US 11,815,001 B2
Planetary gear system arrangement with auxiliary oil system
Michael E. McCune, Colchester, CT (US); William G. Sheridan, Southington, CT (US); and Lawrence E. Portlock, Bethany, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RaytheonTechnologies Corporation, Farmington, CT (US)
Filed on Apr. 28, 2020, as Appl. No. 16/860,172.
Application 15/621,406 is a division of application No. 14/474,869, filed on Sep. 2, 2014, granted, now 9,677,420, issued on Jun. 13, 2017.
Application 14/474,869 is a division of application No. 14/266,888, filed on May 1, 2014, granted, now 8,931,285, issued on Jan. 13, 2015.
Application 16/860,172 is a continuation of application No. 15/621,406, filed on Jun. 13, 2017, granted, now 10,648,383.
Application 14/266,888 is a continuation of application No. 13/428,491, filed on Mar. 23, 2012, granted, now 9,995,174, issued on Jun. 12, 2018.
Application 13/428,491 is a continuation in part of application No. 12/902,525, filed on Oct. 12, 2010, granted, now 8,813,469, issued on Aug. 26, 2014.
Prior Publication US 2020/0386138 A1, Dec. 10, 2020
Int. Cl. F02C 3/10 (2006.01); F01N 3/20 (2006.01); F01D 25/18 (2006.01); F02K 3/06 (2006.01); F02C 7/36 (2006.01); F01D 25/16 (2006.01); F02C 7/06 (2006.01); F02C 7/10 (2006.01); F01N 11/00 (2006.01); F16N 7/34 (2006.01)
CPC F01N 3/208 (2013.01) [F01D 25/16 (2013.01); F01D 25/18 (2013.01); F01N 3/2066 (2013.01); F01N 11/00 (2013.01); F02C 3/10 (2013.01); F02C 7/06 (2013.01); F02C 7/10 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F01N 2610/01 (2013.01); F01N 2610/02 (2013.01); F01N 2610/142 (2013.01); F01N 2610/1406 (2013.01); F01N 2610/148 (2013.01); F01N 2900/1814 (2013.01); F05D 2260/40311 (2013.01); F16N 7/34 (2013.01); Y02T 10/12 (2013.01); Y02T 50/60 (2013.01); Y10T 29/4932 (2015.01); Y10T 137/0324 (2015.04); Y10T 137/7297 (2015.04)] 19 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan shaft diving a fan having fan blades;
a gear system including a sun gear surrounded by a plurality of intermediate gears, a carrier at least partially supporting said plurality of intermediate gears, and a ring gear surrounding said plurality of intermediate gears, wherein said sun gear is driven by a turbine;
at least one fan shaft support bearing located forward of the gear system;
a coupling fixing said ring gear from rotation relative to an engine static structure; and
a lubrication system for lubricating components across a rotation gap, the lubrication system including a lubricant input, a stationary first bearing receiving lubricant from said lubricant input and having a first race in which lubricant flows, and a second bearing for rotating within said first bearing, said second bearing having a first opening in registration with said first race such that lubricant may flow from said first race through said first opening into a first conduit, wherein the stationary first bearing is located radially outward from a central axis of the second bearing with respect to an engine axis.