Burner for a gas-turbine combustion chamber
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorRalf Sebastian Von Der Bank
Life of this patent
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Abstract
On a burner for a gas-turbine combustion chamber which comprises a lean premix burner with centrally integrated stabilizing burner, a core air annulus (11) accommodating the atomizer nozzle (10) of the stabilizing burner is concentrically surrounded by a main air annulus (4) supplying the weak air-fuel mixture. In the adjacent issuing areas of the main air annulus and the core air annulus, a flame stabilization ring (13), which is heated by the combustion gases and whose cross-sectional surface increases in area toward the combustion chamber (5), is provided to produce an approximately hollow-cylindrical hot-gas recirculation zone (17) originating at the flame stabilization ring which ensures a stable flame formation throughout the range of operating conditions of the gas turbine.
Claims19
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.
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 an inwardly directed core air deflector flank and an outwardly directed main air deflector flank for the formation of a steady, approximately hollow-cylindrical, hot recirculation zone which originates at the flame stabilization ring;
- wherein the flame stabilization ring has a fillet on a side facing the gas-turbine combustion chamber, and the atomizer nozzle has an outlet substantially even with a combustion side of the flame stabilization ring along an axis of the lean premix burner.
Dependencies are inferred from the claim text.