Outer airseal abradable rub strip
A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, ≥35% nickel, 12.0-20.0% cobalt, 5.0-15.0% aluminum, and 5.0-15.0% chromium.
1. A blade outer airseal having:
a body comprising:
an inner diameter (ID) surface;
an outer diameter (OD) surface;
a leading end;
a trailing end;
a metallic substrate; and
a coating system atop the substrate along at least a portion of the inner diameter surface,
wherein:
at least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant;
at 1200° F. the metallic matrix has at least 98% by volume fcc and L12 phases combined with at least 30% L12; and
the metallic matrix comprises, by weight:
≥50% nickel;
12.0-20.0% cobalt;
5.0-15.0% aluminum; and
5.0-15.0% chromium.
2. The blade outer airseal of claim 1 wherein the metallic matrix comprises, by weight:
≥55% nickel.
3. The blade outer airseal of claim 1 wherein the metallic matrix comprises, by weight:
≥55% nickel;
15.0-20.0% cobalt;
6.0-10.0% aluminum; and
8.0-12.0% chromium.
4. The blade outer airseal of claim 1 wherein the metallic matrix comprises, by weight:
at least 15.0% combined aluminum and chromium.
5. The blade outer airseal of claim 1 wherein an iron content of the metallic matrix is no more than 5.0% by weight.
6. The blade outer airseal of claim 1 wherein at 1200° F. the metallic matrix has:
at least 98% by volume fcc and L12 phases combined with at least 40% L12.
7. The blade outer airseal of claim 1 wherein the metallic matrix further comprises, by weight:
no more than 4.0% iron
no more than 5.0% combined of all other elements; and
no more than 1.5% of any individual other element.
8. The blade outer airseal of claim 1 wherein the metallic matrix further comprises, by weight:
no more than 5.0% combined of all other elements; and
no more than 1.5% of any individual other element.
9. The blade outer airseal of claim 1 wherein the metallic matrix further comprises, by weight:
no more than 0.5% combined of niobium, molybdenum, tantalum, tungsten, and rhenium.
10. The blade outer airseal of claim 1 wherein the metallic matrix further comprises, by weight:
≤1.0% hafnium;
≤1.0% silicon; and
≤1.0% yttrium.
11. The blade outer airseal of claim 1 wherein:
over the first area of the inner diameter surface, the coating system comprises the abradable layer and a thermal barrier layer between the abradable layer and the substrate.
12. The blade outer airseal of claim 1 wherein:
the abradable layer has a volume content of said solid lubricant of 5.0% to 80%.
13. The blade outer airseal of claim 1 wherein:
the solid lubricant comprises HBN.
14. The blade outer airseal of claim 1 wherein:
the abradable layer has a volume content of said metallic matrix of 20% to 50%.
15. The blade outer airseal of claim 1 wherein:
the abradable layer has less than 20% porosity.
16. The blade outer airseal of claim 1 wherein one or more of:
the coating system has a bondcoat between the abradable layer and the substrate; and
the substrate is a nickel-based superalloy.
17. A method for manufacturing the blade outer airseal of claim 1 , the method comprising:
thermal spray of the abradable layer.
18. A method for using the blade outer airseal of claim 1 , the method comprising:
installing the blade outer airseal on a turbine engine; and
running the turbine engine so that blade tips rub the abradable layer.
19. A blade outer airseal having:
a body comprising:
an inner diameter (ID) surface;
an outer diameter (OD) surface;
a leading end;
a trailing end;
a metallic substrate; and
a coating system atop the substrate along at least a portion of the inner diameter surface,
wherein:
at least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a nickel-based metallic matrix and a solid lubricant; and
at 1200° F. the metallic matrix has:
at least 40% primary fcc;
at least 40% by volume gamma prime (L12); and
at most 10% by volume beta (B2) crystal structure.
20. A gas turbine engine compressor section comprising:
a stage of blades having Ni-based substrates; and
the blade outer airseal of claim 19 wherein the inner diameter (ID) surface faces tips of the blades.
21. The gas turbine engine compressor section of claim 20 wherein the metallic matrix comprises, by weight:
≥50% nickel;
12.0-20.0% cobalt;
5.0-15.0% aluminum;
5.0-15.0% chromium;
no more than 4.0% iron;
no more than 5.0% combined of all other elements; and
no more than 1.5% of any individual other element.