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AssigneeGeneral Electric Company
InventorSujith Sathian
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A process for repairing a turbine component of a turbomachine, as well as a sintered preform used in the process and a high gamma-prime nickel-base superalloy component repaired thereby. The sintered preform contains a sintered mixture of powders of a cobalt-base braze alloy and a cobalt-base wear-resistant alloy. The braze alloy constitutes at least about 10 up to about 35 weight percent of the sintered preform and contains a melting point depressant such as boron. The preform is formed by mixing powders of the braze and wear-resistant alloys to form a powder mixture, and then sintering the powder mixture. To use the preform, a surface portion of the turbine component is removed to expose a subsurface portion, followed by diffusion bonding of the preform to the subsurface portion to form a wear-resistant repair material containing the braze alloy dispersed in a matrix of the wear-resistant alloy.
A sintered preform comprising a sintered mixture of powders of a cobalt-base braze alloy and a cobalt-base wear-resistant alloy, the cobalt-base braze alloy constituting about 10 to about 35 weight percent of the sintered preform and containing a sufficient amount of boron so that the cobalt-base braze alloy has a melting temperature of about 1090° C. to about 1230° C.
A repaired turbine component of a gas turbine, the turbine component being formed of a nickel-base superalloy having a composition and gamma-prime content that causes the turbine component to crack if subjected to gas tungsten arc welding, the turbine component having a repaired region with a wear-resistant repair material diffusion bonded thereto, the wear-resistant repair material consisting of a cobalt-base braze alloy dispersed in a matrix material of a wear-resistant cobalt-base alloy.
A method of repairing a turbine component of a gas turbine, the method comprising the steps of:
Dependencies are inferred from the claim text.