A method for additively manufacturing a textile sheet product and a three-dimensionally printed textile sheet product (1) are disclosed. The method includes the steps of creating a three-dimensional model of the pre-product and additively manufacturing the pre-product according to the three-dimensional model of the pre-product. In additive manufacturing, a production material is applied layer by layer in this case. At at least one predetermined crossover position of at least two fibrous structures (2a, 2b) and a separation layer material is applied which can be removed from the pre-product and/or inactivated.

A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

Some embodiments are directed to a three-dimensional (3D) preform including reinforcing fibres and shape memory alloys (SMA) wires and a composite material including a polymer matrix with a 3D-preform embedded therein, wherein the 3D-preform includes reinforcing fibres and shape memory alloy (SMA) wires.

A volumetric weaving approach employs a vertical aspect of woven warp and weft fibers to generate volumetric structures through formation of tie-downs. Tie downs define warp and weft fibers that take a vertical path or component extending perpendicular to a weave plane. Independently controlled heddles provide selective warp fibers control, and a two-dimensional creel that dispenses the warp fibers at differing feed rates allows manipulation of the fibers into three dimensional structures or portions. As a shuttle draws the weft fiber, different layers are raised and lowered to lend a vertical axis to the resulting volumetric structure. Interconnections between the portions include the use of the tie downs to connect multiple portions to define 3-dimensional panels of a finished article such as a shoe. A single pass defining all the interconnected portions of the shoe generates the fully formed shoe without subsequent cutting and seaming of different textile panels.

A vane arc segment includes an airfoil fairing that has a fairing platform and an airfoil section that extends there from. The fairing platform defines a gaspath side and a non-gaspath side and includes a flange that projects from the non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite that includes a wishbone-shaped fiber layer structure that has first and second arms that converge and merge into a single leg. The first and second arms are formed of fiber plies comprised of a network of fiber tows. The single leg comprises fiber tows from each of the fiber plies of the first and second arms. The fiber tows of the first arm are interwoven in the single leg with the fiber tows of the second arm. The first arm, the second arm, or the single leg forms at least a portion of the flange.

A manufacturing process of a fibrous preform for a composite material includes creating a fibrous texture by three-dimensional or multilayer weaving between a plurality of weft layers and warp layers, the fibrous texture including an extra-thick portion having a sacrificial portion and a useful portion adjacent to the sacrificial portion in the warp direction, the sacrificial portion, placing the fibrous texture in a forming toolset, shaping the fibrous texture so as to obtain a fibrous preform having a sacrificial portion and an adjacent useful portion, removing the sacrificial portion from the fibrous preform. When weaving the fibrous blank, one or more expansion elements are inserted into the weft layers located at the core of the sacrificial portion of the fibrous texture. Each expansion element has a cross-section greater than the cross-section or count of the weft threads or strands present in the useful portion.

A three-dimensional fibrous preform of a fan blade includes a blade root and a blade airfoil between the blade root and a free end of the preform. The airfoil has an area with two skins and a longitudinal stiffener between the skins and, in a transverse plane, transverse yarns of the skins woven in pairs in the first and in the second skin either side of the stiffener, the yarns of a first pair of the first skin are separated into two unit yarns at the stiffener, the unit yarns being woven separately with longitudinal yarns, the yarns of a second pair of the second skin are separated into two unit yarns at the stiffener, the yarns being woven separately with longitudinal yarns, and a yarn of each pair cross over each other twice in the stiffener.

A heart valve assembly, a prosthetic valve device, and a preparation method for a heart valve assembly. The heart valve assembly comprises: a skirt portion having a tubular structure, at least two leaflets provided on an inner wall of the skirt portion, a plurality of integrated anchoring rings provided on the exterior of the skirt portion; one end of the integrated anchoring ring is fixedly provided to the exterior of the skirt portion, and one end thereof is a free end; and the skirt portion, the leaflets and the integrated anchoring rings form an integrated valve structure. The heart valve component simplifies an assembly process by significantly reducing the need for precise sutures for connecting the valve component(s) to a stent, which can reduce the uncertainty of current suture technology.

An improved insulating performance fabric has a double-knit body, formed with traditional, relatively smooth, outer surfaces, and an inner surface with the form of multiple fabric “bubbles” separated, e.g., by a grid pattern of intersecting grooves. An insulating, double-knit performance fabric of this disclosure may also be found in the form of a garment comprising the insulating, double knit performance fabric, or in the form of fabric article comprising the insulating, double knit performance fabric, etc.