Patent ID: 6389815
Filing Date: 2002-05-21
Classification: F23C,F23R

Abstract:
A fuel nozzle assembly for a gas turbine engine, said fuel nozzle assembly comprising:a primary fuel injector having a central axis, wherein the primary fuel injector is disposed for injecting a primary fuel spray into a primary air stream; a secondary fuel injector positioned radially outwardly of the primary fuel injector for injecting a secondary fuel spray into a secondary air stream that is spaced radially outwardly of and that surrounds the primary air stream; and a primary air jet positioned between the primary fuel injector and the secondary fuel injector, wherein the primary air jet is inclined at a first angle of inclination relative to the primary fuel injector central axis to direct a portion of an incoming air stream between the primary air stream and the secondary air stream in an angular, downstream direction relative to the primary air stream, and a secondary air jet that issues in a direction toward the secondary air stream at a second angle of inclination relative to the primary fuel injector central axis, wherein the second angle of inclination is greater than the first angle of inclination.