United Technologies Corporation

S Michael Kurpaska

Norman Pietruska

An improved method is described for repairing Co-base superalloy gas turbine engine components by applying a mixture of base alloy powder and base alloy powder with a melting point depressant to the surface of the component and heating at 2250-2300.degree. F. to diffuse the melting point depressant isothermally into the base alloy. A protective coating is then applied, during which a heating cycle which ages the base material is used. The resultant component has high temperature creep properties which are significantly better than achieved using the prior art process. The same temperature cycle is also useful in the initial heat treatment of Co-base superalloys, and can also be used for rejuvenation of components which have experienced extensive exposure to engine operating conditions.

Method of heat treating a cobalt-base alloy

An improved method is described for restoring the mechanical properties to carbide-containing Co-based superalloy gas turbine components which have been exposed to high temperatures and pressures for extended periods of time. The method includes solution heat treating to 2250.degree.-2300.degree. F. for one to twelve hours to dissolve complex carbides, and aging at approximately 1965.degree.-1975.degree. F. for two to twenty four hours. The rejuvenated components exhibit excellent high temperature creep properties.

Method of rejuvenating cobalt-base superalloy articles

An improved method is described for repairing Co-base superalloy gas turbine engine components by applying a mixture of base alloy powder and base alloy powder with a melting point depressant to the surface of the component and heating at 2250.degree.-2300.degree. F. to diffuse the melting point depressant isothermally into the base alloy. A protective coating is then applied, during which a heating cycle which ages the base material is used. The resultant component has high temperature creep properties which are significantly better than achieved using the prior art process. The same temperature cycle is also useful in the initial heat treatment of Co-base superalloys, and can also be used for rejuvenation of components which have experienced extensive exposure to engine operating conditions.

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Manchester, CT, United States of America

S Michael Kurpaska