Method and system for evaluating residual life of gh4169 high-temperature alloy

Abstract

The present application belongs to the field of material life evaluation, and provides a kind of GH4169 high-temperature alloy residual endurance life evaluation method and system, method includes: obtaining the sample detection result obtained by short-time accelerated aging test and endurance tensile test to GH4169 high-temperature alloy sample, obtains the field working condition data of the GH4169 high-temperature alloy component to be evaluated in actual use;Determine the accelerated aging test mathematical model;In the same stress state, according to the endurance life of GH4169 high-temperature alloy sample under different experimental temperatures in test condition and the expected life under different service temperatures in actual use, determine the accelerated aging coefficient;According to sample detection result, accelerated aging test mathematical model, accelerated aging coefficient and field working condition data, obtain the residual endurance life of GH4169 high-temperature alloy component.The scheme provided by the present application can evaluate the residual endurance life of GH4169 high-temperature alloy component in time and conveniently.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of material life evaluation, in particular to a GH4169 high-temperature alloy residual endurance life evaluation method and system. BACKGROUND

[0002] In the modern industrial field, GH4169 high-temperature alloy is widely used in key industries such as aerospace, energy and power, petroleum and chemical industry. For example, the combustion chamber and turbine blade of an aero-engine, as core components, need to operate stably for a long time under high temperature, high pressure and complex stress environment, which puts high requirements on the performance of high-temperature alloy materials. Among them, the residual endurance life evaluation of high-temperature alloy materials is directly related to the safety and economy of the related equipment and components.

[0003] In the related art, the residual endurance life of GH4169 high-temperature alloy is usually evaluated by extrapolation evaluation schemes such as isothermal line extrapolation method and least constraint method. However, the isothermal line extrapolation method needs a large amount of experimental data at different experimental temperatures for fitting and extrapolation, and the experimental workload is huge; in actual application, the least constraint method has a complex data calculation process and requires high calculation resources and professional knowledge.

[0004] Therefore, the residual endurance life evaluation scheme of the traditional high-temperature alloy material has the technical problems of complex implementation process, and insufficient convenience and reliability. SUMMARY

[0005] The application provides a GH4169 high-temperature alloy residual endurance life evaluation method and system to solve the defects of the traditional high-temperature alloy material residual endurance life evaluation scheme, such as complex implementation process, and insufficient convenience and reliability.

[0006] In one aspect, the application provides a GH4169 high-temperature alloy residual endurance life evaluation method, comprising:

[0007] Obtaining sample detection results obtained by performing short-time accelerated aging test and endurance tensile test on GH4169 high-temperature alloy samples, and obtaining field working condition data of a GH4169 high-temperature alloy component to be evaluated in actual use;

[0008] According to a Larson-Miller parameter expression, an accelerated aging test mathematical model is determined, wherein the accelerated aging test mathematical model is used to represent the functional relationship between different service temperatures and endurance life under the same stress state;

[0009] Under the same stress state, an accelerated aging coefficient is determined according to the endurance life of the GH4169 high-temperature alloy sample under different experimental temperatures in the test condition and the expected life under different service temperatures in actual use;

[0010] According to the sample detection result, the accelerated aging test mathematical model, the accelerated aging coefficient and the field working condition data, the residual creep-rupture life of the GH4169 high-temperature alloy part is obtained.

[0011] According to the GH4169 high-temperature alloy residual creep-rupture life evaluation method provided by the application, short-time accelerated aging test and creep-rupture test are performed on a GH4169 high-temperature alloy sample, and the method comprises the following steps:

[0012] The GH4169 high-temperature alloy sample is subjected to first aging treatment at a first set temperature to obtain a preliminary aging sample, wherein the first set temperature is the maximum precipitation temperature of the stable δ phase of the GH4169 high-temperature alloy sample.

[0013] The preliminary aging sample is subjected to second aging treatment at a second set temperature to obtain an aging damage sample, wherein the second set temperature is lower than the first set temperature.

[0014] The aging damage sample is subjected to creep-rupture test under different stress states to obtain a sample detection result.

[0015] According to the GH4169 high-temperature alloy residual creep-rupture life evaluation method provided by the application, the accelerated aging test mathematical model is determined according to a Larson-Miller parameter expression, and the method comprises the following steps:

[0016] A first function expression between the Larson-Miller parameter and the first service temperature and the first creep-rupture life is established according to the Larson-Miller parameter expression.

[0017] A second function expression between the Larson-Miller parameter and the second service temperature and the second creep-rupture life is established according to the Larson-Miller parameter expression.

[0018] The first function expression and the second function expression are combined according to the condition that the Larson-Miller parameters are equal under the same stress state to obtain the accelerated aging test mathematical model.

[0019] According to the GH4169 high-temperature alloy residual creep-rupture life evaluation method provided by the application, the expression of the accelerated aging test mathematical model is as follows:

[0020]

[0021] Wherein, T1 represents the first service temperature, T2 represents the second service temperature, t1 represents the first creep-rupture life, t2 represents the second creep-rupture life, and C represents a constant related to the steel composition.

[0022] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0023] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0024] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0025] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0026] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0027] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0028] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0029] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0030] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0031] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0032] The application provides a method for evaluating the residual life of GH4169 high-temperature alloy, which comprises the following steps of: determining an accelerated aging coefficient under the same stress state according to the life of a GH4169 high-temperature alloy sample under different experimental temperatures in a test condition and the expected life of the sample under different service temperatures in actual use, and inputting the sample under the different experimental temperatures and the respective life into a Larson-Miller parameter expression to obtain a plurality of Larson-Miller test parameters under the same stress state.

[0033] averaging the plurality of equivalent lives to obtain a life average;

[0034] determining a remaining endurance life by subtracting the life average from a used time of the GH4169 superalloy component in the field operating condition data.

[0035] According to the method for evaluating the remaining endurance life of the GH4169 superalloy, a plurality of key test results are extracted from the test results, including:

[0036] determining key temperature nodes and key stress nodes in the short-term accelerated aging test and the endurance tensile test;

[0037] taking detection data corresponding to the key temperature nodes and the key stress nodes in the test results as a plurality of key detection data.

[0038] According to the method for evaluating the remaining endurance life of the GH4169 superalloy, the method further includes:

[0039] taking the test results of the sample, the accelerated aging test mathematical model, the accelerated aging coefficient, the field operating condition data and the remaining endurance life as report contents to generate a remaining endurance life evaluation report.

[0040] In another aspect, the application further provides a system for evaluating the remaining endurance life of a GH4169 superalloy, including:

[0041] an acquisition module configured to acquire test results of a GH4169 superalloy sample obtained by performing a short-term accelerated aging test and an endurance tensile test on the sample, and to acquire field operating condition data of a GH4169 superalloy component to be evaluated in actual use;

[0042] a modeling module configured to determine an accelerated aging test mathematical model according to a Larson-Miller parameter expression, wherein the accelerated aging test mathematical model is used to represent a functional relationship between different service temperatures and endurance lives under the same stress state;

[0043] a calculation module configured to determine an accelerated aging coefficient according to endurance lives of the GH4169 superalloy sample under different experimental temperatures in a test condition and expected lives under different service temperatures in actual use under the same stress state;

[0044] an evaluation module configured to obtain a remaining endurance life of the GH4169 superalloy component according to the test results of the sample, the accelerated aging test mathematical model, the accelerated aging coefficient and the field operating condition data.

[0045] The application provides a GH4169 high-temperature alloy residual endurance life evaluation method and system. BRIEF DESCRIPTION OF DRAWINGS

[0046] In order to more clearly illustrate the technical solutions in the application or prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the application, and other drawings can be obtained by those skilled in the art without any creative effort based on these drawings.

[0047] Figure 1 Fig. 1 is a flowchart of the GH4169 high-temperature alloy residual endurance life evaluation method provided by the embodiment of the application;

[0048] Figure 2 Fig. 2 is a distribution diagram of fracture time of the GH4169 high-temperature alloy sample under different stress states at 650 DEG C in the endurance tensile test;

[0049] Figure 3 Fig. 3 is a fitting curve between the test stress and the Larson-Miller parameter of the GH4169 high-temperature alloy sample in the endurance tensile test;

[0050] Figure 4 Fig. 4 is a structural diagram of the GH4169 high-temperature alloy residual endurance life evaluation system provided by the embodiment of the application;

[0051] Figure 5Fig. 1 is a structural schematic diagram of an electronic device provided by an embodiment of the present application. DETAILED DESCRIPTION

[0052] In order to make the objects, technical solutions and advantages of the present application clearer, the technical solutions of the present application will be described clearly and completely below with reference to the drawings in the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of protection of the present application.

[0053] The technical solutions of the embodiments of the present application will be described below with reference to the drawings. Figures 1 to 5 The details of the GH4169 high-temperature alloy residual life evaluation method and system provided by the embodiments of the present application will be described.

[0054] Figure 1 Fig. 2 is a flowchart of a GH4169 high-temperature alloy residual life evaluation method provided by an embodiment of the present application.

[0055] As shown in Fig. 2, the GH4169 high-temperature alloy residual life evaluation method provided by the embodiments of the present application mainly includes the following steps: Figure 1

[0056] Step 110: Obtain sample detection results obtained by performing a short-term accelerated aging test and a stress rupture test on a GH4169 high-temperature alloy sample, and obtain field working condition data of a GH4169 high-temperature alloy component to be evaluated in actual use.

[0057] In this embodiment, a reasonable short-term accelerated aging test and stress rupture test can be formulated according to the field working condition data of the GH4169 high-temperature alloy component to be evaluated in actual use, so as to ensure the effectiveness of the sample detection results obtained by the test.

[0058] Step 120: Determine an accelerated aging test mathematical model according to a Larson-Miller parameter expression, wherein the accelerated aging test mathematical model is used to represent a functional relationship between different service temperatures and stress rupture life under the same stress state.

[0059] In this embodiment, the accelerated aging test mathematical model can describe the functional relationship between two different service temperatures and their respective stress rupture life under the same stress state. In this way, the stress rupture life of another group can be directly calculated by the accelerated aging test mathematical model in the case that a group of service temperatures and stress rupture life are known and the service temperature of another group is known.

[0060] ​Step 130: determining the accelerated aging coefficient according to the stress rupture life of the GH4169 high-temperature alloy sample at different experimental temperatures in the test condition and the expected life of the GH4169 high-temperature alloy sample at different service temperatures in actual use under the same stress state.

[0061] It can be understood that the accelerated aging coefficient can represent the difference multiple of the aging speed of the GH4169 high-temperature alloy material under the accelerated working condition and the actual working condition.

[0062] Step 140: obtaining the residual stress rupture life of the GH4169 high-temperature alloy component according to the sample detection result, the accelerated aging test mathematical model, the accelerated aging coefficient, and the field working condition data.

[0063] The scheme provided in the embodiment can quickly and accurately evaluate the residual stress rupture life of the GH4169 high-temperature alloy component under the actual service condition by combining the sample detection result obtained through a simple and convenient test, the field working condition data of the GH4169 high-temperature alloy component to be evaluated in actual use, and the accelerated aging coefficient, and cooperating with the accelerated aging test mathematical model, thereby improving the convenience and reliability of the evaluation link.

[0064] In the embodiment, before the test, the field working condition data of the GH4169 high-temperature alloy component to be evaluated can be determined first, mainly including necessary information such as specification parameters and service parameters. Then, a reasonable short-term accelerated aging test scheme and a stress rupture test scheme are formulated according to the service temperature of the GH4169 high-temperature alloy component. Subsequently, the fastener material used in the supercritical generator set in the power plant is cut off according to the short-term accelerated aging test scheme and the stress rupture test scheme. Finally, the related tests are carried out by reasonable arrangement according to the short-term accelerated aging test scheme and the stress rupture test scheme.

[0065] In an embodiment, the short-term accelerated aging test and the stress rupture test are performed on the GH4169 high-temperature alloy sample, specifically including:

[0066] First, the GH4169 high-temperature alloy sample is subjected to first aging treatment at a first set temperature to obtain a preliminary aging sample; wherein the first set temperature is the maximum precipitation temperature of the δ phase stably precipitated in the GH4169 high-temperature alloy sample.

[0067] In the embodiment, the first set temperature can be specifically 970±10℃, and the duration of the first aging treatment can be 1 hour.

[0068] Then, the preliminary aging sample is subjected to second aging treatment at a second set temperature to obtain an aging damage sample; wherein the second set temperature is lower than the first set temperature.

[0069] Specifically, the second set temperature can be 900 DEG C, and after the first aging treatment, the preliminary aging sample is subjected to the second aging treatment at 900 DEG C, so that the δ phase can be rapidly precipitated in the GH4169 high-temperature alloy sample matrix, and finally the aging structure equivalent to the aging structure in different periods under actual working conditions is obtained.

[0070] In actual application, the aging damage sample with different aging damage degrees is obtained by using the short-time accelerated aging test on the GH4169 high-temperature alloy sample without service, and then the aging damage sample is cooled to room temperature, and at least a part of the aging damage sample is made into a plurality of hardness test pieces for the stress-rupture test.

[0071] Finally, the stress-rupture test is performed on the aging damage sample under different stress states, and the sample test result is obtained.

[0072] In an embodiment, the accelerated aging test mathematical model is determined according to the Larson-Miller parameter expression, and specifically includes:

[0073] On the one hand, the first function expression between the Larson-Miller parameter and the first service temperature and the first stress-rupture life is established according to the Larson-Miller parameter expression.

[0074] In this embodiment, the first function expression is specifically as follows:

[0075] (1)

[0076] Wherein, LMP represents the Larson-Miller parameter, T1 represents the first service temperature, t1 represents the first stress-rupture life, and C represents a constant related to the composition of the steel.

[0077] On the other hand, the second function expression between the Larson-Miller parameter and the second service temperature and the second stress-rupture life is established according to the Larson-Miller parameter expression.

[0078] In this embodiment, the second function expression is specifically as follows:

[0079] (2)

[0080] Wherein, LMP represents the Larson-Miller parameter, T2 represents the second service temperature, t2 represents the second stress-rupture life, and C represents a constant related to the composition of the steel.

[0081] Finally, based on the simultaneous condition that the Larson-Miller parameters are equal under the same stress state, the first function expression and the second function expression are combined to obtain the accelerated aging test mathematical model.

[0082] It can be understood that, since the Larson-Miller parameters are equal under the same stress state, the above two formulas are established as an equation under the same stress state, as follows:

[0083] (3)

[0084] Transforming the equation, the expression of the accelerated aging test mathematical model can be obtained, as follows:

[0085] (4)

[0086] Wherein, T1 represents the first service temperature, T2 represents the second service temperature, t1 represents the first stress rupture life, t2 represents the second stress rupture life, and C represents a constant related to the composition of the steel.

[0087] In an embodiment, under the same stress state, the accelerated aging coefficient is determined according to the stress rupture life of the GH4169 superalloy sample under different experimental temperatures in the test condition and the expected life under different service temperatures in actual use, and specifically includes the following steps.

[0088] In the first step, under the same stress state, the GH4169 superalloy sample is input into the Larson-Miller parameter expression at different experimental temperatures in the test condition and the respective corresponding stress rupture life, to obtain a plurality of Larson-Miller test parameters.

[0089] In the second step, the different service temperatures in actual use and the respective corresponding expected life are input into the Larson-Miller parameter expression, to obtain a plurality of Larson-Miller expected parameters.

[0090] In the third step, each Larson-Miller test parameter is divided by the corresponding Larson-Miller expected parameter, to obtain a plurality of Larson-Miller ratios.

[0091] In the fourth step, the average of the plurality of Larson-Miller ratios is calculated, to obtain the accelerated aging coefficient.

[0092] In some embodiments, after obtaining the accelerated aging coefficient, subsequently, part of the sample detection results or field working condition data that are not involved in the calculation of the accelerated aging coefficient can be selected, the stress rupture life is predicted using the determined accelerated aging coefficient, and the actual result is compared. For example, the stress rupture life of the GH4169 superalloy under other similar working conditions is predicted using the accelerated aging coefficient, and it is determined whether the predicted stress rupture life is close to the actual stress rupture life.

[0093] In actual application, the prediction error value can be obtained by subtracting the predicted permanent life from the actual permanent life, and the prediction error value is compared with the preset error upper limit value. If the prediction error value exceeds the error upper limit value, it is determined that the prediction error value is large, and the error source can be further analyzed, such as whether the model selection is reasonable and whether the data calculation is accurate, and then the acceleration aging coefficient is adjusted, or the model is reselected for calculation, until the prediction error value is lower than the error upper limit value, and a more accurate and reliable acceleration aging coefficient is obtained.

[0094] In an embodiment, the residual permanent life of the GH4169 high-temperature alloy component is obtained according to the test results, the mathematical model of the accelerated aging test, the accelerated aging coefficient, and the field working condition data, and specifically includes:

[0095] Firstly, a plurality of key test results are extracted from the test results.

[0096] In a specific implementation, the plurality of key test results are extracted from the test results, and specifically include:

[0097] Firstly, the key temperature nodes and the key stress nodes in the short-term accelerated aging test and the permanent tensile test are determined.

[0098] Then, the detection data corresponding to the key temperature nodes and the key stress nodes in the test results are taken as the plurality of key detection data.

[0099] It can be understood that the performance of the GH4169 high-temperature alloy material is extremely sensitive to temperature, and the permanent life at different experimental temperatures is obviously different. High temperature can accelerate atomic diffusion and dislocation movement, and accelerate the damage of the GH4169 high-temperature alloy material. Therefore, the key temperature nodes can cover the permanent life of the GH4169 high-temperature alloy component at the actual service temperature and the possible extreme temperature, for example, the fracture time (i.e. the permanent life) of the GH4169 high-temperature alloy sample at the key temperature nodes of 650℃, 700℃, 750℃, etc. can be taken as the key detection data.

[0100] In addition, stress is an important factor leading to fatigue and creep of the GH4169 high-temperature alloy material. The permanent life of the GH4169 high-temperature alloy material will change significantly under different stress states. Therefore, low, medium and high stress states can be taken as key stress nodes, for example, the permanent life of the GH4169 high-temperature alloy sample at the key stress nodes of 400MPa, 500MPa, 600MPa, etc. can be taken as the key detection data.

[0101] Secondly, the experimental temperature and the permanent life in each key test result and the field service temperature in the field working condition data are respectively input into the mathematical model of the accelerated aging test, and a plurality of theoretical lives are calculated.

[0102] Thirdly, the residual life of the GH4169 high-temperature alloy component is calculated according to the multiple theoretical lives, the accelerated aging coefficient and the used time of the GH4169 high-temperature alloy component in the field operation data.

[0103] In one implementation, the residual life of the GH4169 high-temperature alloy component is calculated according to the multiple theoretical lives, the accelerated aging coefficient and the used time of the GH4169 high-temperature alloy component in the field operation data, specifically including:

[0104] Firstly, each theoretical life is multiplied by the accelerated aging coefficient to obtain multiple equivalent lives.

[0105] Then, the multiple equivalent lives are subjected to mean value operation to obtain a life mean value.

[0106] Finally, the life mean value is subtracted from the used time of the GH4169 high-temperature alloy component in the field operation data to obtain the residual life.

[0107] In the embodiment, the multiple equivalent lives are subjected to mean value operation to further calculate the residual life, which can further improve the calculation accuracy of the residual life.

[0108] In one embodiment, the above-mentioned residual life evaluation method of the GH4169 high-temperature alloy can further include:

[0109] The sample detection results, the accelerated aging test mathematical model, the accelerated aging coefficient, the field operation data and the residual life are taken as report contents to generate a residual life evaluation report.

[0110] In actual application, the sample detection results, the accelerated aging test mathematical model, the accelerated aging coefficient, the field operation data and the residual life and other data in the process of evaluating the residual life of the GH4169 high-temperature alloy component can be summarized to be fed back to the user in the form of the residual life evaluation report, which is convenient for the user to intuitively and clearly know the evaluation result of the residual life of the GH4169 high-temperature alloy.

[0111] In the embodiment, the residual life of the GH4169 high-temperature alloy component is calculated according to the multiple equivalent lives, the accelerated aging coefficient and the used time of the GH4169 high-temperature alloy component in the field operation data, and the residual life of the GH4169 high-temperature alloy component is calculated according to the multiple equivalent lives, the accelerated aging coefficient and the used time of the GH4169 high-temperature alloy component in the field operation data.

[0112] Table 1 Partial data of sample detection results

[0113]

[0114] It can be understood that the rupture time in Table 1 is the endurance life of the GH4169 superalloy sample.

[0115] Figure 2 The distribution of the rupture time of the GH4169 superalloy sample in the endurance tensile test at 650°C under different stress states is shown in the following table, Figure 2 wherein the abscissa is the test stress, in MPa, and the ordinate is the rupture time, in h.

[0116] As Figure 2 can be seen from the relationship curve between the rupture time and the test stress, the rupture time gradually decreases with the increase of the test stress, and the rupture time of the GH4169 superalloy sample at 650°C after different short-time accelerated aging times is not much different, and the rupture time of the GH4169 superalloy sample without aging tends to be flat after the test stress increases.

[0117] Figure 3 The fitting curve between the test stress and the Larson-Miller parameter of the GH4169 superalloy sample in the endurance tensile test is shown in the following table, Figure 3 wherein the abscissa is the test stress, in MPa, and the ordinate is the Larson-Miller parameter. It can be seen from Figure 3 that the Larson-Miller parameters corresponding to different stress states overall change linearly.

[0118] By fitting the test stress and the Larson-Miller parameter, the endurance life of the unserved GH4169 superalloy component under different stress states can be obtained, in which the constant C of the GH4169 alloy component is set to 20, and according to the Larson-Miller parameter expression, the parameter relationship expression under the unserved state and the parameter relationship expression under the test state are established, as follows:

[0119] (5)

[0120] (6)

[0121] wherein, represents the Larson-Miller parameter under the unserved state, represents the Larson-Miller parameter under the test state, represents the test stress.

[0122] When the test stress is 550 MPa, it can be deduced that the fracture time after aging for 1134 h is 81.28 h, and the residual life of the GH4169 high-temperature alloy component under the service temperature of 650 ℃ is 6.8 x 10 5 h.

[0123] Based on the same general inventive concept, the present application also protects a system for evaluating the residual life of a GH4169 high-temperature alloy, and the following describes the system for evaluating the residual life of a GH4169 high-temperature alloy provided by the present application, which can be mutually referred to with the method for evaluating the residual life of a GH4169 high-temperature alloy described above.

[0124] As shown in the system for evaluating the residual life of a GH4169 high-temperature alloy provided by the present application, the system specifically includes: Figure 4 The obtaining module 210 is configured to obtain the sample detection results obtained by performing the short-term accelerated aging test and the endurance tensile test on the GH4169 high-temperature alloy sample, and obtain the field working condition data of the GH4169 high-temperature alloy component to be evaluated in actual use.

[0125] The modeling module 220 is configured to determine an accelerated aging test mathematical model according to a Larson-Miller parameter expression, wherein the accelerated aging test mathematical model is used to represent the functional relationship between different service temperatures and the life under the same stress state.

[0126] The calculation module 230 is configured to determine an accelerated aging coefficient according to the life of the GH4169 high-temperature alloy sample under different experimental temperatures in the test condition and the expected life under different service temperatures in actual use under the same stress state.

[0127] The evaluation module 240 is configured to obtain the residual life of the GH4169 high-temperature alloy component according to the sample detection results, the accelerated aging test mathematical model, the accelerated aging coefficient, and the field working condition data.

[0128] The system provided by the present application can quickly and accurately evaluate the residual life of the GH4169 high-temperature alloy component under actual service conditions according to simple, convenient, and non-destructive sample testing, which can avoid economic losses caused by shutdown or pipeline cutting, and can timely evaluate the residual life of the GH4169 high-temperature alloy material due to its convenient and fast characteristics, effectively preventing accidents caused by material aging failure.

[0129]

[0130] ​As to the system in the above-mentioned embodiments, the specific manner in which each module performs operations has been described in detail in the embodiments related to the method, and will not be described in detail here.

[0131] Figure 5 is a structural schematic diagram of an electronic device provided by an embodiment of the present application.

[0132] As Figure 5 shown, the electronic device can include a processor 310, a communications interface 320, a memory 330, and a communications bus 340, wherein the processor 310, the communications interface 320, and the memory 330 complete communications with each other through the communications bus 340. The processor 310 can invoke a logical instruction in the memory 330 to execute the GH4169 high-temperature alloy residual endurance life evaluation method provided by each of the above-mentioned embodiments, which includes: obtaining sample detection results obtained by performing a short-time accelerated aging test and a endurance tensile test on a GH4169 high-temperature alloy sample, and obtaining field working condition data of a GH4169 high-temperature alloy component to be evaluated in actual use; determining an accelerated aging test mathematical model according to a Larson-Miller parameter expression, wherein the accelerated aging test mathematical model is used to represent a functional relationship between different service temperatures and endurance life under the same stress state; determining an accelerated aging coefficient according to the endurance life of the GH4169 high-temperature alloy sample under different experimental temperatures in the test conditions and the expected life under different service temperatures in actual use under the same stress state; and obtaining the residual endurance life of the GH4169 high-temperature alloy component according to the sample detection results, the accelerated aging test mathematical model, the accelerated aging coefficient, and the field working condition data.

[0133] In addition, the logical instruction in the memory 330 described above can be implemented in the form of a software function unit and sold or used as an independent product when used, and can be stored in a computer-readable storage medium. Based on such understanding, the technical solutions of the present application essentially or the part that contributes to the prior art or part of the technical solutions can be embodied in the form of a software product, and the computer software product is stored in a storage medium, includes several instructions to make a computer device (which can be a personal computer, a server, or a network device, etc.) execute all or part of the steps of the method described in each embodiment of the present application. The foregoing storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0134] In another aspect, the present application also provides a computer program product, which comprises a computer program stored on a non-transitory computer readable storage medium, and the computer program can be executed by a processor to enable a computer to perform the method for evaluating the residual life of GH4169 superalloy provided by any of the above embodiments, which comprises: obtaining sample test results obtained by performing a short-term accelerated aging test and a stress rupture test on a GH4169 superalloy sample, and obtaining field working condition data of a GH4169 superalloy component to be evaluated in actual use; determining an accelerated aging test mathematical model according to a Larson-Miller parameter expression, wherein the accelerated aging test mathematical model is used to represent a functional relationship between different service temperatures and stress rupture life under the same stress state; determining an accelerated aging coefficient according to the stress rupture life of the GH4169 superalloy sample at different experimental temperatures in the test conditions and the expected life at different service temperatures in actual use under the same stress state; and obtaining the residual life of the GH4169 superalloy component according to the sample test results, the accelerated aging test mathematical model, the accelerated aging coefficient, and the field working condition data.

[0135] In another aspect, the present application also provides a non-transitory computer readable storage medium, which stores a computer program, and the computer program can be executed by a processor to implement the method for evaluating the residual life of GH4169 superalloy provided by any of the above embodiments, which comprises: obtaining sample test results obtained by performing a short-term accelerated aging test and a stress rupture test on a GH4169 superalloy sample, and obtaining field working condition data of a GH4169 superalloy component to be evaluated in actual use; determining an accelerated aging test mathematical model according to a Larson-Miller parameter expression, wherein the accelerated aging test mathematical model is used to represent a functional relationship between different service temperatures and stress rupture life under the same stress state; determining an accelerated aging coefficient according to the stress rupture life of the GH4169 superalloy sample at different experimental temperatures in the test conditions and the expected life at different service temperatures in actual use under the same stress state; and obtaining the residual life of the GH4169 superalloy component according to the sample test results, the accelerated aging test mathematical model, the accelerated aging coefficient, and the field working condition data.

[0136] The apparatus embodiments described above are merely illustrative, wherein the units shown as separate components can or can not be physically separate, and the components shown as units can or can not be physical units, i.e., can be located in one place, or can be distributed on multiple network units. Part or all of the modules can be selected to achieve the purpose of the present embodiment scheme according to actual needs. Those skilled in the art can understand and implement it without creative labor.

[0137] Those skilled in the art can clearly understand the implementation of the various embodiments by means of software and necessary general hardware platforms through the description of the above embodiments, and of course, the embodiments can also be implemented by hardware. Based on such understanding, the above technical solutions can be embodied in the form of a software product, and the computer software product can be stored in a computer readable storage medium, such as a ROM / RAM, a magnetic disk, an optical disk, etc., and includes a plurality of instructions for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the method described in each embodiment or some parts of the embodiment.

[0138] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing examples, or make equivalent replacement for some technical features thereof; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for assessing the remaining creep life of GH4169 high-temperature alloy, characterized in that, include: Obtain the test results of the GH4169 high-temperature alloy samples by conducting short-time accelerated aging test and endurance tensile test, and obtain the field working condition data of the GH4169 high-temperature alloy components to be evaluated in actual use. Based on the Larson-Miller parameter expression, an accelerated aging test mathematical model is determined. This model characterizes the functional relationship between different service temperatures and aging life under the same stress state. Given one set of service temperatures and aging lives, and another set of service temperatures, the aging life of the other set can be directly calculated using the accelerated aging test mathematical model. The expression for the accelerated aging test mathematical model is as follows: Where T1 represents the first service temperature, T2 represents the second service temperature, t1 represents the first rupture life, t2 represents the second rupture life, and C represents a constant related to the steel composition; Under the same stress state, the accelerated aging coefficient is determined based on the creep life of GH4169 high-temperature alloy specimens at different experimental temperatures under test conditions and the expected life at different service temperatures in actual use. The critical temperature and critical stress points in the short-term accelerated aging test and the endurance tensile test are determined. The test data corresponding to the critical temperature and critical stress points in the test results are used as multiple critical test data. The experimental temperature and endurance life in each critical test result and the field service temperature in the field operating condition data are input into the accelerated aging test mathematical model to calculate multiple theoretical lives. Each theoretical life is multiplied by the accelerated aging coefficient to obtain multiple equivalent lives. The average of the multiple equivalent lives is calculated to obtain the average life. The difference between the average life and the used time of the GH4169 high-temperature alloy component in the field operating condition data is used to obtain the remaining endurance life.

2. The method for assessing the remaining creep life of GH4169 high-temperature alloy according to claim 1, characterized in that, Short-time accelerated aging test and endurance tensile test were performed on GH4169 high-temperature alloy samples, including: The GH4169 high-temperature alloy sample was subjected to the first aging treatment at a first set temperature to obtain a preliminary aged sample; wherein, the first set temperature is the maximum precipitation temperature at which the δ phase of the GH4169 high-temperature alloy sample can be stably precipitated. The preliminary aging sample is subjected to a second aging treatment at a second set temperature to obtain an aging damage sample; wherein the second set temperature is lower than the first set temperature. The aging and damaged specimens were subjected to long-term tensile tests under different stress states to obtain the specimen test results.

3. The method for assessing the remaining creep life of GH4169 high-temperature alloy according to claim 1, characterized in that, Based on the Larson-Miller parameter expression, the mathematical model for accelerated aging tests is determined, including: Based on the Larson-Miller parameter expression, a first functional expression is established between the Larson-Miller parameters and the first service temperature and the first survivability. Based on the Larson-Miller parameter expression, a second functional expression is established between the Larson-Miller parameters and the second service temperature and the second aging lifetime; Based on the condition that the Larson-Miller parameters are equal under the same stress state, the first function expression and the second function expression are combined to obtain the mathematical model of accelerated aging test.

4. The method for assessing the remaining creep life of GH4169 high-temperature alloy according to claim 1, characterized in that, Under the same stress state, based on the creep rupture life of GH4169 high-temperature alloy specimens at different experimental temperatures and the expected life at different service temperatures in actual use, the accelerated aging coefficient is determined, including: Under the same stress state, the GH4169 high-temperature alloy specimens were input into the Larson-Miller parameter expression at different experimental temperatures and their corresponding creep lifes under the test conditions to obtain multiple Larson-Miller test parameters. By inputting the different service temperatures and their corresponding expected lifespans in actual use into the Larson-Miller parameter expression, multiple Larson-Miller expected parameters are obtained. By dividing each Larson-Miller experimental parameter by the corresponding Larson-Miller expected parameter, multiple Larson-Miller ratios are obtained. The accelerated aging coefficient is obtained by averaging the multiple Larson-Miller ratios.

5. The method for assessing the remaining creep life of GH4169 high-temperature alloy according to claim 1, characterized in that, The method further includes: The remaining lifespan assessment report is generated by taking the test results of the sample, the mathematical model of the accelerated aging test, the accelerated aging coefficient, the field working condition data, and the remaining lifespan as the report content.

6. A system for assessing the remaining crease life of GH4169 high-temperature alloy, characterized in that, include: The acquisition module is used to acquire the test results of GH4169 high-temperature alloy samples obtained by short-time accelerated aging test and endurance tensile test, and to acquire the field working condition data of the GH4169 high-temperature alloy components to be evaluated in actual use. The modeling module is used to determine the mathematical model for accelerated aging tests based on the Larson-Miller parameter expression. This mathematical model characterizes the functional relationship between different service temperatures and aging life under the same stress state. Given one set of service temperatures and aging lives, and another set of service temperatures, the aging life of the other set can be directly calculated using the accelerated aging test mathematical model. The expression for the accelerated aging test mathematical model is as follows: Where T1 represents the first service temperature, T2 represents the second service temperature, t1 represents the first rupture life, t2 represents the second rupture life, and C represents a constant related to the steel composition; The calculation module is used to determine the accelerated aging coefficient based on the creep life of GH4169 high-temperature alloy specimens under different experimental temperatures in the test conditions and the expected life under different service temperatures in actual use, under the same stress state. The evaluation module is used to determine the critical temperature and critical stress points in the short-term accelerated aging test and the endurance tensile test. The test data corresponding to the critical temperature and critical stress points in the test results are used as multiple critical test data. The experimental temperature and endurance life in each critical test result, as well as the field service temperature in the field operating condition data, are input into the accelerated aging test mathematical model to calculate multiple theoretical lives. Each theoretical life is multiplied by the accelerated aging coefficient to obtain multiple equivalent lives. The average of the multiple equivalent lives is calculated to obtain the average life. The difference between the average life and the used time of the GH4169 high-temperature alloy component in the field operating condition data is used to obtain the remaining endurance life.

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