| 摘要 |
<p>The invention relates to a fuel injector 101 for a turbine engine such as an airplane turboprop or turbojet, the injector comprising a body 102 including an inlet 104 for admitting fuel under pressure, a stop valve 107 mounted in the body 102 downstream from the inlet 104 and arranged to open at a first determined fuel pressure and to remain open beyond that first pressure in order to feed a primary fuel circuit 136, and a metering valve 115 mounted in the body 102 downstream from the stop valve 107 and arranged to open above a second fuel pressure, greater than the first pressure, and to remain open above the second pressure in order to feed a secondary fuel circuit 117. The stop valve 107 and the metering valve 115 being formed by the body and a movable assembly 133, the valves being formed on opposing ends of the moveable assembly.</p> |
