Abrasive material, especially for turbine blade tips

Details Abrasive material, especially for turbine blade tips Abrasive material, especially for turbine blade tips

1986-12-29

1988-04-05

Lechert, Jr., Stephen J.

Specialized metallurgical processes, compositions for use therei

Compositions

Consolidated metal powder compositions

75230, 75236, 75244, 419 13, 419 17, 419 23, 419 47, C22C 2904

Patent

active

047356561

ABSTRACT:
An abrasive material comprised of a metal matrix and evenly distributed ceramic particulates, is made by mixing powder metal with the ceramic powder and heating to a temperature sufficient to melt most, but not all of the powder. In this way the ceramic does not float to the top of the material, yet a dense material is obtained. A nickel superalloy matrix will have at least some remnants of the original powder metal structure, typically some equiaxed grains, along with a fine dendritic structure, thereby imparting desirable high temperature strength when the abrasive material is applied to the tips of blades of gas turbine engines. Preferred matrices have a relatively wide liquidus-solidus temperature range, contain a melting point depressant, and a reactive metal to promote adhesion to the ceramic.

REFERENCES:
patent: 4063939 (1977-12-01), Weaver et al.
patent: 4148494 (1979-04-01), Zelahy
patent: 4277703 (1980-10-01), Stalker et al.
patent: 4627896 (1986-12-01), Natmy et al.

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