Part coated with a composition for protection against CMAS with controlled cracking, and corresponding treatment method
The invention relates to a turbomachine part comprising a substrate consisting of a metal material, or a composite material, and also comprising a layer of a coating for protection against the infiltration of CMAS-type compounds, at least partially covering the surface of the substrate, the protective coating layer comprising a plurality of elementary layers including elementary layers of a first assembly of elementary layers inserted between elementary layers of a second assembly of elementary layers, each elementary layer of the first assembly and each elementary layer of the second assembly comprising an anti-CMAS compound, and each contact zone between an elementary layer of the first assembly and an elementary layer of the second assembly forming an interface conducive to the spreading of cracks along said interface.
1. A turbomachine part comprising:
a substrate of metallic material, or of composite material; and
a protective coating layer against the infiltration of compounds of the oxides of calcium, magnesium, aluminum or silicon type, referred to as CMAS type, the coating layer at least partially covering the surface of the substrate,
wherein the protective coating layer comprises a plurality of elementary layers,
wherein elementary layers of a first set of the plurality of elementary layers are interposed between elementary layers of a second set of the plurality of elementary layers, each elementary layer of the first set and each elementary layer of the second set comprising an anti-CMAS compound, and
wherein each contact zone between an elementary layer of the first set and an elementary layer of the second set forms an interface promoting a propagation of cracks along said interface,
wherein each elementary layer of the first set has a toughness which differs by at least 0.7 MPa·m 1/2 from the toughnesses of all elementary layers of the second set, or
wherein each elementary layer of the first set has a coefficient of thermal expansion which differs by at least 3.5 10 −6 K −1 from the coefficients of thermal expansion of all elementary layers of the second set.
2. The turbomachine part as claimed in claim 1 , wherein each elementary layer of the first set has a toughness which differs by at least 0.7 MPa·m 1/2 from the toughnesses of all elementary layers of the second set, wherein the toughness of each of the elementary layers of the first set is comprised between 0.5 and 1.5 MPa·m 1/2 and the toughness of each of the elementary layers of the second set is comprised between 1.5 and 2.2 MPa·m 1/2 .
3. The turbomachine part as claimed in claim 1 , wherein each elementary layer of the first set has a toughness which differs by at least 0.7 MPa·m 1/2 from the toughnesses of all elementary layers of the second set, wherein the elementary layers of the first set comprise a material from the following list: RE2Zr2O7 with RE a material of the rare earth family, Ba(Mg1/3Ta2/3)O3, La(Al1/4Mg1/2Ta1/4)O3, or comprise a mixture of several of these materials.
4. The turbomachine part as claimed in claim 1 , wherein each elementary layer of the first set has a toughness which differs by at least 0.7 MPa·m 1/2 from the toughnesses of all elementary layers of the second set, wherein the elementary layers of the second set comprise a material from the following list: YSZ, Y2O3-ZrO2-Ta2O5, BaZrO3, CaZrO3, SrZrO3, or comprise a mixture of several of these materials.
5. The turbomachine part as claimed in claim 1 , wherein each elementary layer of the first set has a coefficient of thermal expansion which differs by at least 3.5 10 −6 K −1 from the coefficients of thermal expansion of all elementary layers of the second set, wherein the coefficient of thermal expansion of each of the elementary layers of the first set is comprised between 3.5 and 6.0 10 −6 K −1 and the coefficient of thermal expansion of each of the elementary layers of the second set is comprised between 7.0 and 12.0 10 −6 K −1 .
6. The turbomachine part as claimed in claim 1 , wherein each elementary layer of the first set has a coefficient of thermal expansion which differs by at least 3.5 10 −6 K −1 from the coefficients of thermal expansion of all elementary layers of the second set, wherein the elementary layers of the first set comprise RE2Si2O7 or RE2SiO5 with RE a material of the rare-earth family, or comprise a mixture of these materials.
7. The turbomachine part as claimed in claim 1 , wherein each elementary layer of the first set has a coefficient of thermal expansion which differs by at least 3.5 10 −6 K −1 from the coefficients of thermal expansion of all elementary layers of the second set, wherein the elementary layers of the second set comprise a material from the following list: YSZ, Y2O3-ZrO2-Ta2O5, BaZrO3, CaZrO3, SrZrO3, RE2Zr2O7 with RE a material of the rare earth family, Ba(Mg1/3Ta2/3)O3, La(Al1/4Mg1/2Ta1/4)O3, YAG, or comprise a mixture of several of these materials.
8. The turbomachine part as claimed in claim 1 , wherein a ratio of a cumulative thickness of the elementary layers of the first set to a cumulative thickness of the elementary layers of the second set is between 1:2 and 2:1.
9. The turbomachine part as claimed in claim 1 , where a total thickness of the protective coating layer is between 20 and 500 μm.
10. The turbomachine part as claimed in claim 1 , wherein the turbomachine part forms a turbine moving blade, or a high-pressure turbine nozzle, or a high-pressure turbine ring, or a combustion chamber wall.
11. The turbomachine as claimed in claim 9 , wherein the total thickness of the protective coating layer is between 20 and 300 μm.