Stack molding pattern and improved shell for manufacturing aircraft turbine engine blade elements via lost wax casting

A shell for manufacturing a plurality of vane elements of an aircraft turbomachine via lost wax moulding, said shell comprising:

• a plurality of shell vane elements each for obtaining one of said turbomachine vane elements, each shell vane element comprising a blade part located between a first end part and a second end part, each shell vane element defining a cavity within which wire elements are arranged, about which metal is intended to be cast, the wire elements passing successively through the first end part, the blade part and the second end part;
• a metal feeder having a centre axis about which said shell vane elements are distributed, said metal feeder comprising a plurality of metal outlets each radially open with respect to the centre axis towards one of the shell vane elements and communicating with the second end part of this shell vane element;
• wherein the shell comprises, being associated with each second end part, a protective screen aiming at protecting a sensitive portion of said wire elements against the direct impact of a metal flow from the feeder, said sensitive portion being located in the second end part, downstream of the protective screen.