Patent ID: 7950232

Claim:
A fuel circuit for an aircraft engine, the circuit comprising: a pump delivering fuel under high pressure to a pump outlet; a head loss element having an inlet connected to the pump outlet, for receiving fuel at said high pressure and an outlet delivering fuel at a pressure lower than said high pressure to an injectors feed pipe; a servo-valve having a first high pressure inlet connected to the outlet upstream from the head loss element and a second low pressure outlet connected to the injectors feed pipe downstream from the head loss element; and a hydraulic actuator of a variable-geometry component of the engine connected to utilization orifices of the servo-valve, the servo-valve being controlled by an electronic regulator module of the engine when displacement of the variable-geometry component is desired to feed high pressure fuel taken from the pump outlet to a first chamber of the hydraulic actuator and receiving from a second chamber of the hydraulic actuator low pressure fuel which is fed to the injectors feed pipe.