Method for making a turbine blade having a wear resistant layer

Powder metallurgy processes – Powder metallurgy processes with heating or sintering – Metal and nonmetal in final product

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Details

291568B, 419 10, 419 47, 428552, 428553, 428564, B22F 700

Patent

active

048511889

ABSTRACT:
An abrasive, wear resistant layer is applied to the tip surface of a superalloy gas turbine blade by high temperature sintering operation which produces a high strength bond between the layer and the blade, minimizes gamma prime phase growth, and prevents recrystallization in the blade. Important features of the invention include removing plastic strain damage from the tip surface prior to the sintering operation, using induction heating techniques to sinter a layer of metal powder particles and ceramic particulates to the blade tip surface, and shielding the airfoil and root portion of the blade from the radiant heating source during the sintering operation while at the same time, conductively removing heat from the blade.

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