Method for producing a bladed component for an aircraft turbine engine
AssigneeSafran
InventorsNicolas Pierre Lanfant, Sebastien Pautard
Life of this patent
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Abstract
A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising including a blade which has a stacking axis and at least one longitudinal end of which is connected to a transverse platform, the method including the steps of: a) producing a fibrous preform, this preform including a first part that is intended to form a blade and at least one second part that is intended to form a platform, this second part of the preform including a disconnect that defines two stacked portions that are separated by a disconnect surface that is substantially parallel to the axis, b) folding the portions, respectively, on two opposing sides of the first part, and c) stiffening the preform.
Claims10
A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising a blade having a stacking axis and having at least one longitudinal end connected to a transverse platform, the method comprising the steps of:
- a) producing a fibrous preform, the preform having a generally elongate shape along said axis and being flat, the preform comprising a first part that is intended to form the blade and at least one second part which is situated at a longitudinal end of the preform and which is intended to form the transverse platform, the second part of the preform comprising a disconnect defining two superimposed portions separated by a disconnect surface substantially parallel to the axis,
- b) folding the portions respectively on two opposite sides of the first part, and
- c) stiffening the preform,
- wherein, in step a), the disconnect is such that the portions are connected together, at a junction between the first and second parts, by a connecting line which has a generally undulating shape.
Dependencies are inferred from the claim text.