초록 ▼

A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion

A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.

대표청구항 ▼

1. 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

1. 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.