US 12,168,959 B2
Gas turbine fan drive gear system
Michael E. McCune, Colchester, CT (US); and William G. Sheridan, Southington, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Sep. 5, 2023, as Appl. No. 18/242,104.
Application 18/242,104 is a division of application No. 17/729,129, filed on Apr. 26, 2022, granted, now 11,773,787.
Application 14/222,919 is a division of application No. 13/975,635, filed on Aug. 26, 2013, granted, now 8,763,251, issued on Jul. 1, 2014.
Application 13/975,635 is a division of application No. 13/629,834, filed on Sep. 28, 2012, granted, now 8,667,688, issued on Mar. 11, 2014.
Application 17/729,129 is a continuation of application No. 16/936,791, filed on Jul. 23, 2020, granted, now 11,339,726, issued on May 24, 2022.
Application 16/936,791 is a continuation of application No. 15/869,276, filed on Jan. 12, 2018, granted, now 10,753,285, issued on Aug. 25, 2020.
Application 15/869,276 is a continuation of application No. 14/222,919, filed on Mar. 24, 2014, granted, now 9,874,150, issued on Jan. 23, 2018.
Prior Publication US 2023/0407796 A1, Dec. 21, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F02C 3/107 (2006.01); F02C 7/32 (2006.01); F02K 3/06 (2006.01); F16H 1/28 (2006.01); F16H 57/023 (2012.01); F16H 57/04 (2010.01); F16H 57/08 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 3/107 (2013.01); F02C 7/32 (2013.01); F02K 3/06 (2013.01); F16H 1/28 (2013.01); F16H 57/023 (2013.01); F16H 57/082 (2013.01); F05D 2230/60 (2013.01); F05D 2260/40311 (2013.01); F16H 57/0423 (2013.01); F16H 57/0456 (2013.01); F16H 57/0479 (2013.01); F16H 57/0486 (2013.01); Y02T 50/60 (2013.01); Y10T 29/49464 (2015.01)] 20 Claims
OG exemplary drawing
 
1. A gear reduction for a gas turbine engine comprising:
a plurality of intermediate gears;
a single structure establishing a carrier centered on an axis and having a pair of axially spaced apart side walls, axially extending circumferentially spaced connecting structure for connecting the pair of side walls, a central opening in at least one of the side walls, and circumferentially spaced smaller openings spaced radially outwardly of the central opening, with internal surfaces of the circumferentially spaced connecting structure defining intermediate gear pockets that extend away from the central opening to the circumferentially spaced openings;
wherein the intermediate gears are receivable through the central opening of the single structure and are secured in the intermediate gear pockets at a position spaced radially inwardly of a radially outermost area in the intermediate gear pockets;
a ring gear including a first ring gear component and a second ring gear component, the first and second ring gear components placed on an outer periphery of the intermediate gears such that ring gear teeth of the first and second ring gear components engage with teeth of the intermediate gears; and
a connection that secures the gear reduction to a propulsor shaft.