A method of dissipating heat from a surface of a first thermoplastic composite (TPC) being inductively welded with a second thermoplastic composite (TPC) includes flexing a heat sink during placement to conform to the surface of the first TPC, cooling the heat sink, applying inductive heat to a weld interface area between the first TPC and the second TPC, and drawing off heat via the heat sink from the surface of the first TPC.

A method of dissipating heat from a surface of a first thermoplastic composite (TPC) being inductively welded with a second thermoplastic composite (TPC) includes flexing a heat sink during placement to conform to the surface of the first TPC, cooling the heat sink, applying inductive heat to a weld interface area between the first TPC and the second TPC, and drawing off heat via the heat sink from the surface of the first TPC.

The invention relates to a method for manufacturing a finished part comprising: a step of placing a trimmed finishing shell inside a heated mold chosen from a first mold referred to as a female mold and a second mold referred to as a male mold in the form of a punch, a step of heating a structural part made of a composite material up to its melting point, a step of placing the structural part on the finishing shell, a step of shaping the structural part against the finishing shell by means of the male mold in the form of a punch cooperating with the female mold, such that the finishing shell is fixed to the structural part that was shaped to obtain the finished part.

A method of manufacturing an armour layer of a flexible pipe for transporting fluid from a subsea location and apparatus are provided. The method comprises winding a first length of composite tape to form a first section of the armour layer and positioning an end region of the first length of composite tape over an end region of a second length of composite tape to form an overlapping tape section. Heat and pressure is applied to the overlapping tape section to form a joined overlapping tape section in which the first length of tape is joined to the second length of tape such that the joined overlapping tape section has a lap shear strength of at least 11 MPa. The joined overlapping tape section and the second length of composite tape are wound to form a second section of the armour layer.

A method of manufacturing an armour layer of a flexible pipe for transporting fluid from a subsea location and apparatus are provided. The method comprises winding a first length of composite tape to form a first section of the armour layer and positioning an end region of the first length of composite tape over an end region of a second length of composite tape to form an overlapping tape section. Heat and pressure is applied to the overlapping tape section to form a joined overlapping tape section in which the first length of tape is joined to the second length of tape such that the joined overlapping tape section has a lap shear strength of at least 11 MPa. The joined overlapping tape section and the second length of composite tape are wound to form a second section of the armour layer.

A connector body having a first end portion defining a first end face of the body and an opposite second end portion defining a second end face of the body, the first end portion including a first peripheral groove with a first sealing ring, and the second end portion including a second peripheral groove with a second sealing ring, an intermediate portion of the—body defining a peripheral surface extending between the first sealing ring and the second sealing ring, the peripheral surface to be covered by the retaining glue for bonding the body to the tube, a glue flow passage at the first end portion extending transversally to the first sealing ring, and a glue injection channel extending from the first end portion towards the second end portion and including a glue injection port in the first end portion and a glue ejection port at the peripheral surface.

A connector body having a first end portion defining a first end face of the body and an opposite second end portion defining a second end face of the body, the first end portion including a first peripheral groove with a first sealing ring, and the second end portion including a second peripheral groove with a second sealing ring, an intermediate portion of the—body defining a peripheral surface extending between the first sealing ring and the second sealing ring, the peripheral surface to be covered by the retaining glue for bonding the body to the tube, a glue flow passage at the first end portion extending transversally to the first sealing ring, and a glue injection channel extending from the first end portion towards the second end portion and including a glue injection port in the first end portion and a glue ejection port at the peripheral surface.

This method is for manufacturing a fan blade rotor which includes an annular rotation support ring around a rotary shaft, a permanent magnet provided alongside the rotation support ring in the radial direction, and a composite material for integrally binding the rotation support ring and the permanent magnet, the method including: a step S1 for arranging the rotation support ring and the permanent magnet side by side in the radial direction; steps S2-S4 for spirally winding, on the rotation support ring and the permanent magnet arranged side by side being as a core, the composite material being an uncured composite material including a reinforcement fiber impregnated with an uncured resin with the fiber direction of the reinforcement fiber set as a longitudinal direction; and a step for curing the resin included in the composite material.

Disclosed herein are methods for fabricating a composite structure by forming, via additive manufacturing, a solid-phase component; positioning the solid-phase component and a reinforcement into a mold cavity; and consolidating, in the mold cavity, the solid-phase component, the reinforcement, and a liquid-phase component to form the composite structure.

A self-stressing shape memory alloy (SMA)/fiber reinforced polymer (FRP) composite patch is disclosed that can be used to repair cracked steel members or other civil infrastructures. Prestressed carbon FRP (CFRP) patches have emerged as a promising alternative to traditional methods of repair. However, prestressing these patches typically requires heavy and complex fixtures, which is impractical in many applications. This disclosure describes a new approach in which the prestressing force is applied by restraining the shape memory effect of nickel titanium niobium alloy (NiTiNb) SMA wires. The wires are subsequently embedded in an FRP overlay patch. This method overcomes the practical challenges associated with conventional prestressing.