Blade thermal mechanical fatigue non-standard test method, system, equipment and medium

Abstract

The invention relates to a blade thermal mechanical fatigue non-standard test method, system and device and a medium, and the method comprises the steps: obtaining the temperature, stress and thermal mechanical fatigue life of a blade based on blade performance parameters according to a pre-established target gas turbine blade three-dimensional model. And determining a test sample of the blade based on the thermal mechanical fatigue life of the blade. And based on the target test sample, determining a clamp matched with the target test sample. According to the relationship fitting result of the strain and the temperature, the target test sample is tested through the clamp, and the blade thermal mechanical fatigue non-standard test result is obtained. The thermal mechanical fatigue of the turbine blade of the gas turbine is subjected to specific position sampling test, the accuracy and reliability of service performance evaluation are improved, and safe operation of the gas turbine is guaranteed. The problem of low accuracy of the thermal mechanical fatigue non-standard test in the related technology is solved.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbine blade testing, and in particular to a non-standard test method, system, equipment and medium for thermal mechanical fatigue of blades. Background Art

[0002] In gas turbines, turbine blades are key components that withstand the impact of high-temperature and high-pressure airflow. Their working environment is extremely harsh and prone to thermomechanical fatigue damage. Thermomechanical fatigue refers to fatigue damage inside the material under high temperature, high stress and high-frequency loading, which leads to cracks, deformation and other problems in the blades, seriously affecting the performance and safety of the gas turbine. Since the casting structure has a great influence on the mechanical properties of the material during the casting process, test rods from the same batch cannot accurately evaluate the service performance of gas turbine turbine blades.

[0003] At present, due to the complex structure of turbine blades, the service performance evaluation of turbine blades mainly involves endurance performance testing of furnace test bars of the same batch. However, the test bars have different structures from turbine blades, and the test samples of turbine blades are of non-standard design. The test bar performance cannot accurately evaluate the actual mechanical properties of gas turbine turbine blades. Therefore, the non-standard test of thermomechanical fatigue in related technologies has the problem of low accuracy. Summary of the invention

[0004] The embodiments of the present application provide a blade thermal mechanical fatigue non-standard test method, system, equipment and medium to at least solve the problem of low precision in thermal mechanical fatigue non-standard testing in related technologies.

[0005] In a first aspect, an embodiment of the present application provides a non-standard test method for blade thermomechanical fatigue, the method comprising:

[0006] According to a pre-established three-dimensional model of a target gas engine turbine blade, based on blade performance parameters, the temperature, stress, strain and thermomechanical fatigue life of the blade are obtained;

[0007] Based on the thermomechanical fatigue life of the blade, determining a test sample of the blade, wherein the test sample is of non-standard size, and pre-processing the test sample to obtain a target test sample;

[0008] Based on the target test sample, determining a fixture matching the target test sample;

[0009] According to the fitting result of the relationship between the strain and the temperature, the target test sample is tested by the fixture to obtain a non-standard test result of blade thermal mechanical fatigue.

[0010] In one embodiment, according to a pre-established three-dimensional model of a target gas engine turbine blade, based on blade performance parameters, the temperature, stress, strain and thermomechanical fatigue life of the blade are obtained, and the method further includes:

[0011] Establishing a preliminary three-dimensional model of a gas engine turbine blade by blue light scanning and industrial CT, performing multi-sample data scanning by a three-coordinate measuring machine to obtain scanning data, and verifying and correcting the preliminary three-dimensional model of a gas engine turbine blade according to the scanning data to obtain a target three-dimensional model of a gas engine turbine blade;

[0012] According to the three-dimensional model of the target gas engine turbine blade, the temperature and stress distribution of the blade are obtained by using a turbulence model and boundary conditions through fluid and structure simulation;

[0013] Based on the blade performance parameters, the thermal mechanical fatigue life of the blade is obtained through fatigue calculation.

[0014] In one embodiment, determining a test sample of a blade based on the thermomechanical fatigue life of the blade comprises:

[0015] According to the distribution information of different thermomechanical fatigue lives in the blade, obtaining a position that meets the preset thermomechanical fatigue life;

[0016] Based on the position that meets the preset thermomechanical fatigue life and according to the actual size of the blade, a test sample of the blade is obtained.

[0017] In one embodiment, the preprocessing of the test sample to obtain a target test sample includes:

[0018] According to the preset size, the test sample is finely processed and ground to obtain a target test sample with a cylindrical shape, wherein the target test sample is provided with threads;

[0019] Among them, the preset dimensions include a length of 85mm-95mm, a test section length of 25mm-35mm, and a test section diameter of 6mm-8mm.

[0020] In one embodiment, after acquiring the target test sample, the method further includes:

[0021] Thermocouples are connected to the test section by welding, wherein the number of groups of thermocouples is 2-5.

[0022] In one embodiment, based on the target test sample, determining a fixture matching the target test sample includes:

[0023] According to the size of the target test sample, the length of the clamp is determined to be 44 mm-54 mm, wherein one end of the clamp is provided with an internal thread matching the target test sample, and the clamp is threadedly connected to the target test sample.

[0024] In one embodiment, the test of the target test sample by the fixture based on the fitting result of the relationship between the strain and the temperature to obtain the non-standard test result of blade thermal mechanical fatigue includes:

[0025] Fix the test sample to the test equipment by the fixture, fix the two contact ends of the high temperature extensometer to the test section in the target sample and calibrate the strain;

[0026] According to the calibrated strain, thermal cycling is performed under zero load control, strain data is recorded, the relationship between the strain and the temperature is fitted, and the fitting parameters are input into the test equipment for strain compensation;

[0027] Setting a temperature range, a heating and cooling rate, and a strain control parameter in the test device, recording total strain data, and obtaining thermomechanical strain data of a target test sample based on the strain data and the total strain data;

[0028] The thermomechanical strain data of the target test sample is used as the non-standard test result of the blade thermomechanical fatigue.

[0029] In a second aspect, an embodiment of the present application provides a blade thermal mechanical fatigue non-standard test system, the system comprising a module for obtaining temperature, stress and thermal mechanical fatigue life of a blade, a module for obtaining a target test sample, a module for obtaining a fixture, and a module for obtaining a blade thermal mechanical fatigue non-standard test result, wherein:

[0030] The module for obtaining temperature, stress and thermomechanical fatigue life of the blade is used to obtain the temperature, stress, strain and thermomechanical fatigue life of the blade based on the blade performance parameters according to the pre-established three-dimensional model of the target gas turbine blade;

[0031] The module for obtaining a target test sample is used to determine a test sample of a blade based on the thermomechanical fatigue life of the blade, wherein the test sample is of a non-standard size, and to pre-process the test sample to obtain a target test sample;

[0032] The fixture acquisition module is used to determine a fixture matching the target test sample based on the target test sample;

[0033] The module for obtaining non-standard test results of blade thermal mechanical fatigue is used to test the target test sample through the fixture according to the fitting result of the relationship between strain and temperature, so as to obtain non-standard test results of blade thermal mechanical fatigue.

[0034] In a third aspect, an embodiment of the present application provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, a non-standard test method for blade thermal mechanical fatigue as described in the first aspect above is implemented.

[0035] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a non-standard test method for blade thermal mechanical fatigue as described in the first aspect above.

[0036] The embodiments of the present application provide a blade thermomechanical fatigue non-standard test method, system, equipment and medium which have at least the following technical effects.

[0037] Based on the pre-established three-dimensional model of the target gas turbine blade, the temperature, stress and thermomechanical fatigue life of the blade are obtained based on the blade performance parameters. Based on the thermomechanical fatigue life of the blade, the test sample of the blade is determined, where the test sample is of non-standard size, and the test sample is preprocessed to obtain the target test sample. Based on the target test sample, the fixture matching the target test sample is determined. According to the fitting results of the relationship between strain and temperature, the target test sample is tested through the fixture to obtain the non-standard test results of the thermomechanical fatigue of the blade. The specific position sampling test of the thermomechanical fatigue of the gas turbine turbine blade is realized, which improves the accuracy and reliability of the service performance evaluation and ensures the safe operation of the gas turbine. The problem of low precision of non-standard thermomechanical fatigue testing in related technologies is solved.

[0038] Details of one or more embodiments of the present application are set forth in the following drawings and description to make other features, objects, and advantages of the present application more readily apparent. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0040] Figure 1 is a flow chart of a non-standard test method for blade thermal mechanical fatigue according to an embodiment of the present application;

[0041] Figure 2 is a flowchart of step S101 according to an exemplary embodiment;

[0042] Figure 3 is a schematic diagram showing thermomechanical fatigue life according to an exemplary embodiment;

[0043] Figure 4 is a schematic diagram of the structure of a target test sample according to an exemplary embodiment;

[0044] Figure 5 is a schematic structural diagram of a clamp according to an exemplary embodiment;

[0045] Figure 6 is a flowchart of step S104 according to an exemplary embodiment;

[0046] Figure 7 is a schematic diagram showing the results of a non-standard thermomechanical fatigue test according to an exemplary embodiment;

[0047] Figure 8 is a block diagram of a system for non-standard testing of blade thermal mechanical fatigue according to an exemplary embodiment;

[0048] Fig. 9 is a block diagram of an electronic device according to an exemplary embodiment. DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solutions and advantages of the present application clearer, the present application is described and illustrated below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not intended to limit the present application. Based on the embodiments provided in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work are within the scope of protection of the present application.

[0050] Obviously, the drawings described below are only some examples or embodiments of the present application. For ordinary technicians in this field, the present application can also be applied to other similar scenarios based on these drawings without creative work. In addition, it can also be understood that although the efforts made in this development process may be complicated and lengthy, for ordinary technicians in this field related to the content disclosed in this application, some changes in design, manufacturing or production based on the technical content disclosed in this application are just conventional technical means, and should not be understood as insufficient content disclosed in this application.

[0051] Reference to "embodiments" in this application means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those of ordinary skill in the art that the embodiments described in this application may be combined with other embodiments without conflict.

[0052] Unless otherwise defined, the technical terms or scientific terms involved in this application should be understood by people with ordinary skills in the technical field to which this application belongs. The words "one", "a", "a", "the" and the like involved in this application do not indicate a quantitative limitation, and may represent the singular or plural. The terms "include", "comprise", "have" and any of their variations involved in this application are intended to cover non-exclusive inclusions; for example, a process, method, system, product or device that includes a series of steps or modules (units) is not limited to the listed steps or units, but may also include steps or units that are not listed, or may also include other steps or units inherent to these processes, methods, products or devices. The words "connect", "connected", "coupled" and the like involved in this application are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The "multiple" involved in this application refers to two or more. "And / or" describes the association relationship of associated objects, indicating that there may be three relationships, for example, "A and / or B" can represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the objects before and after are in an "or" relationship. The terms "first", "second", "third", etc. involved in this application are only used to distinguish similar objects and do not represent a specific ordering of the objects.

[0053] In a first aspect, the present application provides a non-standard test method for blade thermal mechanical fatigue, which is applied to the stator winding end of a steam turbine generator. Figure 1 This is a flow chart of non-standard blade thermal mechanical fatigue test, such as Figure 1 As shown, a non-standard test method for blade thermal mechanical fatigue includes:

[0054] Step S101 : According to a pre-established three-dimensional model of a target gas engine turbine blade, based on blade performance parameters, the temperature, stress, strain and thermomechanical fatigue life of the blade are obtained.

[0055] Step S102: based on the thermomechanical fatigue life of the blade, determine a test sample of the blade, wherein the test sample has a non-standard size, pre-process the test sample, and obtain a target test sample.

[0056] Step S103: Based on the target test sample, determine a fixture that matches the target test sample.

[0057] Step S104: According to the fitting result of the relationship between strain and temperature, the target test sample is tested by a fixture to obtain a non-standard test result of blade thermal mechanical fatigue.

[0058] In summary, the temperature, stress and thermomechanical fatigue life of the blade are obtained based on the blade performance parameters according to the pre-established three-dimensional model of the target gas turbine turbine blade. Based on the thermomechanical fatigue life of the blade, the test sample of the blade is determined, wherein the test sample is of non-standard size, and the test sample is preprocessed to obtain the target test sample. Based on the target test sample, the fixture matching the target test sample is determined. According to the fitting results of the relationship between strain and temperature, the target test sample is tested through the fixture to obtain the non-standard test results of the thermomechanical fatigue of the blade. The specific position sampling test of the thermomechanical fatigue of the gas turbine turbine blade is realized, which improves the accuracy and reliability of the service performance evaluation and ensures the safe operation of the gas turbine. The problem of low precision of non-standard thermomechanical fatigue testing in related technologies is solved.

[0059] Figure 2 is a flowchart of step S101 according to an exemplary embodiment. Figure 2 As shown, step S101, according to the pre-established three-dimensional model of the target gas turbine turbine blade, based on the blade performance parameters, obtain the temperature, stress, strain and thermomechanical fatigue life of the blade, specifically including the following steps:

[0060] Step S1011, establishing a preliminary three-dimensional model of a gas engine turbine blade by blue light scanning and industrial CT, performing multi-sample data scanning by a three-coordinate measuring machine to obtain scanning data, and verifying and correcting the preliminary three-dimensional model of a gas engine turbine blade according to the scanning data to obtain a target three-dimensional model of a gas engine turbine blade;

[0061] Step S1012: According to the three-dimensional model of the target gas engine turbine blade, the turbulence model and boundary conditions are used to obtain the temperature, strain and stress distribution of the blade through fluid and structure simulation;

[0062] Step S1013: Based on the blade performance parameters, obtain the blade thermal mechanical fatigue life through fatigue calculation.

[0063] Optionally, first, a preliminary model is established, and blue light scanning can be used to quickly and accurately obtain three-dimensional data of the object surface. Blue light scanning is suitable for the measurement of complex curved surfaces and can capture the complex geometric features of turbine blades. Industrial CT (Computed Tomography) scanning uses X-rays to scan objects and reconstruct a three-dimensional image of their internal structure. Data scanning and model correction, through a three-coordinate measuring machine (CMM), are used to accurately measure the actual size and shape deviation of the blade to ensure the accuracy of the model. The reliability of the model can be further improved by collecting data from multiple samples. Model verification and correction, combined with the above scanning data, the preliminary established three-dimensional model is verified, and necessary corrections are made according to the actual measurement results to ensure the consistency between the model and the actual object. Subsequently, blade performance analysis, turbulence model and boundary condition setting are carried out. In the CFD (Computational Fluid Dynamics) software, a suitable turbulence model is selected according to the actual situation, and boundary conditions are set, such as inlet temperature, pressure, etc. (selecting a turbulence model and setting boundary conditions are routine operations and will not be repeated here). Fluid and structural simulation: Use CFD and FEA (Finite Element Analysis) tools to simulate the airflow around the blade and the structural response of the blade itself under actual working conditions, so as to obtain temperature distribution and stress distribution. Strain data is obtained by measuring the length change of the sample under different temperature and load conditions. Finally, Figure 3 is a schematic diagram showing the thermomechanical fatigue life according to an exemplary embodiment. Figure 3 As shown in Figure 1, the thermal mechanical fatigue life assessment is based on the results of temperature and stress distribution, using material models and fatigue calculation methods (such as strain-based or energy-based methods) to calculate the fatigue life of the blade under thermal cycles. Figure 3 In the color change from gray to purple, gray indicates the highest thermomechanical fatigue life, and purple indicates the lowest thermomechanical fatigue life.

[0064] The accuracy and reliability of the model are improved through step S101. Simulation analysis can help engineers understand the behavior of blades under different working conditions and provide a basis for design improvement.

[0065] In one embodiment, step S102 determines the test sample of the blade based on the thermomechanical fatigue life of the blade. Specifically, it includes:

[0066] According to the distribution information of different thermomechanical fatigue lives in the blade, the position that meets the preset thermomechanical fatigue life is obtained;

[0067] Based on the position that meets the preset thermomechanical fatigue life, the test sample of the blade is obtained according to the actual size of the blade.

[0068] Optionally, the thermal mechanical fatigue life of different positions of the blade can be calculated by using the three-dimensional blade model established in step S101 and its related temperature and stress distribution analysis results (such as Figure 3 In order to determine which locations require special attention, a preset thermomechanical fatigue life threshold (i.e., corresponding Figure 3 The colors of the red to purple areas are all low thermomechanical fatigue life). By comparing the thermomechanical fatigue life of each location with the preset threshold, the locations that meet the low thermomechanical fatigue life, that is, potential weak points, can be found. Once the locations with low thermomechanical fatigue life are determined, the next step is to prepare test samples from these locations. The test samples should maintain the same or similar size, shape and material properties as the actual blade to ensure the accuracy and relevance of the test results. The test samples are obtained by CNC wire cutting to ensure their dimensional accuracy.

[0069] By determining the test sample of the blade based on the thermomechanical fatigue life of the blade in step S102, the position with low thermomechanical fatigue life can be found, so as to carry out subsequent experiments and improve the accuracy of testing the blade.

[0070] Figure 4 is a schematic diagram of the structure of a target test sample according to an exemplary embodiment. Figure 4 As shown, in step S102, the test sample is preprocessed to obtain a target test sample, including:

[0071] According to the preset size, the test sample is finely processed and ground and polished to obtain a target test sample in the shape of a cylinder, and the target test sample is provided with threads;

[0072] Among them, the preset dimensions include length 85mm-95mm, test section length 25mm-35mm, and test section diameter 6mm-8mm.

[0073] Optionally, according to the preset size range mentioned in step S102, the test sample is finely processed and ground and polished to ensure that its shape and size meet the specified standards. To ensure that the dimensional accuracy of the test sample meets the requirements. Grinding and polishing are to remove processing marks, make the surface of the test sample smoother, and reduce the impact of surface roughness on the test results. Among them, the preset dimensions include a length of 85mm-95mm, which can be 95mm, and a test section length of 25mm-35mm (such as Figure 3 The middle section of the test section can be selected as 25mm, the test section diameter is 6mm-8mm, and 6mm can be selected. The threads are set at both ends of the target test sample and can be selected as M8 threads. It is worth noting that Figure 4 The size of the target test sample is only an exemplary embodiment, and the size of the target test sample also includes the size proposed in this application.

[0074] In one embodiment, after obtaining the target test sample in step S102, the method further includes:

[0075] Thermocouples are connected to the test section by welding, wherein the number of thermocouples is 2-5 groups.

[0076] Optionally, target test samples have been obtained in step S102, and these samples have been finely processed and ground to form specific shapes and sizes for subsequent testing. In order to monitor the temperature changes of the test samples during the thermal cycle test, it is necessary to connect thermocouples at the test section of the test samples. Welding is selected because it can provide strong mechanical connection strength and good thermal conductivity to ensure good contact between the thermocouple and the test sample. The number of thermocouple groups is 2-5 groups, and 3 groups can be selected, so that the temperature can be measured simultaneously at different positions of the test section to obtain more comprehensive temperature distribution information. Specifically, three groups of thermocouples are connected at equal distances along the length direction at the test section position by welding.

[0077] Figure 5 is a schematic diagram of the structure of a clamp according to an exemplary embodiment. Figure 5 As shown, in one embodiment, step S103, based on the target test sample, determining a fixture matching the target test sample, specifically includes:

[0078] According to the size of the target test sample, the length of the clamp is determined to be 44 mm-54 mm, wherein one end of the clamp is provided with an internal thread matching the target test sample, and the clamp is threadedly connected to the target test sample.

[0079] Optionally, a target test sample has been prepared in step S102. In order to ensure the stability of the test sample during the test, a matching fixture needs to be designed. The length of the fixture is set to 44mm-54mm, and 54mm is optional. This length range is determined based on the size of the test sample and the test requirements to ensure that the fixture can firmly fix the test sample and will not affect the test section of the test sample. A thread is provided at one end of the target test sample, so the fixture must also be provided with a matching internal thread at the corresponding end so that the two can be connected together by threads. Through the threaded connection, it can be ensured that the test sample has a firm connection with the fixture during the test process to avoid loosening or falling off during the test. The threaded connection can also provide a certain adjustment function, which is convenient for adjusting the position of the test sample to ensure that the test section is in the optimal test position. It is worth noting that Figure 5 The size of the fixture is only an exemplary embodiment, and the size of the target test sample also includes the size proposed in this application.

[0080] Step S103: By properly designing the length of the fixture, the test sample can be ensured to be in a stable fixed state during the test process, avoiding additional stress or displacement caused by the fixture being too long or too short. This helps to improve the accuracy and reliability of the test results. By threaded connection, a stable connection can be ensured between the test sample and the fixture, improving the reliability and safety during the test process. Threaded connection can also simplify the installation and removal process of the test sample and improve test efficiency.

[0081] Figure 6 is a flowchart of step S104 according to an exemplary embodiment. Figure 6 As shown, step S104, based on the fitting result of the relationship between strain and temperature, the target test sample is tested by a fixture to obtain the non-standard test result of blade thermal mechanical fatigue. Specifically, the following steps are included:

[0082] S1041. Fix the test sample to the test equipment by means of a fixture, fix the two contact ends of the high temperature extensometer to the test section in the target sample and calibrate the strain;

[0083] S1042, performing thermal cycling under zero load control according to the calibrated strain, recording strain data, fitting the relationship between strain and temperature, and inputting the fitting parameters into the test equipment for strain compensation;

[0084] S1043, setting a temperature range, a heating and cooling rate, and a strain control parameter in a test device, recording total strain data, and obtaining thermomechanical strain data of a target test sample based on the strain data and the total strain data;

[0085] S1044. Use the thermomechanical strain data of the target test sample as the non-standard test result of the blade thermomechanical fatigue.

[0086] Optionally, first, fix the two ends of the high temperature extensometer at the corresponding positions of the sample working section to calibrate the strain. Then, perform thermal cycling under zero load control, allow the sample to expand and contract freely, record the strain εth data, and fit the relationship between the obtained strain εth and temperature T, and refer to ε th =S0+S1T+S2T 2 The empirical relationship, where S0, S1, and S2 are constants, is obtained through curve fitting, and the fitting parameters are input into the control software for strain compensation. Finally, the temperature range, heating and cooling rate, and strain control parameters are set in the software, the test is started, and the total strain data εt is recorded. m =ε t -ε th The mechanical strain ε is obtained by m data.

[0087] Combined with practical application examples, Figure 7is a schematic diagram showing the results of a non-standard thermomechanical fatigue test according to an exemplary embodiment. Figure 7 As shown, the test bar and the fixture are assembled and assembled on the MTS universal testing machine through pins. The test conditions are 900℃ / strain 0.7%. After being put on the machine, a thermal cycle process is first carried out to measure the strain change of the sample. After fitting an accurate thermal deformation formula, a formal test is carried out. Figure 7 Specifically, the stress-strain curves of the fifth cycle, half-life cycle, and 25th cycle are shown as a, mechanical strain, b, thermal strain, and c, total strain. It can be seen from the figure that as the number of cycles increases, the plastic strain range of the material increases and its ability to resist deformation weakens.

[0088] As the number of cycles increases, the plastic strain range of the material increases and its ability to resist deformation weakens.

[0089] Step S104 fixes the test sample on the test equipment by a clamp, and uses a high temperature extensometer to measure and calibrate the strain. This step ensures the position stability of the test sample and the accuracy of the strain measurement. By controlling the temperature and strain parameters of the test equipment, the total strain data is recorded, and the mechanical strain data is separated therefrom. These data reflect the mechanical properties of the material under thermal cycles. By analyzing the thermomechanical strain data, the thermomechanical fatigue performance of the material can be evaluated and used as the result of the non-standard test of the thermomechanical fatigue of the blade. Through the above steps, the thermomechanical fatigue performance of the blade under thermal cycles can be effectively evaluated, providing strong data support for the design improvement and performance optimization of gas turbine turbine blades.

[0090] In summary, the temperature, stress and thermomechanical fatigue life of the blade are obtained based on the blade performance parameters according to the pre-established three-dimensional model of the target gas turbine turbine blade. Based on the thermomechanical fatigue life of the blade, the test sample of the blade is determined, wherein the test sample is of non-standard size, and the test sample is preprocessed to obtain the target test sample. Based on the target test sample, the fixture matching the target test sample is determined. According to the fitting results of the relationship between strain and temperature, the target test sample is tested through the fixture to obtain the non-standard test results of the thermomechanical fatigue of the blade. The specific position sampling test of the thermomechanical fatigue of the gas turbine turbine blade is realized, which improves the accuracy and reliability of the service performance evaluation and ensures the safe operation of the gas turbine. The problem of low precision of non-standard thermomechanical fatigue testing in related technologies is solved.

[0091] Principle of the present invention: According to the actual service conditions of turbine blades, fluid and finite element calculations are performed to obtain the temperature, stress, thermomechanical fatigue life distribution and the position prone to failure of the blades. Further, according to the position of the blades prone to thermomechanical fatigue failure (i.e., the position with lower thermomechanical fatigue life) under the obtained service state, and the temperature and stress distribution at this position, the blade thermomechanical fatigue test conditions are designed. And in combination with the shape of the blades and the position prone to failure, the non-standard test sample size for sampling thermomechanical fatigue specimens on turbine blades and the size of the fixture used for thermomechanical fatigue testing are given. The thermomechanical fatigue test is performed with the non-standard test sample size and fixture size to obtain the results of the thermomechanical fatigue test. It is suitable for thermomechanical fatigue testing on MTS testing machines, and can be used to study the thermomechanical fatigue performance of specific positions of nickel-based high-temperature alloy turbine blades, and evaluate their reliability and safety during service.

[0092] In a second aspect, an embodiment of the present application provides a system for non-standard testing of blade thermal mechanical fatigue. Figure 8 FIG. 1 is a block diagram of a system for non-standard testing of blade thermal mechanical fatigue according to an exemplary embodiment. Figure 8 As shown, the system includes a module 810 for obtaining temperature, stress and thermal mechanical fatigue life of a blade, a module 820 for obtaining a target test sample, a module 830 for obtaining a fixture, and a module 840 for obtaining non-standard test results of thermal mechanical fatigue of a blade, wherein:

[0093] The module 810 for obtaining temperature, stress and thermomechanical fatigue life of the blade is used to obtain temperature, stress, strain and thermomechanical fatigue life of the blade based on the blade performance parameters according to the pre-established three-dimensional model of the target gas turbine blade;

[0094] The module 820 for obtaining a target test sample is used to determine a test sample of the blade based on the thermal mechanical fatigue life of the blade, wherein the test sample is of a non-standard size, and to pre-process the test sample to obtain a target test sample;

[0095] A fixture acquisition module 830 is used to determine a fixture matching the target test sample based on the target test sample;

[0096] The module 840 for obtaining non-standard test results of blade thermal mechanical fatigue is used to test the target test sample through a fixture according to the fitting results of the relationship between strain and temperature, and obtain the non-standard test results of blade thermal mechanical fatigue.

[0097] In summary, the non-standard test system for thermal mechanical fatigue of blades provided in the embodiment of the present application solves the problem of low precision of non-standard test for thermal mechanical fatigue in the related art by obtaining the temperature, stress and thermal mechanical fatigue life module 810 of the blade, obtaining the target test sample module 820, obtaining the fixture module 830 and obtaining the non-standard test result module 840 of thermal mechanical fatigue of blades. Specifically, the temperature, stress and thermal mechanical fatigue life of the blade are obtained based on the blade performance parameters according to the pre-established three-dimensional model of the target gas turbine turbine blade. Based on the thermal mechanical fatigue life of the blade, the test sample of the blade is determined, wherein the test sample is of non-standard size, and the test sample is pre-processed to obtain the target test sample. Based on the target test sample, the fixture matching the target test sample is determined. According to the fitting result of the relationship between strain and temperature, the target test sample is tested by the fixture to obtain the non-standard test result of thermal mechanical fatigue of the blade. The specific position sampling test of the thermal mechanical fatigue of the gas turbine turbine blade is realized, which improves the accuracy and reliability of the service performance evaluation and ensures the safe operation of the gas turbine. The problem of low precision of non-standard test for thermal mechanical fatigue in the related art is solved.

[0098] It should be noted that the system for non-standard testing of blade thermal mechanical fatigue provided in this embodiment is used to implement the above-mentioned implementation mode, and the descriptions that have been made will not be repeated. As used above, the terms "module", "unit", "sub-unit", etc. can be a combination of software and / or hardware that implements predetermined functions. Although the devices described in the above embodiments are preferably implemented in software, the implementation in hardware, or a combination of software and hardware, is also possible and conceivable.

[0099] In a third aspect, an embodiment of the present application provides an electronic device, Fig. 9 FIG. 1 is a block diagram of an electronic device according to an exemplary embodiment. Fig. 9 As shown, the electronic device may include a processor 91 and a memory 92 storing computer program instructions.

[0100] Specifically, the processor 91 may include a central processing unit (CPU), or an application specific integrated circuit (ASIC), or may be configured to implement one or more integrated circuits of the embodiments of the present application.

[0101] Among them, the memory 92 may include a large-capacity memory for data or instructions. By way of example and not limitation, the memory 92 may include a hard disk drive (HDD), a floppy disk drive, a solid-state drive (SSD), a flash memory, an optical disk, a magneto-optical disk, a magnetic tape, or a universal serial bus (USB) drive, or a combination of two or more of these. Where appropriate, the memory 92 may include a removable or non-removable (or fixed) medium. Where appropriate, the memory 92 may be inside or outside a data processing device. In a specific embodiment, the memory 92 is a non-volatile memory. In a specific embodiment, the memory 92 includes a read-only memory (ROM) and a random access memory (RAM). Where appropriate, the ROM may be a mask-programmed ROM, a programmable ROM (Programmable Read-Only Memory, PROM for short), an erasable PROM (Erasable ProgrammableRead-Only Memory, EPROM for short), an electrically erasable PROM (Electrically Erasable ProgrammableRead-Only Memory, EEPROM for short), an electrically alterable ROM (Electrically Alterable Read-Only Memory, EAROM for short) or a flash memory (FLASH) or a combination of two or more of these. Under appropriate circumstances, the RAM can be a static random access memory (SRAM) or a dynamic random access memory (DRAM), wherein the DRAM can be a fast page mode dynamic random access memory (FPMDRAM), an extended data output dynamic random access memory (EDODRAM), a synchronous dynamic random access memory (SDRAM), etc.

[0102] The memory 92 may be used to store or cache various data files required for processing and / or communication, as well as possible computer program instructions executed by the processor 91 .

[0103] The processor 91 implements any one of the blade thermomechanical fatigue non-standard testing methods in the above embodiments by reading and executing computer program instructions stored in the memory 92 .

[0104] In one embodiment, a blade thermal mechanical fatigue non-standard test device may further include a communication interface 93 and a bus 90. Fig. 9 As shown, the processor 91, the memory 92, and the communication interface 93 are connected via a bus 90 and communicate with each other.

[0105] The communication interface 93 is used to implement communication between the modules, devices, units and / or equipment in the embodiment of the present application. The communication port 93 can also implement data communication with other components such as: external devices, image / data acquisition equipment, databases, external storage, and image / data processing workstations.

[0106] The bus 90 includes hardware, software or both, and couples the components of a blade thermal mechanical fatigue non-standard test device to each other. The bus 90 includes but is not limited to at least one of the following: a data bus, an address bus, a control bus, an expansion bus, and a local bus. By way of example and not limitation, bus 90 may include an Accelerated Graphics Port (AGP) or other graphics bus, an Extended Industry Standard Architecture (EISA) bus, a Front Side Bus (FSB), a HyperTransport (HT) interconnect, an Industry Standard Architecture (ISA) bus, an InfiniBand interconnect, a Low Pin Count (LPC) bus, a memory bus, a Micro Channel Architecture (MCA) bus, a Peripheral Component Interconnect (PCI) bus, a PCI-Express (PCI-X) bus, a Serial Advanced Technology Attachment (SATA) bus, a Video Electronics Standards Association Local Bus (VLB) bus, or other suitable buses or a combination of two or more of the above. Where appropriate, bus 90 may include one or more buses. Although embodiments of the present application describe and illustrate a particular bus, the present application contemplates any suitable bus or interconnect.

[0107] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a program stored thereon. When the program is executed by a processor, a non-standard test method for blade thermal mechanical fatigue provided in the first aspect is implemented.

[0108] The readable storage medium may include but is not limited to: a portable disk, a hard disk, a random access memory, a read-only memory, an erasable programmable read-only memory, an optical storage device, a magnetic storage device or any suitable combination of the above.

[0109] In a possible implementation, the present invention can also be implemented in the form of a program product, which includes program code. When the program product is run on a terminal device, the program code is used to enable the terminal device to execute the steps of a non-standard blade thermal mechanical fatigue test method provided in the first aspect.

[0110] Among them, the program code for executing the present invention can be written in any combination of one or more programming languages, and the program code can be executed completely on the user device, partially on the user device, as an independent software package, partially on the user device and partially on a remote device, or completely on the remote device.

[0111] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0112] The above embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the invention patent. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application shall be subject to the attached claims.

Claims

1. A non-standard test method for blade thermal mechanical fatigue, characterized in that: The method comprises: According to a pre-established three-dimensional model of a target gas engine turbine blade, based on blade performance parameters, the temperature, stress, strain and thermomechanical fatigue life of the blade are obtained; Based on the thermomechanical fatigue life of the blade, determining a test sample of the blade, wherein the test sample is of non-standard size, and pre-processing the test sample to obtain a target test sample; Based on the target test sample, determining a fixture matching the target test sample; According to the fitting result of the relationship between the strain and the temperature, the target test sample is tested by the fixture to obtain a non-standard test result of blade thermal mechanical fatigue.

2. The method according to claim 1, characterized in that According to the pre-established three-dimensional model of the target gas turbine blade, based on the blade performance parameters, the temperature, stress, strain and thermomechanical fatigue life of the blade are obtained, including: Establishing a preliminary three-dimensional model of a gas engine turbine blade by blue light scanning and industrial CT, performing multi-sample data scanning by a three-coordinate measuring machine to obtain scanning data, and verifying and correcting the preliminary three-dimensional model of a gas engine turbine blade according to the scanning data to obtain a target three-dimensional model of a gas engine turbine blade; According to the three-dimensional model of the target gas engine turbine blade, the temperature and stress distribution of the blade are obtained by using a turbulence model and boundary conditions through fluid and structure simulation; Based on the blade performance parameters, the thermal mechanical fatigue life of the blade is obtained through fatigue calculation.

3. The method according to claim 1, characterized in that The step of determining a test sample of the blade based on the thermomechanical fatigue life of the blade comprises: According to the distribution information of different thermomechanical fatigue lives in the blade, obtaining a position that meets the preset thermomechanical fatigue life; Based on the position that meets the preset thermomechanical fatigue life and according to the actual size of the blade, a test sample of the blade is obtained.

4. The method according to claim 1, characterized in that: The preprocessing of the test sample to obtain a target test sample includes: According to the preset size, the test sample is finely processed and ground to obtain a target test sample with a cylindrical shape, wherein the target test sample is provided with threads; Among them, the preset dimensions include a length of 85mm-95mm, a test section length of 25mm-35mm, and a test section diameter of 6mm-8mm.

5. The method according to claim 4, characterized in that After acquiring the target test sample, the method further includes: Thermocouples are connected to the test section by welding, wherein the number of groups of thermocouples is 2-5.

6. The method according to claim 1, characterized in that Based on the target test sample, determining a fixture matching the target test sample includes: According to the size of the target test sample, the length of the clamp is determined to be 44 mm-54 mm, wherein one end of the clamp is provided with an internal thread matching the target test sample, and the clamp is threadedly connected to the target test sample.

7. The method according to claim 1, characterized in that The method of testing the target test sample by the fixture according to the fitting result of the relationship between the strain and the temperature to obtain the non-standard test result of the blade thermal mechanical fatigue includes: Fix the test sample to the test equipment by the fixture, fix the two contact ends of the high temperature extensometer to the test section in the target sample and calibrate the strain; According to the calibrated strain, thermal cycling is performed under zero load control, thermal strain data is recorded, the relationship between the thermal strain and the temperature is fitted, and the fitting parameters are input into the test equipment for strain compensation; Setting a temperature range, a heating and cooling rate, and a strain control parameter in the test device, recording total strain data, and obtaining thermomechanical strain data of a target test sample based on the strain data and the total strain data; The thermomechanical strain data of the target test sample is used as the non-standard test result of the blade thermomechanical fatigue.

8. A blade thermal mechanical fatigue non-standard test system, characterized in that: The system includes a module for obtaining temperature, stress and thermomechanical fatigue life of a blade, a module for obtaining a target test sample, a module for obtaining a fixture, and a module for obtaining non-standard test results of thermomechanical fatigue of a blade, wherein: The module for obtaining temperature, stress and thermomechanical fatigue life of the blade is used to obtain the temperature, stress, strain and thermomechanical fatigue life of the blade based on the blade performance parameters according to the pre-established three-dimensional model of the target gas turbine blade; The module for obtaining a target test sample is used to determine a test sample of a blade based on the thermomechanical fatigue life of the blade, wherein the test sample is of a non-standard size, and to pre-process the test sample to obtain a target test sample; The fixture acquisition module is used to determine a fixture matching the target test sample based on the target test sample; The module for obtaining non-standard test results of blade thermal mechanical fatigue is used to test the target test sample through the fixture according to the fitting result of the relationship between strain and temperature, so as to obtain non-standard test results of blade thermal mechanical fatigue.

9. An electronic device, characterized in that: The invention comprises a memory and a processor, a computer program stored in the memory and executable on the processor, and the processor implements a non-standard test method for thermal mechanical fatigue of a blade as claimed in any one of claims 1 to 7 when executing the computer program.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, a non-standard test method for blade thermal mechanical fatigue is implemented as described in any one of claims 1 to 7.

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