A metal matrix composite (MMC) tool includes a mesoscale-reinforced hard composite portion that comprises reinforcing particles and mesoscale reinforcing structures dispersed in a binder material. The mesoscale reinforcing structures are printed using at least one additive manufacturing technique and are larger than an average powder-size distribution of the reinforcing particles.

A multi-material component joined by a high entropy alloy is provided, as well as methods of making a multi-material component by joining dissimilar materials with high entropy alloys.

A battery electrode structure includes a substrate, a first conductive layer and a plurality of active particles. The substrate has a substrate surface. The first conductive layer is disposed on the substrate surface. Each of the active particles has a first portion conformally engaged with a surface of the first conductive layer and a second portion protruding outwards from the surface of the first conductive layer.

The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank, manufacturing a housing element, producing an assembly opening corresponding to the housing element in the housing blank, arranging the housing element in the assembly opening, and joining the housing element to the housing blank by means of a welding method. In addition, the invention relates to a turbomachine housing.

In a first aspect, there is a method of making a rotor blade, including designing at least one of an upper skin, a lower skin, a support network, and components therefor; and forming at least one of the upper skin, the lower skin, a support network, and components therefor using an additive manufacturing process. In a second aspect, there is an airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

A method of forming a passage in a turbine component includes: using an additive manufacturing process to form a first support structure on a first surface of the turbine component; forming a second support structure on a second surface of the turbine component, the second support structure being spaced apart from the first support structure; and forming a passage in the turbine component between the first and second support structures.

Methods, apparatus, and systems for fabricating diffractive structures on gemstones for high optical performance are provided. In one aspect, a method includes obtaining a plurality of gemstone characteristics of a gemstone, determining that the gemstone exhibits each of the plurality of gemstone characteristics within a respective predetermined range, identifying a diffractive structure setting associated with a combination of the respective predetermined ranges for the plurality of gemstone characteristics, and fabricating diffractive structures on the gemstone according to the diffractive structure setting.

A method of making a sheath for an airfoil may include the steps of forming an upper sleeve and a lower sleeve, and forming a central portion bonded to the upper sleeve and the lower sleeve. The central portion may be formed by depositing a material on the upper sleeve and the lower sleeve. A portion of the material may be removed from at least one of the central portion, the upper sleeve, or the lower sleeve. The sheath may include a first flank, a central portion bonded to the first flank, and a second flank bonded to the central portion. The central portion may have a substantially uniform microstructure resulting from additive manufacturing.

A source of heat energy and a source of material for performing a material additive process upon the thin wall member is disclosed. A fixture is located relative to the thin wall element. The source of heat energy used for forming a joining member between the workpiece and the fixture to fixedly secure the fixture to the workpiece preventing the thin wall member from deforming when subject to the source of heat energy. A direct material additive process is upon the thin wall member adding material to the thin wall member to improve physical characteristics of the thin wall member. The joining member is mechanically removed from the workpiece after the work piece cools. A portion of the material is mechanically removed from the thin wall member to achieve desired dimensional characteristics.

A method of additive manufacturing comprises determining a first resonant frequency of an unflawed reference workpiece at a first partial stage of completion, fabricating a production workpiece to the first partial stage of completion via additive manufacture, sensing a second resonant frequency of the production workpiece in-situ at the first partial stage of completion, during the fabrication, analyzing the workpiece for flaws based on comparison of the first and second resonant frequencies, and providing an output indicative of production workpiece condition, based on the analysis.

An additive manufacturing system comprises an additive manufacturing tool, a sensor, and a controller. The additive manufacturing tool is disposed to construct a workpiece via iterative layer deposition. The sensor is disposed to determine a resonant frequency of the workpiece in-situ at the additive manufacturing tool, during fabrication. The controller is configured to terminate manufacture of the workpiece if the resonant frequency differs substantially from a reference frequency.