Abstract: A combustion nozzle discharges compressed air and fuel, to be combusted, into a combustion chamber of a combustor of a gas turbine. The combustion nozzle includes an air inlet, a nozzle orifice, an air channel, a fuel channel, and fuel outlets. The air inlet receives the compressed air. The nozzle orifice opens into the combustion chamber and discharges the compressed air. The air channel communicates between the air inlet and the nozzle orifice. The fuel channel receives the fuel, and discharges the fuel from the fuel outlets toward a flow of the compressed air discharged from the nozzle orifice. The air channel includes a Venturi section in which a channel cross-sectional area of the compressed air becomes relatively small. The fuel outlets are provided in the Venturi section.

Abstract: A gas turbine is configured such that: in the case where the rotation speed of the turbine shaft is a predetermined rotation speed, when the magnitude of a load is set to a predetermined load, a compressed air quantity that is supplied to a primary combustion field in a combustor and a fuel quantity that is supplied to the combustor are controlled to quantities for an equivalent ratio that allows misfire to avoided; and when the magnitude of the load is set to no load, the compressed air quantity that is supplied to the primary combustion field in the combustor and the fuel quantity that is supplied to the combustor are reduced compared to when the magnitude of the load is set to the predetermined load, while the equivalent ratio that allows the misfire to be avoided is kept.

Abstract: A gas turbine is configured such that: in the case where the rotation speed of the turbine shaft is a predetermined rotation speed, when the magnitude of a load is set to a predetermined load, a compressed air quantity that is supplied to a primary combustion field in a combustor and a fuel quantity that is supplied to the combustor are controlled to quantities for an equivalent ratio that allows misfire to avoided; and when the magnitude of the load is set to no load, the compressed air quantity that is supplied to the primary combustion field in the combustor and the fuel quantity that is supplied to the combustor are reduced compared to when the magnitude of the load is set to the predetermined load, while the equivalent ratio that allows the misfire to be avoided is kept.

Abstract: A gas turbine is configured such that: in a combustor receiving fuel and compressed air, a compressed air quantity supplied to a primary combustion field in the combustor when the rotation speed of a turbine shaft is a predetermined rotation speed is a quantity causing an equivalent ratio at the primary combustion field to be an equivalent ratio allowing misfire to be avoided in an operation state with a predetermined rotation speed and a predetermined load; fuel supply to the combustor is started when rotation of the turbine shaft is started up; a fuel quantity supplied to the combustor is controlled such that the rotation speed of the turbine shaft rises to the predetermined rotation speed, after ignition within the combustor; and increase in a magnitude of the load to the predetermined load is started before the rotation speed of the turbine shaft reaches the predetermined rotation speed.

Abstract: A combustion nozzle injects compressed air and fuel for combustion into a combustion chamber of a combustor for a gas turbine. The combustion nozzle includes a first air injection hole through which a first air flow of the compressed air is injected into the combustion chamber, a second air injection hole through which a second air flow of the compressed air is injected adjacent to the first air flow into the combustion chamber, and a fuel injection hole through which a fuel flow of the fuel is injected into the combustion chamber at a flow velocity different from a flow velocity of the first air flow and a flow velocity of the second air flow in a state where the fuel flow is sandwiched between the first air flow and the second air flow. The fuel injection hole has an inner diameter smaller than a quenching distance of the fuel.

Abstract: A combustion nozzle discharges compressed air and fuel, to be combusted, into a combustion chamber of a combustor of a gas turbine. The combustion nozzle includes an air inlet, a nozzle orifice, an air channel, a fuel channel, and fuel outlets. The air inlet receives the compressed air. The nozzle orifice opens into the combustion chamber and discharges the compressed air. The air channel communicates between the air inlet and the nozzle orifice. The fuel channel receives the fuel, and discharges the fuel from the fuel outlets toward a flow of the compressed air discharged from the nozzle orifice. The air channel includes a Venturi section in which a channel cross-sectional area of the compressed air becomes relatively small. The fuel outlets are provided in the Venturi section.

Abstract: An air-bleed gas turbine includes a compressor; a combustor; a turbine; and an air bleed portion by which compressed air, which is supplied from the compressor to a circular space that surrounds the combustor, is partially supplied to a device outside the air-bleed gas turbine. The air bleed portion includes an air bleed passage that is communicated with an air bleed port which is connected to the device outside the air-bleed gas turbine, and a communication passage that is communicated with the circular space. The air bleed passage is communicated with the circular space through the communication passage. The flow passage area of the communication passage is increased as the distance from the air bleed port increases in the circumferential direction of the circular space.

Abstract: An air-bleed gas turbine includes a compressor; a combustor; a turbine; and an air bleed portion by which compressed air, which is supplied from the compressor to a circular space that surrounds the combustor, is partially supplied to a device outside the air-bleed gas turbine. The air bleed portion includes an air bleed passage that is communicated with an air bleed port which is connected to the device outside the air-bleed gas turbine, and a communication passage that is communicated with the circular space. The air bleed passage is communicated with the circular space through the communication passage. The flow passage area of the communication passage is increased as the distance from the air bleed port increases in the circumferential direction of the circular space.