An airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

The invention relates to a fibrous texture intended to form the fibrous reinforcement of a turbine engine blade made of composite material, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture. The blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fibers different from the first fibers.

The invention relates to a process (100) for manufacturing an object (1) made of thermoplastic polymer composite from at least two parts (10) made of thermoplastic polymer composite, said thermoplastic polymer composite comprising a fibrous reinforcement and a thermoplastic polymer matrix, said process comprising the steps of: arranging (120) the two parts (10) made of thermoplastic polymer composite adjacently or overlapping at an assembly interface zone (11), and heating (130) to melt the thermoplastic polymer matrix at said assembly interface zone (11), so as to form an object (1) made of thermoplastic polymer composite comprising a welded interface (12).

A method and system temporarily holds a workpiece, most suitably an aero engine turbine blade element during manufacture. The workholding system includes a support body with a contoured body surface, complementary to a workpiece surface, formed of a transparent material to define a bonding zone. The support body is supported by a base to form a workpiece shuttle, and a bond station receives the workpiece shuttle. Complementary zero-point locating elements on the shuttle and station assure accurate positioning. The bond station further has workpiece locating elements configured to accurately position the workpiece on the shuttle in a predetermined position relative to the zero-point locating elements of the shuttle, thereby compensating for shuttle-to-shuttle variance. An adhesive, such as a UV curable adhesive, is applied to the bonding zone and cured by UV through the transparent material, thereby fixing the workpiece in the predetermined position.

The present embodiment relates to a composite fibre structure (100) and a method (200) of manufacturing the composite fibre structure (200). The composite fibre structure (100) includes a core (102) and an outer layer (108) enclosing the core (102). The core (102) further includes at least one of a permanent core (104) and a temporary core (106). The permanent core (104) is 3-D printed along with the temporary core (106) to form the core structure (102). The permanent core (104) and the temporary core (106) are placed alternatively along the section, extending throughout the length of the composite fibre structure (100), or the permanent core (104) and temporary core (102) can be alternate along the length of the composite fibre structure (100). The layer (108), made of a reinforcement material, wraps the core (102) to form the composite fibre structure (100).

A method of debonding a first layer from a second layer, wherein the first layer is bonded to the second layer by an adhesive located between the first and second layers. The method includes inserting a blade of a cleaving tool between the first and second layers, and exerting a controlled force on the cleaving tool to move the cleaving tool so as to de-bond the first and second layers in a region. The force exerted is controlled to match a de-bonding force calculated for the region, and such that the movement of the cleaving tool stops when the calculated force is less than a force required to move the cleaving tool, and continues when the calculated force is higher than or equal to the force required to move the cleaving tool.

A machine tool arranged to deliver an energy source through a processing head onto a work-piece, wherein; the machine-tool has a clamping mechanism arranged to temporarily receive the processing-head, or another machining or processing-head, to process a work-piece; the processing-head comprising one or more guiding mechanisms arranged to direct the energy source onto a work-piece and a processing-head docking-manifold arranged to have connected thereto one or more media to be, in use, supplied to the processing-head to facilitate processing of the work-piece; wherein the processing-head docking-manifold allows the one or more media to be supplied to the processing-head when the processing-head is connected to the clamping mechanism; and wherein the machine-tool also comprises at least one mechanism arranged to move a supply docking-manifold into and/or out of connection with the processing-head docking-manifold such that when the two manifolds are connected the or each media is supplied to the processing head.

A method produces an injection molded part. A plastic material is injected into a cavity for forming the injection molded part. The plastic material in a flow line region of the cavity, where the plastic material from two directions coincides during an injection molding process, is at least partially removed from the cavity via at least two overflow points and, in so doing, is locally swirled or mixed between the overflow points.

A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.

The invention relates to a fibrous texture intended to form the fibrous reinforcement of a turbine engine blade made of composite material, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture. The blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fibers different from the first fibers.