Patent ID: 9494079
Filing Date: 2016-11-15
CPC Classification: F02C,F23D,F23K,F23N,F23R

Claim Text:
1. A fuel injector for a turbine engine or an airplane turboprop or turbojet, the fuel injector comprising: a body including an admission orifice for admitting fuel under pressure; a stop valve mounted in the body downstream from the admission orifice and configured to open at a first determined fuel pressure and to remain open beyond the first determined fuel pressure to feed a primary fuel circuit; a metering valve mounted in the body downstream from the stop valve and configured to open beyond a second determined fuel pressure greater than the first determined fuel pressure, and to remain open beyond the second determined fuel pressure to feed a secondary fuel circuit; a tubular support radially surrounding the metering valve, the metering valve configured to slide within the tubular support; and at least one leakage channel extending in the tubular support from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary fuel circuit.