In a pump housing having an interior for accommodating a pump rotor, which may be transferred from a radially compressed state into a radially expanded state, and comprises a housing skin revolving in circumferential direction, as well as at least one reinforcement element, a stretch-resistant element revolving in circumferential direction is provided, which is stretched less than 5% in the expanded state as opposed to the force-free state in circumferential direction, and which limits any further expansion of the pump housing in radial direction.

An airfoil includes an airfoil section defining suction and pressure sides and leading and a trailing ends, the airfoil section being formed of a fiber-reinforced composite comprised of fiber plies, the fiber plies including at least one core fiber ply defining a tube that circumscribes an internal cavity and an overwrap fiber ply that wraps around the at least one core fiber ply, and aft of the internal cavity the overwrap fiber ply on the pressure side including first fingers and the overwrap ply on the suction side including second fingers, the first fingers being interdigitated with the second fingers to form an interlocked joint in the trailing end.

Platform for an aircraft turbo machine fan rotor, the platform being configured to be secured to a fan disc between two adjacent fan blades. The platform further including a longitudinal wall defining an aerodynamic external face. The wall includes a honeycomb structure interposed between two skins which are respectively an internal skin and an external skin, with the external skin defining the aerodynamic external face.

A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.

A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.

An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span including a first plurality of composite plies. The frangible airfoil portion includes a first plurality of composite plies including fibers having a first fiber modulus. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies including one or more plies having a second fiber modulus. The second fiber modulus is greater than the first fiber modulus. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.

A molding process for the production of a cover wall section for a cover in which the cover wall section has at least one multi-layer fabric that has a reinforcement and, at least on one side, preferably on both sides, a polymer coating, has the following process steps: Provision of at least one multi-layer fabric; draping of the at least one fabric over a molding surface of a mold and stretching of the at least one fabric across the molding surface by at least one tension element; and curing of the at least one fabric and/or the at least one tension element in such a way that the cover wall section is fixed in its shape.

A method of forming a ceramic matrix composite component with cooling channels includes embedding a plurality of wires into a preform structure, densifying the preform structure with embedded wires, and removing the plurality of wires to create a plurality of corresponding channels within the densified structure.

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 process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.