Composite vane for an aircraft turbomachine and method for the manufacture thereof
AssigneeSafran Aircraft Engines
InventorsVincent Marie Jacques Remi DE CARNE-CARNAVALET, Pierre Gregoire ANTON, Celia IGLESIAS CANO
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Abstract
A composite vane for a turbomachine, in particular an aircraft turbomachine, this vane including an aerofoil having a pressure side and a suction side connected together by a leading edge and by a trailing edge, the aerofoil been formed from a fibrous preform obtained by weaving fibres in three dimensions, which is embedded in a polymer matrix, the vane further including a first metal shield extending over and along the leading edge of the aerofoil, the vane further including at least one cover element extending over and along the trailing edge of the aerofoil.
Claims10
A composite vane for a turbomachine, in particular for an aircraft, this vane comprising a blade comprising a pressure side and a suction side connected together by a leading edge and by a trailing edge, the blade being formed from a fibrous preform obtained by weaving fibres in three dimensions which is embedded in a polymeric matrix, the vane comprising a first metal shield extending over and along the leading edge of the blade, the vane further comprising at least one covering element extending over and along the trailing edge of the blade, characterised in that the covering element is made of thermoplastic composite material and comprises at least one fibre fabric which is draped over at least one portion of the pressure side and of the suction side and which extends over and along the trailing edge and the leading edge of the blade, this fabric being interposed between the first shield and the leading edge and comprising fibres different from the fibres of the preform.
Dependencies are inferred from the claim text.