A method for repairing composite components includes installing a plug within a feature defined by a composite component, with the plug being formed from one or more neutral materials. Furthermore, the method includes infiltrating the composite component with an infiltrant to densify a repair region of the composite component, with the plug blocking a flow of the infiltrant into the feature. Moreover, after infiltrating the composite component, the method includes removing the plug from the feature.

A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

The present application relates to a blade of low pressure rectifier axial turbomachine. The blade can also be a rotor blade and/or a turbine blade. The blade includes a composite material with a matrix and a reinforcement that includes a mesh forming a three dimensional structure with a plurality of rods that describe a three-dimensional mesh based on polyhedrons. The three-dimensional structure extends over the majority of the thickness of the blade between the pressure side surface and the suction side surface and/or the majority of the length of the blade between the leading edge and the trailing edge. The rods of the reinforcement are bonded to each other and are distributed throughout the volume between the pressure side surface and the suction side surface of the blade. The rods form a three-dimensional mesh occupying the entire blade. The present application also relates to an iterative method for manufacturing a blade by additional layer manufacturing.

Methods for manufacturing a turbomachine composite part, such as a fan blade, are provided. The composite part has a fibrous structure with a three-dimensional fibrous preform coated with a surface fibrous web, and which is embedded in a polymer matrix The methods include: forming the surface web in a cavity of a mold in order to shape it, wetting and forming the preform on the surface web in order to shape it, and closing the mold, drying the fibrous structure, and injecting thermosetting resin into the mold in order to form said polymer matrix. The surface web is wetted before and/or during the forming thereof.

A method for producing a rotor blade for a gas turbine, the blade having a fastening region and a platform, on which a blade ending in a blade tip is arranged. The method is designed to facilitate a particular high efficiency of the gas turbine with a particularly resource-saving manner of production. The method includes: production of a reinforcement; casting of a first part of the rotor blade about at least one portion of the reinforcement; and construction of a second part of the rotor blade by a 3D-printing method.

An article and method of forming an article are provided. The article includes a side wall at least partially defining an inner region and an outer region of the article, the side wall having a first end and a second end, an end wall formed proximal to the first end of the side wall, the end wall defining a tip portion of the article, and a cooling channel formed in the side wall, within the tip portion. The method of forming an article includes positioning a first sheet of material having a channel formed therein over a first end of a body, positioning at least one additional sheet of material over the first sheet of material, and securing the first sheet of material and the at least one additional sheet of material to the body to form a tip portion including a cooling channel formed therein.

A guide vane for a gas turbine engine, the guide vane including an airfoil made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers agglomerated in the form of a mat, the airfoil being provided at least on a leading edge with a reinforcing strip, the reinforcing strip being made from a single strip of unidirectional fabric or of textile, or by stacking a plurality of pre-impregnated plies of unidirectional fabric or of textile made of carbon fibers or of glass fibers, and at least one platform positioned at a radial end of the airfoil, the platform being made of composite material having fiber reinforcement densified by a matrix, the fiber reinforcement being obtained from pre-impregnated long fibers.

A screw system including a plurality of segmented blades. Each blade segment of the plurality of blade segments including a mounting portion and a vane portion. The mounting portion, having a helical length, for removably attaching the blade segment. The vane portion extending from the mounting portion along the helical length thereof. The vane portion having a front surface that is not parallel to a back surface from the mounting portion to a tip of the blade segment, along the helical length.

A multi-layer braided article and a method of making the multi-layer braided article. The multi-layer braided article includes a braid extending along a first axis, wherein the braid is folded over itself to form a first layer and a second layer; and a wrapper laid over the first layer of the braid and extending circumferentially around the first axis, wherein the wrapper defines an edge of the first layer about which the braid is folded. The multi-layer braided article may form part of a blade for an aircraft. A sleeve may be provided around a conical portion of the article to connect the article to something else, such as a propeller hub, where the multi-layer braided article is formed as part of a blade. The sleeve may provide a primary or secondary load path.

A method for manufacturing a vane from a composite material with a fitted metal leading edge includes the successive draping, on a template of the leading edge of the vane to be manufactured, of a first layer of a base material and of a second layer of an adhesive material, the transfer of the first and second draped layers in the recess of a metal foil, the positioning of the foil including the first and second draped layers alongside the leading edge of a vane preform including a fiber reinforcement impregnated with a precursor of a matrix, the co-curing of the vane preform and of the first and second draped layers so as to obtain a vane made of composite material including on its leading edge a bonded metal foil.