Dense abradable coating with brittle and abradable components
Various embodiments include a dense abradable coating, a method of reducing rub damage to a turbine engine part by applying the dense abradable coating thereto, and a turbine engine part having the abradable coating thereon. Particular embodiments include a dense abradable coating including a pore-free metallic composite, a high-aluminum containing brittle alloy, and a plurality of hollow abradable particles.
1. An abradable coating comprising:
a metallic composite, the metallic composite being pore free and including two or more metals selected from iron (Fe), nickel (Ni), aluminum (Al), chromium (Cr), titanium (Ti), yttrium (Y) and cobalt (Co);
a brittle alloy, the brittle alloy including at least 20 weight percent of aluminum (Al) and at least one other metal, wherein the abradable coating includes 20 to 30 weight percent of the brittle alloy; and
a plurality of abradable particles, the plurality of abradable particles including hollow spheres of one or more oxides, wherein the metallic composite constitutes 40 to 60 weight percent of the abradable coating and includes CoNiCrAlY.
2. The abradable coating of claim 1 , wherein the metallic composite includes MCrAlY, where M is at least two of iron (Fe), nickel (Ni) and cobalt (Co).
3. The abradable coating of claim 1 , wherein the at least one other metal of the brittle alloy is selected from titanium (Ti), nickel (Ni), cobalt (Co), magnesium (Mg), iron (Fe), tungsten (W), zinc (Zn), manganese (Mn), silicon (Si), chromium (Cr), carbon (C) and beryllium (Be).
4. The abradable coating of claim 1 , wherein the brittle alloy constitutes 20 to 30 weight percent of the abradable coating and includes nickel (Ni).
5. The abradable coating of claim 1 , wherein the one or more oxides of the plurality of abradable particles are selected from zinc oxide, silicon oxide, aluminum oxide, zirconium oxide, cerium oxide, fly ash, and hydroxyapatite.
6. The abradable coating of claim 1 , wherein the plurality of abradable particles constitute 20 to 30 weight percent of the abradable coating and have a particle size within a range of 100 nanometers (nm) to 100 microns (μm).
7. The abradable coating of claim 1 , comprising:
approximately 50 weight percent of CoNiCrAlY as the metallic composite,
approximately 20 weight percent of NiA 1 20% as the brittle alloy, and
approximately 30 weight percent of hollow ZnO particles as the plurality of abradable particles.
8. The abradable coating of claim 1 , wherein a thickness of the coating is within a range of 120 mils to 200 mils.
9. The abradable coating of claim 1 , wherein the coating is monolithic or patterned.
10. A method of reducing rub damage to at least one part of a turbine engine, the method comprising:
applying an abradable coating according to claim 1 to a first part of a turbine engine in a location prone to rubbing with a second part of the turbine engine.
11. The method of claim 10 , wherein the applying of the abradable coating includes at least one of a high velocity oxygen fuel (HVOF) coating process, a low pressure plasma spray (LPPS) coating process, a high velocity plasma spray (HVPS) coating process, a high velocity air fuel (HVAF) coating process, and a suspension thermal sprayed high velocity air fuel (STS-HVAF) coating process.
12. The method of claim 10 , wherein
the metallic composite includes MCrAlY, where M is at least two of iron (Fe), nickel (Ni) and cobalt (Co);
the at least one other metal of the brittle alloy is selected from titanium (Ti), nickel (Ni), cobalt (Co), magnesium (Mg), iron (Fe), tungsten (W), zinc (Zn), manganese (Mn), silicon (Si), chromium (Cr), carbon (C) and beryllium (Be); and
the one or more oxides of the plurality of abradable particles are selected from zinc oxide, silicon oxide, aluminum oxide, zirconium oxide, cerium oxide, fly ash, and hydroxyapatite.
13. The method of claim 10 , wherein the plurality of abradable particles have a particle size within a range of 100 nanometers (nm) to 100 microns (μm).
14. The method of claim 10 , wherein the abradable coating comprises:
the metallic composite including 40 to 60 weight percent of MCrAlY, where M is at least two of iron (Fe), nickel (Ni) and cobalt (Co);
the brittle alloy including 20 to 30 weight percent of NiAl, where NiAl includes at least 20 weight percent of aluminum (Al); and
the plurality of abradable particles including 20 to 30 weight percent, where hollow zinc oxide is one of the one or more oxides.
15. The method of claim 10 , wherein applying the abradable coating applies the abradable coating with a thickness within a range of 120 mils to 200 mils and with a bond strength of 8000 pounds per square inch (psi) or greater.
16. The method of claim 10 , wherein applying the abradable coating applies the abradable coating at a thickness so rub damage to the second part for a turbine engine is less than 25% of a total incursion depth, the total incursion depth being the sum of a wear depth of the second part and a wear depth of the abradable coated first part.
17. A turbine engine part having an abradable coating according to claim 1 on at least a portion of a surface thereof, the abradable coating comprising:
metallic composite including 40 to 60 weight percent of MCrAlY, where M is at least two of iron (Fe), nickel (Ni) and cobalt (Co);
brittle alloy including 20 to 30 weight percent of NiAl, where NiAl includes at least 20 weight percent of aluminum (Al); and
the plurality of abradable particles including 20 to 30 weight percent, where the plurality of abradable particles have a particle size within a range of 100 nanometers (nm) to 100 microns (μm), and where hollow zinc oxide is one of the one or more oxides of the plurality of abradable particles.
18. The turbine engine part of claim 17 , wherein the abradable coating has a thickness within a range of 120 mils to 200 mils and a bond strength with the turbine engine part of 8000 pounds per square inch (psi) or greater.