| 摘要 |
The invention relates to a fuel circuit (10) of an aeronautical turbine engine, comprising a main fuel line (12) intended to supply fuel to a combustion chamber (24) of the turbine engine and including a positive-displacement pump (20), an auxiliary fuel line (30) connected to the main fuel line at a joint (32) located downstream of the pump and intended to supply fuel to hydraulic actuators (34) for controlling variable geometry devices of the turbine engine, the auxiliary fuel line including electro-hydraulic servo valves (36) upstream of each cylinder, and a fuel pressure regulating valve (40) arranged on the main fuel line downstream of the pump. |
