Patent ID: 7621131

Claim:
A burner for a gas-turbine combustion chamber which comprises a lean premix burner with centrally integrated stabilizing burner; a core air annulus; an atomizer nozzle of the stabilizing burner positioned in the core air annulus; a single main air annulus of the lean premix burner surrounding the atomizer nozzle and core air annulus and supplying a weak air-fuel mixture; a flame stabilization ring positioned directly between adjacent issuing areas of the core air and the single main air annulus, which includes a radially inwardly directed core air deflector flank extending into and partially blocking a core air flow and a radially outwardly directed main air deflector flank extending into and partially blocking a main air flow to create a substantial blockage area between the core air flow and the main air flow downstream of the flame stabilization ring to form a steady, approximately hollow-cylindrical, hot recirculation zone which originates at the flame stabilization ring, the recirculation zone retaining unvaporized fuel from the atomizer nozzle sufficiently long to more fully vaporize same and form a well-burning and ignitable air-mixture in the combustion chamber; wherein the flame stabilization ring has a fillet on a side facing the gas-turbine combustion chamber.