Patent ID: 11879361
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Other special machines (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 5:
6. A method for manufacturing a vane for a turbine engine stator, comprising at least the following steps:
A) manufacturing a fibrous preform comprising two portions separated from each other by a passage and connected to each other on either side of the passage;
B) preparing an assembly composed of the fibrous preform and of a core produced from non-porous plastics material comprising a core body in the form of an aerodynamic profile that delimits at least a closed cavity of the core, the core body being housed in the passage of the fibrous preform, so that the fibrous preform has a pressure part and a suction part separated from each other by the core body and connected to each other on either side of the core body while forming a leading-edge part and a trailing-edge part; then
C) consolidating the fibrous preform by means of a resin, by a liquid composite moulding method, so as to form a shell wherein the pressure part of the fibrous preform forms a pressure surface of the vane, the suction part of the fibrous preform forms a suction surface of the vane, the leading-edge part of the fibrous preform forms a leading edge of the vane, and the trailing-edge part of the fibrous preform forms a trailing edge of the vane.