Abstract: An abnormality detection system for a combustor for a gas turbine, includes: a sensor for detecting whether an ignition plug is located at an insertion position in a combustion tube of the combustor for the gas turbine, the ignition plug being disposed movably between the insertion position and a retracted position retracted from the combustion tube; and a diagnostic unit configured to diagnose an abnormality in an ignition device including the ignition plug, based on a detection result by the sensor.

Abstract: Provided is a control device of a gas turbine including a compressor, a combustor, and a turbine. The control device executes load control of allowing an operation control point for operation control of a gas turbine to vary in response to a load of the gas turbine. The operation of the gas turbine is controlled on the basis of a rated temperature adjustment line for temperature adjustment control of a flue gas temperature at a predetermined load to a rated flue gas temperature at which performance of the gas turbine becomes rated performance, a preceding setting line for setting of the flue gas temperature at the predetermined load to a preceding flue gas temperature that becomes lower in precedence to the rated flue gas temperature, and a limit temperature adjustment line for temperature adjustment control.

Abstract: A control device is configured to control a gas turbine that is configured to compress a suctioned air with a compressor to obtain compressed air, mix a fuel supplied from a combustor with the compressed air to burn the fuel and the compressed air to generate a combustion gas, operate a turbine with the combustion gas to rotate a rotor, and discharge the combustion gas that has operated the turbine as a flue gas. The compressor includes an inlet guide vane which is capable of adjusting a degree of opening and is on an air-suction side, and the control device is configured to execute temperature adjustment control to control the degree of opening of the inlet guide vane along a temperature adjustment line indicating an upper limit temperature of a flue gas temperature defined according to a load of the gas turbine.

Abstract: Provided is a control device of a gas turbine including a compressor, a combustor, and a turbine. The control device executes load control of allowing an operation control point for operation control of a gas turbine to vary in response to a load of the gas turbine. The operation of the gas turbine is controlled on the basis of a rated temperature adjustment line for temperature adjustment control of a flue gas temperature at a predetermined load to a rated flue gas temperature at which performance of the gas turbine becomes rated performance, a preceding setting line for setting of the flue gas temperature at the predetermined load to a preceding flue gas temperature that becomes lower in precedence to the rated flue gas temperature, and a limit temperature adjustment line for temperature adjustment control.

Abstract: A control device 14 of a gas turbine that compresses a suctioned air with a compressor to obtain compressed air, mixes a fuel supplied from a combustor with the compressed air to burn the fuel and the compressed air to obtain a combustion gas, operates a turbine with the generated combustion gas to rotate a rotor, and discharges the combustion gas that has operated the turbine as a flue gas, the compressor including an inlet guide vane capable of adjusting the degree of opening and provided on an air-suction side, and temperature adjustment control to control the degree of opening of an inlet guide vane being executed along a temperature adjustment line indicating an upper limit temperature of a flue gas temperature defined according to a load of the gas turbine.

Abstract: An object of the present invention is to provide a gas turbine control device which is capable of performing correction on the basis of a fuel composition of fuel gas to be supplied to a gas turbine, and is capable of changing an amount of correction in response to variation with time of the gas turbine. To attain this, a frequency analyzing unit 25 performs a frequency analysis of combustion oscillation of a combustor and splits a result of the analysis into respective frequency bands. Then, a state grasping unit 22 checks an operating state of the gas turbine on the basis of the result of the analysis of the combustion oscillation and process value of the gas turbine, and corrects the checked operating state on the basis of a fuel composition or a heat capacity of fuel gas measured by a fuel characteristic measuring unit 200. A countermeasure determining unit 23 conducts a countermeasure for controlling an operating action of the gas turbine on the basis of the operating state thus checked.

Abstract: A gas turbine controller having a first generator for setting the flow rate of fuel or air being supplied to a combustor in correspondence with a target load, a sensor for detecting intake temperature of a compressor, a second generator for setting a correction amount of a set value of fuel flow rate or air flow rate based on the value detected by the sensor, a third generator for setting a modification amount of the correction amount while taking account of the target load, a first multiplier for operating a modified correction amount from a correction amount set by the second generator and a modification amount set by the third generator, and a second multiplier for calculating the flow rate of fuel or air being supplied to a combustor by adding the modified correction amount to the set value of fuel flow rate or air flow rate.

Abstract: Provided is a gas turbine control method and control device whereby a design performance and an operating state based on ideal fuel flow rate and air flow rate simulated at the time of designing can be maintained by preventing an operation deviated from an operating condition that is based on ideal fuel flow rate and air flow rate simulated by initial design values, in a gas turbine control method designed to search optimal operating conditions automatically using control inputs such as a pilot ratio. The gas turbine controller comprises a second database that stores load sensitivity, i.e.

Abstract: An object of the present invention is to provide a gas turbine control device which is capable of performing correction on the basis of a fuel composition of fuel gas to be supplied to a gas turbine, and is capable of changing an amount of correction in response to variation with time of the gas turbine. To attain this, a frequency analyzing unit 25 performs a frequency analysis of combustion oscillation of a combustor and splits a result of the analysis into respective frequency bands. Then, a state grasping unit 22 checks an operating state of the gas turbine on the basis of the result of the analysis of the combustion oscillation and process value of the gas turbine, and corrects the checked operating state on the basis of a fuel composition or a heat capacity of fuel gas measured by a fuel characteristic measuring unit 200. A countermeasure determining unit 23 conducts a countermeasure for controlling an operating action of the gas turbine on the basis of the operating state thus checked.

Abstract: Extremely cold (e.g., ?20° C.) air A is heated by a heat exchanger 30, which is supplied with steam S via a control valve 32, and heated air A? is taken into a gas turbine 10. The valve opening degree of the control valve 32 is feedback-controlled so that the deviation between the measured temperature t1 and the target temperature TO of the heated air A? is eliminated. Further, when the number of revolutions, N, of the gas turbine 10 increases, or when an IGV opening degree OP increases, the valve opening degree of the control valve 32 is feedforward-controlled in accordance with the increase in the number N of revolutions or the increase in the IGV opening degree OP. By so doing, the temperature of air A? can be maintained at a temperature enabling stable combustion without delay in control, and intake air can be heated without delay in control, even at the start of the gas turbine or during change in the opening degree of an inlet guide vane.

Abstract: An object of the present invention is to provide a gas turbine control device which is capable of performing correction on the basis of a fuel composition of fuel gas to be supplied to a gas turbine, and is capable of changing an amount of correction in response to variation with time of the gas turbine. To attain this, a frequency analyzing unit 25 performs a frequency analysis of combustion oscillation of a combustor and splits a result of the analysis into respective frequency bands. Then, a state grasping unit 22 checks an operating state of the gas turbine on the basis of the result of the analysis of the combustion oscillation and process value of the gas turbine, and corrects the checked operating state on the basis of a fuel composition or a heat capacity of fuel gas measured by a fuel characteristic measuring unit 200. A countermeasure determining unit 23 conducts a countermeasure for controlling an operating action of the gas turbine on the basis of the operating state thus checked.

Abstract: Occurrence of combustion vibration is prevented in a gas turbine plant by enhancing the degree of freedom in setting an airflow rate or a fuel flow rate in correspondence with a target load thereby enhancing combustion stability.

Abstract: Provided is a gas turbine control method and control device whereby a design performance and an operating state based on ideal fuel flow rate and air flow rate simulated at the time of designing can be maintained by preventing an operation deviated from an operating condition that is based on ideal fuel flow rate and air flow rate simulated by initial design values, in a gas turbine control method designed to search optimal operating conditions automatically using control inputs such as a pilot ratio. The gas turbine controller comprises a second database that stores load sensitivity, i.e.

Abstract: An object of the invention is to provide a thermocouple having a high response speed without receiving mechanical damages such as bending and curving even when it is used in a high-speed fluid.

Abstract: A gas turbine has a plurality of combustors in a toroidal arrangement to provide combustion gases to turbine blades, thereby rotating the turbine body. Thermocouples, the number of which is the same as or greater than the number of the combustors, are arranged toroidally at the outlets of the turbine blades and measure the temperatures of the combustion gases at the respective outlets. During the operation of the gas turbine, if an abnormality, such as misfire or fuel injection nozzle obstruction, occurs in one or more of the combustors, the resulting change in gas temperature triggers a signal to stop, and thereby protect the gas turbine. Based on the measured values of the blade pass temperatures of the thermocouples and set threshold temperatures, a fuel supply system may be caused to gradually decrease the fuel supplied to the combustors to bring the gas turbine body to an automatic stop, or it may be cut off instantaneously, thus immediately stopping the gas turbine.

Abstract: A gas turbine output learning circuit is configured to compute a current combustion gas temperature TIT at an inlet of a gas turbine by linear interpolation by use of two characteristic curves A and B respectively representing relations between a pressure ratio and an exhaust gas temperature in the cases of the combustion gas temperature at the inlet of the gas turbine at 1400° C. and 1500° C., then to compute ideal MW corresponding to this combustion gas temperature TIT at the inlet of the gas turbine by linear interpolation according to 1400° C.MW and 1500° C.MW (temperature controlled MW), and then to correct the 1400° C.MW and the 1500° C.MW so as to match the ideal MW with a measured gas turbine output (a power generator output).

Abstract: Extremely cold (e.g., ?20° C.) air A is heated by a heat exchanger 30, which is supplied with steam S via a control valve 32, and heated air A? is taken into a gas turbine 10. The valve opening degree of the control valve 32 is feedback-controlled so that the deviation between the measured temperature t1 and the target temperature TO of the heated air A? is eliminated. Further, when the number of revolutions, N, of the gas turbine 10 increases, or when an IGV opening degree OP increases, the valve opening degree of the control valve 32 is feedforward-controlled in accordance with the increase in the number N of revolutions or the increase in the IGV opening degree OP. By so doing, the temperature of air A? can be maintained at a temperature enabling stable combustion without delay in control, and intake air can be heated without delay in control, even at the start of the gas turbine or during change in the opening degree of an inlet guide vane.

Abstract: A combustion control device for a gas turbine is capable of determining respective fuel flow rate control valve position command values based on fuel ratios. The combustion control device for a gas turbine is configured to calculate fuel flow rate command values for respective types of fuel gas based on a total fuel flow rate command value and fuel gas ratios, to calculate fuel gas flow rates based on the fuel flow rate command values and on a function of the fuel flow rate command value and the fuel gas flow rate, to calculate Cv values of the respective fuel flow rate control valves in accordance with a Cv value calculation formula based on the fuel gas flow rates, a fuel gas temperature, and front and back pressures of the respective fuel flow rate control valves, and to calculate respective fuel flow rate control valve position command values based on the Cv values and on a function between the Cv value and apertures of the fuel flow rate control valves.

Abstract: A combustion control device for a gas turbine is capable of controlling fuel ratios such as a pilot ratio and controlling an aperture of a combustor bypass valve in response to a combustion gas temperature at an inlet of the gas turbine in accordance with the original concept by computing a combustion load command value which is proportional to the combustion gas temperature. The combustion control device is configured to calculate a 700° C. MW value and a 1500° C.

Abstract: An object of the present invention is to provide a gas turbine control device which is capable of performing correction on the basis of a fuel composition of fuel gas to be supplied to a gas turbine, and is capable of changing an amount of correction in response to variation with time of the gas turbine. To attain this, a frequency analyzing unit 25 performs a frequency analysis of combustion oscillation of a combustor and splits a result of the analysis into respective frequency bands. Then, a state grasping unit 22 checks an operating state of the gas turbine on the basis of the result of the analysis of the combustion oscillation and process value of the gas turbine, and corrects the checked operating state on the basis of a fuel composition or a heat capacity of fuel gas measured by a fuel characteristic measuring unit 200. A countermeasure determining unit 23 conducts a countermeasure for controlling an operating action of the gas turbine on the basis of the operating state thus checked.