Gas turbine hot gas component repair method
US8156649B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 8, 2009 |
| Grant date | Apr 17, 2012 |
| Priority date | — |
| Expiry date | May 14, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49732
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.