# US 2008/0187777 A1 · Preform and method of repairing nickel-base superalloys and components repaired thereby > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2008/0187777 A1 - Document ID: US20080187777A1 - Status: Published application - Kind: A1 - Application number: 11/867,118 - Filed: 2007-10-04 - Published: 2008-08-07 - Earliest claimed: 2004-12-17 - Assignees: General Electric Company - Inventors: Sujith Sathian - Web page: https://patentgrep.com/patent/US20080187777A1 ## CPC - B23P 6/005: {using only replacement pieces of a particular form} - B22F 1/09: {Mixtures of metallic powders} - B22F 7/062: {involving the connection or repairing of preformed parts} - C23C 10/28: using solids, e.g. powders, pastes - C23C 10/52: more than one element being diffused in one step - C23C 26/00: Coating not provided for in groups C23C2/00 - C23C24/00 - F01D 5/005: {Repairing methods or devices} - F05D 2230/232: by welding - F05D 2230/236: Diffusion bonding - Y10T 428/12042: Porous component - Y10T 428/12063: Nonparticulate metal component - Y10T 428/12181: Composite powder [e.g., coated, etc.] - Y10T 428/12861: Group VIII or IB metal-base component - Y10T 428/12931: Co-, Fe-, or Ni-base components, alternative to each other - Y10T 428/12944: Ni-base component - B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q) - B22F: WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER (making alloys by powder metallurgy C22C); APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER - C23C: COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL (making metal-coated products by extrusion B21C23/22; covering with metal by connecting pre-existing layers to articles, see the relevant places, e.g. B21D39/00, B23K; metallising of glass C03C; metallising mortars, concrete, artificial stone, ceramics or natural stone C04B41/00; enamelling of, or applying a vitreous layer to, metals C23D; treating metal surfaces or coating of metals by electrolysis or electrophoresis C25D; single-crystal film growth C30B; by metallising textiles D06M11/83; decorating textiles by locally metallising D06Q1/04) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The repaired turbine component according to claim 1, wherein the gamma-prime content of the nickel-base superalloy is about 55 to 59 volume percent. ### Claim 3 (depends on 1) The repaired turbine component according to claim 1, wherein the wear-resistant repair material has a nominal composition consisting of, by weight, about 18.5% chromium, about 0.92% nickel, about 0.64% tungsten, about 0.34% tantalum, about 0.23% boron, about 0.12% carbon, about 0.021% titanium about 26.5% molybdenum about 3.2% silicon, and the balance cobalt and incidental impurities. ### Claim 4 (depends on 1) The repaired turbine component according to claim 1, wherein the wear-resistant repair material has a nominal composition consisting of, by weight, about 27.6% chromium, about 5.5% nickel, about 18.9% tungsten, about 0.366% tantalum, about 0.24% boron, about 0.87% carbon, about 0.023% titanium, about 2.7% iron, about 0.91% vanadium, and the balance cobalt and incidental impurities. ### Claim 5 (depends on 1) The repaired turbine component according to claim 1, wherein the nickel-base superalloy consists of, by weight about 9.5 to about 10 chromium, about 7 to about 8 cobalt, about 3.35 to about 3.65 titanium, about 4.1 to about 4.3 aluminum, about 5.75 to about 6.25 tungsten, about 1.30 to about 1.70 molybdenum, about 4.60 to about 5.0 tantalum, about 0.06 to about 0.1 carbon, about 0.0080 to about 0.010 zirconium, about 0.008 to about 0.0105 boron, and the balance being nickel and incidental impurities.