JP-2026074554-A - Gas turbine control device, gas turbine control method, and program

JP2026074554AJP 2026074554 AJP2026074554 AJP 2026074554AJP-2026074554-A

Abstract

[Problem] To provide a gas turbine control device that can shorten the gas turbine startup time regardless of changes in atmospheric temperature. [Solution] The gas turbine control device includes a startup fuel command value output unit that outputs a startup fuel command value, a fuel control unit that calculates a fuel limit value based on the rotational speed and acceleration rate setting value of the gas turbine, and a selection unit that selects the larger of the startup fuel command value and the fuel limit value as the fuel command value. The fuel control unit includes an acceleration rate limit unit that sets the acceleration rate limit value to a first acceleration rate limit value when the value obtained by subtracting the startup fuel command value from the fuel limit value is less than a predetermined value, and switches the acceleration rate limit value to a second acceleration rate limit value that is lower than the first acceleration rate limit value when the value obtained by subtracting the startup fuel command value from the fuel limit value is greater than a predetermined value, and an acceleration rate setting unit that sets the acceleration rate setting value based on the acceleration rate limit value. [Selection Diagram] Figure 3

Inventors

千土泰弘
足土広祐
谷部一輝
田中慎祐

Assignees

三菱重工業株式会社

Dates

Publication Date: 20260507
Application Date: 20241021

Claims (7)

A startup fuel command value output unit outputs a startup fuel command value when a gas turbine is started up, A fuel control unit that calculates a fuel limit value for the gas turbine based on the rotational speed and acceleration rate setting value of the gas turbine, A selection unit that selects the larger of the above-mentioned startup fuel command value and the above-mentioned fuel limit value as the fuel command value for the gas turbine, Equipped with, The fuel control unit, The acceleration rate limiting unit has a setting that sets the acceleration rate limiting value to a first acceleration rate limiting value when the value obtained by subtracting the startup fuel command value from the fuel limiting value is less than a predetermined value, and switches the acceleration rate limiting value to a second acceleration rate limiting value that is lower than the first acceleration rate limiting value when the value obtained by subtracting the startup fuel command value from the fuel limiting value is greater than a predetermined value. The fuel limit value is calculated based on the acceleration rate setting value set by the acceleration rate limit value. Gas turbine control system.
The fuel control unit further includes a fuel throttle amount calculation unit that calculates a fuel flow throttle amount based on the difference between the measured rotational speed of the gas turbine and the target rotational speed of the gas turbine corresponding to the speed increase rate setting value. The gas turbine control device according to claim 1.
The fuel control unit further includes a speed-up rate setting unit for setting the speed-up rate setting value and a second speed-up rate setting unit for setting a second speed-up rate setting value based on the measured rotational speed of the gas turbine. The acceleration rate setting unit sets the acceleration rate setting value to the lower of the acceleration rate limit value and the second acceleration rate setting value. The gas turbine control device according to claim 1 or 2.
The acceleration rate limiting unit switches to the second acceleration rate limiting value when the measured rotational speed of the gas turbine exceeds a predetermined rotational speed determination value, even if the value obtained by subtracting the startup fuel command value from the fuel limiting value is less than a predetermined value. The gas turbine control device according to claim 1 or 2.
The second speed-up rate setting unit sets the second speed-up rate setting value such that it becomes higher the smaller the measured rotational speed of the gas turbine is. The gas turbine control device according to claim 3.
A step of outputting the startup fuel command value when starting up a gas turbine, A step of calculating the fuel limit value for the gas turbine based on the rotational speed and acceleration rate setting value of the gas turbine, The steps include selecting the larger of the above-mentioned startup fuel command value and the above-mentioned fuel limit value as the fuel command value for the gas turbine, It has, The step of calculating the aforementioned fuel limit value is: The steps include setting the acceleration rate limit value to a first acceleration rate limit value if the value obtained by subtracting the startup fuel command value from the fuel limit value is less than a predetermined value, and switching the acceleration rate limit value to a second acceleration rate limit value lower than the first acceleration rate limit value if the value obtained by subtracting the startup fuel command value from the fuel limit value is greater than a predetermined value, A step of calculating the fuel limit value based on the acceleration rate setting value set by the acceleration rate limit value, Having, Gas turbine control method.
A step of outputting the startup fuel command value when starting up a gas turbine, A step of calculating the fuel limit value for the gas turbine based on the rotational speed and acceleration rate setting value of the gas turbine, The steps include selecting the larger of the above-mentioned startup fuel command value and the above-mentioned fuel limit value as the fuel command value for the gas turbine, A program that causes the gas turbine control device to execute, The step of calculating the aforementioned fuel limit value is: The steps include setting the acceleration rate limit value to a first acceleration rate limit value if the value obtained by subtracting the startup fuel command value from the fuel limit value is less than a predetermined value, and switching the acceleration rate limit value to a second acceleration rate limit value lower than the first acceleration rate limit value if the value obtained by subtracting the startup fuel command value from the fuel limit value is greater than a predetermined value, A step of calculating the fuel limit value based on the acceleration rate setting value set by the acceleration rate limit value, Having, program.

Description

This disclosure relates to a gas turbine control device, a gas turbine control method, and a program. During gas turbine startup, after fuel ignition in the combustor, the rotor is accelerated at a predetermined acceleration rate setting until the rotor speed reaches a predetermined rotational speed R1 (e.g., rated rotational speed). Figure 8 shows an example of control between rotor speed N [rpm] and fuel command value CSO [%] by a conventional gas turbine control device. In Figure 8, N_L is an example of an actual measured value of rotor speed at low atmospheric temperature (e.g., winter), and N_H is an example of an actual measured value of rotor speed at high atmospheric temperature (e.g., summer). CSO_L is an example of a fuel command value at low atmospheric temperature, and CSO_H is an example of a fuel command value at high atmospheric temperature. As shown in Figure 8, the gas turbine control device constantly calculates the fuel limit value FLCSO based on the rotor speed N and acceleration rate setting, and selects the higher of the constant warm-up fuel command value WUP CSO and the fuel limit value FLCSO as the fuel command value CSO. The gas turbine control device supplies fuel to the combustor based on the fuel command value CSO. Referring to the example at low atmospheric temperature shown in Figure 8, we will describe the conventional control method for the fuel command value CSO. Immediately after fuel supply and ignition start (Fuel ON) at time t1, the rotor speed N jumps to a value greater than the target speed based on the acceleration rate setting. Therefore, the gas turbine control device performs feedback control to reduce the difference between the rotor speed N and the target speed, and the fuel limit value FLCSO temporarily decreases. Subsequently, as the jump in rotor speed N settles down, the fuel limit value FLCSO increases. At time t2, when the fuel limit value FLCSO becomes higher than the warm-up fuel command value WUP CSO, the gas turbine control device selects the fuel limit value FLCSO as the fuel command value CSO. The timing when the fuel limit value FLCSO exceeds the warm-up fuel command value WUP CSO is called acceleration entry. After acceleration begins, the rotor speed N increases according to the set rate of increase, and the fuel limit value FLCSO also increases. When the rotational speed N reaches the predetermined rotational speed R1 at time t4, the startup is complete. Patent Document 1 describes a technique for shortening the gas turbine startup time by increasing the rate of increase setting after acceleration is initiated. Furthermore, Patent Document 1 describes a technique for shortening the gas turbine startup time by increasing the rate of increase setting value while the rotor speed N before acceleration rises from the ignition speed R0 to a predetermined speed. This reduces the drop in the fuel limit value FLCSO associated with the aforementioned jump in rotor speed N, thereby suppressing the delay in the timing of acceleration and shortening the gas turbine startup time. Japanese Patent Publication No. 2024-008393 This diagram shows the overall configuration of the gas turbine system according to the first embodiment.This is a block diagram showing the functional configuration of a gas turbine control device according to the first embodiment.This is a first block diagram showing the calculation logic of a gas turbine control device according to the first embodiment.This is a second block diagram showing the calculation logic of a gas turbine control device according to the first embodiment.This figure shows an example of controlling the rotor speed N [rpm] and the fuel command value CSO [%] by a gas turbine control device according to the first embodiment.This is a block diagram showing the calculation logic of a gas turbine control device according to a modified example of the first embodiment.This is a schematic block diagram showing the configuration of a computer according to one embodiment.This figure shows an example of control between rotor speed N [rpm] and fuel command value CSO [%] using a conventional gas turbine control device. <First Embodiment> The embodiments will be described in detail below with reference to the drawings. (Overall configuration of the gas turbine system) Figure 1 is a diagram showing the overall configuration of a gas turbine system according to the first embodiment. As shown in Figure 1, the gas turbine system 100 includes a gas turbine 1 and a gas turbine control device 10 that controls the gas turbine 1. The gas turbine 1 comprises a compressor 2, a combustor 3, and a turbine 4. The compressor 2 and the turbine 4 are connected by a rotor 5. The compressor 2 compresses air taken in from the outside to produce compressed air. The combustor 3 mixes the compressed air supplied from the compressor 2 with fuel and burns it to produce high-temperature combustion gas. The turbine 4 is rotated by the combustion gas generate