JPH08110050A - Gas turbine combustion monitor device - Google Patents

Abstract

PURPOSE: To secure a safety operation of a gas turbine and prevent a plurality of burners from being damaged by computing an excess temperature and outputting an excess temperature detection signal in an excess temperature combustion state when the exhaust temperature of either one of burners exceeds a specified setting value. CONSTITUTION: When a temperature signal A at an exhaust gas temperature detection point is determined to have exceeded a setting signal B by a comparison means 10, an ON signal is inputted into an on-delay timer 12. The on-delay timer 12 outputs an ON signal when the ON signal is inputted and maintained for a specified time, This ON signal is inputted into an OR operation means 13 where the OR of all the portions of gas temperature detection points are computed. As a result of the computation, when excess temperature combustion is generated even at a drum of a burner 1, a partial value of the exhaust air temperature equivalent to the position of the burner which has generated the excess temperature combustion rises so that the ON signal is outputted from the comparison means 10, if the operation continues for a few seconds as set to the on-delay timer 12, an excess temperature detection signal of the burner is outputted and the supply of fuel is halted, thereby bringing a gas turbine to a safety stop.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustion monitoring device provided for monitoring the combustion state of a gas turbine combustor in a power plant.

[0002]

2. Description of the Related Art A conventional gas turbine and combustor is shown in FIG.
This will be described with reference to the system diagram shown in FIG.

In the figure, air is taken in by an air compressor 1 and compressed into high pressure air. This compressed high-pressure air discharged from the air compressor enters the combustor 2 through the air passage (not shown) from the air holes 2a of the combustor 2 and is used for combustion of fuel. A plurality of combustors 2 are annularly arranged around the gas turbine shaft 3.
A stand is installed.

The fuel control valve 5 for supplying fuel to the combustor 2 is controlled by the gas turbine control device 4, and the fuel control valve 5
The fuel that has passed through is burned by being sent from the fuel burner 2b of each combustor 2 into the combustor.

The combustion gas of the combustor 2 is a combustor liner 2c.
From the turbine nozzle 2e to the gas turbine 6 via the transition piece 2d. This high-temperature high-pressure gas is injected into the gas turbine 6 to rotate the gas turbine shaft 3, and the coaxial air compressor 1 and the generator 7 rotate.

As the fuel control valve 5 is opened by the control of the gas turbine controller 4 and the amount of fuel is increased, the speed of the gas turbine shaft directly coupled to the shaft is increased. When the shaft speed reaches the rated speed, the generator 7 is inserted in the power system.

The generator 7 is inserted into the electric power system and starts sending the generator output to the electric power system. After that, as the fuel amount increases, the generator output and the gas turbine exhaust gas temperature increase.

The gas working in the gas turbine 6 is discharged from the gas turbine exhaust section 8 to the atmosphere. A plurality of temperature detectors 9 are annularly arranged in the gas turbine exhaust unit 8 so that the temperature of the exhaust gas can be measured, and the temperature detectors 9 are connected to the gas turbine combustion monitoring device 50. This temperature detector 9
Thermocouples are commonly used for high temperature detection.

In order to monitor the combustion of the combustor 2, it is more accurate to detect the gas temperature at the outlet of the combustor 2 or the inlet of the gas turbine 6, but the gas at the combustor outlet and the gas turbine inlet is detected. Since the temperature is high, the thermocouple is easily broken and reliability is reduced, which is not practical. Therefore, generally, the exhaust gas temperature of the gas turbine exhaust portion 8 is detected.

Although the combustion gas of each combustor 2 is mixed to some extent in the combustion gas turbine that exits from another combustor 2, the temperature distribution at the gas turbine inlet remains up to the gas turbine outlet, so Combustion monitoring is possible by measuring the exhaust gas temperature of the turbine 6.

Next, conventional combustion monitoring will be described.

When one can of the combustor 2 is misfired or incompletely combusted, the temperature of the gas flowing out from the combustor 2 decreases. The combustion gas whose temperature has dropped due to the misfire or incomplete combustion reaches the gas turbine outlet, so that the exhaust gas temperature of the combustion gas flow decreases, and the temperature detection installed near the center of the gas flow. The exhaust gas temperature of the container 9 decreases. The number of temperature detectors 9 differs depending on the number of combustors and the degree of demand for combustion monitoring.

For example, as shown in FIG. 13, when the temperature is detected at 24 points, which is approximately twice as large as that of the 14 cans of the combustor, the temperature drops at a few places.

When the conventional combustion monitoring device detects such a partial temperature decrease of the exhaust gas temperature of the annular gas turbine, the combustor 1 can is judged to be misfired or incompletely burned, and the fuel supply is stopped to stop the gas turbine. Is configured so that it can be safely stopped.

The gas turbine combustion monitor 50 is shown in FIG.
All the detection signals from the exhaust gas temperature detectors 9 which are annularly arranged in the gas turbine exhaust part 8 shown in FIG. 13 as shown in FIG. It is detected that the inlet temperature is close to the limit temperature of the gas turbine moving blade, and the detection signal is used to stop the fuel supply to safely stop the gas turbine.

This prevents the gas turbine and the moving blades from being damaged by overtemperature. Since the gas turbine rotor blade is rotating, combustion gas is sequentially supplied from a plurality of combustors, and thus the average value or intermediate value of all the exhaust gas temperature points is used as described above.

As described above, in the conventional gas turbine, the monitoring of each combustor is intended only for misfire or incomplete combustion, and the monitoring for over temperature is not performed. Overtemperature protection was only for gas turbine blades. The reason for this is that the combustor and the system of fuel and air supplied to the combustor are simple, and there is a low possibility that only one combustor can rise in temperature.

However, in recent years, there has been an increasing demand for consideration of the environment of the gas turbine exhaust gas, that is, reduction of NOx, and in response to this, improved combustors have been developed. Along with this, the combustor structure, the fuel supply system for supplying the combustor, and the compressed air supply system have become complicated.

As a concrete example, in order to combine the diffusion combustion and the premixed combustion, the fuel line is made multi-tube to control the flow rate of the fuel according to each combustion, and the fuel burner is divided for each combustion system. Yes, it also controls the air flow rate of each combustor.

Further complication such as controlling the fuel flow rate of each combustor is easily expected in the future. Therefore, as the NOx reduction progresses, the possibility that the fuel supply system and the air supply system become abnormal increases.

[0021]

However, although the combustor structure has become complicated as described above in recent years, the conventional gas turbine combustion monitoring device 50 cannot monitor the overtemperature of each combustor 2. However, there is a problem that the safety of the combustor 2 is lacking and the life of the device is shortened.

Since the combustion temperature of the combustor is determined by the ratio of the fuel amount to the air amount, when the fuel amount in one can of the combustor increases or the air amount decreases, only one can of combustor burns as compared with other combustors. The temperature will rise.

The situation where the fuel amount increases by one can occurs due to an abnormality in the drive mechanism of the flow rate control valve or an abnormality in the control valve opening command of the control device when the fuel flow rate control of each combustor is performed. In addition, the situation where the air volume decreases by one can
This occurs due to clogging of the air holes 2a of the combustor, an abnormality in the drive mechanism of the flow rate control valve or an abnormality in the control valve opening command of the control device when the air flow rate control of each combustor is performed.

For example, when the combustion temperature of the combustor becomes abnormally high, the combustor liner 2c and the transition piece 2d
Will burn out. Further, the turbine nozzle 2e on the downstream side of the combustor
Is burned out due to a rise in metal temperature. Further, even when the above-mentioned burnout does not occur, the life of the combustor parts is shortened and the replacement time is expedited.

In such a case, since the conventional gas turbine combustion monitoring device 50 monitors using an intermediate value or an average value of all points of the exhaust gas temperature, a partial overtemperature rise cannot be detected.

Therefore, there is a problem in that the overheat combustion of the gas turbine combustor cannot be detected only by the conventional combustion monitoring and overtemperature protection, and the gas turbine cannot be safely operated / stopped.

The present invention has been made to solve the above problems, and an object thereof is to detect overtemperature combustion of a gas turbine combustor to protect the combustor and safely shut down the gas turbine. An object of the present invention is to provide a gas turbine combustion monitoring device capable of performing the above.

[0028]

According to a first aspect of the present invention, a plurality of combustors arranged annularly around a gas turbine shaft to generate high temperature and high pressure gas by combustion of compressed air and fuel,
It has a gas turbine that rotates in conjunction with the gas turbine shaft by the high-temperature and high-pressure gas from these combustors, and detects the temperature of each exhaust gas with multiple temperature detectors arranged annularly on the outlet side of this gas turbine. In a gas turbine combustion monitoring device that monitors the combustion state of each combustor, an overtemperature combustion state calculation unit that calculates and outputs an overtemperature detection signal as an overtemperature combustion state when any of the exhaust gas temperatures is equal to or higher than a predetermined set value. It is provided.

According to a second aspect of the present invention, in the gas turbine combustion monitoring apparatus according to the first aspect, the overtemperature combustion state calculation unit is detected by at least two adjacent temperature detectors with respect to the temperature detector. When all the exhaust gas temperatures are equal to or higher than a predetermined value, an overtemperature detection signal is output as an overtemperature combustion state.

According to a third aspect of the present invention, a plurality of combustors arranged annularly around the gas turbine shaft to generate high temperature and high pressure gas by combustion of compressed air and fuel, and high temperature and high pressure gas from these combustors. Has a gas turbine that rotates in tandem with the gas turbine shaft, and the temperature of each exhaust gas is detected by a plurality of temperature detectors arranged annularly on the outlet side of this gas turbine to monitor the combustion state of each combustor. In the gas turbine combustion monitoring device, when the temperature of the high value becomes a predetermined value or more among the exhaust gas temperatures detected by at least two adjacent temperature detectors with respect to each temperature detector, an overtemperature combustion state is detected. An over temperature combustion state calculation unit for calculating and outputting a temperature detection signal is provided.

According to a fourth aspect of the present invention, a plurality of combustors arranged annularly around the gas turbine shaft to generate high temperature and high pressure gas by combustion of compressed air and fuel, and high temperature and high pressure gas from these combustors. Has a gas turbine that rotates in tandem with the gas turbine shaft, and the temperature of each exhaust gas is detected by a plurality of temperature detectors arranged annularly on the outlet side of this gas turbine to monitor the combustion state of each combustor. In the gas turbine combustion monitoring device, when the maximum temperature value in each exhaust gas temperature is equal to or higher than a predetermined set value, an over temperature detection calculation unit that outputs a first ON signal and adjacent detection corresponding to the detection point of the maximum temperature value Of the adjacent detection point temperature state calculation unit that outputs a second ON signal when the respective temperature deviation values of the exhaust gas temperature and the maximum temperature value due to the points are equal to or less than a predetermined set value, and the first ON signal and the second ON signal It is obtained as provided with overtemperature condition calculation unit for outputting an over temperature detection signal by a force as over-temperature combustion state.

According to a fifth aspect of the present invention, in the gas turbine combustion monitoring apparatus according to the fourth aspect, the second ON signal is output when the temperature detectors at adjacent detection points are broken.

[0033]

According to the first aspect of the present invention, the overtemperature detection signal is output when any of the exhaust gas temperatures by the temperature detector arranged on the gas turbine outlet side is equal to or higher than a predetermined setting.
As a result, an increase in the fuel flow rate or a decrease in the air flow rate occurs in any of the plurality of combustors, an abnormal increase in the combustion temperature of the combustor is detected, and the gas turbine is safely stopped. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

According to the second aspect of the present invention, the at least two temperature detectors arranged adjacently output the overtemperature detection signal when the exhaust gas temperature is equal to or higher than the predetermined set value. As a result, when a plurality of temperature detectors are provided for each combustor, an overtemperature signal that is reliable and has few errors is output because the overtemperature state is determined based on the abnormalities of a plurality of exhaust gas temperatures. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and
The life of the combustor components can be extended.

According to the third aspect of the present invention, when the exhaust gas temperature of the high value among the exhaust gas temperatures by the temperature detectors arranged adjacent to each other is equal to or higher than a predetermined set value, the overtemperature detection signal is arithmetically output. As a result, when a plurality of exhaust gas temperatures detected by the temperature detectors arranged adjacent to each combustor alternately increase or decrease with time,
An overtemperature state is detected without delay from the exhaust gas temperature at which any one of them has reached a high value. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

According to the invention of claim 4, the maximum value of the exhaust gas temperature is a predetermined value or more, and the deviation between the exhaust gas temperature at the detection point adjacent to the detection point of the maximum exhaust gas temperature and the maximum value of the exhaust gas temperature. Is less than or equal to a predetermined value, an overtemperature signal is calculated and output as an overtemperature state. As a result, when a relatively large number of temperature detectors are arranged for each combustor, the exhaust gas temperature of all the temperature detectors also rises, so that an accurate overheating signal with few errors can be output. Therefore, the safe operation of the gas turbine is secured, burnout of the combustor is prevented,
Moreover, the life of the combustor parts can be extended.

According to the fifth aspect of the present invention, when the temperature detectors at the adjacent detection points are broken, the second ON signal is output and the overtemperature detection signal is arithmetically output. As a result, the over temperature detection signal is output instead of the malfunction of the second ON signal caused by the disconnection of the temperature detector. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

[0038]

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows a first embodiment of the present invention, in which a gas turbine combustion monitoring device 51 includes an overtemperature combustion state calculation unit 5
2, the overtemperature combustion state calculator 52 is composed of a plurality of comparing means 10, a function generating means 11, an on-delay timer 12, and a logical sum calculating means 13.

Here, the comparing means 10 compares the temperature signal A at the exhaust gas temperature detection point with a predetermined setting signal B from the function generating means 11 which will be described later, and the temperature signal A at the exhaust gas temperature detection point is the setting signal. When larger than B, the ON signal is output to the on-delay timer 12.

The function generating means 11 inputs the air compressor discharge pressure signal and outputs a setting signal B by a predetermined function calculation. The on-delay timer 12 is turned off from the comparison means 10.
When the N signal is input and the ON signal is input for a predetermined time, the ON signal is output.

The logical sum calculation means 13 outputs an overtemperature detection signal when an ON signal is input from any of the on-delay timers 12.

With the above configuration, the temperature signal A at the exhaust gas temperature detection point is input to each comparison means 10 provided for the number of detection points, while the detection value of the air compressor discharge pressure signal is input to the function generation means 11. The setting signal B obtained by
Both are compared.

When the comparison by the comparing means 10 determines that the temperature signal A exceeds the setting signal B, the ON signal is input to the on-delay timer 12. The on-delay timer 12 outputs O when the ON signal is maintained for a predetermined time.
An N signal is output. This ON signal is the logical sum operation means 1
3 is input, the logical sum calculation means 13 calculates the logical sum of all the exhaust gas temperature detection points.

As a result, when the over-temperature combustion occurs even in one can of the combustor, the value of a part of the exhaust gas temperature corresponding to the position of the combustor where the over-temperature combustion occurs increases, and the ON signal from the comparison means 10 is sent. After being output and continuing for several seconds set in the on-delay timer 12, an overtemperature detection signal of the combustor is output.

When this signal is output to the gas turbine controller, the fuel supply is stopped by the system (not shown) and the gas turbine is stopped safely.

As shown in FIG. 2, it may be added to the condition that the exhaust gas temperature average value is equal to or higher than a predetermined value.
This prevents erroneous detection, limits the detection range, and enables reliable overtemperature detection.

That is, the exhaust gas temperature average value abnormality detection unit 5
3 and the over temperature detection calculation unit 54 may be additionally provided.

With this configuration, the comparing means 15 determines whether or not the average value of all the exhaust gas temperature points obtained by the average value calculating means (not shown) exceeds the value set by the setting means 14. Then, the logical product of the ON signal of the comparison means 15 and the ON signal of the logical sum calculation means 13 is the overtemperature detection calculation part 5
4 is obtained by the logical product calculation means 16.

AND operation means 1 of the over temperature detection operation section 54
In 6, when the output of the logical sum calculation means 13 is an ON signal and the comparison means 15 is outputting an ON signal, an overtemperature detection signal is output.

When the above phenomenon occurs, the temperature of the gas turbine exhaust gas detected by the temperature detector 9 arranged annularly as described in FIG. 12 rises as shown in FIG. In this figure, the exhaust gas temperature detectors 9 arranged on the circumference of the gas turbine exhaust part 8 are shown so as to have the same arrangement as seen from the gas turbine side, and each detector from the zero point position in the figure is shown. The angle is always constant, and the length from the zero point changes depending on the temperature.

Therefore, the temperature becomes long and the temperature becomes low, and the temperature becomes short. Therefore, it can be seen that the detection point (4) in FIG. 3 has a high temperature since the length from the zero point is long.

Thus, the gas turbine combustion monitoring device 5
In No. 1, when the fuel flow rate in the can of the combustor 1 increases or the air flow rate decreases, and when the combustion temperature of the combustor 2 reaches a high temperature close to the limit temperature of the combustor, a part of the exhaust gas temperature exceeds a predetermined temperature. As a result, the above phenomenon can be detected, the fuel supply can be stopped, and the gas turbine can be safely stopped.

In this case, since the equivalent value of the gas turbine inlet temperature can be calculated from the exhaust gas temperature, the air compressor discharge pressure equivalent signal and the turbine efficiency, the function setting curve of the air compressor discharge pressure equivalent signal taking turbine efficiency into consideration is used as a function. It is set in the generating means 11.

The time setting of the on-delay timer 12 is set in accordance with the characteristics of the combustor and the gas turbine. Further, the air compressor discharge pressure may be an air compressor outlet / inlet pressure ratio.

Further, since the temperature detection value is lowered when the temperature detecting thermocouple is broken or the temperature input circuit is broken, the temperature rise is not erroneously detected.

FIG. 4 shows another embodiment of the invention of FIG.

The gas turbine combustion monitoring device 55 has a logical product calculating means 17 added between the comparing means 10 and the on-delay timer 12, and inputs the output of the adjacent comparator 10 to the logical product calculating means 17. It is configured to perform a logical product operation.

Further, as shown in FIG. 5, an air compressor discharge pressure abnormality detection unit 57 and an over temperature detection calculation unit 58 are added to FIG. 4 to prevent erroneous detection used in the air compressor discharge pressure abnormality detection unit 57. The air compressor discharge pressure may be used for the detection range limited signal.

This embodiment is effective when the number of exhaust gas temperature detection points is relatively large for several combustors, and can be adopted when a partial temperature rise of the annular exhaust gas temperature can be detected at two or more points. .

Also in this embodiment, as in the first embodiment shown in FIG. 1, in the gas turbine combustion monitoring device 55, the fuel amount in one can of the combustor increases or the air flow rate decreases.
When the combustion temperature of the combustor 2 reaches a high temperature close to the limit temperature of the combustor, the above phenomenon is detected because a part of the exhaust gas temperature exceeds a predetermined temperature, and the fuel supply is stopped to secure the gas turbine. You can stop at.

When the number of exhaust gas temperature detection points is particularly large compared to several combustors, the logical product calculating means 17 is set to 3
Signals adjacent to each other at points or more may be used.

Further, when the logical product calculating means 17 is provided, the thermocouple for detecting the exhaust gas temperature may be broken and the temperature detection value may remain low. In consideration of such a situation, the temperature detector in which the thermocouple is disconnected is always output an ON signal to the AND operation means 17, and the overtemperature is detected only by the ON signal of the other comparison means 10. You may

FIG. 6 is a block diagram of a gas turbine combustion monitoring apparatus showing a second embodiment of the present invention.

The gas turbine combustion monitoring device 59 comprises an overtemperature combustion state calculation unit 60, and the overtemperature combustion state calculation unit 60.
Are a plurality of high price selection means 20, a comparison means 21, a function generation means 22, an on-delay timer 23, and a logical sum operation means 2.
It consists of 4.

Here, the high value selecting means 20 inputs the temperature signals of the exhaust gas temperature detection points adjacent to each other and outputs the temperature signal A of either high value. The comparison means 21
The temperature signal A of the high value selection means 20 is compared with a setting signal B described later, and when the temperature signal A is larger than the setting signal B, an ON signal is output.

The function generating means 22 processes the air compressor discharge pressure signal with a predetermined function and outputs the setting signal B. The on-delay timer 23 outputs an ON signal when the ON signal is input for a predetermined time. OR operation means 24
Outputs an ON signal when any input is an ON signal.

With the above structure, when the overheated combustion occurs in one can of the combustor, the value of the exhaust gas temperature of a part corresponding to the position of the combustor where the overheated combustion occurs increases. Therefore, the exhaust gas temperature detection point signal of the corresponding portion rises and is input to the high price selection means 20.

The elevated temperature of the exhaust gas temperature detection point signal is selected from the high price selection means 20 and input to the comparison means 21. As a result, the comparison unit 21 outputs an ON signal. ON
The on-delay timer 23, to which the signal is input, outputs an ON signal to the OR operation means 24 after continuing for a set several seconds, and the ON signal is output as an overtemperature detection signal.

FIG. 7 shows a situation in which the exhaust gas temperature of the adjacent temperature detectors 9 alternately rises when the above phenomenon occurs. As shown in the figure, the value of the exhaust gas temperature at the detection point X may fluctuate vertically with time, and accordingly, the exhaust gas temperature may fluctuate alternately with time at the detection point Y as well. At this time, it is considered that the fluctuation becomes particularly large in the vicinity of the temperature rise. In this case, the first
Although the detection may be delayed only by the detection of the embodiment, the overtemperature can be detected quickly by the embodiment.

In this way, since the high value selecting means 20 outputs the higher one of the two points in the input signal, when the exhaust gas temperature fluctuates, it is possible to detect overtemperature combustion without delaying the detection operation. is there.

For example, if the high price selection means 20 is not provided,
When the exhaust gas temperature fluctuates, it is considered that the temperature value decreases before the on-delay timer 23 operates, the output of the comparison means 21 becomes an OFF signal, and the overtemperature cannot be detected. Further, the overtemperature rises. On delay timer 23
Will not be detected until the situation in which is activated deteriorates. Therefore, it is effective for a gas turbine in which fluctuations in exhaust gas temperature are relatively large.

Since the magnitude of this temperature fluctuation varies depending on the characteristics of the gas turbine, the combustor, the exhaust portion, etc., it is necessary to select a detection method according to the characteristics.

A combustion switching completion signal input section 61 and an overtemperature signal output section 62 may be added to FIG. 6 as shown in FIG.

As shown in FIG. 8, if the combustion switching completion signal is input to the logical product calculating means 25, the possibility of over temperature combustion of the combustor increases after completion of combustion switching, so that the over temperature is surely achieved. Can be detected.

When the number of temperature detection points is relatively large,
You may input the adjacent temperature value of the high value selection means 20 into three or more points. It should be noted that the present embodiment also has an advantage that when one of the temperature detection signals input to the high price selection means 20 is disconnected, the monitoring can be continued with the other temperature detection signal.

FIG. 9 is a block diagram of a gas turbine combustion monitoring apparatus showing a third embodiment of the present invention.

The gas turbine combustion monitoring device 63 comprises an exhaust gas temperature abnormality calculating section 64, an adjacent detection point temperature state calculating section 65 and an over temperature state calculating section 66.

Here, the exhaust gas temperature abnormality calculating section 64 comprises a high value selecting means 30, a comparing means 31, and a function generating means 32. The high value selection means 30 inputs the temperature signals of the n exhaust gas temperature detection points and outputs the temperature signal A corresponding to the highest value.

The comparing means 31 compares the temperature signal A with the setting signal B of the function generating means 32, which will be described later, and outputs an ON signal when the temperature signal A is larger than the setting signal B. The function generating means 32 inputs the air compressor discharge pressure signal and outputs the setting signal B according to a predetermined function.

The adjacent detection point temperature state calculation unit 65 is composed of subtraction means 34a and 34b and comparison means 35a and 35b.

The subtracting means 34a outputs the temperature signal A (defined as the detection point X) output from the high value selecting means 30 and the detection point (X-
The temperature signal C of 1) is input and the temperature signal C is subtracted from the temperature signal A. The subtraction means 34b inputs the temperature signal A and the temperature signal D at the detection point (X + 1) and subtracts the temperature signal D from the temperature signal A.

The comparing means 35a and 35b compare the input values with preset values, and output an ON signal when the input values are low. The OR operation unit 36 outputs an ON signal when any of the ON signals is input.

The over-temperature state calculating section 66 comprises a logical product calculating means 33 and an on-delay timer 37.

The logical product calculating means 33 is 0N of the comparing means 31.
The ON signal is output to the on-delay timer 37 when the logical product of the signal and the ON signal of the logical sum calculation means 36 is established.
When the ON signal is input, the on-delay timer 37 outputs an overtemperature detection signal after a predetermined time.

With the above configuration, the temperature signals of all the exhaust gas temperature detection points are input to the high value selecting means 30, and the output high temperature temperature signal A is input to the comparing means 31.

The setting signal B obtained by inputting the air compressor discharge pressure signal to the function generating means 32 is the comparing means 3.
At 1, the temperature signal A is compared, and when the high temperature signal A exceeds the setting signal B, the comparison means 31 outputs an ON signal to the AND operation means 33.

On the other hand, the maximum temperature signal A is detected by the high value selecting means 30, and at the same time, the detection point number (X) of the high temperature value is searched by the searching means (not shown). As a result, (X-1) and (X +) adjacent to this detection point (X)
1) That is, the exhaust gas temperature signal of the detection point number obtained by subtracting 1 from the detection point number and the detection point number obtained by adding 1 is the subtraction means 3
4a and 34b, respectively. Then, the adjacent temperature signals C and D are subtracted from the high-value temperature signal A, and are input to the comparison means 35a and 35b, respectively.

The comparing means 35a and 35b are the subtracting means 34.
When the respective inputs from a and 34b are lower than a preset value, an ON signal is output to the logical sum calculation means 36.

In the OR operation means 36, the comparison means 35
The logical sum of the outputs of a and 35b is calculated, and the result is output to the logical product calculating means 33. The logical product calculating means 33
The logical product of the comparison means 31 and the logical sum calculation means 36 is calculated and the result is output to the on-delay timer 37, and the output is used as the overtemperature detection signal of the combustor 2. The temperature detection point numbers are given in the order of circumference as shown in FIG.

In this way, when the fuel flow rate in the one can of the combustor increases or the air flow rate decreases, and the combustion temperature of the combustor reaches a high temperature close to the limit temperature of the combustor, the exhaust gas temperature detection point Detect the above phenomenon when the maximum value is above the specified value and the temperature adjacent to the maximum temperature and the maximum temperature detection point is below the specified value, and stop the fuel supply and stop the gas turbine safely. You can In this method, the detection method is elaborate, erroneous detection is prevented, and abnormal detection is performed quickly.

FIG. 10 shows the structure of another embodiment of the third embodiment shown in FIG.

In the embodiment shown in FIG. 10, the OR operation means 36a is added to the gas turbine combustion monitoring device 65A so that the temperature detector 9 at the (X-1) detection point adjacent to the maximum temperature value is disconnected. The signal that has been detected and the comparison means 35a
The output signal of is input to the logical sum calculation means 36a, and the output is output to the logical product calculation means 33.

Further, by adding a logical sum calculating means 36b, a signal which detects that the detection point of (X + 1) adjacent to the maximum temperature value (X) is broken and the output signal of the comparing means 35b is a logical sum calculating means. 36b, and outputs the output to the logical product calculating means 33.

In this embodiment, since the over temperature combustion is detected by both operations of the comparison means 35a and 35b, the maximum temperature detection point (X) is adjacent to the over temperature combustion of one combustor. It can be adopted when the temperature values of (X-1) and (X + 1) are certainly close to the maximum temperature value.

Further, even when the thermocouple for detecting the exhaust gas temperature is disconnected and the detected temperature value is still falling, the outputs of the comparison means 35a, 35b are always ON during the disconnection detection.
Since the signal is output, the overtemperature can be detected by the operation of only one of the comparison means 35a and 35b.

FIG. 11 shows the structure of another embodiment of the third embodiment shown in FIG.

In this embodiment, the subtraction means 34c, 34d
And the comparison means 35c and 35d are added to form a gas turbine combustion monitoring device 65B, and the temperature values of the highest temperature detection point (X) and the second adjacent (X-2) and (X + 2) detection points are input. The temperature value is detected to be close to the maximum temperature value.

The outputs of the comparing means 35a and 35b are directly input to the logical product calculating means 33, and the outputs of the comparing means 35c and 35d are input to the logical product calculating means 33 through the logical sum calculating means 36. It is configured.

This embodiment is effective when the number of exhaust gas temperature detection points is relatively large with respect to the number of combustors.
When the over-temperature combustion of the stand occurs, the temperature values of (X-1) and (X + 1) adjacent to the maximum temperature detection point (X) are definitely close to the maximum temperature value and the second adjacent (X- It can be adopted when the temperature values of 2) and (X + 2) are close to either or both of the maximum temperature values.

The set values of the comparing means 35c and 35d are set to values larger than those of the comparing means 35a and 35b. That is, it operates even if the degree of approach is low. The combination of the set value of the adjacent signal and the logical sum / logical product is selected based on the characteristics of the combustor, the turbine, and the like.

The present invention can also be implemented by appropriately selecting and combining the components of the embodiments shown in FIGS. 1, 2, 4, 5, 6, and 8 to 11. . This combination may be adopted in accordance with the characteristics of the combustor, the gas turbine, the gas turbine exhaust part, and the like.

[0103]

As described above, according to the first aspect of the invention, the overtemperature detection signal is output when any of the exhaust gas temperatures by the temperature detector arranged on the gas turbine outlet side is equal to or higher than a predetermined setting. Therefore, it is detected that the combustion temperature of the combustor has risen abnormally partially, and the gas turbine is stopped safely. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

According to the second aspect of the present invention, when a plurality of temperature detectors are provided for each combustor, the overtemperature state is judged by the abnormality of a plurality of exhaust gas temperatures, which is reliable and has few errors. An over temperature detection signal is output. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

According to the third aspect of the invention, when the plurality of exhaust gas temperatures detected by the temperature detectors arranged adjacent to each combustor alternately rise or fall with time, It is possible to detect an overtemperature condition without delay from the exhaust gas temperature that has reached a high value. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

According to the fourth aspect of the present invention, when a relatively large number of temperature detectors are arranged for each combustor, the exhaust gas temperature due to the temperature detectors also rises as a whole, so that the temperature is accurate and has a low error rate. A detection signal can be output. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

According to the fifth aspect of the present invention, the over temperature detection signal is output instead of the malfunction of the second ON signal caused by the disconnection of the temperature detector. Therefore, safe operation of the gas turbine is ensured, burnout of the combustor is prevented, and the life of the combustor parts can be extended.

[Brief description of drawings]

FIG. 1 is a configuration diagram of a gas turbine combustion monitoring device showing a first embodiment of the present invention.

FIG. 2 is a configuration diagram of a gas turbine combustion monitoring device showing another embodiment of FIG.

FIG. 3 is an explanatory view showing the operation of FIG.

FIG. 4 is a configuration diagram of a gas turbine combustion monitoring device showing another embodiment of FIG.

5 is a configuration diagram of a gas turbine combustion monitoring device showing another embodiment of FIG.

FIG. 6 is a configuration diagram of a gas turbine combustion monitoring device showing a second embodiment of the present invention.

FIG. 7 is an explanatory diagram showing the operation of FIG.

8 is a configuration diagram of a gas turbine combustion monitoring device showing another embodiment of FIG.

FIG. 9 is a configuration diagram of a gas turbine combustion monitoring device showing a third embodiment of the present invention.

FIG. 10 is a configuration diagram of a gas turbine combustion monitoring device showing another embodiment of FIG. 9.

11 is a configuration diagram of a gas turbine combustion monitoring device showing another embodiment of FIG.

FIG. 12 is a system diagram of a gas turbine including a conventional gas turbine combustion monitoring device.

FIG. 13 is an explanatory diagram showing the arrangement of temperature detectors.

[Explanation of symbols]

 1 Air Compressor 2 Combustor 4 Gas Turbine Control Device 6 Gas Turbine 8 Gas Turbine Exhaust Section 9 Temperature Detector 10, 15, 21, 32 Comparing Means 11, 22, 32 Function Generating Means 12, 23, 37 On-delay Timer 13 , 24, 36, 36a, 36b OR operation means 14 Setting means 16, 17, 25, 33 AND operation means 20, 30 High value selection means 34a, 34b Subtraction means 50, 51, 55, 59 Gas turbine combustion monitoring device 52 , 60 Over temperature combustion state calculation unit 53 Exhaust gas temperature average value abnormality detection unit 54, 58 Over temperature detection calculation unit 57 Air compressor discharge pressure abnormality detection unit 61 Combustion switching completion signal input unit 62 Over temperature signal output unit 64 Exhaust gas temperature abnormality Calculation unit 65 Adjacent detection point temperature state calculation unit 66 Over temperature state calculation unit

Claims (5)

[Claims] 1. A plurality of combustors arranged annularly around a gas turbine shaft to generate high temperature and high pressure gas by combustion of compressed air and fuel, and the gas turbine shaft by the high temperature and high pressure gas from these combustors. Gas turbine combustion that has a gas turbine that rotates in conjunction with the gas turbine, and that detects the temperature of each exhaust gas by a plurality of temperature detectors that are annularly arranged on the outlet side of the gas turbine to monitor the combustion state of each combustor In the monitoring device, a gas turbine combustion monitoring device comprising an overtemperature combustion state calculation unit that outputs an overtemperature detection signal as an overtemperature combustion state when any of the exhaust gas temperatures is equal to or higher than a predetermined set value. . 2. The over temperature combustion state calculation unit determines that the over temperature combustion state is an over temperature combustion state when the exhaust gas temperatures detected by at least two temperature detectors adjacent to the temperature detector are both above a predetermined value. The gas turbine combustion monitoring device according to claim 1, wherein a temperature detection signal is output. 3. A plurality of combustors arranged annularly around a gas turbine shaft to generate high temperature and high pressure gas by combustion of compressed air and fuel, and the gas turbine shaft by the high temperature and high pressure gas from these combustors. Gas turbine combustion that has a gas turbine that rotates in conjunction with the gas turbine, and that detects the temperature of each exhaust gas by a plurality of temperature detectors that are annularly arranged on the outlet side of the gas turbine to monitor the combustion state of each combustor In the monitoring device, when the temperature of a high value becomes a predetermined value or more among exhaust gas temperatures detected by at least two adjacent temperature detectors with respect to each of the temperature detectors, an overtemperature detection is performed as an overtemperature combustion state. A gas turbine combustion monitoring device, comprising: an overtemperature combustion state calculation unit for calculating and outputting a signal. 4. A plurality of combustors arranged annularly around a gas turbine shaft to generate high temperature and high pressure gas by combustion of compressed air and fuel, and the gas turbine shaft by the high temperature and high pressure gas from these combustors. Gas turbine combustion that has a gas turbine that rotates in conjunction with the gas turbine, and that detects the temperature of each exhaust gas by a plurality of temperature detectors that are annularly arranged on the outlet side of the gas turbine to monitor the combustion state of each combustor In the monitoring device, when the maximum temperature value in each exhaust gas temperature is equal to or higher than a predetermined set value, an overtemperature detection calculation unit that outputs a first ON signal, and an adjacent detection point corresponding to the detection point of the maximum temperature value The adjacent detection point temperature state calculation unit that outputs a second ON signal when the respective temperature deviation values between the exhaust gas temperature and the maximum temperature value due to the above are less than or equal to a predetermined set value, the first ON signal and the second A gas turbine combustion monitoring device, comprising: an overtemperature state calculation unit that outputs an overtemperature detection signal as an overtemperature combustion state by inputting an ON signal. 5. The gas turbine combustion monitoring device according to claim 4, wherein the second ON signal is output when the temperature detectors at the adjacent detection points are disconnected.