Lubrication system and method, and vortex flow separator for use therewith
US8201664B2 · kind B2 · utility
16Cited by
19References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 23, 2008 |
| Grant date | Jun 19, 2012 |
| Priority date | — |
| Expiry date | Nov 17, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/604
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aircraft engine lubrication system has a vortex separator, a first pump line having a first pump, an inlet connected to a separated lubricant area at the outlet end of the separator, and an outlet connectable to the engine. A scavenge line is provided for returning lubricant from the engine to an inlet end of the separator. A lubricant tank is connected in fluid flow communication with the separator by a connection line. A second pump line having a second pump has an inlet connected to the lubricant tank and an outlet connected to the separator for pumping lubricant from the tank to the inlet end of the separator.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.