Ratier-figeac Sas

Hamilton Sundstrand Corporation

Ratier Figeac

Patrice Brion

David P Nagle

Bertrand Prouzet

Ludovic Prunet

Kévin Le Meur

Pascal Amat

Adil Sardi

Fabien Ramirez

Kevin Le-Meur

A method of applying a braided cover to a core comprises braiding a plurality of tows around the core from a plurality of bobbins. One or more properties of the tow on a respective bobbin vary along the length of the tow.

Braiding

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.

Aircraft blade and methods of forming and repairing an aircraft blade

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.

Method of manufacturing a composite aircraft blade

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.

Propeller blades

Disclosed is a process for manufacturing a part, named composite part, formed from at least one composite material including at least one layer of a reinforcing structure impregnated with a polymer matrix within which the reinforcing structure extends, wherein: a composite blank of the composite part is prepared; and a step of curing the polymer matrix of the composite blank is carried out, exerting a pressure on at least one pressed face of the composite blank. The pressure is exerted in the form of a pressure gradient applied to the pressed face of the composite blank so as to cause the gas present within the composite part to flow from a zone of maximum pressurization to a gas evacuation zone. Also disclosed is a device for manufacturing such a part.

Process and device for manufacturing a composite part enabling the evacuation of gas from the composite part

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.

Composite blade and method of manufacture

A propeller blade includes a foam core, an adhesive layer formed on the core and a structural layer that covers at least a portion of the adhesive layer and that surrounds at least a portion of the foam core.

Propeller blade having compliant adhesive at spar interface

According to one embodiment, a propeller blade includes a foam core and a structural layer formed of multiple layers that surrounds at least a portion of the foam core. The structural layer includes a mid-thickness location defined between the foam core and an outer edge of the structural layer and the multiple layers include at least one unidirectional layer and at least one biased layer disposed asymmetrically about the mid-thickness location.

Growing community of inventors

Lunan, France

Patrice Brion