The present invention relates to an interlayer sheet for a spar cap comprising: a first fibre layer comprising a first plurality of fibres, having a first upper fibre surface and a first lower fibre surface, a second fibre layer comprising a second plurality of fibres, having a second upper fibre surface and a second lower fibre surface. The first fibre layer is arranged on top of the second fibre layer, such that the first lower fibre surface is in contact with the second upper fibre surface. The first fibre layer is of a different characteristic than the second fibre layer. Furthermore, the present invention relates to a spar cap for a wind turbine blade, comprising a plurality of pre-cured fibre-reinforced elements including at least a first pre-cured fibre-reinforced element and a second pre-cured fibre-reinforced element; and a number of interlayer sheets arranged between the plurality of pre-cured fibre-reinforced elements.

Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

A method of making an electrically-conductive film is provided. The method includes providing a release layer, optionally having a topologically structured surface, and depositing at least one electrically-conductive layer on the release layer whereby the at least one electrically-conductive layer has an outer surface that substantially replicates the topologically structured surface. The electrically-conductive layer can be peeled away from the release layer to obtain the electrically-conductive film. Such electrically-conductive films can be useful in lightning strike applications.

A method of manufacturing a composite laminate. The method comprises providing a base layer, providing a discontinuous reinforcing patch on the base layer, and providing a top layer over the base layer and discontinuous reinforcing patch. Also, a composite laminate having a discontinuous reinforcing patch interposed between a base layer and a top layer. The discontinuous reinforcing patch comprises a patterned nanomaterial layer with nanomaterial-filled zones and vacant zones.

A method of debonding a first layer from a second layer, wherein the first layer is bonded to the second layer by an adhesive located between the first and second layers. The method includes inserting a blade of a cleaving tool between the first and second layers, and exerting a controlled force on the cleaving tool to move the cleaving tool so as to de-bond the first and second layers in a region. The force exerted is controlled to match a de-bonding force calculated for the region, and such that the movement of the cleaving tool stops when the calculated force is less than a force required to move the cleaving tool, and continues when the calculated force is higher than or equal to the force required to move the cleaving tool.

The invention relates to a molding composed of extruded foam, wherein at least one fiber (F) is present with a fiber region (FB2) within the molding and is surrounded by the extruded foam, while a fiber region (FB1) of the fiber (F) projects from a first side of the molding and a fiber region (FB3) of the fiber (F) projects from a second side of the molding, and the extruded foam is produced by an extrusion process comprising the following steps: I) providing a polymer melt in an extruder, II) introducing at least one blowing agent into the polymer melt provided in step I) to obtain a foamable polymer melt, III) extruding the foamable polymer melt obtained in step II) from the extruder through at least one die aperture into an area at lower pressure, with expansion of the foamable polymer melt to obtain an expanded foam, and IV) calibrating the expanded foam from step III) by conducting the expanded foam through a shaping tool to obtain the extruded foam.

Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.

Discretizers that exhibit improved solid additive laden fluid flow emanating from the discretizers and methods of using same, particularly for making fibrous structures are provided.

A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.