Reliable gearbox for gas turbine engine
US11378015B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Apr 29, 2021 |
| Grant date | Jul 5, 2022 |
| Priority date | — |
| Expiry date | Apr 29, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/40311
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
An engine for an aircraft has an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from a gearbox input shaft portion of the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, a plurality of planet gears, a ring gear, and a planet carrier. The planet carrier and the gearbox support each have a torsional stiffness, and a carrier to gearbox support torsional stiffness ratio is greater than or equal to 2.3.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.