Patent ID: 7871262

Claim:
A method for combusting gaseous fuel, the method comprising: providing a gas turbine having a burner and a combustion chamber, the burner comprising a swirl generator and into which burner liquid fuel can be fed centrally along a burner axis, forming a conical liquid fuel column, and which liquid fuel column is enveloped by, and mixed through with, a rotating combustion air flow which flows tangentially into the swirl generator; feeding a gaseous fuel having a hydrogen portion of at least 50% inside the swirl generator at least one of axially and coaxially to the burner axis, forming a fuel flow with a spatially defined flow pattern which is maintained inside the burner; mixing the fuel flow thoroughly with combustion air to form an air-fuel mixture; bursting open the air-fuel mixture in the region of the burner outlet, including forming a backflow zone in the combustion chamber; and completely combusting the air-fuel mixture inside the combustion chamber while maintaining the backflow zone.