JPH0481527A - Gas turbine control device - Google Patents

Abstract

PURPOSE:To obtain operation with highest efficiency by circularly arranging a gas turbine exhaust gas temperature detector on a gas turbine exhaust part, and further circularly arranging a gas turbine inlet gas temperature detector on a gas turbine inlet high temperature part. CONSTITUTION:A gas turbine inlet gas temperature setter 33 provides a gas turbine inlet gas temperature set value. A gas turbine inlet gas temperature TY is a mean value obtained by passing temperature signals TY1 to TY12 from the twelve gas turbine inlet gas temperature setters 33 through a mean value computation circuit 37. The temperature deviation is obtained from the gas turbine inlet gas temperature set value and the temperature TY by means of an adder 34. The deviation is input to a proportional integral controller 35 to obtain a gas turbine inlet gas temperature control signal 36. The gas turbine inlet gas temperature should be the highest value allowable for the gas turbine inlet high temperature material in order to obtain maximum efficiency of the gas turbine. Thus, the signal 36 is input with priority, and a gas turbine exhaust gas temperature control signal 28 is used for backup.

Description

DETAILED DESCRIPTION OF THE INVENTION [Object of the Invention] (Industrial Application Field) The present invention relates to a gas turbine control device that monitors and controls a gas turbine plant in a power plant such as a combined cycle power plant.

(Prior Art) A system configuration diagram of a conventional gas turbine plant is shown in FIG. In FIG. 18, air taken in through the inlet air guide vane 1 is compressed into high pressure air by an air compressor 2. This high-pressure air compressor discharge air enters the combustor 4 from the combustor air hole 3 through an air passage (not shown) and is used as air for combustion of fuel. There are multiple combustors 4.

For convenience, two machines are shown in FIG. 18.

The fuel control valve 6 is controlled by a command from the gas turbine control device 5, and the fuel that has passed through the fuel control valve 6 is sent from the fuel burner 7 of each combustor 4 to the combustor 4 and burned. A flame detector 8 detects whether the combustion flame is ignited or misfired. Combustion gas from the combustor 4 is sent to the gas turbine 9 through a gas flow path (not shown). This high-pressure, high-temperature gas rotates the gas turbine shaft 10 in the gas turbine 9, so that the air compressor 2 and generator 11 coaxially rotate.

The gas that has been worked in the gas turbine 9 goes from the gas turbine exhaust section 12 to an exhaust heat recovery boiler (not shown).

A gas turbine exhaust gas temperature detector 13 is disposed in the gas turbine exhaust section 12 . For convenience, the number of detectors is 3.
Although only one detector is shown, typically more detectors are provided. The temperature signal of the gas turbine exhaust gas temperature detector 13 is sent to the gas turbine controller [5. The gas turbine control device 5 receives a speed signal obtained from a speed detector 15 mounted close to the gas turbine shaft end gear 14, a discharge air pressure obtained from an air compressor discharge air pressure detector 16, and a flame detector 8. Based on the ignition signal obtained from the ignition signal obtained from the gas turbine exhaust gas temperature detector 13 and the gas turbine exhaust gas temperature obtained from the gas turbine exhaust gas temperature detector 13, the angle of the inlet air guide vane 1 of the air compressor 2 is controlled to adjust the amount of air; The amount of fuel is adjusted by controlling the opening degree of the fuel control valve 6.

The conventional control system diagram for the gas turbine control device is shown in the first diagram.
It is shown in Figure 9. In FIG. 19, when starting the gas turbine, the starting control signal 18 of the starting control section 17 is set to a low value selection circuit 19.
is selected, and the opening degree of the fuel control valve 6 shown in FIG. 18 is controlled via the fuel valve control circuit 20.

The starting control unit 17 maintains the opening degree of the fuel control valve 6 at a predetermined ignition opening degree during the ignition operation, and when the spark plug (not shown) is ignited, the flame detector 8 detects that a flame has been established. It looks like this.

Once the flame is established, it is warmed up and the start control signal 1 is gradually activated.
8, the fuel control valve 6 is opened, and the fuel is gradually increased. The gas turbine speed N obtained from the gas turbine speed detector 15 gradually increases. The load/speed setter 21 is given a rated speed setting value at startup. An adder/subtractor 22 calculates the deviation between the rated speed setting value and the gas turbine speed N, and a proportional controller 23 multiplies the speed deviation to obtain a load/speed control signal 24.

When the gas turbine speed N reaches around the rated speed, the low value selection circuit 19 selects the load/lower value instead of the start control signal 18.
The speed control signal 24 becomes low and is selected.

After the gas turbine shaft 10 is maintained at rated speed, the generator 11 is connected to the power system. After joining, the gas turbine speed will be synchronized with the grid frequency and the rated speed will be maintained.

In order to increase the generator output, the value of the load/speed setter 21 is increased by a generator load control circuit (not shown), the opening degree of the fuel control valve 6 is increased, and the amount of fuel is gradually increased. At this time, the angle of the inlet air guide vane 1 also increases by a circuit not shown, and when it eventually reaches the maximum angle,
There, the amount of air is at its maximum. As the amount of fuel increases, the temperature TX of the gas turbine exhaust gas temperature detector 13 increases. The gas turbine exhaust gas temperature TX is obtained from FIG. FIG. 20 shows a case where the number of gas turbine exhaust gas temperature detectors 13 is n, and the average value calculation circuit 29 selects the average value of each of the n gas temperatures, and sets it as the gas turbine exhaust gas temperature TX. The deviation between the exhaust gas temperature setting value of the exhaust gas temperature setting device 25 and the exhaust gas temperature TX is calculated by the adder/subtractor 26, and the temperature deviation is passed through the proportional integral controller 27 to generate the gas turbine exhaust gas temperature control signal 28. When the air amount reaches the maximum and the fuel amount further increases, the gas turbine exhaust gas temperature control signal 28 is eventually selected as a low value in the low value selection circuit 19 instead of the load/speed control signal 24, and the gas turbine controller! 5 controls the fuel control valve 6 to maintain the gas turbine exhaust gas temperature TX at the set value of the exhaust gas temperature setting device 25. Gas turbine exhaust gas temperature setting device 25
The exhaust gas temperature set value TTREF given by is shown in FIG. 21. Curve 30 is the gas turbine exhaust gas temperature setpoint as a function of air compressor discharge air pressure PCD. This discharge air pressure PCD is obtained from the discharge air pressure detector 16 shown in FIG. A curve 31 shows the gas turbine exhaust gas temperature high alarm set value. FIG. 21 shows an attempt to maintain the gas turbine inlet gas temperature at the maximum allowable temperature of the gas turbine high temperature section material by operating the gas turbine exhaust gas temperature along the curve 30, and the curve slopes downward to the right. This means that the gas turbine exhaust gas temperature must be lowered in order to maintain a constant gas turbine inlet gas temperature because the gas turbine efficiency is high in the area where the gas turbine is located. In response to high gas turbine exhaust gas temperature, the gas turbine is protected by issuing a warning using curve 31 in FIG. 21 or causing the gas turbine to trip. In addition, variations in the gas turbine exhaust gas temperature are monitored, and even when the deviation between the maximum temperature and the minimum temperature exceeds a predetermined value, an alarm is issued or the gas turbine is tripped. This is because if there is a large variation in the gas temperature at the gas turbine inlet, thermal fatigue of the rotating rotor blades inside the gas turbine 9 will increase, and it will also cause gas turbine vibration, so the gas turbine is protected from these. In order to do this, the gas turbine was tripped.

Furthermore, if a predetermined number or more of the temperature detectors fail, the above-mentioned monitoring and normal gas turbine control cannot be performed, so the gas turbine has been tripped in order to protect the gas turbine. Approximately 1300 at the gas turbine inlet high temperature section
℃, high-temperature gas turbines with a temperature of approximately 600℃ at the exhaust section have been put into practical use, and the temperature detector is relatively prone to failure due to the high temperature, so technology that allows continued operation even if the temperature detector fails is needed.
This is required from the perspective of stabilizing the power supply.

(Problems to be Solved by the Invention) In the above-mentioned conventional technology, the gas temperature at the gas turbine inlet high temperature section is not directly measured, so the gas turbine inlet gas temperature cannot be accurately estimated only from the gas turbine exhaust gas temperature. In other words, in monitoring and controlling gas turbine exhaust gas temperature,
The gas temperature at the gas turbine inlet is higher than expected, exposing the high-temperature parts to harsh conditions, or conversely, the gas temperature at the gas turbine inlet is lower than expected, causing the gas turbine to operate at a low efficiency operating point. A situation arises. Furthermore, if the gas turbine exhaust gas temperature detector malfunctions, there is a time delay in detecting the malfunction, resulting in temperature variations. In such a case, it is not immediately clear whether the gas turbine inlet gas temperature is fluctuating or there is a failure in the gas turbine exhaust gas temperature detector, so in order to protect the gas turbine, it is not possible to cause the gas turbine to trip unnecessarily. things can happen. Such a situation is not preferable from the viewpoint of maintaining stability of power supply.

In view of the problems of the prior art as described above, the present invention provides a gas turbine exhaust gas temperature detector disposed annularly in the gas turbine exhaust section, as well as a gas turbine exhaust gas temperature detector disposed annularly in the high temperature section of the gas turbine inlet. The purpose of this invention is to provide the most efficient operation by providing a gas temperature detector and to accurately monitor combustion of the gas turbine based on the gas temperature at the gas turbine inlet.

Another purpose is to quickly detect abnormalities in the gas turbine exhaust gas temperature detector or the gas turbine inlet gas temperature detector.

Another purpose is to continue operation of the gas turbine by providing an estimated temperature in place of an abnormal gas turbine inlet gas temperature detector or an abnormal gas turbine exhaust gas temperature detector.

Another purpose is to show the relationship between the gas turbine inlet gas temperature and the gas turbine exhaust gas temperature so as to approximately match the gas flow path in which the gas rotates from the inlet to the exhaust section inside the gas turbine.

Another purpose is to provide an additional purpose of detecting abnormalities in the combustor.

Another purpose is to provide a sensor for gas turbine inlet gas temperature in cases where it is not possible to install a gas turbine inlet gas temperature detector at a predetermined location in the high temperature part of the gas turbine inlet due to the mechanical structure of the gas turbine.
The method is to estimate the gas temperature at the predetermined location.

Another purpose is to estimate the gas temperature at a predetermined location in the gas turbine exhaust section even when a gas turbine exhaust gas temperature sensor cannot be installed at a predetermined location in the gas turbine exhaust section due to the mechanical structure of the gas turbine. .

[Structure of the invention]

(Means for Solving the Problems) In order to achieve the above objectives, a gas turbine inlet gas temperature detector is arranged in an annular manner at the gas turbine inlet high temperature section, and a gas turbine exhaust gas temperature sensor is arranged at the gas turbine exhaust section as well. Temperature detectors are arranged in a ring. Then, a gas turbine inlet gas temperature detector and a gas turbine exhaust gas temperature detector are installed so that almost the same gas portion of the gas flow rotating around the gas turbine shaft from the gas turbine inlet toward the gas turbine exhaust can be monitored. Match. The temperatures of the associated gas turbine inlet gas temperature detector and gas turbine exhaust gas temperature detector are compared and detected, and an abnormality in the temperature detector is detected, and an estimated temperature value is generated in place of the abnormal temperature detector. give. Abnormalities in the combustor are detected based on the respective temperatures of the gas turbine inlet gas temperature detector and the gas turbine exhaust gas temperature detector.

It also includes zero or more means for estimating the gas temperature at a predetermined location of the gas turbine inlet high temperature section or the gas turbine exhaust section based on the temperatures of the gas turbine inlet gas temperature detector and the gas turbine exhaust gas temperature detector.

(Operation) The gas turbine inlet gas temperature is used to control the gas turbine inlet gas temperature, and at the same time, it is monitored to see if it exceeds the gas turbine inlet gas temperature high alarm limit value.

Also, it is monitored whether the magnitude of each variation (deviation) in the gas turbine inlet gas temperature exceeds an alarm limit value. If the shapes of the gas turbine inlet gas temperature distribution and the gas turbine exhaust gas temperature distribution do not match, it is determined that either the gas turbine inlet gas temperature detector or the gas turbine exhaust gas temperature detector in the portion where they do not match is abnormal. If one of the gas turbine inlet gas temperature detectors is determined to be abnormal, the abnormal gas turbine inlet gas temperature is detected from the temperature of the adjacent gas turbine inlet gas temperature detector and the temperature of the corresponding gas turbine exhaust gas temperature detector. Estimate the temperature of the vessel. If one of the gas turbine exhaust gas temperature detectors is determined to be abnormal, the temperature of the abnormal gas turbine exhaust gas temperature detector is determined from the temperature of the adjacent gas turbine exhaust gas temperature detector and the corresponding gas turbine inlet gas temperature detector. presume.

The temperature at a predetermined location in the gas turbine inlet high temperature section where the gas turbine inlet gas temperature detector is not installed corresponds to the temperature of the adjacent gas turbine inlet gas temperature detector, and the temperature at the above predetermined location and the adjacent gas turbine inlet gas temperature detector. Estimated from the temperature of the gas turbine exhaust gas temperature sensor.

In addition, the temperature of a predetermined part of the gas turbine exhaust part where the gas turbine exhaust gas temperature sensor is not installed is determined by the temperature of the adjacent gas turbine exhaust gas temperature detector, and the temperature of the gas turbine exhaust gas temperature detector corresponding to the predetermined part and the adjacent gas turbine exhaust gas temperature detector. Estimated from the temperature of the turbine inlet gas temperature sensor.

The gas turbine exhaust gas temperature is kept the same as before as a backup for continued operation in case the gas turbine inlet gas temperature detector fails in several places and it becomes difficult to monitor and control the gas turbine. It is possible to retain the functions of gas turbine exhaust gas temperature control, gas turbine exhaust gas temperature high alarm function, and function of monitoring the magnitude of variation (deviation) in gas turbine exhaust gas temperature.

In addition, if the shape of the distribution of the gas turbine inlet gas temperature and the gas turbine exhaust gas temperature is almost the same, but the temperature variation (deviation) is large, it may be due to clogging of the fuel burner inside the combustor or a problem (not shown) inside the combustor. It can be determined that there is an abnormality in the air conditioning system.

(Embodiment) FIG. 1 shows a system configuration diagram of an embodiment of the present invention. In FIG. 1, the same reference numerals as those in FIG. 18 indicate the same explanation as in FIG. 18. What is newly added in FIG. 1 is a gas turbine inlet gas temperature detector 32 disposed annularly in the gas turbine inlet high temperature section. The number of gas turbine inlet gas temperature detectors 32 is the first
Although three examples are shown in the figure for convenience, it is desirable to provide more.

In this embodiment, it is assumed that 12 gas turbine inlet gas temperature detectors and 12 gas turbine exhaust gas temperature detectors are each arranged in an annular shape at approximately equal intervals, and their structural positional relationship is shown in FIG. Figure 2 is a diagram looking from the gas turbine exhaust side to the gas turbine inlet side in the axial direction, with black circles TXI to T
X12 indicates the mounting position of the gas turbine exhaust gas temperature sensor and also indicates the value of each temperature. In addition, white circles 1 to 12 indicate that there are 12 combustors arranged in an annular shape as shown in the figure, and the same number of gas turbine inlet temperature detectors are installed at the inlet high temperature section where the combustion gas coming out of each combustor flows into the gas turbine. are arranged like black circles TYI to TY12. The temperature of the combustion gas exiting the combustor ■ is measured by the gas turbine inlet gas temperature sensor TYI at the gas turbine inlet, and the gas temperature inside the gas turbine is mixed slightly with the combustion gas from the adjacent combustor ■ and combustor O. As the rotor blades (not shown) are rotated, this gas itself rotates to some extent toward the gas turbine exhaust section and is discharged from the gas turbine as exhaust gas.As a result, the combustion gas that exits the combustor (■) performs work inside the gas turbine. After that, it is mainly discharged to the position of the gas turbine exhaust gas temperature detector TX3, and the exhaust gas temperature TX
It becomes exhaust gas of 3 and leaves the gas turbine. Similarly, the combustion gas exiting the combustor ■ is measured by the gas turbine inlet gas temperature sensor TY2 to have a gas turbine inlet gas temperature of TY2, and is slightly mixed with the combustion gas of the adjacent combustor and the combustor ■. Work is performed inside the gas turbine, and as a result, the gas is discharged to the position of the gas turbine exhaust gas temperature detector TX4, and exits the gas turbine as exhaust gas having the exhaust gas temperature TX4. The same applies to the combustion gases of other combustors.

The temperature signal of such a gas turbine inlet gas temperature sensor is used as follows. Figure 3 is the same as Figure 19 with the gas turbine inlet gas temperature control section added.
Components with the same reference numerals as those in the figure indicate the same as the description in FIG. 19. Gas turbine inlet gas temperature setter 33 provides a gas turbine inlet gas temperature set point. The gas turbine inlet gas temperature TY is determined by each temperature signal TYI-TY12 of the 12 gas turbine inlet gas temperature detectors as shown in FIG.
is the average value obtained through the average value calculation circuit 37.

Find the correct average value using each correct temperature signal,
It is important for gas turbine protection to use the average value as the gas turbine inlet gas temperature TY for control. Third
In the figure, the gas turbine inlet gas temperature setting value and the gas turbine inlet gas temperature TY are passed through an adder/subtractor 34 to obtain a temperature deviation, and the temperature deviation is passed to a proportional integral controller 35 to receive a gas turbine inlet log gas temperature control signal 36. is obtained. Since maintaining the gas turbine inlet gas temperature at the maximum allowable temperature of the gas turbine inlet hot section material is equivalent to maximizing gas turbine efficiency, the gas turbine inlet gas temperature control signal 36 is In terms of gas turbine efficiency, it is preferable to allow the gas to pass through preferentially and use the gas turbine exhaust gas temperature control signal 28 for backup. It' is the gas turbine inlet gas temperature sensor TYI
It is also possible to switch the control signal from the gas turbine inlet gas temperature control signal 36 to the gas turbine exhaust gas temperature control signal 28 depending on how many points of the TY12 are out of order, as shown in FIG. This is also possible by appropriately determining the values of the gas turbine exhaust gas temperature setpoint curve 30 shown. The gas turbine inlet gas temperature set point may be a constant value determined from the gas turbine inlet hot section material, as shown by straight line 38 in FIG.

Above this is an alarm setpoint 39 which, if exceeded, will cause an alarm or gas turbine trip. Further, the gas turbine inlet gas temperatures TYI to TY12 are used to monitor the combustion state as shown in FIG. In FIG. 6, the gas turbine inlet gas temperatures TYI to TY12 are passed through a maximum value selector 40 and a minimum value selector 41 to a maximum value TYMA.
X and the minimum value TYM I N are obtained, and both values are passed through a deviation calculator 42 to obtain a gas turbine inlet gas temperature deviation (dispersion) 43. This gas turbine inlet gas temperature deviation 43 is compared with an inlet gas temperature deviation tolerance 44 in a comparator 45, and the inlet gas temperature deviation 43 is compared with the tolerance 44.
If it exceeds the limit, an alarm or gas turbine trip command is output.

Also for gas turbine exhaust gas temperatures TXI to TX12,
In Figure 6, TYI~T, Y12 are TXI~TX1
2 and by providing an exhaust gas temperature deviation tolerance value in place of the inlet gas temperature deviation tolerance value 44, the temperature deviation in the gas turbine exhaust gas temperature can be monitored.

Next, a method for eliminating the possibility of a large temperature deviation due to failure of the gas temperature detector when the gas turbine inlet gas temperature deviation or the gas turbine exhaust gas temperature deviation exceeds a permissible value will be described. When a thermocouple is used as a temperature detector, if the thermocouple is disconnected, it is common to scale out to the up side or down side to eliminate the faulty thermocouple, but it is forced to scale out. Until the thermocouple disconnection is detected,
A conventional drawback is that the temperature is considered to be normal. FIG. 7 is a diagram for explaining the present invention in detail, showing a part of the gas turbine inlet gas temperature distribution and a part of the gas turbine exhaust gas temperature distribution. The horizontal axis shows the arrangement of the combustors, and as explained in Fig. 2, the combustors ■, ■,
(2) Each of the combustion gases exiting the gas turbine enters the gas turbine at an inlet gas temperature of TYI, TY2, . Obtained as TY3,
At each gas turbine exhaust section, the exhaust gas temperature TX3. T
X4. It shows that it can be obtained as TX5. An example is illustrated in which the gas turbine inlet gas temperature deviation exceeds the allowable value and the minimum temperature is TY2. As a simple example that can be intuitively understood, an example is shown in which TX3, TX4, and TX5 are lined up on a straight line. TX3 to TX5 are normal temperatures within which the gas turbine exhaust gas temperature deviation is within an allowable value. In this example, the estimated gas turbine inlet gas temperature may be considered to be TY2A. Therefore, in this case,
The inlet gas temperature deviation exceeds the allowable value, the inlet gas temperature TY2 is the maximum value or the minimum value, and the inlet gas temperature TY2 exceeds the predetermined range of the estimated temperature TY2A. It can be assumed that temperature sensor TY2 is faulty. The logic diagram is shown in the 8th
As shown in the figure.

In FIG. 7, when the values of exhaust gas temperatures TX3 and TX5 match, in order to obtain the estimated temperature TY2A, the adjacent gas temperature, that is, the gas turbine exhaust gas temperature TX6, and the gas turbine inlet gas temperature TY4 or the gas turbine exhaust gas temperature TX2. The estimated temperature TY2A can also be determined using the gas turbine inlet gas temperature TY12.

7 and 8, the gas turbine inlet gas temperature detector TY, 2 is detected to be abnormal, and the adjacent gas turbine inlet gas temperatures TYI and TY3, and the gas turbine exhaust gas temperature TX3. When the estimated temperature TY2A is obtained from TX4 and TX5 by interpolation, the gas turbine inlet gas temperature TY can be obtained more accurately as shown in FIG. FIG. 9 shows the gas turbine inlet gas temperature TY2 in FIG. 4 replaced with the estimated temperature TY2A.

Conversely, if the gas turbine exhaust gas temperature deviation exceeds the allowable value, the method explained in FIG. 7 is similarly applied to estimate the maximum or minimum value of the gas turbine exhaust gas temperature from the gas turbine inlet gas temperature. By comparing this with the estimated value, it is possible to determine whether or not there is a failure in the gas turbine exhaust gas temperature detector using a method similar to that shown in FIG. For example, gas turbine exhaust gas temperature TX4
When determining an abnormality, the gas turbine inlet gas temperature T
The estimated temperature TX4A of the exhaust gas temperature Tx4 is obtained from YI, TY2, and TY3, and the adjacent gas turbine exhaust gas temperatures TX3 and TX5, and can be determined using the logic diagram in FIG. 10. If this logic holds true, the estimated temperature TX4A can be used instead of the abnormal exhaust gas temperature TX4 to more accurately obtain the gas turbine exhaust gas temperature T)l as shown in FIG. Figure 11 is the second
The exhaust gas temperature TX4 in Figure 0 is replaced with the estimated temperature TX4A. Even in the event of a temperature sensor failure, the estimated temperature can be provided to ensure continued operation and normal control.

Next, another embodiment of the present invention is shown in FIG. FIG. 12 is a diagram in which the gas turbine inlet gas temperatures TYI to TY12 and the gas turbine exhaust gas temperatures TXI to TX12 are displayed on the display, and the gas temperatures are displayed so as to increase in the radial direction from the center. , each black circle indicates each gas temperature.

As explained in Fig. 2, the arrangement positional relationship of each gas temperature sensor in Fig. 2 is distinctive in that it is shown in correspondence with the gas flow path that is exhausted while rotating inside the gas turbine. . For example, the combustion gas exiting the combustor (1) exhibits an inlet gas temperature TYI at the gas turbine inlet, rotates to some extent within the gas turbine, and exhibits an exhaust gas temperature Tx3 at the exhaust section. In this way, the gas turbine inlet gas temperature sensor and the gas turbine exhaust gas temperature sensor are arranged so as to approximately match the gas flow that rotates around the gas turbine axis from the gas turbine inlet toward the gas turbine exhaust. By displaying each temperature while shifting the positional relationship, it can be confirmed that the shapes of the gas temperature distributions of the inlet gas temperature and the exhaust gas temperature match, which is excellent as a monitoring means. Instead of the annular display as shown in FIG. 12, a display arranged along the horizontal axis as shown in FIG. 7 may be used, and the effect will be the same.

Next, another embodiment of the present invention will be described using FIG. 12. In Figure 12, the inlet gas temperature TY6 and the exhaust gas temperature T
Both X8 are minimum values, and the shapes of the temperature distributions match.

Therefore, both temperature sensors can be considered normal. In this case, it can be assumed that the temperature of the combustion gas itself is low due to clogging of the fuel burner of the combustor (1) or an abnormality in the air conditioning system within the combustor. Abnormalities in the combustor in this case can be detected using the logic diagram shown in FIG.

Next, another embodiment of the present invention will be described using FIG. 14. FIG. 14 shows the gas turbine inlet gas temperature sensor TY2 in FIG. TY4. TY6゜TY8. TYIO,
This shows a case where TY12 cannot be installed due to the mechanical structure of the gas turbine. Depending on the structure of the gas turbine inlet high temperature section, it is not necessarily the case that as many gas turbine inlet gas temperature detectors as there are combustors are installed. In such a case, it is impossible to actually measure the gas flow flowing out from the combustor (1) at the gas turbine inlet high temperature section because there is no inlet gas temperature detector TY2. In such a case, the temperature can be estimated as follows. An example is shown in FIG. Let the estimated temperature be TYA. The gas flow of the combustor (2) exhibits a temperature TYI at the gas turbine inlet high temperature section and a temperature TX3 at the exhaust section. Similarly, the gas flows of combustor (1) show TY3 and TX5. Regarding the combustor (■), the temperature TX4 of the exhaust part is obtained. In this example, the estimated temperature TYA is obtained by the following equation.

In this way, even if there are restrictions on the installation of gas temperature detectors at the high temperature section at the gas turbine inlet, by appropriately increasing the number of temperature sensors installed at the exhaust section, it is possible to estimate the arbitrary gas temperature at the high temperature section at the gas turbine inlet. This makes it possible to improve the temperature monitoring performance of the inlet high temperature section. This estimated temperature is used for temperature monitoring shown in FIGS. 4 and 6.

Next, another embodiment of the present invention will be described using FIG. 16. FIG. 16 shows the gas turbine exhaust gas temperature detector TX2 in FIG. TX4. TX6. TX8, TXIO, T
This shows the case where XI2 is not installed. In such a case, the gas turbine exhaust temperature detectors TXI and T
Even if I wanted to actually measure the temperature between X3, I couldn't because no exhaust gas temperature detector was installed at that location. In such a case, the temperature can be estimated as follows, similar to the case in FIG. An example is shown in FIG. Let the estimated temperature be TXA. The gas flow of combustor 0 exhibits a temperature TYII at the gas turbine inlet hot section and a temperature TXI at the exhaust. Similarly, the gas flow of combustor σ) exhibits TYI and TX3. Regarding the combustor O, the temperature TY12 of the inlet high temperature section is obtained. In this example, the estimated temperature TXA
is obtained by the following formula.

In this way, even if there is a restriction in attaching a gas temperature detector to the gas turbine exhaust section, it is possible to estimate any gas temperature in the gas turbine exhaust section, and the temperature monitoring performance of the gas turbine exhaust section is improved.

〔Effect of the invention〕

Since the present invention is configured as described above, by using the gas turbine inlet gas temperature, it is possible to perform accurate combustion monitoring of the gas turbine while performing the most efficient operation. Further, an abnormality in the gas turbine exhaust gas temperature detector or the gas turbine inlet gas temperature detector can be detected early in the morning. In addition, since an estimated temperature can be provided in place of an abnormal gas temperature detector, accurate gas turbine exhaust gas temperature and accurate gas turbine inlet gas temperature can always be used for control and monitoring, allowing normal control and Continuation of operation can be achieved. Furthermore, since the temperature display is displayed so that the distribution of the gas turbine inlet gas temperature and the distribution of the gas turbine exhaust gas temperature correspond to the gas flow path, it can be confirmed that the temperature distribution shapes match. Additionally, as an additional effect, abnormalities in the combustor can be detected.

Furthermore, even in locations where a temperature detector cannot be attached, the estimated temperature of that location can be provided, thereby improving temperature monitoring performance.

[Brief explanation of drawings]

FIG. 1 is a system configuration diagram to which the present invention is applied, FIG. 2 is a layout diagram showing the positional relationship between the combustor and the temperature sensor in the present invention, and FIG. 3 is a control system diagram to which the present invention is applied. FIG. 4 is a logic diagram for calculating the gas temperature at the inlet of a gas turbine to which the present invention is applied, FIG. 5 is a diagram showing the gas turbine inlet gas temperature set value and alarm set value of the present invention, and FIG. 6 is a diagram showing the gas turbine inlet gas temperature set value and alarm set value of the gas turbine of the present invention. FIG. 7 is a logic diagram for monitoring the inlet gas temperature deviation; FIG. 7 is a diagram for explaining the estimated gas temperature value of the present invention; FIG. 8 is a logic diagram for detecting an abnormality in the gas turbine inlet gas temperature detector of the present invention; FIG. 9 The figure is a logic diagram for calculating the inlet gas temperature using the estimated inlet gas temperature value according to the present invention, FIG. 10 is a logic diagram for detecting an abnormality in the gas turbine exhaust gas temperature detector according to the present invention, and FIG. 11 is a logic diagram for calculating the inlet gas temperature using the inlet gas temperature estimation value according to the present invention. 12 is a diagram showing the distribution of the gas turbine inlet gas temperature and the gas turbine exhaust gas temperature of the present invention, and FIG. 13 is the combustor of the present invention. 14 is a diagram showing the positional relationship between the combustor and the temperature detector in the embodiment of the present invention, and FIG. 15 is a diagram illustrating the estimated gas temperature value in the embodiment of the present invention. Fig. 16 is a diagram showing the positional relationship between the combustor and the temperature detector in the embodiment of the present invention, Fig. 17 is a diagram illustrating the estimated gas temperature value in the embodiment of the invention, and Fig. 18 is the conventional system configuration. Fig. 19 is a conventional control system diagram, Fig. 20 is a logic diagram for calculating exhaust gas temperature, and Fig. 21 is a diagram giving a gas turbine exhaust gas temperature set value and alarm set value. l...Inlet air guide vane 2...Air compressor 4...Combustor 5...Gas turbine control device 6...Fuel control valve 8...Flame detector 9...Gas turbine 10... - Gas turbine shaft 11... Generator 12... Gas turbine exhaust section 13... Gas turbine exhaust gas temperature detector 15... Speed detector 16... Discharge air pressure detector 32... Gas turbine Inlet Gas Temperature Checker Agent Patent Attorney Rule Ken Yu Chika

Claims (9)

[Claims] (1) In a gas turbine control device that monitors combustion in a gas turbine plant consisting of an air compressor, a combustor, and a gas turbine, a gas turbine inlet gas temperature sensor and a gas turbine exhaust gas are arranged in a ring at the high temperature part of the gas turbine inlet. A gas turbine control device in which combustion is monitored by a gas turbine exhaust gas temperature detector disposed in an annular manner. (2) The gas turbine control device according to claim 1, wherein an abnormality in the gas turbine inlet gas temperature detector is detected based on the temperature of the gas turbine exhaust gas temperature detector. . (3) The gas turbine control device according to claim 1, wherein an abnormality in the gas turbine exhaust gas temperature detector is detected based on the temperature of the gas turbine inlet gas temperature detector. (4) In the gas turbine control device according to claim 2, the temperature of the gas turbine exhaust gas temperature detector and the temperature of the gas turbine inlet gas temperature detector adjacent to the abnormal gas turbine inlet gas temperature detector A gas turbine control device that estimates the temperature of an abnormal gas turbine inlet gas temperature detector based on the temperature of an abnormal gas turbine inlet gas temperature detector. (5) In the gas turbine control device according to claim 3, the temperature of the gas turbine inlet gas temperature detector and the temperature of the gas turbine exhaust gas temperature detector adjacent to the abnormal gas turbine exhaust gas temperature detector A gas turbine control device that estimates the temperature of an abnormal gas turbine exhaust gas temperature detector based on the temperature of an abnormal gas turbine exhaust gas temperature detector. (6) In the gas turbine control device according to claim 1, the gas turbine controller is configured such that the gas turbine A gas turbine control device that displays each temperature by shifting the arrangement positional relationship of an inlet gas temperature detector and a gas turbine exhaust gas temperature detector. (7) A gas turbine control device according to claim 1, which is configured to detect an abnormality in a combustor. (8) In the gas turbine control device according to claim 1, the gas temperature at a predetermined location of the gas turbine inlet high temperature section is determined by comparing the gas temperature of the gas turbine inlet gas temperature detector adjacent to the predetermined location with the gas turbine exhaust gas. A gas turbine control device that performs estimation based on the temperature of a temperature detector. (9) In the gas turbine control device according to claim 1, the gas temperature at a predetermined location in the gas turbine exhaust section is determined by the temperature of a gas turbine exhaust gas temperature detector adjacent to the predetermined location and the gas turbine inlet gas temperature. A gas turbine control device that performs estimation based on the temperature of a detector.