Patent ID: 7200998

Claim:
A combustion method for a gas turbine combustor having a plurality of fuel nozzles each jetting fuel into a combustion chamber, comprising the steps of: jetting fuel from a fuel nozzle into an air hole arranged so as to be spaced from a downstream end of the fuel nozzle in an axial direction of the fuel nozzle, to allow a fuel jet flow from the fuel nozzle to flow through the air hole from an upstream side of the combustion chamber to a downstream end of the combustion chamber, said air hole being disposed coaxially or almost coaxially with a fuel injection hole of said fuel nozzle; and flowing combustion air from a circumference of the fuel jet flow into the combustion chamber through the air hole to premix the jetted fuel, with the diameter of said air hole being larger than the fuel injection hole diameter of said fuel nozzle.