Abstract: A method of loading a superstrate onto a superstrate chuck includes raising a plurality of pins located radially outward of a substrate chuck from a retracted position to a receiving position, placing the superstrate onto the plurality of pins while the plurality of pins are in the receiving position, and coupling the superstrate with the superstrate chuck while the superstrate is on the plurality of pins.

Abstract: The preset invention is to mold a laminate at a high accuracy by appropriately generating slippage between fiber sheets of the laminate at bending. A method for molding a laminate includes a step in which a plurality of gripping parts, which are arranged apart from each other, grip an area, wherein slippage between fiber sheets is prevented, in a plate-shaped laminate including a plurality of fiber sheets laminated each other; a step in which the plurality of gripping parts grip the area wherein slippage between the fiber sheets is prevented, while maintaining the state wherein relative moving of the area of the laminate and the gripping parts is prevented; and a step in which the gripping parts move so as to subject the laminate to bending.

Abstract: A manufacturing process for blades of a turbomachine, e.g. a gas turbine engine for an aircraft. In the process: a) a ceramic core piece that comprises at least two ceramic core elements and a clamping part that connects the ceramic core elements, is positioned in a wax forming device, subsequently; b) a molten wax material is applied to the outside of the ceramic core piece in the wax forming device and the wax is allowed to solidify, and subsequently; c) at least two turbomachine blades are cast using a crystallographically-oriented metal casting process and the wax and the ceramic core piece are removed.

Abstract: In an example, a system is disclosed. The system comprises a one-piece mandrel, a fuselage coupled to the one-piece mandrel, and a strongback apparatus positioned on the fuselage. The strongback apparatus comprises an arcuate central body comprising a front end, a rear end, and a plurality of elongated members that connect the front end to the rear end, and actuators mounted to the plurality of elongated members. The actuators are configured to move in a radially outward direction from extended positions to retracted positions and comprise (i) proximal ends mounted to the plurality of elongated members and (ii) distal ends having vacuum suction cups. In the extended positions, the vacuum suction cups engage the fuselage on which the strongback apparatus is positioned. As the actuators moves from the extended positions to the retracted positions, the vacuum suction cups pull the fuselage away from the one-piece mandrel.

Abstract: A device (100) for extracting an adjuster unit (20) of a brake assembly (25), which includes a shaft (22), a gear (24), and a sleeve (26), includes an insert (102) configured to be partially inserted between the peripheral wall (26a) of the sleeve (26) and a proximal end (22a) of the shaft. The insert (102) includes an engaging section (104) for engaging the sleeve (26) and an inner volume (106) for receiving the proximal end of the shaft (22). An actuator (108) is operatively coupled to the insert (102) and transmits an extraction force (F) so as to move the insert (102) and at least the sleeve (26) away from the brake assembly. The sleeve (26) has a sealing lip (26b) extending radially inwards from the peripheral wall of the sleeve (26), and the insert (102) includes a groove (107) configured to engage the sealing lip.

Abstract: Systems and methods are provided for assembling a structure. The systems and method including micro pulsing a structure along a track in a process direction by less than a length of the structure. The structure is indexed to one or more work stations by mating indexing features in a manufacturing excess of the structure to complementary features at the work stations. The work stations would the perform work on the structure at the work stations while the structure is indexed to the work stations. Iteratively repeating the micro pulsing and indexing and working upon the structure until it is ready to advance to the next assembly process.

Abstract: The present invention relates to a method of manufacturing a labyrinth sealing device mounted between a diaphragm and a turbine rotor of a turbine in order to induce smooth rotation of the turbine rotor and prevent a leakage of gas by minimizing friction between a rotor, such as the turbine rotor, and a stator, such as the diaphragm, when the rotor rotates in the stator, wherein the labyrinth sealing device includes a ring-shaped body and a labyrinth part protruding from one surface of the ring-shaped body, the ring-shaped body is manufactured by centrifugal casting or ring mill, and the labyrinth part is manufactured by 3D printing. The method of manufacturing a labyrinth sealing can improve productivity by reducing material costs and machining costs by manufacturing the labyrinth part (or teeth) protruding from the ring-shaped body using three-dimensional printing after manufacturing the ring-shaped body by centrifugal casting or ring mill.

Abstract: Disclosed is a method for dismantling a wind turbine gearbox (15) from a main shaft (7) in the nacelle (3) of a wind turbine (1), wherein a first end (11) of the main shaft (7) is connected to the gearbox (15) in a connection cavity (22) of the gearbox (15) and a second end (12) of the main shaft (7) is connected to a rotor (4) of the wind turbine (1).

Abstract: This assembly includes a plurality of stacked circular members, and a fixing pin that is disposed inside each of the circular members to arrange and integrate each of the circular members in an axial direction thereof. The fixing pin includes a shaft portion extending in the axial direction, a flange portion extending radially outward from one end side of the shaft portion, a recessed portion that is provided on an end face of the shaft portion on the other side and has a non-circular cross-section orthogonal to the axial direction, and one or a plurality of protruding portions that are provided on an outer circumferential portion of the shaft portion on the other end side and protrude radially outward from an inner circumferential surface of each of the circular members.

Abstract: A process for repositioning a drug-coated stent that is pre-crimped on a balloon of a balloon catheter extending in an axial direction so that an inner surface of the stent lies against an outer surface of the balloon. The stent is gripped with at least one contact element and a protection device between the stent and the at least one contact element to prevent contact between the stent and the at least one contact element. The stent is moved with the at least one contact element in the axial direction with respect to the balloon of the balloon catheter to reposition the stent with respect to the balloon.

Abstract: Systems and methods of making a cast steel alloy crankshaft for an internal combustion engine are provided. The method comprises providing a mold of the crankshaft. The mold has cavities to form the crankshaft. The method further comprises melting a first metallic material at between 1400 degrees Celsius (° C.) and 1600° C. to define a molten metallic material. In addition, the method further comprises feeding the molten metallic material at a riser connection angle of between 30° and 75° in the cavities of the negative sand cast mold. The method further comprises cooling the molten metallic material at a solidification time of between 5 seconds (sec) and 20 sec in the negative sand cast mold with at least one chill member to define a solidified metallic material having dimensions of the cast steel alloy crankshaft. Furthermore, the method comprises separating the solidified metallic material from the negative sand cast mold to define the cast steel alloy crankshaft.

Abstract: This method of manufacturing an outer case for a hot water unit involves a pressing step for subjecting a flat metal plate (30a) to press processing to form a component part (3) of the outer case (C), and a painting step for painting text, symbols, figures or patterns on the component part (3), wherein the painting step involves an inkjet printing step for forming an inkjet printing layer (4) by performing inkjet printing on the flat metal plate (30a). The pressing step is performed after the inkjet printing step, and after the pressing step, there is further a clear coating step for forming a clear layer (5) on the inkjet printing layer (4).

Abstract: A hub assembly for construction of a fan includes a hub plate having a front face, a rear face, and an annular surface extending between the front face and the rear face. The hub plate defines a hub assembly axis extending through the front face and the rear face which is configured to coincide with the fan axis. The hub assembly further includes a plurality of elongated root sections that are circumferentially spaced apart and extend radially from the annular surface. The elongated root sections have a substantially circular cross-section. The hub plate and the plurality of elongated spokes are unitarily formed.

Abstract: A joining device comprises a die and driving means. A first concave portion is recessed in a substantially cylindrical shape in a driving direction on the die, and a second concave portion is recessed in the driving direction in a central portion on a bottom face of the first concave portion. A portion on an external side of the second concave portion on the bottom face of the first concave portion forms a terrace portion that is shallower than the second concave portion, and a diameter of the foot portion of the self-piercing rivet corresponds to a diameter of the terrace portion. In driving the foot portion of the self-piercing rivet toward the terrace portion of the first concave portion, the foot portion of the self-piercing rivet is spread outward by the terrace portion and a part of the members to be joined runs into the second concave portion.

Abstract: A first member and a second member are formed of metal materials of the same type and a third member is formed of a material of a different type that is difficult to weld to the first member and the second member. The first member and the second member are welded to each other via a through hole with the third member interposed therebetween in a region corresponding to a first protrusion. For the first member and the third member, and the second member and the third member, each of respective outer peripheral portions of an overlapping portion of the first member and the third member and an overlapping portion of and the second member and the third member is welded.

Abstract: A method and equipment for forming a front toothing having a plurality of radial teeth on an annular collar of an inner ring of a wheel hub, wherein a plurality of first knives are axially and sequentially impressed on the annular collar and have a first predetermined circumferential profile (P1) configured to form radial reliefs which are spaced by imprints and have a rounded circumferential profile corresponding to the profile of the ridges of the radial teeth to be obtained; thereafter, a plurality of second knives are axially and sequentially impressed on the annular collar inside the imprints and have a third predetermined circumferential profile (P3) configured to reproduce in reverse at least part of respective opposite flanks of the radial teeth of the front toothing to be obtained.

Abstract: Systems and methods are provided for assembling an airframe of an aircraft, including receiving a half barrel section of fuselage, advancing the half barrel section in a process direction across multiple stations to separately and simultaneously perform work on the half barrel sections, and subsequently joining the half barrel segments to form a section of the airframe. Each pair of half barrel sections, such as upper and lower half barrels, are progressed through assembly line processes to be delivered to a joining station for joining the half barrels together to form a circumferential section of the fuselage. Multiple joined circumferential sections are joined together to form an elongated extent of the fuselage. Indexing features are provided in the assembly process to monitor and control the progression of the half barrel sections in the work stations of the assembly line process.

Abstract: A method of manufacturing a casing of an electronic device including the following steps is provided. A metallic housing is provided, wherein the metallic housing has an inner surface and an outer surface opposite to the inner surface and includes a back region and at least one side region. At least one gap, a plurality of apertures and a non-conductive layer are formed on the inner surface of the metallic housing, wherein the apertures is formed on a surface of the at least one gap, part of the non-conductive layer is formed in the at least one gap and extended from the back region to the at least one side region, and part of the non-conductive layer is extended into the apertures. Part of the metallic housing is removed for exposing part of the non-conductive layer, thereby forming a plurality of non-conductive spacers located in the at least one gap.

Abstract: A method for making a catheter. The method includes forming a catheter tube including an outer wall circumscribing at least one lumen and having a closed distal end, and creating a slit valve in a distal segment of the catheter tube proximal of the closed distal end. The slit valve includes a slit through the outer wall and a compliant segment designed to facilitate inward deflection of a portion of the outer wall along the slit when negative pressure is applied to the at least one lumen. The compliant segment is circumferentially spaced apart from the slit.

Abstract: The present disclosure provides a method of manufacturing a damper for a vehicle. The method includes forming a groove on an outer surface of a first component in a first annular region. The first component is tubular. The method further includes inducing a compressive residual stress in a second annular region. The second annular region is at least partially aligned with the first annular region along a longitudinal axis of the first component. The method further includes coupling a second component to the first component. Surfaces of the first component and the second component directly engage one another at an interface. The second component is axially aligned with and radially surrounding at least a portion of the first annular region. In some configurations, forming the groove and inducing the compressive residual stress are performed concurrently, such as by low plasticity burnishing.