Low friction, wear resistant piston seal
A piston seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a metal alloy binder phase and a hard particle phase distributed through the binder phase.
1. A piston seal assembly for a gas turbine engine, comprising:
a seal comprised of a nickel-based superalloy;
a component in contact with the seal and defining a seal-counterface; and
a coating on the seal at the seal-counterface, wherein the coating comprises a metal alloy binder phase and a hard particle phase distributed through the binder phase, wherein the hard particle phase comprises particles of a material selected from the group consisting of Cr 2 O 3 , Al 2 O 3 , carbides, chromium carbides, silicon carbides and combinations thereof, wherein the hard particle phase comprises hard particles having a particle size of between 5 and 150 μm, and wherein the coating has a thickness of between 0.0005 in and 0.005 in.
2. The assembly of claim 1 , wherein the hard particle phase comprises particles of Cr 2 O 3 .
3. The assembly of claim 1 , wherein the metal alloy binder phase comprises a Co—Cr—W alloy.
4. The assembly of claim 1 , wherein the metal alloy binder phase contains between 28 and 32 wt. % chromium, between 3.5 and 5.5 wt. % of tungsten, between 0.9 and 1.4 wt. % carbon, up to 3.0 wt. % nickel, up to 2.0 wt. % silicon, up to 3.0 wt. % iron, up to 2.0 wt. % manganese, up to 1.5 wt. % molybdenum and balance cobalt.
5. The assembly of claim 1 , wherein the coating contains between 60 and 80% volume of the metal alloy binder phase and between 20 and 40% volume of the hard particle phase.
6. The assembly of claim 1 , wherein the seal comprises an age hardening austenitic nickel-based superalloy.
7. The assembly of claim 1 , wherein the seal has non-contact surfaces that are not in contact with the component, and the coating is on the seal at the seal-counterface, and not on the non-contact surfaces.
8. The seal assembly of claim 1 , wherein the component comprises two components, with the seal mounted between the two components to define two seal-counterfaces, and wherein the coating is on the seal at both of the two seal-counterfaces.
9. The assembly of claim 8 , wherein the two components comprise a mid-turbine-frame (MTF) vane and an outer air seal.
10. A seal for a gas turbine engine, comprising a seal comprised of a nickel-based superalloy and a coating on the seal, wherein the coating comprises a metal alloy binder phase and a hard particle phase distributed through the binder phase, wherein the hard particle phase comprises particles of a material selected from the group consisting of Cr 2 O 3 , Al 2 O 3 , carbides, chromium carbides, silicon carbides and combinations thereof, wherein the hard particle phase comprises hard particles having a particle size of between 5 and 150 μm, and wherein the coating has a thickness of between 0.0005 in. and 0.005 in.
11. The seal of claim 10 , wherein the hard particle phase comprises particles of Cr 2 O 3 .
12. The seal of claim 10 , wherein the metal alloy binder phase comprises a Co—Cr—W alloy.
13. The seal of claim 10 , wherein the metal alloy binder phase contains between 28 and 32 wt. % chromium, between 3.5 and 5.5 wt. % of tungsten, between 0.9 and 1.4 wt. % carbon, up to 3.0 wt. % nickel, up to 2.0 wt. % silicon, up to 3.0 wt. % iron, up to 2.0 wt. % manganese, up to 1.5 wt. % molybdenum and balance cobalt.
14. The seal of claim 10 , wherein the coating contains between 60 and 80% volume of the metal alloy binder phase and between 20 and 40% volume of the hard particle phase.
15. A gas turbine engine having a piston seal assembly, comprising:
two structural components defining an interface, wherein the structural components are subjected to vibratory motion during operation of the gas turbine engine; and
a seal according to claim 1 positioned between the components.
16. The gas turbine engine according to claim 15 , wherein the components are a vane and an outer air seal.
17. A gas turbine engine having a piston seal assembly, comprising:
two structural components defining an interface, wherein the structural components are subjected to vibratory motion during operation of a gas turbine engine; and
a seal according to claim 10 positioned between the components.
18. The gas turbine engine according to claim 17 , wherein the components are a vane and an outer air seal.