Aircraft turbine engine with reduction gear
US11085329B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 24, 2019 |
| Grant date | Aug 10, 2021 |
| Priority date | — |
| Expiry date | Nov 7, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/98
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine engine includes a fan. The fan includes a first shaft driven in rotation via a reduction gear, the first shaft being guided in rotation with respect to a support of a fixed structure via an upstream bearing and a downstream bearing, the downstream bearing guiding in rotation the first shaft with respect to a downstream branch of the support, the first shaft and the support together defining an enclosure. The reduction gear includes a ring gear fixed to the structure via a shell. The turbine engine also includes a lubricator composed of at least one pipe for conveying a liquid lubricant, wherein the pipe is located in the enclosure, the pipe passing through an orifice made in the shell and an opening made in the downstream branch.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.