Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve
A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.
1. A fuel circuit for an aviation turbine engine, the fuel circuit comprising:
a main fuel line for feeding fuel in the main fuel line to a combustion chamber of the aviation turbine engine and including a positive displacement pump;
an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the positive displacement pump and serving to feed fuel in the auxiliary fuel line to hydraulic actuators to control variable-geometry equipment of the aviation turbine engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each hydraulic actuator;
a fuel pressure regulator valve arranged on the main fuel line downstream from the positive displacement pump and upstream from the junction;
a fuel metering member which controls a rate at which the fuel is injected into the combustion chamber, the fuel metering member being arranged on the main fuel line downstream from the junction;
a hydromechanical unit which controls the fuel metering member;
a return fuel loop through which excess fuel in the main fuel line passing through the fuel metering member and the fuel leaving the electrohydraulic servo-valves and passing through the fuel metering member is returned to the main fuel line upstream of the positive displacement pump;
a temperature sensor arranged on the main fuel line downstream from the positive displacement pump: and
an electronic control unit that controls opening and closing of the fuel pressure regulator valve as a function of temperature of the fuel in the circuit downstream from the positive displacement pump measured by the temperature sensor, such that a flow section for the fuel passing through the fuel pressure regulator valve and being fed to the fuel metering member and to the auxiliary fuel line is controlled by the electronic control unit,
wherein the electronic control unit is configured to
generate a constriction of a fuel-passing section through the fuel pressure regulator valve by partially closing the fuel pressure regulator valve when the temperature of the fuel measured by the temperature sensor is less than a predetermined threshold temperature in order to lead to a substantial increase in a fuel pressure in a part of the fuel circuit extending between the positive displacement pump and the fuel pressure regulator valve.
2. A circuit according to claim 1 , wherein the main fuel line does not include head loss equipment between the positive displacement pump and the fuel pressure regulator valve.
3. An aviation turbine engine comprising the fuel circuit according to claim 1 .
4. A method of controlling the fuel pressure regulator valve of the fuel circuit according to claim 1 , the method comprising:
closing the fuel pressure regulator valve partially when the temperature of the fuel measured by the temperature sensor is lower than the predetermined threshold temperature; and
opening the fuel pressure regulator valve when the temperature of the fuel measured by the temperature sensor is higher than the predetermined threshold temperature.
5. A circuit according to claim 1 , wherein the electronic control unit is configured to
open the fuel pressure regulator valve when the temperature of the fuel measured by the temperature sensor is higher than the predetermined threshold temperature.
6. A fuel circuit for an aviation turbine engine, the fuel circuit comprising:
a main fuel line for feeding fuel to a combustion chamber of the aviation turbine engine and including a positive displacement pump;
an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the positive displacement pump and serving to feed the fuel to hydraulic actuators to control variable-geometry equipment of the aviation turbine engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each hydraulic actuator;
a fuel pressure regulator valve arranged on the main fuel line downstream from the positive displacement pump and upstream from the junction;
a fuel metering member which controls a rate at which the fuel is injected into the combustion chamber, the fuel metering member being arranged on the main fuel line downstream from the junction;
a hydromechanical unit which controls the fuel metering member; and
a return fuel loop through which excess fuel in the main fuel line passing through the fuel metering member and the fuel leaving the electrohydraulic servo-valves and passing through the fuel metering member is returned to the main fuel line upstream of the positive displacement pump,
wherein the fuel pressure regulator valve is connected to a thermostatic valve that controls said fuel pressure regulator valve opening and closing, the thermostatic valve being arranged in a fuel extractor pipe connecting the fuel pressure regulator valve to the auxiliary fuel line upstream from the electrohydraulic servo-valves, and the thermostatic valve generating a constriction of a fuel-passing section through the fuel pressure regulator valve by opening so as to partially close the fuel pressure regulator valve when the temperature of the fuel is less than a predetermined threshold temperature in order to lead to a substantial increase in the fuel pressure in a part of the fuel circuit extending between the positive displacement pump and the fuel pressure regulator valve.