A method of making an impeller includes building the impeller in a layer by layer process in a build direction along the rotational axis starting from a base of the hub. The plurality of blades includes a plurality of perforated blades that support the shroud during additively manufacturing the impeller. The method can include installing the impeller in a fuel pump, air compressor, or the like, without removing the perforated blades from the impeller.

A rotating machine (100) of the present disclosure includes: a bearing (10); a rotating shaft (20) having a hollow portion (21) included in a portion (20s) supported by the bearing (10); a fluid element (30) attached to one end portion of the rotating shaft (20); an introduction hole (22) that is provided, in the rotating shaft (20), on a back side of the fluid element (30), and that directs a working fluid to the hollow portion (21); and a discharge hole (23) that is provided, in the rotating shaft (20), at a position distant from the introduction hole (22) beyond the portion (20s) supported by the bearing (10), and that directs the working fluid to an outside of the hollow portion (21).

An impeller of a rotating machine according to at least one embodiment includes: a disc; a cover disposed on an opposite side of a radial passage from the disc in an axial direction; and a blade disposed between the disc and the cover. A back surface of the disc has a recess extending in a circumferential direction in a radial range where the blade is disposed.

A compression ring for a shrouded compressor including a radially inner surface having one or more areas configured to mate flush with one or more portions of a radially outward surface of a shroud of the shrouded compressor, a radially outer surface located opposite the radially inner surface, a labyrinth seal located on the radially outer surface, a groove located within the radially inner surface, and a load ring located within the groove.

A tool (T) is provided with: a shaft-like tool body (11) having a first end portion (11a) extending along a central axis line (Ot) and attached to a main shaft, and a second end portion (11b) on an opposite side to the first end portion (11a); and a fore end portion (12) connected to the second end portion (11b) of the shaft-like tool body (11). The fore-end portion (12) includes a central portion (13) including a fore-end face (17) of the tool (T), and a plurality of blade portions (14) protruding radially outward from the central portion (13). A cutting blade of each blade portion (14) includes a main cutting blade (15) adjacent to the fore-end face (17). The main cutting blade (15) includes an outline that forms an angle of 30-150 degrees with respect to the central axis line (Ot) in a cross-sectional view including the central axis line (Ot).

A compressor assembly includes a compressor including a central shaft including an external surface, a shroud extending circumferentially around the central shaft. The shroud including a radially inward surface and radially outward surface located opposite the radially inward surface. The external surface of the central shaft and the radially inward surface of the shroud are in a facing spaced relationship forming a core flow path therebetween. The compressor also includes a plurality of blades extending from the central shaft to the shroud. The compressor assembly also includes a compression ring extending circumferentially around the shroud, the compression ring being in an interference fit with the shroud. The compression ring is configured to apply a radially inward compressive force along one or more portions of the radially outward surface of the shroud, the radially inward compressive is configured to compress the shroud and the plurality of blades into the central shaft.

A centrifugal blower includes an outer rotor, and a turbo fan. The turbo fan includes blades, an other end plate, and a cylinder portion. The cylinder portion is located inside the other end plate, and is fixed to the outer rotor. A surface of the outer rotor configures a rotor guide surface that guides an air flow toward a channel provided between adjacent blades. Each blade has a leading edge side portion located radially inside the cylinder portion. An outer end portion of the rotor guide surface in the radial direction is located at the same position in the axial direction as a one side cylinder end portion of the cylinder portion in the axial direction, in a state where a rotor contact portion of the outer rotor and a blade contact portion of the leading edge side portion are in contact with each other.

There is provided a compact turbine-compressor assembly 25. The turbine-compressor assembly 25 includes a turbine wheel 39 with one or more turbine blades 41 and a compressor wheel 47 that includes one or more compressor blades 49. The compressor wheel 47 is concentric with the turbine wheel 39. Furthermore, the compressor wheel 47 and the turbine wheel 39 are not located at opposite ends of a common axle with a medial portion of the axle distancing them apart, as is the case with prior art turbine-compressor assemblies that are known. In contrast, the turbine wheel 39 and the compressor wheel 47 are located adjacent to each other and in one embodiment they axially overlap each other so that one nests within the other to thereby provide a compact arrangement. The turbine-compressor assembly 25 includes a first fluid path 67 which is configured to convey fluid, which will typically be air, through the turbine blades 41. The turbine-compressor assembly 25 also includes a second fluid path 77 which is configured to convey fluid, which will typically be air, through the compressor blades. The turbine-compressor assembly 25 is arranged so that the first fluid path 67 is distinct from the second fluid path 77 and vice-versa.

A rotor for a rotary machine in includes a hub centered on a central axis and having a disk portion and a shaft portion, a blade extending outward from the hub, and a variable lattice structure in an interior of the rotor. The variable lattice structure includes a first region of the rotor having a first lattice structure and a second region of the rotor having a second lattice structure. The second lattice structure of the second region is denser than the first lattice structure of the first region. The second region is a deflection region or a stress region of the rotor.

A compressor bleed port apparatus includes: a compressor shroud which defines a boundary between a primary flowpath and a plenum; a bleed port including one or more apertures passing through the compressor shroud, each of the one or more apertures having an inlet communicating with the primary flowpath and an outlet communicating with the plenum, and extending along a respective centerline. Each of the one or more apertures is bounded by sidewalls, and includes a diffuser section in which the sidewalls diverge from each other in a downstream direction; A diffusing angle between the sidewalls varies over the length of the diffuser section.