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 |
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.
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