Patent ID: 6189814
Filing Date: 2001-02-20
Classification: F23R

Abstract:
A gas turbine engine fuel injector comprising a member having a first end and a second end, the member reducing in cross-sectional area in the longitudinal direction from the first end to the second end, the member reducing in dimension in a first direction perpendicular to the longitudinal direction from the first end to the second end, the member having a passage extending longitudinally therethrough for the supply of fuel from the first end towards the second end, the member having a plurality of discharge apertures at a predetermined distance from the second end, the discharge apertures being spaced apart in a second direction which is substantially perpendicular to both the first direction and the longitudinal direction, the apertures being arranged to direct fuel substantially in the first direction, at least a portion of the member having a substantially constant dimension in the second direction, a portion of the fuel injector reducing in dimension in the second direction between the first end of the member and the portion of the member having a constant dimension in the second direction.