CPC F01D 25/18 (2013.01) [B01D 19/0068 (2013.01); B01D 19/0073 (2013.01); F01D 25/20 (2013.01); F02C 7/06 (2013.01); F05D 2260/609 (2013.01); Y02T 50/60 (2013.01)] | 29 Claims |
11. A method of operating a gas turbine engine comprising:
a propulsor drive turbine driving a gear reduction, said gear reduction driving a propulsor rotor; and
a lubrication system supplying oil to said gear reduction, with an oil tank, the lubrication system including a lubricant pump; and
supplying an air/oil mixture to an inlet of a deaerator, said deaerator separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into the oil tank,
air within the oil tank moving outwardly through an air exit to the deaerator, and
an inlet velocity of the air/oil mixture to the deaerator is less than or equal to 14 feet/second and an exit velocity from the deaerator of the separated air is less than or equal to 14 feet/second; and
a gear ratio defined by said gear reduction being greater than 2.3.
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