Patent ID: 8375721

Claim:
A burner for a gas turbine engine, comprising: a swirler providing a swirling mix of air and fuel, and a combustion chamber for a combustion of the swirling mix of air and fuel, the swirler comprising: a plurality of vanes arranged in a circle, a plurality of flow slots, each flow slot defined between two adjacent vanes and has an inlet end and an outlet end, and a fuel-placement device, arranged to deposit a first supply of fuel in the form of a liquid fuel in a high shear region between two adjacent flows in the burner; wherein, in operation, air travels along each flow slot from the inlet end to the outlet end, and a second supply of fuel is supplied to the plurality of flow slots, whereby the swirling mix of air and fuel that is annular in form travels away from the swirler toward the combustion chamber, wherein the high-shear region is a result of a creation of a low-pressure region by the swirler, and wherein the two adjacent flows are an aimular swirling mix of air and fuel which is located radially outside the low-pressure region and a counter-flow located inside the swirling mix of air and fuel created by the low-pressure region, wherein the counter-flow is generally toward the swirler and away from the combustion chamber, wherein the first supply of fuel in the form of liquid fuel from the fuel-placement device is subjected to an atomisation due to a high shear from the high shear region, wherein the fuel-placement device is also a partitioning device, whereby a flow of air along each flow slot is divided into a first air flow and a second air flow, wherein the burner includes a fuel-supply port for supplying the first supply of fuel in the form of liquid fuel to the first air flow or the second air flow, wherein when the burner is operating, the first air flow or the second air flow to which the liquid fuel was supplied causes the liquid fuel supplied to form a film of fuel over a first surface of the fuel-placement device, wherein the first surface is located in the plurality of flow slots, and wherein the fuel-placement device is arranged so that the film substantially leaves the first surface in the high-shear region, wherein the fuel-placement device further includes a second surface, wherein the fuel-placement device extends radially in a region adjacent to the first surface, then curving in an increasingly axial direction towards the second surface, wherein the base member is curved similarly to the fuel-placement device so that a passage is created between the fuel-placement device and the base member, and wherein a cross-sectional area of the passage decreases in a direction of flow of an incoming air.