BigPatents India

The present invention relates to a lance (3) for a hybrid burner (2) of a combustor (1) of a gas turbine, comprising an inner passage (10) for a liquid fuel, an outer passage (11), coaxially enclosing the inner passage (10), for a gaseous fuel, a plurality of radially arranged outer nozzles (12) branching off radially from the outer passage (11), a plurality of inner nozzles (14) which branch off radially from the inner passage (10) and which each extend coaxially inside one of the outer nozzles (12) , a distributor section (18) which is arranged upstream of the outer nozzles (12) in the outer passage (11) and has a plurality of radially arranged, coaxially extending through-openings (19) for the gaseous fuel. In order to reduce the flow resistance in the gas path of the lance (3) , the through-openings (19) each have an opening width which is larger in the circumferential direction than in the radial direction. (Fig. 2)