US 11,905,889 B2
Aircraft turbomachine with reducer
Marion Jeanne Pierrette Verdier, Moissy-Cramayel (FR); Yanis Benslama, Moissy-Cramayel (FR); Michel Gilbert Roland Brault, Moissy-Cramayel (FR); Romain Guillaume Cuvillier, Moissy-Cramayel (FR); and Serge René Morreale, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/278,617
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Sep. 19, 2019, PCT No. PCT/FR2019/052193
§ 371(c)(1), (2) Date Mar. 22, 2021,
PCT Pub. No. WO2020/065182, PCT Pub. Date Apr. 2, 2020.
Claims priority of application No. 1858673 (FR), filed on Sep. 24, 2018.
Prior Publication US 2022/0042460 A1, Feb. 10, 2022
Int. Cl. F02C 7/36 (2006.01); F01D 15/12 (2006.01); F02C 3/107 (2006.01); F02C 3/113 (2006.01); F02C 7/06 (2006.01); F02C 3/10 (2006.01); F01D 5/02 (2006.01); F01D 25/16 (2006.01)
CPC F02C 7/36 (2013.01) [F01D 15/12 (2013.01); F01D 5/026 (2013.01); F01D 25/16 (2013.01); F02C 3/10 (2013.01); F02C 3/107 (2013.01); F02C 3/113 (2013.01); F02C 7/06 (2013.01); F05D 2220/30 (2013.01); F05D 2240/50 (2013.01); F05D 2240/60 (2013.01); F05D 2250/36 (2013.01); F05D 2270/023 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A turbomachine with an axis of rotation, comprising: a single ducted fan comprising a first shaft carrying blades and driven in rotation by a second shaft via a speed reducer, said second shaft being driven in rotation by a third shaft of a turbine, said first, second and third shafts sharing the axis of rotation, said first shaft being guided in rotation with respect to a fixed structure of the turbomachine via a first bearing and a second bearing located upstream of said speed reducer, wherein the second shaft is guided in rotation with respect to the first shaft via a third rolling bearing located upstream of said speed reducer, said third rolling bearing comprising an outer ring housed in said first shaft, an inner ring attached to said second shaft, and rolling elements disposed between said inner and outer rings.