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A fuel/mixer injection system for a combustor of a gas turbine engine comprising two major assemblies including a burner-mounted swirler with two outer air passages surrounding a central passage and a piloted air fuel nozzle containing a main fuel injection orifice and a pilot fuel injection orifice

A fuel/mixer injection system for a combustor of a gas turbine engine comprising two major assemblies including a burner-mounted swirler with two outer air passages surrounding a central passage and a piloted air fuel nozzle containing a main fuel injection orifice and a pilot fuel injection orifice the main fuel mixes with swirling air in the central passage and the pilot fuel mixes with the swirling air in the outer air passage. In another embodiment, the piloted fuel nozzle contains an airblast-atomized main fuel injector annulus and a concentric ring with a plurality of circumferentially spaced holes feeds air to the main fuel injector annulus.

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[ It is claimed:] [1.] In combination, a fuel nozzle, a source of fuel and a source of air, and a first swirler and a second swirler for mixing the fuel discharging from the fuel nozzle with the air in the swirlers for admission in a burner for a gas turbine engine, said fuel nozzle having a primary

[ It is claimed:] [1.] In combination, a fuel nozzle, a source of fuel and a source of air, and a first swirler and a second swirler for mixing the fuel discharging from the fuel nozzle with the air in the swirlers for admission in a burner for a gas turbine engine, said fuel nozzle having a primary fuel passage and a primary discharge port disposed at the end of said primary fuel passage and a secondary fuel passage and a secondary discharge port disposed at the end of said secondary fuel passage, said fuel nozzle disposed centrally of said first swirler, said first swirler having a generally conically shaped wall defining a first central duct admitting air from said source to flow therein and said second swirler having a second generally conically shaped wall defining a second central duct admitting air from said source to flow therein, said second central duct coaxially located relative to said first central duct and surrounded by said first central duct, said primary fuel port discharging fuel radially outwardly into said first central duct and adjacent to said second conically shaped wall to admit fuel from said fuel source to mix with the air therein and said secondary fuel port discharging fuel radially inwardly into said second central duct and adjacent to said second conically shaped wall to admit fuel from said fuel source to mix with the air therein, wherein the primary fuel being supplied during low power conditions of said gas turbine engine and said secondary fuel being supplied at higher power conditions of said gas turbine engine.