Front enclosure which is sealed during the modular dismantling of a turbojet with reduction gear
US10422341B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 13, 2014 |
| Grant date | Sep 24, 2019 |
| Priority date | — |
| Expiry date | Mar 16, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/40311
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention relates to a turbofan engine comprising a fan driven, via a fan shaft supported by at least two first bearings, by a turbine shaft supported by at least one second bearing comprising a stationary ring and a movable ring, said turbine shaft driving said fan shaft through a device for reducing the speed of rotation, said device for reducing the speed of rotation and said first and second bearings being housed in a lubrication enclosure in which the shell comprises stationary portions and movable portions connected to one another by sealing means, said reducing device comprising an inducer shaped so as to receive the torque transmitted by said turbine shaft via driving means connected to said movable ring, wherein the lubrication enclosure forms a coaxial ring with the turbine shaft and said driving means comprise a girth gear which is part of the movable sealing walls of the shell of the lubrication enclosure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.