Lubrication system and method, and vortex flow separator for...

Details Lubrication system and method, and vortex flow separator for... Lubrication system and method, and vortex flow separator for...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 25/20 (2006.01) B64D 47/00 (2006.01)

Patent

CA 2650088

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.

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