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Fatigue crack propagation behavior of Ni-based superalloys after overloading at elevated temperatures

Progress in Natural science:materials International 2016年第2期26卷 197-203页

作者： Xinyue Huang Liang Wang Yunming Hu Guangping Guo David Salmon Ying Li Wenxia Zhao National Key Laboratory of Science and Technology on Advanced High Temperature Structural Materials Beijing Institute of Aeronautical Materials MTS Systems Corporation Eden Prairie 3. Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing Institute of Aeronautical Materials

The fatigue crack propagation behavior of three superalloys subjected to a single overloading at elevated temperatures was investigated. The fatigue crack propagation rate FCPR versus stress intensity factor range data da/dN—ΔK were calculated using the two-point secant method. It was found that the crack growth rates of the investigated materials were retarded after overloading with an overload ratio R OL=1.6. The size of the plastic zone in the front of the crack tip and its relation to loading level were discussed. The overload retardation effects are attributed to crack closure. The fatigue damage in the plastic zone can also be a factor to explain the overload retardation.

关键词： High temperature fatigue Fatigue crack propagation rate Overloading Crack closure Superalloys

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Influence of Inclusions on Low Cycle Fatigue Life of PM Superalloy

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IOP Conference Series: materials science and Engineering 2017年第1期269卷

作者： Zhao Kai Liu Xin-ling He Yu-huai AVIC Failure Analysis Center Beijing Institute of Aeronautical Materials Beijing 100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing 100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing 100095 China

In the range of operating the resistance to low cycle fatigue (LCF) of P/M nickel-based superalloy is one of the most important performances. In this paper the fracture features of LCF on P/M nickel-based superalloy were investigated. The study focused on macroscopic and microscopic features of LCF fractures under 650°C, Δ ε=0.82%, R=0.05, 0.33Hz test condition by optical microscope and SEM. The types and morphologies of failure origins were observed. The effect of position and size of inclusions on LCF were researched. A new life prediction model appropriated for this test condition was provided. The result shows that the LCF life and the size of inclusions in this test condition follow the Weibull distribution. The LCF life exponentially decreases with the inclusion size increases.

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The Reliability of the Finite Element Simulation of the Interface Mechanical Effect of Inclusion and Matrix Material in Powder Metallurgy Superalloy

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IOP Conference Series: materials science and Engineering 2017年第1期269卷

作者： Liu Xin-ling Wang Tian-yu Zhao Kai AVIC Failure Analysis Center Beijing Institute of Aeronautical Materials Beijing 100095 China Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing 100095 China Aviation Key Laboratory of Science and Technology on Materials Testing and Evaluation Beijing 100095 China

The inclusion defects in powder metallurgy superalloy have the characteristics of randomness, such as the shape, size, location and composition. It is important to establish effective and reliable finite element model and method to study the influence of the different defects. In this paper, the inclusion/matrix interface model was proposed, and on the basic theory of two-dimensional elastic problems of complex variable function, the analytical formula was derived and the analytical solution was calculated for the condition of circular inclusion in matrix. On the other hand, stress distribution of the interface of inclusion and matrix was simulated by finite element method. The finite element model is proved effective, reliable through comparison analysis between the numerical analysis method and finite element simulation.

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Fractographical investigation on high-cycle fatigue behavior of direct aging GH4169 superalloy

Fractographical investigation on high-cycle fatigue behavior...

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12th IUMRS International Conference on Advanced materials, IUMRS-ICAM 2013

作者： Zhang, Li Wu, Xue Ren Huang, Xin Yue Li, Xu Dong Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Laboratory of Science and Technology on Advanced High Temperature Structure Materials Beijing Institute of Aeronautical Materials Beijing 100095 China

ISBN: (纸本)9783038350897

The present work is aimed at the fatigue crack initiation behavior of the direct aging superalloy GH4169 at 650 °C. Un-notched specimens were tested under high-cycle fatigue loading with the two stress ratios of R = 0.1 and 0.5. Fracture surfaces were examined using field emission scanning electron microscopy (FESEM). Special attention is paid to the crack initiation sites. Two microstructure features in the fatigue crack initiation regions have been observed. One is obviously the feature of the Ti(C,N)-inclusions, and the other is some kinds of facets. The analysis on the facets was carried out by using energy dispersive spectra (EDS). It was found that the elements at the facets are similar to the matrix. However, some inclusions, Nb(C,N), have been found in the subsurface facets in a few specimens. Sometimes, fatigue lives of the specimens for the crack initiating from the inclusions are longer than those of cracks from the facets, depending on the size of inclusions and the depth from sample surface. Crack initiation for most of the specimens occurs at inclusions, and therefore inclusion is a primary source of crack initiation for this alloy. © (2014) Trans Tech Publications, Switzerland.

关键词： Microstructure

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Prediction model for adhesive thickness-dependence of bonding structures for aeronautic lightweight alloy

Prediction model for adhesive thickness-dependence of bondin...

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12th IUMRS International Conference on Advanced materials, IUMRS-ICAM 2013

作者： Xu, Wei Yu, Hui Chen Tao, Chun Hu Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Laboratory of Science and Technology on Advanced High Temperature Structure Materials Beijing Institute of Aeronautical Materials Beijing 100095 China

ISBN: (纸本)9783038350897

In the present research, the influence of the adhesive thickness on the cohesive properties and the overall strength of metallic adhesive bonding structures were investigated with the cohesive zone model to equivalently simulate the adhesive layers with various thicknesses. A theoretical approach was developed to determine the cohesive parameters for the present model when the adhesive thickness varied. And then some numerical examples were given to explore the adhesive thickness-dependence overall strength of the adhesive joints, followed by the comparison with the existing experimental results. Furthermore, the variations of both the cohesive parameters and the overall strength with the various thicknesses were influenced by the ductility of adhesives, which were investigated finally. The results showed that both the cohesive parameters and overall strength of metallic adhesive bonding structures were dependent on the adhesive thickness. Moreover, the variation of overall strength corresponding to brittle adhesive was more remarkable compared to that of ductile adhesive, especially in the comparatively small thickness range. © (2014) Trans Tech Publications, Switzerland.

关键词： Adhesive joints

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FractographicalInvestigation on High-cycle Fatigue Behavior of Direct Aging GH4169 Superalloy

FractographicalInvestigation on High-cycle Fatigue Behavior ...

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国际材联2013国际先进材料大会——主题3:纳米非晶材料、材料加工与基因工程

作者： Li Zhang XuerenWu XinyueHuang XudongLi Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Laboratory of Science and Technology on Advanced High TemperatureStructure Materials Beijing Institute of Aeronautical Materials

The present work is aimed at the fatigue crack initiation behavior of the direct aging superalloy GH4169 at 650℃.Un-notched specimens were tested underhigh-cycle fatigue loading with the two stress ratios of R=0.1 and *** surfaces were examined using field emission scanning electron microscopy(FESEM).Special attention is paid to the crackinitiation *** microstructure features in the fatigue crack initiation regions have been *** is obviously the feature of the Ti(C,N)-inclusions,and the other is some kinds of *** analysis on the facets was carried out by using energy dispersive spectra(EDS).It was found thatthe elements at the facets are similar to the ***,some inclusions,Nb(C,N),have been found in the subsurface facets in a few ***,fatigue lives of the specimens for the crack initiating from the inclusions are longer than those of cracks from the facets,depending on the size of inclusions and the depth from sample *** initiation for most of the specimens occurs at inclusions,and therefore inclusion is aprimary source of crack initiation for this alloy.

关键词： Superalloy,Highcycle fatigue,Fractography,Crack initiation,Inclusions,Microstructure.

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Prediction Model for Adhesive Thickness-dependence of Bonding Structures for Aeronautic Lightweight Alloy

Prediction Model for Adhesive Thickness-dependence of Bondin...

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国际材联2013国际先进材料大会——主题3:纳米非晶材料、材料加工与基因工程

作者： Wei Xu Huichen Yu Chunhu Tao Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Laboratory of Science and Technology on Advanced High Temperature Structure Materials Beijing Institute of Aeronautical Materials

In the present research,the influence of the adhesive thickness on the cohesive properties and the overall strength of metallic adhesive bonding structures were investigated with the cohesive zone model to equivalently simulate the adhesive layers with various thicknesses.A theoretical approach was developed to determine the cohesive parameters for the present model when the adhesive thickness *** then some numerical examples were given to explore the adhesive thickness-dependence overall strength of the adhesive joints,followed by the comparison with the existing experimental ***,the variations of both the cohesive parameters and the overall strength with the various thicknesses were influenced by the ductility of adhesives,which were investigated *** results showed that both the cohesive parameters and overall strength of metallic adhesive bonding structures were dependent on the adhesive ***,the variation of overall strength corresponding to brittle adhesive was more remarkable compared to that of ductile adhesive,especially in the comparatively small thickness range.

关键词： Lightweight alloy,Adhesive bonding interface,Adhesive thickness,Size-dependence

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Influence of temperatures on creep mechanism of a single crystal nickel-based superalloy

Influence of temperatures on creep mechanism of a single cry...

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13th International Conference on Fracture（ICF13）

作者： Huichen Yu Shuang Liang Sugui Tian Ying Li Benjiang Qian Delong Shu Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Beijing Institute of Aeronautical Materials School of Materials Science and Engineering Shenyang University of Technology

By means of calculating stacking fault energy(SFE) of the single crystal nickel-based superalloy at different temperatures,measuring creep properties and analyzing dislocation configuration,an investigation has been made into the influence of the stacking fault energy on the creep mechanism of the alloy at different *** show that there

关键词： Influence of temperatures on creep mechanism of a single crystal nickel-based superalloy

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Fatigue crack propagation behaviour of a nickel based superalloy at elevated temperatures

Fatigue crack propagation behaviour of a nickel based supera...

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12th IUMRS International Conference on Advanced materials(IUMRS-ICAM2013)

作者： L.Wang X.Huang G.Guo Y.Hu L.Zhang AVIC Beijing Institute of Aeronautical Materials Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation Science and Technology on Advanced High Temperature Structural Materials LaboratoryZHONGHANG Testing Innovation Cooperation

The fatigue crack growth behaviour of a nickel based superalloy at elevated temperatures 550,650 and 710°C was studied. The direct current potential drop（DCPD） technique was used to measure the crack length during the test. It was found that the crack growth rates slightly increased with increasing temperatures, but the temperature effect on crack growth rates was less pronounced at higher DK ranges. At the same temperature the crack growth rates increased with increasing load ratios. The oxidation induced crack closure is considered to be a reason of the observed crack growth behaviour in this study.

关键词： Fatigue crack growth Superalloy Elevated temperature Oxidation Crack closure

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LCF behavior and life evaluation of a single crystal nickel base superalloy under different dwell conditions

LCF behavior and life evaluation of a single crystal nickel ...

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28th Congress of the International Council of the aeronautical sciences 2012, ICAS 2012

作者： Yu, Hui Chen Li, Ying Zhang, Shi Chao Wu, Xue Ren Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation National Key Laboratory of Science and Technology on Advanced High Temperature Structural Materials Beijing Institute of Aeronautical Materials Beijing 100095 China

ISBN: (纸本)9781622767540

Low cycle fatigue (LCF) tests were conducted at elevated temperatures of 760°C and 980°C under different dwell conditions on a single crystal nickel base superalloy. The specimens, which have crystallographic orientations near [001], [011] and [111], were tested under total fully reversed axial strain control. The experimental results indicated that the fatigue life-strain amplitude curves were temperature, crystallographic orientation and strain dwell dependent. When strain range was lower than 2% for [001] orientation, the fatigue life was longer at 760°C and shorter at 980°C for the same strain rang. However, when strain range was higher than 2% for [001] orientation, the reverse result was obtained. The longest fatigue life was observed for specimen with [001] orientation, while the shortest one for specimen with [111] orientation mainly due to variations in Young's modulus with orientations. Compared with continuous cycling tests without strain dwell, the ones with tensile, compressive or tensile-compressive strain dwells showed some shorter fatigue lives. The difference of fatigue lives under different strain dwells reflects the fatigue-creep interactions at elevated temperature. The cyclic deformation and life distribution features were analysed and modified Cyclic damage accumulation (CDA) method was proposed to evaluate the fatigue life of the alloy. The prediction agrees well with the experimental results.

关键词： Low-cycle fatigue

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