Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine
US11572833B2 · kind B2 · utility
0Cited by
3References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 2, 2019 |
| Grant date | Feb 7, 2023 |
| Priority date | — |
| Expiry date | Nov 7, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF16N2210/02
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.