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A gas turbine starting method, comprising the steps of rotatively driving a turbine by a motor coupled to the turbine, while at the same time supplying a compressed air to a combustor by an air compressor operating in interlocking motion with the turbine, starting a fuel supply to the combustor when

A gas turbine starting method, comprising the steps of rotatively driving a turbine by a motor coupled to the turbine, while at the same time supplying a compressed air to a combustor by an air compressor operating in interlocking motion with the turbine, starting a fuel supply to the combustor when a revolution speed of the turbine has reached up to a predetermined value, and simultaneously starting an igniting operation on an air-fuel mixture in the combustor, wherein at least during the igniting operation to the air-fuel mixture in the combustor, a quantity of fuel supply per unit time to the combustor is increased while increasing the revolution speed of the turbine, to thereby ensuring the ignition of the air-fuel mixture under various conditions, and depressing the temperature rise of the gas turbine, which may otherwise occur immediately after the ignition.

대표청구항 ▼

What is claimed is: 1. A starting method of a gas turbine apparatus comprising the steps of: rotating a turbine by a motor coupled to said turbine, while supplying a compressed air to a combustor by an air compressor; starting a fuel supply to said combustor when a rotation speed of said turbine ha

What is claimed is: 1. A starting method of a gas turbine apparatus comprising the steps of: rotating a turbine by a motor coupled to said turbine, while supplying a compressed air to a combustor by an air compressor; starting a fuel supply to said combustor when a rotation speed of said turbine has reached a predetermined value, thus producing an air-fuel mixture; and starting an igniting operation to ignite the air-fuel mixture in said combustor; wherein during the igniting operation prior to a time when the air-fuel mixture in said combustor begins to ignite, a quantity of fuel supplied to said combustor per unit time is increased while the revolution speed of said turbine is increased. 2. A gas turbine apparatus comprising: a motor for rotatively driving a turbine; a motor control section for controlling a revolution speed of said motor; a combustor for burning an air-fuel mixture thereby generating a combustion gas therein; an air compressor for supplying a compressed air to said combustor, said compressor operating in interlocking motion with said turbine; and a fuel flow control valve for controlling a quantity of fuel supply per unit time to said combustor; wherein at least during an igniting operation for the air-fuel mixture in said combustor, and prior to a time when the air-fuel mixture in said combustor begins to ignite, a quantity of fuel supply per unit time to said combustor is increased through said fuel flow control valve while increasing a revolution speed of said turbine by said motor through control of said motor control section. 3. A starting method of a gas turbine apparatus comprising the steps of: igniting a mixture of fuel and air while rotatively driving a turbine by a motor, to combust said mixture; and supplying a combustion gas generated by said combustion to said turbine thereby increasing a revolution speed of said turbine; wherein for a predetermined time period immediately after the mixture begins to ignite, a quantity of fuel supply per unit time provided for the combustion is held to be constant. 4. A starting method of a gas turbine apparatus in accordance with claim 3, in which after said predetermined time period has elapsed, the quantity of fuel supply per unit time is gradually increased while at the same time, a rotative driving force for said turbine provided by said motor is decreased gradually. 5. A gas turbine apparatus in which a mixture of air and fuel is combusted and a combustion gas generated by said combustion is supplied to a turbine to rotatively drive said turbine, said apparatus comprising: an ignition means for performing an igniting operation on the air-fuel mixture while rotatively driving said turbine by a motor during starting operation; a fuel flow control valve of variable opening for controlling a quantity of fuel supply per unit time to be provided for the combustion; an ignition detecting means for detecting an ignition of the air-fuel mixture; and an opening holding means for holding the opening of said fuel flow control valve to be constant for a predetermined time period immediately after the beginning of ignition of the air-fuel mixture has been detected by said ignition detecting means. 6. A gas turbine apparatus in accordance with claim 5, said apparatus further comprising a driving force controlling means for gradually decreasing a current supply per unit time to said motor and at the same time gradually increasing the opening of said fuel flow control valve after said predetermined time period has elapsed. 7. A gas turbine apparatus in accordance with claim 6, in which said driving force controlling means comprises: an air fuel ratio control section for controlling an air fuel ratio of a mixture by operating the opening of said fuel flow control valve; and a current supply control section for controlling the current supply per unit time to said motor; wherein after said predetermined time period has elapsed, the opening of said fuel flow control valve is gradually increased by said air fuel ratio control section while controlling said motor by said current supply control section such that said turbine may keep a predetermined target acceleration of revolution. 8. A gas turbine apparatus in accordance with claim 6, in which said driving force controlling means comprises: a current supply control section for controlling the current supply per unit time to said motor; and an acceleration control section for controlling an acceleration of revolution of said turbine by operating the opening of said fuel flow control valve; wherein after said predetermined time period has elapsed, the current supply per unit time to said motor is gradually decreased by said current supply control section while controlling said turbine to keep the predetermined target acceleration of revolution by said acceleration control section.