Abstract: A lean premix burner for a gas-turbine engine includes an annular center body (3) with a conically flaring fuel film applicator (11) supplied with fuel via an annular distributor chamber (14) and fuel channels (12) as well as air ducts (7, 9) with swirler elements (8, 10) provided on the outer and inner circumference. A fuel prefilmer lip (15) is attached to the fuel film applicator (11), with a flow area of a portion of the annular air ducts (7, 9) downstream of the swirler elements (8, 10) decreasing to accelerate the air swirled in correspondence with the airflow direction. By this, the fuel is transported positively without interim separation and without the occurrence of compressive oscillation—to a defined flow break-away edge (16), providing for a good mixture, high combustion efficiency and reduced formation of nitrogen oxide.