Gas turbine engine having fan shaft stiffness ratio
US10830154B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 3, 2020 |
| Grant date | Nov 10, 2020 |
| Priority date | — |
| Expiry date | Mar 3, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes: an engine core with a turbine, compressor, and core shaft; a fan upstream the engine core; a gearbox that can receive an input from the core shaft and output drive to a fan shaft to drive the fan at a lower rotational speed than the core shaft. A fan-gearbox axial distance is greater than or equal to 0.35 m. The fan shaft has: (i) a radial bending stiffness ratio of a radial bending stiffness of the fan shaft at the fan input to a radial bending stiffness of the fan shaft at the gearbox output that is greater than or equal to 6.0×10−3; and/or (ii) a tilt stiffness ratio of a tilt stiffness of the fan shaft at the fan input to a tilt stiffness of the fan shaft at the gearbox output that is greater than or equal to 2.5×10−2.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.