Abstract: A method of forming a build in a powder bed includes providing a first diode laser fiber array and a second diode laser fiber array, emitting a plurality of laser beams from selected fibers of the second diode laser fiber array onto the powder bed, corresponding to a pattern of a layer of the build, simultaneously melting powder in the powder bed corresponding to the pattern of the layer of the build, scanning a first diode laser fiber array along an outer boundary of the powder bed and emitting a plurality of laser beams from selected fibers of the first diode laser fiber array and simultaneously melting powder in the powder bed corresponding to the outer boundary of the layer of the build to contour the layer of the build. An apparatus for forming a build in a powder bed including a first diode laser fiber array and a second diode laser fiber array is also disclosed. The first diode laser fiber array configured to contour the layer of the build.

Abstract: A blade fabrication method is provided and includes additively manufacturing a core, securing the core to a mandrel, electroforming a leading edge sheath directly onto the core and the mandrel and removing the mandrel from the core and the leading edge sheath.

Abstract: A compressible pillar for the preparation of a vacuum insulated glazing (VIG) unit, having a longitudinal extent in the pre-compressed state and including a deformable part having an open structure, which open structure will at least partially collapse when the pillar is subject to a compression force acting in the longitudinal direction of the pillar, the compression force being of at least one value selected within the range of 60 N to 320 N, the pillar will exhibit a partly irreversible deformation causing a reduction in the longitudinal extent of the pillar when the pillar is subjected to the compression force, so that when the compression force is fully released the pillar will exhibit an expansion in the longitudinal direction of the pillar which is less that the reduction in the longitudinal extent of the pillar. Further is shown a process for manufacturing of a compressible pillar, a method of producing a VIG unit as well as a VIG unit.

Abstract: The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:—S1: covering the core (1) by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,—S2: covering the core (1) by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;—S3: applying a heat treatment to the covered core (1) in such a way as to dry the solution and solidify the coating.

Abstract: The method for manufacturing timepiece hairsprings according to the invention comprises the following successive steps: a) forming hairsprings in a wafer, b) forming a thermal compensation layer on the hairsprings, c) identifying the hairsprings having a stiffness within a predetermined range, d) optionally, detaching from the wafer the hairsprings identified in step c), e) modifying the other hairsprings so that the stiffness of at least some of them is within the predetermined range, f) detaching from the wafer these other hairsprings and, if they have not been detached in step d), the hairsprings identified in step c). This method makes it possible to reduce manufacturing dispersions between the hairsprings.

Abstract: A repair method for self-detecting and self-healing of corrosion defects in metals can achieve self-detecting and self-healing repair of an initial corrosion defect and be used to repair a micron-level corrosion defect. Furthermore, the self-detecting and self-healing repair method can be used to effectively repair an initial corrosion defect in a large-sized high-precision structural component, thus effectively improving the service safety of the high-precision metal structural component and prolonging the service life of the same.

Abstract: A method (100) of mounting a blade (22) to or unmounting a blade (22) from a rotor hub (20) of a wind turbine (10), the wind turbine (10) comprising a tower (12) and a nacelle (16) mounted on the tower (12), the rotor hub (20) being coupled to the nacelle (16), the method (100) comprising gripping the blade (22) using a gripper (50), the gripper (50) comprising gripping members (58) configured for gripping the blade (22) and teeth (60) protruding from the gripping members (58), wherein gripping comprises inserting the teeth (60) of the gripper (50) into receptacles (78) of the blade (22); and rotating the blade (22) about a rotation axis (54) perpendicular to a longitudinal blade axis (53) using a blade rotation device (52) of the gripper (50), wherein the teeth (60) are configured for transmitting an axial load (57) of the blade (22) between the blade (22) and the gripping members (58).

Abstract: A pressure measuring device for a scale model for elastic similar structure of a wing in a large transport plane adopts a bracket for pressure measuring steel pipes formed by 3D printing, shapes of an upper surface and an lower surface of the bracket are completely the same as local airfoile profiles of a skin at required pressure measuring positions, and the upper surface and the lower surface of the bracket are bonded to the skin and wing beams; a pressure measuring hose is connected with the pressure measuring steel pipe, and the pressure measuring steel pipe is embedded into the bracket and fixed to it; the upper surface and the lower surface of the bracket are provided with semi-cylindrical convex structures; and the pressure measuring steel pipe extends out of the pressure measuring hole in the surface of the skin for pressure measuring steel pipe in the bracket.

Abstract: Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

Abstract: A lift system for a rotor blade of a wind turbine includes a lifting device having a structural frame body having a root end and a tip end. The root end supports a root cradle and the tip end supports a tip cradle. The root and tip cradles each have a profile that corresponds to at least one exterior surface of the rotor blade so as to receive and support at least a portion of the rotor blade. Due to a shape of the rotor blade, when the rotor blade is installed in the lifting device and lifted uptower, the rotor blade can experience an asymmetric loading. Accordingly, the lift system also includes a variable airflow assembly coupled to tip end of the lifting device. The variable airflow assembly includes at least one surface moveable between a plurality of positions having varying resistances so as to counteract the asymmetric loading.

Abstract: According to an embodiment, a method of correcting a bend of a joint type-turbine rotor comprises: measuring displacement of a convex portion of the bend at a joined portion of the joint type-turbine rotor or displacement of a surface opposite to the convex portion in a circumferential direction of the joint type-turbine rotor; heating the convex portion; and cooling the joined portion after the step of heating. The steps of heating and cooling are performed during the step of measuring.

Abstract: A walking aid accessory that is an aesthetic glider for a walker and a method of manufacturing.

Abstract: A lift system mountable in a nacelle of a wind turbine has a mounting interface removably securable to a generator in the nacelle of the wind turbine, and a knuckle boom rotatably and removably mounted on the mounting interface. The knuckle boom has an extendable boom arm having a translatable boom section slidably mounted on the boom arm. Modularity of the lift system permits lifting components of the lift system up to the nacelle using an existing service crane of the wind turbine, and rapidly dismounting the knuckle boom to permit closing doors of the nacelle in the event of inclement weather without dismounting all of the lift system components.

Abstract: The disclosure relates to a method for producing of refiner disc segments. The method for producing of the invention allows for forming a multitude of refiner segments with only one forming process of a first die which may be lightweight and has reduced cost while at the same time a surface structure with high hardness which reduces wear of the die's surface. The method for producing a disc-type refiner segment for refining lignocellulosic material includes 3D printing a first model; forming a first die part using investment casting; 3D printing a second model; combining the first die part and the second model to create a first die model; using the first die model to generate for forming a sand model by compressing molding sand between the first die and the second die; and casting a refiner disc segment by casting a metal material using the sand model.

Abstract: A method for manufacturing a planet gear or a sun gear of a gearbox of a wind turbine includes forming a base of the planet gear via at least one of casting or forging. The base of the planet gear includes an inner circumferential surface and an outer circumferential surface. Therefore, at least one of the inner circumferential surface or the outer circumferential surface of the planet gear includes a plurality of net or near-net gear teeth. The method also includes applying a coating material to at least a portion of the base of the gear and at least a portion of the plurality of gear teeth of the gear via an additive manufacturing process so as to increase a hardness of the portions of the base and the plurality of gear teeth that includes the coating material.

Abstract: A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.

Abstract: A method for the additive manufacturing of a component includes providing a powdered base material for a component, in particular a component for the hot gas path of a gas turbine, building up the component layer by layer on a building platform by fusing individual layers of the base material, and introducing an oxide dispersion strengthening into a region of the component to be additively manufactured by an oxidic additive, wherein the region is usually exposed to high thermomechanical loading during operation of the component.

Abstract: Systems, methods and containers for forming a beverage. A beverage container includes an enclosure arranged with a movable element that is movable to pierce a membrane and permit beverage material in the container to exit. The movable element can also be moveable to permit pressurized gas entry into the container and through the membrane. Gas can be introduced into the container to force beverage material to exit the container. A gas inlet port can be provided with the enclosure and arranged to mate with a gas source of a beverage machine.

Abstract: During a bonding process, a tip cap and an airfoil base are provided. The tip cap is arranged on the airfoil base. The tip cap is diffusion bonded to the airfoil base.

Abstract: A joint structure installed in the physical structure is provided. The joint structure includes a first latching member and a second latching member. The first latching member includes a first main body, a head portion extending from the first main body and a first convex portion extending from the first main body. The second latching member includes a second main body, a second convex portion extending from the second main body and a third convex portion extending from the second main body. When the first latching member and the second latching member are in an assembling status, the first convex portion slides between the second convex portion and the third convex portion.