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.
Claims8
An abrasive coating system for a substrate of an airfoil in a turbine engine compressor, comprising:
- a plurality of grit particles adapted to be placed on a top surface of said substrate;
- a non-diffused matrix material bonded to said top surface;
- said non-diffused matrix material partially surrounds said grit particles, said non-diffused matrix material comprising plated material and alloying elements distributed throughout the non-diffused matrix material, wherein said grit particles extend above said non-diffused matrix material relative to said top surface;
- and
- a film of oxidant resistant coating applied over said plurality of grit particles and said non-diffused matrix material.
8-19. (canceled)
Dependencies are inferred from the claim text.