CN112666922A - Method and system for testing light gas turbine control system - Google Patents
Method and system for testing light gas turbine control system Download PDFInfo
- Publication number
- CN112666922A CN112666922A CN202011494886.1A CN202011494886A CN112666922A CN 112666922 A CN112666922 A CN 112666922A CN 202011494886 A CN202011494886 A CN 202011494886A CN 112666922 A CN112666922 A CN 112666922A
- Authority
- CN
- China
- Prior art keywords
- gas turbine
- control system
- light
- turbine control
- parameters
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 39
- 238000012360 testing method Methods 0.000 title claims abstract description 32
- 238000013178 mathematical model Methods 0.000 claims abstract description 32
- 238000004364 calculation method Methods 0.000 claims abstract description 22
- 238000004088 simulation Methods 0.000 claims description 39
- 239000000446 fuel Substances 0.000 claims description 21
- 230000002159 abnormal effect Effects 0.000 claims description 14
- 230000003993 interaction Effects 0.000 claims description 12
- 239000003921 oil Substances 0.000 claims description 12
- 239000010687 lubricating oil Substances 0.000 claims description 4
- 238000012937 correction Methods 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 238000001514 detection method Methods 0.000 abstract description 9
- 239000007789 gas Substances 0.000 description 143
- 238000004891 communication Methods 0.000 description 12
- 230000006870 function Effects 0.000 description 12
- 230000003044 adaptive effect Effects 0.000 description 9
- 239000007858 starting material Substances 0.000 description 8
- 238000012544 monitoring process Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 230000008859 change Effects 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 230000001105 regulatory effect Effects 0.000 description 4
- 238000012795 verification Methods 0.000 description 4
- 238000011835 investigation Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000012216 screening Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
Images
Landscapes
- Testing And Monitoring For Control Systems (AREA)
Abstract
The invention discloses a method for testing a light gas turbine control system, belongs to the technical field of gas turbine control system detection modes, and solves the technical problem that the test cost of the light gas turbine control system in the prior art is high. The method comprises the steps of obtaining a first electric signal of the current operation condition in a light gas turbine control system; the first electric signal is converted into a digital signal and is corrected and/or calculated through a light gas turbine mathematical model to determine a plurality of actual parameters of the light gas turbine; and acquiring the actual parameters, calculating each actual parameter in a preset calculation period, and respectively converting the actual parameters into second electric signals to be input into a light gas turbine control system and a system thereof. The invention is used for perfecting the detection function of the gas turbine control system and meeting the requirement of people on lower detection cost of the gas turbine control system.
Description
Technical Field
The invention belongs to the technical field of detection methods of gas turbine control systems, and particularly relates to a method and a system for testing a light gas turbine control system.
Background
The simulation test is an important component in the research and development process of the gas turbine control system, whether the control, protection and other functions of the control system meet the safety, effectiveness and other targets of the operation process of the gas turbine can be verified through the simulation test, so that comprehensive software and hardware tests and system function simulation verification can be carried out on the gas turbine unit control system before the gas turbine unit control system is put into actual operation, a large amount of test cost can be saved through the simulation test of the control system, and a solid foundation is laid for the bench test of the gas turbine control system.
The simulation test system and method of the control system in the prior art are used for medium-power light aeroderivative gas turbines, all subsystems of the simulation system run in the same operation period, the requirements of the control system on different operation periods cannot be met, and the hardware cost is high.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a method for testing a light gas turbine control system, which solves the technical problem that the test cost of the light gas turbine control system in the prior art is high. The technical scheme of the scheme has a plurality of technical beneficial effects, which are described as follows:
in one aspect, the present disclosure provides a method for testing a control system of a light gas turbine, the method comprising:
acquiring a first electric signal of the current operation condition in a light gas turbine control system;
the first electric signal is converted into a digital signal and is corrected and/or calculated through a light gas turbine mathematical model to determine a plurality of actual parameters of the light gas turbine;
and acquiring the actual parameters, calculating each actual parameter in a preset calculation period, and converting each actual parameter into a second electric signal to be input into a light gas turbine control system.
In a preferred or optional embodiment, the method for operating each of the actual parameters in a preset operation period includes:
pre-distributing a plurality of data channels with different operation periods;
the actual parameters of each operation period are distributed to the data channels of the adaptive operation period;
all actual parameters calculated by the data channels in different calculation periods are respectively sent to the light gas turbine control system.
In a preferred or alternative embodiment, the method for sending all actual parameters calculated by the data channels of different calculation periods to the light-duty gas turbine control system respectively comprises the following steps:
and converting the actual parameters of the data channel operation in each different operation period into electric signals and sending the electric signals to the light gas turbine control system.
In a preferred or optional implementation manner, the method further comprises the steps of obtaining input parameters after the human-computer interaction, and determining an operation period corresponding to the input parameters;
and replacing or injecting the actual parameters in the data channel corresponding to the deviation by the input parameters according to the operation period corresponding to the input parameters, and sending the actual parameters to the light gas turbine control system.
In a preferred or alternative embodiment, the operation parameters of the light-duty gas turbine control system after receiving the input parameters are obtained, displayed, and judged whether to send out a shutdown or fault signal, if so, the light-duty gas turbine control system is normal, and if not, the light-duty gas turbine control system is abnormal, and marked.
Another aspect provides a system for light duty gas turbine control system testing, the system comprising:
the acquisition module is used for acquiring a first electric signal of the current operation condition in the light gas turbine control system and converting the first electric signal into a digital signal;
the mathematical model is used for acquiring the digital signals, correcting and/or calculating the digital signals, and determining actual parameters of the plurality of light gas turbines, such as determining parameters of a main engine of the plurality of light gas turbines and hydraulic starting rotation;
and the fault simulation module is used for acquiring the actual parameters, injecting faults into each actual parameter in a preset operation period, and converting the actual parameters into second electric signals to be input into the light gas turbine control system.
In a preferred or optional embodiment, the fault simulation module is further configured to pre-allocate data channels of a plurality of different operation cycles; the actual parameters of each operation period are distributed to the data channels of the adaptive operation period; and all the actual parameters calculated by the data channels in different calculation periods are respectively sent to the light gas turbine control system.
In a preferred or optional implementation manner, the fault simulation module is further configured to obtain an input parameter after human-computer interaction, and determine an operation cycle corresponding to the input parameter; and replacing the actual parameters in the corresponding data channels with the input parameters according to the operation period corresponding to the input parameters, and sending the actual parameters to the light gas turbine control system.
In a preferred or alternative embodiment, the simulation module comprises:
the host and the cabin module are used for acquiring a plurality of actual parameters of the light gas turbine host determined by the mathematical model;
pre-distributing a plurality of data channels with different operation periods; the actual parameters of each operation period are distributed to the data channels of the adaptive operation period; all actual parameters calculated by data channels in different calculation periods are respectively sent to a light gas turbine control system;
the starting system module is in communication connection with the mathematical model, acquires working condition parameters of a pump in the light gas turbine control system, converts the working condition parameters into digital signals and sends the digital signals to the mathematical model so as to acquire actual rotating speed parameters of a starter in the light gas turbine determined by the mathematical model;
pre-distributing a plurality of data channels with different operation periods; the actual parameters of each operation period are distributed to the data channels of the adaptive operation period; and all actual parameters calculated by the data channels in different calculation periods are respectively sent to the light gas turbine control system.
In a preferred or alternative embodiment, the simulation module further comprises:
a lube system module: the oil supply and discharge system fault simulation system is used for simulating faults of the oil supply and discharge system, sending the faults to the light gas turbine control system, judging whether fault signals sent by the light gas turbine control system are received, if yes, the light gas turbine control system is normal, if not, the light gas turbine control system is abnormal, and marking or information feedback is carried out;
washing system and fire extinguishing system module: the light gas turbine control system is used for simulating a fire-fighting fault signal to be sent to the light gas turbine control system, judging whether the fault signal sent by the light gas turbine control system is received or not, if so, judging that the light gas turbine control system is normal, and if not, judging that the light gas turbine control system is abnormal, and marking or feeding back information;
a vibration system module: simulating the current vibration parameters of the light gas turbine control system, and judging whether a shutdown or fault signal is sent when the vibration parameters are larger than a preset vibration value, if so, the light gas turbine control system is normal, and if not, the light gas turbine control system is abnormal, and marking;
a fuel system module: and simulating the fault working state parameter of the fuel control valve to send to the light gas turbine control system, judging whether a fault signal sent by the light gas turbine control system is received or not, if so, judging that the light gas turbine control system is normal, otherwise, judging that the light gas turbine control system is abnormal, and marking or information feedback.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
according to the scheme, each subsystem can operate in different operation periods to meet the related technologies of different operation period requirements of different modules of a control system, for example, temperature, rotating speed, pressure or other signals are calculated in 0-10 milliseconds, 10-15 milliseconds or 20-45 milliseconds or other periods respectively and are converted into electric signals to be sent to a light gas turbine control system, and at least the technical problem that hardware cost is too high is solved;
secondly, signals are sent in different periods, so that firstly, errors existing in programming of the control system are conveniently searched, manual screening is more convenient, and redundant data can be reduced; secondly, whether the control function, the protection function and the like of the control system meet the control requirements of the light gas turbine is verified, the time required for verification is greatly reduced, and the emphasis is to be placed on that the equipment adopted by the recording method is more reasonable and the processing rate can be improved under the condition of the same hardware equipment; and thirdly, calculation is carried out under different operation periods so as to meet the operation period requirements of different control modules of the light gas turbine control system, the flexibility of the light gas turbine control system is improved, and the function of the light gas turbine control system can be better exerted.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a flow chart of a method of testing a light duty gas turbine control system of the present invention;
FIG. 2 is a flow chart of a method for calculating each of the actual parameters within a predetermined calculation period in the method for testing the light gas turbine control system of the present invention;
FIG. 3 is a flow chart of a method for testing the light gas turbine control system to determine if the system is normal according to the present invention;
FIG. 4 is a block diagram of a system for testing the light gas turbine control system of the present invention;
FIG. 5 is a system overall structural framework diagram of the light gas turbine control system test of the present invention.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that various aspects of the embodiments are described below which are within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than the number, shape and size of the components in actual implementation, and the type, number and ratio of the components in actual implementation can be changed freely, and the layout of the components can be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details. In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
A method of testing a light duty gas turbine control system as in fig. 1, the method comprising:
s101, acquiring a first electric signal of the current operation condition in a light gas turbine control system;
s102, the light gas turbine control system is a control system in the prior art, for example, a plc control system or a DCS control system or other control systems are adopted, a monitoring system for the system including a fuel supply system, a control valve system and each part is provided, and signals acquired by first electric signals are electric signals of control parameters of a control circuit in the light gas turbine control system;
s103, converting the first electric signal into a digital signal, and correcting and/or calculating the digital signal through a mathematical model of the light gas turbine to determine a plurality of actual parameters of the light gas turbine;
the mathematical model is a model in the prior art, for example, a non-linear model at the component level established by Matlab Simulink software based on the component characteristics, has higher precision in comparison with actual test run data for verification, and is not described in detail here. After the first electric signal is converted into a digital signal, the digital signal is corrected and/or calculated through a mathematical model to determine a plurality of actual parameters of the light gas turbine, for example, parameters such as gas pressure, temperature or oil supply angle of an oil supply pump of different components or systems in a control system of the light gas turbine are obtained, theoretical values are determined through calculation or correction of the mathematical model, and parameters such as current equipment rotating speed, equipment temperature or pressure or angular speed are output after calculation;
and acquiring actual parameters, calculating each actual parameter in a preset calculation period, and converting each actual parameter into a second electric signal to be input into the light gas turbine control system.
The existing other existing schemes cannot meet the use requirements of the type of gas turbine, and do not have the function of simultaneously injecting various faults of all simulation signals, and the traditional schemes are all simultaneously signal transmission (numerical signals are converted into electric signals), so that at least the hardware cost is too high. According to the scheme, each subsystem can operate in different operation periods to meet the related technologies of different operation period requirements of different modules of the control system, for example, temperature, rotating speed, pressure or other signals are respectively calculated in 0-10 milliseconds, 10-15 milliseconds or 20-45 milliseconds or other periods and converted into electric signals to be sent to the light gas turbine control system, and at least the technical problem that the hardware cost is too high is solved;
secondly, signals are sent in different periods, so that firstly, errors existing in programming of the control system are conveniently searched, manual screening is more convenient, and redundant data can be reduced; secondly, whether the control function, the protection function and the like of the control system meet the control requirements of the light gas turbine is verified, the time required for verification is greatly reduced, and the emphasis is to be placed on that the equipment adopted by the recording method is more reasonable and the processing rate can be improved under the condition of the same hardware equipment; and thirdly, calculation is carried out under different operation periods so as to meet the operation period requirements of different control modules of the light gas turbine control system, the flexibility of the light gas turbine control system is improved, and the function of the light gas turbine control system can be better exerted.
As some embodiments provided in this disclosure, the method for calculating each actual parameter in a preset calculation period includes, as shown in fig. 2:
s201, pre-distributing a plurality of data channels with different operation periods;
s202, distributing the actual parameters of each operation period (data of different operation periods) to the data channels of the adaptive operation periods; for example, the temperature is configured to be 0-10 milliseconds, the rotation speed is configured to be 15-25 milliseconds, and the control system (shut-off valve or oil supply valve, etc.) is configured to be 30-45 milliseconds;
and S203, respectively sending all the actual parameters calculated by the data channels in different calculation periods to a light gas turbine control system. And converting the data of different periods into electric signals in the adaptive periods, and transmitting the electric signals to the light gas turbine control system.
The method can meet the operation or conversion of a plurality of actual parameters in different periods, namely, the light gas turbine control system can receive electric signals in different periods in different time periods, the requirements on system cache or a memory can be reduced, and the hardware cost is further reduced.
As part of the embodiments provided by the present disclosure, the method further includes obtaining an input parameter after the human-computer interaction, and determining an operation period corresponding to the input parameter, where the human-computer interaction is a second control, and the first control is generally an automatic simulation control of the main controller, and belongs to the preset template data.
The manual monitoring console compiles and debugs the running programs of the PLC of each sub-simulator, displays and records the running parameters of each simulator through the human-computer interaction display device, and operates the simulators and sets fault signals. Meanwhile, the manual monitoring platform can record the operation data of each parameter of the simulator system, an operator can select different time intervals to check historical data, and the input parameters can be replaced or injected into actual parameters in a data channel corresponding to the deviation according to the operation period corresponding to the input parameters and sent to the light gas turbine control system. According to the scheme, through the second control of man-machine interaction, important investigation or detection or monitoring and the like can be performed on parts subjected to important detection or other local systems in the light gas turbine control system, and the time consumption of batch data investigation is reduced.
Furthermore, the manual monitoring console is developed by configuration software of Intouch10.1 version, and each sub simulator is developed by GxWorks3 programming software applicable to Mitsubishi PLC FX 5U. Each sub-simulator communicates with the manual monitoring console through an Ethernet RJ-45 interface.
As part of the embodiments provided in the present application, as shown in fig. 3,
s301, acquiring and displaying the operation parameters of the light gas turbine control system after receiving the input parameters;
and S302, judging whether a shutdown or fault signal is sent, if so, the light gas turbine control system is normal, and if not, the light gas turbine control system is abnormal, and marking. The detection of the light gas turbine control system is realized, the detection process is efficient, time consumption is short, and key investigation can be realized.
Another aspect provides a system for testing a light duty gas turbine control system as shown in FIG. 4, the system comprising:
s401, an obtaining module, which is used for obtaining a first electric signal of the current operation condition in the light gas turbine control system and converting the first electric signal into a digital signal;
s402, a mathematical model is used for acquiring digital signals, correcting and/or calculating the digital signals and determining actual parameters of a plurality of light gas turbines;
and S403, acquiring actual parameters by the fault simulation module, calculating each actual parameter in a preset calculation period, and converting each actual parameter into a second electric signal to be input into the light gas turbine control system.
The gas turbine control system comprises a main engine control station, an auxiliary engine control station and a communication control station, wherein an operator loads corresponding control logic of each control station down into a DPU (distributed processing unit), and controls, monitors and protects the whole process from starting to running of the gas turbine. And the control system performs information interaction with the simulator system through the IO card. The hardware equipment and the IO card of the control system related by the invention are consistent with the actual operation equipment.
The system is described in detail below, as follows:
the fault simulation module is also used for pre-distributing a plurality of data channels with different operation periods; the actual parameters of each operation period are distributed to the data channels of the adaptive operation period; all actual parameters calculated by data channels in different calculation periods are respectively sent to a light gas turbine control system;
the fault simulation module is also used for acquiring input parameters after human-computer interaction and determining an operation period corresponding to the input parameters; and replacing the actual parameters in the corresponding data channel with the input parameters according to the operation period corresponding to the input parameters, and sending the actual parameters to the light gas turbine control system.
For example, the fault simulation module includes, as shown in fig. 5:
host computer and storehouse body module: the system is in communication connection with the mathematical model, and is used for acquiring working condition parameters of components in the light gas turbine control system, converting the working condition parameters into digital signals and sending the digital signals to the mathematical model so as to acquire a plurality of actual parameters of the light gas turbine components determined by the mathematical model;
the gas turbine main engine and box simulator is communicated with a gas turbine mathematical model to simulate the operation of the gas turbine and give parameters such as temperature and pressure of each part section of the gas turbine, parameters such as the rotating speed, flame state and surge margin of the gas turbine and monitoring parameters in a gas turbine cabin, and a plurality of actual parameters such as the operation parameters of the gas turbine main engine are obtained;
pre-distributing a plurality of data channels with different operation periods; the actual parameters of each operation period are distributed to the data channels of the adaptive operation period; all actual parameters calculated by data channels in different calculation periods are respectively sent to a light gas turbine control system; the data channel is used for different communication lines, such as 163 data communication or interface data communication in the prior art;
the method comprises the steps that a system starting module comprises a hydraulic pump, a hydraulic oil tank or other oil equipment and the like, the system starting module simulates running parameters such as the rotating speed and the power of a starter, is in communication connection with a mathematical model, acquires working condition parameters (such as a hydraulic pump swash plate opening signal) of a pump in a light gas turbine control system, converts the working condition parameters into digital signals and sends the digital signals to the mathematical model, and therefore a plurality of actual parameters (starter power parameters) of the pump in the light gas turbine determined by the mathematical model are acquired;
pre-distributing a plurality of data channels with different operation periods; the actual parameters of each operation period are distributed to the data channels of the adaptive operation period; and all actual parameters calculated by the data channels in different calculation periods are respectively sent to the light gas turbine control system.
A lube system module: and simulating the working states of pressure or temperature and the like of the lubricating oil system, such as a filter, a lubricating oil pump, an oil supply filter, an oil return filter, oil return parameters of each bearing cavity or magnetic detector parameters and the like. The system is used for simulating faults of a oil supply system and an oil discharge system, sending the faults to a light gas turbine control system, judging whether fault signals sent by the light gas turbine control system are received or not, if so, judging that the light gas turbine control system is normal, otherwise, judging that the light gas turbine control system is abnormal, and marking or feeding back information;
water system and fire extinguishing system module: the light gas turbine control system is used for simulating a fire-fighting fault signal to be sent to the light gas turbine control system, judging whether the fault signal sent by the light gas turbine control system is received or not, if yes, the light gas turbine control system is normal, and if not, the light gas turbine control system is abnormal, and marking or information feedback is carried out;
a vibration system module: acquiring current vibration parameters of a light gas turbine control system, and judging whether a shutdown or fault signal is sent out or not when the vibration parameters are larger than a preset vibration value, if so, judging that the light gas turbine control system is normal, and if not, judging that the light gas turbine control system is abnormal, and marking;
a fuel system module: and (3) simulating the fault working state parameters of the fuel control valve, sending the fault working state parameters to the light gas turbine control system, judging whether fault signals sent by the light gas turbine control system are received, wherein the fault signals at least comprise stop request signals, if so, the light gas turbine control system is normal, if not, the light gas turbine control system is abnormal, and marking or information feedback is carried out.
The fuel system simulator simulates fuel regulating valve operating characteristics and fuel system operating condition parameters. The control system comprises the state and feedback of actions of valves such as a regulating valve, a stop valve and an emptying valve of the fuel system after receiving instructions, and parameters such as the air supply pressure and the temperature of the fuel system. And the fuel system simulator calculates the corresponding natural gas fuel flow according to the opening signal of the fuel regulating valve sent by the control system so as to carry out fault simulation detection on the light gas turbine control system.
Each module is preset with different operation periods respectively to meet the requirements of receiving signals of different periods of a turbine, each module can be controlled by a controller to send simulated fault signals, or send simulated signals in a man-machine interaction mode, and each module has the following functions, for example, the thermal resistance signal simulation is realized through a stepping motor, a driver, an adjustable resistor and a DO module, the DO module in a PLC system sends pulses to the driver, and the driver drives the stepping motor to drive the adjustable resistor, so that the resistance change simulates the temperature change of Pt 100;
if the thermocouple signal simulation is realized through the precision resistor and the AO module, the PLC system adjusts the AO output current to flow through the precision resistor to generate mV voltage so as to simulate the thermocouple signal;
for example, the resistance signal simulation is realized through the stepping motor, the driver, the precision resistor and the AO module, the DO module in the PLC system sends a pulse to the driver, and the driver drives the stepping motor to drive the adjustable resistor, so that the resistance value change is realized. The PLC system adjusts the output current value of the AO module as required to realize 4-20 mA current signal simulation.
For example, the PLC system adjusts the duty ratio and the output period of the high-speed output point according to the requirement, so that the output frequency is adjustable, and the rotation speed signal simulation is realized.
For example, VSV signals are simulated through a stepping motor, a driver, an LVDT and a CPU high-speed output point, the PLC regulates the output point to send pulses to the driver, and the driver drives the stepping motor to drive the LVDT to generate displacement and change output voltage.
For example, the PLC connects or disconnects the output point according to the simulation requirement or the received input signal, and implements the switching value signal model, so that the fault simulation module sets fault injection such as sudden change, disconnection, short circuit, and the like for each sensor signal, to verify whether the protection strategies such as effective judgment, alarm, shutdown, and the like of the sensor in the control logic are effectively triggered. Meanwhile, a group of fault sequential delay triggers can be set to verify the first judgment function of the light gas turbine control system, so that operators can conveniently lock the reason of triggering the fault in time, and the time for fault finding and analysis is saved.
As data input by man-machine interaction, the gas turbine control system calculates parameters such as the swash plate angle of a starter, the stroke of an adjustable stationary blade actuator cylinder, the opening degree of a fuel regulating valve and the like corresponding to each stage of the gas turbine according to a starting mode selected by an operator, and sends the parameters to each module of the simulator system through an IO card. And each module of the simulator system calculates corresponding input parameters required by the model according to the instruction of the control system and transmits the corresponding input parameters to mathematical model input parameter interfaces in the gas turbine main engine and the cabin body sub-simulator in a Modbus communication mode. For example, a mathematical model of a gas turbine simulates the operation state of a real combustion engine, the input parameters are fuel quantity, adjustable stationary blade angle, inlet temperature, inlet pressure, starter power and ignition instruction, and the output parameters comprise the rotation speed of the combustion engine, section temperature of each part, pressure, flow rate and the like. The model calculates corresponding output parameters according to the input data, transmits the output parameters back to the simulator system through Modbus communication, transmits the output parameters back to the control system through the IO card, and the control system performs the next operation according to the feedback state.
The technical effect of the system is as follows:
1. each subsystem of the simulator system can calculate under different operation periods, and the requirements of different control modules of the light aviation retrofit gas turbine control system on different operation periods are met;
2. the simulator system structure can integrate and install five sub-simulators together by a frame to carry out digital simulation tests of a light combustion engine control system, and can also be separately installed to carry out semi-physical simulation tests of the combustion engine control system. The software equipment of the simulation system is recycled, so that the simulation test cost of the gas turbine control system is saved;
3. the gas turbine mathematical model and the simulator subsystem are connected through communication, so that the model does not need to be compiled in a c/c + + process and the like, and the use requirement is met while higher convenience and flexibility are realized;
4. the test system of the gas turbine control system can comprehensively simulate and test the whole operation process of various operation modes, various fault forms and protection strategies of the gas turbine control system, and lays a good foundation for the input and use of the gas turbine control system.
For example, simulation test of normal operation of gas turbine
The simulator end sets the parameters of each system to be in a preparation state before starting, and after an operator of the control system clicks a starting button, the control system checks whether the input signals of each system meet the starting requirements, such as the lubricating oil temperature, the liquid level, the fuel gas pressure, the effectiveness of each sensor and the like, in a sequential control program. After all the checks are passed, the control system transmits a starter operation instruction, a starter swash plate angle, the opening degree of a fuel metering valve and stroke requirements of an adjustable stationary blade actuating cylinder to the simulator system through an IO clamping piece in a digital quantity signal and a 4-20 mA signal or a switching quantity signal, the simulator system converts the signals into starter power, fuel flow, requirements of an adjustable stationary blade angle and the like and transmits the signals to a mathematical model of the gas turbine through Modbus communication, the mathematical model calculates the output of the gas turbine in a corresponding state according to input parameters and transmits the signals back to the simulator system through a Modbus communication module, and the simulator system converts model output parameters and other analog signals into 4-20 mA signals, thermal resistance signals, thermocouple signals and the like through the IO clamping piece and feeds back the signals to the control system for next instruction calculation.
Fault simulation
Taking the fault of the rotating speed sensor of the gas generator as an example, when the gas turbine runs to the rotating speed of a slow vehicle, the simulator end is provided with a fault disconnection of the rotating speed sensor of the gas turbine, the control system monitors that the rotating speed sensors are all in fault, an emergency shutdown command is sent out to cut off the fuel valve, the input of model fuel is changed into 0, and the rotating speed is gradually reduced to a shutdown state.
It should be noted that: the simulator system architecture can integrate and install five sub-simulators together by a frame to carry out a digital simulation test of the gas turbine control system, and can also be separately installed to carry out a semi-physical simulation test of the gas turbine control system;
the above system description is not all but only the extension based on the core idea of the present application, and should not be understood as a specific limitation of the present system.
The method and product provided by the present invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the core concepts of the present invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the invention without departing from the inventive concept, and those improvements and modifications also fall within the scope of the claims of the invention.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011494886.1A CN112666922A (en) | 2020-12-17 | 2020-12-17 | Method and system for testing light gas turbine control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011494886.1A CN112666922A (en) | 2020-12-17 | 2020-12-17 | Method and system for testing light gas turbine control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112666922A true CN112666922A (en) | 2021-04-16 |
Family
ID=75404695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011494886.1A Pending CN112666922A (en) | 2020-12-17 | 2020-12-17 | Method and system for testing light gas turbine control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112666922A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1374871A (en) * | 1971-10-15 | 1974-11-20 | Westinghouse Electric Corp | Digital computer control system for monitoring and controlling operation of industrial gas turbine apparatus |
| CN201035689Y (en) * | 2007-04-27 | 2008-03-12 | 刘星 | Linear multi-parameter composite fire detector |
| CN103557081A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Lightweight gas turbine control system |
| CN103955139A (en) * | 2014-04-21 | 2014-07-30 | 哈尔滨汽轮机厂有限责任公司 | Method for achieving simulation of heavy duty gas turbine by adopting distributed control system |
| CN104950869A (en) * | 2015-04-28 | 2015-09-30 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine control system testing device and method |
| CN110147573A (en) * | 2019-04-16 | 2019-08-20 | 新奥能源动力科技（上海）有限公司 | A kind of emulation mode of gas turbine, device and storage medium |
| JP2019160159A (en) * | 2018-03-16 | 2019-09-19 | 株式会社デンソーテン | Simulation device and method for simulation |
-
2020
- 2020-12-17 CN CN202011494886.1A patent/CN112666922A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1374871A (en) * | 1971-10-15 | 1974-11-20 | Westinghouse Electric Corp | Digital computer control system for monitoring and controlling operation of industrial gas turbine apparatus |
| CN201035689Y (en) * | 2007-04-27 | 2008-03-12 | 刘星 | Linear multi-parameter composite fire detector |
| CN103557081A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Lightweight gas turbine control system |
| CN103955139A (en) * | 2014-04-21 | 2014-07-30 | 哈尔滨汽轮机厂有限责任公司 | Method for achieving simulation of heavy duty gas turbine by adopting distributed control system |
| CN104950869A (en) * | 2015-04-28 | 2015-09-30 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine control system testing device and method |
| JP2019160159A (en) * | 2018-03-16 | 2019-09-19 | 株式会社デンソーテン | Simulation device and method for simulation |
| CN110147573A (en) * | 2019-04-16 | 2019-08-20 | 新奥能源动力科技（上海）有限公司 | A kind of emulation mode of gas turbine, device and storage medium |
Non-Patent Citations (1)
| Title |
|---|
| 李秀娟: ""一种8位嵌入式RISC MCU IP核数据通道模型设计"", 《电子技术应用》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6403690B2 (en) | Automatic test system for gas turbine | |
| CN111505964A (en) | Semi-physical simulation system and test method of aero-engine full real source | |
| CN102155470B (en) | Automatic detection and debugging system and method of hydraulic valve | |
| CN103869707A (en) | Semi-physical simulation test system applied to commercial aero engine control system | |
| CN103628991A (en) | Marine diesel oil-LNG dual-fuel engine management system detection device and method | |
| EP3376313B1 (en) | Real-time gas turbine simulation system and execution method thereof | |
| CN104699068A (en) | Universal simulator for aircraft engines | |
| CN111650925A (en) | dSPACE-based hybrid electric vehicle hardware-in-loop simulation system construction method | |
| CN108919772A (en) | A kind of vehicle control system automation test macro and method | |
| CN113011039B (en) | A heavy-duty gas turbine control system verification platform and verification method | |
| CN108490921A (en) | A kind of engine testing system | |
| CN105752359B (en) | A kind of airborne photoelectric gondola detection means | |
| CN208239866U (en) | A kind of exerciser automatic electrical control system | |
| CN102880166B (en) | The HIL testboard bay of VMS | |
| CN108398937A (en) | Electric-controlled co-rail automatic calibration system | |
| CN107045087A (en) | The test device and its method of double-fed wind power generator current transformer control cabinet | |
| CN112666922A (en) | Method and system for testing light gas turbine control system | |
| CN204613245U (en) | Fluted disc speed measuring comprehensive calibrator | |
| CN117471933A (en) | Diesel engine interface simulation device and system thereof | |
| CN206671435U (en) | The test device of double-fed wind power generator current transformer control cabinet | |
| CN117193247A (en) | Automatic test system for electronic injection control unit of unmanned aerial vehicle engine | |
| CN215811639U (en) | Automatic cycle test system for test run of micro turbojet engine | |
| CN111997961B (en) | Monitoring system of hydraulic station | |
| CN213658261U (en) | An EPS Injection Test Platform Based on SCALEXIO | |
| CN203050899U (en) | Starting device of electronic fuel injection (EFI) engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210416 |