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

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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Research on flow characteristics of bearing chamber sealing system based on oil-gas two-phase flow

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Hangkong Dongli Xuebao/Journal of aerospace Power 2025年第4期40卷

作者： Ren, Guozhe Li, Yanpeng Zhao, Huan Xu, Wenfeng Sun, Dan Yan, Yang Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China

In order to study the oil-gas two-phase flow characteristics and oil sealing and leakage characteristics of aero-engine bearing chamber sealing system， an unsteady solution model of sealing chamber- carbon sealing structure-bearing chamber sealing system and sealing chamber-carbon sealing structure-anti-screw structure-bearing chamber sealing system based on Euler-Euler two-phase flow method was established. The experimental device of oil-gas two-phase flow in bearing chamber was designed and built. The accuracy of the solution method was verified by the experiment of oil sealing characteristics. On this basis， the oil-gas two-phase leakage flow characteristics of conventional bearing chamber sealing system and the bearing chamber sealing system with anti-screw structure under different working conditions were studied. The results showed that for the conventional bearing chamber sealing system， the higher rotational spee indicated， the greater oil leakage. The greater pressure difference also indicated the smaller oil leakage. The anti-screw structure can effectively reduce the oil leakage of the bearing chamber sealing system. When the speed was 15 000 r/min and the pressure difference was 5 kPa， the oil leakage with the anti-screw structure was reduced by more than 95% compared with the bearing chamber sealing system without the anti-screw structure. The clearance of the anti-screw structure had no obvious effect on the sealing and leakage characteristics of the oil. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Airships

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Solving model of friction and wear characteristics of brush seal considering time-varying wear of brush wire

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Hangkong Dongli Xuebao/Journal of aerospace Power 2025年第4期40卷

作者： Lan, Kexin Zhao, Huan Sun, Dan Yang, Zemin Xu, Wenfeng Sun, Jisheng 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

Based on Euler-Bernoulli beam theory and Archard wear theory coupling method， a solution model of brush seal friction and wear characteristics considering time-varying wear of brush wire was proposed. The normal contact force，wear rate and wear loss between the free end of brush wire and the rotor surface were analyzed. The experimental device of brush seal friction and wear characteristics based on cylindrical circumferential friction was designed and built. On the basis of experimental verification of the accuracy of the solution model，the influences of working condition parameters and structural parameters of brush seal on the friction and wear characteristics of brush seal were studied. The results showed that the normal contact force and wear rate between the free end of the brush wire and the rotor surface decreased logarithmically with the increase of the friction time，and finally approached 0. The wear loss increased logarithmically with the increase of friction time，and finally became stable. When the rotation speed was 2 000 r/min and the interference amount was 0.4 mm，the wear of the brush wire mainly occurred in the first 20 h，and the wear of the brush wire became stable at the 50 h. The normal contact force，wear rate and wear amount of the brush wire increased with the increase of the interference amount and the thickness of the brush wire，and the wear amount also increased linearly. With the increase of rotational speed，radial length and diameter of the brush wire and the decrease of the inclination angle of the brush wire，the decrease rate of the normal contact force and wear rate curve of the brush wire was faster，and the time for the brush wire to reach the maximum wear amount was shorter. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Wear of materials

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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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Leakage Flow Characteristics of Novel Two-Stage Brush Seal with Pressure-Equalizing Hole

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Lubricants 2025年第4期13卷 190-190页

作者： Li, Yu Xu, Huanze Zhang, Jinghan Sun, Dan Yang, Zemin Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System Shenyang Aerospace University Shenyang110136 China

Uneven inter-stage pressure drops of the common two-stage brush seal (CBS) lead to a problem that the second stage bristles bear excessive pressure load, and this problem leads to the premature failure of the brush seal. In this paper, a novel two-stage brush seal (NBS) with the backing plate holes of the second stage was proposed, and a three-dimensional numerical model of the NBS was established. Then, the effects of the pressure-equalizing (PE) hole on the inter-stage pressure drop distribution of the NBS were numerically analyzed, and an optimal structure was obtained. Finally, the leakage flow characteristics of this optimal structure were studied. The results showed that the NBS with PE hole increased the passage area of the downstream, and so effectively improved the uneven pressure drops of the CBS, and the pressure drop balance ratio of the NBS was obviously smaller than that of the CBS. For the structural parameters studied in this paper, the pressure drop balance ratio of the NBS was improved by 45.6~67.9% compared to the CBS. Moreover, when PE holes were 0.4 mm in diameter, 5.95 mm in height, and the number of rows was 1, the NBS had the best pressure drop balance and its leakage was only 8.7% higher than that of the CBS. © 2025 by the authors.

关键词： Drops

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Mechanism of influence of eccentricity on aeroelastic stability of labyrinth seal ring

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

作者： Su, Guozheng Sun, Dan Li, Yu Wang, Zhi Wang, Wen Xu, Meipeng Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System School of Aero-Engine Shenyang Aerospace University Shenyang110136 China Commercial Aircraft Engine Company Limited Aero Engine Corporation of China Shanghai200241 China

Aiming at the aeroelastic stability problem of the labyrinth seal ring in the eccentric whirling state of the aeroengine， based on the energy method， rotating coordinate system， three-dimensional interpolation and unsteady dynamic mesh technology were used to establish a solution model for the aeroelastic stability of the labyrinth seal ring，considering the factors of eccentric whirling and modal shape of the labyrinth seal ring. Based on verifying the accuracy of the solution model， the aeroelastic stability of the labyrinth seal ring under the eccentric condition was studied. The influence law of whirling frequency，precession form and mode shape on the aeroelastic stability of labyrinth seal ring was analyzed. The distribution characteristics of the aerodynamic work of labyrinth seal ring in different regions of the tooth cavitys were analyzed，and the influence mechanism of eccentricity on the aeroelastic stability of labyrinth seal ring was revealed. The results show that the aerodynamic damping ratio of labyrinth seal ring with low nodal diameter is more susceptible to eccentric whirling than that of other nodal diameters. The aerodynamic damping ratio of the first nodal diameter gradually decreases with the increase of eccentricity and changes from positive to negative， leading to aerodynamic instability. Compared with the forward precession，the backward precession has larger aerodynamic damping ratio. For the stable state，the aerodynamic damping ratio increases with the increase of the whirling frequency. The aerodynamic work of the labyrinth seal ring presents waveform attenuation and oscillation distribution along the axial direction，and the amplitude of oscillation decays step by step along the direction of the air flow. The aerodynamic work of the low pressure side of the labyrinth seal ring in stable state changes from negative work to positive work. The increase of eccentricity leads to the gradual increase of aerodynamic work in each axial region of the

关键词： Damping

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Integration of vibration and lubricating metal particle information for condition monitoring of aircraft engine main bearings

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

作者： Luan, Xiaochi Bai, Tian Zhao, Junhao Sha, Yundong Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China

To address the challenge of online monitoring and accurate fault diagnosis of the main bearings in aircraft engines using a single detection method， a state monitoring approach based on the fusion of vibration signals and oil debris information is proposed. First， the root mean square value is selected as the time-domain feature parameter，feature energy is defined as the frequency-domain feature parameter，and the number of metal debris particles in the oil is used as the oil debris information. Based on fuzzy inference theory， these parameters are fused by selecting membership functions and defining fuzzy inference rules to perform fusion analysis and fault diagnosis 0of the bearings using vibration signals and oil debris information. The results indicate that after operating for 1 hour， the calculated bearing condition value is 0.18，which falls within the range of 0 to 0.35，signifying that the bearing is in good condition. Midway through its operation at 9 hours，the bearing condition value is 0.5，within the range of 0.35 to 0.65， indicating a suboptimal bearing state. Towards the end of its operation at 18 hours， the calculated bearing condition value is 0.82，within the range of 0.65 to 1，suggesting severe bearing failure. The proposed information fusion method can effectively monitor the operational status of the bearing and can provide an effective means for the condition monitoring of the main bearing in an aircraft engine. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Roller bearings

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Nonlinear response analysis and experimental verification for thin-walled plates to thermal-acoustic loads

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Chinese Journal of Aeronautics 2017年第6期30卷 1919-1930页

作者： Yundong SHA Jian WANG Liaoning Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System Shenyang Aerospace University Shenyang 110136 China

For large deflection strongly nonlinear response problem of thin-walled structure to thermal-acoustic load, thermal-acoustic excitation test and corresponding simulation analysis for clamped metallic thin-walled plate have been implemented. Comparing calculated values with experimental values shows the consistency and verifies the effectiveness of calculation method and model for thin-walled plate subjected to thermal-acoustic load. Then this paper further completes dynamic response calculation for the cross reinforcement plate under different thermalacoustic load combinations. Based on the obtained time-domain displacement response, analyses about structure vibration forms are mainly focused on three typical motions of post-buckled plate,indicating that the relative strength between thermal load and acoustic load determines jump forms of plate. The Probability spectrum Density Functions（PDF） of displacement response were drawn and analyzed by employing statistical analysis method, and it clearly shows that the PDF of postbuckled plate exhibits bimodal phenomena. Then the Power Spectral Density（PSD） functions were used to analyze variations of response frequencies and corresponding peaks with the increase of temperatures, as well as how softening and hardening areas of the plate are determined. In the last section, this paper discusses the change laws of tensile stress and compressive stress in pre/post buckling areas, and gives the reasons for N glyph trend of the stress Root Mean Square（RMS）.

关键词： Buckling Experimental verification Nonlinear response Power spectral density Probability spectrum densitySnap-through Thermal-acoustic load Thin-walled structure

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Experimental study on combustion characteristics of Chinese RP-3 kerosene

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Chinese Journal of Aeronautics 2016年第2期29卷 375-385页

作者： Ma Hongan Xie Maozhao Zeng Wen Chen Baodong School of Energy and Power Engineering Dalian University of Technology Liaoning Key Laboratory of Advanced Test Technology for Aerospace Propulsion System Shenyang Aerospace University

In order to illustrate the combustion characteristics of RP-3 kerosene which is widely used in Chinese aero-engines, the combustion characteristics of RP-3 kerosene were experimentally inves- tigated in a constant volume combustion chamber. The experiments were performed at four different pressures of 0.1 MPa, 0.3 MPa, 0.5 MPa and 0.7 MPa, and three different temperatures of 390 K, 420 K and 450 K, and over the equivalence ratio range of 0.6-1.6. Furthermore, the laminar combus- tion speeds of a surrogate fuel for RP-3 kerosene were simulated under certain conditions. The results show that increasing the initial temperature or decreasing the initial pressure causes an increase in the laminar combustion speed of RP-3 kerosene. With the equivalence ratio increasing from 0.6 to 1.6, the laminar combustion speed increases initially and then decreases gradually. The highest laminar combustion speed is measured under fuel rich condition （the equivalence ratio is 1.2）. At the same time, the Markstein length shows the same changing trend as the laminar com- bustion speed with modification of the initial pressure. Increasing the initial pressure will increase the instability of the flame front, which is established by decreased Markstein length. However, different from the effects of the initial temperature and equivalence ratio on the laminar combustion speed, increasing the equivalence ratio will lead to a decrease in the Markstein length and the stability of the flame front, and the effect of the initial temperature on the Markstein length is unclear. Further- more, the simulated laminar combustion speeds of the surrogate fuel agree with the corresponding experimental datas of RP-3 kerosene within ~10% deviation under certain conditions.

关键词： Combustion mechanism Combustion stability Laminar combustion speed Markstein length RP-3 kerosene

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