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The low cycle fatigue test of IF steel was controlled at 0.6%, 0.4%, 0.2%, and 0.1% strain amplitude until the specimens cracking. After 10000 cycles at 0.4% strain amplitude, changed the strain amplitude from 0.4% to 0.2%. We chose the steps of the low cycle fatigue test under reducing amplitude at 1000, 10000, and 20000 cycles. In addition, after 10000 cycles at 0.6% strain amplitude, changed the strain amplitude from 0.6% to 0.2%. We chose the steps of the low cycle fatigue test under reducing amplitude at 3000, 20000 and 100000 cycles. Then we used electron microscope to observe the dislocation structure, and knew the dislocation morphology of evolution process under reducing amplitude. The dislocation structure evolution of IF steel at low strain amplitude (0.1%, 0.2%) during low cycle fatigue developed the loop patches, dislocation walls, and dislocation cells step-by-step by increasing fatigue cycles. However, the dislocation structure evolution would be changed in the low cycle fatigue under reducing amplitude. We could observe that the dislocation cells were broken to the loop patches in different form. Attest to the dislocation morphology was changed under reducing amplitude. After 10000 cycles at 0.4% strain amplitude, change the strain amplitude from 0.4% to 0.2%., we could observe that the dislocation cells were broken to the loop patches and vein structure. And after 100000 cycles under changed loading amplitude from 0.6% to 0.2%, large area of open domains and some loop patches can be observed.

Indiana University-Purdue University Indianapolis (IUPUI) / High-temperature alloys have been extensively used in many applications, such as furnace muffles, fuel nozzles, heat-treating fixtures, and fuel nozzles. Due to such conditions, these materials should have resistance to cyclic loading, oxidation, and high heat. Although there are numerous prior experimental and theoretical studies, there is insufficient understanding of application of the unified viscoplasticity theory to finite element software for fatigue life prediction. Therefore, the goal of this research is to develop a procedure to implement unified viscoplasticity theory in finite element (FE) model to model the complex material deformation pertaining to thermomechanical load and implement an incremental damage lifetime rule to predict the thermomechanical fatigue life of high-temperature alloys. The objectives of the thesis are: 1. Develop a simplified integrated approach to model the fatigue creep deformation under the framework of ‘unified viscoplasticity theory’ 2. Implement a physics - based crack growth damage model into the framework 3. Predict the deformation using the unified viscoplastic material model for ferritic cast iron (Fe-3.2C-4.0Si-0.6Mo) SiMo4.06 4. Predict the isothermal low cycle fatigue (LCF) and LCF-Creep life using the damage model In this work, a unified viscoplastic material model is applied in a FE model with a combination of Chaboche non-linear kinematic hardening, Perzyna rate model, and static recovery model to model rate-dependent plasticity, stress relaxation, and creep-fatigue interaction. Also, an incremental damage rule has been successfully implemented in a FE model. The calibrated viscoplastic model is able to correlate deformations pertaining to isothermal LCF, LCF-Creep, and thermal-mechanical fatigue (TMF) experimental deformations. The life predictions from the FE model have been fairly good at room temperature (20°C), 400°C, and 550°C under Isothermal LCF (0.00001/s and 0.003/s) and LCF-Creep tests. The material calibration techniques proposed for calibrating the model parameters resulted in a fairly good correlation of FE model derived hysteresis loops with experimental hysteresis, pertaining to Isothermal LCF (ranging from 0.00001/s to 0.003/s), Isothermal LCF-Creep tests (withhold time) and TMF responses. In summary, the method and models developed in this work are capable of simulating material deformation dependency on temperature, strain rates, hold time, therefore, they are capable of modeling creep-stress relaxation and fatigue interaction in high-temperature alloy design.

Modern gas turbine component design applies much effort into prediction and avoidance of fatigue. Advances in the prediction of low-cycle fatigue (LCF) cracks will reduce repair and replacement costs of turbine components. These cracks have the potential to cause component failure. Regression modeling of low-cycle fatigue (LCF)test data is typically restricted for use over the range of the test data. It is often difficult to characterize the plastic strain curve fit constants when the plastic strain is a small fraction of the total strain acquired. This is often the case with high strength, moderate ductility Ni-base superalloys. The intent of this project is to identify the optimal technique for extrapolating LCF test results into stress amplitudes approaching the ultimate strength. The proposed method to accomplish this is by finding an appropriate upper and lower bounds for the cyclic stress-strain and strain-life equations. Techniques investigated include: monotonic test data anchor points, strain-compatibility, and temperature independence of the Coffin-Manson relation. A Ni-base superalloy (IN738 LC) data set with fully reversed fatigue tests at several elevated temperatures with minimal plastic strain relative to the total strain range was used to model several options to represent the upper and lower bounds of material behavior. Several high strain LCF tests were performed with stress amplitudes approaching the ultimate strength. An augmented data set was developed by combining the high strain data with the original data set. The effectiveness of the bounding equations is judged by comparing the bounding equation results with the base data set to a linear regression model using the augmented data set.

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It is impossible to improve the quality of the machines, to increase their reliability and lifetime if the working conditions and the properties of the material are not analyzed. We must know the type of the material (hardening, softening or cyclically stabile), what is chosen for the constructions in low cycle loading, because strain and stress change during the exploitation and depend on this type. If we know the type of the material, we can determine the possibility of its application in concrete exploitation conditions. Real working conditions of the most constructions are close to loading with limited strain (hard straining), because elastic and plastic deformation is met in the zones of crack and stress concentration, that are surrounded with elastically deformed material. The low cycle loading curves parameters A, and are used for the computation of elastic plastic strain curves. These parameters are obtained from the soft low cycle loading results in many cases. The other possible ways for the determination of parameters A, and are shown in this work. The most investigated materials had the initial instability in the interval . For more objective evaluation of stress strain curves parameters A, and , all values of width of hysteresis loop up to semicycle were rejected as insignificant in comparison with the rest lifetime in cycles range . The parameter for the evaluation of hardening (softening) intensity was determined, when the values of... [to full text]

Neįmanoma pagerinti mašinų kokybę, padidinti jų patikimumą ir ilgaamžiškumą, jeigu darbo sąlygos ir medžiagų savybės nėra išanalizuotos. Mes privalome žinoti, medžiagos (kietėjimą, minkštėjimą arba ciklinį stabilumą), kas yra parinkta statinio mažaciklio apkrovimo tipuose, nes įtampos ir apkrovos kaita priklausys nuo šio tipo. Jei mes žinome apie medžiagos rūšį, mes galime nustatyti jos taikymo naudojimo sąlygos galimybes. / It is impossible to improve the quality of the machines, to increase their reliability and lifetime if the working conditions and the properties of the material are not analyzed. We must know the type of the material (hardening, softening or cyclically stabile), what is chosen for the constructions in low cycle loading, because strain and stress change during the exploitation and depend on this type. If we know the type of the material, we can determine the possibility of its application in concrete exploitation conditions.

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Structural steel components erected in real buildings include a wide range of artifacts. In this case, the word artifact is used to describe both defects and fasteners that create discontinuities in the steel such as notches, nicks, welds, powder actuated fasteners, self-drilling screws, repaired defects, and others. Although artifacts occur in real structures and their presence may affect the ductility of elements subjected to large inelastic strains, there is a dearth of experimental data on the seismic behavior of structural systems with artifacts. For instance, full-scale testing of moment resisting connections is expensive which makes it economically infeasible to experimentally examine the wide range of possible artifact types, artifact locations, and structural configurations. A framework has been developed for evaluating the effect of artifacts on special moment resisting frame (SMRF) plastic hinge regions using relatively economical coupon tests. Cyclic bend tests and monotonic tension tests on flat plate coupons that include artifacts are used to calibrate fracture parameters for different low cycle fatigue models such as the Cyclic Void Growth Model (CVGM), Stress-Weighted Damage Model (SWDM) and Cyclic Damage Plasticity Model (CDPM) which are then used in conjunction with finite element (FE) models to predict fracture initiation in full-scale SMRF connections. The framework is general and can be applied to many types of artifacts and seismic structural systems. Fracture propagation has been studied also using CDPM for full-scale tests using FE finite element software LS-DYNA. Alternatively, recommendations for future work is proposed for developing a new test setup, studying artifacts sensitivity to material thickness, and a method of demonstrating equivalence for the artifacts. / Ph. D.

The largest single cause of failure in fan and compressor components in the cold frontal sections of commercial and military gas turbine engines has been attributed to high cycle fatigue (HCF). Additionally, both high-cycle fatigue (HCF) and lowcycle fatigue (LCF) loadings are widely recognized as unavoidable during operation of these components and because the classic Linear Damage Rule (LDR) neglects to account for the synergistic interaction between these damage contributors, dangerous over predictions of lifetime can result. Combined low-cycle fatigue / high-cycle fatigue (HCF/LCF) loadings were investigated in smooth Ti-6Al-4V. The specimens were subjected to a variable amplitude block loading history comprised of completely-reversed (R = -1) tensioncompression overloads followed by constant-amplitude zero-tension (R = 0) minor cycles. Axial specimens were excised from forgings representative of turbine engine fan blade forgings, and consisted of approximately 60% primary α in a matrix of lamellar α + β. Data are reported for smooth specimens of Ti-6Al-4V subjected to both constant amplitude and variable amplitude loadings. The axial specimens were prepared according to two distinct specimen conditions: low stress ground and longitudinallypolished (LSG+LP) and stress-relieved and chemically milled (SR+CM) conditions. Significantly longer lives were observed for the LSG+LP specimen condition under both constant and variable amplitude loading, due to the presence of a beneficial compressive surface residual stress. The presence of this residual stress was confirmed by x-ray diffraction, and its magnitude was of the order of 180 MPa (~20% of the yield stress). In either specimen condition, no appreciable effect of periodic overloads on the life of subsequent minor cycles was observed. / Master of Science