality of chambers with interconnections therebetween, forming from the shrinking platform, the sintering supports, and the part a portable assembly, and debinding the first matrix in the portable assembly to form a portable assembly in a brown state, wherein debinding the first matrix includes penetrating a fluid debinder into the interior structure of the at least one of the shrinking platform, the shrinking supports, and the part to debind the first matrix from within the interior structure.

A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.