Patent ID: 7426833

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 wall provided with said first fuel nozzle at a center thereof, having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out from said first fuel nozzle, and defining a pre-mixture chamber therein; a plurality of air inlet holes bored through said pre-mixture chamber wall and introducing the combustion air to said pre-mixture chamber such that angles at which the combustion air is introduced to said pre-mixture chamber through said air inlet holes are deflected at least toward the circumferential direction of said pre-mixture chamber wall; and a plurality of second fuel nozzles disposed around said pre-mixture chamber wall in an opposing relation respectively to said plurality of air inlet holes and jetting out fuel substantially coaxially with axes of said air inlet holes.