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 a paddlewheel for a flow meter is provided. The method can include providing an inner part of the paddlewheel. The method can also include inserting a plurality of magnets in the inner part of the paddlewheel. The method can also include overmolding an outer part of the paddlewheel over the inner part of the paddlewheel.

A method of manufacturing a composite structure, e.g. wind turbine blade, using reusable and removable perimeter plates to establish air flow channels in conjunction with a vacuum bag and mold. An exemplary setting is the perimeter of large wind blade shells where a perimeter vacuum is used to retain the part in the mold for the bonding process. The reusable plates disclosed herein create air channels whether the vacuum is introduced to the perimeter of the mold: i) through the flange in different locations; or ii) with the use of vacuum lines into the perimeter bag; or iii) built in vacuum channels in the flange of the mold.

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 precision shaving razor with low cost assembly. A bridge is unitarily molded having a leading platform, a handle attachment mechanism and first and a second cross member each molded to extend substantially perpendicularly to the leading platform. A plurality of base members is each unitarily molded to have a first peg and a second peg for attachment to the cross pieces. A plurality of blade covers each unitarily molded. A razor blade is sandwiched between each blade cover-base pair. In some instances, the blade covers are molded to have hard stops to facilitate precise blade position. In some cases, the bases define angular wash through channels and blade guards spaced to facilitate wash through. In some cases, the skin contacting surfaces of the razor are textured during molding to have a glide improving texture.

A protective covering can protect a surface of a composite article from lightning strikes, wherein the surface includes at least one grounding connection. The covering includes a conductive sheet formed from electrically conductive material configured to be affixed to the composite article over a portion of the surface adjacent the grounding connection; and a perforated overlaminate sheet comprising a dielectric material configured to be affixed to the composite article over the conductive sheet. The perforated overlaminate sheet distributes electrical current of the lighting strikes over an area of the protective covering.

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.

A fabric and a method for making the same. The fabric includes a layer of unidirectionally oriented carbon fibre filaments sandwiched between a first layer of glass fibre rovings and a second layer of glass fibre rovings. The first layer of glass fibre rovings and the second layer of glass fibre rovings are linked by a connecting material.

A wind turbine rotor blade has a spar cap including conductive material, and a lightning conductor extending over the spar cap. There is a non-conductive layer between the lightning conductor and the spar cap. An equipotential bonding element electrically bonds the lightning conductor to the spar cap. The non-conductive layer is discontinuous to define a gap, and the equipotential bonding element extends through the gap.

A composite airfoil is disclosed. In various embodiments, a composite airfoil as disclosed herein includes an outer skin comprising one or more layers of carbon fiber composite material, the outer skin defining an aerodynamic surface having a leading edge; and a reinforcement material comprising a roll of fiberglass reinforced fabric positioned behind the outer skin along at least a portion of the leading edge.