A method for evaluating residual performance of a nickel-based alloy turbine blade

Abstract

The application provides a method for evaluating the residual performance of a nickel-based alloy turbine blade, which comprises the following steps: step one, obtaining material simulation samples of different damage degrees of the turbine blade by using a simulation damage test, and constructing the relationship between the organizational parameters and performance indicators of the material and the relationship between the hardness and performance indicators of the material according to the material simulation samples; step two, obtaining a target part sample of the turbine blade, measuring the organizational parameters and hardness of the target part sample of the turbine blade, and respectively calculating the performance indicators corresponding to the organizational parameters and hardness of the target part sample of the turbine blade according to the relationship between the organizational parameters, hardness and performance indicators of the material simulation samples; and step three, calculating the difference between the performance indicators corresponding to the organizational parameters and hardness of the target part sample of the turbine blade, and judging the performance of the turbine blade according to the difference. The method provided by the application can quickly evaluate the residual performance, improve the test accuracy, reduce the number of turbine blades subjected to anatomical examination, and save costs.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a method for evaluating the residual performance of nickel-based alloy turbine blades. Background Technology

[0002] Turbine blades for aero-engines and gas turbines operate under high temperatures and complex loads, placing high demands on their mechanical properties. Currently, nickel-based superalloys are commonly used to manufacture turbine blades; however, these alloys may experience performance degradation during prolonged service. Therefore, it is necessary to assess the remaining life of turbine blades after a certain service period. Due to the limited size and complex shape of turbine blades, it is difficult to directly obtain standard samples to measure their various properties. Furthermore, obtaining small, non-standard samples limits the number of tests that can be performed and significantly reduces accuracy, rendering them unusable directly.

[0003] Currently, the residual performance assessment of turbine blades generally employs empirical methods based on hardness and strength estimation. However, the specific relationship between observed and inferred indicators varies depending on the materials and service conditions of the blades used in different engine models. Furthermore, existing technologies also use microstructure morphology to estimate residual performance, but this method can only assess residual service life and cannot provide a comprehensive evaluation of multiple mechanical properties.

[0004] Furthermore, the above methods all use a single parameter of the material as a single observation indicator, resulting in low accuracy in assessing the residual performance of turbine blades. Summary of the Invention

[0005] The purpose of this application is to provide a method for evaluating the residual performance of nickel-based alloy turbine blades, in order to solve or mitigate at least one of the problems in the prior art.

[0006] The technical solution of this application is: a method for evaluating the residual performance of nickel-based alloy turbine blades, the evaluation method comprising:

[0007] Step 1: Obtain material simulation samples of turbine blades with different damage levels through simulated damage tests, and construct the relationship between material microstructure parameters and performance indicators and the relationship between material hardness and performance indicators based on the material simulation samples;

[0008] Step 2: Obtain a sample of the target part of the turbine blade, measure the microstructure and hardness of the sample, and calculate the performance index corresponding to the microstructure and hardness of the sample based on the relationship between the microstructure and hardness and the performance index of the sample.

[0009] Step 3: Calculate the performance index differences corresponding to the tissue parameters and hardness of the target part of the turbine blade sample, and judge the performance of the turbine blade based on the differences.

[0010] In a preferred embodiment of this application, the simulated loss specimen is obtained by high-temperature stress thermal exposure.

[0011] In a preferred embodiment of this application, the microstructure parameters include the volume fraction of the nickel-based alloy reinforcing phase;

[0012] The hardness includes any one of Vickers hardness, Rockwell hardness, and Brinell hardness;

[0013] The performance indicators include strength, plasticity, and lifespan.

[0014] In a preferred embodiment of this application, the method for calculating the differences in performance indicators corresponding to the tissue parameters and hardness of the turbine blade target region sample is as follows:

[0015]

[0016] In the formula, M represents the performance index error parameters corresponding to the tissue parameters and hardness of the target part of the turbine blade sample.

[0017] X1 represents the performance index corresponding to the tissue parameters of the target part of the turbine blade sample;

[0018] X2 represents the performance index corresponding to the hardness of the target part of the turbine blade sample.

[0019] In a preferred embodiment of this application, when the performance index error parameter is less than the minimum value of a predetermined range, the calculated performance index result is rated as recommended.

[0020] When the performance index error parameter is within the predetermined range, the calculated performance index result is rated as usable.

[0021] When the performance index error parameter exceeds the maximum value within the predetermined range, the calculated performance index result rating is to be used with caution.

[0022] The residual performance evaluation method for nickel-based alloy turbine blades provided in this application is based on the analysis and experimental results of turbine blades used in the target model, thus improving the accuracy of the evaluation. This method is not only applicable to single performance indicators, but can also comprehensively evaluate multiple mechanical properties such as strength indicators (fracture strength, yield strength), plasticity indicators (elongation, shrinkage rate), and crease life. It employs both microstructure parameters and hardness testing for evaluation, and performs cross-validation to determine the confidence level of the evaluation results.

[0023] The method of this application overcomes the problems of existing methods that require dissection and analysis of a large number of blades, resulting in a large workload, long time consumption, and insufficient evaluation accuracy. Based on the pre-established relationship between tissue, hardness, and performance indicators, this method can quickly evaluate the remaining performance through simple analysis, which greatly shortens the inspection process, improves work efficiency, and enhances test accuracy. At the same time, it can greatly reduce the number of turbine blades that need to be dissected and inspected, thus saving costs significantly. Attached Figure Description

[0024] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0025] Figure 1 This is a flowchart of the method for evaluating the residual performance of nickel-based alloy turbine blades according to this application. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0027] like Figure 1 As shown, the method for evaluating the residual performance of nickel-based alloy turbine blades provided in this application includes the following process:

[0028] Step 1: Use material simulation samples with different degrees of damage obtained from simulated damage tests, and determine the relationship between the material's microstructure parameters and performance indicators, and the relationship between the material's hardness and performance indicators based on the material simulation samples.

[0029] For example, in this embodiment provided in this application, based on the relevant research foundation and service conditions of turbine blades, a high-temperature stress thermal exposure method is used to prepare simulated samples of the material to simulate the microstructure characteristics of the material at different stages of service. The simulated microstructure samples at different stages are labeled a, b, c, d, etc., according to the service time from shortest to longest. The maximum degree of microstructure change in the simulated microstructure samples should cover the maximum degree of microstructure and performance change throughout the entire life cycle of the turbine blade.

[0030] The tissue parameters and stiffness of simulated tissue samples at different service stages were measured to obtain the tissue parameter P. a P b P c P d Equal and hardness V a V b V c V d In this application, the microstructure parameter is the volume fraction of the nickel-based alloy reinforcing phase, and the hardness can be Vickers hardness, Brinell hardness, or Rockwell hardness, etc., with Vickers hardness being preferred.

[0031] The prepared simulated tissue samples are processed into standard test bars, and the mechanical properties of the simulated tissue samples at each stage—strength, stiffness, and durability—are measured. In this embodiment of the application, durability T is used as an example to illustrate the mechanical property, that is, the durability T of the simulated tissue samples at each stage is measured after processing into standard test bars. a T b T c T d wait.

[0032] Based on the above results, the relationships between the tissue parameter P and the performance index (lifespan) and the hardness V and the performance index (lifespan) of the simulated tissue samples were established respectively, and the relationship functions T = f(P) and T = f(V) were obtained respectively. The performance index can be obtained from these relationship functions.

[0033] Step 2: Obtain the tissue parameters and hardness of the target part of the turbine blade sample, and calculate the performance index of the target part of the turbine blade sample based on the relationship between the tissue parameters, hardness and performance index of the simulated sample.

[0034] For example, in this embodiment of the application, a sample is taken from the target area of ​​the turbine blade, and the sample is subjected to microstructure analysis and Vickers hardness measurement to obtain the microstructure parameter P of the target area of ​​the turbine blade. Q Hardness V Q .

[0035] The microstructure parameter P of the target part of the turbine blade was calculated based on the relationship function between the microstructure parameters, Vickers hardness, and performance index of the simulated sample and the performance index for longevity. Q Hardness V Q The corresponding calculated mechanical performance index, i.e., the creep rupture life T. Q-P T Q-V .

[0036] Step 3: Compare the performance index results of the target part of the turbine blade obtained by the two methods above to perform cross-validation and rate the accuracy.

[0037] For example, in this embodiment of the application, the performance index results obtained by the above two methods are used to calculate the creep life performance error parameter M of the target part of the turbine blade. Q :

[0038]

[0039] When the lifetime performance error parameter M Q If the value is less than the minimum value of the predetermined range (e.g., 8%), the calculated durability result is rated as recommended.

[0040] When the lifetime performance error parameter M Q If the calculated durability is within a predetermined range (e.g., 8% to 15%), the result is rated as usable.

[0041] When the lifetime performance error parameter M Q If the percentage exceeds the maximum value of the predetermined range (e.g., 15%), the calculated lifetime rating should be considered with caution.

[0042] The residual performance evaluation method for nickel-based alloy turbine blades provided in this application is based on the analysis and experimental results of turbine blades used in the target model, thus improving the accuracy of the evaluation. This method is not only applicable to single performance indicators, but can also comprehensively evaluate multiple mechanical properties such as strength indicators (fracture strength, yield strength), plasticity indicators (elongation, shrinkage rate), and crease life. It employs both microstructure parameters and hardness testing for evaluation, and performs cross-validation to determine the confidence level of the evaluation results.

[0043] The method of this application overcomes the problems of existing methods that require dissection and analysis of a large number of blades, resulting in a large workload, long time consumption, and insufficient evaluation accuracy. Based on the pre-established relationship between tissue, hardness, and performance indicators, this method can quickly evaluate the remaining performance through simple analysis, which greatly shortens the inspection process, improves work efficiency, and enhances test accuracy. At the same time, it can greatly reduce the number of turbine blades that need to be dissected and inspected, thus saving costs significantly.

[0044] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method of residual performance assessment of a nickel-base alloy turbine blade, characterized by, The evaluation method comprises: Step one, obtaining material simulation samples of different damage degrees of turbine blades by using simulation damage test, and constructing the relationship between the organizational parameters and the performance index of the material and the relationship between the hardness and the performance index of the material according to the material simulation samples, the organizational parameters comprising the volume fraction of the strengthening phase of the nickel-based alloy, the hardness comprising any one of Vickers hardness, Rockwell hardness and Brinell hardness, and the performance index comprising the strength index, the plasticity index and the life index; Step two, obtaining a target site sample of the turbine blade, measuring the organizational parameters and the hardness of the target site sample of the turbine blade, and respectively calculating the performance index corresponding to the organizational parameters and the hardness of the target site sample of the turbine blade according to the relationship between the organizational parameters, the hardness and the performance index of the material simulation samples; Step three, calculating the performance index difference corresponding to the tissue parameter and hardness of the turbine blade target site sample In the formula, M is the performance index error parameter corresponding to the tissue parameter and hardness of the turbine blade target site sample, X1 is the performance index corresponding to the tissue parameter of the turbine blade target site sample, and X2 is the performance index corresponding to the hardness of the turbine blade target site sample. According to the difference, the performance of the turbine blade is judged. When the performance index error parameter is less than the minimum value of the predetermined range, the calculated performance index result is rated as recommended for adoption. When the performance index error parameter is within the predetermined range, the calculated performance index result is rated as acceptable for adoption. When the performance index error parameter is greater than the maximum value of the predetermined range, the calculated performance index result is rated as a cautious reference.

2. The method of residual performance evaluation of a nickel-base alloy turbine blade of claim 1, wherein, The simulation damage test is a high-temperature stress heat exposure method.

Images