Gas turbine combustor for a gas turbine with flushing mechanism for a fuel nozzle

The invention relates to a gas turbine combustor for a gas turbine with a fuel nozzle 1 which is provided with a plurality Kraftstoffaustittsbohrungen 23, which are each connected to a fuel line 5, 7, 29, 30, through which fuel is durchleitbar selectively, characterized in that between each fuel outlet bores 23 different static pressures of the air flow between the fuel line with fuel flow and fuel lines are formed without fuel flow.