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15th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Beijing 2024

作者： Lin, Zheng Li, Xiyi Tian, Jing Xiao, Yuanhang Wang, Jingdi Guo, Weijun Key Lab of Advanced Measurement and Test Technology for Aviation Propulsion System Liaoning Province Shenyang China

ISBN: (纸本)9798350354010

In the actual operation of aircraft engines, the early fault diagnosis of inter shaft bearings is extremely challenging due to their complex and variable working conditions and the difficulty in collecting sufficient vibration signals in advance. To address this issue, a cross-domain fault diagnosis model for inter shaft bearings based on small samples is proposed. This model first utilizes the Self-Attention Generative Adversarial Network (SAGAN) to augment limited vibration signals, capturing complex temporal patterns and structures through the self-attention mechanism. Secondly, it employs the Domain Adversarial Neural Network (DANN) to extract domain-invariant features through adversarial training. Finally, an intelligent diagnostic network is used to identify the health status of inter shaft bearings with unknown labels under variable working conditions. Experimental results demonstrate that the proposed method can accurately and effectively achieve cross-domain inter shaft bearing fault diagnosis with limited available samples, and performs excellently in cases of imbalanced source domain samples. This provides a new approach for early fault identification in aircraft engines. © 2024 IEEE.

关键词： Generative adversarial networks

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Numerical simulation study of ionization characteristics of argon dielectric barrier discharge

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Chinese Physics B 2023年第12期32卷 441-448页

作者：刘桂铭陈雷赵智博宋鹏 Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System Shenyang Aerospace UniversityShenyang 110136China College of Mechanical and Electrical Engineering Dalian Minzu UniversityDalian 116600China

In order to better analyze the characteristics of particle distribution and its influencing factors in the ionized space during the process of coaxial dielectric barrier discharge,a self-designed two-dimensional axisymmetric structure exciter was used to carry out optical diagnosis,with the electron temperature calculated through Gaussian fitting.A plasma model was applied to conduct research on the discharge process through numerical simulation,with the changes in electron density and electron temperature were analyzed by using different discharge *** research results show that with an increase in discharge voltage,pressure inside the reactor and relative permittivity,the discharge process is *** addition,a rise in current density leads to an increase in the number of charged particles on the surface of the medium during the discharge process,while a rise in discharge intensity causes an increase in the electron *** temperature decreases due to the increased loss of collision energy between *** results were confirmed by comparing experimental data with simulation results.

关键词： dielectric barrier discharge particle distribution properties electron density electron temperature

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Effect of suction leading edge vortex generator on characteristics of compressor cascade

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Hangkong Dongli Xuebao/Journal of Aerospace Power 2025年第5期40卷

作者： Xu, Wenfeng Zou, Shilong Sun, Dan Lu, Wenxin Ren, Guozhe Zhao, Huan Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China

A compressor linear cascade was studied，and vortex generators were arranged near the suction leading edge of the end wall to improve the stator aerodynamic characteristic and control the corner separation. The effects of the vortex generators with different heights，lengths，and pitch positions on the corner separation flow and aerodynamic characteristics were studied by numerical simulation. The results showed that the suction leading edge vortex generator can generate the induced vortex near the end wall of the passage inlet， which inhibited the accumulation of low-energy fluids in the corner region，shifted the separation starting point backward，and narrowed the corner region along the pitch direction，thereby reducing the flow loss. The vortex generator should be arranged at the starting position of the corner separation. The control effect of the corner separation first increased and then decreased with the increase of the height of the vortex generator. With the increase of the chord of the vortex generator，it gradually decreased. As the arrangement position was far away from the suction，it first increased and then decreased. When the vortex generator was arranged at the boundary between the end wall recirculation region and the mainstream region，the chord was equal to 25% of the blade chord，and the height was equal to 2% of the blade height，the flow loss can be reduced by 10.3%. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Airships

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Imbalanced Inter Shaft Bearing Fault Diagnosis Based on SAGAN-DANN

Imbalanced Inter Shaft Bearing Fault Diagnosis Based on SAGA...

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Prognostics and system Health Management Conference (PHM-Qingdao)

作者： Zheng Lin Xiyi Li Jing Tian Yuanhang Xiao Jingdi Wang Weijun Guo Key Lab of Advanced Measurement and Test Technology for Aviation Propulsion System Liaoning Province Shenyang China

ISBN: (数字)9798350354010

ISBN: (纸本)9798350354027

关键词： Fault diagnosis Shafts Vibrations Employee welfare Visualization Atmospheric modeling Neural networks Feature extraction Wavelet analysis Aircraft propulsion

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Static Nonlinear Modeling and Correction of Spring Element in Bolted Structure of Aeroengine 2nd

Static Nonlinear Modeling and Correction of Spring Element i...

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2nd International Conference of Mechanical system Dynamics, ICMSD 2023

作者： Zhao, Diwen Li, Wensheng Cheng, Quanshi Liu, Yan Liu, Sicheng Xu, Yanwei Liu, Yu Key Lab of Advance Measurement and Test Technology for Aviation Propulsion System Shenyang Aerospace University Liaoning Shenyang110136 China Aerospcae Precision Production Co. Ltd. Tianjin300300 China Tianjin Key Laboratory of Fastening Technology Tianjin300300 China

ISBN: (纸本)9789819980475

In this paper, the nonlinear stiffness characteristics of the bolt-connected structure with a rabbet in the case of an aircraft engine are simulated. Firstly, stiffness characteristics of bolted structures are simulated based on contact elements, a nonlinear spring element simplification method is proposed for simulating the nonlinear stiffness characteristics of bolted connection structures. The simulation results are evaluated based on test results, and a new double weighted response surface correction method is proposed, Finally, the double weighted response surface method is used to correct the statics nonlinear model of bolted structure according to the test results. The results indicate that the simplified nonlinear spring element model established in this paper can predict the nonlinear stiffness characteristics of actual bolted connection structures;The double weighted response surface correction method proposed maintains the stiffness error within 3.5% before and after correction, and the feasibility of simplified modeling method and corrected method is verified. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2024.

关键词： Aircraft engines

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A novel method for inter-shaft bearing fault feature extraction based generalized refined composite multiscale quantum entropy 12

A novel method for inter-shaft bearing fault feature extract...

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12th IEEE Global Reliability and Prognostics and Health Management, PHM-Nanjing 2021

作者： Zhang, Yuwei Tian, Jing Zhang, Fengling Ai, Yanting Wang, Zhi Shenyang Aerospace University Liaoning Key Laboratory Of Advanced Measurement And Test Technology For Aviation Propulsion System Shenyang China

ISBN: (纸本)9781665401302

Targeting the difficulty of fault feature extraction of inter-shaft bearings, a novel feature extraction method to solve the problem of coarse-graining is proposed based on Generalized Refined Composite Multiscale Quantum Entropy (GRCMQE) in this paper. Firstly, based on the advantages of the generalized composite theory of computational stability, combined with the quantum information entropy, a feature extraction method of GRCMQE is proposed. Then, GRCMQE is compared with Multiscale Quantum Entropy (MQE) and Generalized Multiscale Quantum Entropy (GMQE) by analyzing simulation data and the analysis results indicate that GRCMQE method has a better consistency and stability, and it can estimate the complexity of time series more comprehensively. Finally, the proposed method is utilized to analyze experimental data of inter-shaft bearing and the analysis results indicate that the proposed approach can extract the fault feature and identity the fault categories effectively. © 2021 IEEE.

关键词： Feature extraction

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Acoustic and Vibration Response and Fatigue Life Analysis of Thin-Walled Connection Structures Under Heat Flow Conditions

SSRN

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SSRN 2024年

作者： Sha, Yundong Zhao, Wenqiang Tang, Xiaoning Zhao, Fengtong Liaoning Province Key Laboratory of Advanced Measurement And Test Technology of Aviation Propulsion Systems Shenyang Aerospace University Shenyang110136 China

Thin-walled connection structures are commonly used in the hot-end components of aerospace vehicles. Large deflection nonlinear responses and fatigue failure occur due to their discontinuous mass distribution and prominent cross-sectional changes under the action of complex thermal, aerodynamic, and noise loads. A thermoacoustic fatigue test was carried out to obtain the acoustic and vibration responses and fatigue life changes of the connection structure under heat flow conditions in engineering applications. The high-temperature acoustic fatigue test system of aviation thin-walled structures was used, taking the high-temperature alloy thin-walled plate-load-bearing frame bolted connection structure as the research object. As a result, the vibration response and fatigue life under different thermoacoustic loads were obtained. The contact finite element method was used to simulate the connection pretightening force, and the coupled finite element/boundary element method was used to calculate the acoustic and vibration response of heat flow conditions. The changing rules of the frequency response peak value at the critical point of the thin-walled connection structure under the effects of different temperature fields, fluid fields, and sound fields were obtained through the processing and analysis of the calculation results. Considering the structural vibration fatigue damage mechanism, this study employed an improved rainflow counting method to compute the rainflow circulation matrix (RFM) and rainflow damage matrix (RFD) of the vibration stress time history at critical points within the structure framework. Said method was combined with Miner's linear cumulative damage theory to estimate the fatigue life under various thermal-fluid-acoustic coupled loads. A comprehensive analysis validates the accuracy of the established numerical simulation calculation model in identifying critical connection points within structures subjected to pre-tightening forces. This model

关键词： Heat transfer

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Influence of damping ring on the aeroelastic stability of labyrinth seal

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Hangkong Dongli Xuebao/Journal of Aerospace Power 2025年第6期40卷

作者： Li, Yu Liu, Haibo Sun, Dan Yang, Zemin Su, Guozheng Xu, Meipeng Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System School of Aero-engine Shenyang Aerospace University Liaoning Province Shenyang110136 China Key Laboratory of Turbomachinery Advanced Seal Technology Shenyang Shenyang Aerospace University Shenyang110136 China Commercial Aircraft Engine Company Limited Aero Engine Corporation of China Shanghai200241 China

Considering the aeroelastic instability problem of the labyrinth seal of aeroengine, a model for solving the damped vibration reduction of labyrinth seal was established. Based on the energy method, the influences of the structure parameters of the damping ring and its installation position on the aeroelastic stability of the labyrinth seal were studied, and the mechanism of the influence of the damping ring on the aeroelastic stability of the labyrinth seal was revealed. The results showed that the aerodynamic damping ratio of the first mode and second mode was −0.41% and −0.049%, respectively, without the damper ring, which resulted in aeroelastic instability. However after installation of the damping ring, the aerodynamic damping ratio of the second mode changed from negative to positive, and aerodynamic damping ratio of the first mode was still negative, but the damping ratio value increased, the damping ring improved the aeroelastic stability of the labyrinth seal. When the installation interference of the damping ring was larger, the opening amount was smaller, moreover, when the aerodynamic damping ratio of the labyrinth seal was larger, the aeroelastic stability was better. When the damping ring was installed at the cantilever end, the aerodynamic damping ratio was the largest, meantime the labyrinth seal was the most stable. When the damping ring was installed at the wave node, the aerodynamic damping ratio and the amplitude reduction ratio were the smallest, and then the labyrinth seal stability was poor. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Damping

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Study on the thinning characteristics of aviation tubes during bending forming under boundary lubrication friction

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Journal of Manufacturing Processes 2025年 149卷 443-455页

作者： Yu Wu Zhineng Wang Jing Tian Renzhen Chen Weiming Lin Yaochen Lin Health Maintenance for Mechanical Equipment Key Lab Hunan University of Science and Technology Xiangtan 411201 China Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System Shenyang Aerospace University Shenyang 110136 China Zhejiang King-Mazon Intelligent Manufacturing Corp. Ltd Lijiang 321400 China

The reduction of wall thickness during the bending forming process of aviation tubes is a common issue, particularly for large-diameter, thick-walled tubes. Under heavy load conditions, the lubrication state deteriorates, leading to a boundary lubrication state that complicates the prediction of wall thickness reduction. Current research on tube bending forming relies on Coulomb friction, which does not accurately reflect real-world conditions. Therefore, we propose a method for analysing tube thinning during bending forming that considers the friction characteristics of boundary lubrication. ABAQUS/VFRIC was employed to develop a dynamic friction model that considers contact pressure. Additionally, material hardness and RMS roughness were incorporated into the finite element simulation. Results show that as the tubing advances, the contact area between the pressure die and the tube changes and the friction between them generates a certain amount of compressive stress. An increase in contact pressure results in a higher friction coefficient, leading to a substantial rise in the tensile stress on the tube's exterior, further aggravating the thinning of the outer wall. In particular, stress concentrations and elevated strains resulting from boundary lubrication friction are especially pronounced at the 40° and 60° bending positions. In addition, increased RMS roughness and decreased material hardness contribute to more significant thinning effects. Experimental verification indicates that this dynamic friction model offers greater accuracy than the traditional Coulomb friction model in predicting wall thickness thinning, achieving a maximum error reduction to 3% and an accuracy enhancement of 7%. The findings provide theoretical support for process optimisation in aerospace manufacturing and establish a foundation for designing and implementing high-precision forming processes.

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Influence Factors of Frictional Heat between Bristles and Rotor for a Multi-Stage Brush Seal

SSRN

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SSRN 2024年

作者： Sun, Dan Yang, Yixiao Zhao, Huan Zhang, Jieyi Yang, Zemin Zhang, Jinghan Key Laboratory of Turbomachinery Advanced Seal Technology Shenyang Shenyang Aerospace University Shenyang110136 China Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System Shenyang Aerospace University Shenyang110136 China Key Laboratory for Power Transmission of Aero Engine Aero Engine Corporation of China Shenyang110115 China

In multi-stage brush seals (MBS), frictional heat generates at frictional surface, which leads to early failure of the seal The frictional heat was accumulated at the downstream stages caused by transfer of the heat from upstream stage to downstream one with flow of the airflow. A three-dimensional tube bundle model of the MBS was established to study change of heat flux on the frictional heat between bristles and rotor among stages. Increasing height of backing plate to rotor could not only balance the pressure drops but also reduce the bristle temperature at downstream stage. decreasing interference amount and decreasing axial width of bristle pack stage by stage, which had a higher impact on bristle temperature at downstage stages. © 2024, The Authors. All rights reserved.

关键词： Heat flux

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