A woven fibrous preform of a hollow aerodynamic profile of a turbomachine vane or blade, has a non-interlinked trailing edge and a draping of two 3D woven fibrous textures.

An insulating, double-knit fabric containing a first knit layer and a second knit layer coupled with the first knit layer through a plurality of first direction spaced apart rows in a first direction and a plurality of second direction spaced apart rows in a second direction which is perpendicular to the first direction forming a plurality of air pockets in a grid pattern. The fabric also contains a plurality of intermediate fiber regions positioned in the plurality of air pockets, where each of the intermediate fiber regions contains a plurality of rows of multi-filament fibers extending parallel to at least one of the first and second knit layers. The first knit layer and the second knit layer comprise a plurality of flame resistant fibers, a plurality of cellulosic fibers, and a plurality of modacrylic fibers blended together.

A woven fibrous preform of a hollow aerodynamic profile of a turbomachine vane or blade, has a non-interlinked trailing edge and a draping of two 3D woven fibrous textures.

The present application discloses a method and device for generating a jacquard pattern, an electronic device. The method comprises: acquiring structure information of a unit structure of a preform to be prepared, wherein the structure information comprises a positional relationship between the warp yarns and the weft yarns of the unit structure of a preform to be prepared; obtaining a row number and a column number of the jacquard pattern to be generated, and correspondence between each pixel in the jacquard pattern to be generated and the warp yarns and weft yarns of the unit structure of the preform to be prepared, according to the structure information; and obtaining a pixel value of each pixel according to the correspondence and the positional relationship between the warp yarns and the weft yarns, and generating the jacquard pattern to be generated.

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.

The inventive subject matter generally relates to shaped battle constructs for use in consumer products, such as garments and sleeping bags. In certain aspects, the shaped baffles are arranged in a multi-level construction of baffles wherein the baffles are offset in two or more levels. In certain aspects, the entire construct is a unitary woven, seamless construction.

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 thermal sleeve for routing and protecting elongate members and method of construction thereof are provided. The sleeve has a tubular woven wall extending along a central axis between opposite open ends with an outer reflective foil layer fixed thereto. The wall is woven with lengthwise extending warp yarns and circumferentially extending fill yarns. The fill yarns include first and second fill yarns bundled in side-by-side abutting relation as a single pick, thereby forming discrete single pick bundles in axially spaced relation from one another. The first fill yarn is provided as a standard monofilament, while the second fill yarn is provided having a low melt material melted and bonded to the abutting first fill yarn and to portions of the abutting warp yarns, wherein the spaces between the discrete bundles remain substantially free of melted material, thereby further enhancing longitudinal flexibility of the sleeve.

The preform made of a 3D fibrous structure comprises at least 3 layers (1, 2) of weft yarns and/or warp yarns, the structure being woven as a single part by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns. It comprises a predetermined distribution of points of intersection of warp yarn and weft yarn that are bonded by polymer. The polymer represents a mass of less than or equal to 10%. The preform comprises at least one thermoformed portion in which the warp yarns and the weft yarns are bonded at the intersections thereof by polymer where at least one of the warp and/or weft yarns bears polymer.

A process for manufacturing a cylindrical composite component comprises includes producing a fibrous texture in the form of a strip by three-dimensional or multi-layer weaving, winding the fibrous texture on several superimposed lathes on a mandrel with a profile corresponding to that of the component to be manufactured so as to form a fibrous preform, densifying the fibrous preform by a matrix. When the fibrous texture is wound on the mandrel, a web including a fugitive material filled with carbon nanotubes is interposed between the adjacent turns of the fibrous texture.