Compressor rotor with coated blades
US10443411B2 · kind B2 · utility
2Cited by
16References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 18, 2017 |
| Grant date | Oct 15, 2019 |
| Priority date | — |
| Expiry date | Feb 22, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.