Method of manufacturing a coated turbine blade and a coated turbine vane
US10648349B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 8, 2018 |
| Grant date | May 12, 2020 |
| Priority date | — |
| Expiry date | Nov 10, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02P10/25
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.