BARRIER TO PREVENT SUPER ALLOY DEPLETION INTO NICKEL-CBN BLADE TIP COATING
A diffusion barrier coating on a nickel-based alloy substrate comprising the diffusion barrier being coupled to the substrate between the substrate and a abrasive composite material opposite the substrate, wherein the diffusion barrier comprises a nickel cobalt and chromium-aluminum-yttria powder material a high phosphorus nickel-P alloy.
1 . A diffusion barrier coating on a nickel-based alloy substrate comprising:
the diffusion barrier coupled to the substrate between the substrate and a abrasive material opposite the substrate, wherein the diffusion barrier comprises a nickel cobalt and chromium-aluminum-yttria powder material or a high phosphorus nickel-P alloy.
2 . The diffusion barrier coating on a substrate according to claim 1 , wherein said nickel-P alloy comprises a high phosphorus layered grain structure.
3 . The diffusion barrier coating on a substrate according to claim 2 , wherein said diffusion barrier consists of a nickel cobalt and chromium powder material.
4 . The diffusion barrier coating on a substrate according to claim 1 , wherein said abrasive material comprises a nickel-cubic boron nitride material.
5 . The diffusion barrier coating on a substrate according to claim 1 , wherein said diffusion barrier comprises a bond coat between said substrate and said abrasive material.
6 . The diffusion barrier coating on a substrate according to claim 1 , wherein said diffusion barrier comprises a nickel strike layer between said substrate and said diffusion barrier.
7 . A gas turbine engine component comprising:
a compressor integrally bladed rotor having a blade with an airfoil section and a tip having a substrate;
a diffusion barrier coupled to the substrate between the substrate and a composite material opposite the substrate, wherein the diffusion barrier comprises a nickel cobalt and chromium-aluminum-yttria powder material or a high phosphorus nickel-P alloy.
8 . The gas turbine engine component according to claim 7 , wherein said nickel cobalt and chromium-aluminum-yttria powder material comprises a bond layer.
9 . The gas turbine engine component according to claim 7 , wherein said high phosphorus nickel-P alloy comprises a layered grain structure.
10 . The gas turbine engine component according to claim 9 , wherein the diffusion barrier includes multiple layers.
11 . The gas turbine engine component according to claim 9 , wherein said diffusion barrier comprises a nickel strike layer between said substrate and said diffusion barrier.
12 . The gas turbine engine component according to claim 7 , wherein said substrate comprises a nickel-based alloy.
13 . The gas turbine engine component according to claim 7 , wherein said integrally bladed rotor is located in a high pressure compressor section of the gas turbine engine.
14 . A process for diffusion inhibition in a nickel-based alloy substrate of a gas turbine engine component comprising:
applying a diffusion barrier coupled to the substrate, wherein the diffusion barrier comprises a nickel cobalt and chromium-aluminum-yttria powder material or a high phosphorus nickel-P alloy;
coating said diffusion barrier under a abrasive composite; and
subjecting said gas turbine engine component with nickel-based alloy substrate to at least one of a heat treatment and an engine operation.
15 . The process of claim 14 , coating said a nickel cobalt and chromium-aluminum-yttria powder material coating or a high phosphorus nickel-P alloy materials comprises a bond coat.
16 . The process of claim 14 , wherein the diffusion barrier includes multiple layers.
17 . The process of claim 14 , wherein said matrix abrasive material comprises a nickel-cubic boron nitride material.
18 . The process of claim 14 , further comprising:
preventing Cr, Al, and Ti depletion from the nickel-based alloy substrate by reducing diffusion between said nickel-based alloy substrate and said matrix abrasive composite with said diffusion barrier.