Loading patent…
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsChristophe Jean Roger Champenois, Laurent Jean Pierre David, Gerard Fran.cedilla.ois Inizan
Estimating the term…
A turbomachine blade, particularly a fan blade for an aircraft jet engine, is made of a composite material comprising reinforcing fibres embedded in a thermosetting resin matrix, wherein the reinforcing fibres form a multilayer woven fabric in which the warp fibres of each layer are interwoven not only with the weft fibres of the layer but also with the weft fibres of at least the layers immediately above and below it so that the layers are all interconnected. Also, each layer only partly covers the layer below it so that the ends of the warp and weft fibres of a layer extend to near the surface of the blade, and the thickness of the blade at any point is determined by the number of layers present at that point.
A turbomachine blade made of a composite material comprising reinforcing fibres embedded in a matrix of injectable and hardenable material, wherein said reinforcing fibres form single multilayer fabric extending continuously between an intrados face and an extrados face consisting of a plurality of parallel layers disposed one on top of the other such that each layer partly covers the layers below it, the number of layers present at any position determining the thickness of said blade at that position, and wherein each of said layers is formed by weft fibres and warp fibres interwoven with said weft fibers, said weft fibers of each layer partly covered by another layer being connected by warp fibres thereof to the weft fibres of at least one layer thereabove over the extent of the surface covered by said at least one layer thereabove, and said weft fibres of each layer partly covering another layer being connected by warp fibres thereof to the weft fibres of at least one layer therebelow.
Dependencies are inferred from the claim text.