Integrated test system of gas turbine control system

Abstract

The invention discloses an integrated test system of a gas turbine control system, a first gas turbine control system controls operation of a gas turbine based on a control strategy to obtain first operation data and first performance parameters, and a second gas turbine digital twin model is controlled to operate by a second gas turbine twin device based on the control strategy to obtain second operation data and second performance parameters. The gas turbine control system verification analysis device generates model correction parameters according to the first operation data and the second operation data, and the first gas turbine digital twin device updates model parameters of the first gas turbine digital twin model according to the model correction parameters; and the second gas turbine control system controls the updated first gas turbine twin device to operate based on the control strategy so as to obtain a second performance parameter, and the gas turbine control system verification analysis device optimizes the second gas turbine control system according to the first performance parameter and the second performance parameter.

Description

Technical Field

[0001] The invention relates to the technical field of integrated testing, and in particular to an integrated testing system for a gas turbine control system. Background Art

[0002] The gas turbine control system is the central nervous system of the gas turbine and determines the safe and stable operation of the gas turbine. Therefore, it is necessary to conduct a comprehensive test of the gas turbine control system in terms of software and hardware integration to determine the stability and reliability of the gas turbine control system.

[0003] In the related art, software-in-the-loop or hardware-in-the-loop simulation test verification or semi-physical test or on-site debugging test is used to perform function and performance testing. However, software-in-the-loop cannot test the control system hardware; hardware-in-the-loop and semi-physical tests cannot test the control system hardware based on the actual operating conditions of the gas turbine; and on-site debugging tests are prone to equipment damage due to control system defects. Based on this, the above-mentioned prior art cannot achieve long-term automated copy machine testing of the integrated software and hardware of the gas turbine control system, and thus cannot fully verify the reliability and stability of the control system. Summary of the invention

[0004] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0005] To this end, the present invention proposes an integrated test system for a gas turbine control system, which can realize long-term automated copy machine testing of the integrated hardware and software of the gas turbine control system, with a wide range of test conditions and a long test time period, so that the gas turbine control system that passes the test has high reliability and stability and can be directly applied to the actual production of gas turbines.

[0006] To achieve the above-mentioned object, the present invention proposes, on one hand, an integrated test system for a gas turbine control system, the system comprising a first gas turbine control system, a second gas turbine control system, a first gas turbine twin device, a second gas turbine twin device, and a gas turbine control system verification and analysis device, the first gas turbine twin device at least comprising: a first gas turbine digital twin model, the second gas turbine twin device at least comprising: a second gas turbine digital twin model, wherein,

[0007] The first gas turbine control system is used to obtain a control strategy, control the operation of the gas turbine based on the control strategy to obtain first operating data, send the control strategy to the second gas turbine twin device, and send the first operating data and first performance parameter to the gas turbine control system verification and analysis device;

[0008] The second gas turbine twin device is used to receive the control strategy sent by the first gas turbine control system, and control the operation of the second gas turbine digital twin model based on the control strategy to obtain second operation data, and send the second operation data to the gas turbine control system verification and analysis device;

[0009] The gas turbine control system verification and analysis device is used to generate a model correction parameter based on the first operating data and the second operating data, and send the model correction parameter to the second gas turbine twin device and the first gas turbine twin device;

[0010] The first gas turbine twin device is used to update the model parameters of the first gas turbine digital twin model according to the model correction parameters, and control the operation of the updated first gas turbine digital twin model based on the control strategy;

[0011] The second gas turbine control system is used to obtain the control strategy, control the operation of the updated first gas turbine twin device based on the control strategy to obtain second performance parameters, and send the second performance parameters to the gas turbine control system verification and analysis device, and then the gas turbine control system verification and analysis device optimizes the second gas turbine control system according to the first performance parameters and the second performance parameters.

[0012] The integrated test system of the gas turbine control system according to the embodiment of the present invention may also have the following additional technical features:

[0013] In one embodiment of the present invention, the gas turbine control system verification and analysis device includes a steady-state performance analysis microservice module, a dynamic performance analysis microservice module and an automatic adjustment microservice module; the generating of the model correction parameter according to the first operating data and the second operating data includes:

[0014] The steady-state performance analysis microservice module compares the first operating data with the second operating data to obtain a steady-state deviation;

[0015] The dynamic performance analysis microservice module compares the first operation data with the second operation data to obtain a dynamic deviation;

[0016] The automatic adjustment microservice module generates the model correction parameter according to the steady-state deviation and the dynamic deviation.

[0017] In one embodiment of the present invention, the gas turbine control system verification and analysis device further comprises a function and performance analysis microservice module;

[0018] The optimizing the second gas turbine control system according to the first performance parameter and the second performance parameter comprises:

[0019] The function and performance analysis microservice module compares the first performance parameter with the second performance parameter to obtain a performance parameter deviation, and optimizes the second gas turbine control system based on the performance parameter deviation.

[0020] In one embodiment of the present invention, the gas turbine control system verification and analysis device includes an early warning microservice module, a deviation early warning microservice module, a database, an encapsulation microservice module, an edge computing device deployment microservice module and a container module, wherein:

[0021] The early warning microservice module is used to generate early warning information when the steady-state deviation is greater than the steady-state deviation threshold, and / or the dynamic deviation is greater than the dynamic deviation threshold;

[0022] The deviation warning microservice module is used to generate an alarm message when the performance parameter deviation is greater than the performance parameter deviation threshold;

[0023] The database is used to store the steady-state deviation, the dynamic deviation, the performance parameter deviation, the alarm information and the early warning information;

[0024] The packaging microservice module is used to package the model correction parameters and / or the first gas turbine digital twin model and / or the second gas turbine digital twin model into a corresponding container;

[0025] The container module is used to store the packaged containers;

[0026] The edge computing device deploys a microservice module for obtaining corresponding containers from the container module and distributing the containers to the first gas turbine twin device and the second gas turbine digital twin device.

[0027] In one embodiment of the present invention, the first gas turbine control system further includes: a first engineer station, a first operation station, a first history station, a first OPC station, a first control module and an IO module, and the first control module includes: a first control program, wherein:

[0028] The first engineer station is used to maintain the first control program;

[0029] The first operating station is used to control the start and stop of the gas turbine;

[0030] The first historical station is used to store historical operating data of the gas turbine;

[0031] The first OPC station is used for data transmission between the gas turbine control system verification and analysis device and the first gas turbine control system;

[0032] The first control module is used to control the first control program to execute the first control strategy to control the operation of the gas turbine;

[0033] The IO module is used for data transmission between the first gas turbine control system and the gas turbine.

[0034] In one embodiment of the present invention, the second gas turbine control system further includes: a second engineer station, a second operation station, a second history station, a second OPC station, a second control module and an IO module, and the second control module includes: a second control program, wherein:

[0035] The second engineer station is used to maintain the second control program;

[0036] The second operating station is used to control the start and stop of the first gas turbine twin device;

[0037] The second historical station is used to store historical operating data of the first gas turbine twin device;

[0038] The second OPC station is used for data transmission between the gas turbine control system verification and analysis device and the second gas turbine control system;

[0039] The second control module is used to control the second control program to execute the first control strategy and / or the second control strategy to control the operation of the first gas turbine twin device;

[0040] The IO module is used for data transmission between the second gas turbine control system and the first gas turbine twin device.

[0041] In one embodiment of the present invention, the first gas turbine twin device further comprises a first real-time simulation device, a second real-time simulation device and a third real-time simulation device;

[0042] The first real-time simulation device comprises: a first host digital twin model of the gas turbine;

[0043] The second real-time simulation device comprises: a first auxiliary machine digital twin model of the gas turbine;

[0044] The third real-time simulation device includes: a first electrical digital twin model of the gas turbine, wherein the first main engine digital twin model, the first auxiliary engine digital twin model and the first electrical digital twin model constitute the first gas turbine digital twin model.

[0045] In one embodiment of the present invention, the first real-time simulation device further includes a real-time calculation and signal conversion sub-device and a signal conditioning sub-device;

[0046] The real-time computing and signal conversion sub-device is used to run the first host digital twin model and signal conversion of the gas turbine;

[0047] The signal conditioning sub-device is used to achieve electrical signal matching between the second gas turbine control system and the real-time calculation and signal conversion sub-device.

[0048] In one embodiment of the present invention, the second gas turbine twin device further includes a first edge computing device, a second edge computing device, a third edge computing device, and a third OPC station;

[0049] The first edge computing device includes: a second host digital twin model of the gas turbine

[0050] The second edge computing device includes: a second auxiliary machine digital twin model of the gas turbine;

[0051] The third edge computing device includes: a second electrical digital twin model of the gas turbine, wherein the second main engine digital twin model, the second auxiliary engine digital twin model and the second electrical digital twin model constitute the second gas turbine digital twin model;

[0052] The third OPC station is used for data transmission between the gas turbine control system verification and analysis device and the second gas turbine twin device.

[0053] In one embodiment of the present invention, the system further comprises: a switch; wherein,

[0054] The switch is used for data transmission between the first gas turbine control system, the second gas turbine control system and the first gas turbine twin device.

[0055] In the integrated test system of the gas turbine control system of the embodiment of the present invention, the system includes a first gas turbine control system, a second gas turbine control system, a first gas turbine twin device, a second gas turbine twin device, and a gas turbine control system verification and analysis device. The first gas turbine twin device at least includes: a first gas turbine digital twin model, and the second gas turbine twin device at least includes: a second gas turbine digital twin model, wherein the first gas turbine control system is used to obtain a control strategy, control the operation of the gas turbine based on the control strategy to obtain first operating data, and send the control strategy to the second gas turbine twin device, and send the first operating data and first performance parameters to the gas turbine control system verification and analysis device; the second gas turbine twin device is used to accept the control strategy sent by the first gas turbine control system, and control the operation of the second gas turbine digital twin model based on the control strategy to obtain the first The gas turbine control system verification and analysis device is used to generate model correction parameters according to the first and second operation data, and send the model correction parameters to the second gas turbine twin device and the first gas turbine twin device; the first gas turbine twin device is used to update the model parameters of the first gas turbine digital twin model according to the model correction parameters, and control the operation of the updated first gas turbine digital twin model based on the control strategy; the second gas turbine control system is used to obtain the control strategy, control the operation of the updated first gas turbine twin device based on the control strategy to obtain the second performance parameter, and send the second performance parameter to the gas turbine control system verification and analysis device, and then the gas turbine control system verification and analysis device optimizes the second gas turbine control system according to the first performance parameter and the second performance parameter. Therefore, the present invention can realize the long-term automatic copy machine test of the integrated hardware and software of the gas turbine control system, with a wide range of test conditions and a long test time period, so that the gas turbine control system that passes the test has high reliability and stability, and can be directly applied to the actual production of gas turbines.

[0056] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0058] Figure 1 is a schematic diagram of an integrated test system for a gas turbine control system according to an embodiment of the present invention;

[0059] Figure 2It is a structural schematic diagram of a first real-time simulation device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0060] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0061] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0062] The integrated test system of a gas turbine control system according to an embodiment of the present invention will be described below with reference to the accompanying drawings.

[0063] Figure 1 Schematic diagram of an integrated test system for a gas turbine control system according to an embodiment of the present invention.

[0064] like Figure 1 As shown, the integrated test system 10 of the gas turbine control system includes:

[0065] A first gas turbine control system 101, a second gas turbine control system 102, a first gas turbine twin device 103, a second gas turbine twin device 104, and a gas turbine control system verification and analysis device 105. The first gas turbine twin device 103 at least includes: a first gas turbine digital twin model, and the second gas turbine twin device 104 at least includes: a second gas turbine digital twin model, wherein:

[0066] The first gas turbine control system 101 is used to obtain a control strategy, control the gas turbine operation based on the control strategy to obtain first operating data, send the control strategy to the second gas turbine twin device, and send the first operating data and first performance parameters to the gas turbine control system verification and analysis device.

[0067] The above control strategy is a control strategy used for testing the first gas turbine control system.

[0068] Furthermore, after the first gas turbine control system acquires the control strategy, it can control the actual gas turbine operation through the control strategy. When the gas turbine operates based on the control strategy, the corresponding data generated by the gas turbine during operation is the first operation data, and the first operation data can be, for example, effective power, fuel consumption rate, etc., without limitation. At the same time, the first gas turbine control system can also generate first performance parameters, and the first performance parameters can include performance data and system data, such as power, screen outlet temperature, network load rate, packet loss rate, controller parameters, IO module parameters, etc., without limitation.

[0069] Optionally, in some embodiments, the first gas turbine control system 101 further includes: a first engineer station 1011, a first operation station 1012, a first history station 1013, a first OLE for process control (OPC) station 1014, a first control module 1015 and an IO module 1016, wherein the first control module includes: a first control program, wherein the first engineer station is used to maintain the first control program; the first operation station is used to control the start and stop of the gas turbine; the first history station is used to store the historical operation data of the gas turbine; the first OPC station is used to transmit data between the gas turbine control system verification and analysis device and the first gas turbine control system; the first control module is used to control the first control program to execute the first control strategy to control the operation of the gas turbine; and the IO module is used to transmit data between the first gas turbine control system and the gas turbine. Based on this, the first gas turbine control system can send the control strategy to the gas turbine based on the above-mentioned IO module, and send the first operation data and the first performance parameter to the gas turbine control system verification and analysis device based on the first OPC station.

[0070] Optionally, the integrated test system 10 of the gas turbine control system further includes: a switch 106 ; wherein the switch 106 is used for data transmission between the first gas turbine control system 101 , the second gas turbine control system 102 and the first gas turbine twin device 103 .

[0071] The first gas turbine control system 101 may send the control strategy to the second gas turbine twin device 104 and send the control strategy to the second gas turbine control system 102 through the switch 106 .

[0072] The second gas turbine twin device 104 is used to receive the control strategy sent by the first gas turbine control system, and control the operation of the second gas turbine digital twin model based on the control strategy to obtain second operating data, and send the second operating data to the gas turbine control system verification and analysis device.

[0073] Among them, when the digital twin model of the second gas turbine is controlled to operate based on the control strategy, the corresponding data generated by the gas turbine during the operation is the second operating data. The second operating data can be, for example: effective power, fuel consumption rate, etc., without limitation.

[0074] In addition, in some embodiments, the second gas turbine twin device 104 may include a first edge computing device 1041, a second edge computing device 1042, a third edge computing device 1043 and a third OPC station 1044, wherein the first edge computing device 1041 includes a second main engine digital twin model of the gas turbine, the second edge computing device 1042 includes a second auxiliary engine digital twin model of the gas turbine, and the third edge computing device 1043 includes a second electrical digital twin model of the gas turbine, wherein the second main engine digital twin model, the second auxiliary engine digital twin model and the second electrical digital twin model constitute a second gas turbine digital twin model; the third OPC station 1044 is used for data transmission between the gas turbine control system verification and analysis device and the second gas turbine twin device.

[0075] Among them, the digital twin model of the second gas turbine and the digital twin model of the first gas turbine should adopt mechanism modeling, data-driven modeling and other methods to fully simulate the actual gas turbine, and establish the second gas turbine host model and the first gas turbine host model, including compressor model, combustion chamber model, turbine model, rotor model, etc.; the auxiliary machine model of the second gas turbine and the auxiliary machine model of the first gas turbine should be established by mechanism modeling, logical modeling and other methods, including fuel system model, lubricating oil system model, control oil system model, intake system model, etc.; the electrical model of the second gas turbine and the electrical model of the first gas turbine should be established by mechanism modeling, logical modeling and other methods, including Sequential Function Chart (SFC) system model, excitation system model, generator system model, etc. The digital twin model of the second gas turbine and the digital twin model of the first gas turbine include the full process system and full IO signal of the gas turbine.

[0076] The gas turbine control system verification and analysis device 105 is used to generate model correction parameters according to the first operating data and the second operating data, and send the model correction parameters to the second gas turbine twin device and the first gas turbine twin device.

[0077] Among them, the model correction parameters can be used to correct the model parameters of the first gas turbine digital twin model and / or the second gas turbine digital twin model in the first gas turbine twin device and / or the second gas turbine twin device.

[0078] In some embodiments, the gas turbine control system verification and analysis device may further include a steady-state performance analysis microservice module 1051, a dynamic performance analysis microservice module 1052, and an automatic adjustment microservice module 1053. And, the above-mentioned generation of model correction parameters according to the first operation data and the second operation data includes: the steady-state performance analysis microservice module compares the first operation data and the second operation data to obtain a steady-state deviation; the dynamic performance analysis microservice module compares the first operation data and the second operation data to obtain a dynamic deviation; the automatic adjustment microservice module generates the model correction parameters according to the steady-state deviation and the dynamic deviation.

[0079] In some embodiments, a gas turbine twin model adaptive correction method is used to ensure that the gas turbine digital twin model has a high accuracy with the actual gas turbine. According to the deviation between the second gas turbine digital twin model and the key parameters of the actual gas turbine, the extended Kalman filter method is used to obtain the correction parameters of the second gas turbine digital twin model, including the compressor flow characteristic correction coefficient, the compressor efficiency characteristic correction coefficient, the combustion chamber efficiency correction coefficient, the combustion chamber pressure drop correction coefficient, the turbine flow characteristic correction coefficient, the turbine efficiency characteristic correction coefficient, the turbine cooling extraction flow correction coefficient, the mechanical efficiency correction coefficient, etc., without limitation.

[0080] Optionally, in some embodiments, the gas turbine control system verification and analysis device 105 further includes: an early warning microservice module 1054, a deviation early warning microservice module 1055, a database 1056, an encapsulation microservice module 1057, an edge computing device deployment microservice module 1058 and a container module 1059, wherein the early warning microservice module 1054 is used to generate early warning information when the steady-state deviation is greater than the steady-state deviation threshold and / or the dynamic deviation is greater than the dynamic deviation threshold; the deviation early warning microservice module 1055 is used to generate early warning information when the performance parameter deviation is greater than the performance parameter deviation threshold. In the event of an error, an alarm message is generated; a database 1056 is used to store steady-state deviations, dynamic deviations, performance parameter deviations, alarm messages and early warning messages; a packaging microservice module 1057 is used to package model correction parameters and / or the first gas turbine digital twin model and / or the second gas turbine digital twin model into corresponding containers; a container module 1058 is used to store the packaged containers; an edge computing device deployment microservice module 1059 is used to obtain the corresponding container from the container module and distribute the container to the first gas turbine twin device and the second gas turbine digital twin device.

[0081] Among them, the early warning information is used to prompt that the gas turbine characteristics represented by the digital twin model of the second gas turbine are different from the actual gas turbine.

[0082] Furthermore, in some embodiments, the operation of the actual gas turbine and the second gas turbine digital twin model device can be controlled separately based on the control strategy to obtain corresponding operation data, and then the deviation between the operation data is combined to obtain the model parameters for correcting the second gas turbine digital twin model, and the model correction parameters are updated to the gas turbine main engine variable parameter data container and the gas turbine auxiliary engine variable parameter data container in the container module through the encapsulation microservice module, and then the model correction parameters are sent to the second gas turbine twin device and the first gas turbine twin device, so that the second gas turbine digital twin model and the first gas turbine digital twin model can be adjusted based on the model correction parameters, so that the adjusted second gas turbine digital twin model and the first gas turbine digital twin model can be consistent with the characteristics of the actual gas turbine, thereby avoiding the deviation of the test caused by the inconsistency between the second gas turbine digital twin model and the first gas turbine digital twin model and the actual gas turbine.

[0083] Furthermore, the first gas turbine digital twin model and the second gas turbine digital twin model can be synchronized by container deployment and distribution to ensure that the second gas turbine digital twin model and the first gas turbine digital twin model can always be synchronized. Among them, when the digital twin model structure changes, the offline gas turbine digital twin model is modified, and the model is respectively encapsulated into a gas turbine main engine model container, a gas turbine auxiliary engine model container, and a gas turbine electrical model container, and then distributed to each gas turbine control system twin device; when the gas turbine digital twin model modeling parameters change, the modeling parameters can be encapsulated into a gas turbine main engine model modeling data container, a gas turbine auxiliary engine model modeling data container, and a gas turbine electrical model modeling data container, and then distributed; when the gas turbine digital twin model correction parameters change, the correction parameters are encapsulated into a gas turbine main engine correction parameter data container and a gas turbine auxiliary engine correction parameter data container, and then distributed. Through the above container deployment and distribution method, when the model structure or model modeling parameters or model correction parameters change, the digital twin model can be updated independently. Furthermore, the corresponding gas turbine digital twin models in the first gas turbine twin device and the second gas turbine twin device always come from the same model file, the same set of model data, and are distributed and deployed simultaneously.

[0084] The first gas turbine twin device 103 is used to update the model parameters of the first gas turbine digital twin model according to the model correction parameters, and control the operation of the updated first gas turbine digital twin model based on the control strategy.

[0085] In some embodiments, the first gas turbine twin device 103 also includes a first real-time simulation device 1031, a second real-time simulation device 1032 and a third real-time simulation device 1033, wherein the first real-time simulation device includes a first main engine digital twin model of the gas turbine; the second real-time simulation device includes a first auxiliary engine digital twin model of the gas turbine; the third real-time simulation device includes a first electrical digital twin model of the gas turbine, wherein the first main engine digital twin model, the first auxiliary engine digital twin model and the first electrical digital twin model constitute the first gas turbine digital twin model.

[0086] The first real-time simulation device 1031 further includes a real-time calculation and signal conversion sub-device 10311 and a signal conditioning sub-device 10312 to realize the interaction of electrical signals between the first gas turbine digital twin model and the second gas turbine control system. Specifically, the real-time calculation and signal conversion sub-device is used to operate the first main engine digital twin model of the gas turbine and signal conversion, and the signal conditioning sub-device is used to realize the electrical signal matching between the second gas turbine control system and the real-time calculation and signal conversion sub-device.

[0087] as well as, Figure 2 A schematic diagram of the structure of a first real-time simulation device provided by an embodiment of the present invention. Figure 2 As shown, the real-time computing and signal conversion sub-device can adopt real-time simulation hardware equipment based on NI or DSPACE, including a controller and a signal board. The first host digital twin model of the gas turbine runs in the controller. The signal board is used to realize D / A and A / D conversion of the signal, such as AI board, AO board, DI board, DO board, RTD board, TC board, SPD speed board, LVDT board. The signal covers all signal types of the gas turbine.

[0088] In some embodiments, the structures of the first gas turbine twin device and the second gas turbine twin device are different, but the structures of the corresponding gas turbine digital twin models are the same.

[0089] The second gas turbine control system 102 is used to obtain a control strategy, control the operation of the updated first gas turbine twin device based on the control strategy to obtain a second performance parameter, and send the second performance parameter to the gas turbine control system verification and analysis device, which then optimizes the second gas turbine control system based on the first performance parameter and the second performance parameter.

[0090] The second performance parameter may be system data after the second gas turbine control system controls the updated first gas turbine twin device to operate based on the control strategy.

[0091] In some embodiments, the second gas turbine control system 102 also includes a second engineer station 1021, a second operation station 1022, a second history station 1023, a second OPC station 1024, a second control module 1025 and an IO module 1026, wherein the second control module includes a second control program; a second engineer station for maintaining the second control program; a second operation station for controlling the start and stop of the first gas turbine twin device; a second history station for storing historical operation data of the first gas turbine twin device; a second OPC station for transmitting data between the gas turbine control system verification and analysis device and the second gas turbine control system; a second control module for controlling the second control program to execute a control strategy to control the operation of the first gas turbine twin device; and an IO module for transmitting data between the second gas turbine control system and the first gas turbine twin device.

[0092] Optionally, the gas turbine control system verification and analysis device further includes a function and performance analysis microservice module 10510. Optimizing the second gas turbine control system according to the first performance parameter and the second performance parameter includes: the function and performance analysis microservice module compares the first performance parameter and the second performance parameter to obtain a performance parameter deviation, and optimizing the second gas turbine control system based on the performance parameter deviation.

[0093] Specifically, when the performance parameter deviation exceeds the performance parameter deviation threshold, an alarm will be issued through the function and performance analysis microservice module, and the first performance parameter of the first gas turbine control system and the second performance parameter of the second gas turbine control system at the current moment will be recorded through the database. The function and performance deviation of the second gas turbine control system will be analyzed and optimized offline, and then the second gas turbine control system will continue to be tested until the various functions and performance indicators of the second gas turbine control system meet the requirements, and the hardware and software integration test of the gas turbine control system will be completed.

[0094] In the integrated test system of the gas turbine control system proposed in the present invention, the system includes a first gas turbine control system, a second gas turbine control system, a first gas turbine twin device, a second gas turbine twin device, and a gas turbine control system verification and analysis device. The first gas turbine twin device at least includes: a first gas turbine digital twin model, and the second gas turbine twin device at least includes: a second gas turbine digital twin model, wherein the first gas turbine control system is used to obtain a control strategy, control the operation of the gas turbine based on the control strategy to obtain first operating data, and send the control strategy to the second gas turbine twin device, and send the first operating data and first performance parameters to the gas turbine control system verification and analysis device; the second gas turbine twin device is used to accept the control strategy sent by the first gas turbine control system, and control the operation of the second gas turbine digital twin model based on the control strategy to obtain the second The gas turbine control system verification and analysis device is used to generate model correction parameters according to the first operation data and the second operation data, and send the model correction parameters to the second gas turbine twin device and the first gas turbine twin device; the first gas turbine twin device is used to update the model parameters of the first gas turbine digital twin model according to the model correction parameters, and control the operation of the updated first gas turbine digital twin model based on the control strategy; the second gas turbine control system is used to obtain the control strategy, control the operation of the updated first gas turbine twin device based on the control strategy to obtain the second performance parameter, and send the second performance parameter to the gas turbine control system verification and analysis device, and then the gas turbine control system verification and analysis device optimizes the second gas turbine control system according to the first performance parameter and the second performance parameter. Therefore, the present invention can realize the long-term automatic copy machine test of the integrated hardware and software of the gas turbine control system, with a wide range of test conditions and a long test time period, so that the gas turbine control system that passes the test has high reliability and stability, and can be directly applied to the actual production of gas turbines.

[0095] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps recorded in this disclosure can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solutions disclosed in this disclosure can be achieved, and this document does not limit this.

[0096] The above specific implementations do not constitute a limitation on the protection scope of the present disclosure. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present disclosure shall be included in the protection scope of the present disclosure.

Claims

1. An integrated test system for a gas turbine control system, characterized in that: The system includes a first gas turbine control system, a second gas turbine control system, a first gas turbine twin device, a second gas turbine twin device, and a gas turbine control system verification and analysis device, wherein the first gas turbine twin device at least includes: a first gas turbine digital twin model, and the second gas turbine twin device at least includes: a second gas turbine digital twin model, wherein: The first gas turbine control system is used to obtain a control strategy, control the operation of the gas turbine based on the control strategy to obtain first operating data, send the control strategy to the second gas turbine twin device, and send the first operating data and first performance parameter to the gas turbine control system verification and analysis device; The second gas turbine twin device is used to receive the control strategy sent by the first gas turbine control system, and control the operation of the second gas turbine digital twin model based on the control strategy to obtain second operation data, and send the second operation data to the gas turbine control system verification and analysis device; The gas turbine control system verification and analysis device is used to generate a model correction parameter based on the first operating data and the second operating data, and send the model correction parameter to the second gas turbine twin device and the first gas turbine twin device; The first gas turbine twin device is used to update the model parameters of the first gas turbine digital twin model according to the model correction parameters, and control the operation of the updated first gas turbine digital twin model based on the control strategy; The second gas turbine control system is used to obtain the control strategy, control the operation of the updated first gas turbine twin device based on the control strategy to obtain second performance parameters, and send the second performance parameters to the gas turbine control system verification and analysis device, and then the gas turbine control system verification and analysis device optimizes the second gas turbine control system according to the first performance parameters and the second performance parameters.

2. The system according to claim 1, characterized in that The gas turbine control system verification and analysis device includes a steady-state performance analysis microservice module, a dynamic performance analysis microservice module and an automatic adjustment microservice module; The generating of the model correction parameter according to the first operation data and the second operation data comprises: The steady-state performance analysis microservice module compares the first operating data with the second operating data to obtain a steady-state deviation; The dynamic performance analysis microservice module compares the first operation data with the second operation data to obtain a dynamic deviation; The automatic adjustment microservice module generates the model correction parameter according to the steady-state deviation and the dynamic deviation.

3. The system according to claim 1, characterized in that The gas turbine control system verification and analysis device also includes a function and performance analysis microservice module; The optimizing the second gas turbine control system according to the first performance parameter and the second performance parameter comprises: The function and performance analysis microservice module compares the first performance parameter with the second performance parameter to obtain a performance parameter deviation, and optimizes the second gas turbine control system based on the performance parameter deviation.

4. The system according to any one of claims 2-3, characterized in that: The gas turbine control system verification and analysis device includes an early warning microservice module, a deviation early warning microservice module, a database, an encapsulation microservice module, an edge computing device deployment microservice module and a container module, wherein: The early warning microservice module is used to generate early warning information when the steady-state deviation is greater than the steady-state deviation threshold, and / or the dynamic deviation is greater than the dynamic deviation threshold; The deviation warning microservice module is used to generate an alarm message when the performance parameter deviation is greater than the performance parameter deviation threshold; The database is used to store the steady-state deviation, the dynamic deviation, the performance parameter deviation, the alarm information and the early warning information; The packaging microservice module is used to package the model correction parameters and / or the first gas turbine digital twin model and / or the second gas turbine digital twin model into a corresponding container; The container module is used to store the packaged containers; The edge computing device deploys a microservice module for obtaining corresponding containers from the container module and distributing the containers to the first gas turbine twin device and the second gas turbine digital twin device.

5. The system according to claim 1, characterized in that The first gas turbine control system further includes: a first engineer station, a first operation station, a first history station, a first OPC station, a first control module and an IO module. The first control module includes: a first control program, wherein: The first engineer station is used to maintain the first control program; The first operating station is used to control the start and stop of the gas turbine; The first historical station is used to store historical operating data of the gas turbine; The first OPC station is used for data transmission between the gas turbine control system verification and analysis device and the first gas turbine control system; The first control module is used to control the first control program to execute the control strategy to control the operation of the gas turbine; The IO module is used for data transmission between the first gas turbine control system and the gas turbine.

6. The system according to claim 1, characterized in that The second gas turbine control system further includes: a second engineer station, a second operation station, a second history station, a second OPC station, a second control module and an IO module. The second control module includes: a second control program, wherein: The second engineer station is used to maintain the second control program; The second operating station is used to control the start and stop of the first gas turbine twin device; The second historical station is used to store historical operating data of the first gas turbine twin device; The second OPC station is used for data transmission between the gas turbine control system verification and analysis device and the second gas turbine control system; The second control module is used to control the second control program to execute the control strategy to control the operation of the first gas turbine twin device; The IO module is used for data transmission between the second gas turbine control system and the first gas turbine twin device.

7. The system according to claim 1, characterized in that The first gas turbine twin device also includes a first real-time simulation device, a second real-time simulation device and a third real-time simulation device; The first real-time simulation device comprises: a first host digital twin model of the gas turbine; The second real-time simulation device comprises: a first auxiliary machine digital twin model of the gas turbine; The third real-time simulation device includes: a first electrical digital twin model of the gas turbine, wherein the first main engine digital twin model, the first auxiliary engine digital twin model and the first electrical digital twin model constitute the first gas turbine digital twin model.

8. The system according to claim 7, characterized in that The first real-time simulation device also includes a real-time calculation and signal conversion sub-device and a signal conditioning sub-device; The real-time computing and signal conversion sub-device is used to run the first host digital twin model and signal conversion of the gas turbine; The signal conditioning sub-device is used to achieve electrical signal matching between the second gas turbine control system and the real-time calculation and signal conversion sub-device.

9. The system according to claim 1, characterized in that The second gas turbine twin device also includes a first edge computing device, a second edge computing device, a third edge computing device and a third OPC station; The first edge computing device includes: a second host digital twin model of the gas turbine The second edge computing device includes: a second auxiliary machine digital twin model of the gas turbine; The third edge computing device includes: a second electrical digital twin model of the gas turbine, wherein the second main engine digital twin model, the second auxiliary engine digital twin model and the second electrical digital twin model constitute the second gas turbine digital twin model; The third OPC station is used for data transmission between the gas turbine control system verification and analysis device and the second gas turbine twin device.

10. The system according to any one of claims 1 to 9, characterized in that: The system further includes: a switch; wherein, The switch is used for data transmission between the first gas turbine control system, the second gas turbine control system and the first gas turbine twin device.

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