Turbojet engine with offset fans with a differential system
US10247108B2 · kind B2 · utility
2Cited by
6References
13Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 3, 2016 |
| Grant date | Apr 2, 2019 |
| Priority date | — |
| Expiry date | May 24, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/40311
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A propulsion unit of an aircraft including a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan. The power transmission mechanism includes a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.