Patent classifications
B29C70/78
WIND TURBINE ROTOR BLADE
A wind turbine rotor blade having a flatback trailing edge. The flatback trailing edge has at least one insert which has a flat outside and a curved inside.
Diesel exhaust fluid tank with integrated mis-filling prevention device
A diesel exhaust fluid (DEF) storage system may include a reservoir body having a magnet integrally formed about an inlet opening of the reservoir body. For example, the magnet may be molding about a perimeter of the inlet opening during a molding process in which the reservoir body is formed. In some examples, the inlet opening defines a lumen extending into an interior of the reservoir body with the magnet being positioned at a location along the lumen opposite an external end face. The position of the magnet may be effective to engage a corresponding magnet on a DEF fill nozzle, allowing DEF to be introduced into the reservoir body. By integrating the magnet into the reservoir body, protection features that prevent erroneous filling of the reservoir body cannot be removed or bypassed.
Diesel exhaust fluid tank with integrated mis-filling prevention device
A diesel exhaust fluid (DEF) storage system may include a reservoir body having a magnet integrally formed about an inlet opening of the reservoir body. For example, the magnet may be molding about a perimeter of the inlet opening during a molding process in which the reservoir body is formed. In some examples, the inlet opening defines a lumen extending into an interior of the reservoir body with the magnet being positioned at a location along the lumen opposite an external end face. The position of the magnet may be effective to engage a corresponding magnet on a DEF fill nozzle, allowing DEF to be introduced into the reservoir body. By integrating the magnet into the reservoir body, protection features that prevent erroneous filling of the reservoir body cannot be removed or bypassed.
Thermoplastic composite in-situ melt processing method for composite overwrapped tools
An in-situ melt processing method for forming a fiber thermoplastic resin composite overwrapped workpiece, such as a composite overwrapped pressure vessel. Carbon fiber, or other types of fiber, are combined with a thermoplastic resin system. The selected fiber tow and the resin are prepared for impregnation of the tow by the resin. The resin is melted; and, carbon fiber is impregnated with the melted resin at the filament winding machine delivery head. The molten state of the composite is maintained and is applied, in the molten state, to the heated surface of a workpiece. The portion of the surface being wrapped is heated to the melting point of the thermoplastic resin so that the molten composite more efficiently adheres to the heated surface of the workpiece and so that the uppermost layer of fiber resin composite is molten when overwrapped resulting in better adherence of successive layers to one another.
Method for reversible bonding
A method of reversible bonding based on deposition of a coating capable of an indefinite number of reversible bonding cycles as enable by bond exchange reactions is provided. This is accomplished by deposition of crosslinkable aromatic polyester oligomers on a substrate. The coated article is heated to produce a fully thermoset network by condensation reactions. The fully thermoset network has access to a type of bond exchange reaction within the resin that permits the dynamic exchange of ester bonds within the resin. To execute the bonding step a source of heat is applied at a pressure. To debond, there is applied force in tension and/or shear that causes the coating to fail. The reversibility of the process is contingent on the cohesive (rather than adhesive) failure of the coating—that is, the coating must not delaminate from the substrate. Failure must occur in the resin of the reversible coating.
HIGH-WHITENESS MGO SUBSTRATE, PREPARATION METHOD THEREOF AND DECORATIVE BOARD HAVING THE SUBSTRATE
The application discloses a high-whiteness MGO substrate, a preparation method thereof and a decorative board having the substrate. The high-whiteness MGO substrate includes a surface layer and a substrate, wherein the substrate is prepared from a forming agent, a lightweight filler, a modifier and water in parts by mass as follows: 40-49 parts of light burned magnesium oxide powder, 18-25 parts of magnesium sulfate heptahydrate, 16-25 parts of a polyvinyl alcohol solution, 16-20 parts of a plant powder, and 0.5-2 parts of a modifier; the modifier being obtained by mixing citric acid, phosphoric acid, and sodium sulfate in a mass ratio of 10:3:6.
HIGH-WHITENESS MGO SUBSTRATE, PREPARATION METHOD THEREOF AND DECORATIVE BOARD HAVING THE SUBSTRATE
The application discloses a high-whiteness MGO substrate, a preparation method thereof and a decorative board having the substrate. The high-whiteness MGO substrate includes a surface layer and a substrate, wherein the substrate is prepared from a forming agent, a lightweight filler, a modifier and water in parts by mass as follows: 40-49 parts of light burned magnesium oxide powder, 18-25 parts of magnesium sulfate heptahydrate, 16-25 parts of a polyvinyl alcohol solution, 16-20 parts of a plant powder, and 0.5-2 parts of a modifier; the modifier being obtained by mixing citric acid, phosphoric acid, and sodium sulfate in a mass ratio of 10:3:6.
Method for manufacturing a composite casing for a turbomachine compressor
A method for manufacturing a curved composite casing for a turbomachine, notably for a low-pressure compressor of an aircraft turbojet engine, includes the following sequence of steps: (a) draping a preform by automatic placement of carbon fibres on a concave form, referred to as a female form; (b) laying a glass-fibre ply on a convex form, referred to as a male form; (c) transferring the preform onto the convex form, covering the glass-fibre ply on the convex form. Step (b) laying includes a phase (α) of laying a metal strip and/or an epoxy profile on the convex form, then a phase (β) of covering the metal strip with the glass-fibre ply.
Method for manufacturing a composite casing for a turbomachine compressor
A method for manufacturing a curved composite casing for a turbomachine, notably for a low-pressure compressor of an aircraft turbojet engine, includes the following sequence of steps: (a) draping a preform by automatic placement of carbon fibres on a concave form, referred to as a female form; (b) laying a glass-fibre ply on a convex form, referred to as a male form; (c) transferring the preform onto the convex form, covering the glass-fibre ply on the convex form. Step (b) laying includes a phase (α) of laying a metal strip and/or an epoxy profile on the convex form, then a phase (β) of covering the metal strip with the glass-fibre ply.
COMPOSITE
Provided is a composite (A) including a metal plate (B) and a reinforcing member (C) that is made of a resin. The metal plate (B) includes a joint portion (2) that is continuous with one end of a body portion (1), a hole that is formed through the body portion (1) in a thickness direction of the body portion (1) in the proximity of the joint portion (2), and a guide portion provided around the hole. The reinforcing member (C) continuously includes a main portion (5), a coupling portion (6) formed in the hole (3), and a locking portion (7) that is held in close contact with a surface on another side of the body portion (1). The guide portion (4) is at least one of a protruding portion provided on at least one of a rear side and a lateral side relative to the hole (3) in a direction from the body portion (1) to the joint portion (2), and a recessed portion extended from a front side relative to the hole (3) to the hole (3) in the direction from the body portion to the joint portion. In insert molding of the composite (A), a molten resin is introduced preferentially into the hole (3). With this, the joint portion (2) is formed reliably in good condition free from adhesion of the resin.