Method for replacing blade tips of directionally solidified and single crystal turbine blades
US5822852A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jul 14, 1997 |
| Grant date | Oct 20, 1998 |
| Priority date | — |
| Expiry date | Jul 14, 2017 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49742
- WIPO fieldMachine tools
- WIPO sectorMechanical engineering
Abstract
A method for repairing a blade tip of a turbine blade of a gas turbine engine. The method is particularly directed to replacing the squealer tip (14) of a directionally solidified (DS) or single crystal (SX) turbine blade (10), and can be carried out using a brazing or welding technique. The method generally entails the step of machining the tip (14) to remove any damaged, worn, oxidized or eroded portions thereof sustained by the blade (10) during engine operation. A DS or SX superalloy replacement tip (18) is then placed on the surface generated by the machining operation. If a brazing operation is used, a brazing alloy composition (16) is first applied to the blade tip or replacement tip (18) prior to placement of the replacement tip (18). The brazing alloy composition (16) is composed of at least two alloys, one of which having a melting point lower than the recrystallization temperature and solvus temperature of the superalloy of the turbine blade (10), such that heating causes the brazing alloy composition (16) to flow and thereby join the replacement tip (18) to the blade tip of the turbine blade (10). Alternatively, if a welding operation is employed, the joining operation …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.