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Influence Factors for Impact Actions and Transient Trajectories of Fan Blades after Fan Blade Out in Typical 2-Shaft High Bypass Ratio Turbofan engine

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Journal of Thermal Science 2022年第1期31卷 96-110页

作者： XU Xue LI Hongxin FENG Guoquan Shenyang engine Research Institute Aero Engine Corporation of ChinaShenyang 110015China corporation Headquarter Aero Engine Corporation of ChinaBeijing 100097China

To enhance the understanding of design characters, which have prominent influences during the fan blade out event, a simplified geometrical and dynamic analysis method was derived, and a typical 2-shaft high bypass ratio turbofan engine was selected and modeled. Based on analytical deriving and engineering experience learned from the real engine failure case, three determinative impact actions were recognized from the fan blade out process. The transient trajectories of these impact actions were researched in analytical method, and then thickness of acoustic lining, quantity of fan blades and threshold load of structural fuse were analyzed as key design characters. 36 serialized fan blade out transient dynamic simulations were conducted by using the 2-shaft high bypass ratio turbofan engine model within different combinations of the three key design factors. The results from geometrical and dynamic analysis matched mainly well with the results from simulations. Characteristic phenomenon in simulation can be explained theoretically. Five conclusions can be summarized from these results. (1) If thickness fan acoustic lining was thinner, the deviation between simplified analytical calculation and simulation were not outstanding to predict Blade-Casing the first impact time and angular position. (2) An appropriate thickness of acoustic lining could make a lower impact stress of fan casing at the first impact. (3) Different thickness of acoustic linings leaded to two impact modes for blade 2, which were tip impact and root impact. (4) Different impact conditions between blade 1 and blade 2 caused remarkable speed components distinction of blade 1, and leaded to a wide range of transient trajectory of blade 1 during FBO event. (5) Thicker acoustic lining in this research can usually find the porper threshold loads setting, which can give a satisfactory outbound vibration. Two details were raised for further research, which were impact behavior of composite material fan bl

关键词： fan blade out transient trajectory design character structural fuse high bypass ratio turbofan

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Development of secondary flow field under rotating condition in a straight channel with square cross-section

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Chinese Journal of aeronautics 2018年第8期31卷 1703-1715页

作者： Ruquan YOU Kuan WEI Zhi TAO Haiwang LI Guoqiang XU National Key Laboratory of Science and Technology on aero-engines aero-Thermodynamics Beihang University Collaborative Innovation center for Advanced aero-engine Beihang University aero engine Academy of china Aero Engine (Group) Corporation of China

The developing secondary flow fields in the entrance section of a rotating straight channel were experimentally investigated using Particle Image Velocimetry（PIV）. The effects of streamwise position, Reynolds number and rotation number on the development of the secondary flow fields were revealed. The results show that the absolute values of vorticity flux of the trailing side roll cells increase with increasing radius of the measured plane and rotation number. When the absolute value of vorticity flux exceeds a critical value, the merging of the trailing side roll cells appears. Moreover, when the number of the trailing side vortex pairs is even, the absolute values of vorticity flux of the leading side vortices increase along streamwise direction. Otherwise, the absolute values decrease along the streamwise direction. By the circulation analysis, this phenomenon was found to have relationship with the merging of the trailing side roll cells, and further concluded that the secondary flow field in a rotating channel has to be treated as a whole. At last,the increase of the Reynolds number was found to be able to induce the merging position moves upstream.

关键词： Circulation analysis Entrance section Field Programmable GataArray (FPGA) Particle Image Velocimetry(PlV) Rotating channel Secondary flow

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Two-dimensional film cooling over a flat plate in hypersonic flow

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Propulsion and Power Research 2018年第3期7卷 205-217页

作者： Ying Zhou Hong Wu Yulong Li Yi Cai National Key Laboratory of Science and Technology on aero-engine Aero-Thermodynamics&Collaborative Innovation Center for Advanced Aero-EngineSchool of Energy and Power EngineeringBeihang UniversityBeijing 100191China aero engine corporation of china Beijing 100191China

Film cooling,as one efficient active cooling method,will hopefully be used in‘hypersonic vehicles’in the *** hypersonic vehicle's surface is more likely a flat plate than a blunt body,so the cooling characteristics of two-dimensional(2-D)film cooling over a flat plate in hypersonic flow are studied using both theoretical analysis and numerical methods.A cooling efficiency calculation formula under a hypersonic condition is obtained and the numerical results show that it has great predicting *** with the low-speed main-flow condition,several differences exist in the hypersonic main-flow condition.A parameter called the‘generalized turbulent mixing coefficient’is introduced and its approximate value range is given based on numerical results.

关键词： Film cooling Hypersonic vehicle Space technology Numerical simulation Cooling efficiency

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Low-Cycle Fatigue Crack Initiation Behavior of Nickel-Based Single Crystal Superalloy

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稀有金属材料与工程 2024年第9期53卷 2458-2467页

作者： Zhang Jingang Liu Xinling Chen Xing Li Zhen Li Leyu Liu Changkui failure analysis center of aero engine corporation of china AECC Beijing Institute of Aeronautical MaterialsBeijing 100095China Beijing Key Laboratory of aeronautical Materials Testing and Evaluation Beijing 100095China

Low-cycle fatigue crack initiation behavior of nickel-based single crystal superalloy at 530℃ was *** show that the behavior of crack initiation is closely related to the maximum *** the maximum strain is 2.0%,the fatigue crack is originated at the position of persistent slip bands on the surface of specimen,which is located on the{111}slip *** defects are observed at the crack initiation *** the maximum strain is lower than 1.6%,the cracks are initiated at the casting defects on sub-surface or at interior of the *** casting defects are located on the{100}slip plane vertical to the axial *** crack is initiated along the{100}slip plane and then expanded along different{111}slip planes after a short stage of *** the maximum strain decreases,the position of crack initiation gradually changes from the surface to the ***,the secondary cracks extending inward along the fracture surface appear in the crack initiation area,and there is obvious stress concentration near the secondary *** dislocation density is high near the fracture surface in the crack initiation zone,where a lot of dislocations cutting into the γ'phase *** oxide layer of 50‒100 nm is presented on the fracture surface,and Ni,Al,Cr and Co elements are mainly segregated into the oxide layer of the surface.

关键词： crack initiation low-cycle fatigue single crystal superalloy casting defects dislocation density

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High cycle fatigue failure with radial cracks in gears of aero-engines

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Chinese Journal of aeronautics 2020年第10期33卷 2620-2632页

作者： Jie HONG Liming JIANG Xiru XU Yanhong MA School of Energy and Power engineering Beihang UniversityBeijing 100083China Collaborative Innovation center of Advanced aero-engine Beijing 100083China

The gears in aero-engines perform energy and motion transfer between the HighPressure Rotor(HPR)and ***,an occurred fault with radial cracks in the driven gear disk was diagnosed as High Cycle Fatigue(HCF)failure through necessary *** of fault tree and test signals indicated that the fracture was relevant to the swing vibration of the driven gear excited by the unbalance excitation on ***,a corresponding mechanism model was established,in which the gear meshing effect was considered,with lateral and swing vibration *** Governing Equations(GEs)and the Finite Element Model(FEM)were established and ***,the modal shapes,harmonic response,and transient response were analyzed,indicating that the swing vibration of the driven gear could be significantly excited by the unbalance on HPR,which induced the cracks in the driven gear disk to extend ***,influences of factors on the unbalance response were obtained,in which the unbalance response appeared local minimum points and maximum ***,1#and 2#bearing stiffness had rather significant influences on the *** it is efficient to modify them to achieve vibration control.

关键词： Cracks Fault analysis Geared rotors Influences of factors Response Unbalance

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Safety analysis of Flow Parameters in a Rotor-stator Cavity

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Chinese Journal of aeronautics 2012年第6期25卷 831-838页

作者： ZHANG Gong DING Shuiting Airworthiness Technologies Research center Beihang University Beijing 100191 China National Key Laboratory of Science and Technology on aero-engine aero-thermodynamics School of Jet Propulsion Bei hang University Beij ing 100191 China

In order to ensure the safety of engine life limited parts （ELLP） according to airworthiness regulations, a numerical approach integrating one-way fluid structure interaction （FSI） and probabilistic risk assessment （PRA） is developed, by which the variation of flow parameters in a rotor-stator cavity on the safety of gas turbine disks is investigated. The results indicate that the flow parameters affect the probability of fracture of a gas turbine disk since they can change the distribution of stress and temperature of the disk. The failure probability of the disk rises with increasing rotation Reynolds number and Chebyshev number, but descends with increasing inlet Reynolds number. In addition, a sampling based sensitivity analysis with finite difference method is conducted to determine the sensitivities of the safety with respect to the flow parameters. The sensitivity estimates show that the rotation Reynolds number is the dominant variable in safety analysis of a rotor-stator cavity among the flow parameters.

关键词： airworthiness aircraft engines engine life limited parts safety analysis rotor-stator cavity risk assessment

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An experimental method to obtain the hard alpha anomaly distribution for titanium alloy aeroengine disks

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Chinese Journal of aeronautics 2021年第4期34卷 67-82页

作者： Shuiting DING Huimin ZHOU Bochao PAN Haibin JI Xiaojun GUO Guo LI Aircraft/engine Integrated System Safety Beijing Key Laboratory School of Energy and Power EngineeringBeihang UniversityBeijing 100083China Institute of Metal Research Chinese Academy of SciencesShenyang 110004China aero engine corporation of china(AECC) Hunan Aviation Powerplant Research InstituteZhuzhou 412000China

A probability-based damage tolerance methodology has been proposed to improve the recognition of material anomalies, especially hard alpha(TiN) anomalies for aeroengine rotor disks. A key input to this method is hard alpha anomaly distribution, which reflects the occurrence rate and size of anomalies present in the finished part material of titanium rotors. Since anomalies rarely occur naturally, an experimental method is proposed to obtain the anomaly distribution for titanium alloy aeroengine disks to reflect and equivalently replace the manufacturing development in titanium industry. In general, the anomaly distribution information can be divided into two parts: the Probability of Detection(POD) curve and the detected anomaly distribution, which contains the size and frequency data of the detected anomalies. The distribution can be established based on several appropriate assumptions and derivation steps with different confidence levels of POD curves and detected anomaly distributions. In this case, the distribution can be obtained in a relatively short time as a key input to the probability-based damage tolerance methodology. Then the Probability of failure(POF) can be calculated, and the value is found to vary with different confidence levels. On this basis, the conservative estimated POF can be obtained in conjunction with confidence levels.

关键词： aeroengine disk Artificial preparation Hard alpha anomaly distribution Probability of detection(POD) Probability risk assessment

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Spatial transformation of general sampling-aliasing frequency region for rotating-blade parameter identification with emphasis on single-probe blade tip-timing measurement

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Chinese Journal of aeronautics 2023年第3期36卷 220-240页

作者： Jiahui CAO Zhibo YANG Guangrong TENG Shaohua TIAN Guoyong YE Xuefeng CHEN School of Mechanical engineering Xi’an Jiaotong UniversityXi’an 710049China Sichuan Gas Turbine Establishment aero engine corporation of china Mianyang 621000China College of Mechanical and Electrical engineering Zhengzhou University of Light IndustryZhengzhou 450002China

Blade-health monitoring is intensely required for turbomachinery because of the high failure risk of rotating ***-Tip Timing(BTT)is considered as the most promising technique for operational blade-vibration monitoring,which obtains the parameters that characterize the blade condition from recorded ***,its application is hindered by severe undersampling and stringent probe *** inappropriate probe layout can make most of the existing methods invalid or ***,a general conflict arises between the allowed and required layouts because of arrangement *** the sake of economy and safety,parameter identification based on fewer probes has been preferred by *** this work,a spatial-transformation-based method for parameter identification is proposed based on a single-probe BTT *** present the general Sampling-Aliasing Frequency(SAFE)map definition,the traditional time-frequency analysis methods are extended to a time-sampling ***,a SAFE map is projected onto a parameter space using spatial transformation to extract the slope and intercept parameters,which can be physically interpreted as an engine order and a natural frequency using coordinate ***,the effectiveness and robustness of the proposed method are verified by simulations and experiments under uniformly and nonuniformly variable speed conditions.

关键词： Blade-tip timing(BTT) Extended time-frequency analysis Image-feature recognition Parameter extraction Sampling-aliasing frequency map Spatial transformation Vibration analysis

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Containment ability and groove depth design of U type protection ring

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Chinese Journal of aeronautics 2016年第2期29卷 395-402页

作者： Bai Conger Xuan Haijun Huang Xiannian He Zekan Hong weirong High-speed Rotating Machinery Laboratory Institute of Chemical MachineryDepartment of Chemical EngineeringZhejiang UniversityHangzhou 310027China Collaborative Innovation center for Advanced aero-engine Beijing 100083China

High-energy rotor uncontained failure can cause catastrophic damage effects to aircraft systems if not addressed in design. In this paper, numerical simulations of three high-energy rotor disk fragments impacting on U type protection rings are carried out using LS-DYNA. Protection rings with the same mass and different groove depths are designed to study the influence of the groove depth. Simulation results including kinetic energy and impact force variation of single frag- ment are presented. It shows that the groove depth infects both the axial containment ability of the protection ring and the transfer process of energy. The depth of groove ought to be controlled to an appropriate value to meet both the requirement of axial containment and higher safety factor. Ver- ification test on high-speed spin tester has been conducted and shows that protection ring with appropriate U structure can resist the impact of the disk burst fragments. The ring is inflated from a circular to an oval-triangle shape. The corresponding simulation shows good agreement with the test.

关键词： Disk fragments containment High energy rotor Numerical analysis Protection ring Verification test

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Characteristics and mechanisms of turboshaft engine axial compressor casing containment

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Chinese Journal of aeronautics 2021年第1期34卷 171-180页

作者： Zekan HE Xiaojun GUO Haijun XUAN Xiaoming SHAN Xiaojing FAN Chuanyong CHEN Weirong HONG College of Energy engineering Zhejiang UniversityHangzhou 310027China Collaborative Innovation center for Advanced aero-engine Beijing 100083China AECC Hunan Aviation Power plant Research Institute Zhuzhou 410002China

To investigate the containment characteristics and mechanisms of axial compressor blade and casing in turboshaft engine,experimental and simulation research is conducted on Titanium alloy axial compressor blades and stainless steel simulator casings in this *** for four thicknesses(from 0.8 mm to 1.4 mm)of casings are presented on high-speed spin ***,ricochet with and without failure of the casings are obtained in test *** obvious bulges or dishing region are observed,petaling failure occurs in the first bulge or the third deformation *** and elongated dimples are observed at the fracture *** Element(FE)models with calibrated Johnson-Cook material behavior law are built and analyzed by using explicit dynamic software for a better understanding on the containment *** agreement is obtained between the experimental observations and numerical *** evolution of the impact force,energy absorption,temperature increase and the cracks’propagation are *** force peaks occur in the impact *** analysis reveals that penetration condition of ricochet with failure leads to most internal energy of the casing.

关键词： Axial compressor Blade and casing containment Damage characteristic Deformation and failure mechanism

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