A 3D printer includes an ejector device comprising a substrate and a plurality of ejector conduits on the substrate, the ejector conduits being arranged in an array. Each ejector conduit includes: a first end positioned to accept a print material, a second end comprising an ejector nozzle, the ejector nozzle comprising a first electrode and a second electrode, and a passageway for allowing the print material to flow from the first end to the second end, at least one surface of the first electrode being exposed in the passageway and at least one surface of the second electrode being exposed in the passageway. A current pulse generating system is in electrical connection with the first electrode and the second electrode of the plurality of ejector conduits. A magnetic field source is sufficiently proximate the second end of the plurality of ejector conduits so as to generate a flux region disposed within the ejector nozzle of the plurality of ejector conduits during operation of the 3D printer. The 3D printer further comprises a positioning system for controlling the relative position of the ejector device with respect to a print substrate in a manner that would allow the print substrate to receive print material jettable from the ejector nozzle of the plurality of ejector conduits during operation of the 3D printer.

A biocompatible implant according to one aspect of the present disclosure includes a base and a calcium phosphate coating film located on a surface of the base and including silver. The calcium phosphate coating film includes a plurality of calcium phosphate particles located on a surface thereof, and a plurality of needle-like crystals located on a surface of the plurality of calcium phosphate and the plurality of needle-like crystals are located in a gap at an interface between adjacent calcium phosphate particles among the plurality of calcium phosphate particles.

A biocompatible implant according to one aspect of the present disclosure includes a base and a calcium phosphate coating film located on a surface of the base and including silver. The calcium phosphate coating film includes a plurality of calcium phosphate particles located on a surface thereof, and a plurality of needle-like crystals located on a surface of the plurality of calcium phosphate and the plurality of needle-like crystals are located in a gap at an interface between adjacent calcium phosphate particles among the plurality of calcium phosphate particles.

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (Y.sub.1-aLn.sub.1a).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd) and Y.sub.2SiO.sub.5 or a (Y.sub.1-bLn.sub.1′.sub.b).sub.2SiO.sub.5 solid solution (here, Ln.sub.1′ is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (Y.sub.1-cLn.sub.2c).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu) and Y.sub.2SiO.sub.5 or a (Y.sub.1-dLn.sub.2′.sub.d).sub.2SiO.sub.5 solid solution (here, Ln.sub.2′ is any one of Sc, Yb, and Lu).

A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.

Disclosed herein is a method of manufacturing a plasma-resistant coating film. The method includes (1) forming a lower coating layer through a thermal spray process, on a base member, from a first rare earth metal compound powder including 90 to 99.9 wt % of first rare earth metal compound particles and 0.1 to 10 wt % of silica (SiO.sub.2) particles, (2) processing the surface of the lower coating layer formed in step (1) to have an average surface roughness of 1 to 6 μm, and (3) forming an upper coating layer through a suspension plasma spray process, on the lower coating layer which is surface-treated in step (2), from second rare earth metal compound particles, to obtain a structurally dense and chemically stable plasma-resistant coating film with improved plasma resistance.

A component for use in a plasma processing apparatus, which is to be exposed to a plasma, includes a base material, an alumite layer and a thermally sprayed film. The base material has a plurality of through holes and a rough surface at which one end of each of the through holes is opended. The alumite layer is formed on a surface of the base material having the rough surface by an anodic oxidation process. The thermally sprayed film is formed on the rough surface with the alumite layer therebetween.

A component for use in a plasma processing apparatus, which is to be exposed to a plasma, includes a base material, an alumite layer and a thermally sprayed film. The base material has a plurality of through holes and a rough surface at which one end of each of the through holes is opended. The alumite layer is formed on a surface of the base material having the rough surface by an anodic oxidation process. The thermally sprayed film is formed on the rough surface with the alumite layer therebetween.

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

A coated gas turbine engine part includes a substrate and a calcium-magnesium-alumino-silicate CMAS protection layer present on the substrate. The layer includes a first phase of a calcium-magnesium-alumino-silicate CMAS protection material and a second phase including particles of an anti-wetting material dispersed in the first phase.