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A new path‐independent multiaxial fatigue damage parameter σn*, which is defined as the largest normal stress range between adjacent turning points of the maximum shear stress on the critical plane, is proposed to describe multiaxial fatigue damage. By combining the maximum normal stress σn,max or the largest normal stress range σn* with the maximum shear stress range on the critical plane, two axial equivalent stress modification factors, keqσ and keqσ*, are proposed, which can account for the influence of non‐proportional additional hardening. The sensitivity of the proposed axial equivalent stress modification factors to multiaxial variable amplitude loading sequences is analyzed. Furthermore, two new multiaxial fatigue damage models based on the axial equivalent stress modification factors are proposed to estimate fatigue life. The applicability of the presented methodology was verified by the experimental data of En15R steel and 7050‐T7451 aluminum alloy, and the results showed that the predicted fatigue lifetimes agree well with the experimental data under variable amplitude multiaxial loading. [ABSTRACT FROM AUTHOR]

• AMed Ti-6Al-4V with different sizes via ultrasonic cycling up to very-high-cycle regime. • S - N data showing size effect: large sized specimens with small fatigue life or strength. • A new probabilistic control volume scheme to predict fatigue property of large specimens. • A size sensitivity exponent to quantify size effect on fatigue property of AMed alloys. • A general form of probabilistic control volume model to unify original and new models. The effect of specimen size on the fatigue performance of additively manufactured (AMed) Ti-6Al-4V is investigated in this paper. The fatigue tests of Ti-6Al-4V specimens made by laser powder bed fusion were conducted via ultrasonic axial cycling up to very-high-cycle regime with stress ratio R = –1. The S - N data of five group specimens show an evident size effect, that is, with the increase of specimen size, the fatigue life or fatigue strength decreasing gradually. A new probabilistic control volume scheme is developed to evaluate the fatigue life of large sized specimens by the tested data of small sized specimens. The applicability of the proposed model is validated by the present data and those of our previous investigation. Moreover, a general form of probabilistic control volume model is derived to show the original and present models are the special cases for conventional cast and AMed alloys. [ABSTRACT FROM AUTHOR]

A new calculation approach is suggested to the fatigue life evaluation of notched specimens under multiaxial variable amplitude loading. Within this suggested approach, if the computed uniaxial fatigue damage by the pure torsional loading path is larger than that by the axial tension–compression loading path, a shear strain‐based multiaxial fatigue damage parameter is assigned to calculate multiaxial fatigue damage; otherwise, an axial strain‐based multiaxial fatigue damage parameter is assigned to calculate multiaxial fatigue damage. Furthermore, the presented method employs shear strain‐based and axial strain‐based multiaxial fatigue damage parameters in substitution of equivalent strain amplitude to consider the influence of nonproportional additional hardening. The experimental data of GH4169 superalloy and 7050‐T7451 aluminium alloy notched components are used to illustrate the presented multiaxial fatigue lifetime estimation approach for notched components, and the results reveal that estimations are accurate. [ABSTRACT FROM AUTHOR]

An innovative numerical methodology is presented for fatigue lifetime estimation of notched bodies experiencing multiaxial cyclic loadings. In the presented methodology, an evaluation approach of the local nonproportionality factor F for notched specimens, which defines F as the ratio of the pseudoshear strain range at 45° to the maximum shear plane and the maximum shear strain range, is proposed and discussed deeply. The proposed evaluation method is incorporated into the material cyclic stress‐strain equation for purpose of describing the nonproportional hardening behavior for some material. The comparison between multiaxial elastic‐plastic finite element analysis (FEA) and experimentally measured strains for S460N steel notched specimens shows that the proposed nonproportionality factor estimation method is effective. Subsequently, the notch stresses and strains calculated utilizing multiaxial elastic‐plastic FEA are used as input data to the critical plane‐based fatigue life prediction methodology. The prediction results are satisfactory for the 7050‐T7451 aluminum alloy and GH4169 superalloy notched specimens under multiaxial cyclic loading. [ABSTRACT FROM AUTHOR]

A notch correction method is proposed under multiaxial cyclic loading, in which the real stress increments can be directly obtained by correcting the pseudo stress increments at the notch. Moreover, the proposed method does not inherently restrict the direction and magnitude of real backstress increment in the real stress space. Additionally, on the basis of Kanazawa et al.’s model, the proposed method utilizes pseudo notch strains in replacement of measured strains to take account of the additional hardening due to the non-proportionality of external loadings. Based on the proposed correction method integrated with constitutive equations using Garud’s hardening model, a notch stress-strain estimation methodology is developed to calculate the local elastic-plastic stress-strain responses at the notch area. The presented methodology does not require iteration. The applicability of the presented methodology was verified by the experimental data of TC21 titanium alloy notched tubular specimens in this study and SAE 1070 steel notched shaft specimens from the literature. The results showed that the calculated notch strains correlate well with the measured strains under proportional and non-proportional loadings. [ABSTRACT FROM AUTHOR]

Objective To discuss the pathologic mechanism of subacute subdural hematoma (sASDH). Methods Three typical cases of sASDH were reported, and related literature in Chinese published in the past 15 years was reviewed. Results Intervals from onset of acute subdural hematoma to surgery or symptom deterioration resulting in sASDH were 12.5–15.5 days (mean 14.1 days). Delayed liquefaction of hematoma clots occurred in all 3 reported cases. One patient achieved good curative effect after administration of dexamethasone, and another patient relapsed owing to poor drainage after evacuation of hematoma. Conclusions The conversion of acute subdural hematoma to sASDH is an inflammatory reaction process with very regular in time, and it is speculated that the pathologic mechanism may be a delayed hypersensitivity reaction. Antigen released during the liquefaction process of blood clot, with subdural neomembrane cells as antigen-presenting cells, is presented to the T lymphocytes released from the capillaries in the neomembrane and forms sensitized T lymphocytes. When the subsequent antigen is released from the blood clots with a delayed liquefaction and is exposed to sensitized T lymphocytes, the delayed hypersensitivity process occurs. [ABSTRACT FROM AUTHOR]

Abstract Background Fibrinogen-like protein 2 (FGL2) is an inflammatory procoagulant protein. We discerned the impact of serum FGL2 on trauma severity and 30-day mortality in patients with traumatic brain injury (TBI). Methods A total of 114 severe TBI patients were subjected to assessment of trauma severity using the Glasgow coma scale (GCS). Measurement of the serum concentrations of FGL2 was done. 114 matched control subjects for their age and sex were included for comparison of serum concentration of FGL2. Results The concentration of FGL2 was dramatically increased in the patients as compared with the control subjects. FGL2 concentration was inversely correlated with GCS score among the patients. The non-survivors within 30 days exhibited substantially higher FGL2 concentrations than the alive. FGL2 concentrations discriminated the patients at risk of 30-day death with significantly high area under receiver operating characteristic curve. Serum FGL2 emerged as an independent predictor for mortality and overall survival at 30 days after head trauma. Conclusions Serum FGL2 is a promising biomarker for assessing the severity and prognosis in severe TBI. Highlights • Serum fibrinogen-like protein 2 concentrations are elevated after craniocerebral trauma. • Serum fibrinogen-like protein 2 concentrations are associated with trauma severity. • Serum fibrinogen-like protein 2 concentrations are linked to 30-day mortality. [ABSTRACT FROM AUTHOR]

Based on the isothermal fatigue and creep damage, a life prediction approach under multiaxial thermo-mechanical loading was proposed in this investigation. In the proposed method, the multiaxial thermo-mechanical fatigue damage during one cycle period was divided into the isothermal fatigue damage and the creep damage. In order to evaluate conservatively, the isothermal fatigue damage during one cycle period was calculated by using multiaxial fatigue damage model at the maximum temperature during the whole period, and the creep damage during one cycle period was calculated by accumulating the creep damage of all portions originated from the divided time history for the axial load component and temperature history. The life prediction results by the proposed model showed a good agreement with experimental data for nickel-base alloy GH4169 and cobalt-base Haynes188 under axial-torsional thermo-mechanical loading. [ABSTRACT FROM AUTHOR]

Highlights • A constitutive model was proposed under multiaxial thermo-mechanical cyclic loading. • The proposed model can consider the effect of non-proportional hardening. • The dynamic strain aging can induce a cyclic hardening. • The effect of dynamic strain aging is considered in the proposed model. Abstract A unified viscoplastic constitutive model, which can consider the influences of non-proportional hardening and dynamic strain aging on the responded stress, was proposed under axial-torsional thermo-mechanical cyclic loading. In the proposed model, the rotation factor and the non-proportional hardening coefficient were considered in the kinematic hardening rule. And the dynamic strain aging influence factor was also proposed to further modify the kinematic hardening rule, which can consider the induced dynamic strain aging under special strain rate and temperature conditions. Moreover, the simulation using the proposed model can achieve a better fit with the measured data under isothermal and non-isothermal axial-torsional cyclic loadings. Graphical abstracts Image, graphical abstract [ABSTRACT FROM AUTHOR]

• A mechanism based multiaxial thermo-mechanical fatigue damage model is proposed. • The value of the scatter band of life prediction result is less than ± 2. • The mean relative error between predicted and experimental strain amplitudes is 6.54%. In this paper, a life prediction method based on damage mechanism for titanium alloy TC4 under multiaxial thermo-mechanical fatigue loading is proposed. Temperature and time dependent influence factors are proposed and introduced into the strain amplitude-life curve method to consider the temperature and time dependence of damage, respectively. The increase in fatigue and oxidation damages caused by tensile mean stress and non-proportional additional hardening is expressed by the mean stress in Macaulay brackets and by using a multiaxial damage parameter, respectively. A fast cracking influence factor is proposed to consider the influence of fast cracking of materials caused by the combined action of high temperature, tensile stress and shear stress on damage behavior. The material constants are identified by test data under uniaxial and proportional loadings, and are further used for prediction under non-proportional loading. The failure life results of uniaxial isothermal fatigue tests with and without dwell time, uniaxial and multiaxial thermo-mechanical fatigue tests are used to verify the proposed method. The value of the scatter band of life prediction result is less than ± 2, as well as the maximum and mean relative errors between predicted and experimental strain amplitudes are 18.49% and 6.54%, respectively. [ABSTRACT FROM AUTHOR]