An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.

The disclosure relates to turbomachine components which include one or more coating-capturing features for thermal insulation. A turbomachine component may include: a body having an exterior surface positioned within a hot gas path (HGP) section of a turbomachine; and a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature comprises: a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature, a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body, and an indentation positioned between the first and second members.

Casings and methods for manufacturing casings are provided. For example, a casing defining radial, axial, and circumferential directions is provided. The casing comprises an annular inner wall and an annular outer wall, each extending along the axial direction, with the outer wall radially spaced apart from the inner wall. The casing also comprises an auxetic structure extending from the inner wall to the outer wall and including a plurality of lattice elements. Each lattice element extends circumferentially and radially from the inner to the outer wall, and the lattice elements are axially spaced apart from one another. The auxetic structure may define at least one aperture for fluid flow from one portion to another of the auxetic structure and/or may be configured to vary the thermal characteristics of the casing along the axial direction. The casing may be integrally formed as a single monolithic component, e.g., by additive manufacturing.

A rotary-mechanical device, capable of extracting energy from a fluid flow and converting it into rotational motion, may comprise a turbine rotor. This turbine rotor may have an exterior surface extending between two opposing sides. The exterior surface may be formed of a plurality of straight lines, each spanning from a first edge, bordering one of the sides, to a second edge, bordering the opposite side. Each of the straight lines may be disposed in an individual plane running perpendicular to a rotational axis of the turbine rotor, wherein the rotational axis is positioned equidistant between the two sides. A turbine rotor of this type may be formed from a unitary mass by degrading the mass with a wire that may be translated and rotated relative to the mass during degradation.

A hybrid additive manufacturing process is utilized for creating a shrouded rotor with the shrouded rotor having a hub at a radial center, a shroud at a radial outer side, and vanes extending therebetween. The hybrid additive manufacturing process includes forming the shrouded rotor in stages, with a first stage being formed by depositing material in an axial direction through a first stage of the hub, machining an outer surface of the first stage of the hub to smooth the outer surface, depositing material on the first stage of the hub in a radial direction through a first stage of the vanes and the shroud, and machining all surfaces of the first stage of the vanes and an inner surface of the first stage of the shroud to smooth the surfaces. Subsequent stages of the shrouded rotor are formed similarly to the first stage.

A gas turbine engine component that includes a structure having a surface which includes multiple cooling channels having a width of 20-30 m and a depth of 25-50 m.

When a closed type impeller is manufactured from one block, a rough cutting process of cutting a flow path region of a block using a rough cutting tool, and a residue-cutting process of cutting a cutting residue in the cutting process using a residue-cutting tool are executed. The residue-cutting tool has a tool main body having a blade formed on an outer periphery thereof, and a handle having the tool main body fixed to a distal end thereof. A maximum outer diameter of the tool main body is larger than a minimum outer diameter of the handle. Further, the tool main body has a rear blade directed in a direction including a tool rear side component.

A component includes a structural member and an outer wall covering the structural member with a gap between the outer wall and the structural member. The outer wall includes an array of holes, each of the array of holes extending from an exterior surface of the outer wall to an interior surface of the outer wall. The outer wall includes an array of recesses on the interior surface of the outer wall, each hole in the array of holes terminating within one of the array of recesses of the outer wall.

The invention relates to a seal carrier for a turbomachine, in particular a gas turbine, having a carrier base and at least one seal body, wherein the at least one seal body is connected to the carrier base, and wherein the at least one seal body is formed by a plurality of cavities arranged next to one another, in particular uniformly, in the peripheral direction and in the axial direction, wherein the cavities extend out from the carrier base in the radial direction and are delimited by a cavity wall. According to the invention, the seal body has a plurality of damping portions which are designed to locally damp or disrupt the flow of force in the seal body, wherein the carrier base is continuous in the region of the damping portions.

The present disclosure is directed to a method for scaling an airfoil for placement in a turbomachine. The method disclosed herein includes radially scaling a master airfoil to form a scaled airfoil. The method may also include tuning the scaled airfoil. For example, tuning the scaled airfoil may include axially scaling. The scaled airfoil generally has similar characteristics to the master airfoil.