Patent ID: 8201664

Claim:
An aircraft engine lubrication system comprising a vortex separator having a generally cylindrical inner chamber with an inlet end and an outlet end, and a vent port; a first pump line having a first pump, an inlet connected to a separated lubricant area at the outlet end of the separator for receiving separated lubricant therefrom, and an outlet connectable to the engine; a scavenge line having an inlet connectable to the engine, and an outlet connected to the inlet end of the separator for directing a gas/lubricant mixture into the separator; a lubricant tank connected in fluid flow communication with the separator by a connection line; and a second pump line having a second pump, an inlet connected to the lubricant tank and an outlet connected to the separator, the second pump providing a dedicated oil supply to the separator by pumping make-up oil from the lubricant tank to the separator independently of the gas/lubricant mixture supplied to the vortex separator, the dedicated oil supply pumped by the second pump maintaining a vortex of oil in the separator irrespectively of the gas/lubricant mixture fed into the separator by the scavenge line, wherein, in use, a vortex is maintained in the separator, separated lubricant is pumped from the separator to the engine via the first pump line, lubricant is returned to the separator, mixed with gas, by the scavenge line, separated gas is evacuated from the vent port, lubricant is supplied to the separator from the lubricant tank by the second pump line, and excess oil in the separator is returned back to the lubricant tank via the connection line.