Lifetime prediction method and system for turbocharged electronic control actuator

Abstract

The present invention relates to the technical field of turbocharging, and discloses a method and system for predicting the service life of a turbocharged electronic control actuator. The method includes obtaining turbocharged electronic control actuator data, where the turbocharged electronic control actuator data includes turbine blade data and turbocharging data; performing strength analysis on the turbine blade data based on the finite element method to obtain a strength analysis result; calculating the safe service life according to the strength analysis result to obtain a safe service life result; performing dynamic characteristic analysis on the turbocharging data based on the finite element method to obtain a dynamic characteristic analysis result; performing fatigue life analysis according to the dynamic characteristic analysis result to obtain a fatigue life result; and performing prediction according to the safe service life result and the fatigue life result to obtain the predicted service life result of the turbocharged electronic control actuator. This method realizes accurate prediction of the service life of the turbocharged electronic control actuator.

Description

Technical Field

[0001] The present invention relates to the technical field of turbocharging, and particularly to a method and system for predicting the service life of a turbocharged electronic control actuator. Background Art

[0002] The turbocharging technology of aero-engines is a key factor in the performance of aero-engines, and its performance and reliability directly affect the overall performance of the engine. With the development of technology, the structure and reliability of components of turbochargers have been improved, but the reliability of the supercharging mechanism is still a major issue, especially for the turbine part, whose reliability accounts for more than 60% of the supercharging mechanism. In order to achieve a balance between high performance and low fuel consumption, the turbocharging technology needs to be continuously improved, and it is crucial to control the relationship between the supercharging ratio, engine flow rate, rotational speed, and torque. The introduction of a turbocharged electronic control system realizes the rapid, continuous, and precise control of the turbocharging ratio by adjusting the geometric shape of the turbine blades through an electronic control mechanism to adapt to the changes in engine operating conditions.

[0003] In the prior art, through the operation of the electronic control mechanism, the turbocharger of the turbocharged electronic control system can quickly change its operating state according to the needs of the engine operating conditions. As the action mechanism of the system, the electronic control actuator can adjust the geometric shape of the turbine blades, thereby changing the operating conditions of the turbine. However, the full-structure analysis of the turbine blades usually relies on the simulation calculation results to predict their safe service life. In the dynamic strength analysis, due to the incomplete matching between the simulation results and the test state, the fatigue calculation is inconsistent with the test results, and it is impossible to effectively guide the fatigue life calculation of the turbine blades.

[0004] In one prior art, due to the increased sensitivity of the turbine blades to vibration loads, and the action characteristics of the actuator are closely related to the service life of the turbine blades, the simulation calculation results of the turbine blades in the full-structure analysis cannot well guide the fatigue life calculation, so it is impossible to accurately and quickly evaluate the service life of the actuator. Summary of the Invention

[0005] The present invention provides a method and system for predicting the service life of a turbocharged electronic control actuator to solve the problem of being unable to accurately and quickly evaluate the service life of the turbocharged electronic control actuator.

[0006] In a first aspect, to solve the above technical problems, the present invention provides a method for predicting the service life of a turbocharged electronic control actuator, including:

[0007] Obtaining turbocharged electronic control actuator data, where the turbocharged electronic control actuator data includes turbine blade data and turbocharging data;

[0008] Performing strength analysis on the turbine blade data based on the finite element method to obtain a strength analysis result;

[0009] Perform safety life calculation based on the strength analysis result to obtain the safety life result;

[0010] Perform dynamic characteristic analysis on the turbocharging data based on the finite element method to obtain the dynamic characteristic analysis result;

[0011] Perform fatigue life analysis according to the dynamic characteristic analysis result to obtain the fatigue life result;

[0012] Perform prediction based on the safety life result and the fatigue life result to obtain the predicted life result of the turbocharged electronic control actuator.

[0013] In an alternative embodiment, the strength analysis of the turbine blade data based on the finite element method to obtain the strength analysis result includes:

[0014] Perform static strength analysis and dynamic strength analysis on the turbine blade data based on the finite element method; wherein, the static strength analysis result is obtained by analyzing the transient temperature field stress result of the turbine blade at a rotational speed of 0 and a temperature of 1500K; the dynamic strength analysis result is obtained by analyzing the stress result of the turbine blade under the steady-state temperature field at a rotational speed of 5000 r / min and a temperature of 1500K.

[0015] In an alternative embodiment, the safety life calculation according to the strength analysis result to obtain the safety life result includes:

[0016] Calculate the von Mises equivalent stress of each node in the dynamic strength analysis result to obtain the von Mises equivalent stress result;

[0017] Project the von Mises equivalent stress result in the principal stress coordinate system and decompose it into the maximum principal stress and the minimum principal stress;

[0018] Perform safety life calculation based on the maximum principal stress and the minimum principal stress to obtain the safety life result of the maximum principal stress point and the safety life result of the minimum principal stress point;

[0019] Accumulate the safety life result of the maximum principal stress point and the safety life result of the minimum principal stress point to obtain the safety life result of the dangerous section;

[0020] Calculate the safety life of each node based on the von Mises equivalent stress result to obtain the safety life result of each node;

[0021] Compare the safety life result of each node with the safety life result of the dangerous section, and select the minimum safety life result as the safety life result.

[0022] In an alternative embodiment, the dynamic characteristic analysis of the turbocharging data based on the finite element method to obtain the dynamic characteristic analysis result includes:

[0023] Using the finite element method for dynamic characteristic analysis to calculate the turbocharging applied load to linearly accelerate to 5000 r / min at a temperature of 1500K and within 10 ms, and then linearly decrease to 0 within 10 ms, obtaining the load, stress of the turbine blade and the thrust and rotational speed results of the actuator, and taking the load, stress of the turbine blade and the thrust and rotational speed results of the actuator as the dynamic characteristic analysis result.

[0024] In an alternative embodiment, the fatigue life analysis based on the dynamic characteristic analysis result to obtain the fatigue life result includes:

[0025] According to the dynamic characteristic analysis result, calculating the fatigue damage of each point according to the fatigue calculation equation under the Von Mises fatigue damage criterion to obtain the fatigue damage result on the dangerous cross-section;

[0026] Establishing a fatigue model based on the fatigue damage result to obtain the fatigue life result of the turbine blade;

[0027] Wherein the fatigue calculation equation is as follows:

[0028]

[0029] Where, represents the fatigue damage result; represents the fatigue life coefficient of the turbine blade; represents the stress of the turbine blade in the dynamic characteristic analysis result; represents the fatigue limit strength of the turbine blade.

[0030] In an alternative embodiment, the prediction based on the safe life result and the fatigue life result to obtain the predicted life result of the turbocharging electronic control actuator includes:

[0031] Comparing the safe life result with the required life result of the preset turbocharging electronic control actuator. If the safe life result is less than the required life result, the predicted life result is zero;

[0032] If the safe life result is greater than the required life result, perform a primary fatigue life correction on the fatigue life result to obtain the primary corrected fatigue life result;

[0033] Compare the initial corrected fatigue life result and the required life result. If the initial corrected fatigue life result is less than the required life result, the predicted life result is zero;

[0034] If the initial corrected fatigue life result is greater than the required life result, perform a secondary fatigue life correction on the initial corrected fatigue life result to obtain a secondary corrected fatigue life result;

[0035] Substitute the secondary corrected fatigue life result into the accelerated life formula to obtain a life acceleration rate result, and compare the life acceleration rate result with the preset life acceleration rate requirement. If the life acceleration rate result is less than the life acceleration rate requirement, the predicted life result is zero;

[0036] If the life acceleration rate result is greater than the life acceleration rate requirement, select the secondary corrected fatigue life result as the predicted life result.

[0037] In an alternative embodiment, the performing a primary fatigue life correction on the fatigue life result to obtain an initial corrected fatigue life result includes:

[0038] Perform a primary fatigue life correction on the fatigue life result according to the following formula:

[0039]

[0040] where, represents the initial corrected fatigue life result, represents the fatigue life result, represents the required life result.

[0041] In an alternative embodiment, the performing a secondary fatigue life correction on the initial corrected fatigue life result to obtain a secondary corrected fatigue life result includes:

[0042] Calculate the thrust ratio of the turbocharged electronic control actuator according to the following formula to obtain the actuator thrust ratio;

[0043]

[0044] where, represents the actuator thrust ratio, represents the thrust of the turbocharged electronic control actuator, represents the load of the turbocharged electronic control actuator;

[0045] According to the following formula, use the actuator thrust ratio to perform a fatigue ratio coefficient correction on the initial corrected fatigue life result to obtain a fatigue ratio coefficient correction result;

[0046]

[0047] Among them, represents the correction result of the fatigue ratio coefficient, represents the actuator thrust ratio, represents the result of the initial correction of the fatigue life;

[0048] According to the following formula, for perform time correction to obtain the result of the secondary correction of the fatigue life;

[0049]

[0050] Among them, represents the result of the secondary correction of the fatigue life, represents the fatigue life correction coefficient, represents the fatigue life index.

[0051] In a second aspect, the present invention provides a life prediction system for a turbocharged electronic control actuator, including:

[0052] A data acquisition module for acquiring turbocharged electronic control actuator data, where the turbocharged electronic control actuator data includes turbine blade data and turbocharging data;

[0053] A strength analysis module for performing strength analysis on the turbine blade data in the turbocharged electronic control actuator data based on the finite element method to obtain a strength analysis result;

[0054] A safety life calculation module for calculating the safety life according to the strength analysis result to obtain a safety life result;

[0055] A dynamic characteristic analysis module for performing dynamic characteristic analysis on the turbocharging data in the turbocharged electronic control actuator data based on the finite element method to obtain a dynamic characteristic analysis result;

[0056] A fatigue life calculation module for performing fatigue life analysis according to the dynamic characteristic analysis result to obtain a fatigue life result;

[0057] A life prediction module for predicting the predicted life result of the turbocharged electronic control actuator according to the safety life result and the fatigue life result.

[0058] In a third aspect, the present invention further provides an electronic device, including a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor. When the processor executes the computer program, it implements the life prediction method for the turbocharged electronic control actuator described in any one of the above.

[0059] Fourthly, the present invention also provides a computer-readable storage medium, which includes a stored computer program. When the computer program runs, it controls the device where the computer-readable storage medium is located to execute the life prediction method of the turbocharged electronic control actuator described in any one of the above.

[0060] Compared with the prior art, the present invention has the following beneficial effects:

[0061] The present invention relates to the technical field of turbocharging, and discloses a life prediction method and system for a turbocharged electronic control actuator, including obtaining turbocharged electronic control actuator data, where the turbocharged electronic control actuator data includes turbine blade data and turbocharging data; performing strength analysis on the turbine blade data based on the finite element method to obtain a strength analysis result; calculating the safe life according to the strength analysis result to obtain a safe life result; performing dynamic characteristic analysis on the turbocharging data based on the finite element method to obtain a dynamic characteristic analysis result; performing fatigue life analysis according to the dynamic characteristic analysis result to obtain a fatigue life result; and performing prediction according to the safe life result and the fatigue life result to obtain the predicted life result of the turbocharged electronic control actuator. Compared with the prior art, the present invention proposes a life prediction method for a turbocharged electronic control actuator by comprehensively applying finite element analysis, safe life assessment, fatigue life assessment, and turbocharging dynamic characteristic analysis. This method first uses the finite element method to perform static and dynamic strength analysis on the turbine blade to obtain stress results under different working conditions, and then combines the dynamic characteristics of the turbocharger to calculate the thrust and speed of the actuator through fluid-structure interaction analysis. On this basis, the safe life and fatigue life are calculated to predict the service life of the actuator, realizing the evaluation of combining the safe life and fatigue life and improving the accuracy of the life prediction of the turbocharged electronic control actuator. Description of the Drawings

[0062] Figure 1 is a schematic flowchart of the life prediction method for the turbocharged electronic control actuator provided by the first embodiment of the present invention;

[0063] Figure 2 is a schematic structural diagram of the life prediction system for the turbocharged electronic control actuator provided by the second embodiment of the present invention. Detailed Embodiments

[0064] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0065] Aero-engine turbocharging technology is a key factor in the performance of aero-engines. Its performance and reliability directly affect the overall performance of the engine. With the development of technology, the structure and reliability of components of turbochargers have been improved, but the reliability of the supercharging mechanism remains a major issue, especially for the turbine part, whose reliability accounts for more than 60% of the supercharging mechanism. To achieve a balance between high performance and low fuel consumption, turbocharging technology needs to continuously progress, and it is crucial to control the relationship between the boost ratio, engine flow rate, rotational speed, and torque. The introduction of the turbocharging electronic control system realizes rapid, continuous, and precise control of the turbocharging ratio by adjusting the geometric shape of the turbine blades through an electronic control mechanism to adapt to changes in engine operating conditions.

[0066] In the prior art, through the operation of the electronic control mechanism in the turbocharging electronic control system, the turbocharger can quickly change its operating state according to the needs of the engine operating conditions. The electronic control actuator, as the action mechanism of the system, can adjust the geometric shape of the turbine blades, thereby changing the operating conditions of the turbine. However, the full structural analysis of turbine blades usually relies on simulation calculation results to predict their safe life. In dynamic strength analysis, due to the incomplete matching between the simulation results and the test state, the fatigue calculation is inconsistent with the test results, and it is impossible to effectively guide the fatigue life calculation of turbine blades.

[0067] To solve the above technical problems, referring to Figure 1 , the first embodiment of the present invention provides a method for predicting the life of a turbocharging electronic control actuator, including the following steps:

[0068] S11, Obtain turbocharging electronic control actuator data, where the turbocharging electronic control actuator data includes turbine blade data and turbocharging data;

[0069] S12, Perform strength analysis on the turbine blade data based on the finite element method to obtain a strength analysis result;

[0070] S13, Calculate the safe life according to the strength analysis result to obtain a safe life result;

[0071] S14, Perform dynamic characteristic analysis on the turbocharging data based on the finite element method to obtain a dynamic characteristic analysis result;

[0072] S15, Perform fatigue life analysis according to the dynamic characteristic analysis result to obtain a fatigue life result;

[0073] S16, Perform prediction according to the safe life result and the fatigue life result to obtain the predicted life result of the turbocharging electronic control actuator.

[0074] In step S11, it is necessary to obtain the data of the turbocharged electronic control actuator, and the data of the turbocharged electronic control actuator includes turbine blade data and turbocharging data.

[0075] Collect and organize the data of the turbocharged electronic control actuator, including detailed turbine blade design parameters, operating conditions, and the performance data of the turbocharger. The data is sourced from the design documents, manufacturing records, performance test reports, and real-time monitoring systems of the turbocharged electronic control actuator. These data are the basis for subsequent strength analysis, safety life calculation, and fatigue life assessment. It is necessary to ensure their accuracy and integrity to provide reliable input information for predicting the life of the turbocharged electronic control actuator.

[0076] In step S12, perform a strength analysis on the turbine blade data based on the finite element method to obtain the strength analysis result.

[0077] Perform a static strength analysis and a dynamic strength analysis on the turbine blade data based on the finite element method. Among them, the static strength analysis result is obtained by analyzing the transient temperature field stress result of the turbine blade at a rotational speed of 0 and a temperature of 1500K. The dynamic strength analysis result is obtained by analyzing the stress result of the turbine blade under the steady-state temperature field at a rotational speed of 5000 r / min and a temperature of 1500K.

[0078] Specifically, when performing the static strength analysis of the turbine blade, first, it is necessary to establish the geometric model of the blade and divide the mesh in the finite element analysis software, then define the physical and mechanical properties of the material, then set the boundary conditions to simulate the constrained state of the blade during operation, and apply the pressure load based on the maximum design pressure condition on the blade. After that, simulate the temperature distribution of the blade at a high temperature of 1500K through transient thermal analysis, and then calculate the resulting thermal stress, and finally evaluate the static strength performance of the blade at high temperature to ensure that it will not be damaged under the most demanding working conditions. This process involves calculating the Von Mises stress of each element on the blade and comparing it with the allowable stress of the material to verify whether the blade meets the design requirements. Through this analysis, the static strength analysis result of the turbine blade under the thermal stress caused by high temperature in the static state can be obtained, providing important data for subsequent safety life calculation.

[0079] Specifically, when performing the dynamic strength analysis of a turbine blade, it is first necessary to establish a geometric model of the blade in a finite element analysis software and divide the mesh. Then, define the physical and mechanical properties of the material. Next, set the boundary conditions to simulate the rotating state of the blade during operation, and apply a pressure load based on the maximum design pressure condition on the blade. After that, simulate the steady-state temperature field of the blade at a rotational speed of 5000 r / min and a temperature of 1500 K through a steady-state thermal analysis, and then calculate the resulting thermal stress and centrifugal stress. Finally, evaluate the dynamic strength performance of the blade under high-temperature and high-speed rotation conditions to ensure that it will not fail under the most demanding working conditions. This process involves calculating the Von Mises stress of each element on the blade and comparing it with the allowable stress of the material to verify whether the blade meets the design requirements. Through this analysis, the dynamic strength analysis results in the steady-state temperature field of the turbine blade at a rotational speed of 5000 r / min and a temperature of 1500 K can be obtained, providing important data for subsequent fatigue life analysis.

[0080] In step S13, perform a safety life calculation based on the strength analysis results to obtain a safety life result, including:

[0081] Calculate the normal equivalent stress of each node in the dynamic strength analysis result to obtain a normal equivalent stress result;

[0082] Project the normal equivalent stress result in the principal stress coordinate system and decompose it into the maximum principal stress and the minimum principal stress;

[0083] Perform a safety life calculation based on the maximum principal stress and the minimum principal stress to obtain a safety life result at the maximum principal stress point and a safety life result at the minimum principal stress point;

[0084] Accumulate the safety life result at the maximum principal stress point and the safety life result at the minimum principal stress point to obtain a safety life result for the dangerous cross-section;

[0085] Calculate the safety life of each node based on the normal equivalent stress result to obtain a safety life result for each node;

[0086] Compare the safety life result for each node with the safety life result for the dangerous cross-section, and select the minimum safety life result as the safety life result.

[0087] In a specific implementation manner, the calculating the normal equivalent stress of each node in the dynamic strength analysis result to obtain a normal equivalent stress result includes:

[0088] According to the dynamic strength analysis results, the stress components of each node on the blade are calculated, and through mathematical processing of these stress components, applying the von Mises stress criterion and according to the following formula, the complex three-dimensional stress state is transformed into a single equivalent stress value, i.e., the normal form equivalent stress.

[0089]

[0090] Among them, represents the normal form equivalent stress, , , are the normal stresses of the stress of the node on the blade in the three principal directions respectively, , , are the shear stresses of the node on the blade.

[0091] In a specific implementation manner, the projection of the normal form equivalent stress result in the principal stress coordinate system and the decomposition into the maximum principal stress and the minimum principal stress include:

[0092] Find the principal stresses by solving the following characteristic equation, and in the principal stress coordinate system, the maximum principal stress and the minimum principal stress can be directly read;

[0093]

[0094] Among them, represents the principal stress, , , are the normal stresses of the stress of the node on the blade in the three principal directions respectively, The stress of the node on the blade acts on x-y the shear stress on the plane, The stress of the node on the blade acts on y-z the shear stress on the plane; The stress of the node on the blade acts on x-z the shear stress on the plane.

[0095] In a specific implementation manner, the calculation of the safe life based on the maximum principal stress and the minimum principal stress to obtain the safe life results of the maximum principal stress point and the minimum principal stress point includes:

[0096] According to the following formula, the safe life results at the maximum principal stress and the minimum principal stress levels can be calculated.

[0097]

[0098] Among them, Nis the safety life result of the maximum principal stress point or the minimum principal stress point, is the maximum principal stress or the minimum principal stress, and are material constants of the turbine blade, pre-stored in a computer.

[0099] In a specific embodiment, the safety life results of the maximum principal stress point and the minimum principal stress point are accumulated to obtain the safety life result of the dangerous section;

[0100] The safety life result of the dangerous section is calculated according to the following formula:

[0101]

[0102] wherein, N is the safety life result of the dangerous section, is the safety life result of the maximum principal stress point, is the safety life result of the minimum principal stress point.

[0103] In a specific embodiment, calculating the safety life of each node based on the von Mises equivalent stress result to obtain the safety life result of each node, including:

[0104] The safety life result of each node is calculated according to the following formula:

[0105]

[0106] wherein, N is the safety life of the node, is the von Mises equivalent stress of the node, and are material constants of the turbine blade, pre-stored in a computer.

[0107] In a specific embodiment, comparing the safety life results of each node and the safety life result of the dangerous section, and selecting the minimum safety life result as the safety life result. Including:

[0108] The following function is used to select the minimum safety life result as the safety life result:

[0109]

[0110] means selecting the minimum value among all calculated safety lives as the safety life of the overall structure; is the safety life of each node, is the safety life of the dangerous section; It is not a specific mathematical formula but a general computer science concept, referring to an algorithm for selecting the minimum value from a series of elements. This function ensures that the safe life of the turbocharged electronic control actuator is determined by the weakest link, that is, the life of the entire turbocharged electronic control actuator will not exceed the minimum value among these values.

[0111] Simply put, this formula is used to determine the point in the turbocharged electronic control actuator where fatigue failure is most likely to occur, thus ensuring the safety of the entire turbocharged electronic control actuator. If the safe life of any node or critical section is short, then the safe life of the entire turbocharged electronic control actuator is determined by this shortest life.

[0112] In step S14, based on the finite element method, dynamic characteristic analysis is performed on the turbocharged data to obtain dynamic characteristic analysis results, including:

[0113] Using the finite element method for dynamic characteristic analysis, the turbocharged load is calculated as a process of linearly accelerating to 5000 r / min in 10 ms and then linearly decelerating to 0 in 10 ms under the temperature condition of 1500K. The load, stress of the turbine blade, and the thrust and rotational speed results of the actuator are obtained, and the load, stress of the turbine blade, and the thrust and rotational speed results of the actuator are used as dynamic characteristic analysis results.

[0114] The analysis process includes applying specific loads to the turbocharger in a simulation environment, such as linearly accelerating the turbine blade from a stationary state to 5000 r / min in 10 milliseconds and then decelerating to 0 r / min in the same time, while maintaining the turbine blade temperature at a high temperature of 1500K; using finite element analysis software to perform a detailed numerical simulation of the response of the turbocharger under such rapid acceleration and deceleration and high temperature environment.

[0115] Through this finite element analysis, the load, stress distribution of the turbine blade under dynamic loads, and key parameters such as the thrust and rotational speed of the actuator are obtained; these data directly reflect the actual performance of the turbocharger under dynamic conditions, providing important input data for evaluating its safe life and fatigue life; finally, a detailed analysis of these analysis results is carried out to extract the maximum stress point of the turbine blade, the maximum thrust and rotational speed of the actuator, and this information will be used in the subsequent life prediction model to scientifically evaluate the reliability and expected life of the turbocharged electronic control actuator; this method combines advanced numerical simulation technology and engineering practice experience, effectively improving the reliability of the turbocharger and the accuracy of life prediction.

[0116] In step S15, based on the dynamic characteristic analysis results, fatigue life analysis is performed to obtain fatigue life results, including:

[0117] According to the dynamic characteristic analysis results, calculate the fatigue damage at each point according to the fatigue calculation equation under the Von Mises fatigue damage criterion, and obtain the fatigue damage results on the dangerous section;

[0118] Establish a fatigue model based on the fatigue damage results to obtain the fatigue life results of the turbine blade;

[0119] Wherein the fatigue calculation equation is as follows:

[0120]

[0121] Wherein, represents the fatigue damage result; represents the fatigue life coefficient of the turbine blade; represents the stress of the turbine blade in the dynamic characteristic analysis results; represents the fatigue limit strength of the turbine blade.

[0122] Specifically, based on the dynamic characteristic analysis results, use the Von Mises fatigue damage criterion to calculate the fatigue damage at each node. The Von Mises fatigue damage criterion is to convert the complex three-dimensional stress state into a single equivalent stress value, that is, the Von Mises stress, and then evaluate the fatigue damage according to the fatigue damage accumulation theory;

[0123] Based on the fatigue damage of each node calculated above, a fatigue model can be established; this model can reflect the fatigue damage conditions at different positions and can help identify the positions most likely to occur fatigue failure, that is, the so-called "dangerous section"; in this process, it is necessary to comprehensively analyze the fatigue damage of the entire structure to determine the most vulnerable area;

[0124] Based on the fatigue model, further analysis can obtain the overall fatigue life of the turbine blade; if the fatigue damage accumulation at a certain specific position reaches or exceeds 1, it is considered that this position has reached its fatigue life; by analyzing the fatigue life of all key positions, the fatigue life of the entire turbine blade can be finally determined; if the fatigue life of any point is lower than the design requirements, the life of the entire turbine blade is determined by this point;

[0125] It should be noted that the fatigue life coefficient of the turbine blade is usually obtained based on empirical formulas or through regression analysis of a large amount of experimental data and is pre-stored in the computer; the value of the fatigue limit strength of the turbine blade is based on the stress at 1×10^7 cycle times under the maximum design pressure condition of the turbine blade and is pre-stored in the computer.

[0126] In step S16, prediction is performed based on the safety life result and the fatigue life result to obtain the predicted life result of the turbocharged electronic control actuator, including:

[0127] Compare the safety life result with the required life result of the preset turbocharged electronic control actuator. If the safety life result is less than the required life result, the predicted life result is zero;

[0128] If the safety life result is greater than the required life result, perform primary fatigue life correction on the fatigue life result to obtain the primary corrected fatigue life result;

[0129] Compare the primary corrected fatigue life result with the required life result. If the primary corrected fatigue life result is less than the required life result, the predicted life result is zero;

[0130] If the primary corrected fatigue life result is greater than the required life result, perform secondary fatigue life correction on the primary corrected fatigue life result to obtain the secondary corrected fatigue life result;

[0131] Substitute the secondary corrected fatigue life result into the accelerated life formula to obtain the life acceleration rate result, and compare the life acceleration rate result with the preset life acceleration rate requirement. If the life acceleration rate result is less than the life acceleration rate requirement, the predicted life result is zero;

[0132] If the life acceleration rate result is greater than the life acceleration rate requirement, select the secondary corrected fatigue life result as the predicted life result.

[0133] It should be noted that substituting the secondary corrected fatigue life result into the accelerated life formula to obtain the life acceleration rate result. If the life acceleration rate result is less than 60%, the predicted life result is zero; if the life acceleration rate result is greater than 60%, select the secondary corrected fatigue life result as the predicted life result.

[0134] In a specific embodiment, the performing primary fatigue life correction on the fatigue life result to obtain the primary corrected fatigue life result includes:

[0135] Perform primary fatigue life correction on the fatigue life result according to the following formula:

[0136]

[0137] where, represents the primary corrected fatigue life result, represents the fatigue life result, represents the required life result;

[0138] Nonlinear correction is performed through the above formula, taking into account the performance degradation of the material under long-term cyclic loading. At the same time, a coefficient of 0.2 is introduced as a safety margin to ensure that the prediction results are more conservative. In addition, when the fatigue life result is less than the required life , the predicted life is directly determined to be zero, reflecting the threshold effect. This formula is summarized based on a large amount of experimental data and engineering practices, and can effectively reflect the fatigue behavior of specific materials or structures under actual working conditions. It also has a certain degree of adaptability and adjustability, and the parameters can be adjusted according to different situations to better match the actual situation.

[0139] In a specific implementation manner, the secondary fatigue life correction of the initially corrected fatigue life result to obtain the secondary corrected fatigue life result includes:

[0140] Calculate the thrust ratio of the turbocharged electronic control actuator according to the following formula to obtain the actuator thrust ratio;

[0141]

[0142] where, represents the actuator thrust ratio, represents the thrust of the turbocharged electronic control actuator, represents the load of the turbocharged electronic control actuator;

[0143] According to the following formula, use the actuator thrust ratio to correct the initially corrected fatigue life result by the fatigue ratio coefficient to obtain the fatigue ratio coefficient correction result;

[0144]

[0145] where, represents the fatigue ratio coefficient correction result, represents the actuator thrust ratio, represents the initially corrected fatigue life result;

[0146] According to the following formula, perform time correction on to obtain the secondary corrected fatigue life result;

[0147]

[0148] where, represents the secondary corrected fatigue life result, represents the fatigue life correction coefficient, represents the fatigue life index.

[0149] The stress level of the actuator under actual working conditions is reflected by the actuator thrust ratio, and based on this, the fatigue ratio coefficient correction is performed on the initial corrected fatigue life result to obtain the fatigue ratio coefficient correction result, so as to more accurately evaluate the fatigue life of the actuator under different load conditions; and the fatigue ratio coefficient correction result is further adjusted using the time correction formula to consider the performance degradation and cumulative damage effect of the material during long-term use; the purpose of doing this is to combine the actual working state of the actuator with the material characteristics, improve the accuracy of fatigue life prediction, and ensure the reliable operation of the turbocharged electronic control actuator within the design life; through these steps, the durability of the actuator under various working conditions can be more comprehensively evaluated.

[0150] The working process of the present invention is described below by taking a relatively common scenario as an example. A specific implementation manner of the present invention, a method for predicting the life of a turbocharged electronic control actuator, includes the following steps:

[0151] First, use ANSYS (finite element analysis software) to perform CFD mesh division on the turbine blade, divide the entire turbine blade into four parts, namely the rim, compressor blade, turbine blade, and turbine blade, and perform static strength analysis, obtain the stress results of the static strength analysis and store them in the static strength stress library;

[0152] Next, also use ANSYS to perform CFD mesh division on the turbine blade, perform dynamic strength analysis, obtain the stress results of the dynamic strength analysis and store them in the dynamic strength stress library.

[0153] Then, use the CFD tool to perform dynamic characteristic analysis on the turbocharging, divide the turbine blade into turbine blade and turbine blade, determine the rotational speed and load of the turbine blade, obtain the actuator model through UG, simplify it into a cylinder, with the thrust direction perpendicular to the engine rotating shaft, use ANSYS to perform static strength analysis on the actuator, obtain the thrust and rotational speed results of the actuator and store them in the actuator model library;

[0154] Next, using the thrust and rotational speed results of the actuator model in the actuator model library and the rotational speed of the turbine blade, obtain the load of the turbine blade as the base load through actuator-turbine blade coupled transposed loading, perform dynamic strength analysis in the time domain using the results in the dynamic strength stress library, and obtain the stress results of the turbine blade; based on the rotational speed of the turbine blade and the results in the dynamic strength stress library, use the finite element method to obtain the load of the actuator model in the time domain of the load, and then perform dynamic strength analysis in the time domain to obtain the strain calculation results of the actuator model;

[0155] Subsequently, the thrust of the actuator at a certain rotational speed is obtained by using the load and the actuator rotational speed in the time domain of the actuator model load. The dynamic response calculation is performed by using the acceleration of the turbine blade and the load in the time domain of the actuator thrust to obtain the acceleration of the actuator. The safety design is carried out by using the acceleration of the actuator to obtain the safety life of the actuator; then the fatigue life calculation is performed by using the results in the dynamic strength stress library to obtain the fatigue life of the actuator;

[0156] Finally, the overall safety life and fatigue life of the actuator are judged based on the safety life and fatigue life of the actuator.

[0157] Using the method in this patent, calculations are performed with actual data. The rated load of the actuator is 25 kN, the thrust is 10 kN, the rotational speed is 2000 revolutions per minute, and the rated thrust ratio is 0.4; the calculated result of the actuator life is 110000 hours, the life correction time is 50000 hours, the time correction coefficient is 0.3, the acceleration factor is 10, the actual life is 5000 hours, the life calculation error is 6500 hours, and the error rate is 57.7%; another calculation method is to correct according to the actuator thrust ratio λ, the acceleration factor is 20, and after correction, the acceleration factor is 10. The calculated actual life is 80000 hours, the calculation error is 27000 hours, and the error rate is 29.5%; it can be seen from the error rate that the life error corrected according to the actuator load is relatively large, and the actual life is much lower than the required 120000 hours, while the life result calculated according to the actuator rotational speed and load is closer to the actual situation and higher than the required actual life;

[0158] In summary, the calculation method in this patent can accurately and quickly predict the life of the turbocharged actuator.

[0159] Referring to Figure 2 , the second embodiment of the present invention provides a life prediction system for a turbocharged electronic control actuator, including:

[0160] A data acquisition module, configured to acquire turbocharged electronic control actuator data, where the turbocharged electronic control actuator data includes turbine blade data and turbocharging data;

[0161] A strength analysis module, configured to perform strength analysis on the turbine blade data in the turbocharged electronic control actuator data based on the finite element method to obtain a strength analysis result;

[0162] A safety life calculation module, configured to perform safety life calculation according to the strength analysis result to obtain a safety life result;

[0163] A dynamic characteristic analysis module, configured to perform dynamic characteristic analysis on the turbocharging data in the turbocharged electronic control actuator data based on the finite element method to obtain a dynamic characteristic analysis result;

[0164] A fatigue life calculation module, configured to perform fatigue life analysis based on the dynamic characteristic analysis result to obtain a fatigue life result;

[0165] A life prediction module, configured to predict a predicted life result of the turbocharged electronic control actuator according to the safe life result and the fatigue life result.

[0166] It should be noted that the life prediction system of a turbocharged electronic control actuator provided in an embodiment of the present invention is used to execute all process steps of the life prediction method of a turbocharged electronic control actuator in the above embodiment. The working principles and beneficial effects of the two correspond one by one, and thus will not be described in detail.

[0167] An embodiment of the present invention further provides an electronic device. The electronic device includes: a processor, a memory, and a computer program stored in the memory and executable on the processor, such as a life prediction program of a turbocharged electronic control actuator. When the processor executes the computer program, the steps in the embodiments of the above-mentioned life prediction methods of a turbocharged electronic control actuator are implemented, such as Figure 1 step S11 shown. Alternatively, when the processor executes the computer program, the functions of each module / unit in the above-mentioned device embodiments are implemented, such as the life prediction module of a turbocharged electronic control actuator.

[0168] Exemplarily, the computer program may be divided into one or more modules / units. The one or more modules / units are stored in the memory and executed by the processor to complete the present invention. The one or more modules / units may be a series of computer program instruction segments capable of performing specific functions, and the instruction segments are used to describe the execution process of the computer program in the electronic device.

[0169] The electronic device may be a computing device such as a desktop computer, a notebook, a palm computer, and a smart tablet. The electronic device may include, but is not limited to, a processor and a memory. Those skilled in the art can understand that the above components are only examples of the electronic device, and do not constitute a limitation on the electronic device. It may include more or fewer components than the above, or combine some components, or different components. For example, the electronic device may further include input / output devices, network access devices, a bus, etc.

[0170] The so-called processor may be a Central Processing Unit (CPU), or may also be other general-purpose processors, Digital Signal Processors (DSPs), Application Specific Integrated Circuits (ASICs), Field-Programmable Gate Arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The processor is the control center of the electronic device and connects all parts of the entire electronic device through various interfaces and circuits.

[0171] The memory can be used to store the computer programs and / or modules. By running or executing the computer programs and / or modules stored in the memory, and by calling the data stored in the memory, the processor realizes various functions of the electronic device. The memory mainly includes a program storage area and a data storage area. Among them, the program storage area can store an operating system, application programs required for at least one function (such as a sound playback function, an image playback function, etc.); the data storage area can store data created according to the use of the mobile phone (such as audio data, phone book, etc.). In addition, the memory may include high-speed random access memory, and may also include non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a Smart Media Card (SMC), a Secure Digital (SD) card, a Flash Card, at least one magnetic disk storage device, a flash memory device, or other volatile solid-state storage devices.

[0172] Among them, if the modules / units integrated in the electronic device are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on such an understanding, to implement all or part of the processes in the above-described embodiment methods of the present invention, it can also be completed by a computer program instructing relevant hardware. The computer program can be stored in a computer-readable storage medium. When the computer program is executed by a processor, the steps of the above-described various method embodiments can be implemented. Among them, the computer program includes computer program code, and the computer program code can be in the form of source code, object code, executable file, or some intermediate form, etc. The computer-readable medium can include: any entity or device capable of carrying the computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disc, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the content included in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice within the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the computer-readable medium does not include electrical carrier signals and telecommunication signals.

[0173] It should be noted that the device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated. The components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. In addition, in the attached drawings of the device embodiments provided by the present invention, the connection relationships between the modules indicate that there is a communication connection between them, which can be specifically implemented as one or more communication buses or signal lines. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0174] The specific embodiments described above have further elaborated on the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only the specific embodiments of the present invention and is not used to limit the protection scope of the present invention. It is particularly pointed out that for those skilled in the art, any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for predicting the life of a turbocharger electronically controlled actuator, characterized in that: Executed by a computer, including: Acquiring turbocharger electronically controlled actuator data, wherein the turbocharger electronically controlled actuator data includes turbine blade data and turbocharger data; Performing strength analysis on the turbine blade data based on a finite element method to obtain a strength analysis result; Perform safety life calculation according to the strength analysis result to obtain a safety life result; The dynamic characteristics analysis of the turbocharging data is performed based on the finite element method to obtain dynamic characteristics analysis results, including: Finite element analysis software is used to numerically simulate the response of the turbocharger under rapid acceleration and deceleration and high temperature environment, and the dynamic characteristics analysis results including the load and stress of the turbine blades and the thrust and speed of the actuator are obtained; Perform fatigue life analysis according to the dynamic characteristics analysis results to obtain fatigue life results; Predicting according to the safety life result and the fatigue life result to obtain a predicted life result of the turbocharger electronically controlled actuator includes: Comparing the safe life result with a preset required life result of the turbocharger electronically controlled actuator, if the safe life result is less than the required life result, the predicted life result is zero; If the safety life result is greater than the required life result, performing a primary fatigue life correction on the fatigue life result to obtain a primary corrected fatigue life result; comparing the initial corrected fatigue life result with the required life result, and if the initial corrected fatigue life result is less than the required life result, the predicted life result is zero; If the primary corrected fatigue life result is greater than the required life result, performing a secondary fatigue life correction on the primary corrected fatigue life result to obtain a secondary corrected fatigue life result; Determine a life acceleration rate result according to the secondary corrected fatigue life result, and compare the life acceleration rate result with a preset life acceleration rate requirement. If the life acceleration rate result is less than the life acceleration rate requirement, the predicted life result is zero; If the life acceleration rate result is greater than the life acceleration rate requirement, the secondary corrected fatigue life result is selected as the predicted life result.

2. The life prediction method of a turbocharger electronically controlled actuator according to claim 1, characterized in that: The strength analysis of the turbine blade data based on the finite element method to obtain the strength analysis result includes: Based on the finite element method, static strength analysis and dynamic strength analysis are performed on the turbine blade data; wherein, the static strength analysis result is obtained by analyzing the transient temperature field stress results of the turbine blade when the rotation speed is 0 and the temperature is 1500K; the dynamic strength analysis result is obtained by analyzing the stress results of the turbine blade under the steady-state temperature field when the rotation speed is 5000r / min and the temperature is 1500K.

3. The life prediction method of a turbocharger electronically controlled actuator according to claim 2, characterized in that: The safe life calculation is performed according to the strength analysis result to obtain the safe life result, including: Calculating the normalized equivalent stress of each node in the dynamic strength analysis result to obtain the normalized equivalent stress result; Projecting the paradigm equivalent stress result in the principal stress coordinate system and decomposing it into the maximum principal stress and the minimum principal stress; Calculate the safe life based on the maximum principal stress and the minimum principal stress to obtain a safe life result at the maximum principal stress point and a safe life result at the minimum principal stress point; Accumulating the maximum principal stress point safety life result and the minimum principal stress point safety life result to obtain the dangerous section safety life result; Calculate the safety life of each node based on the paradigm equivalent stress results and obtain the safety life results of each node; Compare the safety life results of each node with the safety life results of the dangerous section, and select the minimum safety life result as the safety life result.

4. The life prediction method of a turbocharger electronically controlled actuator according to claim 1, characterized in that: The dynamic characteristic analysis of the turbocharging data based on the finite element method to obtain the dynamic characteristic analysis results includes: The finite element method is used to perform dynamic characteristic analysis and calculation of the turbocharger applied load, which is a process of linear acceleration to 5000r / min under a temperature of 1500K and a time of 10ms, and then linearly reduced to 0 within 10ms. The load and stress of the turbine blades and the thrust and speed results of the actuator are obtained, and the load and stress of the turbine blades and the thrust and speed results of the actuator are used as the dynamic characteristic analysis results.

5. The life prediction method of a turbocharger electronically controlled actuator according to claim 4, characterized in that: The performing fatigue life analysis according to the dynamic characteristic analysis result to obtain the fatigue life result includes: According to the dynamic characteristics analysis results, the fatigue damage of each point is calculated according to the fatigue calculation equation under the Von Mises fatigue damage criterion to obtain the fatigue damage result on the dangerous section; Establishing a fatigue model according to the fatigue damage results to obtain fatigue life results of turbine blades; The fatigue calculation equation is as follows: in, Indicates fatigue damage results; represents the fatigue life factor of the turbine blade; Indicates turbine blade stress in the dynamic characteristic analysis result; Indicates the fatigue limit strength of turbine blades.

6. The life prediction method of a turbocharger electronically controlled actuator according to claim 1, characterized in that: The performing the initial fatigue life correction on the fatigue life result to obtain the initial corrected fatigue life result includes: The fatigue life result is corrected for the initial fatigue life according to the following formula: in, represents the initial corrected fatigue life result, represents the fatigue life result, Indicates the required life result.

7. The life prediction method of a turbocharger electronically controlled actuator according to claim 1, characterized in that: The performing a secondary fatigue life correction on the primary corrected fatigue life result to obtain the secondary corrected fatigue life result comprises: Calculate the thrust ratio of the turbocharger electronically controlled actuator according to the following formula to obtain the actuator thrust ratio; in, represents the actuator thrust ratio, Indicates the thrust of the turbocharger electronic actuator, Indicates the load of the turbocharger electronic control actuator; According to the following formula, the actuator thrust ratio is used to perform fatigue ratio coefficient correction on the initial correction fatigue life result to obtain a fatigue ratio coefficient correction result; in, It represents the correction result of fatigue ratio coefficient. represents the actuator thrust ratio, Indicates the initial modified fatigue life result; According to the following formula, Perform time correction to obtain secondary corrected fatigue life results; in, represents the secondary corrected fatigue life result, represents the fatigue life correction factor, Represents fatigue life index.

8. A life prediction system for a turbocharger electronically controlled actuator, characterized in that: A method for predicting the life of a turbocharger electronically controlled actuator according to any one of claims 1 to 7, comprising: A data acquisition module, used for acquiring turbocharger electronically controlled actuator data, wherein the turbocharger electronically controlled actuator data includes turbine blade data and turbocharger data; A strength analysis module, used for performing strength analysis on turbine blade data in the turbocharger electronic control actuator data based on a finite element method to obtain a strength analysis result; A safety life calculation module is used to calculate the safety life according to the strength analysis result to obtain a safety life result; A dynamic characteristic analysis module, used for performing a dynamic characteristic analysis on the turbocharger data in the turbocharger electronic control actuator data based on a finite element method to obtain a dynamic characteristic analysis result; A fatigue life calculation module, used to perform fatigue life analysis according to the dynamic characteristics analysis result to obtain a fatigue life result; The life prediction module is used to predict the predicted life result of the turbocharger electronic control actuator according to the safety life result and the fatigue life result.

9. An electronic device, characterized in that: The invention comprises a processor, a memory and a computer program stored in the memory and configured to be executed by the processor, wherein when the processor executes the computer program, a life prediction method for a turbocharger electronically controlled actuator as claimed in any one of claims 1 to 7 is implemented.

Images