Gas turbine engine blade tip treatment
US10094227B2 · kind B2 · utility
0Cited by
5References
20Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jul 20, 2015 |
| Grant date | Oct 9, 2018 |
| Priority date | — |
| Expiry date | Apr 13, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S977/776
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A fan blade and method of manufacturing a fan blade includes a metallic fan blade body with a crystalline oxidation layer and immersing the crystalline oxidation layer in a solution of ceramic nanosheets in suspension. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer, wherein the crystalline oxidation layer includes pores containing ceramic nanosheets.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.