Abstract: 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 has a liquid fuel nozzle for jetting out liquid fuel and a pre-mixture chamber wall having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out from the liquid fuel nozzle, and defining a pre-mixture chamber therein. A plurality of gaseous fuel nozzles are disposed around the pre-mixture chamber wall in an opposing relation respectively to a plurality of air inlet holes bored through the pre-mixture chamber wall and jet out gaseous fuel substantially coaxially with the axes of the air inlet holes.

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

Abstract: 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 has a liquid fuel nozzle for jetting out liquid fuel and a pre-mixture chamber wall having a hollow conical shape gradually spreading in the direction in which the fuel is jetted out from the liquid fuel nozzle, and defining a pre-mixture chamber therein. A plurality of gaseous fuel nozzles are disposed around the pre-mixture chamber wall in an opposing relation respectively to a plurality of air inlet holes bored through the pre-mixture chamber wall and jet out gaseous fuel substantially coaxially with the axes of the air inlet holes.

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

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

Abstract: A semiconductor device has gate electrodes disposed in plural columns, respectively, over a semiconductor substrate in such a way as to be lined up along the direction of a gate length, and a gate connection portion provided in the same layer where the respective gate electrodes in the plural columns are placed, for electrically connecting the gate electrodes with each other. The gate connection portion includes a protrusion protruding outward in the direction of the gate length from the gate electrode positioned at the outermost ends of the gate electrodes disposed in the plural columns, respectively.

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

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

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

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

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