A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.

The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.

The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).

A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions.

Composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

An airfoil includes an airfoil section that is formed of a fiber-reinforced composite that has fiber plies. The fiber plies include at least one overwrap fiber ply, first and second support fiber plies, and a serpentine fiber ply. The overwrap fiber ply circumscribes an internal cavity and defines first and second sides and leading and trailing ends of the airfoil section. The first and second support fiber plies define respective first and second radial tubes in the internal cavity. The serpentine fiber ply winds from the first side and around the first radial tube to the second side, then from the second side back to the first side, and then from the first side and around the second radial tube back to the second side.

A shaft component, which in particular can be connected or is connected to the input or output side of a gear box in a gas turbine engine, in particular an aircraft engine, wherein the shaft component has at least two regions comprising fiber reinforced plastic, with fibers in the at least two regions differing in their composition, their geometric properties, their density, their radial position, their axial position and/or in their fiber orientation in the shaft component.

A gas turbine engine component includes a component wall that has an exterior core gaspath side and an opposed interior side. The component wall is formed of a ceramic matrix composite that includes a plurality of fiber plies disposed in a ceramic matrix. The component wall includes a corner that connects first and second wall sections. The fiber plies extend continuously through the first wall section, the corner, and the second wall section. The fiber plies are in a stacked contiguous arrangement in the first and second wall sections and at least some of the fiber plies separate from one another in the corner to define one or more void pockets there between.

A wind turbine blade including a shell structure defining a leading edge and a trailing edge, and an upwind shell and a downwind shell joined along at least one of the leading edge or the trailing edge. The shell structure includes an assembly of preformed parts processed into a collection of prefabricated laminates. The invention also includes a method of manufacturing a wind turbine blade, the method includes processing a number of preformed parts into a collection of prefabricated laminates and assembling the collection of prefabricated laminates to build a shell structure defining a leading edge and a trailing edge.