Patent ID: 6082113
Filing Date: 2000-07-04
Classification: F05B,F23C,F23D

Abstract:
A fuel injector for a combustor in a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air, the injector comprising an injector tip assembly adapted to protrude, in use, through the combustor wall into the chamber, the injector tip including a first air passage comprising an annular array communicating the pressurized air form outside the wall into the combustion chamber, a second air passage made up of an annular array of individual air passages spaced radially from the first air passage and communicating the pressurized air from outside the combustor wall into the combustor, a first fuel gallery extending through the fuel injector tip and defining an annular fuel nozzle between the first air passage and the second air passage, whereby the second air passage is arranged to atomize the fuel emanating from the annular fuel nozzle, and a set of third air passages is arranged in an annular array in the injector tip spaced radially outwardly from the second air passages whereby air from the third passages is arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture; whereby the fuel injector tip is provided with an axial fuel nozzle concentric and central to the first air passage, wherein the axial fuel nozzle is effective to supply a primary fuel for ignition purposes.