65 results about "Creep fatigue" patented technology

The invention provides a steel service life prediction method, device, equipment and medium based on a neural network algorithm, and the method comprises the steps: obtaining a material parameter and an operation parameter of a pipeline steel to obtain a stress parameter and a test temperature of the steel, taking the stress parameter and the test temperature as input nodes, taking the fracture time as an output node, and calculating the service life of the steel. Constructing a neural network model, training the neural network model to obtain a creep fatigue prediction model, obtaining the fracture time of the pipeline steel based on the creep fatigue prediction model, generating a life prediction curve of the pipeline steel according to the fracture time, and predicting the life of the target pipeline steel through the life prediction curve; according to the method, training can be carried out by utilizing limited experimental data and simulation data through the neural network model, and a high-precision creep fatigue prediction model can be constructed in a short time, so that the residual life of the material is rapidly evaluated, and the working efficiency is greatly improved.

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 method for predicting creep-fatigue interactive damage of a powder disc edge. The method comprises the following steps: S1, constructing a creep constitutive model of the powder disc edge; s2, acquiring load holding time; s3, creep stress analysis and creep fatigue weak position acquisition; s4, creep stress segmentation: establishing a creep stress relaxation model in which the stress sigma is related to the time t, and segmenting the creep stress by taking the logarithmic stress as the step length; s5, performing low-cycle fatigue damage analysis, and acquiring the low-cycle fatigue life and the low-cycle fatigue accumulated damage of the section by adopting a stress-life curve or a strain-life curve; s6, creep-stress fracture damage and total damage are analyzed, and creep-stress fracture accumulated damage and low cycle fatigue and creep-stress fracture total damage under corresponding cycles are obtained; s7, designing and verifying a powder disc edge simulation piece; and S8, verifying and improving a powder disc edge creep-fatigue damage prediction model. According to the method, the creep-fatigue prediction precision of the turbine disc edge is 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 relates to the technical field of power generation, in particular to a power station boiler high-temperature thick-wall component stress monitoring system and method.The system comprises at least one high-temperature strain gauge, at least one high-temperature sensor, at least one high-temperature sensor, at least one high-temperature sensor and at least one high-temperature sensor, the at least one high-temperature strain gauge deforms under the condition that the temperature of the wall surface is greater than a preset temperature; the at least one temperature sensor is used for collecting the actual temperature of the high-temperature thick-wall part of the power station boiler; the at least one strain collector is used for generating a strain value of the at least one high-temperature strain gauge; and the monitoring assembly is used for inquiring the material elasticity modulus of the power station boiler high-temperature thick-wall component by taking the actual temperature as an index, and calculating the stress value of the power station boiler high-temperature thick-wall component by combining the strain value. According to the invention, the high-temperature stress-strain testing technology can be applied to the stress online monitoring of the high-temperature thick-wall part of the thermal power plant boiler, and the safety risk caused by creep-fatigue damage during the operation of the high-temperature thick-wall pipeline can be effectively predicted.

The invention relates to the technical field of buried cracks, in particular to a method, a device, equipment and a medium for evaluating the service life of a dissimilar steel pipeline containing buried cracks, and the method comprises the following steps: calculating service stress; the load ratio and the fracture ratio of the dissimilar steel pipeline are calculated, and whether buried cracks are within an acceptable range or not is judged; if the buried crack is in an acceptable range, predicting the residual life of the creep crack extending to the critical depth; calculating a crack propagation increment under the fatigue load according to a preset fatigue cycle period and an internal pressure fluctuation range; based on the crack propagation increment coupling creep and fatigue propagation amount, determining the propagation amount of the total crack, and determining the creep-fatigue coupling life according to the propagation amount of the total crack; the creep dominant life and the creep-fatigue coupling life are compared to generate a final remaining life for the dissimilar steel pipe. Therefore, the defect that a traditional single-mechanism model is insufficient in response to material mismatch characteristics is overcome, and the problem of crack morphology prediction distortion caused by anisotropy of dissimilar steel materials is solved.

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 invention discloses a cyclic viscoplastic constitutive model with coupled damage, combining viscoplastic flow laws, kinematic hardening, isotropic hardening, and damage variable evolution. Based on continuous damage mechanics, the damage variable is combined with the constitutive model to accurately simulate the cyclic deformation behavior of the entire life cycle, with high-precision life prediction capabilities. The present invention conducts strain-controlled low-cycle fatigue tests and tensile load-holding creep fatigue tests to obtain the test data required to construct the cyclic viscoplastic constitutive model, and uses a genetic algorithm to obtain a set of optimal model parameters, which can predict the cyclic deformation behavior and fatigue failure life under various cyclic loading waveforms, such as different strain amplitudes, different strain frequencies, and different load-holding times. The constitutive model ultimately obtained by the present invention has high accuracy, strong universality, and life prediction capabilities.

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.

According to the method for judging the blasting reason of the high-pressure bypass pipeline, provided by the invention, high-precision positioning of a blasting source and objective analysis of a failure mechanism are realized through a multi-source data fusion technology in combination with crack form quantitative analysis, wall thickness reduction spatial distribution modeling and a dynamic weight distribution model. According to the method, a crack propagation path inversion technology is combined with stress field simulation, a blasting point positioning error is reduced, contribution degree weights of core factors such as wall thickness reduction and material deterioration are dynamically distributed by establishing a spatial correlation analysis model of evaluation parameters, the problem that traditional experience sorting is high in subjectivity is solved, and the method is suitable for large-scale popularization and application. Furthermore, based on a quantitative judgment rule of creep-fatigue competitive failure, the failure mode diagnosis accuracy is improved, and the service life of equipment is prolonged.

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 relates to the field of aero-engine high-pressure turbine blade structure simulation test piece design, and provides a porous thin circular tube test piece for simulating a turbine blade front edge cooling air film hole and a design method of the porous thin circular tube test piece. Wherein the test piece adopts a circular tube form, and double-surface symmetrical regular hexagonal hole group distribution is adopted in a working section; through the size coupling constraint of aperture-working section wall thickness-hole pitch, the local stress concentration coefficient of the hole edge of the test piece is similar to that of the air film hole at the front edge of the blade, so that the local simulation of the structure is realized. By designing the structural characteristic simulation test piece with the structure, the stress state of the hole edges of the multiple rows of exhaust film holes of the turbine blade can be simulated in mechanical property tests such as creep / fatigue tests. According to the invention, the phenomenon of stress redistribution among air film holes after the turbine blade is subjected to creep deformation can be simulated, and a plurality of test data points can be provided by one test based on the porous configuration, so that the test efficiency can be improved, and support can be effectively provided for the establishment of a life model.

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.