Abradable coating
The invention relates to an abradable coating for a turbomachine, comprising a mineral compound having a Mohs hardness of 6 or less and a melting temperature of more than 450° C. or even 800° C., and a polymeric compound with a content of between 40% and 70% by volume.
1. An abradable coating for a turbomachine, comprising:
a mineral compound, the Mohs hardness of which is less than or equal to 6 and the melting temperature of which is greater than 450° C., and
a polymeric compound, with a content of between 40% and 70% by volume of the abradable coating,
wherein the mineral compound is selected from: calcium fluoride, hydroxyapatite, lanthanum phosphate, diatomite, muscovite or barium sulfate, and
wherein the porosity is less than 5%.
2. The abradable coating according to claim 1 , wherein the polymeric compound is a polyester or a projectable polymer.
3. The abradable coating according to claim 1 , wherein the mineral compound is hydroxyapatite and the polymeric compound is polyester.
4. The abradable coating according to claim 1 , wherein the coating is insoluble in water and acetone.
5. A turbomachine module, comprising:
a rotor provided with a plurality of moving vanes,
a stator, and
at least one abradable coating according to claim 1 provided at an interface between a portion of the rotor and a portion of the stator.
6. The module according to claim 5 , comprising at least one underlayer with a roughness Ra between 9 μm and 40 μm on the portion of the rotor and on the portion of the stator, under the abradable coating.
7. The module according to claim 6 , wherein the roughness underlayer is located between the portion of the stator and the abradable coating.
8. The module according to claim 6 , wherein the roughness underlayer is composed of a Nickel-Aluminum alloy or a Nickel-Chromium-Aluminum alloy.
9. An aircraft turbomachine comprising a module according to claim 5 .
10. A method of making the abradable coating according to claim 1 , comprising the steps of:
mixing a powder of the mineral compound and a powder of the polymeric compound,
forming the abradable coating from said powder mixture,
applying the abradable coating to an interface between a portion of a rotor having a plurality of moving vanes and a portion of a stator of a turbomachine module.
11. The method of claim 10 , wherein the formation of the abradable coating is performed by single or double injection thermal spraying, extrusion, or hot molding.
12. The method of claim 10 , wherein the application of the abradable coating is performed by bonding with an adhesive film or by direct injection between the portion of the rotor and the portion of the stator.
13. The method according to claim 10 , wherein a roughness underlayer is deposited on the stator portion by plasma spraying in the area, wherein said underlayer has a roughness Ra of 10 μm and said underlayer is composed of a Nickel-Aluminum alloy or a Nickel-Chromium-Aluminum alloy.
14. The method of claim 10 , wherein a roughness underlayer is deposited on the stator portion by arc-wire spraying, said underlayer has a roughness Ra of 40 μm and said underlayer is composed of a Nickel-Aluminum alloy or a Nickel-Chromium-Aluminum alloy.
15. The abradable coating according to claim 1 , wherein the mineral compound has a content of between 30% and 60% by volume of the abradable coating.
16. The abradable coating according to claim 1 , wherein the polymeric compound is a liquid crystal polyester.
17. An abradable coating for a turbomachine, comprising:
a mineral compound, the Mohs hardness of which is less than or equal to 6 and the melting temperature of which is greater than 450° C., and
a polymeric compound, with a content of between 40% and 70% by volume of the abradable coating,
wherein the mineral compound is selected from: calcium fluoride, hydroxyapatite, lanthanum phosphate, diatomite, muscovite or barium sulfate,
wherein the mineral compound is hydroxyapatite and the polymeric compound is polyester.
18. An abradable coating for a turbomachine, comprising:
a mineral compound, the Mohs hardness of which is less than or equal to 6 and the melting temperature of which is greater than 450° C., and
a polymeric compound, with a content of between 40% and 70% by volume of the abradable coating,
wherein the mineral compound is selected from: calcium fluoride, hydroxyapatite, lanthanum phosphate, diatomite, muscovite or barium sulfate,
wherein the coating is insoluble in water and acetone.
19. A turbomachine module, comprising:
a rotor provided with a plurality of moving vanes,
a stator, and
at least one abradable coating according to claim 17 provided at the interface between a portion of the rotor and a portion of the stator.
20. A turbomachine module, comprising:
a rotor provided with a plurality of moving vanes,
a stator, and
at least one abradable coating according to claim 18 provided at the interface between a portion of the rotor and a portion of the stator.
21. An aircraft turbomachine comprising a module according to claim 19 .
22. An aircraft turbomachine comprising a module according to claim 20 .
23. A turbomachine module, comprising:
a rotor provided with a plurality of moving vanes,
a stator, and
at least one abradable coating provided at the interface between a portion of the rotor and a portion of the stator,
said at least one abradable coating comprising:
a mineral compound, the Mohs hardness of which is less than or equal to 6 and the melting temperature of which is greater than 450° C., and
a polymeric compound, with a content of between 40% and 70% by volume of the abradable coating,
wherein the mineral compound is selected from: calcium fluoride, hydroxyapatite, lanthanum phosphate, diatomite, muscovite or barium sulfate,
wherein the turbomachine module comprising at least one underlayer with a roughness Ra between 9 μm and 40 μm on the portion of the rotor and on the portion of the stator, under the abradable coating.
24. An aircraft turbomachine comprising a module according to claim 23 .