An attachment device attaches a plurality of attachment target members to an attachment portion formed in a circumferential direction of a rotating main body portion. A first measurement unit measures a physical amount concerning a perimeter of the attachment portion. An attachment unit attaches, to the attachment portion, the plurality of attachment target members selected based on the physical amount concerning the perimeter measured by the first measurement unit. A second measurement unit measures a physical amount concerning a gap between the adjacent attachment target members to be attached by the attachment unit.

A manufacturing system manufactures a rotating assembly by attaching a plurality of attached target members in a circumferential direction of a rotating main body portion. A storage member capable of storing the plurality of attached target members is placed on a stand. A measurement device measures a physical amount of the attached target member An attachment device attaches one attached target member to a predetermined position in the circumferential direction of the rotating main body portion based on the physical amount measured by the measurement device A transfer device transfers the attached target member.

A method of hyper-feed machining the bladed components of turbomachines, and more specifically their bladed components. Hyper-feed machining, by means of the physical process of controlled fracturing, is the fastest, most precise, and nearest net shape method of machining in existence. The practical effects of the invention are: (1) the production of new and useful small-scale gas turbine engines for a wide range of previously impossible or impractical applications, and (2) the production of existing larger-scale gas turbine engines with great improvements in material removal rates by orders of magnitude, greater precision and geometric complexity of the bladed components, faster overall rates of production of these engines, and significantly reduced costs in production. As a consequence, the best preferred embodiment of the invention is the small-scale turboshaft electric engine for automotive vehicles, which makes possible a turbo-electric vehicle that replaces both the electric battery vehicle and the piston-engine vehicle.

Various implementations include a ring material used for producing a ring molded article. The ring molded article has two convex portions which respectively protrude on opposite sides of the ring molded article in a direction of a center axis thereof and extend in a direction of a circumference of the ring molded article. A straight line passing through centers of gravity of first and second side regions is inclined by an angle relative to the center axis of the ring material, the first and second side regions are obtained by virtually dividing a one half section of the ring material based on a middle of a maximum height of the ring material in the direction of the center axis of the ring material, and a range of the angle is 7 degrees to 40 degrees.

A bladed rotor wheel of an aero turbine stage includes a portion of a rotor blade with a shank portion and a bottom surface; a portion of a forged rotor disk with a rim portion and an outer surface; and a joining structure provided by an additive manufacturing process configured for integrally merging the portion of a rotor blade with the portion of a forged rotor disk. An aero turbine can include such bladed rotor wheel, and an aircraft can include such aero turbine.

A method including bending an elongate portion of a flat strip of metallic material into a ring about an axis extending parallel to a thickness of the elongate portion of the strip of metallic material. The method includes fixing end portions of the ring together to form a flat ring, the flat ring having opposite flat side surfaces, a radially inner surface, a radially outer surface, a pair of radially inner edges, and a pair of radially outer edges, wherein the pair of radially inner edges connect the radially inner surface and the opposite flat side surfaces and the pair of radially outer edges connect the radially outer surface and the opposite flat side surfaces. The method includes connecting a plurality of curved blades to the flat ring and connecting a hub support to the curved blades at a position spaced from the flat ring along the curved blades.

In one aspect, a fan assembly is provided that can be manufactured while producing a significantly reduced amount of scrap material. More specifically, the fan assembly utilizes a hub ring and one or more hub strips to support a plurality of blades rather than a solid center disc or end disc used by some prior approaches. In another aspect, a method is provided that includes bending a member into an annular configuration and joining end portions of the member together to rigidly fix the member in the annular configuration. The rigid annular member may be used as an end ring, a hub ring, an orifice, or other component, while producing significantly less scrap material than traditional approaches.

An installation for pre-assembling the turbine stators of a turbine each formed of several juxtaposed sectors, includes: an input carriage for conveying sectors intended to form the turbine stators. Each sector includes side faces provided with slots and being associated with a given turbine stator; an output carriage having various trays, each associated with a turbine stator; an automated device for inserting sealing pads configured to interact with a sector conveyed by an automated convey pallet, comprising a robot arm for inserting sealing pads into the slots in a side face of the sector; and another robot arm for gripping a sector equipped with pads from a pallet and depositing it on the tray associated with the turbine stator to pre-assemble the turbine stator.

The disclosed embodiment is related to a manufacturing method of a die-formed 3-dimensional plastic impeller of a centrifugal pump and the impeller manufactured thereby, including a mold for twisted blade and a mold for impeller outlet, the mold for twisted blade is configured to form a twisted blade portion of each blade of the impeller, the mold for impeller outlet is configured to form a rear portion of each blade, a hub rim part of the impeller, and a shroud rim part of the impeller so that the hub rim part, the shroud rim part, and the blades are formed in a single piece at the same molding process.

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.