Patent ID: 6158223
Filing Date: 2000-12-12
Classification: F23D,F23R

Abstract:
A gas turbine combustor comprising:a cylinder body having an upstream side;a pilot fuel nozzle disposed along a central axis of said cylinder body;a pilot swirler disposed around said pilot fuel nozzle;a plurality of main burners disposed about an outer periphery of said pilot swirler, wherein combustion air flows along an outer periphery of said cylinder body and turns to enter said cylinder body from the upstream side of said cylinder body so as to flow into said pilot fuel nozzle and said main burners, and then the combustion air is to be mixed with a fuel to effect combustion; andan air flow adjusting device disposed on the upstream end of said cylinder body, said air flow adjusting device being capable of adjusting the flow of combustion air such that a flow velocity of the combustion air in said main burners and said air flow adjusting device is made uniform,wherein said air flow adjusting device is adapted to cause a flow rate of the combustion gas flowing into said main burners and a flow rate of the combustion gas flowing into said pilot swirler to become nearly equal.