Patent ID: 6289677
Filing Date: 2001-09-18
Classification: F05B,F23C,F23D

Abstract:
In 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 along a tip axis through the combustor wall into the chamber, the injector tip including at least an air passage made up of an annular array of individual air passages spaced radially from the tip axis and communicating the pressurized air from outside the combustor wall into the combustor, a fuel gallery extending through the fuel injector tip and defining an annular fuel nozzle radially inwardly from the air passage, whereby each air passage in the annular array is formed to provide a swirl to the mixture and the air passage is arranged to atomize the fuel emanating from the annular fuel nozzle, as a result of the passages in the annular array each being in a plane offset from the plane through the tip axis of the injector tip, a distance D and the angle of the inwardly directed component of the axis of the passage is .theta. and further a second set of air passages is arranged in an annular array in the injector tip spaced radially outwardly from said air passages with the distance of a plane, passing through each passage in the second set of air passages, from the plane passing through the tip axis is D.sub.1 and the angle of the inwardly directed component of each passage of the second set to the tip axis is .phi., whereby air from the second set of air passages is arranged to shape the mixture of atomized fuel and air and to add supplemental air to the mixture.