Gas turbine lean combustor with fuel nozzle with controlled fuel

The invention relates to a gas turbine lean combustor having a combustion chamber (2) and with a fuel nozzle (1) having a pilot fuel injection (17) and a main fuel injection (18), characterized in that the main fuel injection (18) central recesses (23) for controlled inhomogeneous fuel injection comprises the number of which is at the periphery of between 8 and 40 and which have a pitch angle δ2 in the circumferential direction of 10 ° ≦ δ2 ≦ 60 ° and an axial angle δ1 relative to the burner axis (4) between -10 ° ≦ δ1 ≦ 90 °.