CMC components having microchannels and methods for forming microchannels in CMC components are provided. For example, a method for forming microchannels in a CMC component comprises laying up a plurality of body plies for forming a body of the CMC component; laying up a microchannel ply on the plurality of body plies that has at least one void therein for forming at least one microchannel; laying up a cover ply on the microchannel ply to define an outer layer of the CMC component; and processing the laid up body plies, microchannel ply, and cover ply to form the CMC component. In another embodiment, the method comprises applying an additive matrix to the body plies to define at least one microchannel. In still other embodiments, the method comprises machining at least one microchannel in the plurality of body plies.

Provided are a nickel-base alloy having high high-temperature strength, a turbine blade using same, and a method for producing an injection molded article of the nickel-base alloy. The nickel-base alloy contains: at least one metal element from among chrome, molybdenum, and niobium; nickel; aluminum; and carbon. The nickel-base alloy comprises a plurality of crystal grains and a plurality of precipitates. The areas between the individual crystal grains in the nickel-base alloy, i.e., the boundaries of the individual crystal grains serve as crystal grain boundaries. The crystal grains are crystals in which nickel is the primary component. The precipitates are precipitated on the crystal grain boundaries. The precipitates are carbides comprising: at least one metal element from among chrome, molybdenum, and niobium; and carbon. The carbides have a diameter of 0.1-10 m and an aspect ratio of 3 or more.

A mold used to mold a molded product includes a mold surface that contacts a material, a plurality of convex structures are formed on the mold surface, at least one of a corner part of a first convex structure among the plurality of convex structures and a boundary part between adjacent first and second convex structures among the plurality of convex structures includes a curved surface, in a case where a radius of curvature of the curved surface included in at least one of the corner part and the boundary part is R, a pitch of the convex structures is P, and a height of the convex structures is H, a condition 1 micrometer<R<4 micrometers is satisfied, and at least one of a condition 5 micrometers<P<200 micrometers and a third 2.5 micrometers<H<100 micrometers is satisfied.

A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections on the inner and/or outer shroud protrude into the annular gas path, each projection being at least partially circumferentially disposed between two variable vanes and located adjacent the overhang portion thereof. The projections have an angled planar surface that is substantially parallel to a plane defined by a terminal edge of the overhang portion of the variable vanes when pivoted through a vane pivot arc.

A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.

The present disclosure generally relates to turbine engine components having multiple controlled metallic grain orientations. In general, the primary grain orientation is aligned substantially perpendicular to the longitudinal axis of the turbine engine component while the secondary grain orientation is aligned substantially parallel to the longitudinal axis. Such controlled grain orientations provide the blades and vanes with increased strength to withstand the thermal-mechanical stresses of the turbine operation. The disclosure also relates to turbines having these fortified components, and methods of manufacturing the components.

An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.

The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mold in order to produce a blank (3); and b) machining the blank in order to produce the parts,
characterized in that the blank obtained by casting is a solid polyhedron having first and second sides (30a, 30b) and third and fourth sides (30c, 30d), in which the third and fourth sides extend between the first and second sides, flaring apart from the first side towards the second side, first at a first angle and subsequently at a second larger angle, and said at least one part is machined in the blank.

Provided is a method of fabricating an article, including deforming an ingot of a nickel-based superalloy to form an intermediate article, forming a substantially homogeneous dispersion of Laves phase precipitates within the intermediate article, wherein the Laves phase precipitates are present at a concentration of at least about 0.05% by volume and the precipitates have a mean diameter of less than one micron. Also provided is a nickel-based superalloy including a substantially homogeneous dispersion of Laves phase precipitates, wherein the intergranular and transgranular Laves phase precipitates are present at a concentration of at least about 0.1% by volume and wherein the precipitates have a mean diameter of less than one micron. Precipitation of Laves phase may control microstructure during Thermo-mechanical processing and produce superalloys with refined grain size.

A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.