US 11,885,252 B2
Planetary gear system arrangement with auxiliary oil system
William G. Sheridan, Southington, CT (US); Michael E. McCune, Colchester, CT (US); and Lawrence E. Portlock, Bethany, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Jun. 12, 2018, as Appl. No. 16/006,327.
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 16/006,327 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.
Application 13/428,491 is a continuation in part of application No. 16/006,327.
Application 16/006,327 is a continuation of application No. 13/428,491.
Prior Publication US 2018/0347428 A1, Dec. 6, 2018
Prior Publication US 2021/0180492 A9, Jun. 17, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 25/16 (2006.01); F01N 3/20 (2006.01); F01D 25/18 (2006.01); F02C 3/10 (2006.01); F02K 3/06 (2006.01); F02C 7/36 (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)] 24 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan section,
a first compressor stage and a second compressor stage;
a first turbine stage and a second turbine stage, wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as a low spool;
a planetary gear train having at least one planetary gear, a sun gear, a ring gear fixed from rotation relative to an engine static structure, a ring gear support, a carrier supporting said at least one planetary gear, said carrier driving said fan section, wherein said ring gear has a recess configured to balance force transmitted through the ring gear and wherein the ring gear has at least one ring gear opening therethrough and said ring gear support including a ring gear support opening through the ring gear and the ring gear support that is perpendicular to the at least one ring gear opening;
a lubricating system for said planetary gear train, wherein said at least one ring gear opening and said ring gear support opening is in fluid communication with said lubricating system; and
an aft gutter aft of said ring gear and a forward gutter forward of said ring gear, the aft and forward gutters configured to collect lubricant from the lubricating system, and wherein the ring gear support opening is defined between a forward end and an aft end, and wherein the aft end is configured to receive the lubricant from the aft gutter and the forward end is configured to pass the lubricant to the forward gutter;
wherein said low spool drives said fan section via said planetary gear train.