US 11,725,589 B2
Geared gas turbine engine with oil deaerator
William G. Sheridan, Southington, CT (US)
Assigned to Raytheon Technologies Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Oct. 30, 2020, as Appl. No. 17/85,616.
Application 17/085,616 is a continuation of application No. 15/873,961, filed on Jan. 18, 2018, abandoned.
Application 15/873,961 is a continuation of application No. 14/737,670, filed on Jun. 12, 2015, granted, now 9,976,490, issued on May 22, 2018.
Claims priority of provisional application 62/019,452, filed on Jul. 1, 2014.
Prior Publication US 2021/0231059 A1, Jul. 29, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F02C 3/04 (2006.01); F02C 7/06 (2006.01); F16N 39/00 (2006.01); F01D 25/20 (2006.01); F01M 13/04 (2006.01)
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
OG exemplary drawing
 
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.