the invention refers to a method and a device for flame stabilization in a burner system of a stationary combustion engine , preferably a stationary gas turbine , in which a flow of an air / fuel mixture is produced and being swirled to form a vortex flow to which a swirl number is assignable before entering a combustion zone in which the vortex flow of the air / fuel mixture is ignited to form a flame within a reverse flow zone caused by vortex breakdown . the swirl number perturbation driven by thermoacoustic oscillation inside the burner system is controlled by affecting the vortex flow actively before entering the combustion zone on basis of changing a flame transfer function assigned to the burner system with the proviso of minimizing pulsation amplitudes of the flame transfer function .