Abstract: A segment of an abradable ring seal for a turbomachine, includes: a reinforcing support; a composite fabric including fibers impregnated with polymerized resin, and a track of abradable material. The composite fabric is interposed between the reinforcing support 71 and the track of abradable material and is bonded to the reinforcing support, on the one side, and to the track of abradable material, on the other side. The segment of an abradable ring seal has a resistance to tearing in a direction perpendicular to the interface between the track of abradable material and the composite fabric, on the one hand, and between the composite fabric and the reinforcing support, on the other hand, greater than 5.106 newtons per square meter. A process for the manufacture of such a segment is also described.

Abstract: The present invention relates to a preparation method of a tungsten carbide sintered body for a friction stir welding tool used in a friction stir welding tool of a high melting point material such as steel, titanium and the like or a dissimilar material such as aluminum, magnesium-steel, titanium and the like. The preparation method comprises the following steps: filling a tungsten carbide (WC) powder in a mold made of a graphite material; mounting the mold filled with tungsten carbide powder in a chamber of a discharge plasma sintering apparatus; making a vacuum inside of the chamber; molding the tungsten carbide powder while maintaining a constant pressure inside the mold and increasing the temperature according to a set heat increase pattern until the temperature reaches a final target temperature; and cooling the inside of the chamber while maintaining the pressure pressurized in the mold after the molding step.

Abstract: A method for preparing a fiber-reinforced composite article initially performs a trial molding by a molding machine to prepare a trial composite article of a composite molding material including a polymeric material having a plurality of fibers, wherein the trial composite article has a trial fiber orientation distribution. The method further generates a predicted fiber orientation distribution fitting with the trial fiber orientation distribution, wherein the predicted fiber orientation distribution is generated by performing a first molding simulation for the trial composite article by using physical rheology parameters and physical fiber orientation parameters.

Abstract: The present invention provides an in-mold detachable marking device which does not lock rotation of an index body even when the index body is repeatedly rotated to switch marking indications.

Abstract: A method for spreading a resin paste onto a carrier film includes feeding resin paste into a doctor blade unit having a doctor blade, using a feed device that includes a discharge opening through which the resin paste is fed from the feed device into the doctor blade unit, moving a carrier film on a base surface through a doctor blade gap that is formed between the doctor blade and the base surface, and spreading the resin paste onto the carrier film using the doctor blade. The discharge opening is positioned to be immersed into the resin paste that is in the doctor blade unit during operation of a doctor blade apparatus configured to perform the method. A resin mat installation for producing resin mats, particularly of SMC, includes at least one doctor blade apparatus as described above.

Abstract: A control mechanism for maneuvering an end effector is provided. The control mechanism comprises multiple actuator assemblies, multiple arm assemblies, and the end effector. Each of the multiple arm assemblies connect the end effector and the multiple actuator assemblies respectively. Each multiple actuator assemblies controls the movement of the multiple arm assemblies independently. One of the arm is rotated by a tool actuator where the rotating motion of the rotating arm drives a tool attached at the end effector. The control mechanism positions the tool actuator away from the end effector, thereby operating the tool at a remote location away from the end effector.

Abstract: A mold may include a plurality of nanostructures configured to form a lithographic pattern when imprinted into a material. Imprinting may include imprinting the mold a first predetermined distance, modifying a temperature of the material, and altering a position of the mold based on the temperature modification. One or more thermal elements may alter a temperature of a first section of the material and/or one or more nanostructures for a predetermined pulse time less than an equilibrium time required for the mold and/or material to reach a stable temperature state. A first thermal element may selectively alter the temperature of a first section of the material and/or a first nanostructure and a second thermal element may selectively alter the temperature of a second section of the material and/or a second nanostructure. The one or more thermal elements may include one or more thermoelectric elements.

Abstract: A utility glove formed of a glove blank of a fabric material in the shape of at least a portion of a hand having one or more areas of elastomeric material injection molded thereon to form one or more three dimensional molded portions, the three dimensional molded portions being the fabric material with the elastomeric material bonded thereto, wherein one or more three dimensional molded portions leave at least one area of fabric material of the glove blank without elastomeric material bonded to the fabric. The fabric material of the glove blank can be made from one or more fabrics, a treated fabric, a coated fabric or combinations thereof, or the fabric may have a portion with a coating on an area without elastomeric material.

Abstract: A method of fabricating a connecting rod (6) out of composite material using three-dimensional fabric of woven reinforcing fibers, the connecting rod (6) extending in a main direction. The method comprises the steps of: cutting out one or more base pieces (7, 8) from a three-dimensional fabric; cutting out one or more reinforcing pieces (9, 10) from a three-dimensional fabric; installing the various pieces (7, 8, 9, 10) on a support in order to shape them; securing the various pieces (7, 8, 9, 10) to one another by stitching (12, 13, 14, 15) using reinforcing fibers in order to constitute a reinforcing fiber preform; installing the preform on a mandrel; and injecting resin into the preform and polymerizing the resin.

Abstract: A fiber reinforced composite structure includes multiple plies of pre-impregnated fiber reinforced material. Consecutive plies are layered such that the fibers of one ply are at 90 degrees relative to the fibers of a proximate ply, and such that the fibers of each ply are oriented at positive or negative 45 degrees with respect to a reference plane of the fiber reinforced composite structure. In a method for fabricating a fiber reinforced composite structure, pre-impregnated fiber reinforced composite plies are layered into a tool layup. Each ply is cut on the bias at either plus 45 degrees or minus 45 degrees. The bias angles of the layered plies alternate one relative to the next. The layered plies are cured after layering.

Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface. There is no intersection between the first machining surface and the fibers of the main fiber structure.

Abstract: A molded piece 25 of abradable material for use in the manufacture of a segment of an abradable ring seal for a turbomachine includes a mixture of epoxy resin and crosslinking agent. The piece 25 has a curved shape and dimensions adapted to correspond to a receiver provided for that purpose in the inner surface of a casing of a fan of a turbomachine. A process for the manufacture of such a piece is also described.

Abstract: A method of making a carbon binder-reinforced carbon fiber composite is provided using carbonized asphaltenes as the carbon binder. Combinations of carbon fiber and asphaltenes are also provided, along with the resulting composites and articles of manufacture.

Abstract: Apparatus and methods provide for the construction of wing sections having multi-box wing spars. According to one aspect of the disclosure provided herein, an aircraft wing may be constructed by applying one or more layers of composite material onto a plurality of wing mandrels. The wing mandrels, when placed together, form the shape of the wing. After the layers of composite material are applied to each individual mandrel, the mandrels are abutted together. Thereafter, the mandrels are compressed using wing surface tooling applied to the plurality of wing mandrels. The composite material is thereafter cured. After curing, the wing surface tooling and mandrels are removed, resulting in a wing having multi-box wing spars and skin.

Abstract: An integrated composite trailing edge and its method of manufacturing. The trailing edge comprises an integrated main structure having an upper cover, lower flanges, and a set of ribs extending between the upper cover and the lower flanges, with a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure. The method comprises the steps of providing a set of prepreg laminated preforms over a set of tool modules having a hollow so that each laminated configures a double C-shaped laminated preform having an upper section with a recess, two primary and secondary flanges, the upper section partly forming the upper cover, the two primary flanges partly forming the ribs and the two secondary flanges forming the lower flanges.

Abstract: A laser capsule marking system and method may comprise at least two indexing wheels, a feeding mechanism, a laser marker, a first inspection system, a rejection subsystem, a reject verification sensor, and a collection device. The wheels are coaxial and have respective circumferential peripheries with multiple open pockets distributed thereabout. Each pocket is configured to releasably receive a pharmaceutical capsule doped with pigment particles reactive to laser light. The indexing wheels are configured to be incrementally rotated in alternating indexing fashion for transporting discrete arrays of respective pockets through a loading zone, an inspection zone, a marking zone, a reject zone, and an unloading zone. An actuatable reject block may be provided to simultaneously blow a rejected capsule from its pocket, and draw it in for transport to a rejection bin. Each circumferential periphery may be comprised of multiple arcuate shoes removably and replaceably secured to their respective indexing wheel.

Abstract: A method for manufacturing a thick turbine engine part in a composite material by injection of resin under pressure. A fiber preform is positioned in a mold, a resin composition is injected into the mold, the resin composition is polymerized in the mold so as to obtain the part, and the part is removed from the mold. Prior to the injection of the resin composition, a mold release shim is inserted between the fibrous preform and a wall of the mold, and between the polymerization of the resin composition and the removal of the part from the mold, the mold release shim is extracted.

Abstract: According to a molding method for a fiber reinforced composite material, a cavity forming surface 13 of a second mold 12 with a recessed portion 14 for molding a thick portion is brought into contact with a fiber reinforced composite material 15. The fiber reinforced composite material 15 is heated in a state in which the temperature of the cavity forming surface 13 is higher than that of a cavity forming surface 11 of a first mold 10. After that, the first mold 10 and the second mold 12 are closed with a pressure to the fiber reinforced composite material 15 so as to pass the fiber reinforced composite material 15 into the recessed portion 14. This can integrally mold the thick portion with the main body of a molded component.

Abstract: A method of fabricating a wind turbine blade tubular spar, wherein the tubular spar extends along a designated axis, is made of reinforced polymer material having fibers arranged in at least two directions, and a polymer matrix incorporating the fibers, and has two caps and two webs; the method including the steps of: molding and cross-linking at least part of a cap or web in composite material; molding and cross-linking an L-shaped structure, which has two opposite parallel flanges, and at least partly incorporates the previously molded, cross-linked cap or web of composite material; repeating the above steps to mold and cross-link a further L-shaped structure; and joining the two cross-linked, L-shaped structures, with the flanges positioned facing in pairs.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for manufacturing an airfoil component. The system can include: a geometrical mold; an elongated flexible sleeve having a closed-off interior and positioned within the geometrical mold, wherein the elongated flexible sleeve is further positioned to have a desired geometry; an infusing channel in fluid communication with the closed-off interior of the elongated flexible sleeve and configured to communicate a resinous material thereto; a vacuum channel in fluid communication with the closed-off interior of the elongated flexible sleeve and configured to vacuum seal the closed-off interior of the elongated flexible sleeve; and a glass fiber layer positioned within the closed-off interior of the elongated flexible sleeve.