Process and material configuration for making hot corrosion resistant HPC abrasive blade tips
AssigneeRaytheon Technologies Corporation
InventorChristopher W. Strock
Life of this patent
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Abstract
An abrasive coating system for a substrate of an airfoil in a turbine engine high pressure compressor, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, the matrix material consisting of unalloyed chromium and unalloyed aluminum distributed throughout the matrix material, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.
Claims12
A process for coating a turbine engine compressor airfoil with an abrasive, said process comprising:
- applying an adhesion layer onto a tip of the airfoil;
- adhering a plurality of grit particles to said adhesion layer, wherein spaces are formed between said grit particles;
- applying a non-diffused matrix material to said adhesion layer and connecting to said grit particles, said non-diffused matrix material comprising plated material and alloying elements distributed throughout the non-diffused matrix material;
- applying a film of oxidant resistant coating over said plurality of grit particles and said non-diffused matrix material;
- exposing said airfoil to an operating temperature of at least 1000 degrees Fahrenheit;
- diffusing the plated material and the alloying elements within a diffused matrix material;
- and
- forming an alloy of the plated material and the alloying elements within the diffused matrix material.
Dependencies are inferred from the claim text.