Abstract: A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.

Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

Abstract: A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.

Abstract: A propeller blade comprises a composite blade spar and at least one cover shell section adhesively bonded to the blade spar by a thermoplastic adhesive.

Abstract: A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.

Abstract: A method is disclosed for manufacture of a composite blade with an airfoil and a root, wherein the blade comprises a core of chopped fibre composite material and a textile composite material encasing the chopped fibre core. The method comprises: forming a blade insert using chopped fibre composite; surrounding the blade insert with a plurality of layers of a textile in a textile composite material; and thermoforming the blade insert and the surrounding textile composite material in a thermoforming mould in order to consolidate the part.

Abstract: A propeller blade comprises a composite blade spar and at least one cover shell section adhesively bonded to the blade spar by a thermoplastic adhesive.

Abstract: A method of manufacturing a composite article includes: providing a textile preform comprising a combination of filaments of reinforcing material with filaments of a thermoplastic matrix material; placing the preform in a mould; thermoforming the textile preform within the mould to consolidate the textile preform into a composite, the thermoforming including increasing the temperature above the melting temperature of the thermoplastic matrix material and applying pressure; cooling the composite within the mould to below the glass transition temperature of the thermoplastic matrix material, thereby forming a composite article; and removing the composite article from the mould. Part of the filaments used to produce the textile preform is in the form of yarns each comprising a mixture of reinforcing material filaments and matrix material filaments combined to form a single comingled yarn, or one or more yarns of reinforcing material filaments combined with one or more yarns of matrix material filaments.

Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

Abstract: A method is disclosed for manufacture of a composite blade with an airfoil and a root, wherein the blade comprises a core of chopped fibre composite material and a textile composite material encasing the chopped fibre core. The method comprises: forming a blade insert using chopped fibre composite; surrounding the blade insert with a plurality of layers of a textile in a textile composite material; and thermoforming the blade insert and the surrounding textile composite material in a thermoforming mould in order to consolidate the part.

Abstract: A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.