US 12,110,845 B2
Aeronautic propulsion system with improved propulsion efficiency
Maeva Daphné Gros-Borot, Moissy-Cramayel (FR); Gilles Alain Marie Charier, Moissy-Cramayel (FR); Matthieu Bruno François Foglia, Moissy-Cramayel (FR); Caroline Marie Frantz, Moissy-Cramayel (FR); and Adrien Louis Simon, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN TRANSMISSION SYSTEMS, Colombes (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR); and SAFRAN TRANSMISSION SYSTEMS, Colombes (FR)
Filed on Apr. 11, 2023, as Appl. No. 18/133,280.
Application 18/133,280 is a continuation of application No. 17/783,721, previously published as PCT/FR2020/052391, filed on Dec. 11, 2020.
Claims priority of application No. 1914192 (FR), filed on Dec. 11, 2019; and application No. 1914193 (FR), filed on Dec. 11, 2019.
Prior Publication US 2023/0265813 A1, Aug. 24, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02K 3/06 (2006.01); F02C 7/36 (2006.01)
CPC F02K 3/06 (2013.01) [F02C 7/36 (2013.01); F05D 2240/52 (2013.01); F05D 2260/40311 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A propulsion system comprising:
a drive shaft movable in rotation about an axis of rotation;
a low-pressure compressor driven in rotation by the drive shaft, said low-pressure compressor having a predetermined mean radius;
a fan shaft;
a fan driven in rotation by the fan shaft;
a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio; and
an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet channel having a mean radius;
wherein a first ratio between a ratio of the mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.