CN109885023B - Semi-physical simulation test system of gas turbine control system - Google Patents
Semi-physical simulation test system of gas turbine control system Download PDFInfo
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Abstract
The invention discloses a semi-physical simulation test system of a gas turbine control system, which is used for verifying the working performance and long-term operation stability of the gas turbine control system under the full working condition of a gas turbine and evaluating the working reliability and environmental adaptability of the gas turbine control system under the extreme working condition and the fault working condition of the gas turbine; the system comprises a gas turbine control system, a gas turbine physical simulation model and a gas turbine mathematical simulation model which are mutually connected through a communication interface and a network; the physical simulation model of the gas turbine comprises a rotating speed monitoring test bed, an IGV (integrated gas turbine) adjusting test bed, a simulated lubricating oil system, a simulated fuel system and a simulated air system. The test system greatly reduces the cost and the risk of the gas turbine control system during development and test, and has wide application value in the aspects of performance verification and reliability evaluation of the gas turbine control system.
Description
Technical Field
The invention relates to the technical field of simulation tests, in particular to a semi-physical simulation test system of a gas turbine control system.
Background
The gas turbine control system is a key core part in the gas turbine technology and has the characteristics of strong adaptability, high reliability, quick response and the like. With the development and the improvement of the gas turbine technology, the operation data and the control objects involved in the operation of the gas turbine control system are increased day by day, so how to build the gas turbine control system test system to verify the performance of the gas turbine control system is particularly important. At present, a real gas turbine or a gas turbine mathematical model is usually adopted as a controlled object in a gas turbine control system test system, but the real gas turbine has the defects of long construction period, high cost and equipment and personnel damage risks in operation under extreme working conditions, and the gas turbine mathematical model has the defects of low accuracy and capability of only calculating a small amount of working conditions and part of operation data.
Disclosure of Invention
Aiming at the defects of the current test system of the gas turbine control system, the invention provides a test system which uses a semi-physical simulation model of the gas turbine to replace a real gas turbine or a mathematical model of the gas turbine, and is used for verifying the working performance and long-term operation stability of the gas turbine control system under the full working condition of the gas turbine and evaluating the working reliability and environmental adaptability of the gas turbine control system under the extreme working condition and the fault working condition of the gas turbine. The system reduces the research and development cost of the test system of the gas turbine control system, shortens the construction period, avoids the risks of equipment and personnel, and improves the accuracy and reliability of the test system of the gas turbine control system.
In order to achieve the purpose, the invention adopts the technical scheme that:
a semi-physical simulation test system of a gas turbine control system comprises the gas turbine control system, a gas turbine physical simulation model and a gas turbine mathematical simulation model which are mutually connected through a communication interface and a network;
the gas turbine physical simulation model comprises a rotating speed monitoring test bed, an IGV (integrated gas turbine) adjusting test bed, a simulated lubricating oil system, a simulated fuel system and a simulated air system, and is used for simulating the actual operation process of the gas turbine, measuring operation parameters and transmitting the measured operation parameter data to a gas turbine control system and a gas turbine mathematical simulation model;
the gas turbine mathematical simulation model carries out computer modeling simulation based on a characteristic curve of the gas turbine, is used for calculating dynamic and thermodynamic operation data of the gas turbine under all working conditions and extreme working conditions, receives a control signal of the gas turbine control system and feeds the operation data back to the gas turbine control system;
the gas turbine control system is used for controlling the operation data of the gas turbine physical simulation model and the gas turbine mathematical simulation model to change within a preset numerical range of the gas turbine control system under all working conditions and extreme working conditions.
Furthermore, the rotating speed monitoring test bed is used for simulating the actual rotating effect of the gas turbine rotor, and comprises a speed measuring disc for simulating the rotation of the gas turbine rotor, an adjustable speed motor for driving the speed measuring disc to rotate at a high speed, a coupling and a bearing for connecting the adjustable speed motor and the speed measuring disc, and a rotating speed probe for measuring the actual rotating speed of the speed measuring disc; the speed-adjustable motor is in communication connection with the gas turbine mathematical simulation model, the rotating speed of the speed-adjustable motor is adjusted according to the rotating speed data of the gas turbine rotor calculated by the gas turbine mathematical simulation model, and the speed-measuring disc is driven to rotate at a high speed and simulate the actual rotating effect of the gas turbine rotor; the rotating speed probe is in communication connection with the gas turbine control system and used for measuring rotating speed data of the speed measuring disc and transmitting the data to the gas turbine control system.
Furthermore, the IGV adjusting test bench is used for simulating the process of adjusting the IGV opening degree of the gas turbine gas inlet adjustable guide vane system, and comprises a gas inlet adjustable guide vane, a servo device for driving the gas inlet adjustable guide vane, a transmission mechanism for connecting the servo device and the gas inlet adjustable guide vane, a linear displacement sensor for measuring the motion stroke of the servo device, and an angular displacement sensor for measuring the rotation angle of the gas inlet adjustable guide vane; the servo device is in communication connection with a gas turbine control system, and the rotating angle of the air inlet adjustable guide vane is adjusted through the transmission mechanism under the control of the gas turbine control system; the linear displacement sensor is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model and is used for measuring the movement stroke of the servo device and transmitting data to the gas turbine control system and the gas turbine mathematical simulation model; the angular displacement sensor is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model and is used for measuring the actual angle of the air inlet adjustable guide vane and transmitting data to the gas turbine control system and the gas turbine mathematical simulation model.
Further, the simulated lubricating oil system is used for simulating the process of supplying lubricating oil to a lubricating oil system of the gas turbine, and comprises a main lubricating oil pump for supplying lubricating oil to the lubricating oil system, a spare lubricating oil pump for supplying lubricating oil when the main lubricating oil pump works abnormally, an accident lubricating oil pump for supplying lubricating oil when the main lubricating oil pump and the spare lubricating oil pump cannot work, and an oil mist fan for maintaining the vacuum degree of an oil tank; the main lubricating oil pump, the standby lubricating oil pump, the accident lubricating oil pump and the oil mist fan are all in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, start and stop actions of the oil pump and the fan are completed according to control signals transmitted by the gas turbine control system, and start and stop state data are transmitted to the gas turbine mathematical simulation model.
Further, the simulated fuel system is used for simulating the process of supplying gas fuel to the fuel system of the gas turbine, and comprises a pressure control valve for regulating the outlet pressure of the fuel supply system, a flow control valve for regulating the outlet flow of the fuel supply system, and a fuel quick-closing valve for closing the fuel supply in an emergency state; the pressure control valve is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and is used for receiving a control signal of the gas turbine control system, adjusting the outlet pressure of the fuel supply system according to the control signal and transmitting an outlet pressure signal to the gas turbine mathematical simulation model; the flow control valve is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and is used for receiving a control signal of the gas turbine control system, adjusting the outlet flow of the fuel supply system according to the control signal and transmitting the outlet flow signal to the gas turbine mathematical simulation model; the fuel quick-closing valve is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and is used for receiving a control signal of the gas turbine control system, completing opening or closing actions according to the control signal, and transmitting the opening or closing state of the fuel quick-closing valve to the gas turbine mathematical simulation model.
Further, the simulation air system is used for simulating the process of the air system of the gas turbine for extracting air from the air compressor, and comprises a high-pressure air extraction valve, a medium-pressure air extraction valve and a low-pressure air extraction valve; the high-pressure air extraction valve, the medium-pressure air extraction valve and the low-pressure air extraction valve are respectively in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and are used for receiving control signals of the gas turbine control system, completing opening or closing actions according to the control signals, and transmitting the opening or closing state of the high-pressure air extraction valve, the medium-pressure air extraction valve and the low-pressure air extraction valve to the gas turbine mathematical simulation model.
Further, the gas turbine physical simulation model further comprises a signal generator, wherein the signal generator is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model and is used for simulating mechanical faults, abnormal component operation and abnormal operation data and alarm information of variable working conditions of the gas turbine, and transmitting the abnormal operation data and the alarm information to the gas turbine control system and the gas turbine mathematical simulation model.
Furthermore, the gas turbine control system is also provided with a timing device, and the timing device is in communication connection with a servo device in the IGV regulation test platform, a main lubricating oil pump, a spare lubricating oil pump, an accident lubricating oil pump and an oil mist fan in the simulation lubricating oil system, a pressure control valve, a flow control valve and a fuel quick-closing valve in the simulation fuel system, a high-pressure air extraction valve, a medium-pressure air extraction valve and a low-pressure air extraction valve in the simulation air system, and is used for measuring the device action time data required by the device to complete corresponding control actions after a control instruction is sent from the gas turbine control system.
Furthermore, the gas turbine mathematical simulation model comprises a gas turbine fault simulation model, and is used for simulating fault conditions of mechanical faults or abnormal component operation of the gas turbine in the gas turbine mathematical simulation model and calculating operation data of the gas turbine under the fault conditions.
Furthermore, the gas turbine mathematical simulation model is also provided with a timing function module which is used for measuring response time data required by the gas turbine control system when the gas turbine fault simulation model enters a fault working condition and the gas turbine control system sends a control instruction to adjust the operation data of the gas turbine physical simulation model and the gas turbine mathematical simulation model, and finally the gas turbine mathematical simulation model removes the fault working condition.
Compared with the prior art, the invention has the beneficial effects that:
1. the semi-physical simulation test system of the gas turbine control system reduces the research and development cost of the test system of the gas turbine control system, shortens the construction period, avoids the risks of equipment and personnel, and improves the accuracy and reliability of the test system of the gas turbine control system;
2. the semi-physical simulation test system of the gas turbine control system can accurately simulate the full working condition, variable working condition, extreme working condition and fault working condition of the operation of the gas turbine, and can more comprehensively and accurately evaluate the performance of the gas turbine control system;
3. the semi-physical simulation test system of the gas turbine control system can measure the specific response time from the fault condition generation to the control instruction generation of the gas turbine control system and the fault condition relief when the fault condition occurs, and is beneficial to continuously upgrading and optimizing the gas turbine control system;
4. the controlled object of the semi-physical simulation test system of the gas turbine control system is a complete gas turbine simulation model, so that the gas turbine control system verified and evaluated by the semi-physical simulation test system of the gas turbine control system can be directly transplanted to a real gas turbine for use, and the development period of the gas turbine control system is greatly shortened.
Drawings
FIG. 1 is a schematic diagram of the composition and connection relationship of a first embodiment of a semi-physical simulation test system of a gas turbine control system according to the present invention.
FIG. 2 is a schematic diagram of the composition and connection relationship of a second embodiment of the semi-physical simulation test system of the gas turbine control system according to the present invention.
FIG. 3 is a schematic diagram showing the composition and connection relationship of a semi-physical simulation test system of a gas turbine control system according to a third embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings by way of examples so that the advantages and features of the present invention can be more easily understood by those skilled in the art. It should be noted that the following description is only a preferred embodiment of the present invention, and does not limit the scope of the present invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield a still further embodiment. Therefore, it is intended that the present invention encompass such modifications and variations within the scope of the appended claims and their equivalents.
Example one
As shown in FIG. 1, the semi-physical simulation test system for the gas turbine control system comprises a control system and a simulation system, wherein the control system comprises the gas turbine control system and a human-computer interface station, and the simulation system comprises a gas turbine physical simulation model and a gas turbine mathematical simulation model.
The gas turbine control system, the gas turbine physical simulation model and the gas turbine mathematical simulation model are connected with each other through the communication interface and the system control network. The system control network can be selected as a dual-redundancy ring industrial Ethernet, data exchange and communication between points are completed by adopting a TCP/IP protocol, and high-level management and sharing of data are realized through a safety network isolation device.
The gas turbine physical simulation model comprises a rotating speed monitoring test bed, an IGV (integrated ignition timing) adjusting test bed, a simulated lubricating oil system, a simulated fuel system and a simulated air system, and is used for simulating the actual operation process of the gas turbine, measuring operation parameters and transmitting the measured operation parameter data to a gas turbine control system and a gas turbine mathematical simulation model; the gas turbine control system is also provided with a signal generator for simulating mechanical faults, abnormal component operation and abnormal operation data and alarm information of variable working conditions of the gas turbine, and transmitting the abnormal operation data and the alarm information to the gas turbine control system and the gas turbine mathematical simulation model.
The gas turbine mathematical simulation model carries out computer modeling simulation based on a characteristic curve of the gas turbine, is used for calculating dynamic and thermodynamic operation data of the gas turbine under all working conditions and extreme working conditions, receives a control signal of a gas turbine control system and feeds the operation data back to the gas turbine control system; the gas turbine mathematical simulation model is also provided with a gas turbine fault simulation model which is used for simulating the fault working condition of mechanical faults or part working abnormity of the gas turbine in the gas turbine mathematical simulation model and calculating the operation data of the gas turbine under the fault working condition.
The gas turbine control system is used for controlling the operation data of the gas turbine physical simulation model and the gas turbine mathematical simulation model to change within a preset numerical range of the gas turbine control system under all working conditions and extreme working conditions. The human-computer interface station is used for providing an operation and operation interface for process monitoring, control, diagnosis, maintenance and optimization management of the control system, displaying real-time data and abnormal alarm information of a physical simulation model and a mathematical simulation model of the gas turbine to a user, and transmitting a user instruction to the gas turbine control system.
Example two
As shown in fig. 2, the semi-physical simulation test system of the gas turbine control system in this embodiment includes a control system and a simulation system, the control system includes a gas turbine control system and a human-computer interface station, and the simulation system includes a gas turbine physical simulation model and a gas turbine mathematical simulation model.
The gas turbine control system and the gas turbine mathematical simulation model are connected through an SCnet communication interface and a network, and the gas turbine physical simulation model is connected with the gas turbine control system and the gas turbine mathematical simulation model through an IOnet communication interface and the network.
The physical simulation model of the gas turbine comprises a rotating speed monitoring test bed, an IGV (integrated fuel regulation) adjusting test bed, a simulated lubricating oil system, a simulated fuel system and a simulated air system (only the IGV adjusting test bed is shown in the figure). The IGV adjusting test bench comprises a servo device, a transmission mechanism, an air inlet adjustable guide vane, a linear displacement sensor and an angular displacement sensor, wherein the transmission mechanism is composed of a pull rod, a pull ring and a connecting rod. The servo device is in communication connection with the gas turbine control system, and the rotation angle of the air inlet adjustable guide vane is adjusted through the transmission mechanism under the control of the gas turbine control system; the linear displacement sensor and the angular displacement sensor are in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, the linear displacement sensor is used for measuring the movement stroke of the servo device and transmitting data to the gas turbine control system and the gas turbine mathematical simulation model, and the angular displacement sensor is used for measuring the actual angle data of the air inlet adjustable guide vane and transmitting the actual angle data to the gas turbine control system and the gas turbine mathematical simulation model.
In the starting process of the gas turbine, the angle of the air inlet adjustable guide vane needs to be adjusted, and the air inlet flow is changed, so that the stable working range of the gas compressor is expanded, and the surge phenomenon of the gas compressor is avoided.
In the embodiment, the gas turbine control system obtains expected data of the air inlet adjustable guide vane angle through configuration calculation in the starting process of the gas turbine, and transmits an adjusting control instruction to the servo device through the IOnet communication interface; the servo device adjusts the connected pull rod to move forwards according to the control instruction, the pull rod moves to drive the pulling ring arranged on the support to rotate along the circumference, the connecting rod moves along with the rotating ring in the rotating process and rotates the angle of the air inlet adjustable guide vane, and finally the simulation effect of changing the air inlet flow is achieved.
And a linear displacement sensor measurement servo device configured on the IGV regulation test platform measures linear displacement data of the pull rod moving forwards, and transmits the linear displacement data to a gas turbine control system and a gas turbine mathematical simulation model through an IOnet communication interface.
The gas turbine control system carries out configuration operation on the linear displacement data to obtain air inlet adjustable guide vane angle calculation data, and judges whether to continue adjusting the air inlet adjustable guide vane or not by comparing the air inlet adjustable guide vane angle calculation data with the air inlet adjustable guide vane angle expected data.
The gas turbine mathematical simulation model obtains the air intake flow operation data under the current working condition through the simulation calculation of the linear displacement data, and is used for calculating the integral simulation operation data by the gas turbine mathematical simulation model.
The gas turbine mathematical simulation model calculates the whole simulation operation data, and transmits the simulation operation data to the gas turbine control system through the SCnet communication interface for configuration operation of the gas turbine control system.
An angular displacement sensor arranged on the IGV adjusting test bench measures actual angle data of the air inlet adjustable guide vane, and transmits the actual angle data to a gas turbine control system through an IOnet communication interface; and the gas turbine control evaluates whether the gas turbine control system meets the expected performance index on the IGV adjusting function by comparing the actual angle data with the air inlet adjustable guide vane angle calculation data.
The human-computer interface station is in communication connection with the gas turbine control system, and the configuration operation result of the gas turbine control system and the operation data of the gas turbine mathematical simulation model are obtained from the gas turbine control system and displayed on a screen for a user to check.
EXAMPLE III
As shown in fig. 3, the semi-physical simulation test system of the gas turbine control system in the embodiment includes a control system and a simulation system, the control system includes a gas turbine control system, a human-computer interface station and a timing device, and the simulation system includes a gas turbine physical simulation model and a gas turbine mathematical simulation model.
The physical simulation model of the gas turbine comprises a rotating speed monitoring test bed, an IGV (integrated fuel regulation) adjusting test bed, a simulated lubricating oil system, a simulated fuel system and a simulated air system (only the rotating speed monitoring test bed and part of the simulated fuel system are shown in the figure). The gas turbine mathematical simulation model is used for calculating dynamic and thermodynamic operation data of the gas turbine under all working conditions and extreme working conditions, receiving a control signal of the gas turbine control system and feeding back the operation data to the gas turbine control system, and is also provided with a gas turbine fault simulation model and a timing function module.
The rotating speed monitoring test bed comprises a speed measuring disc for simulating the rotation of a gas turbine rotor, an adjustable speed motor for driving the speed measuring disc to rotate at a high speed, a coupler and a bearing for connecting the adjustable speed motor and the speed measuring disc, and a rotating speed probe for measuring the actual rotating speed of the speed measuring disc; the speed-adjustable motor is in communication connection with the gas turbine mathematical simulation model, and the rotating speed probe is in communication connection with the gas turbine control system; the simulated fuel system is configured with a pressure control valve for regulating the outlet pressure of the fuel supply system and a flow control valve for regulating the outlet flow of the fuel supply system.
The gas turbine control system and the gas turbine mathematical simulation model are connected through an SCnet communication interface and a network, and the simulation fuel system and the rotating speed monitoring test bed are connected with the gas turbine control system and the gas turbine mathematical simulation model through an IOnet communication interface and a network.
The gas turbine mathematical simulation model of the present embodiment is configured with a gas turbine fault simulation model. When the gas turbine stably works, starting a fault simulation model of the gas turbine, and transmitting abnormal rotating speed data higher than the rated rotating speed of the gas turbine to the mathematical simulation model of the gas turbine, wherein the mathematical simulation model of the gas turbine enters an overspeed fault working condition; and a timing function module configured in the gas turbine mathematical simulation model automatically starts timing when the gas turbine mathematical simulation model enters a fault working condition.
The gas turbine mathematical simulation model adjusts the rotating speed of the speed-adjustable motor configured on the rotating speed monitoring test bed to be the same as the abnormal rotating speed data through an IOnet communication interface; the speed-adjustable motor drives the coupler and the bearing to rotate, then drives the speed-measuring disc to rotate at a high speed according to the abnormal rotating speed data, and simulates the fault working condition that the rotating speed of the gas turbine is higher than the rated rotating speed.
And a rotating speed probe arranged on the rotating speed monitoring test bed measures to obtain rotating speed data of the speed measuring disc, namely abnormal rotating speed data, and transmits the abnormal rotating speed data to the gas turbine control system through the IOnet communication interface.
And the gas turbine control system receives the abnormal rotating speed data and displays overspeed alarm information to a user through a display screen of the man-machine interface station.
The gas turbine control system receives the abnormal rotating speed data, and transmits a control instruction for reducing the outlet pressure of the fuel supply system to an expected outlet pressure value to a pressure control valve in the simulated fuel system through the IOnet communication interface after configuration calculation; and after receiving the control instruction of the gas turbine control system, the pressure control valve executes the control instruction and transmits new outlet pressure data of the fuel supply system to the gas turbine control system and a gas turbine mathematical simulation model through the IOnet communication interface.
The timing device configured by the gas turbine control system starts timing the equipment action time data of the pressure control valve after the gas turbine control system transmits a control instruction to the pressure control valve; and the timing device stops timing when the outlet pressure data of the fuel supply system transmitted to the gas turbine control system by the pressure control valve reaches an expected outlet pressure value, and calculates the equipment action time data of the pressure control valve.
The gas turbine control system receives the abnormal rotating speed data, and transmits a control instruction for reducing the outlet flow of the fuel supply system to an expected outlet flow value to a flow control valve in the simulated fuel system through an IOnet communication interface after configuration calculation; and after receiving the control instruction of the gas turbine control system, the flow control valve executes the control instruction and transmits the outlet flow data of the new fuel supply system to the gas turbine control system and the gas turbine mathematical simulation model through the IOnet communication interface.
The timing device configured by the gas turbine control system starts timing equipment action time data of the flow control valve after the gas turbine control system transmits a control instruction to the flow control valve; the timing device stops timing when outlet flow data of the fuel supply system transmitted to the gas turbine control system by the flow control valve reaches an expected outlet flow value, and calculates equipment operation time data of the flow control valve.
And after receiving the new outlet pressure value and outlet flow value of the fuel supply system, the mathematical simulation model of the gas turbine carries out simulation calculation again to generate the operating data of the gas turbine.
The outlet pressure value and the outlet flow value of the fuel supply system are reduced, so that the supply amount of the fuel is reduced, and the rotating speed data calculation result of the gas turbine is gradually reduced; after the outlet pressure data and the outlet flow data of the fuel supply system respectively reach the expected outlet pressure value and the expected outlet flow value, the rotating speed calculation data in the mathematical simulation model of the gas turbine is restored to the rated rotating speed of the gas turbine again; and the mathematical simulation model of the gas turbine is recovered to a normal working condition from a fault working condition.
A timing function module in the mathematical simulation model of the gas turbine stops timing, and calculates the response time from the start of timing to the stop of timing of the timing function module; the response time is the response time required by the gas turbine control system to recover from the fault working condition to the normal working condition when the gas turbine is over-speed, and the response time is used for evaluating the working reliability of the gas turbine control system under the fault working condition.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (9)
1. The utility model provides a semi-physical simulation test system of gas turbine control system, includes gas turbine control system, gas turbine physical simulation model and the gas turbine mathematical simulation model through communication interface and network interconnect, its characterized in that:
the gas turbine physical simulation model comprises a rotating speed monitoring test bed, an IGV (integrated gas turbine) adjusting test bed, a simulated lubricating oil system, a simulated fuel system and a simulated air system, and is used for simulating the actual operation process of the gas turbine, measuring operation parameters and transmitting the measured operation parameter data to a gas turbine control system and a gas turbine mathematical simulation model;
the gas turbine mathematical simulation model carries out computer modeling simulation based on a characteristic curve of the gas turbine, is used for calculating dynamic and thermodynamic operation data of the gas turbine under all working conditions and extreme working conditions, receives a control signal of the gas turbine control system and feeds the operation data back to the gas turbine control system;
the simulated fuel system is used for simulating the process of supplying gas fuel to the fuel system of the gas turbine and comprises a pressure control valve for regulating the outlet pressure of the fuel supply system, a flow control valve for regulating the outlet flow of the fuel supply system and a fuel quick-closing valve for closing fuel supply in an emergency state; the pressure control valve is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and is used for receiving a control signal of the gas turbine control system, adjusting the outlet pressure of the fuel supply system according to the control signal and transmitting an outlet pressure signal to the gas turbine mathematical simulation model; the flow control valve is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and is used for receiving a control signal of the gas turbine control system, adjusting the outlet flow of the fuel supply system according to the control signal and transmitting the outlet flow signal to the gas turbine mathematical simulation model; the fuel quick-closing valve is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and is used for receiving a control signal of the gas turbine control system, completing opening or closing actions according to the control signal, and transmitting the opening or closing state of the fuel quick-closing valve to the gas turbine mathematical simulation model;
the gas turbine control system is used for controlling the operation data of the gas turbine physical simulation model and the gas turbine mathematical simulation model to change within a preset numerical range of the gas turbine control system under all working conditions and extreme working conditions.
2. The gas turbine control system semi-physical simulation test system of claim 1, wherein: the rotating speed monitoring test bed is used for simulating the actual rotating effect of the gas turbine rotor and comprises a speed measuring disc, an adjustable speed motor, a coupler, a bearing and a rotating speed probe, wherein the speed measuring disc is used for simulating the rotation of the gas turbine rotor, the adjustable speed motor is used for driving the speed measuring disc to rotate at a high speed, the coupler and the bearing are used for connecting the adjustable speed motor and the speed measuring disc, and the rotating speed probe is used for measuring the actual rotating speed of the speed measuring; the speed-adjustable motor is in communication connection with the gas turbine mathematical simulation model, the rotating speed of the speed-adjustable motor is adjusted according to the rotating speed data of the gas turbine rotor calculated by the gas turbine mathematical simulation model, and the speed-measuring disc is driven to rotate at a high speed and simulate the actual rotating effect of the gas turbine rotor; the rotating speed probe is in communication connection with the gas turbine control system and used for measuring rotating speed data of the speed measuring disc and transmitting the data to the gas turbine control system.
3. The gas turbine control system semi-physical simulation test system of claim 1, wherein: the IGV adjusting test bench is used for simulating the process of adjusting the opening degree of an IGV of an air inlet adjustable guide vane system of a gas turbine, and comprises an air inlet adjustable guide vane, a servo device for driving the air inlet adjustable guide vane, a transmission mechanism for connecting the servo device and the air inlet adjustable guide vane, a linear displacement sensor for measuring the motion stroke of the servo device, and an angular displacement sensor for measuring the rotation angle of the air inlet adjustable guide vane; the servo device is in communication connection with a gas turbine control system, and the rotating angle of the air inlet adjustable guide vane is adjusted through the transmission mechanism under the control of the gas turbine control system; the linear displacement sensor is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model and is used for measuring the movement stroke of the servo device and transmitting data to the gas turbine control system and the gas turbine mathematical simulation model; the angular displacement sensor is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model and is used for measuring the actual angle of the air inlet adjustable guide vane and transmitting data to the gas turbine control system and the gas turbine mathematical simulation model.
4. The gas turbine control system semi-physical simulation test system of claim 1, wherein: the simulation lubricating oil system is used for simulating the process of supplying lubricating oil to a lubricating oil system of the gas turbine, and comprises a main lubricating oil pump for supplying lubricating oil to the lubricating oil system, a spare lubricating oil pump for supplying lubricating oil when the main lubricating oil pump works abnormally, an accident lubricating oil pump for supplying lubricating oil when the main lubricating oil pump and the spare lubricating oil pump cannot work, and an oil mist fan for maintaining the vacuum degree of an oil tank; the main lubricating oil pump, the standby lubricating oil pump, the accident lubricating oil pump and the oil mist fan are all in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, start and stop actions of the oil pump and the fan are completed according to control signals transmitted by the gas turbine control system, and start and stop state data are transmitted to the gas turbine mathematical simulation model.
5. The gas turbine control system semi-physical simulation test system of claim 1, wherein: the simulation air system is used for simulating the process of the air system of the gas turbine for extracting air from the gas compressor and comprises a high-pressure air extraction valve, a medium-pressure air extraction valve and a low-pressure air extraction valve; the high-pressure air extraction valve, the medium-pressure air extraction valve and the low-pressure air extraction valve are respectively in communication connection with the gas turbine control system and the gas turbine mathematical simulation model, and are used for receiving control signals of the gas turbine control system, completing opening or closing actions according to the control signals, and transmitting the opening or closing state of the high-pressure air extraction valve, the medium-pressure air extraction valve and the low-pressure air extraction valve to the gas turbine mathematical simulation model.
6. The gas turbine control system semi-physical simulation test system of any of claims 1-5, wherein: the gas turbine physical simulation model further comprises a signal generator, wherein the signal generator is in communication connection with the gas turbine control system and the gas turbine mathematical simulation model and is used for simulating mechanical faults, component working abnormity of the gas turbine and abnormal operation data and alarm information of variable working conditions of the gas turbine and transmitting the abnormal operation data and the alarm information to the gas turbine control system and the gas turbine mathematical simulation model.
7. The gas turbine control system semi-physical simulation test system of claim 6, wherein: the gas turbine control system is also provided with a timing device which is in communication connection with a servo device in the IGV adjusting test platform, a main lubricating oil pump, a spare lubricating oil pump, an accident lubricating oil pump and an oil mist fan in a simulation lubricating oil system, a pressure control valve, a flow control valve and a fuel quick closing valve in the simulation fuel system, a high-pressure air extraction valve, a medium-pressure air extraction valve and a low-pressure air extraction valve in the simulation air system and used for measuring the equipment action time data required by the equipment to complete corresponding control actions after a control instruction is sent from the gas turbine control system.
8. The gas turbine control system semi-physical simulation test system of claim 1, wherein: the gas turbine mathematical simulation model comprises a gas turbine fault simulation model and is used for simulating fault conditions of mechanical faults or abnormal component operation of the gas turbine in the gas turbine mathematical simulation model and calculating operation data of the gas turbine under the fault conditions.
9. The gas turbine control system semi-physical simulation test system of claim 8, wherein: the gas turbine mathematical simulation model is also provided with a timing function module which is used for measuring response time data required by the gas turbine control system when the gas turbine control system sends a control instruction to adjust the operation data of the gas turbine physical simulation model and the gas turbine mathematical simulation model after the gas turbine fault simulation model enters a fault working condition and finally the gas turbine mathematical simulation model removes the fault working condition.
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| CN201910128558.0A CN109885023B (en) | 2019-02-21 | 2019-02-21 | Semi-physical simulation test system of gas turbine control system |
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| CN110824955A (en) * | 2019-11-21 | 2020-02-21 | 上海电气燃气轮机有限公司 | dSPACE-based gas turbine combined simulation platform and method |
| CN113899557B (en) * | 2020-06-22 | 2023-11-28 | 中国航发商用航空发动机有限责任公司 | Method and device for determining characteristics of an aeroengine air system |
| CN113011039B (en) * | 2021-03-31 | 2022-12-02 | 上海发电设备成套设计研究院有限责任公司 | Heavy gas turbine control system verification platform and verification method |
| CN113341694B (en) * | 2021-06-08 | 2022-12-02 | 杭州汽轮动力集团有限公司 | Equivalent verification system and method for flow control valve control strategy |
| CN113294246B (en) * | 2021-06-30 | 2022-11-04 | 中国航发动力股份有限公司 | Method for controlling rotatable guide vanes of gas turbine |
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Address after: 357 Shiqiao Road, Xiacheng District, Hangzhou City, Zhejiang Province Patentee after: Hangzhou Steam Turbine Holding Co.,Ltd. Address before: 357 Shiqiao Road, Xiacheng District, Hangzhou City, Zhejiang Province Patentee before: HANGZHOU TURBINE POWER GROUP CO.,LTD. |
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