Patent ID: 7963764

Claim:
A lance for a hybrid burner of a combustor of a gas turbine, the lance comprising: an inner passage for a liquid fuel defining a lance axis, wherein the liquid fuel is disposed in the inner passage; an outer passage for a gaseous fuel coaxially enclosing the inner passage, wherein the gaseous fuel is disposed in the outer passage; a plurality of outer nozzles branching off radially from the outer passage; a plurality of inner nozzles branching off radially from the inner passage, each extending coaxially inside a respective one of the outer nozzles; and a distributor section disposed axially upstream of the outer nozzles with respect to the lance axis in the outer passage and having a plurality of axially extending through-openings for the gaseous fuel, each through-opening having an opening width that is larger in a circumferential direction than in a radial direction, wherein a portion of the outer passage is disposed axially between the distributor section and the outer nozzles so as to effect a pressure difference of the gaseous fuel in the outer passage between an upstream and a downstream side of the distributor.