检索结果-南通市图书馆

A semi-analytical multi-harmonic balance method on full-3D contact model for dynamic analysis of dry friction systems

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2024年第2期37卷 309-329页

作者： He SUN Dayi ZHANG Yaguang WU Qingyang SHEN dianyin hu Research Institute of Aero-Engine Beihang UniversityBeijing 100191China School of Energy and Power Engineering Beihang UniversityBeijing 100191China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100191China Sino-French Engineering School Beihang UniversityBeijing 100191China AECC Sichuan Gas Turbine Research Establishment Chengdu 610500China

Dry friction damping structures are widely-used in aero-engines to mitigate *** nonlinear nature of friction and the two-dimensional in-plane motion on the contact interface bring challenges to accurately and efficiently predict the forced response of frictionally damped *** state-of-the-art Multi-Harmonic Balance Method(MHBM)on quasi-3D contact model in engineering cannot precisely capture the kinematics on the friction interface although the efficiency is *** full-3D contact model can describe the constitutive relationship of the interface in a more accurate manner;however,the efficiency and convergence are not guaranteed for large-scale *** this paper,a semi-analytical MHBM on full-3D contact model is *** original Trajectory Tracking Method(TTM)for evaluating the contact force is reformulated to make the calculation more concise and the derivation of the Analytical Jacobian Matrix(AJM)*** on the chain rule of derivation,the AJM which is the core to upgrade the performance is *** a shrouded blade finite element model,the accuracy and efficiency of the proposed method are compared with both the MHBM on full-3D contact model with numerical Jacobian matrix and the MHBM on quasi-3D contact model with *** results show that the AJM improves significantly the efficiency of the MHBM on full-3D contact *** time cost of the proposed method is in the same order of magnitude as that of the MHBM on quasi-3D contact *** also confirm that the full-3D contact model is necessary for the dynamic analyses of shrouded *** one uses the quasi-3D model,the estimation relative error of damping can even reach 31.8%in some *** addition,the AJM also brings benefits for stability *** is highly recommended that engineers use the MHBM on full-3D contact model for the dynamic analysis and design of shrouded blades.

关键词： Dry friction damping Multi-harmonic balance method Trajectory tracking method Jacobian matrix Shrouded blade

Creep-fatigue crack growth behavior in GH4169 superalloy

在线全文

学校读者我要写书评

暂无评论

Frontiers of Mechanical Engineering 2019年第3期14卷 369-376页

作者： dianyin hu Xiyuan WANG Jianxing MAO Rongqiao WANG School of Energy and Power Engineering Beihang University Beijing 100191 China Collaborative Innovation Center of Advanced Aero-Engine Beijing 100191 China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100191 China

This study aims to examine the crack growth behavior of turbine disc GH4169 superalloy under creepfatigue loading. Crack growth experiments were performed on compact tension specimens using trapezoidal waveform with dwell time at the maximum load at 650℃. The crack growth rate of GH4169 superalloy significantly increased with dwell time. The grain boundaries oxidize during the dwell process, thereby inducing an intergranular creep-fhtigue fracture mode. In addition, testing data under the same dwell time showed scattering at the crack growth rate. Consequently, a modified model based on the Saxena equation was proposed by introducing a distribution factor for the crack growth rate. Microstructural observation confirmed that the small grain size and high volume fraction of the δ phase led to a fast creep-fatigue crack growth rate at 650℃, thus indicating that two factors, namely, fine grain and presence of the δ phase at the grain boundary, increased the amount of weakened interface at high temperature, in which intergranular cracks may form and propagate.

关键词： crack growth rate creep-fhtigue GH4169 superalloy CT specimen dwell time

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

维普期刊数据库评论

在线全文

维普期刊数据库

学校读者我要写书评

暂无评论

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

A unifying approach in simulating the shot peening process using a 3D random representative volume finite element model

在线全文

学校读者我要写书评

暂无评论

Chinese Journal of Aeronautics 2017年第4期30卷 1592-1602页

作者： dianyin hu Ye GAO Fanchao MENG Jun SONG Yanfei WANG Mengxi REN Rongqiao WANG School of Energy and Power Engineering Beihang University Beijing 100083 China Collaborative Innovation Center of Advanced Aero-Engine Beijing 100083 China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100083 China Mining and Materials Engineering McGill University Montreal QC H3A 0C5 Canada Experimental School of Beihang University Beijing 100083 China School of Automation Science and Electrical Engineering Beihang University Beijing 100083 China

Using a modified 3D random representative volume（RV）finite element model,the effects of model dimensions（impact region and interval between impact and representative regions）,model shapes（rectangular,square,and circular）,and peening-induced thermal softening on resultant critical quantities（residual stress,Almen intensity,coverage,and arc height）after shot peening are systematically examined.A new quantity,i.e.,the interval between impact and representative regions,is introduced and its optimal value is first determined to eliminate any boundary effect on shot peening ***,model dimensions are respectively assessed for all model shapes to reflect the actual shot peening process,based on which shape-independent critical shot peening quantities are ***,it is found that thermal softening of the target material due to shot peening leads to variances of the surface residual stress and arc height,demonstrating the necessity of considering the thermal effect in a constitutive material model of shot *** study clarifies some of the finite element modeling aspects and lays the ground for accurate modeling of the SP process.

关键词： Almen intensity Boundary effect Finite element modeling Residual stress Shot peening

Investigation on experimental load spectrum for high and low cycle combined fatigue test

在线全文

学校读者我要写书评

暂无评论

Propulsion and Power Research 2013年第4期2卷 235-242页

作者： Rongqiao Wang Jiaming Wei dianyin hu Xiuli Shen Jiang Fan School of Energy and Power Engineering Beihang UniversityBeijing 100191China

As the outfield load spectrum is so complicated that it cannot be used directly for test study in *** paper presents a method to determine load spectrum for high and low cycle combined fatigue of turbine mortise at elevated temperature through experimental and numerical *** of all,the low cycle load spectrum with duration time is determined through cumulative damage *** rain flow counting method is applied to obtain main cycles and sub cycles,and then the stress cycle is converted into pulsation cycle(stress ratio=0)based on the S-N curve and the Goodman curve;Secondly,three groups of different amplitudes tests are established to determine the high cycle ***,another three groups of the high-low combined cycle fatigue(HLCCF)tests for turbine mortise of a certain type engine are carried *** results show that the macro and micro failure modes are identical with outfield's,which verifies the accuracy of the conversion method.

关键词： High-low combined cycle fatigue Load spectrum Turbine mortise Rain flow counting method Fracture analysis

维普期刊数据库评论

在线全文

维普期刊数据库

学校读者我要写书评

暂无评论

Ni_3Al基单晶高温合金蠕变本构模型

航空动力学报 2018年第3期33卷 657-662页

作者：王荣桥张斌胡殿印北京航空航天大学能源与动力工程学院北京100191 北京航空航天大学航空发动机结构强度北京市重点实验室北京100191 先进航空发动机协同创新中心北京100191

结合Ni_3Al基单晶高温合金蠕变行为的细观机理,在晶体滑移理论的基础上,建立了描述Ni_3Al基单晶高温合金蠕变行为的本构模型,并通过ANSYS提供的UPFs二次开发平台对所建立的本构模型进行了有限元实现。利用蠕变试验数据,结合遗传算法获... 详细信息

结合Ni_3Al基单晶高温合金蠕变行为的细观机理,在晶体滑移理论的基础上,建立了描述Ni_3Al基单晶高温合金蠕变行为的本构模型,并通过ANSYS提供的UPFs二次开发平台对所建立的本构模型进行了有限元实现。利用蠕变试验数据,结合遗传算法获取了两种Ni_3Al基材料的蠕变本构模型参数。利用所建立的蠕变本构模型对两种Ni_3Al基材料的高温拉伸试件进行了有限元模拟,与试验结果吻合良好。这表明在晶体滑移理论基础上建立的本构模型是合理的,并且能够较好地描述Ni_3Al基单晶高温合金三个阶段的蠕变行为,具有一定的应用价值。

关键词： Ni3Al基单晶蠕变本构模型晶体滑移理论 ANSYS二次开发

基于贝叶斯理论的低循环疲劳寿命模型不确定性量化

在线全文

学校读者我要写书评

暂无评论

航空学报 2017年第9期38卷 244-253页

作者：王荣桥刘飞胡殿印李达北京航空航天大学能源与动力工程学院北京100083 先进航空发动机协同创新中心北京100083 航空发动机结构强度北京市重点实验室北京100083

为量化低循环疲劳寿命模型中的不确定性因素,利用贝叶斯理论,采用经典的模型校准形式确立了寿命模型的不确定性量化形式,并结合正态性检验对误差项进行验证;应用马尔可夫链-蒙特卡罗(MCMC)算法获得了模型参数后验分布的抽样样本,在小子... 详细信息

为量化低循环疲劳寿命模型中的不确定性因素,利用贝叶斯理论,采用经典的模型校准形式确立了寿命模型的不确定性量化形式,并结合正态性检验对误差项进行验证;应用马尔可夫链-蒙特卡罗(MCMC)算法获得了模型参数后验分布的抽样样本,在小子样试验数据条件下确定了低循环疲劳寿命的95%不确定性区间,较好地覆盖了寿命的分散性;对参数样本进行了相关性分析,并将异方差回归概率模型与贝叶斯概率模型进行了比较。最后,利用Morris全局灵敏度分析方法获得了Manson-Coffin模型参数的全局灵敏度指标;同时,验证了在模型参数对先验信息敏感,或者说在先验信息影响极大的情况下,采用无信息先验处理方法的合理性。

关键词：贝叶斯理论不确定性量化低循环疲劳概率模型全局灵敏度

在线全文

学校读者我要写书评

暂无评论

流固耦合在涡轮多学科优化设计中的应用

航空学报 2013年第12期34卷 2777-2784页

作者：贾志刚王荣桥胡殿印中航空天发动机研究院有限公司北京100028 北京航空航天大学能源与动力工程学院北京100191

针对以往的多学科优化设计(MDO)中未能考虑高精度的耦合分析,开展了涉及耦合分析的多学科优化方法研究。以涡轮叶片为研究对象,兼顾优化效率和精度,提出了涉及耦合的涡轮叶片多学科优化策略。该策略以协同优化(CO)策略作为框架,将可变... 详细信息

针对以往的多学科优化设计(MDO)中未能考虑高精度的耦合分析,开展了涉及耦合分析的多学科优化方法研究。以涡轮叶片为研究对象,兼顾优化效率和精度,提出了涉及耦合的涡轮叶片多学科优化策略。该策略以协同优化(CO)策略作为框架,将可变复杂度建模方法(VCM)和3种精度(高、中、低)模型嵌入其中。其中,通过两点式标度函数和周期更新方法提高可变复杂度建模方法管理3种精度模型的能力。3种精度模型包括涡轮叶片的流固耦合分析、单学科分析和响应面近似方程。最终解决了涡轮叶片多学科优化设计精度和效率的难题,得到可行的最优化结果。

关键词：流固耦合分析多学科优化设计可变复杂度建模方法协同优化策略涡轮叶片

GH720Li镍基高温合金蠕变-疲劳试验研究

在线全文

学校读者我要写书评

暂无评论

稀有金属材料与工程 2018年第7期47卷 2185-2191页

作者：胡殿印马琦航高晔王荣桥北京航空航天大学北京100191 先进航空发动机协同创新中心北京100191 航空发动机结构强度北京市重点实验室北京100191

对先进航空发动机涡轮盘的典型材料镍基高温合金GH720Li的蠕变-疲劳特性进行了试验研究。通过对真实涡轮盘上取样的圆棒试验件,开展了650℃不同保持时间下的GH720Li合金蠕变-疲劳试验。结果表明,650℃下保持时间对GH720Li合金的蠕变-疲... 详细信息

对先进航空发动机涡轮盘的典型材料镍基高温合金GH720Li的蠕变-疲劳特性进行了试验研究。通过对真实涡轮盘上取样的圆棒试验件,开展了650℃不同保持时间下的GH720Li合金蠕变-疲劳试验。结果表明,650℃下保持时间对GH720Li合金的蠕变-疲劳特性影响较大,即,在较长的保持时间(>30 min)下,蠕变损伤占主导地位,降低了材料的蠕变-疲劳寿命。SEM断口分析表明:随着保持时间的增加,裂纹形成区由穿晶和沿晶混合断裂向沿晶断裂转化;裂纹扩展区由穿晶断裂向穿晶、沿晶的混合模式转化。最后,基于GH720Li合金的蠕变-疲劳试验数据,分别选取载荷谱转换法和机械功密度法进行GH720Li合金的蠕变-疲劳寿命预测,并研究了2种模型的工程适用性。

关键词： GH720Li 蠕变-疲劳保持时间断口分析寿命模型