Abstract: Product formed from a ceramic material, at least part of the said product not being formed from amorphous silica and including pores and satisfying the following criteria (a), (b) and (c): (a) at least 70% by number of the said pores are frustoconical tubular pores extending substantially parallel to each other in a longitudinal direction; (b) in at least one cross-section plane, the mean size of the cross sections of the said pores is greater than 0.15 ?m and less than 300 ?m; (c) in at least one cross-section plane, at least 50% by number of the pores have a convexity index Ic of greater than 87%, the convexity index of a pore being equal to the ratio Sp/Sc of the surfaces Sp and Sc delimited by the perimeter and by the convex envelope of the said pore, respectively.

Abstract: The invention relates to a method for manufacturing a thermal barrier protection covering a superalloy metal substrate and comprising at least one metal sublayer (13) and a ceramic layer (14) based on zirconia stabilized with yttrium having a column structure defining pores. The following steps are applied: impregnation of a portion of the pores of the ceramic layer (14) with a sol based on zirconia is achieved via a sol-gel route and this in order to form an anchoring sublayer (22), on said ceramic layer topped with said anchoring sub-layer (22), a continuous protective layer (20) based on oxide, is formed via a sol-gel route, and a heat treatment is carried out, whereby an outer protection layer is formed against the attack of the thermal barrier (11) by CMASes. Application to the protection of aeronautical protection parts.

Abstract: The invention relates to a method for manufacturing a thermal barrier protection covering a superalloy metal substrate and comprising at least one metal sublayer (13) and a ceramic layer (14) based on zirconia stabilized with yttrium having a column structure defining pores. The following steps are applied: impregnation of a portion of the pores of the ceramic layer (14) with a sol based on zirconia is achieved via a sol-gel route and this in order to form an anchoring sublayer (22), on said ceramic layer topped with said anchoring sub-layer (22), a continuous protective layer (20) based on oxide, is formed via a sol-gel route, and a heat treatment is carried out, whereby an outer protection layer is formed against the attack of the thermal barrier (11) by CMASes. Application to the protection of aeronautical protection parts.

Abstract: Product formed from a ceramic material, at least part of the said product not being formed from amorphous silica and including pores and satisfying the following criteria (a), (b) and (c): (a) at least 70% by number of the said pores are frustoconical tubular pores extending substantially parallel to each other in a longitudinal direction; (b) in at least one cross-section plane, the mean size of the cross sections of the said pores is greater than 0.15 ?m and less than 300 ?m; (c) in at least one cross-section plane, at least 50% by number of the pores have a convexity index Ic of greater than 87%, the convexity index of a pore being equal to the ratio Sp/Sc of the surfaces Sp and Sc delimited by the perimeter and by the convex envelope of the said pore, respectively.

Abstract: Product formed from a ceramic material, at least part of the product not being formed from amorphous silica, having pores and satisfying the following criteria: (a?) at least 70% by number of the pores are tubular pores extending substantially parallel to each other in a longitudinal direction; (b?) in at least one cross-section plane, at least 30% by number of the pores have a section of convex hexagonal shape, these pores being known hereinbelow as “hexagonal pores”, at least 80% by number of the hexagonal pores having a roundness index of greater than 0.70, the roundness index being equal to the ratio SA/LA of the lengths of the small and long axes of the ellipse in which the section is inscribed; the mean size of the cross sections of the pores is greater than 0.15 ?m and less than 25 ?m.