CPC F02C 7/36 (2013.01) [F01D 25/20 (2013.01); F02C 3/04 (2013.01); F02C 7/06 (2013.01); F16N 39/002 (2013.01); F01M 2013/0427 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/608 (2013.01); F05D 2260/98 (2013.01); Y02T 50/60 (2013.01)] | 7 Claims |
1. A gas turbine engine comprising:
a fan drive turbine for driving a gear reduction, said gear reduction for driving a fan rotor;
a lubrication system for supplying oil to said gear reduction, the lubrication system including a lubricant pump supplying a mixed air and oil to a deaerator inlet, said deaerator including a separator for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank, with said separator including a member having lubricant flow paths on both of two opposed sides;
wherein said separator includes a scroll spiraling from said inlet to a deaerator exit; and
wherein a dwell time of oil in the tank as removed by said oil pump, on average, is five seconds or less.
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