47 results about "Creep fatigue" patented technology

The invention provides an internal damage assessment method and system based on a multi-modal graphite component, and relates to the technical field of material deterioration assessment, and the method comprises the steps: generating a standardized multi-modal data stream through synchronously collecting five-modal data; extracting acoustic and electro-thermal physical features from the multi-modal data stream, and constructing a multi-dimensional damage sensitive feature vector; inputting the multi-dimensional damage sensitive feature vectors into a deep learning network corrected by a physical constraint layer, and extracting crack quantization parameters from the deep learning network; inputting the crack quantization parameters into a digital twin driven irradiation-creep-fatigue coupling damage model, and calculating the residual life and failure probability of the overall structure; and in combination with the space coordinate information of the three-dimensional crack probability field, a preventive maintenance instruction and schedule for the high-risk modular component are generated and optimized. According to the method, accurate perception, quantitative evaluation, accurate prognosis and optimized decision making of the internal damage of the graphite component are realized, the resource utilization efficiency is maximized, and unnecessary shutdown loss is reduced.

The invention discloses a heavy-duty gas turbine blade creep fatigue life design method considering an anisotropic effect, and relates to the technical field of gas turbine key component creep fatigue life evaluation.The method comprises the steps that orientation factor parameters on characteristic orientation are determined based on tensile data on [001] crystal orientation; constructing a modified stress relaxation formula; constructing an anisotropic failure strain energy density equation based on the pure creep performance data and the orientation factor parameters, and determining an upper platform of failure inelastic strain energy density on [001] crystal orientation; further determining an upper platform of the failure inelastic strain energy density on the feature orientation; constructing a creep damage prediction model based on a modified stress relaxation formula and an anisotropic failure strain energy density equation; and adopting the creep damage prediction model to obtain the creep fatigue life of the anisotropic turbine blade material sample. The method meets the actual requirements of service life evaluation of the high-temperature part of the heavy-duty gas turbine.

The invention discloses a life health management method and system for an HR3C material, and relates to the technical field of data processing, and the method comprises the steps: collecting the operation condition data of the HR3C material in a service state, carrying out the creep, fatigue and creep-fatigue interaction performance testing of a welding seam and a heat affected zone, and obtaining the real-time service state data; combining a high-temperature accelerated aging test result to construct a structure-performance coupling model; and performing microscopic damage calculation and residual life prediction based on the organization-performance coupling model and the real-time service state data, and generating a health assessment index to execute health management. The technical problems that in the prior art, damage evolution of the HR3C material under the complex high-temperature working condition cannot be accurately evaluated in real time, and the service life prediction and health management precision is insufficient are solved, and the purposes that through performance coupling analysis and aging process feedback under the multiple working conditions, microcosmic damage is accurately evaluated, and the remaining service life is dynamically predicted are achieved. And the health management precision is improved.

The invention discloses a damage evolution prediction method and device based on dynamic order reduction, equipment, a medium and a product, and relates to the field of aero-engine health management and monitoring. The method comprises the following steps: performing a finite element fatigue / creep-fatigue simulation test on a similar structural member covering stress states under various operating conditions, and extracting a time-physical field matrix of finite element fatigue simulation results under the various operating conditions; performing dynamic order reduction processing on the time-physical field matrix to reduce the dimension of the matrix to obtain an order-reduced matrix; constructing a reduced order model; performing equivalent stress field distribution reduction according to the reduced-order model to obtain a reduced-order reduced physical field; and performing damage distribution evolution and fatigue life prediction under fatigue or creep-fatigue load based on the reduced-order reduction physical field, and performing correction based on a fatigue life prediction model. According to the invention, the efficiency and universality of life prediction can be improved.

The invention discloses a method and system for predicting the service life of a steel base material based on creep-fatigue interaction, and relates to the technical field of data processing.The method comprises the steps that stress, strain and temperature data of an in-service steel base material are collected to construct a service parameter set, a creep, fatigue and composite loading test sequence is generated based on the parameter set, and the service life of the steel base material is predicted; and carrying out a creep-fatigue interaction test, extracting damage evolution data, carrying out multi-dimensional association on the damage evolution data and service parameters, establishing a creep-fatigue collaborative damage model, and realizing accurate prediction of the residual life of the steel base material through iterative calculation. The technical problems that in the prior art, the interaction effect of creep and fatigue under the complex service condition cannot be considered at the same time, so that the steel base metal service life prediction result is large in deviation, and reliability is insufficient are solved, and the aim of predicting the service life of the steel base metal by constructing the creep-fatigue collaborative damage model and combining real service parameters is achieved. And the service life prediction precision and reliability of the steel base metal under the complex working condition are improved.

The invention discloses a high-temperature component reliability interval assessment method, device, equipment, medium and product, and relates to the technical field of reliability assessment, the method comprises the following steps: carrying out probability damage assessment on a high-temperature component to obtain stress and strain probability distribution of a dangerous point of the high-temperature component; constructing and training a plurality of physical information neural network models by taking the creep fatigue test conditions of the high-temperature part as input and the test life as output; according to the life prediction result of each physical information neural network model, constructing a life prediction interval and basic trust distribution of each model; carrying out fusion through a Dempster method to obtain a fusion life prediction interval; according to the fused life prediction interval and the stress and strain probability distribution, a reliability interval evaluation result of the life of the high-temperature component is obtained, the model uncertainty brought by the selected model is considered, and the method has the advantages of being high in prediction precision, high in engineering applicability and good in physical interpretation.

The invention discloses a spaceflight structure strength analysis method based on a multi-physics field, which comprises the following steps: establishing a parameterized finite element model integrated with a friction heat generation effect by acquiring in-orbit temperature time sequence data and material creep characteristic parameters, and simulating inelastic strain accumulation of a structure under a thermal cycle load; a nonlinear damage model considering a creep-fatigue interaction effect is adopted to calculate an accumulated damage degree, an effective stiffness matrix is constructed to deduce a structure inherent frequency drift distance and a shape retention capability parameter, and finally, through a safety margin evaluation algorithm, the effective strength of a material and the maximum equivalent stress of the structure are dynamically compared, so that the performance of the material is evaluated. And accurate prediction of quantitative residual strength and safe service life is realized. According to the method, the technical problems that the local thermal coupling effect is not depicted enough and the creep fatigue nonlinear interaction effect is ignored are solved, and the precision and reliability of on-orbit performance degradation prediction of the spaceflight flexible structure are remarkably improved.

This invention discloses a method and system for predicting the creep fatigue behavior of martensitic heat-resistant steel, relating to the field of high-temperature creep fatigue performance evaluation technology. The method includes: acquiring the microstructure evolution of copper-containing martensitic heat-resistant steel during the test process, obtaining the cyclic strength change rate based on the microstructure evolution, and calculating the creep rate of the copper-containing martensitic heat-resistant steel in the dislocation climb hard phase, as well as the dislocation density under cyclic loading conditions; based on the cyclic strength change rate, creep rate, and dislocation density, obtaining the elastic strain tensor, plastic strain tensor, and creep strain tensor of the copper-containing martensitic heat-resistant steel, and predicting the stress-strain evolution of the copper-containing martensitic heat-resistant steel under cyclic loading conditions based on the elastic modulus tensor; this invention overcomes the limitations of macroscopic creep fatigue behavior prediction methods and provides a new approach to revealing the influence of microstructure on creep fatigue performance.

This application discloses a method, apparatus, equipment, medium, and product for predicting damage evolution based on dynamic order reduction, relating to the field of aero-engine health management and monitoring. The method includes: conducting finite element fatigue / creep-fatigue simulation tests on structural components covering stress states under various operating conditions, and extracting the time-physics field matrix from the finite element fatigue simulation results under each operating condition; dynamically reducing the order of the time-physics field matrix to reduce its dimension, obtaining a reduced-order matrix; constructing a reduced-order model; restoring the equivalent stress field distribution based on the reduced-order model to obtain the reduced-order physical field; predicting the damage distribution evolution and fatigue life under fatigue or creep-fatigue loading based on the reduced-order physical field, and making corrections based on the fatigue life prediction model. This application can improve the efficiency and universality of life prediction.

The present application relates to the technical field of aero-engine, disclose a kind of gear end tooth repair method, comprising the following steps: S1, preparation package, after filling alloy disc powder in package, package is set on the end tooth of gear;S2, by pressure device let the end tooth of gear and package between vacuum after package brazing sealing;S3, to gear heat isostatic pressing;S4, to gear heat treatment;S5, using circular arc end tooth grinder to gear grinding processing.The alloy disc powder can be realized with the same mechanics of gear parent alloy, anti creep fatigue, no metallurgical defect connection, can effectively solve the problem of crack, poor mechanical properties, poor creep performance, poor wear resistance and so on.

The embodiment of the invention discloses a mode importance analysis method for a turbine blade in a fuzzy failure state, which comprises the following steps of: constructing a creep-fatigue life reliability analysis model of the turbine blade in the fuzzy failure state, introducing a one-dimensional standard normal variable, and fusing fuzziness of the failure state into a limit state function to form a generalized limit state function; a Kriging model of a generalized limit state function corresponding to each mode is updated by adopting a sequence, repeated training of the Kriging model is avoided, the utilization rate of a training sample is improved, the system reliability and the component reliability are analyzed respectively, and then mode importance analysis under a turbine blade fuzzy failure state is completed in combination with a mode importance index system. According to the analysis result, the importance sequence of the fatigue life reliability of each part of the turbine blade in the fuzzy failure state can be explored, the characteristics of key parts of the turbine blade in the fuzzy failure state can be identified, and a scientific and reasonable basis is provided for structural optimization and fault detection of the turbine blade.

The application discloses a kind of creep fatigue testers capable of monitoring the change of round tube shaft diameter, comprising: sample protection tube, upper sleeve head, lower sleeve head, pressure inlet pipe and locking part;Two ends of sample protection tube are respectively detachably provided with upper cover and lower cover;The bottom end of lower sleeve head is fixed on lower cover, and the top end of lower sleeve head is provided with a first plug-in slot;The bottom end of upper sleeve head is provided with a second plug-in slot, the top end of upper sleeve head is provided with a third plug-in slot, and a first through hole for connecting the second plug-in slot and the third plug-in slot is provided on the upper sleeve head;The bottom end of pressure inlet pipe penetrates through the upper cover and is sealingly inserted and fixed with the third plug-in slot, and the locking part is connected between the pressure inlet pipe and the upper cover;The shaft diameter measuring mechanism is connected between the upper cover and the lower cover, and the detection end of the shaft diameter measuring mechanism can rotate with the axis of the round tube sample tube as the center.The application can monitor the change process of the shaft diameter of the round tube sample tube at every point around the round tube during creep fatigue test.

The application discloses a kind of based on the prediction method of cyclic creep deformation behavior of unified viscoplastic theory, specific implementation is at the same test temperature, carry out cyclic creep test under different conditions, obtain corresponding data;Unified viscoplastic constitutive model is established, including the establishment of main control equation, flow rule, movement hardening criterion, isotropic hardening criterion;A group of strain control creep-fatigue tests at the above temperature is carried out, and corresponding data is obtained, including each cycle hysteresis loop, each cycle peak stress, strain amplitude;The initial material parameters of the constitutive model are determined using the creep-fatigue test data, and the optimal material parameters are obtained by fitting a group of cyclic creep deformation curves through trial parameter method;The final constitutive model is determined using the obtained optimal material parameters, and the deformation behavior of the material under cyclic creep load is predicted by the constitutive model.The application has the advantages of strong applicability and high precision, and can predict the deformation behavior of the material under cyclic creep.

The invention discloses a creep fatigue test method and device for a polar plate of an electrochemical fuel cell. The testing method comprises the steps that S1, a plurality of temperature points which change in a stepped mode are sequentially applied to a pole plate within a first preset temperature range so that a stepped temperature creep test can be carried out, and the first preset temperature range covers the working temperature range of an electric pile of the electrochemical fuel cell; s2, keeping the temperature of the polar plate constant in a first preset temperature range, and applying cyclic stress to the polar plate to perform a stress cyclic test; s3, applying temperature to the polar plate in a second preset temperature range which is higher than the working temperature range of the electric pile of the electrochemical fuel cell, so as to carry out a high-temperature accelerated aging test; and S4, acquiring and calculating creep related parameters of the polar plate in the testing process of S1 to S3. The test method and device provided by the invention can accurately and efficiently evaluate the creep fatigue characteristics of the polar plate.

The application discloses a nonlinear calibration method for high-temperature mechanical property testing, and relates to the technical field of mechanical property testing of key components of high-temperature equipment. The method comprises the following steps: obtaining information data of a target material under different working conditions; the information data comprises half-life cycle load-displacement data; pre-processing the information data; based on the pre-processed information data, performing data conversion based on a polynomial function model to determine strain data; the strain data is used to realize cross-working-condition unified representation of data; the polynomial function model is a relationship model used to represent the strain-displacement calibration relationship, which is constructed based on experimental data by using a least square method; the experimental data is strain-displacement data obtained after a set number of fatigue and creep-fatigue tests are performed based on multiple loading conditions. The application aims to realize displacement and strain conversion and improve conversion accuracy.

The present application relates to the technical field of high-temperature component creep fatigue test and life assessment, and particularly relates to a high-temperature structure deformation accumulation dynamic creep fatigue load design method under a peak regulation working condition. High-temperature creep performance, cyclic deformation performance, a target test temperature, a typical start-stop number or equivalent cycle number, a main load level range during steady operation, and basic parameters of stress / strain control capability of a testing machine of a target high-temperature structure or a sample thereof are obtained. A stress / strain hybrid control mode is used to generate a dynamic creep fatigue load waveform of the high-temperature structure or the sample thereof. When a dynamic creep fatigue load is executed on a creep fatigue testing machine and a cycle feature meets preset stability and repeatability criteria, the load design is determined to be effective. The present application is easy to implement on existing equipment: the designed load waveform can be realized through software control on a creep fatigue testing machine with stress / strain double closed loop and program loading function, without the need to increase additional hardware, and the engineering operability is strong.

The invention discloses an asphalt mixture creep fatigue interaction damage evaluation method which comprises the following steps: S1, carrying out a direct tensile fatigue test and a static creep test on an asphalt mixture sample to obtain stress-strain data; s2, constructing a fatigue damage model of the asphalt mixture, and determining fitting parameters of the model; s3, establishing a creep damage constitutive model and a creep damage model, determining fitting parameters of the creep damage model, and calculating the creep critical damage degree of the asphalt mixture; s4, performing sequential tests of different loading sequences on the asphalt mixture test piece; s5, calculating damage corresponding to different sequential tests; s6, correcting the fatigue damage model and the creep damage model; and S7, establishing a creep fatigue interaction model. The method can be used for evaluating and identifying the relationship between damage accumulation and interaction of the asphalt mixture under the interaction of creep and fatigue.

The application provides an aero-engine part creep-fatigue life design method. A part finite element model is established, mission profile stress analysis is carried out to obtain the principal stress cycle peak stress σ max and the principal stress cycle stress ratio R of the dangerous position of the part; a creep-fatigue interaction judgment criterion is established by using the relationship between (1-R)*σ max and twice the material proportional limit 2σ s ; a creep-fatigue damage interaction envelope line of the part is established; the creep-fatigue life of the dangerous position of the part is calculated based on the relationship between (1-R)*σ max and 2σ s . The relationship between (1-R)*σ max and 2σ s is used as the judgment criterion, the constraint relationship of temperature and load on the creep-fatigue interaction effect is comprehensively considered; the creep-fatigue interaction damage limit with reliability indexes is determined through the interaction damage envelope line with specific confidence and survival rate requirements; the creep-fatigue life calculation method considers the influence of stress relaxation on creep damage and fatigue damage in the cycle process, and the applicability of the analysis method under different stress states is ensured.

A method and system for determining a critical inelastic strain rate during a creep-fatigue damage process are provided. The method includes: obtaining a plurality of high-temperature equipment materials; under a same temperature condition, conducting a creep test, a fatigue test, and a creep-fatigue interaction test on the high-temperature equipment materials, respectively; establishing a stress relaxation formula based on the creep test result; establishing a fitting equation for an inelastic strain energy density at a failure based on the fatigue test result; establishing a net tensile hysteresis energy-induced fatigue damage equation based on the creep-fatigue interaction test result; and according to a linear cumulative damage rule, determining a creep-fatigue life of the high-temperature equipment materials based on the stress relaxation formula, the fitting equation for an inelastic strain energy density at a failure, and the net tensile hysteresis energy-induced fatigue damage equation.

The invention provides a digital twin modeling method for predicting creep fatigue life of a turbine disc, which comprises the following steps of: S1, determining an input load of each working condition through experimental working condition design; s2, performing finite element simulation on the turbine disc according to the input load to obtain stress-strain fields under different working conditions; s3, establishing a reduced-order model of stress-strain calculation according to the stress-strain field obtained through calculation in S2; s4, establishing a regression model based on the stress-strain data under different working condition loads; s5, fusing the reduced-order model and the regression model, and establishing an agent model of the stress field and the strain field of the turbine disc; s6, calculating stress-strain data under the load value according to the load monitored in real time; and S7, calculating the creep fatigue residual life of the turbine disc through the total damage. According to the data order reduction technology and the data fitting regression technology, the agent model of the stress field and the strain field of the turbine disc is established, and rapid calculation of the stress and the strain of the turbine disc under different working conditions is achieved.

The application provides a material high-temperature performance testing device and method, which comprises a columnar expansion body, a first rigid connecting plate, a second rigid connecting plate, a creep fatigue sample and a high-temperature box. The columnar expansion body is provided with a central hole in the axial direction. The first rigid connecting plate is connected to one end of the columnar expansion body. The second rigid connecting plate is connected to the other end of the columnar expansion body. The creep fatigue sample is arranged in the central hole and is connected to the first rigid connecting plate and the second rigid connecting plate in an interference fit. The columnar expansion body, the first rigid connecting plate, the second rigid connecting plate and the creep fatigue sample are all arranged in the high-temperature box. The material linear expansion coefficient of the columnar expansion body is greater than that of the creep fatigue sample, and the material linear expansion coefficient of the creep fatigue sample is much greater than that of the first rigid connecting plate and the second rigid connecting plate. The application can realize multiple form loading matching temperature load and force load and realize the testing of the high-temperature performance of the material.

The application discloses a turbine disc creep-fatigue test load determination method and belongs to the technical field of aero-engines. The method comprises the following steps: performing transient stress and creep analysis on a turbine disc, calculating fatigue damage components and creep damage components in each stage, and accumulating total fatigue damage values and total creep damage values in a complete flight cycle; determining a flight state with the maximum total damage as a standard cycle; taking the standard cycle as the only reference, a complete set of test parameters are determined: the maximum creep damage state temperature is set as a test temperature, the maximum stress is used to determine a test rotating speed, the test cycle number is determined by backstepping, and the peak value holding time is determined by backstepping. The application realizes the cooperative and accurate design of thermal-mechanical loads, ensures that the test highly simulates actual working conditions, and provides a scientific basis for engine life determination.

The invention discloses an aero-engine service life management method based on digital twinning. The method comprises the following steps that firstly, a twinning reduced-order model of aero-engine parts is constructed based on environment parameter data and operation parameter data of an aero-engine durability test; and then carrying out actual load prediction calculation by using a twin reduced-order model to obtain actual load process data. A creep fatigue damage interaction physical model is constructed based on creep fatigue interaction test data, and a damage interaction life evaluation model is constructed in combination with the load characteristic data and the creep fatigue damage interaction physical model. And then calculating the life consumption and the residual life of the aero-engine part based on the actual load history data of the aero-engine and the damage interaction life evaluation model to obtain part life data. And finally, recognizing and diagnosing a part damage mode by combining the part damage image and the part life data, obtaining a part life management report, and performing life management on the aero-engine.

The invention discloses a probabilistic life prediction method and device for a high-temperature rotating component, and relates to the technical field of life reliability analysis, and the method comprises the steps: building a finite element model of the high-temperature rotating component, and determining at least one group of working condition parameters of the high-temperature rotating component and the cycle index corresponding to each group of working condition parameters; the working condition parameters comprise strain amplitude and load holding time; based on a finite element model, according to all the working condition parameters of the high-temperature rotating part and the cycle index corresponding to each group of working condition parameters, adopting a probability life prediction model to obtain the crack initiation reliability of the high-temperature rotating part; the probabilistic life prediction model is a unified constitutive-damage-statistical model which is subjected to parameter calibration in advance according to a constant-amplitude fatigue and creep-fatigue test result; and determining the fatigue and creep-fatigue probability life of the high-temperature rotating part according to the crack initiation reliability. According to the method, the fatigue and creep-fatigue probability life of the high-temperature rotating part under the constant-amplitude and variable-amplitude load can be quickly and accurately predicted.

The invention discloses a creep fatigue life prediction method and device of a test piece, a medium and a product, and relates to the field of creep fatigue life prediction.The method comprises the steps that in a preset working condition range, the input load of the working condition of the test piece is determined through a test design method; performing finite element simulation analysis on the test piece according to the input load of each working condition, determining stress-strain results under different working conditions, and constructing a simulation database; based on the simulation database, respectively constructing a first order reduction model and a second order reduction model; determining a creep damage value and a fatigue damage value by adopting a creep damage model and a fatigue damage model respectively based on the first order reduction model and the second order reduction model according to the load of the real-time working condition of the test piece; and predicting the creep fatigue residual life according to the creep damage value and the fatigue damage value. According to the invention, real-time monitoring of the load condition of the test piece and rapid prediction of stress and strain can be realized.

The application discloses a high-temperature component reliability interval evaluation method and device, equipment, medium and product, relates to the technical field of reliability evaluation, and the method comprises the following steps: performing probability damage evaluation on a high-temperature component to obtain stress and strain probability distribution of a dangerous point of the high-temperature component; a plurality of physical information neural network models are constructed and trained with the creep fatigue test conditions of the high-temperature component as input and test life as output; according to the life prediction results of each physical information neural network model, the life prediction interval and basic trust distribution of each model are constructed; the fusion life prediction interval is obtained by fusing through the Dempster method; and according to the fusion life prediction interval and the stress and strain probability distribution, the reliability interval evaluation result of the life of the high-temperature component is obtained. The application considers the model uncertainty caused by the selected model, has the advantages of high prediction accuracy, strong engineering applicability and good physical explanation.

The invention provides a device and a method for testing the high-temperature performance of a material. The device comprises a columnar expansion body, a first rigid connecting plate, a second rigid connecting plate, a creep fatigue sample and a high-temperature box, a center hole is formed in the columnar expansion body in the axis direction. The first rigid connecting plate is connected to one end of the columnar expansion body; the second rigid connecting plate is connected to the other end of the columnar expansion body; a creep fatigue sample is arranged in the central hole and is in interference fit connection with the first rigid connecting plate and the second rigid connecting plate; the columnar expansion body, the first rigid connecting plate, the second rigid connecting plate and the creep fatigue sample are all arranged in the high-temperature box; the material linear expansion coefficient of the columnar expansion body is larger than that of the creep fatigue sample, and the material linear expansion coefficient of the creep fatigue sample is far larger than that of the first rigid connecting plate and that of the second rigid connecting plate. According to the invention, multi-form loading with matched temperature load and force load can be realized, and the high-temperature performance of the material can be tested.

The application discloses a high-temperature pressure-bearing hydrogen mixed in-situ creep fatigue test system based on digital twinning, which comprises a host and environment system, a digital twinning control platform, a vacuum pump, an argon source, a hydrogen source and a data acquisition system; the host and environment system comprises a host and an environment system, the host comprises a host support and a load applying device, a test piece is borne in the environment system, and the load applying device is used for applying mechanical load to the test piece in the environment system; the environment system comprises a heating device and a test piece containing device, the test piece is placed in the test piece containing device, the high-temperature environment is provided by the heating device, and the test piece containing device is connected with the argon source, the hydrogen source and the vacuum pump; the digital twinning control platform is used for controlling the safe operation and maintenance of the whole high-temperature pressure-bearing hydrogen environment, and the data acquisition system is used for collecting experimental data; the high-temperature pressure-bearing hydrogen mixed in-situ creep fatigue test system based on digital twinning can realize in-situ creep fatigue performance test of a material under a high-temperature hydrogen mixed environment.

The invention belongs to the technical field of high-temperature alloy connection, and provides a 650 DEG C supercritical diffuser nickel base alloy welding structure and a preparation method thereof. According to the method, an amorphous nickel-chromium-iron-silicon-boron alloy interlayer foil (the thickness is 20-60 microns, and the amorphous nickel-chromium-iron-silicon-boron alloy interlayer foil comprises 5-25 wt% of Cr, 0-30 wt% of Fe, 1-8 wt% of Si, 0.5-4 wt% of B and 45-75 wt% of Ni) is placed on a butt joint interface of two nickel-based alloy components, and a welding joint area is formed through instantaneous liquid phase diffusion welding (the temperature is 1000-1150 DEG C, the pressure is 2-20 MPa, and heat preservation is conducted for 1-10 h). The ultra-low leakage airtight sealing performance that the equivalent welding layer thickness is 0.05-0.50 mm and the leakage rate reaches 1 * 10 <-1 > * 10 Pa.m / s is realized; the problems that according to a traditional welding method, the requirements for high-temperature strength, creep fatigue reliability and ultralow leakage rate airtight under the 650 DEG C supercritical working condition are difficult to meet at the same time, the contradiction between a manufacturing end low-temperature short-time wide process window and the service end long-term structure interface stability is caused, and interface wetting filling and brittle phase control are difficult to collaboratively optimize are solved.

The embodiment of the invention provides a battery packaging life prediction method and device, electronic equipment and a storage medium, and is applied to the technical field of batteries. The method comprises the following steps: responding to a prediction request of the battery packaging life; according to the respiratory fatigue experiment data and the creep fatigue experiment data, establishing a recession model of the to-be-tested battery; inputting the target working condition into a recession model to obtain a recession curve, and inputting the target working condition into an internal air pressure model to obtain an internal air pressure change curve; and determining the packaging life of the to-be-tested battery according to the intersection point of the recession curve and the internal air pressure change curve. According to the scheme, the packaging reliability of the battery is influenced by the respiratory fatigue and the creep fatigue, the decline model is established by combining the influence of the respiratory fatigue and the creep fatigue, and the packaging life is determined according to the target working condition, so that the packaging reliability of the battery can be predicted according to the actual use scene of the battery; therefore, the prediction accuracy of the packaging effect is improved in the early stage of battery development.