US 12,065,976 B2
Oil recovery device for a turbomachine
Antoine Jacques Marie Pennacino, Moissy-Cramayel (FR); Amélie Argie Antoinette Chassagne, Moissy-Cramayel (FR); Patrice Jocelyn Francis Gedin, Moissy-Cramayel (FR); Juan-Luis Marcos Izquierdo, Moissy-Cramayel (FR); and Jordane Emile André Peltier, 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 Jul. 7, 2023, as Appl. No. 18/348,870.
Claims priority of application No. 2206971 (FR), filed on Jul. 7, 2022.
Prior Publication US 2024/0011443 A1, Jan. 11, 2024
Int. Cl. F16H 57/04 (2010.01); F02C 7/06 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 7/06 (2013.01); F16H 57/0428 (2013.01); F16H 57/0456 (2013.01); F16H 57/0479 (2013.01); F16H 57/0486 (2013.01); F05D 2220/323 (2013.01); F05D 2260/40311 (2013.01); F05D 2260/98 (2013.01)] 16 Claims
OG exemplary drawing
 
1. An oil recovery device for a reducer of a turbomachine of an aircraft, the device comprising a gutter extending around an axis and configured to be arranged facing oil ejection means formed in a ring gear of the reducer of the turbomachine, the gutter comprising at least one oil reception chamber which extends around the axis and which is open towards the axis so as to receive the oil coming from the oil ejection means, the chamber being delimited by a first wall and a second wall arranged facing each other, the first wall comprising an axial oil evacuation orifice and the second wall having a radial dimension relative to the axis which increases increasingly along the axis towards the axial orifice, so as to allow the oil ejected by the reducer to be conveyed to the axial orifice,
wherein radially external ends of the first and second walls are connected directly to each other, the radially external ends of the first and second walls being in contact with each other.