A step of forming a low-angle helical layer on an outer surface of at least part of each liner dome portion and an outer surface of a liner cylindrical portion, a step of forming an inner hoop layer on an outer surface of the low-angle helical layer on the liner cylindrical portion, and a step of forming a mixed layer by alternately laminating a low-angle helical layer and an outer hoop layer on an outer surface of the inner hoop layer and low-angle helical layer on each liner dome portion. Then, on the liner cylindrical portion, 90% or more of the sum of the thickness of the inner hoop layer and the thickness of the outer hoop layer in the mixed layer is arranged within the range of 75% of the fiber reinforced plastics layer adjacent to the liner in a thickness direction of the fiber reinforced plastics layer.

A laminated moulded part of fibre-reinforced resin matrix composite material, the moulded part comprising a first ply comprising fibres impregnated with a resin, an outer surface of the first ply defining an outer surface of the laminated moulded part, a rope located around at least a part of a periphery of the first ply, the rope comprising a plurality of strands of fibres twisted together and impregnated with a resin, a second ply comprising fibres impregnated with a resin, the second ply at least partly covering an inner surface of the first ply, at least a portion of a peripheral edge of the second ply being located inwardly of a corresponding portion of the rope, and at least a portion of the periphery of the first ply being folded over so as to wrap around the rope and cover the corresponding peripheral edge of the second ply.

A rigid coupler for use in electrically isolating an electrically conductive fluid conveyance system is described. The rigid coupler includes a nonconductive liner having a first end configured to couple to a first adjoining section of the fluid conveyance system, and a second end, opposite said first end, configured to couple to a second adjoining section of the fluid conveyance system. A reinforcing structure circumscribes the nonconductive liner and is coupled to a portion of the nonconductive liner extending between the first and second ends of the nonconductive liner. The reinforcing structure includes a multi-axial braided fiber material impregnated with a matrix material. A fiber overwrap is hoop wound about at a least a portion of the reinforcing structure between the first and second ends of the nonconductive liner.

A winglet is disclosed including first and second covers, a front spar, a rear spar, a rib, and a mid spar between the front spar and the rear spar. The rib and each spar are joined to the first cover and to the second cover. The mid spar has a length and the mid spar curves along all or part of its length. The length of the mid spar extends from an inboard end of the mid spar to an outboard end of the mid spar, and the rib wraps around the inboard or outboard end of the mid spar.

A method is disclosed for continuously manufacturing a composite hollow structure. The method may include continuously coating fibers with a matrix, and revolving matrix-coated fibers about a non-fiber axis. The method may also include diverting the matrix-coated fibers radially outward away from the non-fiber axis, and curing the matrix-coated fibers.

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.

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.