Intelligent testing method and device for gas turbine control system

Abstract

The application provides an intelligent test method and device for a gas turbine control system, an electronic device and a storage medium. The method comprises the following steps: obtaining a plurality of operation data generated by a simulation model corresponding to a gas turbine under a simulation operation condition, a simulation operation mode and a simulation atmospheric environment corresponding to a preset probability of the gas turbine; processing measurement values of simulation sensors collecting the operation data by a gas turbine control system corresponding to the gas turbine to obtain a plurality of control instructions corresponding to the measurement values; feeding back the control instructions to a simulation actuator to feed back a plurality of execution results to the simulation model; and determining the reliability of the gas turbine control system according to a plurality of response results of the simulation model. Therefore, the accuracy of the response results of the simulation model under various simulation conditions or scenes is used to accurately determine the reliability of the gas turbine control system, and the test coverage and test efficiency of the gas turbine control system are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of gas turbines, and particularly relates to an intelligent testing method and device for a gas turbine control system, an electronic device and a storage medium. BACKGROUND

[0002] How to ensure the quality of the gas turbine control system is an important matter in the development of new gas turbines. In the related art, software-in-the-loop, hardware-in-the-loop simulation testing verification, fault injection, semi-physical testing, on-site debugging testing and other means are generally used for function and performance testing to ensure the quality of the gas turbine digital control system. The commonly used testing methods include: the first testing method is to test the reliability and accuracy of the action of a specific control or protection function under the condition of assumed input parameters; the second testing method is to test the reliability and accuracy of the action of the system under the condition of predetermined operation mode or working condition in a software-in-the-loop or hardware-in-the-loop simulation verification environment; and the third testing method is to inject a deterministic fault in a simulation verification environment to test the reliability of the action of the system under the fault condition. The sufficiency of the test depends on the experience of the tester, it is difficult to control the test quality, and there is a large difference between the test conditions and the real running scene, so the reliability of the gas turbine control system in the real scene cannot be accurately determined. SUMMARY

[0003] The present application provides an intelligent testing method and device for a gas turbine control system, an electronic device and a storage medium.

[0004] The first aspect of the present application provides an intelligent testing method for a gas turbine control system. The method comprises the following steps: obtaining simulation running working conditions, simulation running modes and simulation atmospheric environments corresponding to a preset probability of a gas turbine; obtaining a simulation model corresponding to the gas turbine; controlling the simulation model to run under the simulation running working conditions, the simulation running modes and the simulation atmospheric environments to obtain a plurality of running data generated by the simulation model running under the simulation running working conditions, the simulation running modes and the simulation atmospheric environments; controlling a gas turbine control system corresponding to the gas turbine to process measurement values of analog sensors collecting each running data to obtain a plurality of control instructions corresponding to each measurement value; feeding back each control instruction to an analog actuator corresponding to the simulation model to obtain a plurality of execution results of the analog actuator; feeding back the plurality of execution results to the simulation model to obtain a plurality of response results of the simulation model; and determining the reliability of the gas turbine control system according to the plurality of response results.

[0005] In an embodiment of the present application, the control of the gas turbine corresponds to a gas turbine control system processing measurement values of analog sensors collecting the operation data to obtain a plurality of control instructions corresponding to the measurement values, including: obtaining the measurement values of the analog sensors collecting the operation data, and converting the measurement values into control signals receivable by the gas turbine control system; and controlling the gas turbine control system to generate the plurality of control instructions corresponding to the measurement values based on the control signals.

[0006] In an embodiment of the present application, the feedback of the control instructions to the analog execution mechanism corresponding to the simulation model to obtain a plurality of execution results of the analog execution mechanism, including: converting the control instructions into execution signals receivable by the analog execution mechanism; and controlling the analog execution mechanism to generate the plurality of execution results corresponding to the execution signals based on the execution signals.

[0007] In an embodiment of the present application, the feedback of the plurality of execution results to the simulation model to obtain a plurality of response results of the simulation model, including: sending the plurality of execution results to the simulation model to enable the simulation model to run based on each of the execution results, stop running, or normally run for a time period longer than a preset time period to obtain the plurality of response results of the simulation model.

[0008] In an embodiment of the present application, the determination of the reliability of the gas turbine control system according to the plurality of response results, including: obtaining a plurality of standard response results of the gas turbine under the simulation running conditions, the simulation running modes and the simulation atmospheric environment; matching the plurality of response results with the plurality of standard response results to obtain a matching degree between the plurality of response results and the plurality of standard response results; and determining that the gas turbine control system is reliable in a case where the matching degree is greater than or equal to a preset matching threshold.

[0009] The application provides an intelligent testing method of a gas turbine control system, obtains multiple operation data generated by a simulation model corresponding to a gas turbine under simulation operation conditions, simulation operation modes and simulation atmospheric environments of the gas turbine under a preset probability of the gas turbine, processes measurement values of simulated sensors collecting the operation data by a gas turbine control system corresponding to the gas turbine, obtains control instructions corresponding to the measurement values, feeds back the control instructions to simulated actuators, feeds back multiple execution results to the simulation model, and determines reliability of the gas turbine control system according to multiple response results of the simulation model, so that the reliability of the gas turbine control system is accurately determined based on the accuracy of the multiple response results of the simulation model under various simulated conditions or scenes, and the test coverage and test efficiency of the gas turbine control system are improved.

[0010] The application provides an intelligent testing device of a gas turbine control system, the device comprises: a first obtaining module, configured to obtain simulation operation conditions, simulation operation modes and simulation atmospheric environments of a preset probability of a gas turbine; a second obtaining module, configured to obtain a simulation model corresponding to the gas turbine; a first control module, configured to control the simulation model to run under the simulation operation conditions, the simulation operation modes and the simulation atmospheric environments, so as to obtain multiple operation data generated by the simulation model under the simulation operation conditions, the simulation operation modes and the simulation atmospheric environments; a second control module, configured to process measurement values of simulated sensors collecting the operation data by a gas turbine control system corresponding to the gas turbine, so as to obtain control instructions corresponding to the measurement values; a first feedback module, configured to feed back the control instructions to simulated actuators corresponding to the simulation model, so as to obtain multiple execution results of the simulated actuators; a second feedback module, configured to feed back the execution results to the simulation model, so as to obtain multiple response results of the simulation model; and a determining module, configured to determine reliability of the gas turbine control system according to the multiple response results.

[0011] In an embodiment of the application, the device further comprises: the second control module, specifically configured to: obtain measurement values of simulated sensors collecting the operation data, and convert the measurement values into control signals receivable by the gas turbine control system; and control the gas turbine control system to generate multiple control instructions corresponding to the measurement values based on the control signals.

[0012] In an embodiment of the application, the first feedback module is specifically configured to: convert the control instructions into execution signals receivable by the simulated actuators; and control the simulated actuators to generate multiple execution results corresponding to the execution signals based on the execution signals.

[0013] In an embodiment of the present application, the second feedback module is specifically configured to send the multiple execution results to the simulation model, so that the simulation model runs based on each execution result, stops running, or normally runs, and in the case that the simulation model normally runs and the running time of the simulation model is greater than a preset time length, multiple response results of the simulation model are obtained.

[0014] In an embodiment of the present application, the determination module is specifically configured to obtain multiple standard response results of the gas turbine under the simulation running conditions, the simulation running modes and the simulation atmospheric environment; match the multiple response results and the multiple standard response results to obtain a matching degree between the multiple response results and the multiple standard response results; and in the case that the matching degree is greater than or equal to a preset matching threshold, determine that the gas turbine control system is reliable.

[0015] The present application proposes an intelligent testing device for a gas turbine control system, obtains multiple running data generated by a simulation model corresponding to a gas turbine running under simulation running conditions, simulation running modes and simulation atmospheric environment of the gas turbine corresponding to a preset probability of the gas turbine, controls a gas turbine control system corresponding to the gas turbine to process measurement values of analog sensors collecting each running data, to obtain each control instruction corresponding to each measurement value, feeds back each control instruction to an analog actuator, to feed back multiple execution results to the simulation model, so as to determine the reliability of the gas turbine control system according to multiple response results of the simulation model. Therefore, based on the accuracy of each response result of the gas turbine simulation model under various simulation conditions or scenes, the reliability of the gas turbine control system is accurately determined, and the test coverage and test efficiency of the gas turbine control system are improved.

[0016] The third aspect embodiment of the present application proposes an electronic device, which comprises a memory, a processor and a computer program stored in the memory and executable on the processor, and when the processor executes the program, the intelligent testing method for the gas turbine control system in the embodiments of the present application is realized.

[0017] The fourth aspect embodiment of the present application proposes a computer readable storage medium, which stores a computer program, and when the program is executed by a processor, the intelligent testing method for the gas turbine control system in the embodiments of the present application is realized.

[0018] The other effects of the above optional modes will be described in the following in combination with specific embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0019] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0020] Figure 1 This is a flowchart illustrating an intelligent testing method for a gas turbine control system provided in an embodiment of this application.

[0021] Figure 2 This is a flowchart illustrating another intelligent testing method for a gas turbine control system provided in an embodiment of this application;

[0022] Figure 3 This is a diagram of an intelligent test architecture for a gas turbine control system provided in an embodiment of this application;

[0023] Figure 4 This is a schematic diagram of an intelligent test principle for a gas turbine control system provided in an embodiment of this application;

[0024] Figure 5 This is a schematic diagram of the structure of an intelligent testing device for a gas turbine control system provided in an embodiment of this application;

[0025] Figure 6 This is a block diagram of an electronic device according to an embodiment of this application. Detailed Implementation

[0026] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0027] The following description, with reference to the accompanying drawings, describes an intelligent testing method, apparatus, and electronic device for a gas turbine control system according to embodiments of this application.

[0028] Figure 1 This is a flowchart illustrating an intelligent testing method for a gas turbine control system provided in this embodiment. It should be noted that the executing entity of the intelligent testing method for the gas turbine control system provided in this embodiment is an intelligent testing device for the gas turbine control system. This intelligent testing device can be implemented by software and / or hardware. In this embodiment, the intelligent testing device for the gas turbine control system can be configured in an electronic device, which may include a server. This embodiment does not specifically limit the type of electronic device.

[0029] Figure 1 This is a flowchart illustrating an intelligent testing method for a gas turbine control system provided in an embodiment of this application.

[0030] As Figure 1 shown, the intelligent test method of the gas turbine control system can include:

[0031] Step 101, obtaining a simulation running condition, a simulation running mode and a simulation atmospheric environment corresponding to a preset probability of the gas turbine.

[0032] In some embodiments, the simulation running condition corresponding to the gas turbine can be a normal simulation running condition of the gas turbine and an abnormal or accident simulation condition of the gas turbine, wherein the abnormal or accident simulation condition of the gas turbine can be a blade fracture accident condition of the gas turbine, but is not limited thereto, and this embodiment does not make specific limitation thereto.

[0033] In some embodiments, the simulation running mode corresponding to the gas turbine can include, but is not limited to, a start-up mode, a blow-down mode, a warm-up mode, a full-speed no-load mode and a load running mode.

[0034] In some embodiments, the simulation atmospheric environment corresponding to the gas turbine can include an atmospheric temperature and an atmospheric humidity, but is not limited thereto.

[0035] In other embodiments, the simulation atmospheric environment corresponding to the gas turbine is an atmospheric environment corresponding to a site environment of an intended application of the gas turbine, specifically, the atmospheric temperature of the simulation atmospheric environment can be any value in a temperature variation range of the site throughout the year, and the atmospheric humidity of the simulation atmospheric environment can be any value of the humidity throughout the day.

[0036] In some embodiments, in order to improve the test efficiency of the gas turbine control system, the preset probability corresponding to each of the simulation running condition, the simulation running mode and the simulation atmospheric environment of the preset probability can be preset, specifically, the probability of obtaining the normal simulation running condition can be reduced, and the probability of obtaining the abnormal or accident simulation condition can be increased, so as to improve the test coverage rate of the gas turbine control system.

[0037] Step 102, obtaining a simulation model corresponding to the gas turbine.

[0038] In some embodiments, the initial parameters of the simulation model corresponding to the gas turbine can be set according to the simulation running condition and the simulation running mode, and the simulation model can be constructed by a simulation tool according to the initial parameters.

[0039] Step 103, controlling the simulation model to run under the simulation running condition, the simulation running mode and the simulation atmospheric environment, so as to obtain a plurality of running data generated by the simulation model running under the simulation running condition, the simulation running mode and the simulation atmospheric environment.

[0040] In some embodiments, the simulation operating condition, the simulation operating mode and the simulation atmospheric environment can be corresponding to the real environment of the gas turbine, and the simulation operating condition, the simulation operating mode and the simulation atmospheric environment can be randomly selected according to a preset probability. The simulation model is controlled to run under the simulation operating condition, the simulation operating mode and the simulation atmospheric environment. Thus, the obtained running data can be randomly simulated running data, so as to improve the sufficiency of the running data and improve the testing quality of the gas turbine testing system.

[0041] In step 104, the measurement values of the simulation sensors for collecting the running data are processed by the gas turbine control system corresponding to the gas turbine to obtain a plurality of control instructions corresponding to the measurement values.

[0042] In some embodiments, the measurement values of the simulation sensors for collecting the running data can include current values or voltage values, but are not limited thereto.

[0043] In some embodiments, the gas turbine control system corresponding to the gas turbine can be a pre-set digital control and protection system. The measurement values are processed by the pre-set digital control and protection system to generate a plurality of control instructions or protection instructions, so as to realize dynamic processing of the running data and improve the testing efficiency of the gas turbine control system.

[0044] In step 105, the control instructions are fed back to the simulation execution mechanism corresponding to the simulation model to obtain a plurality of execution results of the simulation execution mechanism.

[0045] In some embodiments, the simulation execution mechanism can control any simulation device in the simulation model. For example, the simulation execution mechanism can control the opening threshold of a pump valve in the simulation model, but is not limited thereto.

[0046] It can be understood that, if the execution result of the simulation execution mechanism does not match the standard execution result corresponding to the control instruction, it indicates that the simulation execution mechanism can have a fault.

[0047] In step 106, the plurality of execution results are fed back to the simulation model to obtain a plurality of response results of the simulation model.

[0048] In some embodiments, each response result in the plurality of response results of the simulation model obtained according to the execution result can be that the simulation model is in a shutdown state or a continuous running state.

[0049] In step 107, the reliability of the gas turbine control system is determined according to the plurality of response results.

[0050] In some embodiments, a plurality of standard response results corresponding to a plurality of running data of the simulation model can be acquired, and the reliability of the gas turbine control system can be determined according to a comparison result of the plurality of response results and the plurality of standard response results.

[0051] Specifically, any one example response result in the plurality of response results can be compared with a corresponding example standard response result, and in a case where the example response result matches the example standard response result, it is indicated that the corresponding gas turbine control system under the example response result is correct, and otherwise, in a case where the example response result does not match the example standard response result, it is indicated that the corresponding gas turbine control system under the example response result is incorrect, so as to determine the correctness of the corresponding gas turbine control system under each example response result according to a matching result of each example response result and a corresponding example standard response result, and determine the reliability of the gas turbine control system based on a numerical value of the correctness.

[0052] The present application provides an intelligent testing method of a gas turbine control system, a plurality of running data generated by a simulation model corresponding to a gas turbine under a simulation running condition, a simulation running mode and a simulation atmospheric environment of the gas turbine corresponding to a preset probability of the gas turbine are acquired, a measurement value of a simulation sensor collecting each running data is processed by a gas turbine control system corresponding to the gas turbine, to obtain each control instruction corresponding to each measurement value, each control instruction is fed back to a simulation execution mechanism, to feed back a plurality of execution results to the simulation model, so as to determine the reliability of the gas turbine control system according to a plurality of response results of the simulation model, thereby, based on the accuracy of each response result of the gas turbine simulation model under various simulation conditions or scenes, the reliability of the gas turbine control system is accurately determined, and the test coverage and test efficiency of the gas turbine control system are improved.

[0053] For the purpose of clear understanding of the present application, the following will be described in combination with Figure 2 The processing process of the intelligent testing method of the gas turbine control system is exemplarily described, and the embodiment is a further refinement or expansion of the above-mentioned embodiment.

[0054] As Figure 2 shown, the intelligent testing method of the gas turbine control system can include:

[0055] Step 201, a simulation running condition, a simulation running mode and a simulation atmospheric environment corresponding to a preset probability of a gas turbine are acquired.

[0056] Step 202, a simulation model corresponding to the gas turbine is acquired.

[0057] In step 203, the simulation model is controlled to run under the simulation running condition, the simulation running mode and the simulation atmospheric environment, so as to obtain a plurality of running data generated by the simulation model running under the simulation running condition, the simulation running mode and the simulation atmospheric environment.

[0058] It should be noted that the specific implementation of steps 201-203 can refer to the related description in the above embodiments.

[0059] In step 204, the measurement values of the analog sensors collecting the respective running data are obtained, and the respective measurement values are converted into control signals receivable by the gas turbine control system.

[0060] In some embodiments, the control signals receivable by the gas turbine control system can be physical signals such as pressure values or temperature values, but are not limited thereto.

[0061] In some embodiments, the measurement values of the analog sensors collecting the respective running data can be converted into pressure values and temperature values receivable by the gas turbine control system.

[0062] In step 205, the gas turbine control system is controlled to generate a plurality of control instructions corresponding to the respective measurement values based on the control signals.

[0063] In some embodiments, the gas turbine control system can generate control instructions for adjusting the pressure values and the temperature values according to the pressure values or the temperature values in the control signals.

[0064] In step 206, the respective control instructions are converted into execution signals receivable by the analog actuators.

[0065] In some embodiments, the execution signals receivable by the analog actuators can be standard voltage signals and standard current signals, but are not limited thereto.

[0066] In step 207, the analog actuators are controlled to generate a plurality of execution results corresponding to the execution signals based on the execution signals.

[0067] In some embodiments, the analog actuators can generate a plurality of execution results for controlling the simulation model running according to the standard voltage signals or the standard current signals in the execution signals.

[0068] In step 208, the plurality of execution results are sent to the simulation model, so that the simulation model runs based on the respective execution results, stops running, or normally runs for a time period longer than a preset time period, so as to obtain a plurality of response results of the simulation model.

[0069] In step 209, a plurality of standard response results of the gas turbine under the simulation running condition, the simulation running mode and the simulation atmospheric environment are obtained.

[0070] In some embodiments, the multiple standard response results of the gas turbine under the simulation operating condition, the simulation operating mode and the simulation atmospheric environment can be obtained from the multiple response results of the historical operating data, or can be given by the relevant technical personnel, but are not limited thereto.

[0071] In step 210, the multiple response results are matched with the multiple standard response results to obtain the matching degree between the multiple response results and the multiple standard response results.

[0072] In step 211, in the case that the matching degree is greater than or equal to the preset matching threshold, it is determined that the gas turbine control system is reliable.

[0073] In some embodiments, the preset matching threshold can be set to 95%, but is not limited thereto, and this embodiment does not make a specific limitation thereto.

[0074] In another embodiment, in the case that the matching degree is less than the preset matching threshold, the test accuracy of the gas turbine test system is low, and it is determined that the gas turbine control system is unreliable.

[0075] The present application provides an intelligent test method for a gas turbine control system. The simulation operating condition, the simulation operating mode and the simulation atmospheric environment corresponding to a preset probability of the gas turbine are obtained, a simulation model corresponding to the gas turbine is obtained, the simulation model is controlled to operate under the simulation operating condition, the simulation operating mode and the simulation atmospheric environment, operating data generated by the operation is obtained, measurement values of simulation sensors collecting each operating data are obtained, and each measurement value is converted into a control signal receivable by the gas turbine control system. The gas turbine control system generates multiple control instructions corresponding to each measurement value based on the control signal, converts each control instruction into an execution signal receivable by a simulation execution mechanism, and controls the simulation execution mechanism to generate multiple execution results corresponding to the execution signal based on the execution signal. The multiple execution results are sent to the simulation model, so that the simulation model operates based on each execution result. In the case that the simulation model stops operating, or in the case that the simulation model normally operates and the operating time of the simulation model is greater than a preset time, multiple response results of the simulation model are obtained. Multiple standard response results of the gas turbine under the simulation operating condition, the simulation operating mode and the simulation atmospheric environment are obtained. The multiple response results are matched with the multiple standard response results to obtain the matching degree between the multiple response results and the multiple standard response results. In the case that the matching degree is greater than or equal to a preset matching threshold, it is determined that the gas turbine control system is reliable. Thus, the gas turbine control system processes multiple response results of the gas turbine under various simulation operating conditions or scenes, ensuring the reliability of the test of the gas turbine control system, and improving the test quality and test efficiency of the gas turbine control system.

[0076] To better implement the intelligent test method of the gas turbine control system, the embodiment of the application provides an intelligent test architecture diagram of a gas turbine control system, as shown in the figure. Figure 3 Specifically, the intelligent test architecture diagram of the gas turbine control system includes a running mode, a running condition selection module, an atmospheric environment simulation module, a gas turbine generator set simulation module, a sensor failure selection module, a sensor signal conversion module, an operation instruction conversion module, an actuator failure selection module, a test record and coverage rate statistical analysis module, and the gas turbine control system.

[0077] The running mode and the running condition selection module are configured to randomly obtain a simulation running condition and a simulation running mode corresponding to the gas turbine.

[0078] The atmospheric environment simulation module is configured to simulate a simulation atmospheric environment corresponding to the gas turbine.

[0079] The gas turbine generator set simulation module is configured to simulate a simulation model of the gas turbine, and control the simulation model to run in the simulation running condition, the simulation running mode and the simulation atmospheric environment, so as to obtain a plurality of running data generated by the simulation model running in the simulation running condition, the simulation running mode and the simulation atmospheric environment.

[0080] The sensor failure selection module is configured to simulate measurement values of simulation sensors for collecting the plurality of running data.

[0081] The sensor signal conversion module is configured to convert each measurement value into a control signal receivable by the gas turbine control system.

[0082] The gas turbine control system is configured to process the control signal, so as to generate a plurality of control instructions corresponding to each measurement value.

[0083] The operation instruction conversion module is configured to convert each control instruction into an execution signal receivable by a simulation actuator.

[0084] The actuator failure selection module is configured to process the execution signal, generate a plurality of execution results corresponding to the execution signal, and feed back the plurality of execution results to the simulation model, so as to control the simulation model to run based on each execution result, thereby obtaining a plurality of response results when the simulation model runs.

[0085] The test record and coverage rate statistical analysis module is configured to record the plurality of response results, and compare the plurality of response results with a plurality of standard response results, so as to determine the reliability of the gas turbine control system.

[0086] It can be understood that, for the purpose of clearly describing the intelligent test principle of the gas turbine control system, the embodiment of the application further provides an intelligent test principle diagram of a gas turbine control system, as shown in the figure. Figure 4As shown, specifically, by randomly selecting the simulation running mode and the simulation running condition of the preset probability of the gas turbine, and recording the corresponding accident condition data when the simulation running accident condition is selected, the initial parameters of the generator set model of the gas turbine are set according to the simulation running mode and the simulation running condition, so as to establish the simulation model of the gas turbine, and according to the selected simulation atmospheric environment condition, a plurality of running data generated by the simulation model of the gas turbine running under the preset probability of the simulation running condition, the simulation running mode and the simulation atmospheric environment are obtained, the measurement values of the same type of simulation sensors collecting each running data are obtained, and according to the comparison result of the number of failures of each measurement value and the preset simulation sensor failure number threshold, the gas turbine control system generates a plurality of corresponding control instructions, and sends each control instruction to the simulation model corresponding to the simulation execution mechanism, obtains a plurality of execution results of the simulation execution mechanism executing each control instruction, and according to the comparison result of the number of failures in the plurality of execution results and the preset simulation execution mechanism failure number threshold, the simulation model continues to run under the current simulation atmospheric environment, if the simulation model stops running, or in the case that the simulation model normally runs and the running time of the simulation model is greater than the preset time, a plurality of response results of the simulation model are obtained, the coverage of the sum of the plurality of response results and the set plurality of standard response results is judged, if the coverage reaches the test end condition corresponding to the gas turbine control system, the intelligent test of the gas turbine control system is ended.

[0087] Wherein, the gas turbine control system can generate control instructions by hand, or can generate control instructions by the gas turbine control system.

[0088] Figure 5 is a structural schematic diagram of an intelligent testing device of a gas turbine control system provided by an embodiment of the present application.

[0089] As Figure 5 shown, the intelligent testing device 500 of the gas turbine control system includes a first acquisition module 501, a second acquisition module 502, a first control module 503, a second control module 504, a first feedback module 505, a second feedback module 506 and a determination module 507, wherein:

[0090] The first acquisition module 501 is configured to acquire the simulation running condition, the simulation running mode and the simulation atmospheric environment corresponding to the preset probability of the gas turbine.

[0091] The second acquisition module 502 is configured to acquire the simulation model corresponding to the gas turbine.

[0092] The first control module 503 is configured to control the simulation model to run in a simulation running condition, a simulation running mode and a simulation atmospheric environment, so as to obtain a plurality of running data generated by the simulation model running in the simulation running condition, the simulation running mode and the simulation atmospheric environment.

[0093] The second control module 504 is configured to control a gas turbine control system corresponding to the gas turbine to process measurement values of simulation sensors collecting the plurality of running data, so as to obtain a plurality of control instructions corresponding to the plurality of measurement values.

[0094] The first feedback module 505 is configured to feed back the plurality of control instructions to simulation actuators corresponding to the simulation model, so as to obtain a plurality of execution results of the simulation actuators.

[0095] The second feedback module 506 is configured to feed back the plurality of execution results to the simulation model, so as to obtain a plurality of response results of the simulation model.

[0096] The determining module 507 is configured to determine the reliability of the gas turbine control system according to the plurality of response results.

[0097] The application provides an intelligent testing device for a gas turbine control system. The device obtains a plurality of running data generated by a simulation model corresponding to a gas turbine running in a simulation running condition, a simulation running mode and a simulation atmospheric environment corresponding to a preset probability of the gas turbine, controls a gas turbine control system corresponding to the gas turbine to process measurement values of simulation sensors collecting the plurality of running data, so as to obtain a plurality of control instructions corresponding to the plurality of measurement values, feeds back the plurality of control instructions to simulation actuators, feeds back a plurality of execution results of the simulation actuators to the simulation model, and determines the reliability of the gas turbine control system according to a plurality of response results of the simulation model. Thus, the accuracy of the plurality of response results of the simulation model in various simulation conditions or scenes is used to accurately determine the reliability of the gas turbine control system, and the test coverage and test efficiency of the gas turbine control system are improved.

[0098] In an embodiment of the application, the second control module 504 is specifically configured to:

[0099] Obtain the measurement values of the simulation sensors collecting the plurality of running data, and convert the plurality of measurement values into control signals receivable by the gas turbine control system.

[0100] Control the gas turbine control system to generate the plurality of control instructions corresponding to the plurality of measurement values based on the control signals.

[0101] In an embodiment of the application, the first feedback module 505 is specifically configured to:

[0102] Convert the plurality of control instructions into execution signals receivable by the simulation actuators.

[0103] The control simulation actuator generates multiple execution results corresponding to the execution signals based on the execution signals.

[0104] In one embodiment of this application, the second feedback module 506 is specifically used for:

[0105] Multiple execution results are sent to the simulation model so that the simulation model runs based on each execution result. Multiple response results from the simulation model are obtained when the simulation model stops running, or when the simulation model is running normally and the runtime of the simulation model exceeds the preset time.

[0106] In one embodiment of this application, the determining module 507 is specifically used for:

[0107] Obtain multiple standard response results of the gas turbine under simulated operating conditions, simulated operating modes, and simulated atmospheric environments.

[0108] Multiple response results are matched with multiple standard response results to obtain the degree of matching between the multiple response results and the multiple standard response results.

[0109] If the matching degree is greater than or equal to the preset matching threshold, the gas turbine control system is determined to be reliable.

[0110] like Figure 6 The diagram shown is a block diagram of an electronic device according to an embodiment of this application.

[0111] like Figure 6 As shown, the electronic device includes:

[0112] The memory 601, the processor 602, and the computer instructions stored in the memory 601 and executable on the processor 602.

[0113] When the processor 602 executes instructions, it implements the intelligent testing method for the gas turbine control system provided in the above embodiments.

[0114] Furthermore, electronic devices also include:

[0115] Communication interface 603 is used for communication between memory 601 and processor 602.

[0116] The memory 601 is used to store computer instructions that can be run on the processor 602.

[0117] The memory 601 may include high-speed RAM memory, and may also include non-volatile memory, such as at least one disk storage device.

[0118] The processor 602 is configured to implement the intelligent testing method of the gas turbine control system according to the above embodiments when executing a program.

[0119] If the memory 601, the processor 602 and the communication interface 603 are implemented independently, the communication interface 603, the memory 601 and the processor 602 can be connected with each other through a bus and complete communication between each other. The bus can be an Industry Standard Architecture (ISA) bus, a Peripheral Component (PCI) bus or an Extended Industry Standard Architecture (EISA) bus, etc. The bus can be divided into an address bus, a data bus, a control bus, etc. For the convenience of representation, Figure 6 Only one thick line is used to represent the bus in the figure, but it does not mean that there is only one bus or only one type of bus.

[0120] Optionally, if the memory 601, the processor 602 and the communication interface 603 are integrated on a chip, the memory 601, the processor 602 and the communication interface 603 can complete communication between each other through an internal interface.

[0121] The processor 602 can be a Central Processing Unit (CPU), or an Application Specific Integrated Circuit (ASIC), or one or more integrated circuits configured to implement one or more embodiments of the present application.

[0122] In addition, the terms "first", "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise explicitly and specifically limited.

[0123] In the description of the specification, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are contained in at least one embodiment or example of the present application. In the specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. In addition, the person skilled in the art can combine and combine the different embodiments or examples described in the specification and the features of the different embodiments or examples without contradiction.

[0124] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary and are not to be construed as limiting the present application, and the person skilled in the art can make changes, modifications, replacements and variations to the above-described embodiments within the scope of the present application.

Claims

1. An intelligent testing method for a gas turbine control system, characterized by, Wherein, The method comprises: Obtaining simulation running conditions, simulation running modes and simulation atmospheric environments corresponding to the gas turbine at a preset probability, the simulation running conditions, the simulation running modes and the simulation atmospheric environments being randomly selected according to the preset probability, the preset probability being a probability of reducing selection of normal simulation running conditions and increasing selection of abnormal or accident simulation running conditions, so as to improve test coverage of the gas turbine control system; Obtaining a simulation model corresponding to the gas turbine; Controlling the simulation model to run under the simulation running conditions, the simulation running modes and the simulation atmospheric environments, so as to obtain a plurality of running data generated by the simulation model running under the simulation running conditions, the simulation running modes and the simulation atmospheric environments; Controlling the gas turbine control system corresponding to the gas turbine to process measurement values of analog sensors collecting each running data, so as to obtain a plurality of control instructions corresponding to each measurement value, comprising: obtaining measurement values of analog sensors collecting each running data, and converting each measurement value into a state signal receivable by the gas turbine control system; controlling the gas turbine control system to generate a plurality of control instructions corresponding to each measurement value based on the state signal; Feeding back each control instruction to an analog actuating mechanism corresponding to the simulation model, so as to obtain a plurality of execution results of the analog actuating mechanism; Sending the plurality of execution results to the simulation model, so that the simulation model runs based on each execution result, stops running, or normally runs and runs for more than a preset time length, so as to obtain a plurality of response results of the simulation model; Obtaining a plurality of standard response results of the gas turbine under the simulation running conditions, the simulation running modes and the simulation atmospheric environments; Matching the plurality of response results with the plurality of standard response results, so as to obtain a matching degree between the plurality of response results and the plurality of standard response results; In a case where the matching degree is greater than or equal to a preset matching threshold, determining that the gas turbine control system is reliable.

2. The method of claim 1, wherein, The feeding back each control instruction to an analog actuating mechanism corresponding to the simulation model, so as to obtain a plurality of execution results of the analog actuating mechanism, comprises: Converting each control instruction into an execution signal receivable by the analog actuating mechanism; Controlling the analog actuating mechanism to generate a plurality of execution results corresponding to the execution signal based on the execution signal.

3. An intelligent test device for a gas turbine control system, characterized by Wherein, The device comprises: A first obtaining module for obtaining simulation running conditions, simulation running modes and simulation atmospheric environments corresponding to the gas turbine at a preset probability, the simulation running conditions, the simulation running modes and the simulation atmospheric environments being randomly selected according to the preset probability, the preset probability being a probability of reducing selection of normal simulation running conditions and increasing selection of abnormal or accident simulation running conditions, so as to improve test coverage of the gas turbine control system; A second obtaining module is configured to obtain a simulation model corresponding to the gas turbine; A first control module is configured to control the simulation model to run under the simulation running condition, the simulation running mode and the simulation atmospheric environment, so as to obtain a plurality of running data generated by the simulation model running under the simulation running condition, the simulation running mode and the simulation atmospheric environment; A second control module is configured to control a gas turbine control system corresponding to the gas turbine to process measurement values of analog sensors collecting the running data, so as to obtain a plurality of control instructions corresponding to the measurement values, including: obtaining the measurement values of the analog sensors collecting the running data, and converting the measurement values into state signals receivable by the gas turbine control system; controlling the gas turbine control system to generate a plurality of control instructions corresponding to the measurement values based on the state signals; A first feedback module is configured to feed back the control instructions to analog actuators corresponding to the simulation model, so as to obtain a plurality of execution results of the analog actuators; A second feedback module is configured to send the execution results to the simulation model, so that the simulation model runs based on the execution results, stops running, or normally runs and the running time of the simulation model is longer than a preset time, so as to obtain a plurality of response results of the simulation model; A determination module is configured to obtain a plurality of standard response results of the gas turbine under the simulation running condition, the simulation running mode and the simulation atmospheric environment; match the response results and the standard response results, so as to obtain a matching degree between the response results and the standard response results; and determine that the gas turbine control system is reliable in a case where the matching degree is greater than or equal to a preset matching threshold.

4. The apparatus of claim 3, wherein, The first feedback module is specifically configured to: convert the control instructions into execution signals receivable by the analog actuators; and control the analog actuators to generate a plurality of execution results corresponding to the execution signals based on the execution signals.

5. An electronic device, comprising: The method comprises: a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the intelligent testing method of the gas turbine control system according to any one of claims 1-2.

6. A computer-readable storage medium having stored thereon a computer program, characterized in that, The program is executed by the processor to implement the intelligent testing method of the gas turbine control system according to any one of claims 1-2.

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