Fuel feed circuit for an aircraft engine
View Patent ↗A head loss element is interposed between the outlet from the pump delivering high pressure fuel and the pipe feeding combustion chamber injectors. A servo-valve for feeding a hydraulic actuator of a variable-geometry component of the engine has an HP admission inlet connected to the outlet from the pump upstream from the head loss element and an LP outlet connected to the feed pipe downstream from the head loss element. Thus, the flow rate taken upstream from the head loss element for driving the actuator is compensated by the flow rate reinjected downstream from the head loss element, thereby avoiding any movement of the variable-geometry component giving rise to a disturbance in the flow rate delivered to the injectors.
1. 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.
2. A circuit according to claim 1 , wherein the head loss element is a mechanism enabling head loss to be regulated.
3. A circuit according to claim 1 , wherein the head loss element comprises a diaphragm.
4. A circuit according to claim 1 , wherein the head loss element is dimensioned to generate a head loss lying in the range 10 bars to 40 bars.
5. An aircraft engine including a fuel feed circuit according to claim 1 .
6. A circuit according to claim 2 , wherein the head loss element includes a cylinder having a piston mounted therein, the inlet connected to the pump outlet for receiving fuel at said pressure is provided at a first end wall of the cylinder, and the outlet delivering fuel at the lower pressure is connected to a slot disposed in a side wall of the cylinder.
7. A circuit according to claim 6 , wherein the piston includes a front face which faces the first end wall and a rear face which abuts a spring disposed between a second end wall of the cylinder and the piston.
8. A circuit according to claim 7 , wherein axial movement of the piston within the cylinder is based on a pressure difference between the inlet and the outlet of the head loss element.