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Macro-phenomenological high-strain-rate elastic fracture model for ice-impact simulations

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Chinese Journal of Aeronautics 2023年第3期36卷 146-160页

作者： Jiang FAN Qinghao YUAN fulei jing Guangchen BAI Xiuli SHEN School of Energy and Power Engineering Beihang UniversityBeijing 100191China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100191China Collaborative Innovation Center of Advanced Aero-Engine Beijing 100191China Aero-Engine Academy of China Aero Engine(Group)Corporation of ChinaBeijing 101304China

The ice impact can cause a severe damage to an aircraft’s exposed structure,thus,requiring its *** numerical simulation represents an effective method to overcome this *** establishment of the ice material model is ***,ice is not a common structural material and exhibits an extremely complex material *** material models of ice reported so far are not able to accurately simulate the ice behavior at high strain *** study proposes a novel high-precision macro-phenomenological elastic fracture model based on the brittle behavior of ice at high strain *** developed model has been compared with five reported models by using the smoothed particle hydrodynamics method so as to simulate the ice-impact process with respect to the impact speeds and ice *** important metrics and phenomena(impact force history,deformation and fragmentation of the ice projectile and deflection of the target)were compared with the experimental data reported in the *** findings obtained from the developed model are observed to be most consistent with the experimental data,which demonstrates that the model represents the basic physics and phenomena governing the ice impact at high strain *** developed model includes a relatively fewer number of material ***,the used parameters have a clear physical meaning and can be directly obtained through ***,no adjustment of any material parameter is needed,and the consumption duration is also *** advantages indicate that the developed model is suitable for simulating the iceimpact process and can be applied for the anti-ice impact design in aviation.

关键词： Crack propagation Elastic fracture High strain rate Ice impact Impact force Material model

Review of Numerical Simulation of TGO Growth in Thermal Barrier Coatings

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Computer Modeling in Engineering & Sciences 2022年第8期132卷 361-391页

作者： Quan Wen fulei jing Changxian Zhang Shibai Tang Junjie Yang Aero Engine Academy of China Aero Engine(Group)Corporation of ChinaBeijing101304China Institute for Aero Engine Tsinghua UniversityBeijing100084China

Thermally grown oxide(TGO)is a critical factor for the service life of thermal barrier coatings(TBC).Numerical simulations of the growth process of TGO have become an effective means of comprehensively understanding the progressive damage of the TBC *** present,technologies of numerical simulation to TGO growth include two categories:coupled chemical-mechanical methods and mechanical equivalent *** former is based on the diffusion analysis of oxidizing elements,which can describe the influence of bond coat(BC)consumption and phase transformation in the growth process of TGO on the mechanical behavior of each layer of TBC,and has high accuracy for the thickness evolution of TGO,but they cannot describe the lateral growth of TGO and the rumpling phenomenon *** latter focuses on describing the final stress and strain state after the growth of a specific TGO rather than the complete growth processes of *** on the measured TGO thickness growth curve,simulations of thickening and lateral growth can be achieved by directly applying anisotropic volumetric strain to oxidized elements and switching elements properties from the BC to the TGO.

关键词： Thermal grown oxide(TGO) numerical simulation thermal barriers coatings(TBC) finite element method lateral growth

Stress-controlled LCF experiments and ratcheting behaviour simulation of a nickel-based single crystal superalloy with [001] orientation

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Chinese Journal of Aeronautics 2021年第8期34卷 112-121页

作者： Bin ZHANG Rongqiao WANG Dianyin HU Kanghe JIANG Jianxing MAO fulei jing Xinyi HAO School of Energy Power EngineeringBeihang UniversityBeijing 100083China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100083China Research Institute of Aero-Engine Beihang UniversityBeijing 100083China Hunan Aviation Powerplant Research Institute Aero Engine(Group)Corporation of ChinaZhuzhou 412002China Aero Engine Academy of China Aero Engine(Group)Corporation of ChinaBeijing 101304China

Uniaxial ratcheting behaviour and low cycle fatigue(LCF)failure mechanism of nickel-based single crystal superalloy DD6 with[001]orientation are investigated through the stresscontrolled LCF tests with stress ratio *** the deformation behaviour during the wholelifetime from the beginning of the experiment to the fracture of the specimen,as well as the fractographic/metallographic morphology,are compared with the strain-controlled LCF experimental *** the scanning electron microscope(SEM)observations,it is shown that the failure characteristics under stress-controlled LCF loading are similar with those under strain-controlled ***,unlike strain-controlled LCF loading,even under fully reversed cycle loading for stress-controlled LCF,DD6 shows significant ratcheting behaviour due to the tensioncompression *** addition,the LCF lifetimes under stress control are significantly shorter than the LCF lifetimes under strain control,and the culprit might be the detrimental effect of ratcheting strain on LCF *** on these phenomena,an improved crystal plasticity constitutive model on the basis of slip-based Walker constitutive model is developed through modifying the kinematic hardening rule in order to overcome the inaccurate prediction of decelerating stageand stable stage of ratcheting ***,combining the continuum damage mechanics,a damage-coupled crystal plasticity constitutive model is proposed to reflect the damage behaviour of DD6 and the accelerating stage of ratcheting *** simulation results for the stress-controlled LCF deformation behaviour including the whole-lifetime ratcheting behaviour show good agreement with the experimental data.

关键词： Crystal plasticity constitutive model Low cycle fatigue Nickel-based single crystal superalloy Ratcheting behaviour Stress-controlled experiment

Characterization and mechanical modeling of interfacial damage in EB-PVD thermal barrier coatings considering multiple failure factors

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Journal of Materials Science & Technology 2024年第23期190卷 42-55页

作者： Dianyin Hu Zhengzhe Lv Haiyan Liu fulei jing Yan Zhao Shenyu Zhang Hao Du Rongqiao Wang Research Institute of Aero-Engine Beihang UniversityBeijing 100191China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100191China United Research Center of Mid-Small Aero-Engine Beijing 100191China Aero Engine Academy of China Aero Engine(Group)Corporation of ChinaBeijing 101304China School of Energy and Power Engineering Beihang UniversityBeijing 100191China

In this work,heat treatment experiments at 1050 and 1100℃were carried out on single-crystal su-peralloy specimens coated with the electron beam physical vapor deposition(EB-PVD)thermal barrier coating(TBC)***,the evolution of microstructural characteristics and sintering-induced mechanical properties were separately obtained by the field emission scanning electron microscope(FE-SEM)and nanoindenter,providing inputs for damage ***,the critical compressive strain of TBCs at room temperature was acquired using 3D digital image correlation(3D-DIC)technology to characterize the interfacial damage combined with the experimentally observed buckling *** re-sults demonstrate that not only does oxidative damage exist in the TBCs system due to thermally grown oxide(TGO)growth,but additional damage is generated by thermal cycling and sintering behavior,***,a nonlinear cumulative interfacial damage model considering multiple failure factors is developed to predict TBCs’*** error between the measured damage and calculated damage is less than 15%,showing good prediction accuracy.

关键词： Thermal barrier coatings Critical compressive strain Multiple failure factors Damage model

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小孔对DD6单晶热机械疲劳的影响

航空动力学报 2021年第8期36卷 1669-1679页

作者：荆甫雷唐诗白杨俊杰中国航空发动机集团有限公司中国航空发动机研究院北京101304 清华大学航空发动机研究院北京100084

通过开展同相(IP)和反相(OP)循环下DD6单晶带孔试样与光滑试样的机械应变控制热机械疲劳(TMF)试验,研究孔边应力集中与温度-应变相位角对裂纹萌生寿命的影响。结果表明:带孔试样裂纹萌生于孔边最大主应力位置,其寿命比相同名义载荷的光... 详细信息

通过开展同相(IP)和反相(OP)循环下DD6单晶带孔试样与光滑试样的机械应变控制热机械疲劳(TMF)试验,研究孔边应力集中与温度-应变相位角对裂纹萌生寿命的影响。结果表明:带孔试样裂纹萌生于孔边最大主应力位置,其寿命比相同名义载荷的光滑试样低约一个数量级;带孔试样的OP寿命均短于IP,这与光滑试样寿命趋势一致。结合基于滑移系的黏塑性数值模拟,获取不同试验条件下的单晶应力应变分布特征及其演化规律,并构建单晶TMF损伤与宏细观参量的关联。在此基础上,建立一种能够综合考虑应力集中与相位角影响的单晶TMF寿命模型,对光滑试样与带孔试样IP、OP TMF寿命预测结果基本落在试验寿命的2倍分散带内。

关键词：单晶热机械疲劳应力集中同相反相寿命预测

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镍基单晶高温合金热机械疲劳行为与寿命建模

航空动力学报 2021年第5期36卷 897-906页

作者：陈景阳荆甫雷杨俊杰中国航空发动机集团有限公司商用航空发动机有限责任公司上海200241 中国航空发动机集团有限公司商用航空发动机有限责任公司上海市航空发动机数字孪生重点试验室上海200241 中国航空发动机集团有限公司中国航空发动机研究院北京101304 清华大学航空发动机研究院北京100084

通过DD6单晶薄壁管试样机械应变控制热机械疲劳(TMF)试验,获取温度交变、相位角以及载荷控制方式对单晶应力应变响应与疲劳寿命的影响规律。结果表明:温度交变会引起明显的应力不对称性并造成额外损伤,导致TMF寿命明显低于最高循环温度... 详细信息

通过DD6单晶薄壁管试样机械应变控制热机械疲劳(TMF)试验,获取温度交变、相位角以及载荷控制方式对单晶应力应变响应与疲劳寿命的影响规律。结果表明:温度交变会引起明显的应力不对称性并造成额外损伤,导致TMF寿命明显低于最高循环温度的等温疲劳(IF)寿命,并且反相(OP)循环寿命普遍要低于同等载荷的同相(IP)循环,这种寿命变化趋势与应力控制存在明显差异。采用Walker本构模型进行单晶材料在不同TMF循环下的滑移系黏塑性分析,构建单晶TMF损伤与滑移系细观应力应变参量的关联。在此基础上,选取最大Schmid应力、最大滑移剪应变率、滑移剪应变范围、循环Schmid应力比作为损伤参量,建立基于细观参量的TMF寿命模型,其对不同相位、不同载荷控制方式的TMF寿命预测精度均在2倍分散带内。

关键词：单晶高温合金热机械疲劳机械应变控制应力控制寿命预测

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单晶高温疲劳损伤参量的选取与寿命建模

航空学报 2016年第9期37卷 2749-2756页

作者：荆甫雷王荣桥胡殿印蒋康河中航空天发动机研究院有限公司基础与应用研究中心北京101304 北京航空航天大学能源与动力工程学院北京100083

高温疲劳损伤是引起单晶涡轮叶片破坏的主要因素之一。利用不同试验条件下DD6标准试件的低周疲劳和蠕变-疲劳试验结果,结合基于滑移系的黏塑性应力-应变分析,分别研究了晶体取向、应变范围、平均应变以及保载时间等对单晶高温疲劳损伤... 详细信息

高温疲劳损伤是引起单晶涡轮叶片破坏的主要因素之一。利用不同试验条件下DD6标准试件的低周疲劳和蠕变-疲劳试验结果,结合基于滑移系的黏塑性应力-应变分析,分别研究了晶体取向、应变范围、平均应变以及保载时间等对单晶高温疲劳损伤的影响机制。进而采用滑移剪应变最大的滑移系作为临界滑移系,选取临界滑移系上的最大Schmid应力、最大滑移剪应变率、循环Schmid应力比以及滑移剪应变范围等细观参量作为损伤参量,建立了一种新的基于临界平面的循环损伤累积(CDA)模型。结果表明,该模型对于DD6高温疲劳寿命预测精度基本在3倍分散带内。

关键词：镍基单晶高温合金高温疲劳损伤寿命预测临界平面滑移系

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镍基单晶高温合金DD6热机械疲劳试验

航空动力学报 2018年第12期33卷 2965-2971页

作者：荆甫雷蒋康河张斌胡殿印王荣桥中国航空发动机集团有限公司中国航空发动机研究院北京101304 中国航空发动机集团有限公司湖南动力机械研究所湖南株洲412000 北京航空航天大学能源与动力工程学院北京100191

针对单晶气冷涡轮叶片的服役载荷特征,以镍基单晶高温合金DD6为对象,设计开展了薄壁圆管试样热机械疲劳(TMF)试验。结果表明:DD6变形响应呈现出明显的TMF棘轮效应,且与相位角、机械载荷水平等密切相关;在相同载荷条件下,同相(IP)TMF寿... 详细信息

针对单晶气冷涡轮叶片的服役载荷特征,以镍基单晶高温合金DD6为对象,设计开展了薄壁圆管试样热机械疲劳(TMF)试验。结果表明:DD6变形响应呈现出明显的TMF棘轮效应,且与相位角、机械载荷水平等密切相关;在相同载荷条件下,同相(IP)TMF寿命总是明显短于反相(OP)。引入高温保载时间或增大机械载荷均会引起棘轮应变的明显增加,缩短结构寿命。结合断口和纵向切片分析,识别了不同载荷条件下影响单晶寿命的关键损伤因素,其中IP TMF主导损伤机理为蠕变和疲劳,而OP TMF主导损伤机理为氧化和疲劳。

关键词：单晶高温合金热机械疲劳同相反相棘轮效应损伤

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考虑温度影响的干摩擦接触分子动力学研究

北京航空航天大学学报 2023年第11期49卷 3031-3038页

作者：许洪斌樊江倪铭李星星荆甫雷北京航空航天大学能源与动力工程学院北京100191 北京航空航天大学北京市航空发动机结构与强度重点实验室北京100191 北京航空航天大学先进航空发动机协同创新中心北京100191 四川航天系统工程研究所成都610100 中国航空发动机研究院北京101304

基于多尺度方法对干摩擦行为进行预测已成为当前研究热点。对于航空发动机等高温机械系统,温度对干摩擦行为影响至关重要。针对高温影响下微动界面摩擦行为开展分子动力学建模与分析,研究不同温度下微凸体的切向碰撞过程;考虑温度的升... 详细信息

基于多尺度方法对干摩擦行为进行预测已成为当前研究热点。对于航空发动机等高温机械系统,温度对干摩擦行为影响至关重要。针对高温影响下微动界面摩擦行为开展分子动力学建模与分析,研究不同温度下微凸体的切向碰撞过程;考虑温度的升高使摩擦界面微凸体黏着作用增强,提出不同于赫兹接触理论预测的真实面积计算方法;基于所建的分子动力学模型和G-W接触模型,研究不同温度下接触面的摩擦系数,与实验测量的摩擦系数结果吻合,验证所提方法的正确性。对于在高温环境下接触、摩擦及微动等界面力学问题的研究提供了可借鉴的方法,同时为高温旋转机械动力学多尺度方法提供了可参考的解决手段。

关键词：多尺度分子动力学摩擦表面 G-W接触模型航空发动机

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