Back to results
US 6,089,828 AGranted
Coated article and method for inhibiting frictional wear between mating titanium alloy substrates in a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsTerry L. Hollis, Thomas J. Rising, John G. Dorrance, Bruce I. Beeman, Jr.
Life of this patent
Estimating the term…
Abstract
A pair of mating titanium alloy substrates for use in a gas turbine engine are provided, one of which comprises an aluminum bronze alloy wear resistant coating. The coating consists essentially of 9.0-11.0% aluminum (Al), 0.0-1.50% iron (Fe), and a remainder of copper (Cu). The wear resistant coating is disposed between the mating substrates and inhibits frictional wear between the mating substrates.
Claims6
A rotor blade for a gas turbine engine rotor stage, comprising:
- an airfoil;
- a blade root, attached to said airfoil;
- and
- an aluminum bronze alloy wear resistant coating applied to said blade root, said coating consisting essentially of 9.0-1 1.0% Al, 0.0-1.50% Fe, and a remainder of Cu.
1 more element
A rotor stage for a gas turbine engine rotor stage, comprising:
- a titanium alloy rotor disk, having an outer hub with a plurality of rotor blade attachment slots disposed in said outer hub;
- and
- a plurality of rotor blades, each said rotor blade having an airfoil, a blade root attached to said airfoil, and an aluminum bronze alloy wear resistant coating applied to said blade root, said coating consisting essentially of 9.0-11.0% Al, 0.0-1.50% Fe, and a remainder of Cu, wherein each said blade root is received within one of said rotor blade attachment slots within said rotor disk;
- and
- wherein said wear resistant coating is applied to a surface of each said blade root, such that said coating is disposed between said blade attachment slot and said blade root when said blade root is received within said blade attachment slot.
2 more elements
Dependencies are inferred from the claim text.