The application discloses a conformable support structure for use in fiber composite precursor; a resin impregnated conformable fiber composite precursor, which may surround the support structure, for being manually manipulated and plastically deformed into a desired shape before being cured into a final product having the desired shape; the corresponding final product, which may be an orthosis or other product; and methods of making the final product or orthosis. The support structure is typically plastically deformable by hand to form the desired shape, may be substantially planar and may have various voids to promote controlled plastic deformation of the frame in one or more desired directions. The core may comprise a wire or tube and may include packing or filler material. The precursor includes a fiber layer impregnated with a thermoset resin and includes a compressor around the fiber layer. The fiber layer is supported internally or externally by the conformable support member. The precursor may be custom fitted to match the shape of an object and then thermally cured into a strong rigid product. The cured precursor can then be used to make a custom finished product.

Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together.

A fiber reinforced resin composite for ballistic protection comprising a plurality of first and second plies wherein the first and second plies further comprise a woven fabric and a polymeric resin. The fabric has a Russell tightness factor of from 0.2 to 0.7 and a cover factor of at least 0.45, The fabric is impregnated with the resin, the resin comprising from 5 to 30 weight percent of the total weight of fabric plus resin. The fabric of each first and second ply comprises regions wherein the fabric is distorted from an orthogonal woven state by a distortion angle of least 30 degrees. The composite may further comprising a third ply having a surface area no greater than 50% of the surface area of a first and second ply. The ratio of the number of first plus second plies to the number of third plies is from 2:1 to 12:1.

A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).

One object is to provide a reel leg fixing apparatus including a hood portion having an efficiently reduced thickness and weight while maintaining a sufficient strength. Another object of the present invention is to provide a reel leg fixing apparatus including a hood portion having a reduced thickness and weight while efficiently ensuring necessary strength at relevant portions, and a method of fabricating the reel leg fixing apparatus. Still another object of the present invention is to provide a reel leg fixing apparatus including a hood portion having an oblique end that allows weight reduction and maintains a sufficient strength.

One object is to provide a reel leg fixing apparatus including a hood portion having an efficiently reduced thickness and weight while maintaining a sufficient strength. Another object of the present invention is to provide a reel leg fixing apparatus including a hood portion having a reduced thickness and weight while efficiently ensuring necessary strength at relevant portions, and a method of fabricating the reel leg fixing apparatus. Still another object of the present invention is to provide a reel leg fixing apparatus including a hood portion having an oblique end that allows weight reduction and maintains a sufficient strength.

A 3D object according to the invention involves substrate layers infiltrated by a hardened material. The 3D object may be fabricated by a method comprising the following steps: Flatten a substrate layer. Position powder on all or part of a substrate layer. Repeat this step for the remaining substrate layers. Stack the substrate layers. Transform the powder into a substance that flows and subsequently hardens into the hardened material. The hardened material solidifies in a spatial pattern that infiltrates positive regions in the substrate layers and does not infiltrate negative regions in the substrate layers. In a preferred embodiment, the substrate is carbon fiber and excess substrate is removed by abrasion.

A 3D object according to the invention involves substrate layers infiltrated by a hardened material. The 3D object may be fabricated by a method comprising the following steps: Flatten a substrate layer. Position powder on all or part of a substrate layer. Repeat this step for the remaining substrate layers. Stack the substrate layers. Transform the powder into a substance that flows and subsequently hardens into the hardened material. The hardened material solidifies in a spatial pattern that infiltrates positive regions in the substrate layers and does not infiltrate negative regions in the substrate layers. In a preferred embodiment, the substrate is carbon fiber and excess substrate is removed by abrasion.

A composite structure is fabricated using a preform comprising a stack of unidirectional prepreg plies that are stitched together. During curing of the prepreg, the stitches melt and dissolve.

In an artificial defect material 10 of an FRP structure, a heat-resistant high-linear-expansion material 20 arranged between the layers thermally expands in case of high-temperature shaping of the FRP structure, so that a predetermined shape is shaped between a plurality of layers of the fiber reinforcing base material 14 and the material 20 thermally shrinks at the room temperature after the shaping, so that a space is formed due to the shrinkage difference from the fiber reinforcing base materials 14. The material 20 has a linear expansion coefficient larger than that of the FRP structure by a predetermined value or more, and has the shape keeping property and the heat resistance to endure the shaping temperature.