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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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Experimental Study on Geometry Characteristics of Turbulent Premixed Flames for Natural Gas/Air Mixtures

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Journal of Thermal Science 2025年第1期34卷 268-282页

作者： ZHENG Weilin WANG Qijiao XIAO Huahua CHEN Xiaoxiao XIE Fan ZENG Wen Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System Shenyang Aerospace UniversityShenyang 110136China State Key Laboratory of Fire Science University of science and Technology of ChinaHefei 230027China AVIC Shenyang Aircraft Design and Research Institute Shenyang 110035China

In this study,focusing on the geometry characteristics of spherical expanding flame,the turbulent premixed flames of natural gas/air mixtures were investigated in a fan-stirred turbulent *** effects of initial temperature(T=300-400 K),initial pressure(P=0.1-0.3 MPa),turbulence intensity(u'=1.0-2.7 m/s),oxygen volumetric percentage(φ(O_(2))=15%-21%)and carbon dioxide volumetric percentage(φ(CO_(2))=0-20%)were delved *** flame profile under the Cartesian coordinate system was derived from the schlieren images taken by the high-speed ***,from both macroscopic and microscopic perspectives,the influence of experimental conditions on the flame geometry characteristics was explored through flame front extraction,wavelet decomposition and network *** results demonstrate that for significant flame wrinkling,changes in species concentrations and turbulence intensity have more pronounced effects on the flame wrinkling *** wrinkling of the flame front maintains a certain degree of similarity,as evidenced by the locally concentrated distribution of the angles of the maximum fluctuation *** disturbance energy under large-scale(D6-D8)disturbances exhibits relatively high values with a similar trend,exerting a significant impact on the geometry characteristics of the flame *** peaks of correlation degree are scattered either with the decomposition scale or the development of flame radius,indicating no linear correlation between different detail ***,the probability distribution of node degrees in key wrinkled regions exhibits different trends with that of large-scale wrinkling and disturbance energy,especially with changes in initial *** occurs because the number of key wrinkles varies based on the perturbation's strength or the region's ***,an increase in the fluctuation frequency of the flame's local radius may not necessarily lead to an increase in the number of key folded regions.

关键词： geometry characteristics large-scale wrinkling wavelet decomposition network topology fan-stirred turbulent combustor

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Experimental study on tribological performance between bristles and coating material pairs of brush seal

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

作者： Zhao, Huan Liu, Wei Sun, Dan Feng, Yuzhong Xu, Wenfeng Wen, Shuaifang Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China

The experimental identification model of brush seal friction coefficient based on cylindrical circumferential friction was established，and the tribological performance experimental device of brush seal wire and coating material pairs were designed and built. Two bristles materials，nickel-based bristles GH4169 and cobalt-based bristles GH605，and four coating materials，WC，Zr2O3，Cr2O3 and Al2O3，were designed and processed. The positive pressure，friction force，friction torque，friction coefficient and wear between friction pairs were experimentally studied，and the tribological properties of different bristles and coating materials were comprehensively evaluated. The results show that when the coating is WC，considering the positive pressure，friction force and friction torque of bristles and the coating material pair，the cobalt base bristles is superior to the nickel base bristles，and the friction coefficient of the nickel base bristles and the cobalt base bristles and the coating material pair is approximately the same. When the coating is Zr2O3 and Cr2O3，considering the positive pressure of bristles and the coating material，the cobalt-based bristles is better than the nickel-based bristles. Considering the friction force，friction torque and friction coefficient of bristles and coating material，nickel-based bristles is better than cobalt-based bristles. When the coating is Al2O3，considering the positive pressure，friction and friction torque of bristles and the coating material，the cobalt-based bristles is better than the nickel-based bristles. Considering the friction coefficient of bristles and coating material，nickel base bristles is better than cobalt base bristles. The wear rate of nickel-based bristles is about 6 times that of cobalt-based bristles. Under the precondition of protecting the rotor surface coating，when the rotor surface coating is WC，Zr2O3，Cr2O3，Al2O3，nickel-based bristles is better than cobalt-based bristles. © 2025 Beijing University of Aeronautics an

关键词： Enamels

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Influence of Texture on Hall-Petch Slope in Hot-extruded AZ31 Magnesium Alloys

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Journal of Wuhan University of technology(Materials Science) 2023年第4期38卷 917-923页

作者：王岭 ZHAO Yiquan WANG Yanmeng SUN Chao CHEN Hongmei ZHANG Jing ZHAO Mei LIU Ying WANG Yinong Liaoning Key Laboratory of Chemical Additive Synthesis and Separation Yingkou Institute of TechnologyYingkou115014China CATARC Automotive Test Center(Tianjin)Co. LtdTianjin300399China School of Electrical Engineering Dalian University of TechnologyDalian116024China Provincial Key Lab of Advanced Welding Technology Jiangsu University of Science and TechnologyZhenjiang212003China School of Metallurgy and Materials Engineering Jiangsu University of Science and TechnologyZhangjiagang215600China School of Materials Science and Engineering Dalian University of TechnologyDalian116024China

To study the influence of texture on Hall-Petch slope,the Hall-Petch relationships of two hot-extruded AZ31 alloys(A117 and A189)were determined by the measurement of yield strength at room *** determine the real texture difference,the texture changes were facilitated by the variation of extrusion ratio and demonstrated by the actual grain orientation *** A117 alloys exhibited higher Hall-Petch slope in comparison of A187 in the condition of tension and compression,because A117 alloys had lower volume fraction of grains in the range of basal pole 75°-90°.The Hall-Petch slope differences for both alloys were analyzed and discussed by boundary obstacle against deformation propagation in grains with various *** to the higher volume fraction of grains in the range of basal pole 75°-90°in A189,the effect of hindering dislocation slip or twinning propagation by grains boundary was weaker than of A117.

关键词： Hall-Petch relationship AZ31 texture

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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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Numerical and experimental study on the effect of the stage number on the characteristics of leakage flow and heat transfer in brush seal

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

作者： Lin, Xiyue Sun, Dan Guo, Hailong Li, Yu Yang, Yixiao Zhang, Jinghan Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China Key Laboratory of Turbomachinery Advanced Seal Technology Shenyang Aerospace University Shenyang110136 China Hunan Aviation Powerplant Research Institute Aero Engine Corporation of China Zhuzhou410315 China

For multi-stage brush seal,stage number has a great influence on the characteristics of leakage flow and heat transfer. The theoretical formula,which explains how the stage number affects the characteristics of leakage flow and heat transfer in multi-stage brush seal,was derived. The solution model of multi-stage brush seal was established and the numerical simulation was carried out based on the fluid-solid-thermal coupling calculation method. The leakage and pressure distribution measurement experiment of multi-stage brush seal was designed. The experimental device of leakage and pressure distribution characteristics of multi-stage brush seal was built. The experimental results were compared with the numerical results to verify the accuracy of the numerical simulation. The distribution characteristics of flow field and temperature field between different series brush seals were analyzed and compared. The influences of series on the leakage characteristics,flow characteristics and heat transfer characteristics of brush seal were studied. The results showed that under the same pressure ratio,from one to three stages brush seals,for each additional level,the pressure drop value borne by each stage of brush tows decreased, and the maximum pressure drop of brush tows decreased by 30.0%—36.3%. The maximum velocity of the flow field appeared below the rear baffle of the last stage brush tow,and the maximum velocity of the flow field decreased with the increase of stage number. Under the same pressure ratio,with the increase of stage number,the sealing performance of the brush seal was enhanced. For each additional stage,the leakage was reduced by 15.7%—22.0%. Under the same pressure ratio,the maximum temperature increased with the increase of stage number,and the maximum temperature increased by 3.7%—9.1% for each additional stage. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Electric heating

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Effect of Tip Bifurcation On Aerodynamic Characteristics and Flow Field Structure in Compressor Cascade

SSRN

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SSRN 2024年

作者： Xu, Wenfeng Mi, Hanqin Li, Ao Ren, Guozhe Lu, Wenxin Sun, Dan Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang Key Laboratory of Advanced Sealing Technology for Turbomachinery Shenyang110136 China

In this study, the tip bifurcation of the compressor cascade is proposed, referring to the biological characteristics of bird wing bifurcation. The influence of tip bifurcation with different structural parameters on the aerodynamic performance and flow field structure of compressor cascade at different incidence angles is studied by numerical simulation. The research shows that the tip bifurcation can make the starting position of the corner separation move backward, inhibit the separation along the pitch and blade height direction, and reduce the flow loss of the cascade. The separation control effect of the corner region first increases and then decreases as the bifurcation height increases, and gradually diminishes as the arrangement position approaches the trailing edge. When the tip bifurcation is set at the starting position of the corner separation and its height is equal to 4%H, the flow improvement effect in the passage is the most obvious, and the cascade flow loss is reduced by 14.4%. At the same time, the tip bifurcation cascade has effective positive incidence angle characteristics, but when the incidence angle is less than the minimum loss incidence angle, the tip bifurcation increases the cascade loss. © 2024, The Authors. All rights reserved.

关键词： Numerical models

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Numerical study on leakage flow characteristics of carbon fiber brush seal between counter-rotating shafts

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

作者： Xu, Huanze Sun, Dan Hu, Guangyang Zhang, Jieyi Mu, Wei Wang, Mingzhang Li, Yu Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China Key Laboratory of Turbomachinery Advanced Seal Technology Shenyang Aerospace University Shenyang110136 China Shenyang Engine Research Institute Aero Engine Corporation of China Shenyang110015 China Key Laboratory for Power Transmission of Aero Engine Aero Engine Corporation of China Shenyang110015 China

There are higher requirements for the seal performance and service life of the sealing structure between counter-rotating shafts of the aero-engine. The structure of carbon fiber rotating brush seal between rotating shafts was proposed. Based on the theory of bristles centrifugal effect mechanics and porous media theory, the method of bristles shape variable correction porosity and resistance coefficient was used to establish a solution model for the leakage flow characteristics of carbon fiber rotating brush seal between rotating shafts. The influence of bristle lay angle, bristle diameter and rotating speed on the mechanical deformation characteristics of carbon fiber bristles was analyzed, and the leakage flow characteristics of brush seal between rotating shafts were studied. The results showed that the deformation and rotation angle of the bristle could increase by increasing the speed of the inner rotor, reducing the diameter of the bristle and increasing the bristle lay angle. Considering the centrifugal effect of the bristles, when the inner rotor speed was 3 230 r/min, the deformation of the T650 carbon fiber bristles in the radial direction of the shaft was 16.43% of the deformation of the Haynes25 bristles. When the inner rotor speed was 10 000 r/min, the bristle lay angle increased from 30° to 45°, and the radial deformation of the bristles on the shaft was increased by 104.02%. Under the same working conditions, the fine-diameter bristles sealing effect was better. When the contact gap between the bristles and the outer rotor was 0 mm, the bristle diameter was reduced from 0.07 mm to 0.05 mm, and the leakage was reduced by 12.42%. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Airships

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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.

关键词： Bending forming Friction model Wall thinning

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Experimental Study and Comprehensive Analysis of Leakage Characteristics of the Casing Flange in an Aero-Engine

SSRN

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SSRN 2023年

作者： Ai, Yanting Han, Shiruo Tian, Jing Liu, Yu Yao, Yudong Guan, Jiaoyue Zhang, Yuhang Shenyang Aerospace University Key Lab of Advanced Measurement and Test Technology for Aviation Propulsion System Liaoning Province China Northwestern Polytechnical University School of Power and Energy China

Leakage at the casing flange in aero-engines can reduce the engine performance and endanger the normal operation of the whole aircraft. An experimental system is designed in this paper to investigate the influence of loaded parameters and structural parameters on the sealing characteristics of the casing flange in aero-engines. The system includes an experimental table subsystem, a hydraulic subsystem, an inflation and leakage measurement subsystem and an experimental data acquisition subsystem. The results show that the gas pressure has a greater influence compared to the axial force. When the gas pressure rises from 0.2 MPa to 0.5 MPa, the leakage volume increases from about 9 L/min to about 34 L/min. Among the structural parameters, the number of bolts has the greatest influence, followed by the number of layers, and the surface roughness has the least influence, with the three influencing parameters not being mutually exclusive. The benefits of improving the structural parameters to reduce the leakage volume all increase with the rise of gas pressure. The leakage volume of experiment parts with 48 bolts arranged on the 2-layer casing flange with surface roughness 1.6 and 3.2 are taken as two sets of the contract type data and fitted by the nested Genetic Algorithm. The fitted results indicate that increase of surface roughness from 1.6 to 3.2 will result in an increase of 26 L/min in the leakage volume. The conclusions from the paper can provide guidance suggestions for the sealing design of the aero-engine casing. © 2023, The Authors. All rights reserved.

关键词： Flanges

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