Provided is a method of manufacturing a panel of a wind turbine nacelle, which method includes the steps of providing a mold for the panel; arranging at least one divider in the mold to spatially divide the mold into at least a first mold region and a second mold region; arranging composite material in the mold; curing the composite material; and separating the cured panel into at least a first panel portion and a second panel portion along a line defined by a divider. Also provided is a method of constructing a wind turbine nacelle, and a wind turbine including such a nacelle.

A method for repairing composite components includes positioning repair material within a repair region of a composite component formed of a composite material. Furthermore, the method includes heating the repair region to a first temperature. Additionally, the method includes heating a remaining portion of the composite component to a second temperature. Moreover, the method includes melt infiltrating the repair region with an infiltrant to densify the repair material. The first temperature is at or above a melting point of the infiltrant and the second temperature is less than the melting point.

A curing mold for manufacturing a turbomachine component is made of composite material from a preform, including: a first and a second body defining an air gap receiving the preform; at least one primary channel arranged in the first and/or the second body; an injection member of a pressurized fluid in the primary channels; at least one secondary channel, in which a piston slides, which delimits, on the one hand, a first chamber in communication with the or a primary channel and, on the other hand, a second chamber in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.

A smart materials system includes a first tool configured to respond to an external stimulus, a second tool configured to respond to the external stimulus, and a core layer disposed between the first tool and the second tool such that the core layer is deformed when the first tool and the second tool respond to the external stimulus.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.

A fan track liner for a fan containment arrangement for a gas turbine engine comprises a cellular impact structure and a supporting sub-laminate integrally formed with each other from a fibre-reinforced polymer material.

An acoustic core has a plurality of cell walls formed of an additive-manufacturing material and a resonant space defined by the plurality of cell walls. At least some of the resonant cells have a multitude of sound-attenuating protuberances formed of the additive-manufacturing material of the cell walls protruding into the resonant space with a random or semi-random orientation and/or size. The sound-attenuating protuberances may be formed by orienting an additive-manufacturing tool with respect to a toolpath to form a contour of a workpart, in which the toolpath includes a plurality of overlapping toolpath passes configured so as to intentionally introduce an amount of additive-manufacturing material to the workpart that exceeds a domain occupied by the contour. As the amount of additive-manufacturing material intentionally introduced exceeds the domain occupied by the contour, a portion of the additive-manufacturing material may incidentally form the plurality of sound-attenuating protuberances.

A hybrid mandrel for forming a composite part may comprise a core and a sleeve located around the core. The core may include a rigid material. The sleeve may comprise an elastomeric material. The part may be formed by locating the hybrid mandrel in an injection mold, depositing a molten resin around the hybrid mandrel, curing the molten resin; and removing the hybrid mandrel.

An impeller includes a central, shaft or a tube for mounting on a shaft, a hollow hub is located around the shaft or tube, and a series of blades are attached to the outside of the hub by their bases. A reinforcing rib is provided for each blade, and extends on the shaft or tube in a radial direction and forms a facial connection between the shaft or tube and the inside of the hub at a position opposite the attachment of the base of a blade concerned.