Fan blade for a gas turbine engine
US12196104B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 27, 2023 |
| Grant date | Jan 14, 2025 |
| Priority date | — |
| Expiry date | Oct 27, 2043 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fan blade includes an aerofoil portion including a leading edge extending from a root to a tip and defining a blade span therebetween. A leading edge thickness is defined as a thickness of a cross-section at a given radius at a location along a camber line that is 9% of the total length of the camber line from the leading edge. For cross-sections through the aerofoil portion at radii between 50% and 70% of the blade span from a root radius, the leading edge thickness includes a first maximum value. For cross-sections through the aerofoil portion at radii greater than 70% of the blade span from the root radius, the leading edge thickness includes a second maximum value that is between 105% and 125% of the first maximum value.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.