Preform and method of repairing nickel-base superalloys and components repaired thereby
US7506793B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Oct 4, 2007 |
| Grant date | Mar 24, 2009 |
| Priority date | — |
| Expiry date | Oct 4, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/12944
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.