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.

A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.

A processed article is manufactured with a tool including a cutting blade. The cutting blade is arranged to be in contact with two machined segment surfaces so that two contact points are defined between the two machined segment surfaces and the cutting blade in a corner. A machining pitch is set in a pick feed direction of the tool at the corner to a first machining pitch for when a part of the cutting blade corresponding to a projected shape of a side surface of the cutting blade having a first curvature radius is a cutting point. A cut is performed along a feed direction in the two adjacent machined segment surfaces successively at the corner so that the tool proceeds toward the corner in one of the machined segment surfaces and away from the corner in the other one of the machined segment surfaces.

In an inner pipe assembly step, sheet-metal-made inner-pipe divided bodies and a cast inner-pipe divided body are connected to assemble an inner pipe. In a center flange connecting step, the sheet-metal-made inner-pipe divided bodies are connected to a center flange. In an outer pipe connecting step, an outer pipe covering the inner pipe is connected to the center flange and an exhaust-air-inlet-side flange. In a masking step, at least one of: a connected portion between the sheet-metal-made inner-pipe divided bodies and the cast inner-pipe divided body; or an opening portion between the outer pipe and the inner pipe is sealed. In a cutting machining step, an inner wall surface of the cast inner-pipe divided body facing the turbine wheel is subjected to a cutting machining after the masking step.

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 shrouded rotor constructed through a hybrid additive manufacturing process. The shrouded rotor including a hub at a radial center having an outer surface forming an inner wall of a flow path, a shroud at a radial outer side having an inner surface forming an outer wall of the flow path, and vanes extending within the flow path between the hub and the shroud. The outer surface of the hub, the inner surface of the shroud, and all surfaces of the vanes have a surface roughness average of less than 32R.sub.a.

A seal assembly includes a first feather seal with a first cooling hole extending through the first feather seal. The seal assembly also includes a second feather seal adjacent to the first feather seal. The second feather seal includes a second cooling hole extending through the second feather seal. The first cooling hole is positioned over at least a portion of the second cooling hole.

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.

The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage delimited in part by an intrados wall and an extrados wall of the vane, there being flow-disturbing lugs, made as one piece with one of the intrados and extrados walls, passing across the passage. According to the invention, in any plane of section passing orthogonally through the lugs, the space defined between these lugs has a geometry defined exclusively by a set of annulus shapes of the same dimensions, partially overlapping one another and each in part delimiting at least two of these lugs.

A vane strut positioning and securement system includes a housing including a washer aperture defined in an inner diameter thereof and a lock washer disposed within the washer aperture of the housing, the lock washer configured to lock a vane strut orientation under compression against a vane strut washer. The washer aperture is defined partially through a thickness of the housing, and the housing includes a strut post opening defined through the housing from the inner diameter to an outer diameter of the housing.