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Laser ablation ignition modes in a cavity-based supersonic combustor 认领 引用
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作者 Jianheng JI Zun CAI +4 位作者 Taiyu WANG Yifu TIAN Mingbo SUN Jiajian ZHU Zhenguo WANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2025年第4期112-126,共15页
A numerical and experimental study was conducted to investigate the Laser Ablation(LA)ignition mode in an ethylene-fueled supersonic combustor with a cavity flameholder.Theexperiments were operated under a Mach number... A numerical and experimental study was conducted to investigate the Laser Ablation(LA)ignition mode in an ethylene-fueled supersonic combustor with a cavity flameholder.Theexperiments were operated under a Mach number 2.92 supersonic inflow,with stagnation pressureof 2.4 MPa and stagnation temperature of 1600 K.Reynolds-averaged Navier-Stokes simulationswere conducted to characterize the mixing process and flow field structure.This study identifiedfour distinct LA ignition modes.Under the specified condition,laser ablation in zero and negativedefocusing states manifested two distinct ignition modes termed Laser Ablation Direct Ignition(LADI)mode and Laser Ablation Re-Ignition(LARI)mode,correspondingly.LA ignition in alocal small cavity,created by depressing the flow field regulator,could facilitate the ignition modetransforming from LARI mode to Laser Ablation Transition Ignition(LATI)mode.On the otherhand,the elevation of the flow field regulator effectively inhibited the forward propagation of theinitial flame kernel and reduced the dissipation of LA plasma,further enhancing the LADI mode.Based on these characteristics,the LADI mode was subdivided into strong(LADI-S)and weak(LADI-W)modes.Facilitating the transition of ignition modes through alterations in the local flowfield could contribute to attaining a more effective and stable LA ignition. 展开更多
关键词 Laser ablation Ignition mode Supersonic combustor Flame propagation Cavity
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Exact solutions for the transcritical Riemann problem of two-parameter fluids 认领 引用
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作者 Haotong BAI Yixin YANG +2 位作者 Wenjia XIE Dejian LI Mingbo SUN 《Applied Mathematics and Mechanics(English Edition)》 SCIE EI CSCD 2025年第12期2385-2406,共22页
Transcritical and supercritical fluids widely exist in aerospace propulsion systems,such as the coolant flow in the regenerative cooling channels of scramjet engines.To numerically simulate the coolant flow,we must ad... Transcritical and supercritical fluids widely exist in aerospace propulsion systems,such as the coolant flow in the regenerative cooling channels of scramjet engines.To numerically simulate the coolant flow,we must address the challenges in solving Riemann problems(RPs)for real fluids under complex flow conditions.In this study,an exact numerical solution for the one-dimensional RP of two-parameter fluids is developed.Due to the comprehensive resolution of fluid thermodynamics,the proposed solution framework is suitable for all forms of the two-parameter equation of state(EoS).The pressure splitting method is introduced to enable parallel calculation of RPs across multiple grid points.Theoretical analysis demonstrates the isentropic nature of weak waves in two-parameter fluids,ensuring that the same mathematical properties as ideal gas could be applied in Newton's iteration.A series of numerical cases validate the effectiveness of the proposed method.A comparative analysis is conducted on the exact Riemann solutions for the real fluid EoS,the ideal gas EoS,and the improved ideal gas EoS under supercritical and transcritical conditions.The results indicate that the improved one produces smaller errors in the calculation of momentum and energy fluxes. 展开更多
关键词 two-parameter fluid Riemann problem(RP) exact solution supercritical fluid pressure splitting transcritical fluid
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Flow structures and unsteadiness in hypersonic shock wave/turbulent boundary layer interaction subject to steady jet 认领 引用 被引量：6
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作者 Qiang Liu Wei Xie +4 位作者 Zhenbing Luo Mingbo Sun Pan Cheng Xiong Deng Yan Zhou 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2023年第12期22-35,共14页
Direct numerical simulations of Mach 6 hypersonic flow over a 34°compression corner subject to steady jet are conducted.Distributions of skin friction coefficient,wall pressure,mean velocity and temperature,bound... Direct numerical simulations of Mach 6 hypersonic flow over a 34°compression corner subject to steady jet are conducted.Distributions of skin friction coefficient,wall pressure,mean velocity and temperature,boundary layer thickness and Stanton number demonstrate that the flow changes dramatically in the shock waveurbulent boundary layer interaction area.It is found that the steady jet has no effect on suppressing flow separation unexpectedly,but increases its spatial scale instead.Instantaneous flow structures show that the turbulence amplification can be observed after the application of flow control,and abundant Görtler-like vorticities appear,but the strength of the main shock decreases.Analyzing the wall fluctuating pressure signals using weighted power spectral density,we found an interesting thing.That is,although the low-frequency oscillation phenomenon induced by separation shock is suppressed by the steady jet,wall fluctuating pressure beneath the jet shock is oscillating at a frequency lower than 0.1u∞/δref.Results of coherent and intermittency factor reveal that it is related to the backand-forth movement of the jet shock itself. 展开更多
关键词 STBLI Hypersonic flow Steady jet Direct numerical simulation Flow structure Pressure fluctuating Unsteadiness
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Review of atomization mechanism and spray characteristics of a liquid jet in supersonic crossflow 认领 引用 被引量：7
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作者 Yaozhi ZHOU Zun CAI +4 位作者 Qinglian LI Chenyang LI Mingbo SUN Peibo LI Hongbo WANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第8期1-23,共23页
The injection and atomization process of a liquid fuel jet is critical for an ignition start of a scramjet engine.Airwall-mounted crossflow injection strategy is widely used in scramjet combustors,avoiding high total ... The injection and atomization process of a liquid fuel jet is critical for an ignition start of a scramjet engine.Airwall-mounted crossflow injection strategy is widely used in scramjet combustors,avoiding high total pressure loss and allowing the liquid fuel to rapidly undergo atomization,mixing,and evaporation.In this review,research progress on a liquid jet in supersonic crossflow was evaluated from aspects of atomization mechanism and spray characteristics.When a liquid jet is injected into a supersonic crossflow,primary and secondary breakups occur successively.The surface instability of liquid can significantly affect the breakup process.This review discusses the current understanding of the breakup process and spray characteristics of a liquid jet in supersonic crossflow including the mechanism of atomization and the characteristics of distribution and atomization.The development of windward Rayleigh-Taylor(R-T)unstable waves is the main factor in column breakup.The development of Kelvin-Helmholtz(K-H)unstable waves along the circumferential direction of the jet or droplets is the main factor of surface and droplet breakups.The liquid-gas momentum ratio is the most important factor affecting the penetration depth.The span width of the liquid jet is affected by the windward area.Breakup and coalescence lead to a transformation of the size distribution of droplets from S-or C-shaped to I-shaped,and the velocity distribution of the droplets on the central symmetry plane has a mirrored S-shape.The droplet distribution on the spanwise cross-section retains a structure similar to an“Ω”shape.At last,some promising recommendations have been proposed,namely a theoretical predictive model which can describe the breakup mechanism of a liquid jet,the distribution characteristics and droplets size distribution of a liquid jet under a cavity combustion chamber,especially for enthalpy flows with complex wave structures. 展开更多
关键词 Atomization Liquid fuels Spraynozzles Supersonicflow Two phase flow
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MCGA-assisted ignition process and flame propagation of a scramjet at Mach 2.0 认领 引用 被引量：7
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作者 Tiangang LUO Jiajian ZHU +5 位作者 Mingbo SUN Rong FENG Yifu TIAN Qinyuan LI Minggang WAN Yongchao SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第7期378-387,共10页
The ignition process and flame propagation with ethylene fuel in cavity-stabilized scramjet by a Multi-Channel Gliding Arc(MCGA)at Mach 2.0 were investigated.Effects of equivalence ratios on the MCGA-assisted ignition... The ignition process and flame propagation with ethylene fuel in cavity-stabilized scramjet by a Multi-Channel Gliding Arc(MCGA)at Mach 2.0 were investigated.Effects of equivalence ratios on the MCGA-assisted ignition process and flame propagation of the scramjet were recorded by two high-speed cameras from different view angles.The discharge characteristics of MCGA are also collected synchronously with the high-speed cameras.The distributions of temperature,velocity,and equivalence ratios in non-reactive flows of the cavity were simulated by Reynolds Averaged Navier-Stokes(RANS)model.The results show that MCGA can achieve reliable ignition with the Global Equivalence Ratios(GER)between 0.06 and 0.17.The ignition process is composed of flame kernel generation,flame development,and stable combustion.The time from flame kernel generation to the establishment of global flame decreases as GER decreases from 0.17 to 0.08.In the streamwise direction,the flame first develops to the Cavity Leading Edge(CLE)because of the influence of the cavity recirculation zone and then uplifts into the cavity shear layer,and finally develops to the Cavity Trailing Edge(CTE).In the spanwise direction,the flame width is less than 50%of the width of the cavity before developing to CLE and begins to develop towards the two sides of the combustor after reaching CLE,which is affected by the angular recirculation zone on both sides of CLE.The ignition processes by MCGA in the scramjet combustor are significantly affected by local distributions of equivalence ratios and velocity in the cavity. 展开更多
关键词 Cavity Ignition process Multi-Channel Gliding Arc(MCGA) Scramjet Supersonic flow
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Mixing and combustion characteristics in a scramjet combustor with different distances between cavity and backward-facing step 认领 引用 被引量：7
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作者 Mingjiang LIU Mingbo SUN +4 位作者 Daoning YANG Guoyan ZHAO Tao TANG Bin AN Hongbo WANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第7期400-411,共12页
The mixing and combustion characteristics in a cavity flameholding combustor under inlet Mach number 2.92 are numerically investigated with ethylene injection.Dimensionless distance is defined as the ratio of the actu... The mixing and combustion characteristics in a cavity flameholding combustor under inlet Mach number 2.92 are numerically investigated with ethylene injection.Dimensionless distance is defined as the ratio of the actual distance to the height of the combustor entrance.The cavity shear-layer mode,the lifted cavity shear-layer mode,and jet wake mode with upstream separation are observed respectively with dimensionless distance equals to 1.5,4.5,and 7.5.In both non-reacting and reacting flow fields,the numerical results are essentially in agreement with the schlieren photography,flame chemiluminescence images,and wall pressure,which verify the reliability of the numerical method.The results of non-reacting flow fields show that the BackwardFacing Step(BFS)can promote the flow separation downstream at a fixed distance.The more forward the separation position is,the larger the separation zone is in the non-reacting flow field.Furthermore,the larger the separation zone is,the higher the intensity of combustion in the reacting flow field is.A reasonable distance can reduce the total pressure loss generated by the shock waves in the combustor.The flame presents remarkable three-dimensional characteristics in the reacting flow fields.When dimensionless distance equals to 4.5,there are flames near the side wall above the cavity and it is difficult for the flame stabilization in the center of the combustor,while the combustion intensity in the center of the combustor is higher than that near the side wall when dimensionless distance equals to 7.5.In the cavity flameholding combustors with a backward-facing step,the higher combustion intensity may bring much total pressure loss to the combustor.Thus,it is a good choice to achieve better thrust performance when dimensionless distance equals to 4.5 compared to the other two combustors. 展开更多
关键词 Backward-facing step Cavity Combustion Scramjet combustor Supersonic flow
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Characteristics of penetration and distribution of a liquid jet in a divergent cavity-based combustor 认领 引用 被引量：6
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作者 Yaozhi ZHOU Zun CAI +3 位作者 Qinglian LI Chenyang LI Mingbo SUN Shaotian GONG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第12期139-150,共12页
The atomization process of a liquid jet in a divergent cavity-based combustor was investigated experimentally using high-speed photography and schlieren techniques under a Mach number 2.0 supersonic crossflow.Gas-liqu... The atomization process of a liquid jet in a divergent cavity-based combustor was investigated experimentally using high-speed photography and schlieren techniques under a Mach number 2.0 supersonic crossflow.Gas-liquid flow field was studied at different divergent angles and injection schemes.It is found that complex wave structures exist in the divergent cavity-based combustor.The spray field can be divided into three distinct zones:surface wave-dominated breakup zone,rapid atomization zone and cavity mixing zone.A dimensionless spray factor is defined to describe the concentration of spray inside the cavity qualitatively.As a result,it is revealed that for the large divergent angle cavity,the injection scheme near the upstream inlet has a higher penetration depth but a lower spray distribution,where the injection scheme near the cavity has a more spray distribution.For the small divergent angle cavity,the injection scheme near the upstream inlet also has a higher penetration depth and the injection scheme near the start point of the divergent section has a more sufficient spray distribution.The small divergent angle cavity-based combustor with the upstream wall transverse injection is an optimized injection scheme to improve both penetration and spray distribution inside the cavity.Finally,a penetration depth formula is proposed to explain the spray and distribution behaviors in the divergent cavity-based combustor. 展开更多
关键词 Atomization Liquid fuels Spray nozzles Supersonic flow Two-phase flow
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Flamelet-like models applied in scramjet combustors:A state of art and prospect 认领 引用 被引量：3
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作者 Tao TANG Zhenguo WANG +4 位作者 Yuhui HUANG Mingbo SUN Hongbo WANG Guoyan ZHAO Jiangfei YU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第10期24-43,共20页
Developing supersonic combustion models with efficiency,accuracy and practicality is important foundation to deeply understand the complex combustion processes in scramjet engines.Characterized by efficiency and intui... Developing supersonic combustion models with efficiency,accuracy and practicality is important foundation to deeply understand the complex combustion processes in scramjet engines.Characterized by efficiency and intuition,the flamelet-like models are widely used models in computational combustion methods.However,the supersonic combustion flow field has the nature of strong compressibility,multiple modality,and multiple scales,which poses a great challenge to the traditional flamelet-like models with fixed boundary conditions,and then the complex chemical reaction mechanisms that may face will impose additional computational burden.In this context,this paper reviews the flamelet-like models used in scramjet engines,and summarizes prominent issues in the application practice,including modeling partially premixed combustion,defining progress variable,solving temperature efficiently,evaluating assumed Probability Density Function(PDF)models,and treating mixture fraction variance.Furthermore,possible prospects and directions of improvements are proposed and highlighted for the flamelet-like models.To fully describe the physicochemical scenario and address the raised challenges,these improvements are dedicated to dealing with the compressibility,temperature rise,time-scales,species of interest,multi-inlet combustion,the progress variable definition,and the higher Mach number flight condition. 展开更多
关键词 Combustion model Flamelet-like model Model improvements Supersonic combustion Scramjet
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Drag reduction characteristics of recirculation flow at rocket base in an RBCC engine under ramjet/scramjet mode 认领 引用 被引量：1
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作者 Menglei LI Mingbo SUN +6 位作者 Peibo LI Daoning YANG Bin AN Yizhi YAO Jikai CHEN Taiyu WANG Jiaoru WANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第3期104-115,共12页
To reduce the drag generated by the recirculation flow at the rocket base in a RocketBased Combined Cycle(RBCC)engine operating in the ramjet/scramjet mode,a novel annular rocket RBCC engine based on a central plug co... To reduce the drag generated by the recirculation flow at the rocket base in a RocketBased Combined Cycle(RBCC)engine operating in the ramjet/scramjet mode,a novel annular rocket RBCC engine based on a central plug cone was proposed.The performance loss mechanism caused by the recirculation flow at the rocket base and the influence of the plug cone configuration on the thrust performance were studied.Results indicated that the recirculation flow at the rocket base extended through the entire combustor,which creates an extensive range of the"low-kineticenergy zone"at the center and leads to an engine thrust loss.The plug cone serving as a surface structure had a restrictive effect on the internal flow of the engine,making it smoothly transit at the position of the large separation zone.The model RBCC engine could achieve a maximum thrust augmentation of 37.6%with a long plug cone that was twice diameter of the inner isolator.However,a shorter plug cone that was half diameter of the inner isolator proved less effective at reducing the recirculation flow for a supersonic flow and induced an undesirable flow fraction that diminished the thrust performance.Furthermore,the effectiveness of the plug cone increased with the flight Mach number,indicating that it could further broaden the operating speed range of the scramjet mode. 展开更多
关键词 Rocket-based combined cycle Ramjet/scramjet mode Plug cone Drag reduction k-x SST turbulent model
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Mutual effects between a gliding arc discharge and a premixed flame 认领 引用
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作者 Jiajian ZHU Le LI +2 位作者 Yifu TIAN Minggang WAN Mingbo SUN 《Plasma Science and Technology》 SCIE EI CAS CSCD 2024年第12期140-149,共10页
Mutual effects between a gliding arc(GA)discharge at atmospheric pressure and a premixed CH4/air flame were experimentally investigated.Effects of the flame on the GA were studied using simultaneous measurements of... Mutual effects between a gliding arc(GA)discharge at atmospheric pressure and a premixed CH4/air flame were experimentally investigated.Effects of the flame on the GA were studied using simultaneous measurements of the current,the voltage,and the instantaneous images of the plasma columns.The GA in the flame has a thicker and more diffusive plasma column,and it is more frequently ignited at a smaller breakdown voltage than that in the air.The GA extension velocity and the gliding velocity in the flame are larger than those in the air.The electrode voltage drop of the GA discharge in the flame is about 160 V,whereas that in the air is about 220 V.Compared with the GA in the air,the different features of the GA in the flame can be explained by high-temperature,weakly ionized,and species-abundant environment that are generated by the premixed CH4/air flame.Effects of the gliding arc discharge on the premixed flames were demonstrated using planar laser-induced fluorescence of hydroxyl radicals(OH)and formaldehyde(CH2O).OH and CH2O can be formed in the CH4/air mixture in the presence of the GA due to kinetic effects,and the increase of OH and CH2O shows the great potential of the GA for combustion enhancement. 展开更多
关键词 gliding arc premixed flame discharge characteristics plasma-assisted combustion mutual effects planar laser-induced fluorescence(PLIF)
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Effect of injection scheme on asymmetric phenomenon in rectangular and circular scramjets 认领 引用 被引量：9
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作者 Guangwei MA Mingbo SUN +3 位作者 Guoyan ZHAO Changhai LIANG Hongbo WANG Jiangfei YU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2023年第1期216-230,共15页
The asymmetric separation has a crucial effect on the performance of the scramjet.In this study,the asymmetric separation and combustion in both rectangular and circular scramjets are investigated numerically,and the ... The asymmetric separation has a crucial effect on the performance of the scramjet.In this study,the asymmetric separation and combustion in both rectangular and circular scramjets are investigated numerically,and the effect of injection scheme is analyzed.The characteristics of the flow field are analyzed based on sufficient code verification.In the rectangular scramjet,the separation tends to occur in the corner due to the corner boundary-layer effect.The separation is asym-metric and only two corners have serious separation.The fuel penetration depth in the separation zone increases and the combustion is intensified.When the injection scheme is uniform,both the combustion and separation become weak.In the circular scramjet,the separation and combustion are basically axisymmetric in the scramjet with one-row injection scheme.The asymmetric combustion becomes obvious in cases with multi-row injection scheme.When the injection orifices distribute intensively on the top and bottom sides,the strongest and weakest separations occur near these two sides respectively.When the distribution of orifices becomes uniform,the direction of separation cannot be predicted.For multi-row cases,the nonuniform injection scheme could result in violent combustion and asymmetric flow structures compared with the uniform injection scheme. 展开更多
关键词 Asymmetric phenomenon Cavity Combustion Injection scheme Scramjet Supersonic
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Scaling effects on combustion modes in a single-side expansion kerosene-fueled scramjet combustor 认领 引用 被引量：7
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作者 Fan LI Mingbo SUN +4 位作者 Jiajian ZHU Zun CAI Hongbo WANG Yanxiang ZHANG Yongchao SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第5期684-690,共7页
The combustion modes in two different scramjet combustors with the mass flow rates of 1.8 kg/s and 3.6 kg/s are experimentally investigated to explore the scaling effects on supersonic combustion with a Mach number 2.... The combustion modes in two different scramjet combustors with the mass flow rates of 1.8 kg/s and 3.6 kg/s are experimentally investigated to explore the scaling effects on supersonic combustion with a Mach number 2.0 inflow.It is found that the scramjet combustor with a larger scale can broaden the flame rich blowout limit.As the Equivalence Ratio(ER)increases,the combustion in the small-scale combustor maintains in the cavity-stabilized mode,and the flamebase moves downstream along the cavity shear layer;however,the combustion in the large-scale combustor gradually transfers from the cavity-stabilized mode to the jet-wake-stabilized mode.The differences in the cavity residence time,the ignition delay time and the Damkohler number caused by different scales of the scramjet combustor are likely to account for the scaling effects on the combustion modes. 展开更多
关键词 Cavity Combustion Combustion stabilized mode Scaling effect Scramjet Supersonic
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Effect of kerosene injection states on mixing and combustion characteristics in a cavity-based supersonic combustor 认领 引用 被引量：5
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作者 Xu LIU Peibo LI +6 位作者 Fei LI Hongbo WANG Mingbo SUN Chao WANG Yixin YANG Dapeng XIONG Yanan WANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第4期308-320,共13页
It has been found that the static pressure distribution along the axial direction of liquid kerosene is lower than that of the gaseous kerosene under the same flow condition and overall equivalent ratio from previous ... It has been found that the static pressure distribution along the axial direction of liquid kerosene is lower than that of the gaseous kerosene under the same flow condition and overall equivalent ratio from previous studies.To further investigate this phenomenon,a compressible two-phase parallel simulation method is utilized to analyze the mixing and combustion characteristics of gaseous and liquid kerosene jets in a cavity-based supersonic combustor.The numerical results are consistent with the experiments and demonstrate that gaseous injection leads to a cavity shear layer that dives deeper into the cavity,forming two recirculation zones in the front and rear of the cavity.In contrast,the cavity shear layer is closer to the mainstream during liquid injection,and only a large recirculation zone is formed in the rear of the cavity.As a result of the cavity shear layer and the recirculating flow,the fuel vapor of gaseous injection accumulates in the front of the cavity,while for the liquid injection,the fuel vapor disperses in the cavity,cavity shear layer,and the region above,and the rear of the cavity has a higher fuel vapor concentration than the front.This unique fuel distribution causes the combustion area to be concentrated in the cavity during the gaseous injection but dispersed inside and downstream of the cavity during the liquid injection.As a result,forming a thermal throat under the same conditions is more challenging during liquid injection,and the generated static pressure distribution is lower than that during the gaseous injection. 展开更多
关键词 Gaseous injection Liquid injection Mixing process Combustion Supersonic flow
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Advances and challenges in developing a stochastic model for multi-scale fluid dynamic simulation:One-dimensional turbulence 认领 引用 被引量：1
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作者 Chongpei CHEN Tianyun GAO +2 位作者 Jianhan LIANG Lin ZHANG Mingbo SUN 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第11期1-23,共23页
The modeling of turbulence,especially the high-speed compressible turbulence encountered in aerospace engineering,has always being a significant challenge in terms of balancing efficiency and accuracy.Most traditional... The modeling of turbulence,especially the high-speed compressible turbulence encountered in aerospace engineering,has always being a significant challenge in terms of balancing efficiency and accuracy.Most traditional models typically show limitations in universality,accuracy,and reliance on past experience.The stochastic multi-scale models show great potential in addressing these issues by representing turbulence across all characteristic scales in a reduced-dimensional space,maintaining sufficient accuracy while reducing computational cost.This review systematically summarizes advances in methods related to a widely used and refined stochastic multi-scale model,the One-Dimensional Turbulence(ODT).The advancements in formulations are emphasized for stand-alone incompressible ODT models,stand-alone compressible ODT models,and coupling methods.Some diagrams are also provided to facilitate more readers to understand the ODT methods.Subsequently,the significant developments and applications of stand-alone ODT models and coupling methods are introduced and critically evaluated.Despite the extensively recognized effectiveness of ODT models in low-speed turbulent flows,it is crucial to emphasize that there is still a research gap in the field of ODT coupling methods that are capable of accurately and efficiently simulating complex,three-dimensional,high-speed compressible turbulent flows up to now.Based on an analysis of the advantages and limitations of existing ODT methods,the recent advancement in the conservative compressible ODT model is considered to have provided a promising approach to tackle the modeling challenges of high-speed compressible turbulence.Therefore,this review outlines several recommended new research subjects and challenging issues to inspire further research in simulating complex,three-dimensional,high-speed compressible turbulent flows using ODT models. 展开更多
关键词 Turbulence Compressible flow Fluid dynamics Turbulence models Stochastic
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Large eddy simulation of supersonic flow in ducts with complex cross-sections 认领 引用
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作者 Huifeng Chen Mingbo Sun +3 位作者 Dapeng Xiong Yixin Yang Taiyu Wang Hongbo Wang 《Theoretical & Applied Mechanics Letters》 CAS CSCD 2023年第6期432-440,共9页
Large Eddy Simulation(LES)has been employed for the investigation of supersonic flow characteristics in five ducts with varying cross-sectional geometries.The numerical results reveal that flow channel configurations ... Large Eddy Simulation(LES)has been employed for the investigation of supersonic flow characteristics in five ducts with varying cross-sectional geometries.The numerical results reveal that flow channel configurations exert a considerable influence on the mainstream flow and the near-wall flow behavior.In contrast to straight ducts,square-to-circular and rectangular-to-circular ducts exhibit thicker boundary layers and a greater presence of vortex structures.Given the same inlet area,rectangular-to-circular ducts lead to higher flow drag force and total pressure loss than square-to-circular ducts.Characterized by the substantial flow separation and shock waves,the"S-shaped duct shows significant vertically-asymmetric characteristics. 展开更多
关键词 Scramjet LES Complex cross-section Boundary layer
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Broad phenotypic alterations and potential dysfunction of lymphocytes in individuals clinically recovered from COVID-19 认领 引用
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作者 Jingyi Yang Maohua Zhong +15 位作者 Ejuan Zhang Ke Hong Qingyu Yang Dihan Zhou Jianbo Xia Yao-Qing Chen Mingbo Sun Bali Zhao Jie Xiang Ying Liu Yang Han Mengxin Xu Xi Zhou Chaolin Huang You Shang Huimin Yan 《Journal of Molecular Cell Biology》 SCIE CAS CSCD 2021年第3期197-209,共13页
Although millions of patients have clinically recovered from COVID-19,little is known about the immune status of lymphocytes in these individuals.In this study,the peripheral blood mononuclear cells of a clinically re... Although millions of patients have clinically recovered from COVID-19,little is known about the immune status of lymphocytes in these individuals.In this study,the peripheral blood mononuclear cells of a clinically recovered(CR)cohort were comparatively analyzed with those of an age-and sex-matched healthy donor cohort.We found that CD8+T cells in the CR cohort had higher numbers of effector T cells and effector memory T cells but lower Tc1(IFN-γ+),Tc2(IL-4+),and Tc17(IL-17A+)cell frequencies.The CD4+T cells of the CR cohort were decreased in frequency,especially the central memory T cell subset.Moreover,CD4+T cells in the CR cohort showed lower programmed cell death protein 1(PD-1)expression and had lower frequencies of Th1(IFN-γ+),Th2(IL-4+),Th17(IL-17A+),and circulating follicular helper T(CXCR5+PD-1+)cells.Accordingly,the proportion of isotype-switched memory B cells(IgM−CD20hi)among B cells in the CR cohort showed a significantly lower proportion,although the level of the activation marker CD71 was elevated.For CD3−HLA-DR−lymphocytes in the CR cohort,in addition to lower levels of IFN-γ,granzyme B and T-bet,the correlation between T-bet and IFN-γ was not observed.Additionally,by taking into account the number of days after discharge,all the phenotypes associated with reduced function did not show a tendency toward recovery within 4-11 weeks.The remarkable phenotypic alterations in lymphocytes in the CR cohort suggest that severe acute respiratory syndrome coronavirus 2 infection profoundly affects lymphocytes and potentially results in dysfunction even after clinical recovery. 展开更多
关键词 COVID-19 recovered individuals lymphocyte subsets phenotypic alteration potential dysfunction
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