Geared gas turbine engine
US10823084B1 · kind B1 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 3, 2020 |
| Grant date | Nov 3, 2020 |
| Priority date | — |
| Expiry date | Mar 3, 2040 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
An engine for an aircraft includes 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; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft so as to drive the fan at a lower rotational speed than the core shaft, the gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support arranged to mount the gearbox within the engine. The fan shaft, core shaft, gearbox and the gearbox support together may form a transmission.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.