Patent ID: 9033263
Filing Date: 2015-05-19
Classification: F23D,F23R

Abstract:
1. A fuel injection nozzle for a gas turbine combustion chamber, comprising: an inner air swirler for providing an inner flow of air through an inner swirl channel; an outer air swirler for providing an outer flow of air through an outer swirl channel, the outer swirl channel being a radially outermost air channel of the nozzle; an annular flow divider directly separating the inner and outer flows of air, the flow divider including a downstream-most trailing edge and a radially outer surface and a radially inner surface upstream of and adjacent to the trailing edge, the radially outer surface having a concave shape facing away from a center axis of the fuel injection nozzle in an axial cross-section, the radially inner surface having a convex shape facing toward the center axis in the axial cross-section; the radially outer surface and the radially inner surface converging together in a downstream direction to form a tapering shape of the flow divider toward the trailing edge in the axial cross-section; the converging radially outer surface and radially inner surface providing for converging of the inner and outer flows of air downstream of the trailing edge of the flow divider; the flow divider having a plurality of fuel openings positioned around a circumference of the flow divider and having respective center axes, wherein the center axes of the fuel openings are set in the downstream direction and wherein the fuel openings are arranged immediately on and through the trailing edge between the converging inner and outer flows of air to inject fuel in the downstream direction of the nozzle directly into a shear layer formed between the inner and outer flows of air, the injection of the fuel into the shear layer creating a mixture between the fuel and air; the fuel openings positioned on the trailing edge to inject the fuel into the position where the inner and outer flows of air converge downstream of the trailing edge; at least a portion of the outer swirl channel being directly open to the combustion chamber outside of a cylinder established by an outer circumference of the annular flow divider at the downstream-most edge and being parallel to an axis of the nozzle such that at least a portion of the outer flow of air has a direct and unobstructed path to the combustion chamber.