US 12,305,522 B2
Turbomachine lubrication system comprising a bypass for preferentially supplying lubricant to a low-speed reduction gear
Jérémy Edmond Fert, Moissy-Cramayel (FR); and Jacques Auriol, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/249,148
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 12, 2021, PCT No. PCT/FR2021/051768
§ 371(c)(1), (2) Date Apr. 14, 2023,
PCT Pub. No. WO2022/079382, PCT Pub. Date Apr. 21, 2022.
Claims priority of application No. 2010565 (FR), filed on Oct. 15, 2020.
Prior Publication US 2023/0407764 A1, Dec. 21, 2023
Int. Cl. F01D 25/20 (2006.01); F01M 1/16 (2006.01)
CPC F01D 25/20 (2013.01) [F01M 1/16 (2013.01); F05D 2220/323 (2013.01); F05D 2260/40 (2013.01); F05D 2260/98 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A lubrication system for a turbomachine including a reduction gear for driving a module of the turbomachine, comprising:
a main branch comprising at least one heat exchanger;
a non-return device that is configured to limit/prevent the circulation of lubricant from the reduction gear to the main branch, the non-return device comprising a non-return valve; and a bypass branch that is arranged in parallel to the main branch, the bypass branch comprising a hydraulic resistance that is lower than the hydraulic resistance of the main branch,
the reduction gear that is located downstream of the main branch and of the bypass branch,
the lubrication system comprising at least one bypass device that is configured to supply the bypass branch with lubricant when a pressure value of the lubricant is below a threshold value.