| abstract |
The invention relates to a method for coating a core (1) by isostatic compaction for the production of a turbine component (2), such as a leading edge shroud of a blade, the coating method comprising the following steps :-S1: the core (1) is covered by a first solution comprising a first refractory component configured to resist diffusion of substances, the first component comprises a metal oxide, -S2: by a first solution comprising a A second solution of two components covers the core (1), the second component is designed to bond with the first component to form a homogeneous layer, the second component comprises a mineral binder; -S3: For the warp The covered core (1) is heat treated to dry the solution and cure the coating. |