JP2003214179A - Sensor system and gas turbine device with the same - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a sensor system and a gas turbine device with the sensor system capable of improving the reliability of a measured value of a sensor while reducing the cost, and predicting the failure of the sensor. <P>SOLUTION: This sensor system comprises sensors 16, 17, 18 for measuring the physical quantity of a measured object, an error detecting part 23 for detecting the error between the measured value by the sensors 16, 17, 18 and a predetermined reference value, and a measured value correcting part 26 for correcting the measured values of the sensors 16, 17, 18 on the basis of the error detected by the error detecting part 23. <P>COPYRIGHT: (C)2003,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a sensor system and a gas turbine device equipped with the sensor system.

[0002]

2. Description of the Related Art In general, various devices are equipped with sensors for measuring physical quantities of various objects to be measured which change during operation in order to operate these devices safely and appropriately. There are various targets measured by the sensor, and for example, the temperature, pressure, flow rate, etc. of air are measured by the sensor.

An example of a device equipped with a sensor will be described below using a gas turbine device. A general gas turbine device includes a turbine rotatably mounted via a rotary shaft, a combustor that combusts a mixture of fuel and air to generate combustion gas, and a fuel supply amount to the combustor. It is basically composed of a fuel control valve for controlling and an air compressor for sending air to a combustor. In the above-described configuration, a mixture of air and fuel is formed in the combustor, and the mixture is burned in the combustor to generate high-temperature and high-pressure combustion gas. The combustion gas is supplied to the turbine so that the turbine rotates at high speed.

As a sensor provided in such a gas turbine device, the temperature (Co
CIT sensor that measures mbustor inlet air temperature (CIT), exhaust gas temperature (Exhaust Gas Temper
ature, EGT) and an OIL sensor for measuring the pressure of oil supplied for cooling and lubrication of bearings (hereinafter appropriately referred to as hydraulic pressure). The values measured by these various sensors are used as a determination factor for safely and reliably starting the gas turbine device or safely continuing the operation.

[0005]

However, in the conventional sensor, the measurement accuracy of the sensor deteriorates,
Even if an error occurs between the measured value and the actual value, the measured value including this error is used as each judgment element. As a result, for example, there is a problem that the start-up of the gas turbine device fails or the gas turbine device should be immediately stopped due to some abnormality, but the stop operation is delayed.

Moreover, such a decrease in the measurement accuracy of the sensor is judged only after an abnormal value such as an extremely high or low value measured by the sensor is measured. Then, the value deviating from the actual value is used as each judgment element until it is judged that the measurement accuracy of the sensor has deteriorated, and as a result, the problem as described above occurs.

In order to solve such a problem, conventionally, three kinds of sensors are measured for one kind of object to be measured, and the measured value having the most deviated value is excluded from the three measured values. Therefore, there is a method of improving the measurement accuracy. However, in this method, three sensors are used for one kind of object to be measured, so that there is a problem that the cost is high, and it is currently used only in a special device such as a nuclear power plant.

The present invention has been made in view of such conventional problems, and it is possible to improve the reliability of the measured value of the sensor while suppressing the cost, and further to predict the failure of the sensor. An object of the present invention is to provide a sensor system capable of achieving the above and a gas turbine device including the sensor system.

[0009]

In order to solve the above-mentioned problems, the present invention provides a sensor for measuring a physical quantity of an object to be measured, and an error between a measured value measured by the sensor and a predetermined reference value. Is provided, and a measurement value correction unit that corrects the measurement value of the sensor based on the error detected by the error detection unit. In this case, a measurement value recording unit for recording the measurement value measured by the sensor is provided, and the predetermined reference value is a predetermined measurement value selected from the measurement values recorded in the measurement value recording unit. Is preferred. Further, it is preferable that the measurement value correction unit adds a correction value that cancels the error detected by the error detection unit to the measurement value of the sensor. Further, it is preferable to provide an error occurrence warning unit for transmitting an error occurrence warning signal when the error detected by the error detection unit exceeds a predetermined reference range.

According to the present invention, even if an error occurs between the measured value measured by the sensor and the actual value, this error is automatically corrected, so that a highly reliable measured value can be obtained. It will be possible. As a result, the physical quantity of the object to be measured can be accurately determined based on the obtained measured value, and various devices such as the gas turbine device can be operated safely and appropriately. Also, if the detected error exceeds the predetermined reference range, it can be determined that the sensor function is degraded, so it is possible to detect this before the sensor completely fails. Becomes

[0011]

BEST MODE FOR CARRYING OUT THE INVENTION A gas turbine apparatus equipped with a sensor system according to an embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is a schematic diagram showing an overall configuration of a gas turbine device including a sensor system according to this embodiment.

As shown in FIG. 1, the present gas turbine system includes a turbine 1, a combustor 2 for combusting a mixture of fuel and air to generate combustion gas, and an amount of fuel supplied to the combustor 2. A fuel control valve 19 for controlling the air flow rate and an air compressor 3 for sending air to the combustor 2 under pressure. Further, the gas turbine device includes a heat exchanger 4 that heats air used for combustion by using heat of combustion gas, and a turbine control unit 11 that controls the turbine 1.

The turbine 1 has a plurality of rotary blades (not shown) for receiving a fluid and rotating, and is rotatably supported in a casing (not shown) via a rotary shaft 6. The air compressor 3 is configured to be driven by the turbine 1 via the rotating shaft 6 to compress air. The air compressor 3 is connected to the combustor 2 via a pipe 7, and the air compressed by the air compressor 3 is supplied to the combustor 2 via the pipe 7. The heat exchanger 4 is installed in the middle of the pipe 7, and the air compressor 3
The air compressed by is heated by the heat exchanger 4 and then supplied to the combustor 2.

The fuel control valve 19 is arranged on the upstream side of the combustor 2, and the fuel supplied from a fuel supply source (not shown) is supplied to the combustor 2 after passing through the fuel control valve 19. The fuel control valve 19 has a variable valve opening, and the amount of fuel supplied to the combustor 2 is adjusted by operating the valve opening.

The fuel and air supplied to the combustor 2 form an air-fuel mixture in the combustor 2, and the air-fuel mixture burns in the combustor 2 to generate high-temperature and high-pressure combustion gas. Then, by supplying this combustion gas to the turbine 1, the turbine 1 rotates at high speed. The generator 5 is connected to the shaft end of the rotary shaft 6, and the generator 5 is rotationally driven via the rotary shaft 6 to generate power. The turbine 1
The combustion gas supplied to the heat exchanger 4 is sent to the heat exchanger 4 through the pipe 8 and then exhausted.

Further, the present gas turbine apparatus is provided with an oil pump 15 which circulates cooling oil for cooling a part of the gas turbine apparatus which becomes hot due to the supply of combustion gas.
Is provided. A part of the cooling oil circulated by the oil pump 15 is supplied to a bearing (not shown) that rotatably supports the rotating shaft 6, and also functions as lubricating oil for maintaining the lubricating performance of the bearing. is doing.

The turbine controller 11 is configured to perform PID feedback control with the turbine 1 as a control target. That is, the current rotation speed and acceleration of the turbine 1 obtained by the rotation speed detection unit 12 arranged near the end of the rotary shaft 6 and the acceleration calculation unit (not shown) are used as feedback values, and this feedback value is preset. The control signal for minimizing the deviation from the target value is calculated by the PID operation. Then, by operating the opening degree of the fuel control valve 19 according to the value of the calculated control signal, the combustor 2
Adjust the flow rate of fuel supplied to the. In this way
By adjusting the amount of fuel supplied to the combustor 2, the temperature of the combustion gas supplied to the turbine 1 is adjusted, whereby the rotation speed and acceleration of the turbine 1 are controlled.

Further, the present gas turbine system has a CIT sensor 17 for measuring the temperature of the air pressure-fed to the combustor 2.
And an EGT sensor 18 that measures the temperature of the exhaust gas,
An OIL sensor 16 that measures the pressure of oil (OIL) supplied for cooling and lubrication, and a measurement value processing unit 21 that performs processing such as correction based on each measurement value measured by these sensors are provided. ing. Then, the sensor system according to the present embodiment is configured by each of these sensors and the measurement value processing unit 21.

The CIT sensor 17 is installed in the pipe 7 in the vicinity of the combustor 2. The CIT sensor 17 allows the air of the air just before flowing into the combustor 2 after being heated by the heat exchanger 4 to be detected. The temperature (CIT) is measured. CI
The measurement value measured by the T sensor 17 is sent to the turbine control unit 11 via the measurement value processing unit 21, and the optimum fuel supply amount for ignition and combustion of the air-fuel mixture is determined based on the measurement value.

The EGT sensor 18 is installed in the pipe 8 connecting the turbine 1 and the heat exchanger 4. The measurement value measured by the EGT sensor 18 is sent to the turbine control unit 11 via the measurement value processing unit 21, and is used by the turbine control unit 11 for controlling the rotation speed of the turbine 1.

The OIL sensor 16 is an oil pump 15
It is installed in the vicinity of, and based on the measurement value measured by the OIL sensor 16, it is determined whether the cooling action and the lubrication of the bearing are normally performed.

In the sensor system according to this embodiment, when there is an error in the measurement value measured by each sensor,
The measurement value processing unit 21 automatically corrects the measurement value so as to cancel the error. Then, the corrected measured value is sent to the turbine control unit 11 and used for safely operating the gas turbine device.

Now, the sensor system of this embodiment will be described in more detail with reference to FIG. Figure 2
FIG. 1 is a schematic diagram showing an overall configuration of a sensor system according to this embodiment. As described above, the sensor system according to this embodiment includes the CIT sensor 17, the EGT sensor 18, the OIL sensor 16, and the measurement value processing unit 21 that processes the measurement value of each sensor.

As shown in FIG. 2, the measurement value processing unit 21
A measurement value recording unit 22 that records the measurement value measured by each sensor, an error detection unit 23 that detects an error between the measurement value measured by each sensor and a predetermined reference value, and an error detection unit 23 that detects the error. Measurement value correction unit 26 that corrects the measurement value of each sensor based on the error, and error detection unit 23
When the error detected by exceeds the predetermined reference range, the first error occurrence warning unit 24 that issues an error occurrence warning signal
And a second error occurrence warning unit 25.

As shown in FIG. 2, the measured values measured by the respective sensors are first sent to the measured value recording section 22, and only the predetermined measured values are recorded from the sent measured values. The sensor is recorded in the section 22 for each sensor. The predetermined measurement value recorded by the measurement value recording unit 22 is, for example, the CIT sensor 17 or the EGT.
The value measured by the sensor 18 is the value of CIT or EGT measured immediately before the start of the gas turbine device. More specifically, each time the gas turbine device is started, CIT and EGT immediately before starting are measured, and the measured values are recorded in the measured value recording unit 22. Then, normally, the temperature of the gas turbine apparatus main body before starting is sufficiently lowered to the normal temperature, so the values of CIT and EGT measured immediately before starting should be recorded as a substantially constant value at each starting. become.

On the other hand, when the value measured by the OIL sensor 16 is recorded, it is the hydraulic pressure measured when the vehicle is operating under no load. Since the hydraulic pressure when operating in the no-load state changes at a certain constant value, the measured value measured at this time is recorded as a substantially constant value. Then, the measurement value group recorded in the measurement value recording unit 22 is used as a reference value for detecting an error in the error detection unit 23 described below.

The error detection unit 23 selects a predetermined measurement value from the measurement values recorded for each sensor in the measurement value recording unit 22 and detects the error in the measurement value of each sensor from the selected measurement value. It is used as a reference value for. Then, by comparing the measurement value measured at the same timing as when the reference value was measured or at the time of driving condition with the reference value, the error between the measurement value and the reference value can be detected. ing.

The error detected by the error detector 23 is
The error signal is sent to the first error occurrence warning unit 24 together with the measurement value of each sensor. In the first error occurrence warning unit 24, a first reference range that can be allowed as an error is preset for each sensor. The first reference range is set around the reference value selected by the error detector 23. Then, based on the error signal sent from the error detection unit 23, if the error exceeds the reference range, the first
The error occurrence warning signal of is sent. Further, as shown in FIG. 2, an operation stop unit 31 is connected to the first error occurrence warning unit 24, and when the first error occurrence warning signal is transmitted, the gas turbine receives this signal and receives the signal. The starting operation or the operation of the device is stopped.

The operation of the first error occurrence warning unit 24 will be described with reference to FIG. FIG. 3 is a diagram for explaining a case where the first error occurrence warning unit included in the present embodiment transmits the first error occurrence warning signal. As shown by the dotted line in FIG. 3, the first reference range is set within a range of ± α centering on the reference value P. Since high measurement accuracy is obtained when the sensor is functioning normally, there is almost no error between the measured value and the reference value. Therefore, the error detected by the error detection unit 23 falls within the first reference range as shown in A of FIG. 3, and in this case, the first error occurrence warning signal is not transmitted.

On the other hand, when the measurement accuracy of the sensor is lowered and the measured value is deflected, and as shown in FIG. 3B, the error exceeds the first reference range, the first error occurrence warning signal is given. Sent. Then, when the first error occurrence warning signal is transmitted, the operation stop unit 31 receives this signal and the start operation or operation of the gas turbine device is stopped.

The error signal and the measurement value output from the first error occurrence warning unit 24 are then sent to the second error occurrence warning unit 25. The basic configuration of the second error occurrence warning unit 25 is the same as that of the first error occurrence warning unit 24 described above, but the second error occurrence warning unit 25 uses the second error occurrence warning unit 25 that is narrower than the first reference range described above.
The reference range of is set. Then, when the error signal sent to the second error occurrence warning unit 25 exceeds the second reference range, the second error occurrence warning signal is transmitted.

As shown in FIG. 2, the second error occurrence warning unit 2
An alarm device 32 is connected to 5 and when the second error occurrence warning signal is transmitted from the second error occurrence warning unit 25, the alarm device 32 receives this signal and informs the operator of the gas turbine device. An alarm is set to be issued. According to the second error occurrence warning unit 25 configured as above, when the measurement value of the sensor exceeds the second reference range, it can be determined that the measurement accuracy of the sensor has deteriorated. It is possible to detect this before the failure.

The error signal and measurement value output from the second error occurrence warning unit 25 are then sent to the measurement value correction unit 26. The measurement value correction unit 26 corrects the measurement value by adding or subtracting a correction value that cancels an error to the measurement value. For example, when the error between the measured value measured by the OIL sensor 16 and the reference value is β (Pa), the measured value correction unit 26 causes the OIL sensor 16 to
By adding the correction value −β (Pa) to the measurement value measured by, the error is canceled. Each measured value corrected in this way is sent to the turbine control unit 11 as shown in FIG. 2, and is used for various controls of the gas turbine device as described above.

Next, the operation of the sensor system according to this embodiment will be specifically described with reference to FIG. FIG. 4 is a diagram showing the measured values of the sensor of the present embodiment and the corrected measured values over time. In addition, in FIG.
Although the description will be made using the IL sensor 16, the operation is similar when other sensors are used. In FIG. 4, the solid line indicates the measured value measured by the OIL sensor 16, and the dotted line indicates the actual hydraulic pressure. Further, as shown in the figure, the minimum hydraulic pressure value is set for the purpose of protecting the gas turbine device, and if it is detected that the hydraulic pressure is lower than this minimum hydraulic pressure value, the operation of the gas turbine device is stopped. It has become.

As shown in FIG. 4, the OIL sensor 16 measures a value that exceeds the actual hydraulic pressure by β (Pa). In this case, the error detected by the error detection unit 23 is β (Pa). Therefore, in the measurement value correction unit 26, a value that cancels this error, that is, -β (Pa) is added to the measurement value, so that the finally obtained measurement value is reduced to the value indicated by the dotted line.

As shown in FIG. 4, for example, when some abnormality occurs in the oil pump 15 and the hydraulic pressure is decreasing, the measured value (solid line) is below the minimum hydraulic value unless the measured value is corrected. The time for which it is detected is t ₂ . On the other hand, according to the measurement value (dotted line) corrected by the measurement value correction unit 26, the time when it is detected that the lowered measurement value is below the minimum hydraulic pressure value is t ₁ .

That is, the measured value after the correction is lowered to the minimum hydraulic pressure value by t ₂ -t ₁ earlier than the measured value before the correction, and it is early detected that the measured pressure value is below the minimum hydraulic pressure value. Will be. As a result, it becomes possible to stop the gas turbine device more quickly, and it is possible to prevent damage to the gas turbine device due to a decrease in cooling action due to a decrease in hydraulic pressure or poor bearing lubrication. .

The sensor system of the present invention is not limited to the above-mentioned embodiment, and it goes without saying that various modifications can be made without departing from the gist of the present invention. For example, if the measurement target of the sensor is CI
Other than T, EGT, and hydraulic pressure, the sensor system according to the present invention can be applied to other devices than the gas turbine device.

[0039]

As described above, according to the present invention,
Even if an error occurs between the measured value measured by the sensor and the actual value, this error is automatically corrected, so that a highly reliable measured value can be obtained. As a result, the physical quantity of the object to be measured can be accurately determined based on the obtained measured value, and various devices such as the gas turbine device can be operated safely and appropriately. Also, if the detected error exceeds the predetermined reference range, it can be determined that the sensor function is degraded, so it is possible to detect this before the sensor completely fails. Becomes

[Brief description of drawings]

FIG. 1 is a schematic diagram showing an overall configuration of a gas turbine apparatus including a sensor system according to an embodiment of the present invention.

FIG. 2 is a schematic diagram showing an overall configuration of a sensor system according to an embodiment of the present invention.

FIG. 3 is a diagram for explaining a case where a first error occurrence warning unit included in the sensor system according to the embodiment of the present invention transmits an error occurrence warning signal.

FIG. 4 is a diagram showing measured values of a sensor included in a sensor system according to an embodiment of the present invention and corrected measured values over time.

[Explanation of symbols]

1 turbine 2 Combustor 3 air compressor 4 heat exchanger 5 generator 6 rotation axes 7,8 piping 11 Turbine controller 12 Rotation speed detector 15 oil pump 16 OIL sensor 17 CIT sensor 18 EGT sensor 19 Fuel control valve 21 Measurement value processing unit 22 Measurement value recording section 23 Error detector 24 First error occurrence warning section 25 Second error occurrence warning section 26 Measurement value correction unit 31 Operation stop part 32 alarm

   ─────────────────────────────────────────────────── ─── Continued front page    (72) Inventor Masahiro Miyamoto             11-1 Haneda Asahi-cho, Ota-ku, Tokyo Co., Ltd.             Inside the EBARA CORPORATION (72) Inventor Yasushi Furuya             11-1 Haneda Asahi-cho, Ota-ku, Tokyo Co., Ltd.             Inside the EBARA CORPORATION (72) Inventor Masafumi Kataoka             11-1 Haneda Asahi-cho, Ota-ku, Tokyo Co., Ltd.             Inside the EBARA CORPORATION F-term (reference) 2F075 AA10

Claims (5)

[Claims] 1. A sensor for measuring a physical quantity of an object to be measured, an error detecting section for detecting an error between a measured value measured by the sensor and a predetermined reference value, and an error detected by the error detecting section. A sensor system comprising: a measurement value correction unit that corrects a measurement value of the sensor based on the sensor system. 2. A measurement value recording section for recording a measurement value measured by the sensor is provided, and the predetermined reference value is a predetermined measurement selected from the measurement values recorded in the measurement value recording section. The sensor system according to claim 1, wherein the sensor system is a value. 3. The sensor according to claim 1, wherein the measurement value correction unit adds a correction value that cancels the error detected by the error detection unit to the measurement value of the sensor. system. 4. The error occurrence warning unit for transmitting an error occurrence warning signal when the error detected by the error detection unit exceeds a predetermined reference range. The sensor system according to any one. 5. A sensor for measuring a physical quantity of an object to be measured, in a gas turbine device for rotatively driving the turbine by burning a mixture of air and fuel and supplying combustion gas generated by the combustion to the turbine. An error detection unit that detects an error between the measurement value measured by the sensor and a predetermined reference value, and a measurement value correction unit that corrects the measurement value of the sensor based on the error detected by the error detection unit. A gas turbine device comprising a sensor system having: