Dual fuel mixing in a multishear fuel injector with a plurality of concentric ducts
AssigneeUnited Technologies Corporation
InventorJohn William Green
Life of this patent
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Abstract
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.
Claims5
A fuel nozzle in combination with a first annular air passage and a second annular air passage concentrically mounted relative to said first annular air passage for mixing the fuel discharging from the fuel nozzle with the air in the first annular and second annular air passages for admission in a burner for a gas turbine engine, said fuel nozzle having a primary fuel passage and port and a secondary fuel passage and port, said fuel nozzle disposed concentric to and within said first annular air passage, said first annular air passages having a ring member and said ring member having a plurality of circumferentially spaced air injection holes for admitting air into the burner, a central duct coaxially located relative to and within said ring member, said primary fuel port discharging fuel into the air discharging from said circumferentially spaced air injection holes, and said secondary fuel port discharging fuel into said central duct prior to being admitted into said burner.
Dependencies are inferred from the claim text.