Method of manufacturing foundry ceramic cores for turbomachine vanes

摘要

The process for manufacturing a foundry core (100), comprises arranging a mixture having a load of ceramic particles and organic binder in a mold, extracting the core from the mold, and unbinding and thermally treating the core consolidation. The foundry core comprises several fine zones having a thickness of 0.1-0.5 mm in a trailing edge of turbomachine blade. The core zone is thickened in connection to an overlayer. The overlayer is machined after extracting the core from the mold in order to create an opening channel sufficient for the flow of the mixture. The process for manufacturing a foundry core (100), comprises arranging a mixture having a load of ceramic particles and organic binder in a mold, extracting the core from the mold, and unbinding and thermally treating the core consolidation. The foundry core comprises several fine zones having a thickness of 0.1-0.5 mm in a trailing edge of turbomachine blade. The core zone is thickened in connection to an overlayer. The overlayer is machined after extracting the core from the mold in order to create an opening channel sufficient for the flow of the mixture during its injection into the mold. The machining is mechanically carried out by milling with chip removal, abrasion and drilling of matter on a drilling machine to 4-5 axes, before and after the thermal treatment operation. The layer zone is situated proximate to the trailing edge and constitutes a tenon (100GH) as an evacuation channel for internal cooling of the turbomachine blade. A paste is supplied for the filling of mold in the tenon. The machining comprises a step of shelving of the tenon surface. The overlayer is applied to the several fine zone layers.