JP3086695B2 - Gas turbine control device - Google Patents

Description

The present invention relates to a gas turbine control device for monitoring and controlling a gas turbine plant in a power plant such as a combined cycle power plant.

(Prior Art) FIG. 18 shows a system configuration diagram of a conventional gas turbine plant. In FIG. 18, the air taken in through the inlet air guide vanes 1 is compressed by the air compressor 2 into high-pressure air. The high-pressure air discharged from the air compressor passes through an air passage (not shown), enters the combustor 4 from the combustor air hole 3, and is used as fuel combustion air. Although there are a plurality of combustors 4, for convenience, FIG. 18 shows two combustors.

The fuel control valve 6 is controlled by a command from the gas turbine controller 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 burns. The combustion flame is detected by a flame detector 8 as to whether it is in an ignition state or a misfire state. The combustion gas of the combustor 4 is sent to a gas turbine 9 through a gas passage (not shown). Since the high-pressure high-temperature gas rotates the gas turbine shaft 10 in the gas turbine 9, the coaxial air compressor 2 and the generator 11 rotate. The gas that has worked in the gas turbine 9 is the gas turbine exhaust 12
From the waste heat recovery boiler (not shown). The gas turbine exhaust section 12 is provided with a gas turbine exhaust gas temperature detector 13. Although only three detectors are shown for convenience, more detectors are typically 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 includes a speed detector 15 mounted near the gas turbine shaft end gear 14.
, The discharge signal obtained from the air compressor discharge air pressure detector 16, the ignition signal obtained from the flame detector 8,
Based on the gas turbine exhaust gas temperature detector 13 and the like, the angle of the inlet air guide blades 1 of the air compressor 2 is controlled to adjust the air amount, and the fuel control valve 6 is opened. It controls the fuel amount by controlling the degree.

Figure 1 shows a conventional control system diagram for a gas turbine controller.
As shown in FIG. In FIG. 19, when the gas turbine is started, the start control signal 18 of the start control unit 17 is selected by the low value selection circuit 19, and the fuel control valve 6 of FIG.
Is controlled. The activation control unit 17 performs the ignition operation,
The opening of the fuel control valve 6 is maintained at a predetermined ignition opening. When the fuel is ignited by a spark plug (not shown), the flame detector 8 detects that a flame has been established. When the flame is established, warm-up is performed, the start control signal 18 is gradually increased, 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 setting unit 21 is provided with a rated speed set value at the time of startup.
The adder / subtracter 22 calculates a deviation between the rated speed set value and the gas turbine speed N, and multiplies the speed deviation by the proportional controller 23 to obtain a load / speed control signal 24. When the gas turbine speed N reaches near the rated speed, the load / speed control signal 24 becomes a low value in the low value selection circuit 19 instead of the start control signal 18 and is selected. After the gas turbine shaft 10 is maintained at the rated speed, the generator 11 is connected to the power system. After insertion, the gas turbine speed is synchronized with the system frequency, and the rated speed is maintained. In order to increase the generator output, the value of the load / speed setting unit 21 is increased by a generator load control circuit (not shown), the opening of the fuel control valve 6 increases, and the fuel amount gradually increases. At this time, the angle of the inlet air guide blade 1 is also increased by a circuit (not shown), and when it reaches the maximum angle, the air amount becomes maximum there.
Gas turbine exhaust gas temperature detector with increasing fuel quantity
The temperature TX of 13 increases. Gas turbine exhaust gas temperature TX
Obtained from Figure 20. FIG. 20 shows a case in which the number of the gas turbine exhaust gas temperature detectors 13 is n. The average value calculation circuit 29 selects an average value of each of the n gas temperatures, and sets the average value as the gas turbine exhaust gas temperature TX. A deviation between the exhaust gas temperature set value of the exhaust gas temperature setter 25 and the exhaust gas temperature TX is calculated by an adder / subtractor 26, and the temperature deviation is passed through a proportional integral controller 27 to generate a gas turbine exhaust gas temperature control signal 28. When the air amount becomes maximum and the fuel amount further increases, the gas turbine exhaust gas temperature control signal 28 is shortly selected by the low value selection circuit 19 instead of the load / speed control signal 24, and the gas turbine control device 5 The fuel control valve 6 is controlled so as to maintain the gas turbine exhaust gas temperature TX at the set value of the exhaust gas temperature setter 25. As the exhaust gas temperature set value TTREF given by the gas turbine exhaust gas temperature setter 25, the one shown in FIG. 21 is used.
Curve 30 is the gas turbine exhaust gas temperature set point and is obtained as a function of air compressor discharge air pressure PCD. This discharge air pressure PCD is obtained from the discharge air pressure detector 16 in FIG. Curve 31 shows the gas turbine exhaust gas temperature high alarm set value. FIG. 21 attempts to maintain the gas turbine inlet gas temperature at the maximum allowable temperature of the gas turbine hot section material by operating the gas turbine exhaust gas temperature along the curve 30. Since the gas turbine efficiency is high in some parts, it means that the gas turbine exhaust gas temperature must be lowered in order to maintain the gas turbine inlet gas temperature constant. When the gas turbine exhaust gas temperature is high, a warning is issued by the curve 31 in FIG. 21 or the gas turbine is tripped to protect the gas turbine. Further, variations in the exhaust gas temperature of the gas turbine are monitored, and 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 the temperature variation of the gas temperature at the gas turbine inlet is large, the thermal fatigue of the rotating blades inside the gas turbine 9 increases,
Gas turbines are tripped to protect the gas turbine from these because it causes vibration of the gas turbine. Further, when a predetermined number or more of the temperature detectors fail, the above-described monitoring and normal gas turbine control cannot be performed, so that the gas turbine is tripped for the purpose of protecting the gas turbine. A high-temperature gas turbine with a temperature of about 1300 ° C at the gas turbine inlet high temperature section and a temperature of about 600 ° C at the exhaust section has been put into practical use. A technology that can achieve the above is required from the viewpoint of stabilizing the power supply.

(Problems to be Solved by the Invention) In the above conventional technology, the gas temperature at the gas turbine inlet high temperature portion is not directly measured, so that 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 by gas turbine exhaust gas temperature, the gas turbine inlet gas temperature is higher than expected and the high temperature part is exposed to severe conditions, or conversely, the gas turbine inlet gas temperature is lower than expected, There are cases where the operation is performed at an operation point where the gas turbine efficiency is low. Further, when the gas turbine exhaust gas temperature detector fails, there is a time delay in the detection of the failure, which appears as a temperature variation.
In such a case, it is not immediately known whether the gas temperature at the gas turbine inlet is fluctuating or the gas turbine exhaust gas temperature detector is malfunctioning. Can occur. This is not preferable from the viewpoint of maintaining stable power supply.

In view of the above-mentioned problems of the prior art, the present invention provides a gas turbine exhaust gas temperature detector annularly disposed at a gas turbine exhaust part, and a gas turbine inlet gas temperature annularly disposed at a gas turbine inlet high temperature part. An object of the present invention is to provide the detector with the detector to perform the most efficient operation and to accurately monitor the combustion of the gas turbine by the gas temperature at the gas turbine inlet.

Another object is to quickly detect an abnormality in the gas turbine exhaust gas temperature detector or the gas turbine inlet gas temperature detector.

Another object is to continue operation of the gas turbine by giving an estimated temperature instead of an abnormal gas turbine inlet gas temperature detector or an abnormal gas turbine exhaust gas temperature detector.

Another object is to show the relationship between the gas temperature at the gas turbine inlet and the gas exhaust gas temperature so as to substantially match the gas flow path in which the gas rotates from the inlet to the exhaust portion inside the gas turbine.

Another object is to provide an additional purpose of detecting an abnormality of the combustor.

Another object is to estimate the gas temperature of the gas turbine inlet gas temperature detector even when the gas turbine inlet gas temperature detector cannot be installed at the gas turbine inlet high temperature part predetermined position due to the mechanical structure of the gas turbine. It is.

Another object is to estimate the gas temperature at a predetermined location even when a gas turbine exhaust gas temperature detector cannot be attached to a predetermined location of the gas turbine exhaust section due to the mechanical structure of the gas turbine. .

[Configuration of the invention]

(Means for Solving the Problems) In order to achieve the above object, a gas turbine inlet gas temperature detector is annularly disposed at a gas turbine inlet high temperature part, and a gas turbine exhaust gas is also provided at a gas turbine exhaust part. The temperature detector is arranged in a ring. A gas turbine inlet gas temperature detector and a gas turbine exhaust gas temperature detector are supported so that almost the same gas portion of the gas flow that rotates from the gas turbine inlet toward the gas turbine exhaust around the gas turbine shaft can be monitored. Attach. The temperature of the corresponding gas turbine inlet gas temperature detector and the temperature of the gas turbine exhaust gas temperature detector are compared and compared with each other to detect abnormalities in the temperature detector, and to estimate the temperature in place of the abnormal temperature detector. give. An abnormality of the combustor is detected based on each temperature of the gas turbine inlet gas temperature detector and the gas turbine exhaust gas temperature detector.

Further, the gas temperature at a predetermined portion of the gas turbine inlet high temperature portion or the gas turbine exhaust portion is estimated based on the temperatures of the gas turbine inlet gas temperature detector and the gas turbine exhaust gas temperature detector. The above means are provided.

(Operation) The gas turbine inlet gas temperature is used for gas turbine inlet gas temperature control, and at the same time, it is monitored whether the gas turbine inlet gas temperature high alarm limit value is exceeded.

Also, it is monitored whether the magnitude of each variation (deviation) of the gas temperature at the gas turbine inlet does not exceed the alarm limit value. If the distribution of the gas turbine inlet gas temperature does not match the distribution of the gas turbine exhaust gas temperature, it is determined that either the gas turbine inlet gas temperature detector or the gas turbine exhaust gas temperature detector at the mismatched portion is abnormal. If one of the gas turbine inlet gas temperature detectors is determined to be abnormal, an 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 vessel temperature. When 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 gas turbine exhaust gas temperature detector adjacent thereto and the corresponding gas turbine inlet gas temperature detector. presume.

Corresponds to the temperature of the gas turbine inlet high temperature section where the gas turbine inlet gas temperature detector is not attached, the temperature of the gas turbine inlet gas temperature detector adjacent to it, and the above-mentioned predetermined location and the adjacent gas turbine inlet gas temperature detector. From the temperature of the gas turbine exhaust gas temperature detector.

In addition, the temperature of the gas turbine exhaust portion at a predetermined location where the gas turbine exhaust gas temperature detector is not attached, the temperature of the gas turbine exhaust gas temperature detector adjacent thereto, and the gas corresponding to the predetermined location and the adjacent gas turbine exhaust gas temperature detector. It is estimated from the temperature of the turbine inlet gas temperature detector.

The gas turbine exhaust gas temperature is the same as the conventional one for backup purposes in order to continue operation, considering that it is difficult to monitor and control the gas turbine due to some failures at the gas turbine inlet gas temperature detector. It is possible to leave the function of controlling the temperature of the exhaust gas of the gas turbine, the function of warning the temperature of the exhaust gas of the gas turbine high, and the function of monitoring the magnitude of the variation (deviation) of the temperature of the exhaust gas of the gas turbine.

In addition, when the distribution of the gas turbine inlet gas temperature and the gas turbine exhaust gas temperature distribution substantially match, but the temperature variation (deviation) is large, clogging of the fuel burner inside the fuel unit or unillustrated inside the fuel unit. It can be determined that the air conditioning system is abnormal.

(Embodiment) FIG. 1 shows a system configuration diagram of an embodiment of the present invention.
In FIG. 1, the same components as those in FIG. 18 indicate the same components as those described in FIG. In FIG. 1, what is newly added is a gas turbine inlet gas temperature detector 32 which is annularly disposed at the gas turbine inlet high temperature portion.
Although the number of gas temperature detectors 32 at the gas turbine inlet is three in FIG. 1 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 annularly arranged at substantially equal intervals, and the structural positional relationship is shown in FIG. FIG. 2 is a view of the gas turbine inlet side viewed from the gas turbine exhaust side in the axial direction.
Indicates the mounting position of the gas turbine exhaust gas temperature detector and the value of each temperature. The white circles 1 to 12 have 12 combustors.
As shown in the figure, the same number of gas turbine inlet temperature detectors are provided at black inlet TY1 to TY12 at the inlet high temperature section where the combustion gas exiting from each combustor flows into the gas turbine.
It is arranged as follows. The gas temperature of the combustion gas exiting the combustor is measured at the gas turbine inlet by the gas temperature sensor TY1 at the gas turbine inlet, and the gas (not shown) inside the gas turbine is slightly mixed with the combustion gas of the adjacent combustor and the combustor. While rotating the blades, this gas itself is discharged from the gas turbine as exhaust gas while rotating to some extent toward the gas turbine exhaust, and as a result, the combustion gas exiting the combustor works inside the gas turbine, It is mainly discharged to the position of the turbine exhaust gas temperature detector TX3, and exits the gas turbine as exhaust gas at the exhaust gas temperature TX3. Similarly, the combustion gas exiting the combustor is measured by the gas turbine inlet gas temperature detector TY2 as having a gas turbine inlet gas temperature of TY2, and is slightly mixed with the adjacent combustor and the combustion gas of the combustor, and the gas inside the gas turbine is detected. As a result, the exhaust gas is discharged to the position of the gas turbine exhaust gas temperature detector TX4, and the exhaust gas exits the gas turbine at the exhaust gas temperature TX4. The same applies to the combustion gas of other combustors.

The temperature signal of such a gas temperature sensor at the inlet of the gas turbine is used as follows. FIG. 3 is obtained by adding a gas temperature control unit at the gas turbine inlet in FIG. 19, and those having the same reference numerals as those in FIG. 19 are the same as those in FIG. The gas turbine inlet gas temperature setter 33 provides a gas turbine inlet gas temperature set value. As shown in FIG. 4, the gas temperature TY of the gas turbine inlet gas is calculated by averaging the temperature signals TY1 to TY12 of the twelve gas turbine inlet gas temperature detectors.
Average value obtained through 7. It is important to protect the gas turbine that a correct average value is obtained using each correct temperature signal and that the average value is used as a gas turbine inlet gas temperature TY for control. In FIG. 3, the gas turbine inlet gas temperature set value and the gas turbine inlet gas temperature TY are passed through an adder / subtractor 34 to determine a temperature deviation, and the temperature deviation is passed through a proportional integral controller 35 to control the gas turbine inlet gas temperature control. A 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 It is preferable from the viewpoint of gas turbine efficiency that the gas is passed through preferentially and the gas turbine exhaust gas temperature control signal 28 is used for backup. This is achieved by switching the control signal from the gas turbine inlet gas temperature control signal 36 to the gas turbine exhaust gas temperature control signal 28 when some of the gas turbine inlet gas temperature detectors TY1 to TY12 fail. It is also possible, or by appropriately determining the value of the curve 30 of the gas turbine exhaust gas temperature set value shown in FIG. The gas turbine inlet gas temperature set value may be a constant value determined by the gas turbine inlet high temperature portion material as shown by the straight line 38 in FIG. An alarm set value 39 is provided thereon, and when this value is exceeded, an alarm or a gas turbine trip is performed. The gas temperatures TY1 to TY12 at the gas turbine inlet are used for monitoring the combustion state as shown in FIG. In FIG. 6, the gas temperature TY1 to TY12 at the gas turbine inlet is passed through a maximum value selector 40 and a minimum value selector 41 to obtain a maximum value TYMAX and a minimum value TYMIN, and both values are passed through a deviation calculator 42. The gas turbine inlet gas temperature deviation (variation) 43 is obtained. This gas turbine inlet gas temperature deviation 43 is obtained by comparing the allowable value 44 of the inlet gas temperature deviation with the comparator 45.
When the inlet gas temperature deviation 43 exceeds the allowable value 44, an alarm or a gas turbine trip command is output.

For the gas turbine exhaust gas temperatures TX1 to TX12, the sixth
In the figure, while replacing TY1 to TY12 with TX1 to TY12,
By giving the exhaust gas temperature deviation allowable value instead of the inlet gas temperature deviation allowable 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 a failure of the gas temperature detector when the gas turbine inlet gas temperature deviation or the gas turbine exhaust gas temperature deviation exceeds an allowable value will be described. When a thermocouple is used as a temperature detector, if the thermocouple breaks, it is common practice to scale out to the up or down side to eliminate the faulty thermocouple, but forcibly scale out For this reason, there is a conventional defect that the temperature is regarded as a normal temperature before the disconnection of the thermocouple is detected. FIG. 7 is a diagram for explaining an embodiment of the present invention, in which a part of a gas turbine inlet gas temperature distribution and a part of a gas turbine exhaust gas temperature distribution are shown. The horizontal axis shows the arrangement of the combustors. As described in FIG. 2, each of the combustion gases exiting the combustors is obtained at the gas turbine inlet as inlet gas temperatures TY1, TY2, and TY3, respectively. In the exhaust gas temperature TX3, TX4, TX5
Is obtained as Now, the gas turbine inlet gas temperature deviation exceeds the allowable value and the minimum temperature is TY2
The example in the case of having been shown is shown. As a simple example that can be understood intuitively, the example in which TX3, TX4, and TX5 are arranged in a straight line is shown. TX3 to TX5 are normal temperatures where the gas turbine exhaust gas temperature deviation is within an allowable value. In this example, the estimate of the gas turbine inlet gas temperature may be considered to be TY2A.
Therefore, in this case, the inlet gas temperature deviation exceeds the allowable value, and the inlet gas temperature TY2 is the maximum value or the minimum value, and the inlet gas temperature TY2 further exceeds the predetermined range of the estimated temperature TY2A. Inlet gas temperature detector
TY2 can be considered as a failure. The logic diagram is shown in FIG.

In FIG. 7, when the values of the 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 obtained by using the gas turbine inlet gas temperature TY12.

7 and 8, the gas turbine inlet gas temperature detector TY2 is detected as abnormal, and the adjacent gas turbine inlet gas temperatures TY1 and TY3, and the gas turbine exhaust gas temperature TX3,
When the estimated temperature TY2A is obtained from TX4 and TX5 by an interpolation method, the gas temperature TY at the gas turbine inlet can be obtained more accurately as shown in FIG. FIG. 9 is obtained by replacing the gas turbine inlet gas temperature TY2 in FIG. 4 with the estimated temperature TY2A.

Conversely, when the gas turbine exhaust gas temperature deviation exceeds the allowable value, the method described in FIG. 7 is similarly applied, and the maximum value or the minimum value of the gas turbine exhaust gas temperature is estimated from the gas turbine inlet gas temperature. In this way, by comparing the estimated value with the estimated value, the presence or absence of a failure of the gas turbine exhaust gas temperature detector can be determined by a method similar to that shown in FIG. For example, gas turbine exhaust gas temperature TX4
Gas turbine inlet gas temperature TY
1, TY2 and TY3 and adjacent gas turbine exhaust gas temperature
Obtain the estimated temperature TX4A of the exhaust gas temperature TX4 from TX3 and TX5,
This can be determined by the logic diagram in FIG. When this logic is established, the gas turbine exhaust gas temperature TX can be obtained more accurately as shown in FIG. 11 by using the estimated temperature TX4A instead of the abnormal exhaust gas temperature TX4. FIG. 11 shows the estimated exhaust gas temperature TX4 in FIG.
Replaced with X4A. Even when the temperature detector fails, the estimated temperature is given so that the operation can be continued and normal control can be achieved.

Next, another embodiment of the present invention is shown in FIG. No.
FIG. 12 is a diagram in which the gas temperatures at the gas turbine inlet gas temperatures TY1 to TY12 and the gas turbine exhaust gas temperatures TX1 to TX12 are displayed on a display, and the gas temperature is displayed so as to increase in the radial direction from the center. Each black circle indicates each gas temperature. As shown in FIG. 2, the arrangement of each gas temperature detector in FIG. 2 is characterized in that it is associated with a gas flow path that is exhausted while rotating inside the gas turbine. . For example, the combustion gas exiting the combustor exhibits an inlet gas temperature TY1 at the gas turbine inlet, the gas rotates to some extent inside the gas turbine, and the exhaust gas exhibits an exhaust gas temperature TX3. In this way, the gas turbine inlet gas temperature detector and the gas turbine exhaust gas temperature detector are arranged so as to substantially match the gas flow rotating from the gas turbine inlet toward the gas turbine exhaust around the gas turbine shaft. By displaying each temperature with the positional relationship shifted, it is possible to confirm that the shapes of the gas temperature distributions of the inlet gas temperature and the exhaust gas temperature match, which is excellent as 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 adopted. The effect is equivalent.

Next, another embodiment of the present invention will be described with reference to FIG. In FIG. 12, the inlet gas temperature TY6 and the exhaust gas temperature TX8 are both minimum values, and the shapes of the temperature distributions match. Therefore, both temperature detectors can be considered normal. In this case, it can be considered that the temperature of the combustion gas itself is low due to clogging of the fuel burner of the combustor or abnormality of the air conditioning system in the combustor. The abnormality of the combustor in this case can be detected by the logic diagram of FIG.

Next, another embodiment of the present invention will be described with reference to FIG. FIG. 14 shows a case where the gas temperature detectors TY2, TY4, TY6, TY8, TY10, and TY12 at the gas turbine inlet in FIG. 2 cannot be mounted due to the mechanical structure of the gas turbine. Depending on the structure of the gas turbine inlet high temperature section, the gas turbine inlet gas temperature detectors are not always installed by the number of combustors. In such a case, it is impossible to actually measure the gas flow flowing out of the combustor at the gas turbine inlet high-temperature portion because the inlet gas temperature detector TY2 is not provided. 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 indicates the temperature TY1 at the gas turbine inlet high temperature section and TX3 at the exhaust section. Similarly, the combustor gas flows indicate TY3 and TX5. For the combustor, the temperature TX4 of the exhaust section is obtained. In this example, the estimated temperature TYA is obtained by the following equation.

As described above, even if there is a restriction on the installation of the gas temperature detector at the gas turbine inlet high temperature part, it is possible to estimate an arbitrary gas temperature at the gas turbine inlet high temperature part by appropriately increasing the number of temperature detectors mounted at the exhaust part. And the temperature monitoring performance of the inlet high-temperature portion is improved. This estimated temperature is shown in FIG.
Used for temperature monitoring shown in FIG.

Next, another embodiment of the present invention will be described with reference to FIG. FIG. 16 shows a case where the gas turbine exhaust gas temperature detectors TX2, TX4, TX6, TX8, TX10 and TX12 in FIG. 2 are not mounted. In such a case, it is impossible to actually measure the temperature between the temperature detectors TX1 and TX3 of the gas turbine exhaust part because the exhaust gas temperature detector is not mounted at that position. In such a case, the temperature can be estimated as follows, as in the case of FIG. An example is shown in FIG. Let the estimated temperature be TXA. The gas flow of the combustor shows the temperature TY11 at the gas turbine inlet high temperature section,
TX1 is shown in the exhaust part. Similarly, the combustor gas flows indicate TY1 and TX3. For the combustor, the temperature T at the inlet hot section
Y12 has been obtained. In this example, the estimated temperature TXA is obtained by the following equation.

As described above, even if there is a restriction on the attachment of the gas temperature detector to the gas turbine exhaust part, it is possible to estimate an arbitrary gas temperature of the gas turbine exhaust part, and the temperature monitoring performance of the gas turbine exhaust part is improved.

〔The invention's effect〕

Since the present invention is configured as described above, it is possible to detect an abnormality of the gas turbine exhaust gas temperature detector, the gas turbine inlet gas temperature detector or the combustor at an early stage. In addition, since the estimated temperature can be given instead of the abnormal gas temperature detector, the accurate gas turbine exhaust gas temperature and the accurate gas turbine inlet gas temperature can be used for control and monitoring at all times. Operation continuation can be realized. In addition, since the temperature display indicates that the gas turbine inlet gas temperature distribution and the gas turbine exhaust gas temperature distribution correspond to the gas flow paths, it is possible to confirm that the temperature distribution shapes match. Further, an abnormality of the combustor can be detected as an additional effect.

Furthermore, the temperature monitoring performance is improved because the estimated temperature at the location where the temperature detector cannot be attached can be given.

[Brief description of the drawings]

FIG. 1 is a system configuration diagram to which the present invention is applied, FIG. 2 is a layout diagram showing a positional relationship between a combustor and a temperature detector in the present invention, 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 gas turbine inlet to which the present invention is applied, FIG. 5 is a diagram showing the gas turbine inlet gas temperature set value and the alarm set value of the present invention, and FIG. FIG. 7 is a diagram for explaining an estimated gas temperature value of the present invention, FIG. 8 is a logic diagram for detecting an abnormality of a gas turbine inlet gas temperature detector of the present invention, FIG. FIG. 10 is a logic diagram for calculating the inlet gas temperature using the estimated value of the inlet gas temperature of the present invention, FIG. 10 is a logic diagram for detecting an abnormality of the gas turbine exhaust gas temperature detector of the present invention, and FIG. 11 is the present invention. Exhaust gas temperature using the estimated exhaust gas temperature FIG. 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, FIG. 13 is a logic diagram for detecting an abnormality of the combustor of the present invention, and FIG. FIG. 15 is a diagram showing a positional relationship between a combustor and a temperature detector in the embodiment of the present invention. FIG. 15 is a diagram for explaining an estimated gas temperature value in the embodiment of the present invention.
FIG. 1 is a diagram showing a positional relationship between a combustor and a temperature detector in an embodiment of the present invention, FIG. 17 is a diagram for explaining gas temperature estimation values in an embodiment of the present invention, FIG. 18 is a conventional system configuration diagram, FIG. 19 is a conventional control system diagram, FIG. 20 is a logic diagram for calculating the exhaust gas temperature, and FIG. 21 is a diagram for giving a gas turbine exhaust gas temperature set value and an alarm set value. DESCRIPTION OF SYMBOLS 1 ... Inlet air guide blade 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 13… Gas turbine exhaust gas temperature detector 15… Speed detector 16… Discharge air pressure detector 32… Gas turbine inlet gas temperature detector

────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Kazuki Ono 1 Toshiba-cho, Fuchu-shi, Tokyo Inside the Toshiba Fuchu factory (56) References JP-A-2-64232 (JP, A) JP-A-59- 68527 (JP, A) Japanese Utility Model Showa 60-183236 (JP, U) Japanese Patent Publication No. 57-38768 (JP, B2) C. Delbec, C.I. V. Dohner, L .; C. Angello, "Advanced Diagnost ic Instrumentation for Combustion Tu rbines", American P ower Conference, 1986 years ('86 -4-15), p228-234 (58 ) investigated the field (Int.Cl. ^7, DB name) F02C 9 / 00 F23N 5/02 345 JICST file (JOIS)

Claims (7)

(57) [Claims] 1. A gas turbine control device for controlling combustion of a gas turbine plant including an air compressor, a combustor, and a gas turbine, wherein the gas turbine control device is provided in a ring shape at a high temperature portion of an inlet of the gas turbine. A plurality of gas turbine inlet gas temperature detectors for detecting, a plurality of gas turbine exhaust gas temperature detectors disposed annularly in an exhaust portion of the gas turbine, and detecting a gas turbine exhaust gas temperature, and the plurality of gas turbine inlet gas First determining means for determining whether a gas turbine inlet gas temperature deviation of a temperature detected by a temperature detector is equal to or more than an allowable value, and detecting a corresponding gas turbine inlet gas temperature detecting a maximum value or a minimum value of the temperature; Gas turbine based on the temperature of the gas turbine inlet gas temperature detector adjacent to the gas turbine inlet gas temperature detector. Second estimating means for estimating an estimated temperature of the gas inlet gas temperature detector, and judging whether or not the estimated temperature and the detected temperature of the gas turbine inlet gas temperature detector are equal to or higher than a predetermined value;
And a detecting means for detecting as a failure the gas temperature detector at the gas turbine inlet which detected the maximum value or the minimum value when both of the determination conditions of the second determination means are satisfied. apparatus. 2. A gas turbine control device for controlling the combustion of a gas turbine plant comprising an air compressor, a combustor and a gas turbine, wherein the gas turbine control device is disposed annularly at a high temperature portion of an inlet of the gas turbine, and controls a gas temperature at the gas turbine inlet. A plurality of gas turbine inlet gas temperature detectors for detecting, a plurality of gas turbine exhaust gas temperature detectors disposed annularly in an exhaust portion of the gas turbine to detect a gas turbine exhaust gas temperature, and the plurality of gas turbine exhaust gas temperatures A first method for determining whether or not the gas turbine exhaust gas temperature deviation of the temperature detected by the detector is equal to or greater than an allowable value
Determining means for detecting the maximum value or the minimum value of the temperature and detecting the gas turbine exhaust gas temperature based on the temperature of the gas turbine exhaust gas temperature detector adjacent to the gas turbine exhaust gas temperature detector. Determining means for estimating the estimated temperature of the gas turbine exhaust gas temperature detector and determining whether or not the estimated temperature and the detected temperature of the gas turbine exhaust gas temperature detector are equal to or higher than a predetermined value; and the determination of the first and second determining means. A gas turbine control device comprising: a detection unit that detects, when both conditions are satisfied, a gas turbine exhaust gas temperature detector that detects a maximum value or a minimum value as a failure. 3. A gas turbine control device for controlling combustion of a gas turbine plant including an air compressor, a combustor, and a gas turbine, wherein the gas turbine control device is disposed annularly at a high temperature portion of an inlet of the gas turbine, and controls a gas temperature at a gas turbine inlet. A plurality of gas turbine inlet gas temperature detectors to be detected, a plurality of gas turbine exhaust gas temperature detectors disposed annularly in an exhaust portion of the gas turbine, and detecting a gas turbine exhaust gas temperature, and a gas turbine exhaust gas temperature detector. An abnormality of the gas turbine inlet gas temperature detector is detected based on the temperature, and 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 are detected. Gas turbine control device for estimating the temperature of an abnormal gas turbine inlet gas temperature detector . 4. A gas turbine control device for performing combustion control of a gas turbine plant comprising an air compressor, a combustor and a gas turbine, wherein the gas turbine control device is provided in a ring shape at an inlet high-temperature portion of the gas turbine and controls a gas temperature at the gas turbine inlet. A plurality of gas turbine inlet gas temperature detectors for detecting, a plurality of gas turbine exhaust gas temperature detectors annularly disposed in an exhaust portion of the gas turbine to detect a gas turbine exhaust gas temperature, and a gas turbine inlet gas temperature detector Detecting the abnormality of the gas turbine exhaust gas temperature detector based on the temperature of the gas turbine exhaust 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 configured to estimate the temperature of an abnormal gas turbine exhaust gas temperature detector. 5. A gas turbine control device for performing combustion control of a gas turbine plant comprising an air compressor, a combustor, and a gas turbine, wherein the gas turbine control device is disposed annularly at a high temperature portion at an inlet of the gas turbine, and controls a gas temperature at the gas turbine inlet. A plurality of gas turbine inlet gas temperature detectors for detecting, and a plurality of gas turbine exhaust gas temperature detectors arranged in an annular shape in the exhaust part of the gas turbine to detect the gas turbine exhaust gas temperature, for detecting the same gas flow temperature The predetermined temperature of the gas turbine inlet gas temperature detection and the temperature of the gas turbine exhaust gas temperature detector are both minimum values, and both the gas turbine inlet gas temperature deviation and the gas turbine exhaust gas temperature deviation are above the allowable value. A gas turbine control device configured to detect a combustor abnormality corresponding to a certain condition. 6. A gas turbine control device for controlling combustion of a gas turbine plant comprising an air compressor, a combustor, and a gas turbine, wherein the gas turbine control device is provided in a ring shape at an inlet high-temperature portion of the gas turbine and controls the gas temperature at the gas turbine inlet. A plurality of gas turbine inlet gas temperature detectors for detecting, a plurality of gas turbine exhaust gas temperature detectors arranged in a ring on an exhaust portion of the gas turbine to detect a gas turbine exhaust gas temperature, and a predetermined portion of the gas turbine inlet high temperature portion The gas temperature of 2
Temperature of two gas turbine inlet gas temperature detectors, two gas turbine exhaust gas temperature detectors detecting the same gas flow temperature as the two gas turbine inlet gas temperature detectors, and the two gas turbine exhaust gas temperature detectors A gas turbine control device for estimating the same distribution of gas temperature based on the temperature of a third gas turbine exhaust gas temperature detector disposed in the middle of the gas turbine. 7. A gas turbine control device for controlling combustion of a gas turbine plant comprising an air compressor, a combustor, and a gas turbine, wherein the gas turbine control device is provided in a ring shape at an inlet high-temperature portion of the gas turbine, and controls a gas temperature at a gas turbine inlet. A plurality of gas turbine inlet gas temperature detectors for detecting, a plurality of gas turbine exhaust gas temperature detectors arranged in an annular shape in an exhaust portion of the gas turbine, and detecting a gas turbine exhaust gas temperature, The temperature of two gas turbine exhaust gas temperature detectors adjacent to the predetermined location, the temperature of two gas turbine inlet gas temperature detectors for detecting the same gas flow temperature as the two gas turbine exhaust gas temperature detectors And a third gas turbine inlet gas temperature detector disposed intermediate the two gas turbine inlet gas temperature detectors A gas turbine control device configured to estimate the distribution shape of the gas temperature based on the temperature of the gas turbine.