Method and system for predicting service life of turbocharging electric control actuator

Abstract

The invention relates to the technical field of turbocharging, and discloses a method and system for predicting the service life of a turbocharging electric control executor, and the method comprises the steps: obtaining the data of the turbocharging electric control executor, and the data of the turbocharging electric control executor comprises turbine blade data and turbocharging data; performing strength analysis on the turbine blade data based on a finite element method to obtain a strength analysis result; performing safe life calculation according to the strength analysis result to obtain a safe life result; performing dynamic characteristic analysis on the turbocharging data based on a 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 a predicted life result of the turbocharging electric control actuator. According to the method, the service life of the turbocharging electric control actuator can be accurately predicted.

Description

Technical Field

[0001] The present invention relates to the technical field of turbocharging, and in particular to a life prediction method and system for a turbocharging electronically controlled actuator. Background Art

[0002] Aircraft engine turbocharging technology is a key factor in aircraft engine performance, and its performance and reliability directly affect the overall performance of the engine; with the development of technology, the reliability of the structure and components of turbochargers has been improved, but the reliability of the supercharging mechanism is still a major problem, especially the turbine part, whose reliability accounts for more than 60% of the supercharging mechanism; in order to strike a balance between high performance and low fuel consumption, turbocharging technology needs to continue to improve, and it becomes crucial to control the relationship between the boost ratio, engine flow, speed and torque; the introduction of the turbocharger electronic control system, through the electronic control mechanism to adjust the geometry of the turbine blades, to achieve fast, continuous and precise control of the turbocharger ratio to adapt to changes in engine operating conditions.

[0003] In the prior art, the turbocharger electronic control system enables the turbocharger to quickly change its working state according to the engine's operating conditions through the operation of the electronic control mechanism. The electronically controlled actuator, as the system's actuating mechanism, can adjust the geometry of the turbine blades, thereby changing the turbine's operating conditions. However, the full structural analysis of turbine blades usually relies on simulation calculation results to predict their safe life, while in dynamic strength analysis, since the simulation results cannot fully match the test conditions, the fatigue calculation is inconsistent with the test results, and it is impossible to effectively guide the fatigue life calculation of turbine blades.

[0004] In one prior art, since the sensitivity of turbine blades to vibration loads increases and the action characteristics of the actuator are closely related to the life of the turbine blades, the simulation calculation results of the turbine blades in the full structural analysis cannot well guide the calculation of fatigue life, so the life of the actuator cannot be accurately and quickly evaluated. Summary of the invention

[0005] The present invention provides a life prediction method and system for a turbocharger electronically controlled actuator, so as to solve the problem that the life of the turbocharger electronically controlled actuator cannot be accurately and quickly evaluated.

[0006] In a first aspect, in order to solve the above technical problems, the present invention provides a method for predicting the life of a turbocharger electronically controlled actuator, comprising: 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; Performing dynamic characteristic analysis on the turbocharging data based on a finite element method to obtain dynamic characteristic analysis results; Perform fatigue life analysis according to the dynamic characteristics analysis results to obtain fatigue life results; A prediction is performed based on the safety life result and the fatigue life result to obtain a predicted life result of the turbocharger electronically controlled actuator.

[0007] In an optional implementation, the performing strength analysis on the turbine blade data based on the finite element method to obtain a 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.

[0008] In an optional implementation, performing safe life calculation according to the strength analysis result to obtain a safe life result includes: 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.

[0009] In an optional implementation, the dynamic characteristics analysis of the turbocharging data based on the finite element method to obtain the dynamic characteristics 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, stress of the turbine blades, and the thrust and speed results of the actuator are obtained, and the load, stress, thrust and speed results of the turbine blades are used as the dynamic characteristic analysis results.

[0010] In an optional implementation, performing fatigue life analysis according to the dynamic characteristic analysis result to obtain a 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:

[0011] 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.

[0012] In an optional implementation, the predicting according to the safety life result and the fatigue life result to obtain the 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; Substituting the secondary corrected fatigue life result into the accelerated life formula to obtain a life acceleration rate result and comparing 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.

[0013] In an optional implementation manner, performing an initial fatigue life correction on the fatigue life result to obtain an initial corrected fatigue life result includes: The fatigue life result is corrected for the initial fatigue life according to the following formula:

[0014] in, represents the initial corrected fatigue life result, represents the fatigue life result, Indicates the required life result.

[0015] In an optional implementation manner, performing a secondary fatigue life correction on the primary corrected fatigue life result to obtain the secondary corrected fatigue life result includes: The thrust ratio of the wheel boost electronically controlled actuator is calculated according to the following formula to obtain the actuator thrust ratio;

[0016] in, represents the actuator thrust ratio, Indicates the thrust of the turbocharger electronic actuator. Indicates the load of the wheel boost 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;

[0017] in, Indicates 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;

[0018] in, represents the secondary corrected fatigue life result, represents the fatigue life correction factor, Represents fatigue life index.

[0019] In a second aspect, the present invention provides a life prediction system for a turbocharger electronically controlled actuator, 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.

[0020] In a third aspect, the present invention further provides an electronic device comprising a processor, a memory, and a computer program stored in the memory and configured to be executed by the processor, wherein the processor implements the life prediction method of a turbocharger electronic control actuator as described above when executing the computer program.

[0021] In a fourth aspect, the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium includes a stored computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute any one of the above-mentioned methods for predicting the life of a turbocharger electronically controlled actuator.

[0022] Compared with the prior art, the present invention has the following beneficial effects: The present invention relates to the technical field of turbocharging, and discloses a life prediction method and system for a turbocharger electronically controlled actuator, comprising acquiring turbocharger electronically controlled actuator data, wherein the turbocharger electronically controlled actuator data includes turbine blade data and turbocharging data; performing strength analysis on the turbine blade data based on a finite element method to obtain a strength analysis result; performing safe life calculation based on the strength analysis result to obtain a safe life result; performing dynamic characteristic analysis on the turbocharging data based on a finite element method to obtain a dynamic characteristic analysis result; performing fatigue life analysis based on the dynamic characteristic analysis result to obtain a fatigue life result; and performing prediction based on the safe life result and the fatigue life result to obtain a predicted life result of the turbocharger electronically controlled actuator. Compared with the prior art, the present invention proposes a life prediction method for a turbocharger electronic control actuator by comprehensively applying finite element analysis, safety life assessment, fatigue life assessment and turbocharger dynamic characteristics analysis. The method first uses the finite element method to perform static and dynamic strength analysis on the turbine blades 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-solid coupling analysis. On this basis, the safety life and fatigue life are calculated to predict the service life of the actuator, thereby realizing the combination of safety life and fatigue life assessment and improving the accuracy of life prediction of the turbocharger electronic control actuator. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic flow chart of a life prediction method for a turbocharger electronically controlled actuator provided by a first embodiment of the present invention; Figure 2 It is a schematic diagram of the structure of a life prediction system for a turbocharger electronically controlled actuator provided in the second embodiment of the present invention. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] Aircraft engine turbocharging technology is a key factor in aircraft engine performance, and its performance and reliability directly affect the overall performance of the engine; with the development of technology, the reliability of the structure and components of turbochargers has been improved, but the reliability of the supercharging mechanism is still a major problem, especially the turbine part, whose reliability accounts for more than 60% of the supercharging mechanism; in order to strike a balance between high performance and low fuel consumption, turbocharging technology needs to continue to improve, and it becomes crucial to control the relationship between the boost ratio, engine flow, speed and torque; the introduction of the turbocharger electronic control system, through the electronic control mechanism to adjust the geometry of the turbine blades, to achieve fast, continuous and precise control of the turbocharger ratio to adapt to changes in engine operating conditions.

[0026] In the prior art, the turbocharger electronic control system enables the turbocharger to quickly change its working state according to the engine's operating conditions through the operation of the electronic control mechanism. The electronically controlled actuator, as the system's actuating mechanism, can adjust the geometry of the turbine blades, thereby changing the turbine's operating conditions. However, the full structural analysis of turbine blades usually relies on simulation calculation results to predict their safe life, while in dynamic strength analysis, since the simulation results cannot fully match the test conditions, the fatigue calculation is inconsistent with the test results, and it is impossible to effectively guide the fatigue life calculation of turbine blades.

[0027] In order to solve the above technical problems, refer to Figure 1 The first embodiment of the present invention provides a life prediction method for a turbocharger electronically controlled actuator, comprising the following steps: S11, acquiring turbocharger electronically controlled actuator data, wherein the turbocharger electronically controlled actuator data includes turbine blade data and turbocharger data; S12, performing strength analysis on the turbine blade data based on a finite element method to obtain a strength analysis result; S13, performing safety life calculation according to the strength analysis result to obtain a safety life result; S14, performing dynamic characteristic analysis on the turbocharger data based on the finite element method to obtain dynamic characteristic analysis results; S15, performing fatigue life analysis according to the dynamic characteristics analysis result to obtain a fatigue life result; S16, predicting based on the safety life result and the fatigue life result to obtain a predicted life result of the turbocharger electronically controlled actuator.

[0028] In step S11, it is necessary to obtain turbocharger electronically controlled actuator data, wherein the turbocharger electronically controlled actuator data includes turbine blade data and turbocharger data.

[0029] Collect and organize the data of the turbocharger electronic control actuator, including detailed turbine blade design parameters, operating conditions and turbocharger performance data. The data comes from the design documents, manufacturing records, performance test reports and real-time monitoring systems of the turbocharger electronic control actuator. These data are the basis for subsequent strength analysis, safety life calculation and fatigue life assessment. Their accuracy and completeness must be ensured in order to provide reliable input information for predicting the life of the turbocharger electronic control actuator.

[0030] In step S12, a strength analysis is performed on the turbine blade data based on a finite element method to obtain a strength analysis result.

[0031] 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.

[0032] Specifically, when conducting a static strength analysis of turbine blades, it is first necessary to establish a geometric model of the blades and divide the mesh in the finite element analysis software, then define the physical and mechanical properties of the material, and then set boundary conditions to simulate the constraint state of the blades at work, and apply a pressure load based on the maximum design pressure condition to the blades. After that, transient thermal analysis is used to simulate the temperature distribution of the blades at a high temperature of 1500K, and then the resulting thermal stress is calculated, and finally the static strength performance of the blades at high temperatures is evaluated to ensure that they will not be damaged under the most demanding working conditions; this process involves calculating the Von Mises stress of each unit on the blade and comparing it with the allowable stress of the material to verify whether the blades meet the design requirements; through this analysis, the static strength analysis results of the turbine blades under thermal stress caused by high temperature in a stationary state can be obtained, providing important data for subsequent safety life calculations.

[0033] Specifically, when conducting a dynamic strength analysis of turbine blades, it is first necessary to establish a geometric model of the blades and divide the mesh in the finite element analysis software, then define the physical and mechanical properties of the material, and then set the boundary conditions to simulate the rotation state of the blades in operation, and apply a pressure load based on the maximum design pressure condition to the blades. After that, a steady-state thermal analysis is performed to simulate the steady-state temperature field of the blades at a speed of 5000r / min and a temperature of 1500K, and then the resulting thermal stress and centrifugal stress are calculated, and finally the dynamic strength performance of the blades under high temperature and high-speed rotation conditions is evaluated to ensure that they will not be damaged under the most demanding working conditions; this process involves calculating the Von Mises stress of each unit on the blade and comparing it with the allowable stress of the material to verify whether the blades meet the design requirements; through this analysis, the dynamic strength analysis results of the turbine blades in a steady-state temperature field at a speed of 5000r / min and a temperature of 1500K can be obtained, providing important data for subsequent fatigue life analysis.

[0034] In step S13, a safe life calculation is performed according to the strength analysis result to obtain a 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.

[0035] In a specific implementation, the calculating the normalized equivalent stress of each node in the dynamic strength analysis result to obtain the normalized equivalent stress result includes: According to the results of dynamic strength analysis, the stress components of each node on the blade are calculated and mathematically processed, and the complex three-dimensional stress state is converted into a single equivalent stress value, namely the paradigm equivalent stress, by applying the von Mises stress criterion and according to the following formula.

[0036]

[0037] in, represents the paradigm equivalent stress, , , are the normal stresses of the nodes on the blade in the three main directions, , , is the shear stress at the node on the blade.

[0038] In a specific implementation, projecting the normal equivalent stress result in a principal stress coordinate system and decomposing it into a maximum principal stress and a minimum principal stress includes: The principal stresses are found by solving the following characteristic equations, and in the principal stress coordinate system, the maximum and minimum principal stresses can be directly read;

[0039] in, represents the principal stress, , , are the normal stresses of the nodes on the blade in the three main directions, The stresses at the nodes on the blade act on xy Shear stress on a plane, The stresses at the nodes on the blade act on yz Shear stress on a plane; The stresses at the nodes on the blade act on xz Shear stress on a plane.

[0040] In a specific implementation, the safe life calculation is performed based on the maximum principal stress and the minimum principal stress to obtain the safe life result of the maximum principal stress point and the safe life result of the minimum principal stress point, including: According to the following formula, the safety life results under the maximum principal stress and the minimum principal stress levels can be calculated.

[0041]

[0042] in, N is 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 It is the material constant of the turbine blade and is pre-stored in the computer.

[0043] In a specific implementation manner, the maximum principal stress point safety life result and the minimum principal stress point safety life result are accumulated to obtain a dangerous section safety life result; The safe life of the dangerous section is calculated according to the following formula:

[0044] in, N is the result of the safe life of the dangerous section, is the safety life result of the maximum principal stress point, It is the safe life result of the minimum principal stress point.

[0045] In a specific implementation, the calculating the safe life of each node based on the paradigm equivalent stress result to obtain the safe life result of each node includes: The safety life of each node is calculated according to the following formula:

[0046] in, N is the safe lifetime of the node, is the paradigm equivalent stress of the node, and It is the material constant of the turbine blade and is pre-stored in the computer.

[0047] In a specific implementation, the safe life results of each node are compared with the safe life results of the dangerous section, and the minimum safe life result is selected as the safe life result. Use the following function to select the minimum safety life result as the safety life result:

[0048] It means that the smallest value among all calculated safety lives is selected as the safety life of the overall structure; is the safety life of each node, is the safe life of the dangerous section; It is not a specific mathematical formula, but a general computer science concept, which refers to an algorithm for selecting the minimum value of a series of elements. This function ensures that the safe life of the turbocharger electronic control actuator is determined by the weakest link, that is, the life of the entire turbocharger electronic control actuator will not exceed the minimum of these values.

[0049] In simple terms, this formula is used to determine the point in the turbocharger electronic control actuator where fatigue failure is most likely to occur, thereby ensuring the safety of the entire turbocharger electronic control actuator. If the safe life of any node or dangerous section is shorter, the safe life of the entire turbocharger electronic control actuator is determined by this shortest life.

[0050] In step S14, a dynamic characteristic analysis is performed on the turbocharging data based on a finite element method to obtain a dynamic characteristic analysis result, including: 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, stress of the turbine blades, and the thrust and speed results of the actuator are obtained, and the load, stress, thrust and speed results of the turbine blades are used as the dynamic characteristic analysis results.

[0051] The analysis process involves applying specific loads to the turbocharger in a simulation environment, such as linearly accelerating the turbine blades from a stationary state to 5000 r / min in 10 milliseconds, and then decelerating to 0 r / min in the same amount of time, while maintaining the turbine blade temperature at a high temperature of 1500K; using finite element analysis software, a detailed numerical simulation of the turbocharger's response to this rapid acceleration and deceleration and high temperature environment is performed.

[0052] Through this finite element analysis, the load and stress distribution of the turbine blades under dynamic loads, as well as key parameters such as the thrust and speed of the actuator are obtained; these data directly reflect the actual performance of the turbocharger under dynamic conditions, and provide important input data for evaluating its safe life and fatigue life; finally, these analysis results are analyzed in detail to extract the maximum stress point of the turbine blades, the maximum thrust and speed of the actuator, and this information will be used in subsequent life prediction models to scientifically evaluate the reliability and expected life of the turbocharger electronic control actuator; this method combines advanced numerical simulation technology and engineering practice experience to effectively improve the reliability of the turbocharger and the accuracy of life prediction.

[0053] In step S15, fatigue life analysis is performed according to the dynamic characteristic analysis result to obtain fatigue life results, including: 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:

[0054] 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.

[0055] Specifically, based on the dynamic characteristics analysis results, the Von Mises fatigue damage criterion is used to calculate the fatigue damage on each node. The Von Mises fatigue damage criterion converts the complex three-dimensional stress state into a single equivalent stress value, namely the Von Mises stress, and then evaluates the fatigue damage according to the fatigue damage accumulation theory; Based on the fatigue damage of each node calculated above, a fatigue model can be established; this model can reflect the fatigue damage at different locations and can help identify the location where fatigue failure is most likely to occur, the so-called "dangerous section"; in this process, a comprehensive analysis of the fatigue damage of the entire structure is required to determine the most vulnerable area; Based on the fatigue model, further analysis can derive the overall fatigue life of the turbine blade; if the fatigue damage accumulation at a specific location reaches or exceeds 1, it is considered that the location has reached its fatigue life; by analyzing the fatigue life of all key locations, the fatigue life of the entire turbine blade can be determined; if the fatigue life of any point is lower than the design requirement, the life of the entire turbine blade is determined by this point; It should be noted that the fatigue life coefficient of the turbine blade is usually obtained based on an empirical formula 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 of the turbine blade at 1×10^7 cycles under the maximum design pressure condition, and is pre-stored in the computer.

[0056] In step S16, prediction is performed based on the safety life result and the fatigue life result to obtain a predicted life result of the turbocharger electronically controlled actuator, including: 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; Substituting the secondary corrected fatigue life result into the accelerated life formula to obtain a life acceleration rate result and comparing 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.

[0057] It should be noted that the secondary corrected fatigue life result is substituted into the accelerated life formula to obtain the life acceleration rate result. If the life acceleration rate result is greater than 60%, the predicted life result is zero. If the life acceleration rate result is less than or equal to 60%, the secondary corrected fatigue life result is selected as the predicted life result.

[0058] In a specific implementation, performing an initial fatigue life correction on the fatigue life result to obtain an initial corrected fatigue life result includes: The fatigue life result is corrected for the initial fatigue life according to the following formula:

[0059] in, represents the initial corrected fatigue life result, represents the fatigue life result, Indicates the required life result; The above formula is used for nonlinear correction, taking into account the performance degradation of the material under long-term cyclic loads, and introducing a coefficient of 0.2 as a safety margin to ensure that the prediction results are more conservative; in addition, when the fatigue life results Shorter than required life When , the predicted life is directly determined to be zero, which reflects the threshold effect. This formula is based on a large amount of experimental data and engineering practice, and can effectively reflect the fatigue behavior of specific materials or structures under actual working conditions. It has certain adaptability and adjustability, and can adjust parameters according to different situations to better match the actual situation.

[0060] In a specific implementation manner, performing a secondary fatigue life correction on the primary corrected fatigue life result to obtain the secondary corrected fatigue life result includes: The thrust ratio of the wheel boost electronically controlled actuator is calculated according to the following formula to obtain the actuator thrust ratio;

[0061] in, represents the actuator thrust ratio, Indicates the thrust of the turbocharger electronic actuator. Indicates the load of the wheel boost 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;

[0062] in, Indicates 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;

[0063] in, represents the secondary corrected fatigue life result, represents the fatigue life correction factor, Represents fatigue life index.

[0064] The actuator thrust ratio is used to reflect the stress level of the actuator under actual working conditions, and the fatigue ratio coefficient is corrected for the initial corrected fatigue life result accordingly 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 effects of the material during long-term use; the purpose of this is to combine the actual working state of the actuator with the material properties, 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.

[0065] The following describes the working process of the present invention by taking a relatively common scenario as an example. A specific implementation of the present invention is a life prediction method for a turbocharger electronically controlled actuator, comprising the following steps: Firstly, the turbine blade is meshed by CFD using ANSYS (finite element analysis software), and the whole turbine blade is divided into four parts, namely, the wheel rim, the compressor blade, the turbine blade and the turbine blade, and a static strength analysis is performed to obtain the stress results of the static strength analysis and store them in the static strength stress library; Next, ANSYS is also used to perform CFD meshing on the turbine blades, conduct dynamic strength analysis, obtain the stress results of the dynamic strength analysis and store them in the dynamic strength stress library.

[0066] Then, the dynamic characteristics of the turbocharger are analyzed using CFD tools, the turbine blades are divided into turbine blades and turbine blades, the speed and load of the turbine blades are determined, the actuator model is obtained through UG, simplified into a cylinder, and the thrust direction is perpendicular to the engine shaft. The actuator is subjected to static strength analysis using ANSYS, and the thrust and speed results of the actuator are obtained and stored in the actuator model library; Next, using the thrust and speed results of the actuator model in the actuator model library and the speed of the turbine blades, the load of the turbine blades is obtained as the basic load through actuator-turbine blade coupling transposed loading, and the dynamic strength analysis in the time domain is performed using the results in the dynamic strength stress library to obtain the stress results of the turbine blades; based on the speed of the turbine blades and the results in the dynamic strength stress library, the load of the actuator model in the time domain is obtained using the finite element method, and then the dynamic strength analysis in the time domain is performed to obtain the strain calculation results of the actuator model; Subsequently, the thrust of the actuator at the speed is obtained using the load of the actuator model in the load time domain and the actuator speed. The acceleration of the turbine blades and the load of the actuator in the thrust time domain are used to perform dynamic response calculations to obtain the acceleration of the actuator. The acceleration of the actuator is used to perform safety design to obtain the safe life of the actuator. The results in the dynamic strength stress library are then used to calculate the fatigue life to obtain the fatigue life of the actuator. Finally, the overall safety life and fatigue life of the actuator are judged based on the actuator's safety life and actuator fatigue life.

[0067] The method in this patent is used to calculate with actual data. The rated load of the actuator is 25 kN, the thrust is 10 kN, the speed is 2000 rpm, and the rated thrust ratio is 0.4; the actuator life calculation result is 110,000 hours, the life correction time is 50,000 hours, the time correction coefficient is 0.3, the acceleration factor is 10, the actual life is 5,000 hours, the life calculation error is 6,500 hours, and the error rate is 57.7%; another calculation method is to correct it according to the actuator thrust ratio λ, the acceleration factor is 20, and the corrected acceleration factor is 10. The actual life is calculated to be 80,000 hours, the calculation error is 27,000 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 large, and the actual life is far lower than the required 120,000 hours, while the life result calculated according to the actuator speed and load is closer to the actual life, and higher than the required actual life; In summary, the calculation method in this patent can accurately and quickly predict the life of the turbocharger actuator.

[0068] Reference Figure 2 The second embodiment of the present invention provides a life prediction system for a turbocharger electronically controlled actuator, 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.

[0069] It should be noted that the life prediction system of a turbocharger electronically controlled actuator provided in an embodiment of the present invention is used to execute all the process steps of the life prediction method of a turbocharger electronically controlled actuator in the above embodiment. The working principles and beneficial effects of the two correspond one to one, and thus will not be repeated here.

[0070] 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 for a turbocharger electronically controlled actuator. When the processor executes the computer program, the steps in the above-mentioned embodiments of the life prediction method for the turbocharger electronically controlled actuator are implemented, such as Figure 1 Alternatively, when the processor executes the computer program, the functions of the modules / units in the above-mentioned device embodiments are realized, such as the life prediction module of the turbocharger electronically controlled actuator.

[0071] Exemplarily, the computer program may be divided into one or more modules / units, which are stored in the memory and executed by the processor to implement the present invention. The one or more modules / units may be a series of computer program instruction segments capable of implementing specific functions, which are used to describe the execution process of the computer program in the electronic device.

[0072] The electronic device may be a computing device such as a desktop computer, a notebook, a PDA, and a smart tablet. The electronic device may include, but is not limited to, a processor and a memory. Those skilled in the art will appreciate that the above components are merely examples of electronic devices and do not constitute a limitation on the electronic device. The electronic device may include more or fewer components than the above components, or may combine certain components, or different components. For example, the electronic device may also include input and output devices, network access devices, buses, etc.

[0073] The processor may be a central processing unit (CPU), other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or any conventional processor, etc. The processor is the control center of the electronic device, and uses various interfaces and lines to connect various parts of the entire electronic device.

[0074] The memory can be used to store the computer program and / or module, and the processor realizes various functions of the electronic device by running or executing the computer program and / or module stored in the memory, and calling the data stored in the memory. The memory can mainly include a program storage area and a data storage area, wherein the program storage area can store an operating system, an application required for at least one function (such as a sound playback function, an image playback function, etc.), etc.; the data storage area can store data created according to the use of the mobile phone (such as audio data, a phone book, etc.), etc. In addition, the memory can include a high-speed random access memory, and can also include a non-volatile memory, such as a hard disk, a memory, a plug-in hard disk, a smart memory card (Smart Media Card, SMC), a secure digital (Secure Digital, SD) card, a flash card (Flash Card), at least one disk storage device, a flash memory device, or other volatile solid-state storage devices.

[0075] Wherein, if the module / unit integrated in the electronic device is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such an understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Wherein, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium. It should be noted that the content contained in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media do not include electric carrier signals and telecommunication signals.

[0076] It should be noted that the device embodiments described above are merely schematic, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. In addition, in the accompanying drawings of the device embodiments provided by the present invention, the connection relationship between the modules indicates that there is a communication connection between them, which may be specifically implemented as one or more communication buses or signal lines. A person of ordinary skill in the art may understand and implement it without paying any creative effort.

[0077] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. It is particularly pointed out that for those skilled in the art, any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of protection 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; Performing dynamic characteristic analysis on the turbocharging data based on a finite element method to obtain dynamic characteristic analysis results; Perform fatigue life analysis according to the dynamic characteristics analysis results to obtain fatigue life results; A prediction is performed based on the safety life result and the fatigue life result to obtain a predicted life result of the turbocharger electronically controlled actuator.

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 predicting according to the safety life result and the fatigue life result to obtain the 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; Substituting the secondary corrected fatigue life result into the accelerated life formula to obtain a life acceleration rate result and comparing 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.

7. The life prediction method of a turbocharger electronically controlled actuator according to claim 6, 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.

8. The life prediction method of a turbocharger electronically controlled actuator according to claim 7, 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: The thrust ratio of the wheel boost electronically controlled actuator is calculated 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 wheel boost 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, Indicates 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.

9. A life prediction system for a turbocharger electronically controlled actuator, characterized in that: include: 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 electronically controlled 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.

10. An electronic device, characterized in that: It 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 8 is implemented.

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