A virtual-real combined cascade test method and system

Abstract

The application provides a virtual-real combined cascade test method and system, and the method comprises the following steps: S1, determining a modeling ratio according to characteristic geometric parameters of an original blade of a test piece, and modeling original blade profiles of the test piece and characteristics of a virtual test device according to the characteristic geometric parameters of the original blade and the virtual test device and the modeling ratio, to generate multiple groups of virtual blade rows; S2, placing the blade rows at a center position of a flow channel of the virtual test device, and obtaining different test piece layout schemes according to different blade row installation angles; S3, modeling according to the different test piece layout schemes, obtaining a structural layout scheme and an aerodynamic scheme of the test piece through simulation analysis, and determining a test boundary pressure of the test piece; and S4, generating an opening state of a valve in the virtual test device under each test state according to the test boundary pressure, and forming a test state control scheme. The application improves the cascade test efficiency and quality, and meets the needs of blade profile verification and algorithm checking.

Description

Technical Field

[0001] This invention relates to the field of aero-engine and gas turbine testing technology, specifically to a method and system for combined virtual and real blade cascade testing. Background Technology

[0002] Planar blade cascade testing is a fundamental mechanism research test for aero-engines and gas turbines, used to verify and validate simulation software and algorithms. The test requires performance tests under various operating conditions with Reynolds number, Mach number, and angle of attack as variables. The amount of testing is large, and simply increasing the number of physical test devices to solve the supply and demand contradiction is no longer sufficient to meet the research needs of the current rapid development. On the other hand, the development of digital technology has provided new technical approaches to improve efficiency. At present, the domestic and foreign aero-engine industry has not yet formed sufficiently mature digital testing methods and technologies, and has been relying on physical testing for performance verification in the research and development model. Although the introduction of simulation technology to form a "design-simulation-test-optimization" technical approach has shortened the aero-engine development cycle, it still cannot solve the contradiction between the current stage of large-scale engine development and customized agile research and development needs. Therefore, in addition to using traditional CAE software to simulate the aero-engine aerodynamic design and prediction, the simulation coverage needs are constantly increasing, and the requirements for the realism of the depiction of the real engine system are also constantly increasing. Therefore, domestic scholars have carried out research on multi-system, strongly nonlinear coupled model modeling and simulation technology of pipelines, fuel regulation and other systems, with a focus on specific problems, using modeling tools such as AMEsim and Simulink, which has improved the effectiveness of system use.

[0003] At the aero-engine design level, in recent years, industry scholars have also carried out a series of studies based on this technology and framework, clarifying the collaborative relationship between digital main line, digital twin, and digital system model. In the management of the entire life cycle of aero-engines, they have realized the construction of simulation system models for design, manufacturing, testing, and operation and maintenance, and made breakthroughs in a series of key technologies such as lightweight modeling technology, model self-correction, and full-system model verification database technology. However, there is still a lack of integrated verification in specific application scenarios. Moreover, due to the large amount of testing demand and the difficulty in constructing inlet uniformity in the environment, blade cascade testing requires a large amount of simulation calculation and a large amount of manpower for state control, and the testing efficiency urgently needs to be improved. Summary of the Invention

[0004] In view of this, embodiments of this application provide a method and system for combined virtual and real blade cascade testing to solve the problems of low testing efficiency and long testing cycle in existing blade cascade testing.

[0005] This application provides the following technical solution: a method for combined virtual and real blade cascade testing, comprising the following steps:

[0006] S1. Construct a virtual test device for the blade cascade test, determine the modeling ratio based on the characteristic geometric parameters of the original blade of the test piece, and modularize the original blade shape of the test piece and the features of the virtual test device based on the characteristic geometric parameters of the original blade and the characteristic geometric parameters of the virtual test device, as well as the modeling ratio, to generate multiple sets of virtual blade rows;

[0007] S2. Place the generated blade array at the center of the flow channel of the virtual test equipment, and obtain different test specimen layout schemes according to different blade array installation angles;

[0008] S3. Model the different test specimen layout schemes to generate a virtual fluid domain, perform simulation analysis on the virtual fluid domain, obtain the structural layout scheme and aerodynamic scheme of the test specimen, and determine the test boundary pressure of the test specimen;

[0009] S4. Based on the determined test boundary pressure of the test piece, generate the valve opening state in the virtual test equipment under each test state to form a test state control scheme.

[0010] According to one embodiment of this application, the method further includes: processing and installing the physical test piece according to the structural layout scheme and pneumatic scheme of the test piece to obtain a test platform; and conducting physical tests on the test platform according to the structural layout scheme and pneumatic scheme of the test piece, as well as the test boundary pressure of the test piece.

[0011] According to one embodiment of this application, the method further includes: using the test boundary pressure of the test specimen and the test state control scheme as a benchmark, and setting the pressure deviation range as a warning range based on the test equipment risk analysis and emergency plan in the test requirements;

[0012] The test parameters in the physical test are compared with the parameters in the test state control scheme in real time, and the comparison results are matched with the warning range. If the comparison results are within the warning range, the test state control scheme is used.

[0013] According to one embodiment of this application, step S1 further includes: detecting the blade thickness based on the coordinate points of the modularized blade profile parameters, and adjusting the modularization ratio to ensure that the blade thickness and blade aspect ratio meet the test requirements.

[0014] According to one embodiment of this application, step S2 specifically includes: determining the disk angle, upper chamber length, lower chamber length, guide vane angle, and tail plate angle of the virtual test equipment based on different blade row installation angles, thereby obtaining the different test piece layout schemes.

[0015] According to one embodiment of this application, step S3, the process of simulating the virtual fluid domain includes: setting the input variables of the simulation as the length of the upper sump chamber, the length of the lower sump chamber, the angle of the guide vane, the angle of the tail plate, and the air extraction pressure in front of the guide vane; and setting the target output parameters of the simulation as the average Mach number difference, the average intake airflow angle difference, and the average intake pressure difference along the blade front line.

[0016] According to one embodiment of this application, step S3 further includes optimizing the structural layout scheme and aerodynamic scheme of the test piece according to the test requirements and the target output parameters to obtain the optimal structural layout scheme and aerodynamic scheme.

[0017] This application also provides a combined virtual and real blade cascade testing system, including:

[0018] The test specimen design platform is used to construct a virtual test device for blade cascade testing. The modularization ratio is determined based on the characteristic geometric parameters of the original blade of the test specimen. Based on the characteristic geometric parameters of the original blade and the characteristic geometric parameters of the virtual test device, as well as the modularization ratio, the original blade shape of the test specimen and the features of the virtual test device are modularized to generate multiple sets of virtual blade rows.

[0019] The test piece design platform is also used to place the generated blade array at the center of the flow channel of the virtual test equipment, and obtain different test piece layout schemes according to different blade array installation angles;

[0020] The test specimen design platform is also used to model according to the different test specimen layout schemes, generate a virtual fluid domain, perform simulation analysis on the virtual fluid domain, obtain the structural layout scheme and aerodynamic scheme of the test specimen, and determine the test boundary pressure of the test specimen;

[0021] The test control design platform is used to generate the valve opening status of the virtual test equipment under each test state according to the determined test boundary pressure of the test piece, and form a test state control scheme.

[0022] According to one embodiment of this application, the system further includes: a physical testing platform, used for processing and installing the physical test piece according to the structural layout scheme and pneumatic scheme of the test piece to obtain the testing platform; and for conducting physical tests on the testing platform according to the structural layout scheme and pneumatic scheme of the test piece, as well as the test boundary pressure of the test piece.

[0023] According to one embodiment of this application, the test control design platform is further configured to use the test boundary pressure of the test piece and the test state control scheme as a benchmark, and set the pressure deviation range as an early warning range based on the test equipment risk analysis and emergency plan in the test requirements;

[0024] The system also includes: a test data management platform, used to compare the test parameters in the physical test with the parameters in the test state control scheme in real time, match the comparison results with the warning range, and if the comparison results are within the warning range, then the test state control scheme is used.

[0025] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include: From the perspective of digital upgrading of test subjects, the embodiments of this invention propose a virtual and real combined blade cascade test method and system, which further improves the efficiency and quality of blade cascade tests, solves the problems of low test efficiency and long test cycle in existing blade cascade tests, and quickly meets the needs of blade shape verification and algorithm calibration. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is a schematic flowchart of the blade cascade test method combining virtual and real methods according to an embodiment of the present invention;

[0028] Figure 2 This is a schematic diagram of the structure of the blade cascade test system combining virtual and real elements according to an embodiment of the present invention. Detailed Implementation

[0029] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0030] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0031] like Figure 1 As shown, this embodiment of the invention provides a combined virtual and real blade cascade testing method, including the following steps:

[0032] S1. Construct a virtual test device for the blade cascade test, determine the modeling ratio based on the characteristic geometric parameters of the original blade of the test piece, and modularize the original blade shape of the test piece and the features of the virtual test device based on the characteristic geometric parameters of the original blade and the characteristic geometric parameters of the virtual test device, as well as the modeling ratio, to generate multiple sets of virtual blade rows;

[0033] S2. Place the generated blade array at the center of the flow channel of the virtual test equipment, and obtain different test specimen layout schemes according to different blade array installation angles;

[0034] S3. Model the different test specimen layout schemes to generate a virtual fluid domain, perform simulation analysis on the virtual fluid domain, obtain the structural layout scheme and aerodynamic scheme of the test specimen, and determine the test boundary pressure of the test specimen;

[0035] S4. Based on the determined test boundary pressure of the test piece, generate the valve opening state in the virtual test equipment under each test state to form a test state control scheme.

[0036] In some embodiments of the present invention, the method further includes: processing and installing the physical test piece according to the structural layout scheme and pneumatic scheme of the test piece to obtain a test platform; and conducting physical tests on the test platform according to the structural layout scheme and pneumatic scheme of the test piece, as well as the test boundary pressure of the test piece.

[0037] In practice, this also includes: storing the processing attribute parameters, sensing part information, and test information of the test piece; storing the processing attribute parameters of the test piece, such as the processing manufacturer and processing accuracy; storing the sensing part information of the test piece, such as probes and pressure gauges; storing the information of the test piece, such as test channels, measurement modules, and test displacement mechanisms; and, according to the test piece's structural layout and pneumatic scheme, processing and installing the test piece on a physical testing platform, and recording the installation status into the test data management platform for subsequent inspection and troubleshooting.

[0038] In practice, experiments are conducted using a physical testing platform, following the established experimental procedures. This includes adjusting various experimental conditions and collecting experimental data. The valve opening and corresponding boundary pressure, meeting the experimental technical requirements, are transmitted to the experimental data storage module for storage. The process also includes retrieving simulation calculation results from the experimental data storage module based on the valve status and boundary pressure conditions at the site, and displaying the valve status and post-processed flow field images in real-time on the human-machine interface of the experimental execution module.

[0039] In some embodiments of the present invention, the method further includes: using the test boundary pressure of the test specimen and the test state control scheme as a benchmark, and setting a pressure deviation range as a warning range according to the test equipment risk analysis and emergency plan in the test requirements; comparing the test parameters in the physical test with the parameters in the test state control scheme in real time, matching the comparison result with the warning range, and if the comparison result is within the warning range, then using the test state control scheme.

[0040] In practice, data such as pipeline pressure, valve opening, and equipment safety parameters during the test are compared in real time with the parameters in the test state control scheme, and decisions are made based on the deviation between the two schemes.

[0041] When the deviation is less than 1%, the test status control scheme is used; when 1% < deviation < 5%, the test status control scheme is modified; when the deviation > 5%, the test decision module issues an emergency stop command, and the on-site experts decide whether to continue the test based on the actual situation.

[0042] In some embodiments of the present invention, an experimental data management platform is used to organize experimental data and generate reports. According to the requirements of the client, the process data and results data of the experiment are transmitted to the experimental data management platform. The data analysis module generates charts and graphs, determines whether repeatability testing is necessary, and finally generates an experimental report.

[0043] In some embodiments of the present invention, step S1 further includes: detecting the blade thickness based on the coordinate points of the modularized blade profile parameters, and adjusting the modularization ratio to ensure that the blade thickness and blade aspect ratio meet the test requirements.

[0044] In practice, step S1 includes the following steps:

[0045] S1.1: Obtain the chord length b, pitch t, ​​inlet airflow angle β1, and original blade coordinates of the original blade shape; obtain the test chamber inlet length L and width W; structure the above parameters and input them into the test piece design module; the system will calculate the appropriate number of blades N. The calculation principle is that t is an integer, the aspect ratio should not be lower than 2, and the minimum should not be lower than 1.8.

[0046] S1.2: The modeling ratio n of the blades is determined according to the number of blades, and other physical properties of the test specimen are scaled up or down proportionally.

[0047] S1.3: Based on the coordinate points of the blade profile parameters after modeling, use the blade profile thickness detection function to make a preliminary judgment on the strength of the modeled blade. It is advisable that the maximum thickness of the blade profile is not less than 3mm. If this is not met, return to S1.1, reduce the number of blades to N-1, recalculate the modeling ratio, and continue until the maximum thickness is not less than 3mm.

[0048] S1.4: Using the coordinate transformation function, according to the calculated number of blades N, the program generates N blade shapes along the Y direction. The interval length between the N blade shapes is n×t, forming a blade row. The blade coordinates β1 are rotated by an angle to generate the rotated coordinates, ensuring that the installation angle is correct. Finally, a script file .scr is generated.

[0049] S1.5: Import the .scr file into the CAD software to generate the blade row.

[0050] In some embodiments of the present invention, step S2 specifically includes: determining the disk angle, upper chamber length, lower chamber length, guide vane angle, and tail plate angle of the virtual test equipment according to different blade row installation angles, thereby obtaining the different test piece layout schemes.

[0051] In practice, step S2 includes the following steps:

[0052] S2.1: Use CAD software to obtain the center points of the lines connecting the leading edges of N blades, ensuring that these center points are aligned with the center of the flow channel. Simultaneously, determine the lengths Lup and Ldown of the upper and lower condensate chambers for the wind tunnel, and the angle β of the guide vanes in the upper and lower condensate chambers. up β down This forms layout scheme 1.

[0053] S2.2: Using CAD software, rotate the blade array by different angles according to the center point of the disk used for installing the test specimen. n Get each angle i n The length L of the upper and lower chambers of the wind tunnel up L down This forms layout schemes 2 to n.

[0054] S2.3: Export layout schemes 1 to n as .dwg format files.

[0055] In some embodiments of the present invention, step S3, the process of simulating the virtual fluid domain, includes: setting the input variables of the simulation as the length of the upper sump chamber, the length of the lower sump chamber, the angle of the guide vane, the angle of the tail plate, and the suction pressure in front of the guide vane; and setting the target output parameters of the simulation as the average Mach number difference, the average inlet airflow angle difference, and the average inlet pressure difference along the blade front line. Step S3 also includes optimizing the structural layout and aerodynamic scheme of the test piece according to the experimental requirements and the target output parameters to obtain the optimal structural layout and aerodynamic scheme.

[0056] In practice, step S3 includes the following steps:

[0057] S3.1: Import layout schemes 1 to n using UG NX software and generate the fluid domain. The optimization variable is the length L of the upper and lower chambers.up L down The angle β of the upper and lower sump deflectors up β down The air extraction pressure P in front of the upper and lower sump deflectors up P down The target parameters for optimization are the average Mach number difference, average velocity direction angle difference, and average pressure difference on the parallel line in front of the blade cascade.

[0058] S3.2: Based on the Isight software, an optimized workflow is built. The workflow is divided into four parts: mesh generation, numerical solution, post-processing, and data post-processing.

[0059] S3.3: The mesh is generated using a mesh parametric method.

[0060] S3.4: The numerical solution employs a quasi-three-dimensional solution technique.

[0061] S3.5: Post-processing uses CFD-Post parameterized processing.

[0062] S3.6: Use the data post-processing module to calculate the achievement status of the target parameters.

[0063] S3.7: Based on the data post-processing, provide the layout and aerodynamic schemes under the optimal target parameters, and give the inlet and outlet boundary pressures required for the test.

[0064] In practice, the method further includes the following steps:

[0065] S4.1: Enter the attribute parameters of the test piece into the test data storage module, specifically involving information such as the processing method and processing parameters.

[0066] S4.2: Input the information of the test specimen, such as the sensing part, into the test data storage module. Specifically, this includes the validity period of the sensing part, the effective scope of use, and the stepping scheme of the sensing part.

[0067] S4.3: Input the test specimen information into the test data storage module using the test channel, specifically involving the validity period, applicable scope, and accuracy of each pressure and temperature measurement module.

[0068] S4.4: According to the test specimen layout scheme and pneumatic scheme, perform physical processing and installation of the test specimen, and record the installation status into the test data management platform, specifically involving installation steps, operating procedures, and specific installation parameters.

[0069] In practice, the method further includes the following steps:

[0070] S5.1: Using the equipment state control model, based on the inlet and outlet boundary pressures given in S3.7, generate the valve opening state under each test state, specifically involving the valve stroke, the opening and closing sequence of each valve, and the valve opening and closing rate to maintain the stability of the test state, thus forming a test state control scheme.

[0071] S5.2: Transmit the valve opening degree and corresponding boundary pressure under each state to the test data storage module.

[0072] In practice, the method further includes the following steps:

[0073] S6.1: Test warning value setting: Use the test boundary pressure and valve opening scheme as the benchmark, and set the deviation value ±5% as the warning value.

[0074] S6.2: Transmit the early warning value to the test data storage module for data storage and utilization.

[0075] In practice, the method further includes the following steps:

[0076] S7.1: During the test, the test data management platform sends the control scheme to the test execution module. The test execution module adjusts the valve state to the corresponding control scheme design state according to the test control scheme to achieve the adjustment of test condition 1. When the required state is not achieved according to the control scheme, the tester's PID automatic control achieves the state adjustment. After the adjustment is completed, the sensing part moves according to the sensing part stepping scheme to collect pressure signals.

[0077] S7.2: Transmit the valve opening degree and boundary pressure value when the actual state is reached to the test data storage module.

[0078] S7.3: Based on the valve status and inlet / outlet boundary pressure, retrieve the corresponding flow field simulation results calculated in S3.7 stored in the test data storage module, and use the inlet / outlet boundary pressure as a trigger to visualize the valve status and flow field on the display screen of the test execution module.

[0079] In practice, the method further includes the following steps:

[0080] S8.1: During the test, test safety-related parameters such as pipeline pressure and valve opening value are transmitted to the test decision module in real time and compared with the control strategies of S3.7 and S5.1.

[0081] S8.2: When there is a difference between the actual pressure and the simulated pressure, it is recommended to implement the following standards: When the deviation is <1%, the subsequent test state should continue with this scheme; when 1% < deviation < 5%, the test data management platform should transmit the actual control scheme to the test state control scheme design module, use the data to correct the control model, and retransmit the corrected control scheme to the test data management platform, overriding the aforementioned scheme, to further guide the operation; when the deviation is >5%, and the warning set value is reached, the judgment system should provide the specific location of the pressure difference and the time history diagram. When the pipeline pressure involving test safety reaches the warning value, the test decision module should issue a command to directly switch to the emergency shutdown state, issue an emergency exit command to the valves and other actuators, and discharge the airflow from the test section. For abnormal pressure measurement points of test specimens that do not involve test safety, the test expert should decide whether to continue the test. After the decision is made, the test execution module should issue a command to continue the test or stop the test.

[0082] S8.2: Repeat S7.1 to S8.2 until all states are completed.

[0083] In practice, the method further includes the following steps:

[0084] S9.1: Transmit the final test control data, pipeline pressure data, test parameters of test specimens, and other data to the test data management platform in accordance with the prescribed format.

[0085] S9.2: Generate charts from the experimental data according to the experimental requirements, and through analysis of the charts, mark any anomalies in the data quality, and decide whether to conduct repeated experiments to verify the anomalies.

[0086] S9.3: Analyze the processed data and generate an experimental report from the data management platform.

[0087] like Figure 2 As shown, this embodiment of the invention also provides a combined virtual and real blade cascade testing system, comprising:

[0088] The test specimen design platform is used to construct a virtual test device for blade cascade testing. The modularization ratio is determined based on the characteristic geometric parameters of the original blade of the test specimen. Based on the characteristic geometric parameters of the original blade and the characteristic geometric parameters of the virtual test device, as well as the modularization ratio, the original blade shape of the test specimen and the features of the virtual test device are modularized to generate multiple sets of virtual blade rows.

[0089] The test piece design platform is also used to place the generated blade array at the center of the flow channel of the virtual test equipment, and obtain different test piece layout schemes according to different blade array installation angles;

[0090] The test specimen design platform is also used to model according to the different test specimen layout schemes, generate a virtual fluid domain, perform simulation analysis on the virtual fluid domain, obtain the structural layout scheme and aerodynamic scheme of the test specimen, and determine the test boundary pressure of the test specimen;

[0091] The test control design platform is used to generate the valve opening status of the virtual test equipment under each test state according to the determined test boundary pressure of the test piece, and form a test state control scheme.

[0092] In some embodiments of the present invention, the system further includes: a physical testing platform, used to process and install the physical test piece according to the structural layout scheme and aerodynamic scheme of the test piece to obtain the testing platform; and to conduct physical tests on the testing platform according to the structural layout scheme and aerodynamic scheme of the test piece, as well as the test boundary pressure of the test piece.

[0093] In some embodiments of the present invention, the test control design platform is further configured to use the test boundary pressure of the test specimen and the test state control scheme as a benchmark, and set the pressure deviation range as a warning range according to the test equipment risk analysis and emergency plan in the test requirements; the system further includes: a test data management platform, configured to compare the test parameters in the physical test with the parameters in the test state control scheme in real time, match the comparison results with the warning range, and if the comparison results are within the warning range, then the test state control scheme is used.

[0094] This invention provides a virtual-physical integrated blade cascade testing system. The system mainly comprises a test piece design platform, a test control design platform, a physical testing platform, and a test data management platform. The test piece design platform includes modules for test piece modeling, test piece layout design, and test piece aerodynamic design. The test control design platform includes modules for test state control design and test early warning. The physical testing platform includes modules for test piece processing parameter input, test piece installation status sensing, test piece sensory component status sensing, and test execution. The test data management platform includes modules for test data storage, test data chart generation, and test report generation. This system can be used to realize a complete application process from test design, test execution, and test data analysis and delivery. This invention improves the efficiency and quality of blade cascade testing, solves the problems of low testing efficiency and long testing cycles in existing blade cascade testing, and quickly meets the needs of blade profile verification and algorithm calibration.

[0095] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for testing blade cascades using a combination of real and virtual methods, characterized in that, Includes the following steps: S1. Construct a virtual test device for the blade cascade test, determine the modeling ratio based on the characteristic geometric parameters of the original blade of the test piece, and modularize the original blade shape of the test piece and the features of the virtual test device based on the characteristic geometric parameters of the original blade and the characteristic geometric parameters of the virtual test device, as well as the modeling ratio, to generate multiple sets of virtual blade rows; S2. Place the generated blade array at the center of the flow channel of the virtual test equipment, and obtain different test specimen layout schemes according to different blade array installation angles; S3. Model the different test specimen layout schemes to generate a virtual fluid domain, perform simulation analysis on the virtual fluid domain, obtain the structural layout scheme and aerodynamic scheme of the test specimen, and determine the test boundary pressure of the test specimen; S4. Based on the determined test boundary pressure of the test piece, generate the valve opening state in the virtual test equipment under each test state to form a test state control scheme.

2. The blade cascade test method combining virtual and real methods according to claim 1, characterized in that, The method further includes: Based on the structural layout and pneumatic design of the test specimen, the test specimen is processed and installed to obtain a test platform; based on the structural layout and pneumatic design of the test specimen, and the test boundary pressure of the test specimen, physical tests are conducted on the test platform.

3. The blade cascade test method combining virtual and real methods according to claim 2, characterized in that, The method further includes: Using the test boundary pressure of the test specimen and the test state control scheme as a benchmark, and based on the test equipment risk analysis and emergency plan in the test requirements, the pressure deviation range is set as the early warning range. The test parameters in the physical test are compared with the parameters in the test state control scheme in real time, and the comparison results are matched with the warning range. If the comparison results are within the warning range, the test state control scheme is used.

4. The blade cascade test method combining virtual and real methods according to claim 1, characterized in that, Step S1 also includes: detecting the blade thickness based on the coordinate points of the modularized blade profile parameters, and adjusting the modularization ratio to ensure that the blade thickness and blade aspect ratio meet the test requirements.

5. The blade cascade test method combining virtual and real methods according to claim 1, characterized in that, Step S2 specifically includes: determining the disk angle, upper chamber length, lower chamber length, guide vane angle, and tail plate angle of the virtual test equipment according to different blade row installation angles, thereby obtaining the different test piece layout schemes.

6. The blade cascade test method combining virtual and real methods according to claim 1, characterized in that, In step S3, the process of simulating the virtual fluid domain includes: setting the input variables of the simulation as the length of the upper sump chamber, the length of the lower sump chamber, the angle of the guide vane, the angle of the tail plate, and the air extraction pressure in front of the guide vane; and setting the target output parameters of the simulation as the average Mach number difference, the average intake airflow angle difference, and the average intake pressure difference along the blade front line.

7. The blade cascade test method combining virtual and real methods according to claim 6, characterized in that, Step S3 also includes optimizing the structural layout and aerodynamic scheme of the test piece according to the test requirements and the target output parameters to obtain the optimal structural layout and aerodynamic scheme.

8. A combined virtual and real blade cascade testing system, characterized in that, include: The test specimen design platform is used to construct a virtual test device for blade cascade testing. The modularization ratio is determined based on the characteristic geometric parameters of the original blade of the test specimen. Based on the characteristic geometric parameters of the original blade and the characteristic geometric parameters of the virtual test device, as well as the modularization ratio, the original blade shape of the test specimen and the features of the virtual test device are modularized to generate multiple sets of virtual blade rows. The test piece design platform is also used to place the generated blade array at the center of the flow channel of the virtual test equipment, and obtain different test piece layout schemes according to different blade array installation angles; The test specimen design platform is also used to model according to the different test specimen layout schemes, generate a virtual fluid domain, perform simulation analysis on the virtual fluid domain, obtain the structural layout scheme and aerodynamic scheme of the test specimen, and determine the test boundary pressure of the test specimen; The test control design platform is used to generate the valve opening status of the virtual test equipment under each test state according to the determined test boundary pressure of the test piece, and form a test state control scheme.

9. The blade cascade test system combining virtual and real methods according to claim 8, characterized in that, The system also includes: A physical testing platform is used to process and install the physical test piece according to the structural layout and aerodynamic scheme of the test piece to obtain the testing platform; and to conduct physical tests on the testing platform according to the structural layout and aerodynamic scheme of the test piece and the test boundary pressure of the test piece.

10. The blade cascade test system combining virtual and real methods according to claim 9, characterized in that, The test control design platform is also used to set the pressure deviation range as the early warning range based on the test boundary pressure of the test piece and the test state control scheme, according to the test equipment risk analysis and emergency plan in the test requirements. The system also includes: a test data management platform, used to compare the test parameters in the physical test with the parameters in the test state control scheme in real time, match the comparison results with the warning range, and if the comparison results are within the warning range, then the test state control scheme is used.

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