Method of reconditioning a turbine blade
US7231713B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 16, 2004 |
| Grant date | Jun 19, 2007 |
| Priority date | — |
| Expiry date | Dec 22, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49746
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of reconditioning a rotating blade (1) with a shroud (8) following the operation in a gas turbine, includes the application of a barrier (14) placed on the edge of the shroud (8) facing the edge of a shroud (8) of an adjacent blade having creep deformation. The barrier (14) prevents hot gas ingestion into a shroud cavity (10). It is pre-fabricated or built-up layer-by-layer by welding or laser cladding or other methods. Additionally, the mass of the shroud (8) is reduced in order to re-establish the initial mass of the shroud. A thermal barrier coating (15) is additionally applied to the surfaces of the shroud (8) that are exposed to the hot gas of the turbine. The method significantly increases the lifetime of the blade (1).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.