Process for manufacturing ceramic cores for turbomachine blades
View Patent ↗A process for manufacturing a ceramic foundry core having at least one thin region with a thickness “e”, in particular in of a turbomachine blade trailing edge, including the forming in a mold of a mixture including a ceramic particle filler and an organic binder, the extraction of the core from the mold, the binder removal and consolidation heat treatment of the core. The process is one in which a core is formed in the mold, the region of this core being thickened relative to the thickness “e” by an overthickness E and in which the overthickness is machined after the core has been extracted from the mold and before or after the heat treatment operation. In particular, the machining is carried out mechanically by milling, either with removal of chips on the cores before firing, or by abrasion on the fired cores.
1. A process for manufacturing a foundry core for casting a turbomachine blade, said core comprising at least one thin region with a thickness between 0.1 and 0.5 mm corresponding to a cavity in said turbomachine blade, said process comprising:
providing a mold,
forming a core in said mold by injecting a mixture into said mold, said mixture comprising a ceramic particle filler and an organic binder, wherein said mold is configured so as to provide, during said injecting, a channel with an opening sufficient to promote a flow of said mixture through said channel during said injecting and wherein, upon cooling, said mixture within said channel forms a thickened region in said core, said thickened region of said core having a thickness thicker than said thickness of said thin region,
extracting said core from the mold,
removing the binder from said core, and
consolidating the core by heat treatment,
wherein said process comprises a step of machining said thickened region after said step of extracting said core from said mold, and wherein said machining is performed on said thickened region so as to obtain said thin region of said core.
2. The process as claimed in claim 1 , wherein the machining is carried out before the heat treatment.
3. The process as claimed in claim 2 , wherein the machining is carried out mechanically by milling with removal of chips.
4. The process as claimed in claim 1 , wherein the machining is carried out after the heat treatment.
5. The process as claimed in claim 4 , wherein the machining is carried out mechanically by abrasion.
6. The process as claimed in claim 5 , wherein the machining is carried out with a milling cutter by removing material on an at least three axis milling machine.
7. The process as claimed in claim 1 , wherein the thin region lies close to a leading edge of said core and forms a tenon configured to form an air channel for exhausting air thereby internally cooling said turbomachine blade.
8. The process as claimed in claim 7 , wherein said mixture is fed in the mold at a location corresponding to said tenon.
9. The process as claimed in claim 7 , wherein the machining includes a step of radiusing a surface of the tenon.
10. The process as claimed in claim 1 , wherein said core comprises a plurality of thin regions, and said mold is configured to provide an overthickness for several thin regions.
11. The process as claimed in claim 1 , wherein said thickened region, before said step of machining, is thicker than said thin region by an overthickness of at least about 14% of said thin region.
12. The process as claimed in claim 1 , wherein said mold is configured to provide said channel during said injecting such that an injection pressure of said mixture is less than that of another process that is free of a step of forming said thickened region in said core.
13. The process as claimed in claim 12 , wherein said injection pressure of said process is less than that of said another process by at least about 17%.
14. The process as claimed in claim 1 , wherein said thickened region has a shape that is different from that of said thin region.