Creep life prediction method for nickel-based single crystal superalloy blades

Abstract

The present invention discloses a method for predicting the creep life of a nickel-based single-crystal high-temperature alloy blade. Based on the stress distribution and service temperature of the dangerous parts of the nickel-based single-crystal high-temperature alloy blade during actual service, full-life creep tests and creep interruption tests of the nickel-based single-crystal high-temperature alloy blade are carried out, and the matrix phase channel width and γ' strengthening phase size at different creep times are obtained by fitting a first relationship between the matrix phase channel width and the creep time, and a second relationship between the γ' strengthening phase size and the creep time is fitted, and then a third relationship between the creep life of the nickel-based single-crystal high-temperature alloy blade and the matrix phase channel width and the γ' strengthening phase size is obtained by transformation. The third relationship between the creep life of the nickel-based single-crystal high-temperature alloy blade and the matrix phase channel width and the γ' strengthening phase size is fully considered. The influence of the matrix phase channel width, the γ' strengthening phase size, the stress distribution of the dangerous parts of the nickel-based single-crystal high-temperature alloy blade during actual service and the service temperature on the creep life is fully considered. The creep life of the test piece to be tested is quickly and accurately predicted by the three relationship formulas.

Description

Technical Field

[0001] The present invention relates to the technical field of material mechanical property prediction, and in particular to a method for predicting the creep life of a nickel-based single crystal high-temperature alloy blade. Background Art

[0002] Nickel-based single-crystal superalloys, with their excellent mechanical properties at high temperatures, have become an irreplaceable key material for military and civilian engine turbine blades. They are widely used in the manufacture of aircraft engine and gas turbine blades. However, nickel-based single-crystal superalloy blades are subjected to centrifugal loads in high-temperature environments, and creep is inevitable during service, potentially causing significant losses. Research has shown that creep is a major failure mode in the airfoil of nickel-based single-crystal turbine blades. Therefore, accurately predicting the creep life of nickel-based single-crystal superalloys is of great significance for the design and assessment of the life of nickel-based single-crystal turbine blades.

[0003] For example, Chinese invention patent application CN114813329B discloses a method for predicting the remaining life of a nickel-based single crystal high-temperature alloy under random creep loads, comprising: (1) conducting full-life creep tests and interrupted creep tests on standard parts under different loads to obtain matrix phase channel width-time curves under different loads; (2) dimensionlessly converting the creep time under different loads to obtain matrix phase channel width-normalized time curves; (3) obtaining a matrix phase channel width-normalized time function equation; (4) for a batch of standard parts subjected to random creep loads, selecting some of the standard parts and obtaining the average value of the matrix phase channel width of the standard parts; (5) substituting the average value of the matrix phase channel width obtained in (4) into the matrix phase channel width-normalized time function equation established in (3), and combining the time that the current standard parts have been subjected to random creep loads to obtain the remaining life of the batch of standard parts under the same random creep load.

[0004] However, the excellent high-temperature performance of nickel-based single-crystal high-temperature alloys is mainly related to the large amount of γ' strengthening phase precipitated continuously in the γ matrix phase. However, in the above prediction method, the prediction of its creep life only considers the width of the matrix phase channel, and does not consider the influence of the size of the γ' strengthening phase. The prediction accuracy is low. Although the normalization treatment can greatly improve the prediction efficiency, it does not consider the influence of stress distribution and service temperature on creep life during the actual service of nickel-based single-crystal high-temperature alloy blades, which further reduces the accuracy of creep life prediction. Summary of the Invention

[0005] The present invention provides a method for predicting the creep life of a nickel-based single crystal high-temperature alloy blade, so as to solve the technical problem of low prediction accuracy of the existing method for predicting the creep life of a nickel-based single crystal high-temperature alloy blade.

[0006] According to one aspect of the present invention, a method for predicting the creep life of a nickel-based single-crystal high-temperature alloy blade is provided, comprising the following steps: S10: obtaining the stress distribution and service temperature of a dangerous part of a nickel-based single-crystal high-temperature alloy blade according to a typical service condition of an aero-engine; S20: conducting a full-life creep test of the nickel-based single-crystal high-temperature alloy blade according to the stress distribution and service temperature to obtain the creep life and full-life creep curve of the nickel-based single-crystal high-temperature alloy blade; S30: determining the creep interruption time according to the full-life creep curve to conduct a creep interruption test; S40: extracting a cross-sectional sample at the test fracture position in the full-life creep test and a cross-sectional sample at the same position in the creep interruption test, and scanning and obtaining Microstructure of the cross-sectional sample; S50: Measure and obtain the matrix phase channel width and γ' strengthening phase size of the nickel-based single crystal high-temperature alloy blade at different creep times from the microstructure to fit the first relationship between the matrix phase channel width and the creep time, and fit the second relationship between the γ' strengthening phase size and the creep time, and then transform to obtain the third relationship between the creep life of the nickel-based single crystal high-temperature alloy blade and the matrix phase channel width and γ' strengthening phase size; S6: Confirm the creep time based on the service time of the test piece, predict the matrix phase channel width of the test piece based on the first relationship, predict the γ' strengthening phase size of the test piece based on the second relationship, and predict the creep life of the test piece based on the third relationship.

[0007] As a further improvement of this solution:

[0008] Furthermore, the first relation is as follows:

[0009] ;

[0010] Where d is the matrix phase channel width, t is the creep time, d0 is the initial matrix phase channel width, and c1 is the material parameter one.

[0011] Furthermore, the second relationship is as follows:

[0012] ;

[0013] Where r is the size of the γ' strengthening phase, r0 is the initial γ' strengthening phase size, and c2 is the second material parameter.

[0014] Furthermore, the transformation process of the third relational expression is as follows:

[0015] The relationship between the matrix phase channel width and the γ' strengthening phase size and the minimum creep rate at a constant temperature is determined as follows:

[0016] ;

[0017] The fitting relationship between creep life and minimum creep rate is:

[0018] ;

[0019] The third relation obtained by transformation is:

[0020] ;

[0021] Where, is the minimum creep rate, σ is the loading stress, σ or is the Orowan stress, D is the diffusion coefficient of the strengthening phase in the matrix, G is the shear modulus, K is the Boltzmann constant, T is the service temperature, m is the fitting parameter, is the second fitting parameter, is the creep life.

[0022] Furthermore, the Orowan stress should satisfy the following relationship:

[0023] ;

[0024] Where b is the Burgers vector.

[0025] Furthermore, it is characterized in that step S10 specifically includes the following steps: according to the typical service conditions of the aircraft engine, the service speed and temperature field of the nickel-based single crystal high-temperature alloy blade are obtained, and the stress distribution and service temperature of the dangerous parts of the nickel-based single crystal high-temperature alloy blade are calculated in combination with finite element simulation means.

[0026] Furthermore, step S20 specifically includes the following steps: S21: designing and manufacturing a simulation part of a nickel-based single crystal high-temperature alloy blade according to the temperature field and stress distribution, and iteratively calculating the loading stress at the clamping end of the simulation part during the full-life creep test, wherein the material of the simulation part is a nickel-based single crystal high-temperature alloy, and the structural characteristics of the creep test assessment part of the simulation part are the same as the structural characteristics of the dangerous parts of the part to be tested; S22: the creep testing machine clamps the simulation part, and maintains it for a preset time after heating to the service temperature to apply loading stress to the clamping end of the simulation part, and then carries out a full-life creep test of the simulation part until the simulation part creep breaks, thereby obtaining the creep life and full-life creep curve of the nickel-based single crystal high-temperature alloy blade.

[0027] Furthermore, in step S22, the temperature error of the simulated component after heating is no more than ±3°C.

[0028] Furthermore, step S30 specifically includes the following steps: determining the start time of the second creep stage and the start time of the third creep stage as creep interruption time according to the full-life creep curve, so as to perform two groups of creep interruption tests.

[0029] Furthermore, step S40 specifically includes the following steps: extracting cross-sectional samples at the test fracture position in the full-life creep test and cross-sectional samples at the same position in the two groups of creep interruption tests, corroding them with a corrosive liquid, and polishing the cross-sectional samples with a polishing machine to observe the microstructure of the three groups of cross-sectional samples through a scanning electron microscope.

[0030] The present invention has the following beneficial effects:

[0031] The method for predicting the creep life of nickel-based single-crystal high-temperature alloy blades of the present invention conducts full-life creep tests on nickel-based single-crystal high-temperature alloy blades based on the stress distribution of dangerous parts of nickel-based single-crystal high-temperature alloy blades during actual service and under the conditions of service temperature, so as to improve the reliability of full-life creep test results, thereby improving the reliability of subsequent creep interruption test results and the prediction accuracy of creep life; through full-life creep tests and creep interruption tests, the matrix phase channel width and γ' strengthening phase size at different creep times are obtained to fit the first relationship between the matrix phase channel width and creep time, and the second relationship between the γ' strengthening phase size and creep time is fitted, and then the creep life of nickel-based single-crystal high-temperature alloy blades is transformed to obtain the relationship between the matrix phase channel width and γ' strengthening phase size. The third relationship between the size of the γ' strengthening phase is used to fully consider the influence of the matrix phase channel width and the γ' strengthening phase size on the creep life of the nickel-based single crystal high-temperature alloy blade; finally, the creep time is confirmed based on the service time of the test piece, so as to accurately predict the creep life of the test piece through three relationship formulas, and then the service time of the nickel-based single crystal high-temperature alloy blade can be effectively managed, and the maximum utilization can be achieved while avoiding creep failure; compared with the existing technology, this scheme fully considers the influence of the γ' strengthening phase size, the stress distribution of the dangerous parts of the nickel-based single crystal high-temperature alloy blade during actual service and the service temperature on the creep life in addition to the matrix phase channel width, and quickly and accurately predicts the creep life of the nickel-based single crystal high-temperature alloy blade, has strong practicality, and is suitable for wide promotion and application.

[0032] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0034] Figure 1 This is a flowchart of a method for predicting the creep life of a nickel-based single crystal high-temperature alloy blade according to a preferred embodiment of the present invention;

[0035] Figure 2Schematic diagram of the microstructure in the creep life prediction method of nickel-based single crystal high-temperature alloy blades in a preferred embodiment of the present invention;

[0036] Figure 3 This is a functional relationship diagram of the matrix phase channel width and creep time under different service temperatures and stress loads in the creep life prediction method of nickel-based single crystal high-temperature alloy blades in a preferred embodiment of the present invention;

[0037] Figure 4 This is a relationship curve between creep rupture life and minimum creep rate in the creep life prediction method of nickel-based single crystal high-temperature alloy blades in the preferred embodiment of the present invention. DETAILED DESCRIPTION

[0038] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0039] It should be understood that the terms "first," "second," and "third" are used merely as labels, and are not intended to limit the quantity of their objects.

[0040] like Figure 1 As shown, the method for predicting the creep life of nickel-based single crystal high-temperature alloy blades in this embodiment includes the following steps: S10: obtaining the stress distribution and service temperature of the dangerous parts of the nickel-based single crystal high-temperature alloy blades according to the typical service conditions of the aircraft engine; S20: conducting a full-life creep test of the nickel-based single crystal high-temperature alloy blades according to the stress distribution and service temperature to obtain the creep life and full-life creep curve of the nickel-based single crystal high-temperature alloy blades; S30: determining the creep interruption time according to the full-life creep curve to conduct a creep interruption test; S40: extracting the cross-sectional sample at the test fracture position in the full-life creep test and the cross-sectional sample at the same position in the creep interruption test, and scanning to obtain the cross-sectional test sample. S50: measuring the matrix phase channel width and γ' strengthening phase size of the nickel-based single crystal high-temperature alloy blade at different creep times from the microstructure to obtain a first relationship between the matrix phase channel width and the creep time, and a second relationship between the γ' strengthening phase size and the creep time, and then transforming to obtain a third relationship between the creep life of the nickel-based single crystal high-temperature alloy blade and the matrix phase channel width and the γ' strengthening phase size; S6: confirming the creep time based on the service time of the test piece, predicting the matrix phase channel width of the test piece based on the first relationship, predicting the γ' strengthening phase size of the test piece based on the second relationship, and predicting the creep life of the test piece based on the third relationship.

[0041] Specifically, the method for predicting the creep life of a nickel-based single-crystal high-temperature alloy blade of the present invention conducts a full-life creep test of the nickel-based single-crystal high-temperature alloy blade under the conditions of the stress distribution and service temperature of the dangerous parts of the nickel-based single-crystal high-temperature alloy blade during actual service, so as to improve the reliability of the full-life creep test results, thereby improving the reliability of the subsequent creep interruption test results and the prediction accuracy of the creep life; through the full-life creep test and the creep interruption test, the matrix phase channel width and the γ' strengthening phase size at different creep times are obtained, and the first relationship between the matrix phase channel width and the creep time is obtained by fitting, and the second relationship between the γ' strengthening phase size and the creep time is obtained by fitting, and then the creep life of the nickel-based single-crystal high-temperature alloy blade is transformed to obtain the relationship between the matrix phase channel width and the γ' strengthening phase size. 'The third relationship between the size of the strengthening phase is used to fully consider the influence of the matrix phase channel width and the γ' strengthening phase size on the creep life of the nickel-based single-crystal high-temperature alloy blade; finally, the creep time is confirmed based on the service time of the test piece, so as to accurately predict the creep life of the test piece through three relationship formulas, and then the service time of the nickel-based single-crystal high-temperature alloy blade can be effectively managed, and the maximum utilization can be achieved while avoiding creep failure; compared with the existing technology, this scheme fully considers the influence of the γ' strengthening phase size, the stress distribution of the dangerous parts of the nickel-based single-crystal high-temperature alloy blade during actual service and the service temperature on the creep life in addition to the matrix phase channel width, and quickly and accurately predicts the creep life of the nickel-based single-crystal high-temperature alloy blade, which is highly practical and suitable for wide promotion and application.

[0042] It should be understood that, as shown in the figure, the microstructure of the cross-sectional specimen has multiple different matrix phase channel widths and γ' strengthening phase sizes. Therefore, it is necessary to measure the matrix phase channel width and γ' strengthening phase size multiple times and take their average value as the parameter for fitting the first relationship.

[0043] In this embodiment, the first relationship is as follows:

[0044] ;

[0045] Where d is the matrix phase channel width, t is the creep time, d0 is the initial matrix phase channel width, and c1 is the material parameter one.

[0046] Specifically, based on the above first relationship, after determining the creep time of the nickel-based single crystal high-temperature alloy blade, its matrix phase channel width can be predicted to provide data support for the subsequent prediction of creep life.

[0047] It should be understood that the creep life predicted in this embodiment refers to the remaining working life of the nickel-based single crystal high-temperature alloy blade before creep failure.

[0048] It should be understood that the service time of a nickel-based single crystal high-temperature alloy blade is equivalent to the creep time. Therefore, once its service time is known, its creep time can be determined.

[0049] It should be understood that the initial matrix phase channel width and material parameters are all known parameters to those skilled in the art.

[0050] In this embodiment, the second relationship is as follows:

[0051] ;

[0052] Where r is the size of the γ' strengthening phase, r0 is the initial γ' strengthening phase size, and c2 is the second material parameter.

[0053] Specifically, based on the second relationship above, after determining the creep time of the nickel-based single crystal high-temperature alloy blade, its γ' strengthening phase size can be predicted to provide data support for the subsequent prediction of creep life.

[0054] It should be understood that the size of the initial γ' strengthening phase and the material parameters are all known parameters to those skilled in the art.

[0055] In this embodiment, the transformation process of the third relational expression is as follows:

[0056] The relationship between the matrix phase channel width and the γ' strengthening phase size and the minimum creep rate at a constant temperature is determined as follows:

[0057] ;

[0058] The fitting relationship between creep life and minimum creep rate is:

[0059] ;

[0060] The third relation obtained by transformation is:

[0061] ;

[0062] Where, is the minimum creep rate, σ is the loading stress, σ or is the Orowan stress, D is the diffusion coefficient of the strengthening phase in the matrix, G is the shear modulus, K is the Boltzmann constant, T is the service temperature, m is the fitting parameter, is the second fitting parameter, is the creep life.

[0063] Specifically, based on the relationship between the matrix phase channel width and the γ' strengthening phase size and the minimum creep rate at a constant temperature, as well as the relationship between the creep life and the minimum creep rate, the relationship between the matrix phase channel width and the γ' strengthening phase size and the creep life can be transformed. After the matrix phase channel width and the γ' strengthening phase size are predicted respectively by the first and second relationship formulas, the creep life can be predicted by the third relationship formula, so as to effectively manage the service time of the nickel-based single crystal high-temperature alloy blades and maximize the utilization of the nickel-based single crystal high-temperature alloy blades.

[0064] In this embodiment, the Orowan stress should satisfy the following relationship:

[0065] ;

[0066] Where b is the Burgers vector.

[0067] In this embodiment, step S10 specifically includes the following steps: according to the typical service conditions of the aircraft engine, the service speed and temperature field of the nickel-based single crystal high-temperature alloy blade are obtained, and the stress distribution and service temperature of the dangerous parts of the nickel-based single crystal high-temperature alloy blade are calculated by combining finite element simulation means.

[0068] Specifically, the above steps are used to obtain the stress distribution and service temperature of dangerous parts of the nickel-based single crystal high-temperature alloy blade, so as to improve the reliability of subsequent full-life creep test results, creep interruption test results and the prediction accuracy of creep life.

[0069] It should be understood that the dangerous parts of nickel-based single crystal high-temperature alloy blades refer to the root fillet, leading edge, blade crown and other parts.

[0070] In this embodiment, step S20 specifically includes the following steps: S21: designing and manufacturing a simulation part of a nickel-based single crystal high-temperature alloy blade according to the temperature field and stress distribution, and iteratively calculating the loading stress at the clamping end of the simulation part during the full-life creep test, wherein the material of the simulation part is a nickel-based single crystal high-temperature alloy, and the structural characteristics of the creep test assessment part of the simulation part are the same as the structural characteristics of the dangerous parts of the part to be tested; S22: the creep testing machine clamps the simulation part, and maintains it for a preset time after heating to the service temperature to apply loading stress to the clamping end of the simulation part, and then carries out a full-life creep test of the simulation part until the simulation part creep breaks, thereby obtaining the creep life and full-life creep curve of the nickel-based single crystal high-temperature alloy blade.

[0071] Specifically, a simulation part of a nickel-based single-crystal high-temperature alloy blade is designed and manufactured based on the temperature field and stress distribution, so that a full-life creep test and a subsequent creep interruption test can be carried out on the simulation part. The reliability of the test results is improved by ensuring that the material and structural characteristics of the simulation part are the same as those of the part to be tested. The loading stress at the clamping end of the clamped simulation part is iteratively calculated to make the stress distribution and stress gradient of the simulation part during the test consistent with the stress distribution and stress gradient of the part to be tested, further improving the reliability of the test results.

[0072] It should be understood that the test piece refers to a nickel-based single crystal high-temperature alloy blade actually in service.

[0073] In this embodiment, in step S22, the temperature error of the simulated component after heating is no more than ±3° C. Specifically, by ensuring that the temperature error of the simulated component after heating is no more than ±3° C., the working state of the DUT is realistically simulated, thereby improving the reliability of the test results.

[0074] In this embodiment, step S30 specifically includes the following steps: determining the start time of the second creep stage and the start time of the third creep stage as creep interruption time according to the full-life creep curve, so as to perform two groups of creep interruption tests.

[0075] Specifically, two groups of creep interruption tests are conducted to improve the accuracy of subsequent fitting of the first and second relationship equations.

[0076] In this embodiment, step S40 specifically includes the following steps: extracting cross-sectional samples at the test fracture position in the full-life creep test and cross-sectional samples at the same position in the two groups of creep interruption tests, corroding them with a corrosive liquid, and polishing the cross-sectional samples with a polishing machine to observe the microstructure of the three groups of cross-sectional samples through a scanning electron microscope.

[0077] Specifically, the microstructure is observed with an etching solution and polished with a polishing machine to improve the accuracy.

[0078] Optionally, the microstructure of the cross-section sample can be observed using Oringe software.

[0079] An embodiment is as follows:

[0080] According to the typical service conditions of a certain type of aircraft engine, the temperature and stress of dangerous parts of nickel-based single-crystal high-temperature alloy blades were calculated by finite element simulation, and the test load was determined, including test load characteristics such as low temperature high stress and high temperature low stress. Based on the above test loads, full-life creep tests and creep interruption tests were carried out in sequence.

[0081] Combined with SEM measurements of matrix phase channel width and γ' strengthening phase size in full life test, second stage interruption test and third stage interruption test under statistical test load, the first and second relationship equations are constructed, and then the third relationship equation is obtained by transformation.

[0082] The creep time is determined according to the service time of nickel-based single crystal high-temperature alloy blades in aircraft engines, so as to predict their creep life through three relationships.

[0083] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

[0084] This article uses specific examples to illustrate the principles and implementation methods of this application. The above examples are only used to help understand the method and core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression, there are objectively infinite specific structures. For ordinary technicians in this technical field, without departing from the principles of this application, they can make several improvements, modifications or changes, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the concept and technical solution of this application to other occasions without improvement, should be regarded as the scope of protection of this application.

Claims

1. A method for predicting the creep life of a nickel-based single crystal high-temperature alloy blade, characterized in that: The following steps are involved: S10: Obtain the stress distribution and service temperature of dangerous parts of nickel-based single crystal superalloy blades based on typical service conditions of aircraft engines; S20: Conduct full-life creep tests on nickel-based single-crystal superalloy blades based on stress distribution and service temperature to obtain the creep life and full-life creep curve of the nickel-based single-crystal superalloy blades; S30: Determine the creep interruption time according to the full life creep curve to conduct the creep interruption test; S40: Extract the cross-sectional specimen at the test fracture position in the full-life creep test and the cross-sectional specimen at the same position in the creep interruption test, and scan to obtain the microstructure of the cross-sectional specimen; S50: The matrix phase channel width and γ' strengthening phase size of the nickel-based single crystal high-temperature alloy blade at different creep times are measured from the microstructure to obtain a first relationship between the matrix phase channel width and creep time, and a second relationship between the γ' strengthening phase size and creep time is obtained by fitting. Through the relationship between the matrix phase channel width and the γ' strengthening phase size at a constant temperature and the minimum creep rate, and the fitting relationship between the creep life and the minimum creep rate, a third relationship between the creep life of the nickel-based single crystal high-temperature alloy blade and the matrix phase channel width and the γ' strengthening phase size is obtained; S6: confirming the creep time based on the service life of the test piece, predicting the matrix phase channel width of the test piece based on the first relationship, predicting the γ' strengthening phase size of the test piece based on the second relationship, and predicting the creep life of the test piece based on the third relationship.

2. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 1, characterized in that: The first relationship is as follows: Where d is the matrix phase channel width, t is the creep time, d0 is the initial matrix phase channel width, and c1 is the material parameter one.

3. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 2, characterized in that: The second relationship is as follows: Where r is the size of the γ' strengthening phase, r0 is the initial γ' strengthening phase size, and c2 is the second material parameter.

4. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 3, characterized in that: The transformation process of the third relation is as follows: The relationship between the matrix phase channel width and the γ' strengthening phase size and the minimum creep rate at a constant temperature is determined as follows: The fitting relationship between creep life and minimum creep rate is: The third relation obtained by transformation is: Where, is the minimum creep rate, σ is the loading stress, σ or is the Orowan stress, D is the diffusion coefficient of the strengthening phase in the matrix, G is the shear modulus, K is the Boltzmann constant, T is the service temperature, m is the fitting parameter 1, C0 is the fitting parameter 2, t r is the creep life.

5. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 4, characterized in that: The Orowan stress should satisfy the following relationship: Where b is the Burgers vector.

6. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to any one of claims 1 to 5, characterized in that: Step S10 specifically includes the following steps: According to the typical service conditions of aircraft engines, the service speed and temperature field of nickel-based single-crystal high-temperature alloy blades are obtained, and the stress distribution and service temperature of dangerous parts of nickel-based single-crystal high-temperature alloy blades are calculated by combining finite element simulation.

7. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 6, characterized in that: Step S20 specifically includes the following steps: S21: Based on the temperature field and stress distribution, design and manufacture a simulation of a nickel-based single-crystal high-temperature alloy blade, and iteratively calculate the loading stress at the clamping end of the simulation during the full-life creep test. The simulation is made of a nickel-based single-crystal high-temperature alloy, and the structural characteristics of the creep test assessment area of the simulation are the same as those of the hazardous area of the test piece. S22: The creep testing machine clamps the simulation part and keeps it for a preset time after heating it to the service temperature to apply loading stress to the clamping end of the simulation part, and then conducts a full-life creep test on the simulation part until the simulation part creep breaks, thereby obtaining the creep life and full-life creep curve of the nickel-based single crystal high-temperature alloy blade.

8. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 7, characterized in that: In step S22, the temperature error of the simulated component after heating is no more than ±3°C.

9. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to any one of claims 1 to 5, characterized in that: Step S30 specifically includes the following steps: According to the full-life creep curve, the starting time of the second creep stage and the starting time of the third creep stage are determined as the creep interruption time to carry out two groups of creep interruption tests.

10. The method for predicting creep life of nickel-based single crystal high-temperature alloy blades according to claim 9, characterized in that: Step S40 specifically includes the following steps: Cross-sectional specimens at the test fracture position in the full-life creep test and cross-sectional specimens at the same position in the two groups of creep interruption tests were extracted, corroded with etching liquid, and polished with a polishing machine to observe the microstructure of the three groups of cross-sectional specimens using a scanning electron microscope.

Images