FUEL INJECTOR FOR A TURBINE ENGINE

摘要

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 admission means (104) for admitting fuel under pressure, a stop valve (107) mounted in the body (102) downstream from the admission means (104) and designed 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 designed to open above a second determined 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) form a common movable assembly (133).

主权项

1. A fuel injector for a turbine engine, the injector comprising a body including admission device for admitting fuel under pressure, a stop valve mounted in the body downstream from the admission device and designed to open at a first determined fuel pressure and to remain open beyond that first pressure in order to feed a primary fuel circuit, and a metering valve mounted in the body downstream from the stop valve and designed to open above a second determined fuel pressure, greater than the first pressure, and to remain open above the second pressure in order to feed a secondary fuel circuit, wherein the stop valve and the metering valve form a common movable assembly, the stop valve being formed by a first end of the movable assembly, the metering valve being formed by a second end of the movable assembly.