JPS58187530A - Control system for starting of gas turbine - Google Patents

Abstract

PURPOSE:To obtain stabilized burnability always irrespective of an open air temperature, by enabling to apply a fuel oil temperature and a correction signal of a temperature at an opening of a gas turbine compressure to a starting control system through which program control is made at the time of starting of a gas turbine. CONSTITUTION:A gas turbine burns fuel in a burner 2, under supply of compressed air by an air compressor 1, fed through a fuel flow control valve 7, makes a work by feeding high temperature and high pressure gas generated within the gas turbine 3, and drives a generator 4. At the time of starting of the gas turbine, an igniting fuel flow signal preset is made to apply from a signal generator 19 by igniting instructions. This signal corrected by an output signal of a correcting operation circuit 22 by making temperature of fuel oil and compressed air into inputs is applied to the fuel flow control valve 7 as a final igniting fuel flow signal from a fuel controller 8.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention is based on an old friend of fuel, a gas turbine, and an electric motor.
This is related to the control method that is used to start the program.

Figure 1 shows a row of planes at the StarVisi departure station.

The 6th air that is compressed to 100 million liters by combustion 62/lI
J heat n becomes a high temperature gas. This gas is processed by the turbine 3, which drives the generator 4 and heats the generator 4.The generated electricity is used to power the generator
Power is transmitted to The fuel regulator 7 controls the fuel flowing into the combustor according to the output signal from the fuel control device 8.

FIG. 2 shows a block diagram of the fuel 71S'lJ-device.

The fuel control system of the gas turbine is a startup control system 9. Speed ICE
/ Load control system 10. Acceleration m? 1lilJ groan yarn 11. Exhaust control is broadly divided into 1d41 and 12.

Startup Control - The fuel light weight is controlled according to the start-up program No. 1 that was added when starting up the system A gas turbine, and the gas turbine is started up at the rated power consumption of the gas turbine R.

The speed control system controls the speed and load after the gas turbine reaches its rated speed.

The turbine speed at the time of acceleration and launch is determined and the weight must not exceed 7'Ctillf.

I also want to control the crystallization, and the sales that have been established by the swindlers.
I/'1o1t111misakichoi)'s exit.

9 chivalry gate 13? The four above-mentioned Rira Turbines! ! I am sure that I will choose the other side depending on my situation.

The moving plate 91 shows the gas turbine excitation function in three cases.

When the gas turbine is set to the ignition speed in reverse T, the preset ignition fuel flow rate is given to the fuel valve control, and after the VIPs are selected, the fuel control valve is set. The number automatically turns on the ignition signal and the turbine warm water flow heavy old number 1
5, and upon completion of warm-up, the turbine is accelerated and reaches the rated speed.

Here, the ignition fuel flow rate signal is set so as to be able to supply fuel violet corresponding to the suitable ignition air-fuel ratio (mixture ratio of compressed air and fuel), but conventionally this setting has been constant; There was a drawback that the fuel could not be changed fully automatically in response to changes in the maximum AN level due to changes in external atmospheric temperature, etc.

Arrow 2 is the cause of poor fires due to changes in the external atmosphere.
There are many spots.

■-The optimum air-fuel ratio changes due to changes in temperature.

Figure 2-4 shows the state of fuel injection and expansion in the combustion engine, and as the fuel oil temperature changes, the needle nozzle 1 becomes viscous.
The expansion state of the fuel injected by 6L is the spark plug 17.
The most common ignition position can be removed.

The purpose of 2+ Yuanmei is to provide a start-up control method that can supply ignition fuel Rtk corresponding to a general standard fire air-fuel ratio under any external atmospheric temperature conditions.

The compressed air temperature and fuel oil are the ninth to eliminate the cause of failure of VIPs due to changes in external atmospheric temperature! By using a circuit that corrects the ignition fuel flow rate signal of the startup control system using the degree as a coefficient, it is possible to supply an air flow that corresponds to the breakthrough air-fuel ratio.

Figure 5 shows a block diagram of the start-up control system, and Figure 6 shows an example of Maki's old style.

When the ignition command is input, the flame d from the original generator 19
l) The output is the same as the ignition fuel current level set. This 16 flyV(-Toshina Tsumatsu and pressing force is set manually and the output signal of the 22 is used as a bias.
Give a light ignition system nine shifts to the fuel control project.

Here, the Rinnobuki circuit is 1. When the tFE temperature is low, the viscosity increases and the eruption diffusion becomes narrow, making it difficult to ignite. Furthermore, when the compressed air temperature decreases, the optimum ignition air-fuel ratio increases, so the fuel flow is directed in the tJw direction, and in the opposite direction when the air temperature increases.

Note that the correction amount is determined depending on each gas turbine condition.

According to the present invention, since the ignition fuel flow rate can be automatically controlled, there is an effect of increasing the performance of the gas turbine due to changes in the external atmospheric temperature.

[Brief explanation of the drawing]

Figure 1 shows the gas turbine power generation equipment, Figure 2 shows the fuel control system block, Figure 3 shows the gas turbine startup characteristics, Figure 4 shows the state of fuel spray in the combustor, and Figure 5 shows the startup control system. The block diagram in FIG. 6 is an ignition control circuit according to the present invention. 1... earth machine, 2... combustor, 3... turbine,
4...Hakkaki Thou, 5...Shiyamoki, 6...System, 7
...Fuel adjustment valve, 8...Fuel lI+control equipment, 9...
・Start control system, 10... Speed 1 load control system, 11...
Acceleration control system, 12...Temperature Ik system, 13...
Clear gate, 14 ・Ignition fuel flow-signal, 15... Warm and warm combustion, 16... Fuel nozzle nope 17... Ignition flag, 18... Combustor, 19-20... 1d Signal generation command, 22...Supplementary calculation circuit. Kaya 2nd 3rd J14th

Claims (1)

[Claims] 1. In the fuel oil-fired gas turbine generator feed #i, by providing fuel oil temperature and gas turbine pressure #i fuel inlet temperature correction signals to the startup control system that is controlled by the gas turbine startup wait program, A gas turbine startup system that outputs an ignition fuel flow rate signal depending on the temperature and that always has access to a designated key person.