Patent ID: 8393159

Claim:
A gas turbine combustor for mixing fuel into combustion air introduced from a compressor, burning an air-fuel mixture, and supplying produced combustion gas to a gas turbine, the combustor comprising: a first fuel nozzle for jetting out fuel; a pre-mixture chamber having a single wall defining said pre-mixture chamber therein downstream of the first fuel nozzle; air holes bored in a circumferential direction through said pre-mixture chamber wall in plural stages in the direction of an axis of the pre-mixture chamber wall; and second fuel nozzles disposed in plural stages in the direction of the axis around an exterior of said pre-mixture chamber wall in an opposing relationship and alignment respectively with said air holes; said air holes and said second fuel nozzles being configured to generate swirling flows in said pre-mixture chamber, and the length of each of the air holes effective for mixing being determined by the thickness of the pre-mixture chamber wall.