A flexible, self-supporting hybrid veil that is permeable to liquid and gas. The hybrid veil includes: (a) intermingled, randomly arranged fibres in the form of a nonwoven structure; (b) particles dispersed throughout the nonwoven structure, wherein a majority of the particles are penetrating through the thickness of the nonwoven structure; and (c) a polymeric or resinous binder present throughout the veil. Such hybrid veil can be incorporated into composite laminates, prepregs, fabrics and fibrous preforms.

Provided is a laminated substrate wherein a sheet-shaped material with a porosity of 50-99% is laminated onto at least one surface of a prepreg substrate which includes a reinforcing fiber and a thermoplastic resin.

Composite structures and methods of forming composite structures are provided. The composite structures can include one or more composite structure components. Each composite structure component is formed from a composite panel that includes one or more sheets of material. The sheets of material include a thermoplastic material and a plurality of reinforcing fibers. A composite panel can be formed in three dimensions to form a composite structure component. Multiple composite structure components can be fused to one another to form a composite structure. In addition, each composite structure component and the composite structure formed therefrom can include an aperture. An interior volume can be formed between adjacent composite structure components. Methods for forming a composite structure can include a step of simultaneously molding and fusing composite structure components.

The present invention concerns Method for producing a unidirectional tape, the method comprising the steps of a) providing an impregnation slurry comprising primary particles and secondary particles, water, optionally an organic carrying medium, optionally an organic compound and optionally a surface active compound, and providing a unidirectional fiber layer having an average interstitial filament distance, wherein the primary particles comprise a first polymer and the primary particles have a particle size equal to or smaller than the average interstitial filament distance, and the secondary particles comprise a second polymer and the secondary particles have a particle size larger than the average interstitial filament distance, b) impregnating the unidirectional fiber layer with the impregnation slurry to form an impregnated unidirectional fiber web comprising an impregnated unidirectional fiber layer and a surface polymer layer, wherein the impregnated unidirectional fiber layer comprises, preferably consists of, the unidirectional fibers and the primary particles, and the surface polymer layer comprises the secondary particles, c) drying the impregnated unidirectional fiber web to obtain a unidirectional tape.

Provided is a technology for imparting a design having a higher degree of freedom than in the related art to a composite material product including a woven fabric, which is formed of a thread made of a specific fiber (carbon fiber, glass fiber, aramid fiber), and a resin. As a first step, a specific fiber cloth (100), which is the woven fabric formed of the thread made of a specific fiber, and a backing sheet (200) formed of a thermoplastic resin are stacked. Subsequently, embroidery is performed with an embroidery thread (300) to form a design on a front surface of the specific fiber cloth (100). The embroidery thread (300) is made of the specific fiber, and penetrates through the specific fiber cloth (100) and the backing sheet (200). Then, the specific fiber cloth (100) and the backing sheet (200) are sandwiched between resin sheets (400) each formed of a thermoplastic resin, and the whole is cured by an RFI method.

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.

The invention proposes a method for manufacturing a grille for a cascade type thrust reverser, of a jet engine, said method including the following steps: a) manufacturing a first component comprising long fibres, pre-impregnated by a thermoplastic or thermosetting resin; b) manufacturing, together with step a), a series of second components each including discontinuous fibres, pre-impregnated by a thermoplastic or thermosetting resin, step b) being carried out such that the second components are, on the one hand, arranged to transversally with respect to a longitudinal direction of the first component on at least one side of the first component and, on the other hand, spaced from one another according to this longitudinal direction, so as to form a comb-shaped structure, wherein the second components are consolidated to the first component.

An article includes a hybrid nanocomposite product, which includes a nanostructure array and a resin matrix contained among and/or around the nanostructure array. The array/matrix is placed in between layers of dry or resin-infused fiber composite to permit formation of a composite structure. The nanostructure array and/or the resin matrix may be disposed in an abutting relationship with other layers of a composite. The array/matrix can provide reinforcement of the composite in the z-direction. Transfer of resin into dry fiber forms may be provided when the array/matrix acts as a resin transfer medium. Nanostructure arrays with a resin matrix can be prepared to form a resin film product. Methods are presented for infusing composites via resin-transfer molding (RTM), vacuum-assisted resin transfer molding (VARTM), resin film infusion (RFI), or injection molding wherein a resin matrix film substantially maintains alignment and position of the nanostructure array during the infusion process.

A method and process is provided for manufacturing a glassed reinforced polymer composite laminate panel. The method and process includes the steps of providing a mold including a flexible polymer film; depositing a layer of gel coat on the flexible polymer film; curing the layer of gel coat to provide a semi-rigid intermediate panel; applying a layer of resin material overtop of the cured gel coat layer; laying a sheet of woven or non-woven surface veil material over top of the cured gel coat layer; laying a sheet of glass reinforced matte overtop of the surface film sheet; applying a second layer of resin material overtop the sheet of glass reinforced matte to form the glassed reinforced polymer composite laminate panel; and curing the glassed reinforced polymer composite laminate panel. The method for manufacturing the composite laminate panel can be a continuous process making a panel of indeterminate length.