An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

A fiber structure includes a plurality of weft layers and of warp layers interlinked by multilayer three-dimensional weaving, the fiber structure having at least first and second portions that are adjacent in the warp direction, the first portion presenting, in a direction perpendicular to the warp and weft directions, a thickness that is greater than the thickness of the second portion, wherein the first portion has at its core at least one fiber fabric obtained by three-dimensional weaving of warp yarns and weft yarns in the form of a Mock Leno weave grid, the at least one fabric being present between two skins present at the surface of the first portion and being linked to the skins by warp yarns belonging to the skins that are locally deflected into the fabric.

A method of fabricating an airfoil element out of composite material, comprises: making a fiber preform (300), said preform being impregnated with resin; polymerizing the resin with a matrix so as to obtain an airfoil element made of composite material comprising fiber reinforcement densified by a matrix; and fastening metal reinforcement on the composite material airfoil element, the metal reinforcement being fastened on the airfoil element by rivets. The method further comprises, prior to impregnating the fiber preform (300) with resin, inserting spacer elements (10) between the fibers of the fiber preform (300) and removing said spacer elements after the resin has been polymerized so as to form at least one passage between the fibers of the fiber reinforcement of the composite material airfoil element.

This invention relates to processes and systems of rapid prototyping and production. Its features includes flexible material deposition along tangential directions of surfaces of a part to be made, thereby eliminating stair-shape surface due to uniform horizontal layer deposition, increasing width of material deposition to increase build up rate, applying the principles of traditional forming/joining processes, such as casting, fusion welding, plastic extrusion and injection molding in the fabrication process so that various industrial materials can be processed, applying comparatively low cost heating sources, such as induction heating and arc-heating. Additional features include varying width and size of material deposition in accordance with geometry to be formed and applying a differential molding means for improved shape formation and surface finishing.

In an aspect, a method of filling a plurality of cooling holes in an airfoil component, the method comprises injecting a curable composition into a fill channel such that the curable composition flows through the fill channel to the plurality of cooling holes; forming a plurality of beads of the curable composition on a surface of the component over the plurality of cooling holes; directing a radiation to the respective beads in directions parallel to the respective central axes of the cooling holes associated with the respective beads to cure curable composition of the respective beads; and heating the component to cure the curable composition located in the fill channel.

A composite airfoil is disclosed. The composite airfoil includes a first ply having a first plurality of strips of fiber oriented at a first angle with respect to a longitudinal axis and a second plurality of strips of fiber oriented at a second angle with respect to the longitudinal axis at least a first subset of the first plurality of strips of fibers have fibers intersecting and oriented at an angle to the fibers in at least a second subset of the second plurality of strips of fibers within a ply boundary.

In one embodiment, an assembly fixture may include a base structure including a plurality of strands of a fiber-reinforced thermoplastic material comprising a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the base structure further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the base structure, The assembly fixture may further include a plurality of fastening structures coupled to the base structure, wherein the plurality of fastening structures is configured to fasten a plurality of components of a composite structure for assembly using a heated bonding process.

An example method for forming a flat composite charge into a composite blade stiffener includes cutting a flat composite charge along a cut line into a first piece and a second piece having an angle, positioning the first piece and the second piece of the flat composite charge on a forming mandrel about a tooling plunger, activating the tooling plunger to drive the first piece and the second piece into a cavity of the forming mandrel resulting in the first piece and the second piece folding at the cut line, withdrawing the tooling plunger from the cavity of the forming mandrel, compressing the forming mandrel to apply a lateral pressure to the first piece and the second piece folded into the cavity, and applying a vertical pressure to a first flange and a second flange of the first piece and the second piece, respectively, to form the composite blade stiffener.

A method of manufacturing a rotor blade includes (1) assembling a first blade module that defines a first-module span axis and includes a first-module skin and a first- module spar, and each of the first-module skin and the first-module spar includes a first thermoplastic polymer and reinforcement material; (2) assembling a second blade module that defines a second-module span axis and includes a second-module skin and a second- module spar, and each of the second-module skin and the second-module spar includes a second thermoplastic polymer and reinforcement material; (3) transporting the first blade module and the second blade module to a field location; (4) aligning, at the field location, the first-module span axis with the second-module span axis to define an aligned pair of modules; and (5) heating a portion of the aligned pair of modules to form a weld joint between the first-module spar and the second-module spar.

There is disclosed a tool for manufacturing a composite component, the tool comprising: a skin composed of fibre reinforced plastic and defining a layup surface for the composite component, the skin having a plurality of passageways extending from the layup surface to an opposing surface of the skin; a backing secured to the skin, the backing and the skin defining a cavity therebetween; a support core disposed within the cavity and comprising a gas-permeable material in fluid communication with the passageways; and a conduit extending through the backing such that the conduit is in fluid communication with the gas-permeable material.