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Distributed Collaborative Response Surface Method for Mechanical Dynamic Assembly Reliability Design

Chinese Journal of Mechanical Engineering 2013年第6期26卷 1160-1168页

作者： BAI Guangchen fei chengwei School of Energy and Power Engineering Beihang University

Because of the randomness of many impact factors influencing the dynamic assembly relationship of complex machinery, the reliability analysis of dynamic assembly relationship needs to be accomplished considering the randomness from a probabilistic perspective. To improve the accuracy and efficiency of dynamic assembly relationship reliability analysis, the mechanical dynamic assembly reliability（MDAR） theory and a distributed collaborative response surface method（DCRSM） are proposed. The mathematic model of DCRSM is established based on the quadratic response surface function, and verified by the assembly relationship reliability analysis of aeroengine high pressure turbine（HPT） blade-tip radial running clearance（BTRRC）. Through the comparison of the DCRSM, traditional response surface method（RSM） and Monte Carlo Method（MCM）, the results show that the DCRSM is not able to accomplish the computational task which is impossible for the other methods when the number of simulation is more than 100 000 times, but also the computational precision for the DCRSM is basically consistent with the MCM and improved by 0.40-4.63% to the RSM, furthermore, the computational efficiency of DCRSM is up to about 188 times of the MCM and 55 times of the RSM under 10000 times simulations. The DCRSM is demonstrated to be a feasible and effective approach for markedly improving the computational efficiency and accuracy of MDAR analysis. Thus, the proposed research provides the promising theory and method for the MDAR design and optimization, and opens a novel research direction of probabilistic analysis for developing the high-performance and high-reliability of aeroengine.

关键词： machinery dynamic assembly reliability analysis distributed collaborative response surface method,blade-tip radial running clearance

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Dynamic parametric modeling-based model updating strategy of aeroengine casings

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Chinese Journal of Aeronautics 2021年第12期34卷 145-157页

作者： chengwei fei Haotian LIU Shaolin LI Huan LI Liqiang AN Cheng LU Department of Aeronautics and Astronautics Fudan UniversityShanghai 200433China School of Energy and Power Engineering Beihang UniversityBeijing 100083China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100083China Department of Mechanical Engineering North China Electric Power UniversityBaoding 071003China

For accurate Finite Element(FE)modeling for the structural dynamics of aeroengine casings,Parametric Modeling-based Model Updating Strategy(PM-MUS)is proposed based on efficient FE parametric modeling and model updating techniques regarding uncorrelated/correlated mode *** structure is parametrically modeled by simplifying initial structural FE model and equivalently simulating mechanical *** modes between FE model and experiment are reasonably handled by adopting an objective function to recognize correct correlated modes *** parametrized FE model is updated to effectively describe structural dynamic characteristics in respect of testing *** model updating technology is firstly validated by the detailed FE model updating of one fixed–fixed beam structure in light of correlated/uncorrelated mode shapes and measured mode *** PM-MUS is applied to the FE parametrized model updating of an aeroengine stator system(casings)which is constructed by the proposed parametric modeling *** revealed in this study,(A)the updated models by the proposed updating strategy and dynamic test data is accurate,and(B)the uncorrelated modes like close modes can be effectively handled and precisely identify the FE model mode associated the corresponding experimental mode,and(C)parametric modeling can enhance the dynamic modeling updating of complex structure in the accuracy of mode *** efforts of this study provide an efficient dynamic model updating strategy(PM-MUS)for aeroengine casings by parametric modeling and experimental test data regarding uncorrelated modes.

关键词： Aeroengine casings Correlated mode pair Model updating Parametric modeling Structural dynamics Uncorrelated modes

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Fusion Fault Diagnosis Approach to Rolling Bearing with Vibrational and Acoustic Emission Signals

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Computer Modeling in Engineering & Sciences 2021年第11期129卷 1013-1027页

作者： Junyu Chen Yunwen Feng Cheng Lu chengwei fei School of Aeronautics Northwestern Polytechnical UniversityXi’an710072China Department of Aeronautics and Astronautics Fudan UniversityShanghai200433China

As the key component in aeroengine rotor systems,the health status of rolling bearings directly influences the reliability and safety of aeroengine rotor *** order to monitor rolling bearing conditions,a fusion fault diagnosis method,namely empirical mode decomposition(EMD)-Mahalanobis distance(E2MD)and improved wavelet threshold(IWT)(E2MD-IWT)for vibrational signals and acoustic emission(AE)signals is developed to improve the diagnostic accuracy of rolling *** IWT method is proposed with a hard wavelet threshold and a soft wavelet ***,it is shown to be effective through numerical *** is utilized to process the original AE signals for rolling bearings so as to generate a set of components called intrinsic modes functions(IMFs).The Mahalanobis distance(MD)approach is introduced in order to determine the smallest MD between the original AE signal and IMF ***,the IWT approach is employed to select the IMF components with the largest *** is demonstrated that the proposed E2MD-IWT method for vibrational and AE signals can improve rolling bearing fault diagnosis,beyond its ability to effectively eliminate noise *** study offers a promising approach to fault diagnosis for rolling bearings in aeroengines with regard to vibration signals and AE signals.

关键词： Empirical mode decomposition mahalanobis distance improved wavelet threshold rolling bearings

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Advanced multiple response surface method of sensitivity analysis for turbine blisk reliability with multi-physics coupling

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Chinese Journal of Aeronautics 2016年第4期29卷 962-971页

作者： Zhang Chunyi Song Lukai fei chengwei Lu Cheng Xie Yongmei School of Mechanical and Power Engineering Harbin University of Science and Technology School of Energy and Power Engineering Beihang University Department of Mechanical Engineering The Hong Kong Polytechnic University

To reasonably implement the reliability analysis and describe the significance of influencing parameters for the multi-failure modes of turbine blisk, advanced multiple response surface method (AMRSM) was proposed for multi-failure mode sensitivity analysis for reliability. The mathematical model of AMRSM was established and the basic principle of multi-failure mode sensitivity analysis for reliability with AMRSM was given. The important parameters of turbine blisk failures are obtained by the multi-failure mode sensitivity analysis of turbine blisk. Through the reliability sensitivity analyses of multiple failure modes (deformation, stress and strain) with the proposed method considering fluid-thermal-solid interaction, it is shown that the comprehensive reliability of turbine blisk is 0.9931 when the allowable deformation, stress and strain are 3.7 x 10(-3) m, 1.0023 x 10(9) Pa and 1.05 x 10(-2) m/m, respectively; the main impact factors of turbine blisk failure are gas velocity, gas temperature and rotational speed. As demonstrated in the comparison of methods (Monte Carlo (MC) method, traditional response surface method (RSM), multiple response surface method (MRSM) and AMRSM), the proposed AMRSM improves computational efficiency with acceptable computational accuracy. The efforts of this study provide the AMRSM with high precision and efficiency for multi-failure mode reliability analysis, and offer a useful insight for the reliability optimization design of multi-failure mode structure. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license.

关键词： Advanced multiple response surface method Artificial neural network Intelligent algorithm Multi-failure mode Reliability analysis Turbine blisk

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Whole-process design and experimental validation of landing gear lower drag stay with global/local linked driven optimization strategy

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Chinese Journal of Aeronautics 2021年第2期34卷 318-328页

作者： chengwei fei Haotian LIU Zhengzheng ZHU Liqiang AN Shaolin LI Cheng LU Department of Aeronautics and Astronautics Fudcm UniversityShanghai 200433China School of Aeronautics Northwestern Polytechnical UniversityXi'an 710072Xi'anChina Department of Mechanical Engineering North China Electric Power UniversityBaoding 071003China School of Energy and Power Engineering Beihang UniversityBeijing 100083China Beijing Key Laboratory of Aero-Engine Structure and Strength Beijing 100083China

Landing gear lower drag stay is a key component which connects fuselage and landing gear and directly effects the safety and performance of aircraft takeoff and landing. To effectively design the lower drag stay and reduce the weight of landing gear, Global/local Linked Driven Optimization Strategy(GLDOS) was developed to conduct the overall process design of lower drag stay in respect of optimization thought. The whole-process optimization involves two stages of structural conceptual design and detailed design. In the structural conceptual design, the landing gear lower drag stay was globally topologically optimized by adopting multiple starting points algorithm. In the detailed design, the local size and shape of landing gear lower drag stay were globally optimized by the gradient optimization strategy. The GLDOS method adopts different optimization strategies for different optimization stages to acquire the optimum design effect. Through the experimental validation, the weight of the optimized lower dray stay with the developed GLDOS is reduced by 16.79% while keeping enough strength and stiffness, which satisfies the requirements of engineering design under the typical loading conditions. The proposed GLDOS is validated to be accurate and efficient in optimization scheme and design cycles. The efforts of this paper provide a whole-process optimization approach regarding different optimization technologies in different design phases, which is significant in reducing structural weight and enhance design tp wid 1 precision for complex structures in aircrafts.

关键词： Global/local linked driven optimization Landing gear Lower drag stay Optimization Whole-process design

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Hierarchical model updating strategy of complex assembled structures with uncorrelated dynamic modes

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Chinese Journal of Aeronautics 2022年第3期35卷 281-296页

作者： chengwei fei Haotian LIU Rhea PATRICIA LIEM Yatsze CHOY Lei HAN Department of Aeronautics and Astronautics Fudan UniversityShanghai 200433China Department of Mechanical and Aerospace Engineering Hong Kong University of Science and TechnologyHong Kong 999077China Department of Mechanical Engineering Hong Kong Polytechnic UniversityHong Kong 999077China

In structural simulation and design,an accurate computational model directly determines the effectiveness of performance *** establish a high-fidelity dynamic model of a complex assembled structure,a Hierarchical Model Updating Strategy(HMUS)is developed for Finite Element(FE)model updating with regard to uncorrelated *** principle of HMUS is first elaborated by integrating hierarchical modeling concept,model updating technology with proper uncorrelated mode treatment,and parametric *** the developed strategy,the correct correlated mode pairs amongst the uncorrelated modes are identified by an error minimization *** proposed updating technique is validated by the dynamic FE model updating of a simple fixed–fixed *** proposed HMUS is then applied to the FE model updating of an aeroengine stator system(casings)to demonstrate its *** studies reveal that(A)parametric modeling technique is able to build an efficient equivalent model by simplifying complex structure in geometry while ensuring the consistency of mechanical characteristics;(B)the developed model updating technique efficiently processes the uncorrelated modes and precisely identifies correct Correlated Mode Pairs(CMPs)between FE model and experiment;(C)the proposed HMUS is accurate and efficient in the FE model updating of complex assembled structures such as aeroengine casings with large-scale model,complex geometry,high-nonlinearity and numerous parameters;(D)it is appropriate to update a complex structural FE model *** efforts of this study provide an efficient updating strategy for the dynamic model updating of complex assembled structures with experimental test data,which is promising to promote the precision and feasibility of simulation-based design optimization and performance evaluation of complex structures.

关键词： Aeroengine casings Assembled structures Correlated mode pair Hierarchical model updating Objective function Uncorrelated modes

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Novel Kriging-Based Decomposed-Coordinated Approach for Estimating the Clearance Reliability of Assembled Structures

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Computer Modeling in Engineering & Sciences 2021年第11期129卷 1029-1049页

作者： Da Teng Yunwen Feng Cheng Lu chengwei fei Jiaqi Liu Xiaofeng Xue School of Aeronautics Northwestern Polytechnical UniversityXi’an710072China Department of Aeronautics and Astronautics Fudan UniversityShanghai200433China

Turbine blisks are assembled using blades,disks and *** can endure complex loads at a high temperature,high pressure and high *** safe operation of assembled structures depends on the reliability of each *** Carlo(MC)simulation is commonly used to analyze structural reliability,but this method needs to run thousands of *** order to assess the clearance reliability of assembled structures in an efficient and precise manner,the novel Kriging-based decomposed-coordinated(DC)(DCNK)approach is proposed by integrating the DC strategy,the Kriging model and the importance sampling-based Markov chain(MCIS)*** this method,the DC strategy is used to decompose a multi-objective problem into many single-objective *** relationships between these many single-objectives and the overall objective are then *** Kriging model is applied to establish the limit state functions of the single-objectives and multi-objective problems,while the MCIS method is used to assess the structural assembled clearance ***,a highly nonlinear complex compound function is first utilized to verify the DCNK model from a mathematical ***,the reliability of an aeroengine high-pressure turbine(HPT)blade-tip radial running clearance(BTRRC)is analyzed to validate the DCNK approach by considering thermo-structural *** analytical results show that the reliability is 0.9976 when the allowance value of the BTTRC is 1.7650×10^(−3)*** with different methodologies(including direct simulation,the classical Kriging model,and the weighted response surface method(WRSM)),the proposed method holds obvious advantages in computing time and precision,as well as simulation efficiency and *** efforts of this paper provide a useful approach to analyzing assembled clearance reliability and contribute to the development of structural reliability theory.

关键词： Kriging-based decomposed-coordinated approach assembled clearance reliability assessment importance

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基于DCRSM的HPT叶尖径向运行间隙可靠性分析

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航空学报 2013年第9期34卷 2141-2149页

作者：费成巍白广忱北京航空航天大学能源与动力工程学院北京100191

为了有效地进行航空发动机高压涡轮(HPT)叶尖径向运行间隙(BTRRC)设计,从概率的角度进行BTRRC的可靠性分析。根据BTRRC的结构特点,提出了高精度、高效率可靠性分析的分布式协同响应面法(DCRSM),以二次响应面函数为基础建立了DCRSM数学模... 详细信息

为了有效地进行航空发动机高压涡轮(HPT)叶尖径向运行间隙(BTRRC)设计,从概率的角度进行BTRRC的可靠性分析。根据BTRRC的结构特点,提出了高精度、高效率可靠性分析的分布式协同响应面法(DCRSM),以二次响应面函数为基础建立了DCRSM数学模型,并将DCRSM应用到航空发动机HPT BTRRC的可靠性分析中加以验证。结果显示:当稳态叶尖间隙δ=1.86mm时,BTRRC的可靠度为0.996 8,综合考虑发动机效率和可靠性,基本上满足BTRRC的设计和工程需要。通过方法比较显示了DCRSM在BTRRC可靠性分析中,不但能解决难以分析的问题,还能在保证计算精度的前提下提高计算速度和计算效率;充分验证了DCRSM在BTRRC可靠性分析中的有效性和可行性,为复杂机械可靠性分析和优化提供了有效依据。

关键词：航空发动机高压涡轮叶尖径向运行间隙多对象多学科可靠性分布式协同响应面法

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基于DRHOSVM的复杂结构瞬态可靠性分析

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机床与液压 2023年第22期51卷 45-52页

作者：殷锐费成巍西安明德理工学院智能制造与控制技术学院陕西西安710124 复旦大学航空航天系上海200433

为提高结构瞬态可靠性分析的效率和精度,基于降维策略和参数优化思想,以支持向量机为建模基础,提出基于降维策略的参数优化支持向量机算法(DRHOSVM)。以航空发动机涡轮叶盘的疲劳寿命数据集为算法验证对象进行瞬态可靠性分析,通过对比... 详细信息

为提高结构瞬态可靠性分析的效率和精度,基于降维策略和参数优化思想,以支持向量机为建模基础,提出基于降维策略的参数优化支持向量机算法(DRHOSVM)。以航空发动机涡轮叶盘的疲劳寿命数据集为算法验证对象进行瞬态可靠性分析,通过对比直接模拟、传统支持向量机、Kriging,以验证其在建模特性和仿真性能方面的有效性和适用性。结果表明:DRHOSVM在高维数据规模下具有良好的算法精度和效率,适用于复杂结构的可靠性分析。

关键词：复杂结构瞬态可靠性分析降维策略参数优化支持向量机

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涡轮盘径向变形非线性动态概率分析

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北京航空航天大学学报 2013年第7期39卷 927-931页

作者：赵合阳白广忱费成巍邢伟震北京航空航天大学能源与动力工程学院中国人民解放军空军93705部队

为了合理设计和控制叶尖间隙,对涡轮盘径向变形进行非线性动态概率分析.考虑材料属性的非线性和载荷的动态性进行轮盘径向变形的确定性分析,得出轮盘变形随时间变化规律,找出了涡轮盘变形最大值.通过轮盘变形的概率分析得到:轮盘径向变... 详细信息

为了合理设计和控制叶尖间隙,对涡轮盘径向变形进行非线性动态概率分析.考虑材料属性的非线性和载荷的动态性进行轮盘径向变形的确定性分析,得出轮盘变形随时间变化规律,找出了涡轮盘变形最大值.通过轮盘变形的概率分析得到:轮盘径向变形的分布特征、不同径向变形设计值δ下的失效数和可靠度、不同可靠度下的各随机参数的极限值,影响涡轮盘径向变形的随机参数的灵敏度.

关键词：径向变形概率分析非线性动态响应面法

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