Gas turbine engine having flight cycle ratio
US10859001B1 · kind B1 · utility
9Cited by
0References
18Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Mar 17, 2020 |
| Grant date | Dec 8, 2020 |
| Priority date | — |
| Expiry date | Mar 17, 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 for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft and output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft; and a gearbox support arranged to at least partially support the gearbox within the engine. A flight cycle ratio of: is less than or equal to 3.20. A method of operating the gas turbine engine is also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.