US 12,264,628 B2
Fuel supply system with air expulsion drain for an aircraft engine
Philippe Jean René Marie Benezech, Moissy-Cramayel (FR); Alexis Thomas Valentin Longin, Moissy-Cramayel (FR); Pierre Anthony Sicaire, Moissy-Cramayel (FR); and Gabriel Darrieumerlou, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 18/287,745
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Apr. 13, 2022, PCT No. PCT/FR2022/050698
§ 371(c)(1), (2) Date Oct. 20, 2023,
PCT Pub. No. WO2022/223907, PCT Pub. Date Oct. 27, 2022.
Claims priority of application No. 2104169 (FR), filed on Apr. 21, 2021.
Prior Publication US 2024/0183314 A1, Jun. 6, 2024
Int. Cl. F02C 7/236 (2006.01); F02C 7/232 (2006.01); F02C 7/32 (2006.01)
CPC F02C 7/236 (2013.01) [F02C 7/232 (2013.01); F02C 7/32 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A liquid fuel supply system for an aircraft engine, the liquid fuel supply system comprising:
a fuel tank;
a suction duct connected to the fuel tank and located higher than the fuel tank;
an electric pump;
a first supply pump configured to be mechanically driven by an accessory gear box and to be connected at an outlet of the first supply pump to a fuel supply circuit of the aircraft engine;
a second supply pump extending upstream of the electric pump with reference to a direction of a stream of fuel through the liquid fuel supply system, and
an air expulsion drain,
wherein the electric pump is in communication with the suction duct independently of the first supply pump,
the electric pump is in communication with the air expulsion drain, and
the first supply pump is in communication with the suction duct independently of the electric pump,
prior to a starting of the aircraft engine, the system electric pump pumps fuel through the second supply pump when the aircraft engine and the first supply pump are stopped.