Turbine engine abradable systems
A turbine engine has: a first member ( 22 ) having a surface bearing an abradable coating, the abradable coating ( 36 ) being at least 90% by weight ceramic; and a second member ( 24 ) having a surface bearing an abrasive coating. The abrasive coating ( 56 ) has a metallic matrix ( 64 ) and a ceramic oxide abrasive ( 66 ) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
1. A turbine engine comprising:
a first member having a surface bearing an abradable coating, the abradable coating being at least 90% by weight ceramic; and
a second member having a surface bearing an abrasive coating, the abrasive coating comprising a metallic matrix and an ceramic oxide abrasive held by the metallic matrix,
the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating,
wherein:
at least 50% by weight of the ceramic oxide abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating;
the at least 50% by weight of the ceramic oxide abrasive is chromium oxide; and
the at least 20% by weight of the ceramic of the abradable coating is rutile titania.
2. The turbine engine of claim 1 wherein:
the abradable coating has cohesive strength 800 psi to 3000 psi (5.5 MPa to 20.7 MPa).
3. The turbine engine of claim 1 wherein:
the ceramic oxide abrasive forms at least 5% by weight of the abrasive coating.
4. The turbine engine of claim 1 wherein:
at least 90% by weight of the ceramic oxide abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
5. The turbine engine of claim 1 wherein:
at least 90% by weight of the ceramic oxide abrasive has a melting point 400K to 1850K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
6. The turbine engine of claim 1 wherein:
the abradable ceramic comprises a ceramic matrix and a ceramic filler; and
the ceramic filler is softer than the ceramic matrix.
7. The turbine engine of claim 6 wherein:
at least 50% by weight of the ceramic oxide abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
8. The turbine engine of claim 6 wherein:
the ceramic filler has a melting temperature or a sublimation temperature higher than a melting point of said ceramic matrix.
9. The turbine engine of claim 6 wherein:
the ceramic filler has a Mohs hardness 5.0 or less.
10. The turbine engine of claim 6 wherein:
the ceramic filler is selected from the group consisting of: HBN; and Magneli phase titanium oxide.
11. The turbine engine of claim 1 wherein:
the metallic matrix is an MCrAlY.
12. The turbine engine of claim 1 wherein:
the first member comprises a blade outer airseal substrate having an inner diameter surface and a bondcoat atop the inner diameter surface, the abradable coating atop the bondcoat.
13. A method for using the turbine engine of claim 1 , the method comprising:
running the engine to relatively rotate the first member and the second member; and
the running causing the abrasive coating to contact and cut the abradable coating.
14. The method of claim 13 wherein:
during the running, in absolute temperature, the local maximum operating temperature is at most 60% the melting point of at least 50% by weight of the ceramic of the abradable coating.
15. A turbine engine comprising:
a first member having a surface bearing an abradable coating, the abradable coating being at least 90% by weight ceramic; and
a second member having a surface bearing an abrasive coating, the abrasive coating comprising a metallic matrix and an ceramic oxide abrasive held by the metallic matrix,
the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating,
wherein:
at least 50% by weight of the ceramic oxide abrasive has a melting point at least 400K higher
than a melting point of at least 20% by weight of the ceramic of the abradable coating;
the at least 50% by weight of the ceramic oxide abrasive is zirconia-toughened alumina; and
the at least 20% by weight of the ceramic of the abradable coating is enstatite.
16. The turbine engine of claim 15 wherein:
the metallic matrix is an MCrAlY.
17. The turbine engine of claim 15 wherein:
the first member comprises a blade outer airseal substrate having an inner diameter surface and a bondcoat atop the inner diameter surface, the abradable coating atop the bondcoat.
18. A method for using the turbine engine of claim 15 the method comprising:
running the engine to relatively rotate the first member and the second member; and
the running causing the abrasive coating to contact and cut the abradable coating.
19. The method of claim 18 wherein:
during the running, in absolute temperature, the local maximum operating temperature is at most 60% the melting point of at least 50% by weight of the ceramic of the abradable coating.
20. The turbine engine of claim 15 wherein:
the ceramic oxide abrasive forms at least 5% by weight of the abrasive coating.