Shell mould for manufacturing aircraft turbomachine bladed elements using the lost-wax moulding technique and comprising screens that form heat accumulators

A shell mold for manufacturing a plurality aircraft turbomachine bladed elements using a lost wax molding technique, the shell mold being in a shape of a cluster and comprising:

• a plurality of shell mold bladed elements each configured to obtain one of the turbomachine bladed elements, each shell mold bladed element comprising a blade portion located between a first end part delimiting an impression of a platform and a second end part delimiting an impression of another platform, the blade portion comprising a trailing edge zone and an opposite leading edge zone;
• a metal feeder having a central axis around which the shell mold bladed elements are distributed;
• a shell mold interior space centered on the central axis, and delimited by the shell mold bladed elements;
• and
• a plurality of screens that form heat accumulators arranged in the shell mold interior space, across from inwardly-directed trailing edge zones of the shell mold interior space.

A shell mold for manufacturing a plurality of aircraft turbomachine bladed elements using a lost wax molding technique, the shell mold being in a shape of a cluster and comprising:

• a plurality of shell mold bladed elements each configured to obtain one of the turbomachine bladed elements;
• a metal feeder having a central axis;
• a plurality of metal casting arms distributed around the central axis of the metal feeder, with each of the casting arms including a first end connected to the feeder;
• and
• a thermal insulation coating carried out using a plurality of thermal insulation strips covering at least a portion of an outside surface of the shell mold.