Mitsubishi Hitachi Power Systems, Ltd.

Koji Takaoka

Yoshifumi Iwasaki

Takashi Sonoda

Akihiko Saito

Ryuji Takenaka

Hideki Haruta

Wataru Akizuki

Yuji Komagome

Kozo Toyama

Noriyoshi Uyama

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.

Control device, system, control method, power control device, gas turbine, and power control method

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.

Gas turbine inlet guide vane control device, system and control method

A combustion control device is installed in a gas turbine including a compressor, a combustor, a turbine, a turbine bypass pipe through which compressed air from a casing is discharged to a turbine downstream part so as to bypass the turbine, and a turbine bypass valve that regulates a turbine bypass flow rate of the compressed air. The combustion control device includes: a fuel distribution setting unit that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section that sets the valve openings of fuel regulating valves. The fuel distribution setting unit includes correction means for modifying the fuel distribution ratios.

Gas turbine combustion control device and combustion control method and program therefor

A combustion control device () is installed in a gas turbine including a compressor (), combustors (), a turbine (), a bleed air pipe () through which bleed air is returned to an inlet of an air intake facility (), and an air bleed valve () that regulates the amount of bleed air extracted. The combustion control device () includes: a fuel distribution setting unit () that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section () that sets the valve openings of fuel regulating valves. The fuel distribution setting unit () includes correction means for modifying the fuel distribution ratios.

Growing community of inventors

Kanagawa, Japan

Koji Takaoka