HEAT TREATMENT AND REPAIR OF COBALT-BASE SUPERALLOY ARTICLES

摘要

The invention relates to an improved process gas turbine engine component repair superalloy cobalt, comprising applying a mixture of a base alloy powder and a base alloy powder added to a lowering of the melting agent on the surface of the component, then heating between 2250 and 2300 ° F in order to spread the melting point lowering agent isothermally into the base alloy. Then one proceeds to a step of applying a protective coating which is used during a heating cycle aging the base material. The component obtained has high-temperature creep properties substantially superior to those obtained by the method of the prior art. The same temperature cycle is also useful in the initial heat treatment of the cobalt based superalloy, and may also be used in the regeneration of components having undergone prolonged exposure to engine operating conditions.