Method for predicting creep life of nickel-based single crystal superalloy blade

Abstract

The invention discloses a method for predicting the creep life of a nickel-based single-crystal high-temperature alloy blade, which is used for carrying out a full-life creep test and a creep interruption test on the nickel-based single-crystal high-temperature alloy blade on the basis of stress distribution and service temperature of a dangerous part of the nickel-based single-crystal high-temperature alloy blade during actual service. Obtaining a matrix phase channel width and a gamma'strengthening phase size under different creep time, fitting to obtain a first relational expression of the matrix phase channel width and the creep time, and fitting to obtain a second relational expression of the gamma 'strengthening phase size and the creep time; transforming to obtain a third relational expression between the creep life of the nickel-based single crystal high-temperature alloy blade and the matrix phase channel width and the gamma'strengthening phase size, and fully considering the influence of the matrix phase channel width, the gamma 'strengthening phase size, the stress distribution of the dangerous part of the nickel-based single crystal high-temperature alloy blade in actual service and the service temperature on the creep life. And quickly and accurately predicting the creep life of the to-be-tested piece through the three relational expressions.

Description

Technical Field

[0001] The present invention relates to the technical field of prediction of mechanical properties of materials, and particularly to a method for predicting the creep life of nickel-based single-crystal superalloy blades. Background Art

[0002] Nickel-based single-crystal superalloys have excellent mechanical properties at high temperatures and have become an irreplaceable key material for military and civilian engine turbine blades, and are widely used in the manufacture of aeroengine and gas turbine turbine blades. However, nickel-based single-crystal superalloy blades are subjected to centrifugal loads in a high-temperature environment and will inevitably creep during service, which may cause huge losses. Research shows that creep is one of the important failure modes in the blade body part 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 life design and evaluation of nickel-based single-crystal turbine blades.

[0003] For example, Chinese Patent Application CN114813329B discloses a method for predicting the remaining life of nickel-based single-crystal superalloys under random creep loads, including: (1) conducting full-life creep tests and interrupted creep tests on standard parts under different loads to obtain the matrix phase channel width-time curves under different loads; (2) dimensionless normalizing the creep time under different loads to obtain the matrix phase channel width-normalized time curves; (3) obtaining the 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 to obtain 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 part has withstood the random creep load, the remaining life of this batch of standard parts under the same random creep load can be obtained.

[0004] However, the excellent high-temperature performance of nickel-based single-crystal superalloys is mainly related to a large number of γ'-strengthening phases continuously precipitated in the γ matrix phase. However, in the above prediction method, the prediction of creep life only considers the matrix phase channel width and does not consider the influence of the size of the γ'-strengthening phase, resulting in low prediction accuracy. Although the normalization process 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 process of nickel-based single-crystal superalloy blades, further reducing the prediction accuracy of creep life. Summary of the Invention

[0005] The present invention provides a method for predicting the creep life of nickel-based single-crystal superalloy blades to solve the technical problem of low prediction accuracy of the existing methods for predicting the creep life of nickel-based single-crystal superalloy blades.

[0006] According to one aspect of the present invention, a method for predicting the creep life of a nickel-based single crystal superalloy blade is provided, including the following steps: S10: According to the typical service conditions of an aeroengine, obtain the stress distribution and service temperature of the dangerous part of the nickel-based single crystal superalloy blade; S20: Conduct a full-life creep test on the nickel-based single crystal superalloy 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 superalloy blade; S30: Determine the creep interruption time according to the full-life creep curve to conduct a creep interruption test; S40: Extract the cross-sectional specimens at the test fracture position in the full-life creep test and the cross-sectional specimens at the same position in the creep interruption test, and scan to obtain the microstructure of the cross-sectional specimens; S50: Measure the matrix phase channel width and γ'-strengthening phase size of the nickel-based single crystal superalloy 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 superalloy 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: Further, the first relationship is as follows: ; In the formula, d is the matrix phase channel width, t is the creep time, d0 is the initial matrix phase channel width, and c1 is material parameter one.

[0008] Further, the second relationship is as follows: ; In the formula, r is the γ'-strengthening phase size, r0 is the initial γ'-strengthening phase size, and c2 is material parameter two.

[0009] Further, the transformation process of the third relationship is as follows: Determine the relationship between the matrix phase channel width and the γ'-strengthening phase size and the minimum creep rate at a constant temperature as: ; The fitting relationship between the creep life and the minimum creep rate is: ; The transformed third relationship is: ; In the formula, is the minimum creep rate, σ is the applied stress, σor 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 first fitting parameter, is the second fitting parameter, is the creep life.

[0010] Furthermore, the Orowan stress should satisfy the following relationship: ; where b is the Burgers vector.

[0011] Furthermore, it is characterized in that step S10 specifically includes the following steps: According to the typical service conditions of the aero-engine, obtain the service speed and temperature field of the nickel-based single-crystal superalloy blade, and combine with finite element simulation means to calculate the stress distribution and service temperature of the dangerous part of the nickel-based single-crystal superalloy blade.

[0012] Furthermore, step S20 specifically includes the following steps: S21: According to the temperature field and stress distribution, design and manufacture a simulation part of the nickel-based single-crystal superalloy blade, and iteratively calculate the loading stress at the clamping end of the simulation part during the full-life creep test. Among them, the material of the simulation part is nickel-based single-crystal superalloy, and the structural characteristics of the creep test assessment part of the simulation part are the same as those of the dangerous part of the test piece; S22: The creep testing machine clamps the simulation part, and after heating to the service temperature, maintains for a preset time to apply the loading stress to the clamping end of the simulation part, and then conducts the full-life creep test of the simulation part until the simulation part creeps and fractures, so as to obtain the creep life and full-life creep curve of the nickel-based single-crystal superalloy blade.

[0013] Furthermore, in step S22, the temperature error after heating the simulation part is not greater than ±3°C.

[0014] Furthermore, step S30 specifically includes the following steps: Determine the starting time of the second stage of creep and the starting time of the third stage of creep as the creep interruption time according to the full-life creep curve, so as to conduct two groups of creep interruption tests.

[0015] Furthermore, step S40 specifically includes the following steps: Extract the cross-sectional specimens at the test fracture position in the full-life creep test and the cross-sectional specimens at the same position in the two groups of creep interruption tests, corrode them with the etching solution, and polish the cross-sectional specimens with a polishing machine to observe the microstructures of the three groups of cross-sectional specimens through a scanning electron microscope.

[0016] The present invention has the following beneficial effects: The creep life prediction method for nickel-based single-crystal superalloy blades of the present invention is based on the stress distribution and service temperature during actual service of the dangerous parts of nickel-based single-crystal superalloy blades. A full-life creep test of nickel-based single-crystal superalloy blades is carried out to improve the reliability of the full-life creep test results, and further improve the reliability of subsequent creep interruption test results and the prediction accuracy of creep life. Through the full-life creep test and creep interruption test, the matrix phase channel width and γ'-strengthening phase size at different creep times are obtained, so as to fit the first relationship between the matrix phase channel width and creep time, and fit the second relationship between the γ'-strengthening phase size and creep time. Then, the third relationship between the creep life of nickel-based single-crystal superalloy blades and the matrix phase channel width and γ'-strengthening phase size is transformed to fully consider the influence of the matrix phase channel width and γ'-strengthening phase size on the creep life of nickel-based single-crystal superalloy blades. 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 the three relationships, and then the service time of nickel-based single-crystal superalloy blades can be effectively managed and utilized to the greatest extent while avoiding creep failure. Compared with the prior art, in addition to the matrix phase channel width, the influence of the γ'-strengthening phase size, the stress distribution and service temperature during actual service of the dangerous parts of nickel-based single-crystal superalloy blades on the creep life is fully considered, and the creep life of nickel-based single-crystal superalloy blades is predicted quickly and accurately, with strong practicability and suitable for wide promotion and application.

[0017] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The following will refer to the drawings for a further detailed description of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 is a flow block diagram of the creep life prediction method for nickel-based single-crystal superalloy blades according to a preferred embodiment of the present invention; Figure 2 is a schematic diagram of the microstructure in the creep life prediction method for nickel-based single-crystal superalloy blades according to a preferred embodiment of the present invention; Figure 3 is a function relationship diagram between the matrix phase channel width and creep time under different service temperatures and stress loads in the creep life prediction method for nickel-based single-crystal superalloy blades according to a preferred embodiment of the present invention; Figure 4 is a relationship curve between the creep fracture life and the minimum creep rate in the creep life prediction method for nickel-based single-crystal superalloy blades according to a preferred embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0019] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0020] It should be understood that the terms "first", "second", and "third" are only used as labels and do not limit the quantity of their objects.

[0021] As Figure 1 shown, the method for predicting the creep life of a nickel-based single-crystal superalloy blade in this embodiment includes the following steps: S10: According to the typical service conditions of an aero-engine, obtain the stress distribution and service temperature of the dangerous part of the nickel-based single-crystal superalloy blade; S20: Conduct a full-life creep test on the nickel-based single-crystal superalloy 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 superalloy blade; S30: Determine the creep interruption time according to the full-life creep curve to conduct a creep interruption test; S40: Extract the cross-sectional specimens at the test fracture position in the full-life creep test and the cross-sectional specimens at the same position in the creep interruption test, and scan to obtain the microstructure of the cross-sectional specimens; S50: Measure the matrix phase channel width and γ'-strengthening phase size of the nickel-based single-crystal superalloy blade at different creep times from the microstructure, fit to obtain the first relationship between the matrix phase channel width and creep time, and fit to obtain the second relationship between the γ'-strengthening phase size and creep time, and then transform to obtain the third relationship between the creep life of the nickel-based single-crystal superalloy 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.

[0022] Specifically, for the creep life prediction method of the nickel-based single-crystal superalloy blade of the present invention, based on the stress distribution and service temperature of the dangerous part of the nickel-based single-crystal superalloy blade during actual service, a full-life creep test of the nickel-based single-crystal superalloy blade is carried out to improve the reliability of the full-life creep test results, and further improve 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 to fit the first relationship between the matrix phase channel width and the creep time, and the second relationship between the γ'-strengthening phase size and the creep time is fitted, and then the third relationship between the creep life of the nickel-based single-crystal superalloy blade and the matrix phase channel width and the γ'-strengthening phase size is transformed 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 superalloy blade; finally, the creep time is confirmed based on the service time of the test piece, and the creep life of the test piece is accurately predicted through the three relationships, and then the service time of the nickel-based single-crystal superalloy blade can be effectively managed and utilized to the greatest extent while avoiding creep failure; compared with the prior art, in addition to the matrix phase channel width, the influence of the γ'-strengthening phase size, the stress distribution and the service temperature of the dangerous part of the nickel-based single-crystal superalloy blade during actual service on the creep life is fully considered, and the creep life of the nickel-based single-crystal superalloy blade is predicted quickly and accurately, with strong practicability and suitable for wide promotion and application.

[0023] 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 the γ'-strengthening phase size multiple times and take their average values as the parameters for fitting the first relationship.

[0024] In this embodiment, the first relationship is as follows: ; In the formula, 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.

[0025] Specifically, based on the above first relationship, after determining the creep time of the nickel-based single-crystal superalloy blade, its matrix phase channel width can be predicted to provide data support for the subsequent prediction of the creep life.

[0026] It should be understood that the creep life predicted in this embodiment refers to the remaining working life of the nickel-based single-crystal superalloy blade before creep failure.

[0027] It should be understood that the service time of the nickel-based single-crystal superalloy blade is equivalent to the creep time. Therefore, after knowing its service time, its creep time can be determined.

[0028] It should be understood that both the initial matrix phase channel width and material parameter one are known parameters to those skilled in the art.

[0029] In this embodiment, the second relational expression is as follows: ; In the formula, r is the size of the γ' strengthening phase, r0 is the initial size of the γ' strengthening phase, and c2 is material parameter two.

[0030] Specifically, based on the above second relational expression, after determining the creep time of the nickel-based single-crystal superalloy blade, its γ' strengthening phase size can be predicted, providing data support for the subsequent prediction of creep life.

[0031] It should be understood that both the initial size of the γ' strengthening phase and material parameter two are known parameters to those skilled in the art.

[0032] In this embodiment, the transformation process of the third relational expression is as follows: The relational expression between the matrix phase channel width, the γ' strengthening phase size and the minimum creep rate at a constant temperature is determined as: ; The fitting relational expression between creep life and the minimum creep rate is: ; The transformed third relational expression is: ; In the formula, is the minimum creep rate, σ is the applied 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 fitting parameter one, is fitting parameter two, is the creep life.

[0033] Specifically, based on the relationship between the matrix phase channel width, the γ' strengthening phase size and the minimum creep rate at a constant temperature, and the relationship between creep life and the minimum creep rate, the relationship between the matrix phase channel width, the γ' strengthening phase size and creep life can be transformed and obtained. After predicting the matrix phase channel width and the γ' strengthening phase size respectively through the first relational expression and the second relational expression, the creep life can be predicted through the third relational expression, so as to effectively manage the service time of the nickel-based single-crystal superalloy blade and make the most of the nickel-based single-crystal superalloy blade.

[0034] In this embodiment, the Orowan stress should satisfy the following relational expression: ; In the formula, b is the Burgers vector.

[0035] In this embodiment, step S10 specifically includes the following steps: According to the typical service conditions of the aero-engine, obtain the service rotation speed and temperature field of the nickel-based single-crystal superalloy blade, and combine with finite element simulation means to calculate the stress distribution and service temperature of the dangerous parts of the nickel-based single-crystal superalloy blade.

[0036] Specifically, through the above steps, obtain the stress distribution and service temperature of the dangerous parts of the nickel-based single-crystal superalloy blade, so as to improve the reliability of the subsequent full-life creep test results, creep interruption test results and the prediction accuracy of creep life.

[0037] It should be understood that the dangerous parts of the nickel-based single-crystal superalloy blade refer to parts such as the root fillet, leading edge, and blade crown.

[0038] In this embodiment, step S20 specifically includes the following steps: S21: According to the temperature field and stress distribution, design and manufacture a simulation part of the nickel-based single-crystal superalloy blade, and iteratively calculate the loading stress at the clamping end of the simulation part during the full-life creep test. The material of the simulation part is nickel-based single-crystal superalloy, and the structural characteristics of the creep test assessment part of the simulation part are the same as those of the dangerous parts of the part to be tested; S22: The creep testing machine clamps the simulation part, and after heating to the service temperature, maintains for a preset time to apply the loading stress to the clamping end of the simulation part, and then conducts the full-life creep test on the simulation part until the simulation part creeps and fractures, so as to obtain the creep life and full-life creep curve of the nickel-based single-crystal superalloy blade.

[0039] Specifically, design and manufacture a simulation part of the nickel-based single-crystal superalloy blade based on the temperature field and stress distribution, so as to conduct the full-life creep test and subsequent creep interruption test through the simulation part, and ensure that the material and structural characteristics of the simulation part are the same as those of the part to be tested to improve the reliability of the test results. By iteratively calculating the loading stress at the clamping end of the clamped simulation part, the stress distribution and stress gradient during the test of the simulation part are made consistent with those of the part to be tested, further improving the reliability of the test results.

[0040] It should be understood that the part to be tested refers to the nickel-based single-crystal superalloy blade in actual service.

[0041] In this embodiment, in step S22, the temperature error of the simulation part after heating is not greater than ±3°C. Specifically, by ensuring that the temperature error of the simulation part after heating is not greater than ±3°C, the working state of the part to be tested is truly simulated, and the reliability of the test results is improved.

[0042] In this embodiment, step S30 specifically includes the following steps: Determine the starting time of the second creep stage and the starting time of the third creep stage as the creep interruption time according to the full-life creep curve, so as to conduct two groups of creep interruption tests.

[0043] Specifically, through two groups of creep interruption tests, the accuracy of subsequent fitting of the first relationship and the second relationship can be improved.

[0044] In this embodiment, step S40 specifically includes the following steps: Extract the cross-sectional specimens at the test fracture position in the full-life creep test and the cross-sectional specimens at the same position in the two groups of creep interruption tests, corrode them with a corrosive solution, and polish the cross-sectional specimens with a polishing machine, so as to observe the microstructure of the three groups of cross-sectional specimens through a scanning electron microscope.

[0045] Specifically, through corrosion with a corrosive solution and polishing with a polishing machine, the observation accuracy of the microstructure can be improved.

[0046] Optionally, use oringe software to observe the microstructure of the cross-sectional specimens.

[0047] One embodiment is as follows: According to the typical service conditions of a certain type of aero-engine, combined with finite element simulation means, calculate the temperature and stress at the dangerous parts of the nickel-based single-crystal superalloy blade, determine the test loads, including test load characteristics such as low temperature and high stress, high temperature and low stress, etc. Based on the above test loads, conduct full-life creep tests and creep interruption tests in sequence.

[0048] Combine SEM measurement to statistically analyze the matrix phase channel width and γ' strengthening phase size in the full-life test, the second-stage interruption test, and the third-stage interruption test under the test loads, construct the first relationship and the second relationship, and then transform to obtain the third relationship.

[0049] Determine the creep time according to the service time of the nickel-based single-crystal superalloy blade serving in the aero-engine, so as to predict its creep life through the three relationships.

[0050] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

[0051] In this article, specific examples are used to illustrate the principles and implementation manners of the present application. The descriptions of the above examples are only used to help understand the method and its core idea of the present application. The above is only the preferred implementation manner of the present application. It should be noted that due to the limited nature of literal expression and objectively infinite specific structures, for those of ordinary skill in the art, without departing from the principles of the present application, several improvements, embellishments or changes can be made, or the above technical features can be combined in an appropriate manner; these improvements, embellishments, changes or combinations, or directly applying the concept and technical solution of the present application to other occasions without improvement, shall all be regarded as the protection scope of the present application.

Claims

1. A method for predicting the creep life of a nickel-based single crystal superalloy blade, characterized in that It includes the following steps: S10: According to the typical service conditions of an aero-engine, obtain the stress distribution and service temperature of the critical parts of a nickel-based single-crystal superalloy blade; S20: Conduct a full-life creep test on the nickel-based single-crystal superalloy blade based on the stress distribution and service temperature to obtain the creep life and full-life creep curve of the nickel-based single-crystal superalloy blade; S30: Determine the creep interruption time based on the full-life creep curve to conduct a creep interruption test; S40: Extract the cross-sectional specimens at the test fracture position in the full-life creep test and the cross-sectional specimens at the same position in the creep interruption test, and scan to obtain the microstructure of the cross-sectional specimens; S50: Measure the matrix phase channel width and γ'-strengthening phase size of the nickel-based single-crystal superalloy blade at different creep times from the microstructure, to fit the first relationship between the matrix phase channel width and creep time, and fit the second relationship between the γ'-strengthening phase size and creep time, and then transform to obtain the third relationship between the creep life of the nickel-based single-crystal superalloy blade, the matrix phase channel width, and the 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.

2. The method for predicting the creep life of a nickel-based single crystal superalloy blade according to claim 1, wherein The first relationship is as follows: ； In the formula, d is the matrix phase channel width, t is the creep time, d0 is the initial matrix phase channel width, and c1 is material parameter one.

3. The creep life prediction method for nickel-based single crystal superalloy blades according to claim 2, wherein The second relationship is as follows: ； In the formula, r is the γ'-strengthening phase size, r0 is the initial γ'-strengthening phase size, and c2 is material parameter two.

4. The method for predicting the creep life of a nickel-based single crystal superalloy blade according to claim 3, wherein The transformation process of the third relationship is as follows: Determine that the relationship between the matrix phase channel width, the γ'-strengthening phase size, and the minimum creep rate at a constant temperature is: ； The fitting relationship between the creep life and the minimum creep rate is: ； The transformed third relationship is: ； In the formula, is the minimum creep rate, σ is the applied 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 first fitting parameter, is the second fitting parameter, is the creep life.

5. The method for predicting the creep life of a nickel-based single crystal superalloy blade according to claim 1, characterized in that, The Orowan stress should satisfy the following relationship: ； In the formula, b is the Burgers vector.

6. The creep life prediction method for a nickel-based single crystal superalloy blade according to any one of claims 1-5, characterized in that Step S10 specifically includes the following steps: According to the typical service conditions of an aero-engine, obtain the service speed and temperature field of the nickel-based single-crystal superalloy blade, and combine with finite element simulation means to calculate the stress distribution and service temperature of the critical parts of the nickel-based single-crystal superalloy blade.

7. The creep life prediction method for a nickel-based single crystal superalloy blade according to claim 6, characterized in that Step S20 specifically includes the following steps: S21: According to the temperature field and stress distribution, design and manufacture a simulation part of the nickel-based single-crystal superalloy blade, and iteratively calculate the loading stress at the clamping end of the simulation part during the full-life creep test. Among them, the material of the simulation part is nickel-based single-crystal superalloy, and the structural characteristics of the creep test assessment part of the simulation part are the same as those of the critical part of the test piece; S22: Clamp the simulation part with a creep testing machine, keep it for a preset time after heating to the service temperature, apply the loading stress to the clamping end of the simulation part, and then conduct the full-life creep test of the simulation part until the simulation part creeps and fractures, so as to obtain the creep life and full-life creep curve of the nickel-based single-crystal superalloy blade.

8. The creep life prediction method for a nickel-based single crystal superalloy blade according to any one of claims 1-5, characterized in that, In step S22, the temperature error after heating the simulation part is not greater than ±3°C.

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

10. The method for predicting the creep life of a nickel-based single crystal superalloy blade according to claim 9, characterized in that, Step S40 specifically includes the following steps: Extract the cross-sectional specimens at the test fracture position in the full-life creep test and the cross-sectional specimens at the same position in the two groups of creep interruption tests, corrode them with etching solution, and polish the cross-sectional specimens with a polishing machine to observe the microstructures of the three groups of cross-sectional specimens through a scanning electron microscope.

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