Abstract: The invention relates to a method of fabricating a turbine engine blade out of composite material comprising fiber reinforcement densified by a matrix, the blade comprising an airfoil, a platform situated at a longitudinal end of the airfoil, and at least one functional element projecting from the outside face of the platform. The method comprises: making a single-piece fiber blank by multilayer weaving; shaping the fiber blank to obtain a single-piece fiber preform having a first portion (302) forming a preform for the blade airfoil (320) and a second portion (314) forming a preform for the platform (340) and at least one preform for a functional element (352; 354); and densifying the fiber preform with a matrix. The second preform portion comprises a set of yarn layers interlinked by weaving with at least one zone of non-interlinking being provided to make it possible to deploy the functional element preform relative to the first platform preform.

Abstract: A process for producing a part provided with an external element includes: providing an electrically conductive substrate having an upper surface and a raised pattern with a crest on the upper surface; depositing an electrically insulating layer onto the upper surface around the pattern to a thickness less than or equal to the distance between the crest and the upper surface; depositing a metal layer onto the crest by galvanic growth so that the metal layer partly rests on the insulating layer; dissolving the insulating layer; covering an assembly including the substrate and the metal layer with a mass of a base material of the part to form an imprint; separating the mass and the metal layer from the substrate, the mass then exhibiting an external element formed by a recess, the shape of which corresponds to the imprint and the base of which interfaces with the metal layer.

Abstract: A method of manufacturing a rotary electric machine armature that includes a cylindrical armature core in which a plurality of slots that extend in an axial direction are disposed in a circumferential direction and a coil wound around the armature core, the slots having respective radial openings that open in a radial direction, and the coil being formed by joining a plurality of segment conductors to each other.

Abstract: Methods for manufacturing a tandem guide vane segment that includes an outer platform, a front guide vane, and a rear guide vane, wherein the front guide vane and the rear guide vane are arranged in a firmly fixated manner with respect to one another. One method includes manufacturing an integral front segment section that includes the front guide vane and a front section of the outer platform, manufacturing an integral rear segment section that includes the rear guide vane and a rear section of the outer platform, and connecting the two segment sections to each other.

Abstract: Provided is a method of disassembling a cold head provided with a displacer that extends in an axial direction, a cylinder that accommodates the displacer, and a displacer drive unit that is fastened to the cylinder and is connected to the displacer such that the displacer is driven in the axial direction, the method including mounting a lifting-up jig onto the displacer drive unit, unfastening the displacer drive unit and the cylinder from each other, and operating the lifting-up jig such that the displacer drive unit is lifted up from the cylinder together with the displacer.

Abstract: A nail plater apparatus includes at least one nail plate magazine configured to hold a plurality of nail plates, and at least one nail plate extractor assembly associated with the at least one nail plate magazine and configured to position at least one nail plate therefrom to at least one nail plate pressing area. A board feeder is configured to position a board to a board receiving area. At least one nail plate presser assembly is adjacent the board receiving area and aligned with the at least one nail plate pressing area and configured to press the at least one nail plate into the board.

Abstract: A fastening apparatus includes a fastening device (1, 3) that heats in a non-contacting state, and then applies pressure to, a shaft part (11b) or shaft body (111) while it is inserted through the through holes (W10, W20) of workpieces (W1, W2), thereby forming at least a second head part (11c) of a fastener (11). The fastening device (1, 3) includes: a fastening die (15) that forms the second head part (11c); and a shaft-part pressure-applying device (9) that applies the pressure to the fastening die (15). A determining device (5) determines whether the fastener (11) is defective or not by calculating a load curve defined by the time and the load during which the pressure was applied and then determining whether an amount of change per unit of time in the load curve after a reference load has been exceeded is within a range of a predetermined reference value.

Abstract: An assembly including a support tower and at least two support systems, each bearing a panel of a section of an aircraft fuselage and including four fixing points. The support tower includes a tower extending along an axis X, a seat on which the tower is mounted and which is rotationally mobile about the axis X, and, for each fixing point, a fixing base mounted on a three-dimensional adjustment system mounted on the tower and motorized to displace the fixing base in two horizontal directions and one vertical direction, where each fixing point and the associated fixing base can be locked with one another to ensure the fixing of one with the other, and that can be unlocked to allow them to be separated. Such an assembly makes it possible to keep the various elements of the section vertical during assembly and allows for a space saving on the ground and a saving on transfer utilities.

Abstract: A method for producing a bearing component includes providing a bearing component blank with an iron-based metal substrate, hardening the metal substrate, treating the metal substrate by an alkaline treatment bath in a region to form an iron oxide-based blackening layer as a conversion layer with an initial layer thickness (db) on the region, and rolling a spherical body over the region to compress the conversion layer in the region to form a bearing component with a protective layer having a final layer thickness (de) that is less than 95% of the initial layer thickness (db). The spherical body may be a component part of a hydrostatic finish rolling tool or a hydrostatic deep rolling tool. The spherical body may include a hard metal or a ceramic.

Abstract: A method for weight off wheel shock strut servicing includes deflating the shock strut, compressing the shock strut via a jack until the shock strut is in a compressed position, charging the shock strut with an oil until a pressure of the oil reduces a volume of a residual air located inside of the shock strut, lowering the jack until a shock strut piston reaches a pre-determined extension, and charging the shock strut with a gas until the gas comprises a pre-determined pressure.

Abstract: A method of making an axle sleeve includes forming a main body comprising a cylinder and forming an expansion member whereby a diameter of the main body may be varied. The method includes cutting an inner helical cutout comprising a first slit defined through the main body and extending helically from an inner edge of the main body, cutting an outer helical cutout comprising a second slit defined through the main body and extending helically from an outer edge of the main body, forming an inner edge remaining portion comprising an annular section of the main body unbroken by the inner helical cutout, and forming an outer edge remaining portion comprising an annular section of the main body unbroken by the outer helical cutout.

Abstract: A method is provided for manufacturing a component. This method includes additively manufacturing a crucible for casting of the component. A metal material is directionally solidified within the crucible to form a metal single crystal material. A sacrificial core is removed to reveal a metal single crystal component with internal passageways. A component is provided for a gas turbine engine that includes a metal single crystal material component with internal passageways. The metal single crystal material component was additively manufactured of a metal material concurrently with a core that forms the internal passageways. The metal material was also remelted and directionally solidified.

Abstract: A support frame (44) and method are described herein for support of a wind turbine blade (22) on a vehicle during transport to an installation site. A load indicator (46) is provided adjacent one or more support pads (52) when using the support frame (44), with the load indicator (46) being configured to determine and communicate an amount of movement of the wind turbine blade (22) relative to the support frame (44) during initial loading into the support frame (44) and during transport. To this end, the load indicator (46) helps assure that the wind turbine blade (22) is properly loaded into the support frame (44) in a desired transport position, while also confirming whether significant shocks or other movements have occurred during transport that could lead to a higher likelihood of internal or external damage at the blade (22).

Abstract: A method of manufacturing a valve body having one or more corrosion-resistant internal surfaces. The method involves performing a casting process, which includes pouring a first material into a mold box, to produce a valve body casting made of the first material. During the casting process, a layer of a second material is formed on one or more internal surfaces of the valve body casting, the second material having a higher corrosion resistance than the first material, by: (1) applying, with an additive manufacturing technique, the second material to one or more external surfaces of a core, and (2) inserting the core into the mold box. A portion of the first material binds to the second material on the one or more external surfaces of the core while the first material is poured into the mold box.

Abstract: A retention knob tool. A tubular body, is held in the tubular sleeve, and symmetrically formed around an axis. The tubular body also has an internal bore. Four locking ball retainer sockets are formed in the tubular body. A retention knob aperture is recessed within a top plate. Four balls are movably held in the ball retainer sockets. A tubular end stop is affixed to the tubular body rearward end. A drive tool cavity is recessed within the tubular body rearward end. The sleeve forward end includes a recessed circumferential portion bounded by a first thicker portion of the inside wall, where the first thicker portion bears against the balls when the tubular body is translated rearwardly into an inward lock position and the inward force is removed from the plurality of balls when the tubular body is extended forwardly into a release position.

Abstract: Methods for reworking structures and reworked cellular core panels, reworked structures comprising the reworked cellular core panels, and guides and cutting apparatuses for reworking cellular acoustic panels and reworking cellular acoustic and non-acoustic panels are disclosed.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: A fastening device template for joining mosaic pieces together having two variants that are easy to install by unskilled labor so as to help them achieve professional result. The device can be for assembling individual planks that together make up a floor covering such as solid wood flooring and engineered flooring, or it can be used for tiles. It can also be used to assemble individual parts which, together, create a piece of furniture. In this application, the generic term “mosaic” or “mosaic units” will be used to describe the individual pieces which, as indicated hereinabove, have a multitude of possible uses. Mosaic units can be assembled in all possible XYZ plans: side-to-side, side-to-face, side-to-end, end-to-end, end-to-face. In order to do so, the invention has an elongated clip core. At least one wing member attached to and extending a portion of the length of the clip core, and resilient leg members adapted to be frictionally inserted within a groove of a mosaic piece.

Abstract: A rocket engine includes a copper alloy combustion chamber, a non-copper weld transition ring welded to the copper alloy combustion chamber, and an injector assembly welded to the non-copper weld transition ring. The engine can be manufactured by forming the copper alloy combustion chamber using additive manufacturing, welding the non-copper weld transition ring to the copper alloy combustion chamber, and welding the injector assembly to the non-copper weld transition ring.

Abstract: A method of manufacturing a heat exchanger array that includes stacking a plurality of heat exchanger units in an aligned configuration with respective first ports of the heat exchanger units aligned. The heat exchanger units can include a first and second sheet coupled together to define an cavity between the first and second sheets; the first port at a first end of the heat exchanger unit defined by the first and second sheets; and a second port at a second end of the heat exchanger unit defined by the first and second sheets. The method further includes stacking the plurality of heat exchanger units in an aligned configuration with the first ports of the plurality of heat exchanger units aligned and generating a first plurality of respective couplings between adjacent sheets of adjacent heat exchanger units about adjacent first ports. The coupling can be generated by an adhesive.