Mitsubishi Heavy Industries Limited

Kozo Toyama

Masumi Nomura

Kentaro Fujii

Satoshi Tanaka

Hiroyuki Iba

Shinsuke Nakamura

Tomo Kawakami

Kotaro Miyauchi

Fuminori Fujii

Shoichi Harada

Shouichi Nagata

Hitoi Ono

Toshimitsu Morimoto

Kuniharu Fujibayashi

Fuminori Fuji

Naoki Ujiie

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 unitperforms a frequency analysis of combustion oscillation of a combustor and splits a result of the analysis into respective frequency bands. Then, a state grasping unitchecks 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. A countermeasure determining unitconducts a countermeasure for controlling an operating action of the gas turbine on the basis of the operating state thus checked.

Gas turbine control device and gas turbine system

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.

Gas turbine control device

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. the correlation between the load amount of a gas turbine and control inputs such as a fuel flow rate, air flow rate, pilot fuel ratio, and top hat fuel ratio in the gas turbine, wherein the amount of load variation for at least one of control inputs, a fuel flow rate or an air flow rate supplied to a combustor is predicted according to operational conditions obtained by searching using the load sensitivity, regulation is made according to the prediction results, and the regulation results are stored in the second database.

Gas turbine control method and device

Extremely cold (e.g., &#x2212;20&#xb0; C.) air A is heated by a heat exchanger, which is supplied with steam S via a control valve, and heated air A' is taken into a gas turbine. The valve opening degree of the control valveis feedback-controlled so that the deviation between the measured temperature tand the target temperature TO of the heated air A&#x2032; is eliminated. Further, when the number of revolutions, N, of the gas turbineincreases, or when an IGV opening degree OP increases, the valve opening degree of the control valveis 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&#x2032; 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.

Intake air heating control device for gas turbine

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.

Gas turbine protection device

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&#xb0; C. and 1500&#xb0; 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&#xb0; C.MW and 1500&#xb0; C.MW (temperature controlled MW), and then to correct the 1400&#xb0; C.MW and the 1500&#xb0; C.MW so as to match the ideal MW with a measured gas turbine output (a power generator output).

Gas turbine output learning circuit and combustion control device for gas turbine having the same

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.

Combustion control device for gas turbine

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&#xb0; C. MW value and a 1500&#xb0; C. MW value based on an inlet guide vane aperture, an intake-air temperature, and an atmospheric pressure ratio, then to calculate the combustion load command value to render the combustion gas temperature at the inlet of the gas turbine dimensionless by direct interpolation based on these values and an actual measurement value of a power generator output, and to control apertures of a pilot fuel flow rate control valve, a top hat fuel flow rate control valve, and a main fuel flow rate control valve based on ratios of fuel gas to be determined based on this combustion load command value, and thereby to control fuel supplies to a pilot nozzle, a top hat nozzle, and a main nozzle.

An IGV opening command is set based on an IGV opening A set by an exhaust gas temperature control section, an IGV opening B set by a compressor surge protective control section, and an IGV opening C set by an exhaust gas pressure protective control section. The value of the IGV opening A, or the value of the IGV opening B, whichever is higher, is selected, the higher selected value, or the value of the IGV opening C, whichever is lower, is selected, and the lower selected value is set as the IGV opening command (gas turbine back pressure rise avoidance priority mode). Alternatively, the value of the IGV opening A, or the value of the IGV opening C, whichever is lower, is selected, the lower selected value, or the value of the IGV opening B, whichever is higher, is selected, and the higher selected value is set as the IGV opening command (compressor surge avoidance priority mode). Alternatively, a switcher switches between these modes.

Inlet guide vane control device of gas turbine

In a gas turbine control apparatus, a frequency analyzing section frequency-analyzes at least one of pressure oscillation in combustors of a gas turbine and acceleration oscillation of each of the combustors and outputs a first frequency analysis result as the result of frequency analysis for a plurality of predetermined frequency bands. A control unit controls at least one of a first fuel flow rate of fuel and a first air flow rate of air based on the first frequency analysis result for the plurality of frequency bands. The fuel and the air are supplied to the gas turbine.

Gas turbine control apparatus and gas turbine system using the same

A turbine inlet temperature operating section () determines the turbine inlet temperature Tbased on the flow rate Gf and temperature Tf of fuel being supplied to a combustor () and the flow rate Gand temperature Tof air. Based on the turbine inlet temperature T, a pilot ratio operating section () sets a pilot ratio, and a bypass valve operating section () and an IGV opening operating section () generate a bypass valve control signal and an IGV control signal, respectively.

Combustor controller

A gas turbine control apparatus, etc. are provided by which combustion fluctuation, even if arising in plural frequency bands, can be effectively suppressed. If the combustion fluctuation arises in plural frequency bands, corresponding to a predetermined priority order, adjustment is done so that the combustion fluctuation of the frequency band of a high priority order is suppressed. If the gas turbine state changes after the adjustment, this is reflected on a data base. If no sufficient data is stored yet in the data basefor any the reason, such as immediately after installation of the gas turbine, correction is made using data of countermeasures based on data of another same type gas turbine contained in a basic data base 31 and data of countermeasures based on experiences of skilled adjusting operators contained in a knowledge data base. Also, in a stabilized operation, operation condition may be varied so that an optimal operation condition is automatically searched.

Gas turbine control apparatus, gas turbine system and gas turbine control method

A combustion temperature high speed detection device is provided with a phase lead processing portion, thereby canceling out a detection lag of a temperature detector, and detecting the combustion gas temperature of a combustor at a high speed. The combustion temperature high speed detection device is also provided with a first-order lag filtering portion with a time constant of 0.25 second, a phase lag processing portion with a time constant of 10 seconds, a temperature change filtering portion with a cutoff frequency of 2 to 3 Hz, and a disturbance filtering portion including first-order lag filtering portions with different time constants and a high value selecting portion. Thus, high speed detection of the combustion gas temperature more suitable for a gas turbine system can be performed.

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Takasago, Japan

Kozo Toyama