Composite material part with a silicon-containing ceramic matrix protected against corrosion

1. A method of forming an environmental barrier on a substrate of ceramic matrix composite material containing silicon, the method comprising forming an anticorrosion protection layer of an aluminosilicate type compound of an alkali or alkaline-earth or rare earth element, the method being characterized in that a chemical barrier forming layer of aluminum nitride is interposed between the substrate and the anticorrosion protection layer, wherein the aluminum nitride layer is formed directly on the substrate and the anti-corrosion layer is formed directly on the aluminum nitride layer, and wherein the anti-corrosion layer is formed of an aluminosilicate compound of an alkali, alkaline earth, or rare-earth element.

2. A method according to claim 1 , characterized in that the aluminum nitride layer is formed having a thickness lying in the range 10 μm to 100 μm, approximately.

3. A method according to claim 1 , characterized in that the aluminum nitride layer is formed by a chemical vapor deposition process.

4. A method according to claim 1 , characterized in that the aluminum nitride layer is formed by a plasma-enhanced chemical vapor deposition process.

5. A method according to claim 1 , characterized in that:

the aluminum nitride layer is formed having a thickness lying in the range 10 μm to 100 μm, approximately;

the aluminum nitride layer is formed by a chemical vapor deposition process.

6. A part comprising a composite material substrate with a ceramic matrix containing silicon and an environmental barrier formed on the substrate and comprising an anticorrosion protection layer containing an aluminosilicate type compound of an alkali or alkaline-earth or rare-earth element, the part being characterized in that a layer of aluminum nitride is interposed between the substrate and the anticorrosion protection layer, wherein the aluminum nitride layer is formed directly on the substrate and the anti-corrosion layer is formed directly on the aluminum nitride layer, and wherein the anti-corrosion layer is formed of an aluminosilicate compound of an alkali, alkaline earth, or rare-earth element.

7. A part according to claim 6 , characterized in that the layer of aluminum nitride is of thickness lying in the range 10 μm to 100 μm, approximately.

8. A component for the hot portion of an industrial or aviation gas turbine, the component being constituted by a part according to claim 7 .

9. A component according to claim 8 forming a turbine ring, and characterized in that it is also provided with an outer layer of abradable material.

10. A part according to claim 6 , characterized in that at least one outer phase of the composite material matrix comprises silicon carbide or a ternary silicon-boron-carbon system.

11. A part according to claim 6 , characterized in that the anticorrosion protection layer is a barium and strontium aluminosilicate (BSAS).

12. A part according to claim 11 , characterized in that it is also provided with an outer layer forming a thermal barrier.

13. A component for the hot portion of an industrial or aviation gas turbine, the component being constituted by a part according to claim 6 .

14. A component according to claim 13 forming a turbine ring, and characterized in that it is also provided with an outer layer of abradable material.

15. A part according to claim 6 , characterized in that:

the layer of aluminum nitride is of thickness lying in the range 10 μm to 100 μm, approximately;

at least one outer phase of the composite material matrix comprises silicon carbide or a ternary silicon-boron-carbon system;

the anticorrosion protection layer is a barium and strontium aluminosilicate (BSAS).

16. A part according to claim 15 , characterized in that it is also provided with an outer layer forming a thermal barrier.

17. A component for the hot portion of an industrial or aviation gas turbine, the component being constituted by a part according to claim 16 .

18. A component according to claim 17 forming a turbine ring, and characterized in that it is also provided with an outer layer of abradable material.

19. A component for the hot portion of an industrial or aviation gas turbine, the component being constituted by a part according to claim 15 .

20. A component according to claim 19 forming a turbine ring, and characterized in that it is also provided with an outer layer of abradable material.