Abstract: The invention relates to a burner for combustors of gas turbines, the burner having an atomizer nozzle for atomisation of fuel in the combustion air and having a primary and secondary flow channel. In the burners, mostly used in aircraft engines, an extensively homogenous distribution of the air-fuel mixture is to be achieved in the combustor to reduce emissions. The flow channels opening into the combustor are separated from a first component arranged concentrically in relation to the burner axis and having a sleeve-shaped atomizer lip extending cylindrically or conically, and the external secondary flow channel is bounded externally and radially by a second annular component arranged concentrically and having an internal wall extending to converge and diverge. The second component forms an area with the most narrow flow cross-section, and the first component is arranged radially inwards and ends with the atomizer lip at the axial height of the cross-section or upstream thereof.